Learjet 45 QRH code E
February 21, 2017 | Author: renerjr | Category: N/A
Short Description
Learjet 45 aircraft QRH performance code E...
Description
Crew Checklist
E U.S. UNITS The content of this electronic collection in no way supersedes the current content outlined in the approved Airplane Flight Manual and any revisions thereto. In case of conflict, the hardcopy Airplane Flight Manual takes precedence. Revisions may be published without notice. Verification that copies are the latest version is the responsibility of the user. (Return to Welcome Screen)
CL-126B
CREW CHECKLIST & QUICK REFERENCE HANDBOOK
Copyright © 2004 by Bombardier Aerospace All rights reserved. Printed in Canada.
Subject: Learjet 45 Crew Checklist — Change 1 HIGHLIGHTS The following summary describes the changes that are incorporated with this change.
NORMAL PROCEDURES Starting Engines
Added a bleed air system check to verify proper operation of the bleed air shutoff valves.
Before Taxi
Revised procedure to match the AFM. Refer to temporary flight manual change TFM 2006-01 (Minimize AUX HYD pump run time).
Taxi & Before Takeoff
Revised APU shutdown — Unloads the APU (bleed air) before shutdown. Separated the One Engine Taxi procedure from the Taxi & Before Takeoff procedure. The One Engine Taxi procedure is moved to the back of the Normal Checklist so as not to interfere with the normal flow. Revised procedure to match the AFM. Refer to temporary flight manual change TFM 2006-01 (Minimize AUX HYD pump run time).
Runway Lineup
Revised procedure to match the AFM. Refer to temporary flight manual change TFM 2006-01 (Minimize AUX HYD pump run time).
After Takeoff
All aircraft have implemented SB 45-22-4 (Honeywell Phase III Software Upgrade). Therefore, rudder boost may remain on for all aircraft.
After Landing/Clearing Revised procedure to match the AFM. Refer to temporary flight Runway manual change TFM 2006-01 (Minimize AUX HYD pump run time). Shutdown
Revised procedure to match the AFM. Refer to temporary flight manual change TFM 2006-01 (Minimize AUX HYD pump run time). Revised APU shutdown — Unloads the APU (bleed air) before shutdown.
Quick Turn-Around
Revised APU shutdown — Unloads the APU (bleed air) before shutdown.
PERFORMANCE DATA Takeoff Distances
Change 1
CL-126B Change 1
Revised takeoff distances to include the correction for high altitude. Affects data presented for 10,000 ft pressure altitude.
Highlights-1
EMERGENCY PROCEDURES General
Updated cross-references throughout the emergency checklist.
LR GEN FAIL
Added details pertaining to the use of the clearance delivery radio. Revised presentation of battery duration table to match the AFM; no change to the technical content.
Engine Failure
Added “Obstacle Clearance Altitude” as a consideration for engineout, accelerate-go takeoff. Addressed change in logic of MSW (as it relates to the spoiler system). Refer to temporary flight manual change TFM 2005-09 (Removal of MSW input to spoiler system). Denoted first five steps (during approach) as memory items.
Aborted Takeoff
Added step referencing the AFM for further disposition.
BLEED AIR LEAK
Deleted information that attempted to locate the bleed air leak. Information was confusing and provided no value.
“OVERSPEED”
Changed “Yaw Damper — As required” to “Yaw Damper — As desired”
Ditching
Clarified the usage of flotation equipment.
REV UNSAFE
Added “Obstacle Clearance Altitude” as a consideration for engineout, accelerate-go takeoff. Addressed change in logic of MSW (as it relates to the spoiler system). Refer to temporary flight manual change TFM 2005-09 (Removal of MSW input to spoiler system).
ABNORMAL PROCEDURES General
Redistributed VLND tables. Tables are placed near abnormal landing procedures so that VLND data is available without turning pages.
AP AIL MISTRIM
Revised procedure to match the AFM. Refer to temporary flight manual change TFM 2005-06.
EMER BATT LOW
Corrected formatting error; no change to the technical content.
BLEED OVHT
Split procedure into two (one for aircraft with SB 45-72-1 and one for aircraft without SB 45-72-1). Refer to temporary flight manual change TFM 2005-11 (Nuisance CAS message associated with SB 45-72-1).
OXYGEN OFF
Corrected formatting error; no change to the technical content.
SPOILER FAIL
Editorial change (“FLIGHT group” was “FLIGHT panel”).
Landing Gear Free Fall
Added step allowing pilot’s discretion in the use of AUX HYD extension procedure.
Highlights-2
CL-126B Change 1
Main Hydraulic System Failure Landing
Added parentheses to provide clarity; no change to the technical content.
ADVISORY/STATUS ANNUNCIATIONS PRI TRIM FAULT
Updated cross-reference to PRI TRIM FAIL procedure.
WHEEL MSTR
Addressed change in logic of MSW (as it relates to the spoiler system). Refer to temporary flight manual change TFM 2005-09 (Removal of MSW input to spoiler system).
BRAKE FAULT
Deleted reference to five flight repair interval; it is the function of the MEL to provide this information.
REV FAULT
Corrected formatting error; no change to the technical content.
SUPPLEMENTAL DATA Master EICAS Index: Updated the “NO GO or MEL RELIEF” information for the following CAS messages: EMERGENCY EXIT amber CAS
Added MEL relief 52-1.
EXTERNAL DOORS amber CAS
Changed MEL relief to 52-1.
L FUEL QTY FAULT white CAS
Added MEL relief 28-4.
R FUEL QTY FAULT white CAS
Added MEL relief 28-3.
L OIL FILTER R OIL FILTER LR OIL FILTER white CAS
Changed MEL relief to N/A.
OXYGEN QTY LOW amber CAS
Changed MEL relief to N/A.
CL-126B Change 1
Highlights-3
LIST OF EFFECTIVE PAGES Use this List of Effective Pages to determine the current status of the Crew Checklist and Quick Reference Handbook. Pages affected by the current change are indicated by an asterisk (*) immediately preceding the page number.
Dates of issue for original and changed pages are: Original ............................................ O ........................................April 1998 Reissue............................................ A .............................. December 1999 Reissue............................................ B .................................. October 2004 Change .............................................1 .............................. November 2006 Page
Change
* Title ............................................... * LOEP-1 thru LOEP-6..................... * LOEP-7 (Added)............................ * LOR ............................................... i thru iv...........................................
Aircraft Affected/Effectivity Code
1 1 1 1 B
All All All All All
1 B 1 1
* N-12.1............................................ 1
All All All Aircraft 45-002 & on not modified by SB 45-11-4 Aircraft 45-002 & on modified by SB 45-11-4 All All
Normal Procedures * N-1................................................. N-2 thru N-6................................... * N-7 thru N-11................................. * N-12 ..............................................
* N-13 thru N-17............................... 1 * N-18 (Added)................................. 1 Performance Data P-1................................................. P-2................................................. P-2.1 ............................................. P-2.2.............................................. P-3................................................. P-3.1.............................................. P-3.2.............................................. P-4................................................. P-4.2.............................................. P-5................................................. P-5.1 ............................................. P-5.2.............................................. P-6................................................. P-6.2.............................................. P-7................................................. P-7.1.............................................. P-7.2..............................................
B B B B B B B B B B B B B B B B B
All
B E F B E F B F B E F B F B E F
C and D C and D C D and E C and D C D and E C and D
Denotes pages presented in either U.S. or metric units.
Change 1
LOEP-1
CL-126B October 2004 Change 1
Page
Change
P-8 ................................................. P-8.2 .............................................. P-9 ................................................. P-9.1 ............................................. P-9.2 .............................................. P-10 ............................................... P-10.2 ............................................ P-11 ............................................... P-11.1 ........................................... P-11.2 ............................................ P-12 ............................................... P-12.2 ............................................ P-13 ............................................... P-13.1 ........................................... P-13.2 ............................................ P-14 ............................................... P-14.2 ............................................ P-15 ............................................... P-15.1 ........................................... P-15.2 ............................................ P-16 ............................................... P-16.2 ............................................ P-17 ............................................... P-17.1 ........................................... P-17.2 ............................................ P-18 ............................................... P-18.2 ............................................ P-19 ............................................... P-19.1 ........................................... P-19.2 ............................................ P-20 ............................................... P-20.2 ............................................ P-21 ............................................... P-21.1 ........................................... P-21.2 ............................................ P-22 ............................................... P-22.2 ............................................ * P-23 ............................................... * P-23.1 ........................................... * P-23.2 ............................................ P-24 ............................................... P-24.2 ............................................ P-25 ............................................... P-26 ............................................... P-26.1 ........................................... P-26.2 ............................................
B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B 1 1 1 B B B B B B
Aircraft Affected/Effectivity Code
B F B E F B F B E F B F B E F B F B E F B F B E F B F B E F B F B E F B F B E F B F
C D and E C and D C D and E C and D C D and E C and D C D and E C and D C D and E C and D C D and E C and D C D and E C and D C D and E C and D C D and E
All
B C and D E F
Denotes pages presented in either U.S. or metric units. CL-126B October 2004 Change 1
LOEP-2
Page
Change
P-27............................................... P-27.1 ........................................... P-27.2............................................ P-28............................................... P-28.2............................................ P-29............................................... P-29.1 ........................................... P-29.2............................................ P-30............................................... P-30.2............................................ P-31............................................... P-31.1 ........................................... P-31.2............................................ P-32............................................... P-32.2............................................ P-33............................................... P-33.1 ........................................... P-33.2............................................ P-34............................................... P-34.2............................................ P-35............................................... P-35.1 ........................................... P-35.2............................................ P-36............................................... P-36.2............................................ P-37............................................... P-37.1 ........................................... P-37.2............................................ P-38............................................... P-38.2............................................ P-39............................................... P-39.1 ........................................... P-39.2............................................ P-40............................................... P-40.2............................................ P-41............................................... P-41.2............................................ P-42............................................... P-42.2............................................ P-43............................................... P-43.2............................................ P-44............................................... P-44.2............................................ P-45............................................... P-45.2............................................ P-46............................................... P-46.2............................................
B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B
Aircraft Affected/Effectivity Code
B E F B F B E F B F B E F B F B E F B F B E F B F B E F B F B E F B F B F B F B F B F B F B F
C and D C D and E C and D C D and E C and D C D and E C and D C D and E C and D C D and E C and D C D and E C and D C D and E C D and E C D and E C D and E C D and E C D and E C D and E
Denotes pages presented in either U.S. or metric units.
LOEP-3
CL-126B October 2004 Change 1
Page
Change
P-47 ............................................... B P-47.2 ............................................ B P-48 ............................................... B P-48.2 ............................................ B P-49 ............................................... B P-49.2 ............................................ B P-50 ............................................... B P-51 ............................................... B P-51.2 ............................................ B P-52 ............................................... B P-52.2 ............................................ B P-53 ............................................... B P-53.2 ............................................ B P-54 ............................................... B P-54.2 ............................................ B P-55 ............................................... B P-55.2 ............................................ B P-56 ............................................... B P-56.2 ............................................ B P-57 ............................................... B P-57.2 ............................................ B P-58 ............................................... B P-59 ............................................... B P-59.2 ............................................ B P-60 ............................................... B P-60.2 ............................................ B P-61 ............................................... B P-61.2 ............................................ B P-62 ............................................... B P-62.2 ............................................ B P-63 ............................................... B P-63.2 ............................................ B P-64 ............................................... B P-64.2 ............................................ B P-65 ............................................... B P-65.2 ............................................ B P-66 ............................................... B P-67 ............................................... B P-67.2 ............................................ B P-68 ............................................... B P-68.2 ............................................ B P-69 ............................................... B P-69.2 ............................................ B P-70 ............................................... B P-70.2 ............................................ B P-71 ............................................... B P-71.2 ............................................ B
Aircraft Affected/Effectivity Code
B C D and E F B C D and E F B C D and E F All
B F B F B F B F B F B F B F
C D and E C D and E C D and E C D and E C D and E C D and E C D and E
All
B F B F B F B F B F B F B F
C D and E C D and E C D and E C D and E C D and E C D and E C D and E
All
B F B F B F B F B F
C D and E C D and E C D and E C D and E C D and E
Denotes pages presented in either U.S. or metric units. CL-126B October 2004 Change 1
LOEP-4
Page
Change
P-72............................................... P-72.2............................................ P-73............................................... P-73.2............................................ P-74 .............................................. P-75............................................... P-76............................................... P-77............................................... P-78............................................... P-78.2............................................ P-79 thru P-89 ...............................
B B B B B B B B B B B
Aircraft Affected/Effectivity Code
B C D and E F B C D and E F All All All All
B C D and E F All
Emergency Procedures E-i and E-ii..................................... B E-1 thru E-8 ................................... B * E-9 and E-10 ..................................1 E-11 thru E-14 ............................... B * E-15 thru E-17 ................................1 E-18............................................... B * E-19................................................1 E-20............................................... B E-20.1............................................ B * E-21................................................1 * E-21.1.............................................1 E-22............................................... B E-22.1............................................ B E-23............................................... B E-24............................................... B E-24.1............................................ B E-25 thru E-27 ............................... B * E-28................................................1 E-29 .............................................. B * E-30 thru E-32 ................................1
All All All All All All All Aircraft 45-002 thru 45-225 modified by SB 45-55-6 Aircraft 45-226 & on, and prior craft modified by SB 45-55-6 Aircraft 45-002 thru 45-225 modified by SB 45-55-6 Aircraft 45-226 & on, and prior craft modified by SB 45-55-6 Aircraft 45-002 thru 45-225 modified by SB 45-55-6 Aircraft 45-226 & on, and prior craft modified by SB 45-55-6 All Aircraft 45-002 thru 45-225 modified by SB 45-55-6 Aircraft 45-226 & on, and prior craft modified by SB 45-55-6 All All All All
not airnot airnot air-
not air-
Abnormal Procedures A-i thru A-iv.................................... B A-1 thru A-6 ................................... B * A-7................................................. 1
All All All
Denotes pages presented in either U.S. or metric units.
LOEP-5
CL-126B October 2004 Change 1
Page
Change
Aircraft Affected/Effectivity Code
A-8 thru A-12 ................................ B * A-13 ............................................... 1 A-14 .............................................. B * A-15 ............................................... 1 A-16 thru A-27 ............................... B * A-28 ............................................... 1 * A-28.1 (Added) .............................. 1 * A-28A (Added) ............................... 1 A-29 thru A-32 ............................... B * A-33 ............................................... 1 A-34 thru A-36 ............................... B * A-37 ............................................... 1 A-38 thru A-48 ............................... B A-49 ............................................... B A-49.1 ............................................ B A-50 thru A-52 ............................... B A-53 ............................................... B A-53.1 ............................................ B A-54 and A-55................................ B A-56 and A-57................................ B A-56.1 and A-57.1.......................... B A-58 thru A-60 ............................... B A-61 and A-62................................ B A-61.1 and A-62.1.......................... B A-63 .............................................. B A-64 ............................................... B A-64.1 ............................................ B A-65 thru A-67 ............................... * A-68 ............................................... * A-69 ............................................... * A-70 ............................................... * A-71 ............................................... * A-72 ...............................................
B 1 1 1 1 1
All All All All All Aircraft 45-002 & on not modified by SB 45-72-1 Aircraft 45-002 & on modified by SB 45-72-1 Aircraft 45-002 & on modified by SB 45-72-1 All All All All All Aircraft 45-002 & on not modified by SB 45-55-6 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 All Aircraft 45-002 & on not modified by SB 45-55-6 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 All Aircraft 45-002 & on not modified by SB 45-55-6 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 All Aircraft 45-002 & on not modified by SB 45-55-6 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 All Aircraft 45-002 & on not modified by SB 45-55-6 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 All All All All All All
Denotes pages presented in either U.S. or metric units. CL-126B October 2004 Change 1
LOEP-6
Page
Change
* A-73 and A-74 ............................... * A-75............................................... A-76............................................... * A-77............................................... A-78............................................... * A-79 and A-80 ............................... A-81 and A-82 ............................... A-83...............................................
1 1 B 1 B 1 B B
Aircraft Affected
All All All All All All All All
Advisory/Status A/S-i and A/S-ii .............................. A/S-1 thru A/S-13 .......................... * A/S-14 and A/S-15 ........................ A/S-16 thru A/S-23 ........................ * A/S-24 and A/S-25 ........................ A/S-26 ...........................................
B B 1 B 1 B
All All All All All All
Supplemental Data S-1 thru S-5 ................................... B S-6................................................. B
S-6.1.............................................. B
S-7................................................. B
S-7.1.............................................. B
S-8 thru S-25 ................................. * S-26 thru S-28 ............................... S-29............................................... * S-30............................................... S-31 and S-32 ...............................
B 1 B 1 B
All Aircraft 45-002 thru 45-169 without Altitude Compensated Oxygen System Aircraft 45-170 & on, and prior aircraft with Altitude Compensated Oxygen System Aircraft 45-002 thru 45-169 without Altitude Compensated Oxygen System Aircraft 45-170 & on, and prior aircraft with Altitude Compensated Oxygen System All All All All All
Denotes pages presented in either U.S. or metric units.
LOEP-7
CL-126B October 2004 Change 1
LOG OF REVISIONS REVISION NO.
DESCRIPTION
Reissue B October 2004
Harmonizes with Reissue of the AFM dated 5-19-2004.
Change 1 November 2006
Harmonizes with Change 1 of the AFM dated 8-24-2006.
CL-126B October 2004 Change 1
INCORPORATED BY
DATE
LOR
IMPORTANT TO THE OWNER OF THIS CHECKLIST
A yearly checklist revision service is available. The cost of revision service will be billed at current pricing levels. If you wish to receive the checklist revision service, please fill in the blanks below and mail to the address at the bottom of the page.
AIRCRAFT SERIAL NUMBER
MAILING ADDRESS FOR REVISION SERVICE:
YOUR NAME: MAILING ADDRESS:
BUSINESS PHONE NO: FAX NO:
MAIL THIS TO:
Learjet Inc. P.O. Box 7707 Wichita, Kansas 67277-7707 Attn: Document Control MS#71
TECHNICAL PUBLICATION SQUAWK SHEET We are constantly striving to make our publications more usable in the field. In order to do this, we need your comments, criticism, and suggestions concerning any Learjet aircraft publication. The action taken on your Squawk Sheet will be noted below and a copy will be returned to you. Be sure that your correct mailing address and business phone number are provided. Manager Technical Publications Learjet, Inc. PLEASE FURNISH THE FOLLOWING: CHECKLIST PROCEDURE: A/C SERIAL NO.:
PAGE NO.:
YOUR NAME: MAILING ADDRESS:
PHONE NO.:
FAX NO.:
E-MAIL ADDRESS: COMMENTS:
Briefly describe any errors encountered or suggestions for additional coverage.
Action Taken:
MAIL THIS TO:
CL-126B
Learjet Inc. P.O. Box 7707 Wichita, Kansas 67277-7707 Attn: Manager Technical Publications MS#53
IMPORTANT NOTICE Applicability: This checklist is applicable to Learjet 45 aircraft serial number 45-002 thru 45-2000. Use of Checklist: These are suggested procedures only and in no way supersede current procedures outlined in the FAA Approved Airplane Flight Manual and any revisions thereto. In the event of conflict, the FAA Approved Airplane Flight Manual takes precedence. This checklist has been designed so that pages not applicable to a particular aircraft may be removed from the checklist. Removing such pages allows the operator to construct a checklist applicable to a particular aircraft. Each text page of this checklist contains an effectivity block with serializations or effectivity codes located at the bottom of the page. To remove pages not applicable to your aircraft, examine the effectivity block to determine if the page is applicable to your aircraft. If the page is not applicable, remove the page from the checklist and discard. If the page is applicable, retain the page. The performance effectivity codes used in this checklist are identical to the effectivity codes used in the basic airplane flight manual. For an explanation of the effectivity codes, refer to FLIGHT MANUAL PERFORMANCE DATA in the AFM introduction.
NOTE Be sure to examine each page of the checklist to ensure that all pages not applicable to your aircraft are removed.
CL-126B October 2004
i
CHECKLIST CONVENTIONS EICAS (Engine Indicating/Crew Alerting System) EICAS indications will be presented by all capital letters within their appropriate display fields.
CAS
EI
System Page System Page Menu EICAS Display
Switch Indications Normal switch condition will be assumed not illuminated on the “quiet-darknormal” instrument panel and pedestal. “Quiet-dark-normal” is defined as day, VMC normal system operation in cruise flight. Switch legends will be presented in all capital letters (e.g. PACK Switch). Illuminated switch indications will be also be noted in all capital letters (e.g. PACK ... OFF). Switch conditions that are not illuminated will be lead capped (e.g. PACK ... On), unless they are part of a longer description.
Voice
and Crew Warning Panel (CWP) Annunciations
Voice annunciations will be preceded by an audio symbol (headings only) and in all capital letters within quotes. CWP annunciations will be presented by all capital letters and are usually accompanied by a CAS.
Symbols and “If” Statements Checklist items marked with this symbol (◆) may be used for preflight during intermediate stops where both engines are shut down provided certain criteria are met. The symbol applies thru the Before Starting Engines checklist. Refer to Section II Introduction in the FAA Approved Airplane Flight Manual for list of criteria.
ii
CL-126B October 2004
Symbols and “If” Statements (Cont) Certain procedures are dependent on prescribed conditions. These conditions are presented in bold as independent “If” statements. “If” statements preceded by a symbol (e.g. ● , ■ or S) indicate more than one condition for that step. Other conditions for that step will be indicated by repeating that step and symbol. Procedures completed at any substep level will be noted. (e.g. This checklist is complete.) Procedures not completed at a substep level will direct the user to the next applicable step. (e.g. Go to step 3.) The last procedure of any substep will either state “This checklist is complete.” or “Go to step #.”, or refer the user to another appropriate procedure. Circuit Breakers Many procedures involve manipulating circuit breakers. The following criteria should be followed during “Circuit Breaker” steps. -
-
Circuit breakers that are “Set” should be checked for that normal condition. If the circuit breaker is not “Set”, it may be reset only once. If the circuit breaker opens again, do not reset. Circuit breakers that “Pull” should only be pulled and not reset. Circuit breakers that “Pull and Reset” should be pulled, delayed for several seconds, and reset only once.
Allow sufficient cooling time for circuit breakers that are “Reset” or cycled through a “Pull and Reset.”
CL-126B October 2004
iii
CREW NOTES
iv
CL-126B October 2004
NORMAL PROCEDURES CONTENTS Exterior Preflight......................................................................... N-2 Cabin Preflight............................................................................ N-5 Before Starting Engines ............................................................. N-5 Starting Engines......................................................................... N-7 Before Taxi ................................................................................. N-8 Taxi & Before Takeoff ................................................................. N-9 Runway Lineup........................................................................... N-10 After Takeoff ............................................................................... N-10 Climb .......................................................................................... N-11 Cruise......................................................................................... N-11 Descent ...................................................................................... N-11 Approach.................................................................................... N-12 Before Landing ........................................................................... N-13 Go Around.................................................................................. N-13 Landing ...................................................................................... N-13 After Landing/Clearing Runway.................................................. N-14 Shutdown ................................................................................... N-15 Quick Turn-Around .................................................................... N-15 One Engine Taxi......................................................................... N-17
Change 1
CL-126B October 2004 Change 1
EFFECTIVITY ALL
N-1
Exterior Preflight ◆
During Exterior Preflight, check all vents clear, check access doors for security, & all aircraft surfaces for condition. 5
1
4
6
2
3
22
7 8
21
12 20
19
9 18
11
16
10
13
17
14
16
15
1
Left Pitot-Static Probe, Stall Vane & Ice Detect Probe............Check
2
Right & Standby Pitot-Static Probes, Stall Vane, & Static Air Temperature Probe ............................Check
3 ◆ Controls Lock .......................................................... Remove & Stow Gear ............................................................................................DN L & R BATT ................................................................................. On (Procedure Continued) EFFECTIVITY
N-2
ALL
CL-126B October 2004
EMER BATT ...........................................................................EMER APU MASTER (if installed) ..........................................................ON Fuel Quantities ....................................................................... Check AUX HYD.....................................................................................ON SUMRY Page B-ACUM Pressure.............................. 2610-3600 psi AUX HYD..................................................................................... Off EMERGENCY/PARKING BRAKE ...............................................Set SUMRY Page B-ACUM Pressure.................................... ≥ 1200 psi AUX HYD.....................................................................................ON AUX HYD..................................................................................... Off Exterior Lights........................................................................ Check 12
FILTER & RESERVOIR Lights (MAIN, AUX, ADD or OVER) (Hyd Service Pnl) ...................................... Not Illuminated & Secure
14
APU (if installed) ..................................................... Check Oil Level
3
APU MASTER (if installed) .......................................................... Off EMER BATT .............................................................................. OFF L & R BATT................................................................................OFF
4
Windshield .............................................................................. Check Nose Gear Strut....... Extended a minimum of one-half inch (13mm) ◆ Gear & Wheel Well, Nose Compartment Doors, Wheel & Tire ........................................................................... Check Ground Wire ............................................................... Disconnected
5
Radome & Radome Erosion Shoe .................................... Condition
6
Windshield, Oxygen Discharge Disc & Service Door, Nose Compartment Doors, Wing Inspection Light & Lens, Standby Pitot & Static Drains ............ Check & Secure
7
◆ Emergency Exit, Upper Antennas & Dorsal Inlets, Upper Gravity Fueling Door, Right Engine Inlet & Fan, Right Generator & Alternator Scoops, Lower Antennas, Landing Light Fairing & Lens Condition, Fuel Drains & Access Door, Toilet Servicing Door, Right Main Gear ..................................................................... Check Oxygen Servicing Door (if applicable) ...................................Secure (Procedure Continued)
CL-126B October 2004
EFFECTIVITY ALL
N-3
8
Right Wing ..............................................................................Check
9
Right Nav Light/Lens & Static Wicks..................................Condition Ground Wire ............................................................... Disconnected
10
Right Aileron, Spoiler & Flap..............................................Condition
11
Right Brakes & Brake Wear Indicators ..............................Condition Right Engine Oil ............................................................ Check Level
12 ◆ Single-Point Fueling & Fuel Quantity Panel Access Doors... Secure 13 ◆ Right Engine Exhaust ............................................................. Clear ◆ Right Thrust Reverser.................... Condition & Completely Stowed 14
Tailcone Interior, Engine Fire Extinguisher Discs, Right VOR/LOC Antenna, APU Exhaust (if installed) .............. Clear
15 ◆ Vertical Stabilizer, Rudder, Horizontal Stabilizer, Elevator, Delta Fins & Logo Lights (if installed), Static Wicks, Beacon/Strobe Light & Lens ..............................Check ◆ Tailstand............................................................................ Removed 16
Battery Vents, APU Inlet (if installed) ....................................... Clear Left VOR/LOC Antenna .....................................................Condition ◆ Baggage Heat, Baggage Door............... On (if applicable) & Closed
17 ◆ Left Engine Exhaust ................................................................ Clear ◆ Left Thrust Reverser ...................... Condition & Completely Stowed 18
Left Engine Oil .............................................................. Check Level Left Brakes & Brake Wear Indicators.................................Condition
19
Left Spoiler, Flap & Aileron......................................................Check
20
Left Nav Light/Lens & Static Wicks ....................................Condition Ground Wire ............................................................... Disconnected
21
Left Wing.................................................................................Check
22 ◆ Fuel Drains & Access Door, .................................... Drain & Secure Left Main Gear, Left Engine Inlet & Fan, Left Generator & Alternator Scoops, Upper Fuselage, Fuel Vent Inlet................ Clear Oxygen System Discharge Indicator (if applicable) ................Check EFFECTIVITY
N-4
ALL
CL-126B October 2004
Cabin Preflight ◆ 1. Cabin Furnishings ................................................................ Secure ◆ 2. Emergency Exit ......................... Aisle Clear/Security Pin Removed ◆ 3. Lavatory Door .................................. Open & Access Unobstructed
Before Starting Engines All switches not illuminated, except as noted. ◆ 1. Seats, Safety Belts, & Shoulder Harnesses ........... Secure & Adjust 2. Crew Oxygen Masks & Smoke Goggles ................................ Check 3. L & R Circuit Breakers .................................................................Set ◆ 4. Gear............................................................................................. DN ◆ 5. Electrical System: a.
L & R BATT ................................................. On, Simultaneously
b.
EMER BATT.....................................................................EMER
c.
L & R AV MSTR ................................. On (OFF for BATT starts)
d.
L & R NON-ESS.................... As Desired (OFF for BATT starts)
e.
L & R GEN .......................................................................... OFF
f.
EXT PWR (if desired)..............Connect, AVAIL, then EXT PWR
g.
APU (if installed) ...................................................... As Desired (1) BCN/STROBE............................................................. BCN (2) APU MASTER................................................................ON (3) FIRE DET.................................................................. Check (4) APU START/STOP...................................................START (5) EXT PWR (if applicable) ..................AVAIL and Disconnect (6) APU GEN .......................................................................ON (7) APU BLEED ...................................................................ON (8) PACK..............................................................................ON
h.
BUS-TIE .............................Closed for EXT PWR or APU Starts (Open for BATT starts) 6. L & R CREW LIGHTS..................................................................Set 7. L & R Audio Panels .....................................................................Set (Procedure Continued) CL-126B October 2004
EFFECTIVITY ALL
N-5
8. L & R Rudder Pedals .............................................................. Adjust 9. ELEV DISC Handle & ROLL DISC Lever ..................Check Stowed 10. Flight Controls.........................................................................Check 11. LTS............................................................................................. Test 12. DU & REVERSION Panels .................................................... NORM ◆ 13. EICAS .....................................................................................Check EIs, Fuel Quantity, CAS, & SUMRY Page. a.
Fuel TOTALIZER RESET (FUEL Page) ............................. Zero
14. ANTI-ICE Panel: a.
L & R PROBES, L & R WSHLD ..........................................OFF
15. Aircraft Lighting ............................................................................ Off ◆ 16. GEAR/HYD Panel: a.
AUX HYD ............................................................................. ON
b.
SUMRY Page B-ACUM Pressure ....................... 2610-3600 psi
c.
EMERGENCY/PARKING BRAKE ........................................ Set
d.
AUX HYD .............................................................................. Off
17. PAX OXYGEN/PRESSURIZATION Panels ........................Checked ◆
a.
PACK...................................... OFF (On, if APU BLEED — ON)
b.
LDG ALT............................................................ Set Destination
18. ENVIRONMENTAL CONTROL Panel ...................... Checked & Set ◆ 19. RUD BOOST ............................................................................... On 20. SYSTEM TEST Panel................................................................ Test ◆
a.
FIRE DET ........ Check, Unless Accomplished During APU Start
If EXT PWR or APU is not used, start one engine & continue checks with the following switches On: • L or R GEN .................................................................................. On • L & R AV MSTR ........................................................................... On b.
GEAR, FLAPS, ADC, STALL, ANTI-ICE, GPWS .............Check
21. Master CAUT .......................................................................... Inhibit 22. Trim System ............................................................................Check ◆ 23. FUEL Panel ............................................................................Check (Procedure Continued) EFFECTIVITY
N-6
ALL
CL-126B October 2004
24. L & R ENGINE Panels: a.
L & R ENG CMPTR...............................................................ON
b.
ENG SYNC ......................................................................... OFF
◆ 25. Altimeters.............................................. Set Pilot, Copilot & Standby ◆ 26. Standby Instruments........................................ Uncaged & Checked ◆ 27. FMS .............................................................................................Set ◆ 28. Takeoff Data (V1, VR, V2, TO Pitch, Distance) ................. Computed & Speeds Set ◆ 29. Avionics .......................................................................................Set
Starting Engines 1. Cabin Door ...........................................................Closed & Latched 2. SUMRY Page ELEC VOLTS ................................................... Check - Ni-Cad — 23 VDC or Lead Acid — 24 VDC Minimum 3. BCN/STROBE .......................................................................... BCN 4. EMERGENCY/PARKING BRAKE................................................Set 5. Thrust Lever(s) ......................................................................... IDLE 6. Engine ...................................................................................... Start 7. Engine Instruments................................................................. Check 8. SUMRY Page HYD - MAIN Pressure ........................ 2210-3600 psi 9. Other Engine ........................................................................... Start 10. EMER LIGHTS ..... ON, Check EMER Lights Illuminated, then ARM 11. EXT PWR (if applicable) ................................... AVAIL & Disconnect 12. PACK ......................................................................................... OFF 13. Anti-Ice System ..............................................Check & As Required 14. APU BLEED (if installed) ............................................................. Off 15. PACK ........................................................................................... On 16. Bleed Air System (first flight of day)........................................ Check 17. APU BLEED (if installed) .............................................. As Required 18. EMER PRESS ....................................................................... Check CL-126B October 2004 Change 1
EFFECTIVITY ALL
N-7
Change 1
Before Taxi 1. Circuit Breakers .......................................................................... Set 2. VOLTS & AMPS ......................................................................Check 3. Manual Mode Governor ......................................................Checked 4. L & R WSHLD .............................................................................. On 5. Spoilers ...................................................................................Check a.
SPOILER.......................... EXT, Check Equal Rate & Extension
b.
SPOILER............................................... ARM, Check Retracted
6. FLAPS ........................................................................ Set 8° or 20° 7. Flight Controls.........................................................................Check a.
Rudder Boost ................................................... Verify Green RB
8. EICAS .....................................................................................Check 9. Passengers Briefed/Cabin Check ..................................... Complete 10. Aircraft Lighting ...................................................... On, As Required 11. NO SMOKING BELTS ................................................................. On 12. NOSE STEER............................................................................. ON 13. SUMRY Page B-ACUM Pressure .............................. 2610-3600 psi 14. EMERGENCY/PARKING BRAKE........................................Release
EFFECTIVITY
N-8
ALL
CL-126B October 2004 Change 1
Change 1
Taxi & Before Takeoff 1. Brakes & Nose Wheel Steering .............................................. Check 2. Flight Instruments ............................................................... Checked 3. Thrust Reversers .................................................................... Check 4. Engine Instruments & N1 Bugs............................................... Check 5. Takeoff Data (V1, VR, V2, TO Pitch, Distance) ........................ Check 6. Nav Equipment ....................................................................... Check 7. FLAPS ................................................... 8° or 20°, Check Indication 8. Trims ............................................... Set PIT, AIL, & RUD for Takeoff 9. Crew Takeoff Briefing.........................................................Complete 10. HI FLOW...................................................................................... Off 11. Radar............................................................................ As Required 12. Anti-Ice Systems: a.
WING/STAB, L & R NAC ........................................ As Required
13. APU (if installed) ..............................................................Shut Down a.
APU BLEED .......................................................................... Off
b.
APU START/STOP................................................................ Off
c.
APU MASTER (after 30-second delay)................................. Off
d.
FMS Fuel Quantity ......................................................... Update
Takeoff Pitch Trim Setting 1 to 10 8.7
CL-126B October 2004 Change 1
CENTER-OF-GRAVITY — % MAC 12 14 16 18 20 8.1 7.6 7.0 6.4 5.9
22 to aft limit 5.3
EFFECTIVITY ALL
N-9
Runway Lineup 1. Transponder ............................................................................TA/RA 2. L & R PROBES ............................................................................ On 3. RECOG, L & R LDG-TAXI Lights ................................................. On 4. BCN/STROBE.................................................................... STROBE 5. AUX HYD ................................................................................... ON 6. APR ..........................................................................................ARM 7. EICAS/SUMRY or FLT Page...................................................Check
After Takeoff 1. Gear ............................................................................................ UP 2. FLAPS ........................................................................UP at V2 + 25 3. Yaw Damper.................................................................. As Required 4. SPOILER ...................................................................................RET 5. Anti-Ice Systems ........................................................... As Required a.
Thrust Levers .................................................................. ≤ MCT
b.
WING/STAB ......................................................................... ON
c.
L & R NAC ........................................................................... ON
6. L & R LDG-TAXI Lights ..............................................................OFF 7. L & R IGN .................................................................................... Off 8. APR ............................................................................................. Off
EFFECTIVITY
N-10
ALL
CL-126B October 2004 Change 1
Change 1
Climb 10,000 Ft Checks: 1. NO SMOKING BELTS .................................................. As Required 2. Pressurization......................................................... Check & Normal Transition Altitude (or 18,000 Ft) Checks: 3. Altimeters (x3) ..................................... Set to 29.92" Hg (1013 hPa) 4. RECOG Light............................................................................. OFF 5. Oxygen System .................................................................. Checked
Cruise (As Required By Regulation) 1. Pressurization......................................................... Check & Normal 2. Fuel Management......................................................... As Required 3. Engine Instruments................................................................. Check 4. Other Systems...................................................................... Monitor
Descent 1. Pressurization.............................................................. LDG ALT Set 2. Anti-Ice Systems........................................................... As Required a.
Thrust Levers .................................................................. ≤ MCT
b.
WING/STAB ..........................................................................ON
c.
L & R NAC.............................................................................ON
Transition Level (or FL 180) Checks: 3. Altimeters (x3) .............................................................................Set 4. RECOG Light............................................................................... On 5. Passengers Briefed/Cabin Check ......................................Complete 6. NO SMOKING BELTS ................................................................. On 7. Fuel Quantities & Balance ...................................................... Check
CL-126B October 2004 Change 1
EFFECTIVITY ALL
N-11 N-12
Approach 1. Landing Data (VREF, VAPP, Distance)......... Computed & Speeds Set 2. Approach Setup & Crew Briefing ...................................... Complete 3. HI FLOW ...................................................................................... Off 4. ENG SYNC ................................................................................OFF
Landing Speeds Below 4000 Feet WEIGHT — 1000 LB 17 18 19 19.2
SPEED
14
15
16
VREF
106
110
113
116
119
122
VAPP
115
119
122
125
129
132
20
20.5
123
125
126
132
134
136
°F °C WT — LB
-4 -20
14 -10
SEA LEVEL
19,200 19,000 18,000 17,000 16,000 15,000 14,000
2410 2390 2310 2230 2160 2080 2000
2480 2460 2380 2290 2220 2140 2050
2550 2530 2440 2350 2270 2190 2100
2620 2600 2510 2410 2320 2240 2150
2700 2680 2580 2470 2380 2290 2200
2770 2750 2650 2540 2430 2340 2240
2840 2820 2710 2600 2490 2400 2290
2000 ft
19,200 19,000 18,000 17,000 16,000 15,000 14,000
2550 2530 2440 2350 2270 2190 2100
2630 2610 2520 2420 2330 2250 2150
2710 2690 2590 2480 2390 2300 2200
2790 2760 2660 2550 2450 2360 2260
2870 2840 2730 2620 2510 2410 2310
2950 2920 2810 2690 2570 2470 2360
3030 3000 2880 2760 2640 2520 2410
4000 ft
Landing Distances
19,200 19,000 18,000 17,000 16,000 15,000 14,000
2710 2690 2590 2490 2390 2310 2210
2800 2770 2670 2560 2460 2370 2270
2880 2860 2750 2640 2520 2430 2320
2970 2950 2830 2710 2590 2490 2380
3060 3030 2910 2790 2660 2550 2440
3150 3120 2990 2860 2730 2610 2490
3240 3210 3080 2940 2800 2670 2550
TEMP
32 50 68 86 0 10 20 30 LANDING DISTANCE — FEET
104 40
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
N-12 N-13
EFFECTIVITY EFFECTIVITY 45-002 & on ALL not modified by SB 45-11-4
CL-126B October 2004 Change 1
Climb 10,000 Ft Checks: 1. NO SMOKING BELTS .................................................. As Required 2. Pressurization......................................................... Check & Normal Transition Altitude (or 18,000 Ft) Checks: 3. Altimeters (x3) ..................................... Set to 29.92" Hg (1013 hPa) 4. RECOG Light............................................................................. OFF 5. Oxygen System .................................................................. Checked
Cruise (As Required By Regulation) 1. Pressurization......................................................... Check & Normal 2. Fuel Management......................................................... As Required 3. Engine Instruments................................................................. Check 4. Other Systems...................................................................... Monitor
Descent 1. Pressurization.............................................................. LDG ALT Set 2. Anti-Ice Systems........................................................... As Required a.
Thrust Levers .................................................................. ≤ MCT
b.
WING/STAB ..........................................................................ON
c.
L & R NAC.............................................................................ON
Transition Level (or FL 180) Checks: 3. Altimeters (x3) .............................................................................Set 4. RECOG Light............................................................................... On 5. Passengers Briefed/Cabin Check ......................................Complete 6. NO SMOKING BELTS ................................................................. On 7. Fuel Quantities & Balance ...................................................... Check
CL-126B October 2004 Change 1
EFFECTIVITY ALL
N-11 N-12
Approach 1. Landing Data (VREF, VAPP, Distance)......... Computed & Speeds Set 2. Approach Setup & Crew Briefing ...................................... Complete 3. HI FLOW ...................................................................................... Off 4. ENG SYNC ................................................................................OFF
Landing Speeds Below 4000 Feet SPEED
14
15
16
WEIGHT — 1000 LB 17 18 19 19.2
20
21
21.5
VREF
106
110
113
116
119
122
123
125
127
128
VAPP
115
119
122
125
129
132
132
134
137
138
°F °C WT — LB
-4 -20
14 -10
SEA LEVEL
19,200 19,000 18,000 17,000 16,000 15,000 14,000
2410 2390 2310 2230 2160 2080 2000
2480 2460 2380 2290 2220 2140 2050
2550 2530 2440 2350 2270 2190 2100
2620 2600 2510 2410 2320 2240 2150
2700 2680 2580 2470 2380 2290 2200
2770 2750 2650 2540 2430 2340 2240
2840 2820 2710 2600 2490 2400 2290
2000 ft
19,200 19,000 18,000 17,000 16,000 15,000 14,000
2550 2530 2440 2350 2270 2190 2100
2630 2610 2520 2420 2330 2250 2150
2710 2690 2590 2480 2390 2300 2200
2790 2760 2660 2550 2450 2360 2260
2870 2840 2730 2620 2510 2410 2310
2950 2920 2810 2690 2570 2470 2360
3030 3000 2880 2760 2640 2520 2410
4000 ft
Landing Distances
19,200 19,000 18,000 17,000 16,000 15,000 14,000
2710 2690 2590 2490 2390 2310 2210
2800 2770 2670 2560 2460 2370 2270
2880 2860 2750 2640 2520 2430 2320
2970 2950 2830 2710 2590 2490 2380
3060 3030 2910 2790 2660 2550 2440
3150 3120 2990 2860 2730 2610 2490
3240 3210 3080 2940 2800 2670 2550
TEMP
32 50 68 86 0 10 20 30 LANDING DISTANCE — FEET
104 40
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
N-12.1 N-13.1
EFFECTIVITY EFFECTIVITY 45-002 & on ALL modified by SB 45-11-4
CL-126B October 2004 Change 1
Before Landing 1. SPOILER .................................................................................. ARM 2. FLAPS ............................................................................... 8° or 20° 3. AUX HYD.....................................................................................ON 4. Gear ............................................................................................ DN 5. L & R LDG-TAXI Lights ........................................... On As Required 6. FLAPS ........................................................... DN, Check Indication 7. EICAS/SUMRY or FLT Page................................................... Check
Go Around 1. Autopilot......................................................................... Disengaged 2. Thrust Lever(s) .................................................. T/O or As Required 3. FLAPS ..........................................................................................8° 4. Gear............................................................................................. UP 5. Climb at VAPP. 6. When clear of obstacles, accelerate to VAPP + 20 & retract flaps. 7. Spoilers...................................................................................... RET
Landing 1. Brakes........................................................................... As Required 2. Spoilers.................................................................... Verify Extended If spoilers are not extended automatically: a.
SPOILER Lever .................................................................. EXT
3. Thrust Reversers ........................................................... As Desired
CL-126B October 2004 Change 1
EFFECTIVITY ALL
N-13 N-14
After Landing/Clearing Runway 1. Standby Attitude Indicator........................................................ Cage 2. Transponder ..................................................................... STANDBY 3. L & R PROBES ..........................................................................OFF 4. WING/STAB, L & R NAC............................................... As Required 5. Lights .............................................................................. As Desired 6. SPOILER ...................................................................................RET 7. FLAPS ................................................... UP or Set for Next Takeoff 8. Radar ........................................................................................... Off 9. APU (if installed) ............................................................. As Desired a.
APU MASTER ...................................................................... ON
b.
APU START/STOP ..........................................................START
c.
APU GEN ............................................................................. ON
d.
APU BLEED ......................................................................... ON
10. SUMRY Page B-ACUM Pressure .............................. 2610-3600 psi 11. AUX HYD .................................................................................... Off 12. Thrust Lever.......................................................CUTOFF (Optional)
EFFECTIVITY
N-14 N-15
ALL
CL-126B October 2004 Change 1
Change 1
Shutdown 1. EMERGENCY/PARKING BRAKE and/or Chocks .......................Set 2. L & R AV MSTR ......................................................................... OFF 3. L & R WSHLD............................................................................ OFF 4. Anti-Ice Systems.......................................................................... Off 5. EMER LIGHTS .......................................................................... OFF 6. NOSE STEER ............................................................................ Off 7. Thrust Lever(s) ...................................................................CUTOFF 8. PACK ......................................................................................... OFF 9. FMS ........................................................................................... OFF 10. Instrument Lights ............................................................ As Desired 11. APU (if installed) ..............................................................Shut Down a.
APU BLEED .......................................................................... Off
b.
APU START/STOP................................................................ Off
c.
APU MASTER (after 30-second delay)................................. Off
12. BCN/STROBE ........................................................................... OFF 13. EMER BATT .............................................................................. OFF 14. L & R BATT ................................................................................ OFF 15. Controls Lock...........................................................................Install
Quick Turn-Around (One or No Engine Shutdown) Before Taxi 1. LDG ALT ...................................................................Set Destination 2. Fuel Quantities ................................................Checked & Balanced 3. FMS .............................................................................................Set 4. Takeoff Data (V1, VR, V2, TO Pitch, Distance) ................. Computed & Speeds Set 5. Avionics .......................................................................................Set 6. Cabin Door ...........................................................Closed & Latched (Procedure Continued) CL-126B October 2004 Change 1
EFFECTIVITY ALL
N-15 N-16
7. Engine................................................ Start (Both Engines Running) 8. Engine Instruments & N1 Bugs ...............................................Check 9. PACK............................................................................................ On 10. Circuit Breakers ............................................................... Check Set 11. L & R AV MSTR ........................................................................... On 12. L & R WSHLD .............................................................................. On 13. SPOILER .................................................................................. ARM 14. FLAPS ............................................ Set 8° or 20°, Check Indication 15. RUD BOOST................................................................................ On 16. Flight Controls.........................................................................Check 17. Passengers Briefed/Cabin Check ..................................... Complete 18. NO SMOKING BELTS ................................................................. On
Taxi 1. Flight Instruments ...................................................................Check 2. FLAPS ............................................ Set 8° or 20°, Check Indication 3. Trims ................................................ Set PIT, AIL & RUD for Takeoff 4. Crew Takeoff Briefing........................................................ Complete 5. HI FLOW ...................................................................................... Off 6. Radar ............................................................................ As Required 7. Anti-Ice Systems: a.
WING/STAB, L & R NAC ........................................ As Required
8. APU (if installed) ............................................................. Shut Down a.
APU BLEED .......................................................................... Off
b.
APU START/STOP ................................................................ Off
c.
APU MASTER (after 30-second delay) ................................. Off
d.
FMS Fuel Quantity ......................................................... Update
9. Go to Runway Lineup checklist, page N-10.
EFFECTIVITY
N-16 N-16.1
ALL
CL-126B October 2004 Change 1
One Engine Taxi 1. Accomplish steps 1 thru 8 of the Starting Engines checklist, Page N-7. 2. PACK ........................................................................................... On 3. Circuit Breakers ...........................................................................Set 4. VOLTS & AMPS...................................................................... Check 5. Spoilers................................................................................... Check a.
SPOILER.......................... EXT, Check Equal Rate & Extension
b.
SPOILER............................................... ARM, Check Retracted
6. FLAPS ..........................................................................Set 8° or 20° 7. Flight Controls ........................................................................ Check a.
Rudder Boost ................................................... Verify Green RB
8. EICAS..................................................................................... Check 9. Passengers Briefed/Cabin Check ......................................Complete 10. Aircraft Lighting...................................................... On, As Required 11. NO SMOKING BELTS ................................................................. On 12. NOSE STEER .............................................................................ON
14. EMER LIGHTS ..... ON, Check EMER Lights Illuminated, then ARM 15. EXT PWR (if applicable) ................................... AVAIL & Disconnect When Ready to Taxi: 16. EMERGENCY/PARKING BRAKE........................................ Release 17. Brakes & Nose Wheel Steering .............................................. Check 18. Flight Instruments ............................................................... Checked 19. Takeoff Data (V1, VR, V2, TO Pitch, Distance) ........................ Check 20. Nav Equipment ....................................................................... Check 21. FLAPS ................................................... 8° or 20°, Check Indication (Procedure Continued)
CL-126B October 2004 Change 1
EFFECTIVITY ALL
N-17 N-17.1
ONE ENGINE TAXI
13. SUMRY Page B-ACUM Pressure .............................. 2610-3600 psi
22. Trims ............................................... Set PIT, AIL, & RUD for Takeoff Takeoff Pitch Trim Setting 1 to 10 8.7
CENTER-OF-GRAVITY — % MAC 12 14 16 18 20 8.1 7.6 7.0 6.4 5.9
22 to aft limit 5.3
23. HI FLOW ...................................................................................... Off 24. PACK..........................................................................................OFF When Ready to Start 2nd Engine: 25. SUMRY Page ELEC VOLTS ...................................................Check 26. Thrust Lever.............................................................................. IDLE 27. Engine....................................................................................... Start 28. VOLTS & AMPS ......................................................................Check 29. Manual Mode Governor ......................................................Checked 30. L & R WSHLD .............................................................................. On 31. Anti-Ice System...............................................Check & As Required 32. APU (if installed) ............................................................. Shut Down a.
APU BLEED .......................................................................... Off
b.
APU START/STOP ................................................................ Off
c.
APU MASTER (after 30-second delay) ................................. Off
d.
FMS Fuel Quantity ......................................................... Update
33. PACK............................................................................................ On 34. Bleed Air System (first flight of day)........................................Check 35. EMER PRESS ........................................................................Check 36. Thrust Reversers ....................................................................Check 37. Engine Instruments & N1 Bugs ...............................................Check 38. Radar ............................................................................ As Required 39. Crew Takeoff Briefing........................................................ Complete 40. Anti-Ice Systems: a.
WING/STAB, L & R NAC ........................................ As Required
41. Go to Runway Lineup checklist, Page N-10 EFFECTIVITY
N-18 N-17.2
ALL
CL-126B October 2004 Change 1
Learjet 45 AFM
PERFORMANCE DATA FOR AIRCRAFT WITH EFFECTIVITY CODE
E 45-002 thru 45-2000 when modified by SB 45-11-4 (Increase Maximum Takeoff Weight to 21,500 LB) but NOT modified by SB 45-72-1 (TFE731-20BR-1B Engine Upgrade)
U.S. UNITS
October
CL-126B October 2004
i
TAKEOFF WEIGHT LIMITS — FLAPS 8°............................................. P-2 FLAPS 8° TAKEOFF DATA (SPEEDS, DISTANCE, TARGET PITCH ATTITUDE & THRUST) Sea Level thru 10000 Feet..................................................P-3 thru P-24 TAKEOFF WEIGHT LIMITS — FLAPS 20°......................................... P-26 FLAPS 20° TAKEOFF DATA (SPEEDS, DISTANCE, TARGET PITCH ATTITUDE & THRUST)
PERFORMANCE
TAKEOFF
TAKEOFF FLAPS 8°
PERFORMANCE DATA CONTENTS
EN ROUTE CLIMB PERFORMANCE — TWO ENGINE ....................................... P-41 LONG RANGE CRUISE — TWO ENGINE ........................................ P-51 CONSTANT MACH CRUISE .............................................................. P-59 LONG RANGE CRUISE — ONE ENGINE ......................................... P-67 DESCENT PERFORMANCE SCHEDULE.......................................... P-75 MAXIMUM RANGE DESCENT — ONE ENGINE .............................. P-76 HOLDING OPERATIONS ................................................................... P-77 LANDING LANDING WEIGHT LIMITS................................................................. P-78 LANDING DATA (SPEEDS & DISTANCE) Sea Level thru 10000 Feet................................................P-79 thru P-89
CL-126B October 2004
EFFECTIVITY ALL
P-1
TAKEOFF FLAPS 20°
Sea Level thru 6000 Feet..................................................P-27 thru P-40
PERFORMANCE
TAKEOFF WEIGHT LIMITS FLAPS 8° TEMPERATURE PRESSURE °F
14
32
50
68
86
104
ALTITUDE °C
-10
0
10
20
30
40
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
(FEET) 10000
WEIGHT LIMIT ~ POUNDS 21500
21500
21500
19760
17380
9000
20630
18200
8000
21500
19020
7000
19840
6000
20660
18230
5000
21500
19050
4000
19870
3000
20700
2000
21500
1000 S.L.
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed. DO NOT EXCEED MAXIMUM CERTIFIED TAKEOFF WEIGHT
P-2.1
EFFECTIVITY CODE
E
CL-126B October 2004
°F
°C WT (LB) DATA
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 119 119 130 10 4630 118 118 129 11 4350 113 117 126 12 3940 109 115 124 12 3570 106 112 121 14 3310 106 108 118 14 3250 106 107 116 14 3200 106 107 116 14 3140
119 119 130 10 4790 118 118 129 11 4500 113 117 126 11 4080 109 115 124 12 3700 105 112 121 14 3420 106 108 118 14 3360 106 107 116 14 3300 106 107 116 14 3240
119 119 130 10 4950 118 118 129 11 4640 113 117 126 11 4210 109 115 124 12 3820 105 112 121 14 3530 105 108 118 14 3460 105 107 116 14 3400 106 107 116 14 3340
119 119 130 9 5130 118 118 129 11 4810 113 117 126 11 4350 109 115 124 12 3940 105 112 121 14 3640 105 108 118 14 3570 105 107 116 14 3500 105 107 116 14 3440
119 119 130 9 5290 118 118 129 11 4970 113 117 126 12 4500 109 115 124 11 4060 105 112 121 14 3750 105 108 118 14 3670 105 107 116 14 3610 105 107 116 14 3540
119 119 130 9 7050 118 118 129 9 6610 116 117 126 9 5640 113 115 124 9 4870 109 112 121 11 4320 105 108 118 14 3940 105 107 116 13 3860 105 107 116 13 3770
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-3.1
PERFORMANCE
TEMP
TAKEOFF FLAPS 8°
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
TAKEOFF FLAPS 20°
TAKEOFF (FLAPS 8°) — SEA LEVEL
PERFORMANCE
TAKEOFF (FLAPS 8°) — SEA LEVEL TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-4
°C
ANTI-ICE OFF
104
40
87.3
95
35
88.6
87.8
31
89.6
86
30
89.5
77
25
88.7
68
20
87.9
59
15
87.1
50
10
86.3
41
5
85.6
32
0
84.8
23
-5
84.0
14
-10
83.3
EFFECTIVITY CODE
B C D E
CL-126B October 2004
°F
°C WT (LB) DATA
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 119 119 130 10 4780 118 118 129 11 4480 113 117 126 11 4060 109 115 124 12 3690 105 112 121 14 3420 106 108 118 14 3360 106 107 116 14 3300 106 107 116 14 3240
119 119 130 10 4940 118 118 129 11 4640 113 117 126 11 4210 109 115 124 12 3820 105 112 121 14 3530 105 108 118 14 3470 105 107 116 14 3400 106 107 116 14 3350
119 119 130 9 5140 118 118 129 11 4820 113 117 126 11 4360 109 115 124 12 3940 105 112 121 13 3640 105 108 118 14 3580 105 107 116 14 3510 105 107 116 14 3450
119 119 130 9 5300 118 118 129 11 4990 113 117 126 12 4520 109 115 124 11 4070 105 112 121 14 3760 105 108 118 14 3680 105 107 116 14 3620 105 107 116 14 3550
119 119 130 9 5920 118 118 129 9 5520 115 117 126 11 4860 110 115 124 12 4380 106 112 121 12 3950 105 108 118 14 3840 105 107 116 14 3760 105 107 116 14 3690
119 119 130 9 8020 118 118 129 9 7400 117 117 126 9 6510 114 115 124 9 5520 111 112 121 11 4720 105 108 118 11 4180 105 107 116 13 4050 105 107 116 13 3950
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-5.1
PERFORMANCE
TEMP
TAKEOFF FLAPS 8°
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
TAKEOFF FLAPS 20°
TAKEOFF (FLAPS 8°) — 1000 FEET
PERFORMANCE
TAKEOFF (FLAPS 8°) — 1000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-6
°C
ANTI-ICE OFF
104
40
87.1
95
35
88.4
86
30
89.8
82.4
28
90.4
77
25
90.0
68
20
89.2
59
15
88.4
50
10
87.6
41
5
86.8
32
0
86.0
23
-5
85.2
14
-10
84.5
EFFECTIVITY CODE
B C D E
CL-126B October 2004
°F
°C WT (LB) DATA
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 119 119 130 10 4930 117 118 129 11 4630 113 117 126 11 4210 109 115 124 12 3810 105 112 121 14 3530 105 108 118 14 3470 105 107 116 14 3410 106 107 116 14 3350
119 119 130 9 5130 118 118 129 11 4820 113 117 126 11 4360 109 115 124 12 3940 105 112 121 13 3650 105 108 118 14 3580 105 107 116 14 3520 105 107 116 14 3460
119 119 130 9 5310 118 118 129 11 5000 113 117 126 12 4520 109 115 124 11 4080 105 112 121 14 3770 105 108 118 14 3690 105 107 116 14 3630 105 107 116 14 3560
119 119 130 9 5470 118 118 129 11 5160 113 117 126 12 4680 109 115 124 11 4210 105 112 121 14 3880 105 108 118 14 3810 105 107 116 14 3740 105 107 116 14 3670
119 119 130 9 6650 118 118 129 9 6160 116 117 126 9 5300 112 115 124 11 4750 107 112 121 12 4250 105 108 118 14 4020 105 107 116 14 3930 105 107 116 14 3850
119 119 130 9 9220 118 118 129 9 8520 117 117 126 9 7370 115 115 124 9 6350 111 112 121 9 5380 107 108 118 11 4570 105 107 116 12 4270 105 107 116 12 4160
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-7.1
PERFORMANCE
TEMP
TAKEOFF FLAPS 8°
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
TAKEOFF FLAPS 20°
TAKEOFF (FLAPS 8°) — 2000 FEET
PERFORMANCE
TAKEOFF (FLAPS 8°) — 2000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-8
°C
ANTI-ICE OFF
104
40
86.9
95
35
88.2
86
30
89.6
77
25
91.0
75.2
24
91.1
68
20
90.4
59
15
89.6
50
10
88.8
41
5
88.0
32
0
87.2
23
-5
86.4
14
-10
85.7
EFFECTIVITY CODE
B C D E
CL-126B October 2004
°F
°C WT (LB) DATA
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 119 119 130 9 5110 117 118 129 11 4800 113 117 126 11 4350 109 115 124 12 3940 105 112 121 14 3650 105 109 118 14 3580 105 108 116 14 3520 105 107 116 14 3460
119 119 130 9 5300 117 118 129 11 4970 113 117 126 11 4510 109 115 124 12 4080 105 112 121 14 3770 105 109 118 14 3700 105 108 116 14 3630 105 107 116 14 3570
119 119 130 9 5460 117 118 129 11 5180 113 117 126 12 4690 109 115 124 11 4220 105 112 121 14 3890 105 109 118 14 3820 105 108 116 14 3750 105 107 116 14 3680
119 119 130 9 5850 118 118 129 11 5480 114 117 126 11 4920 109 115 124 12 4450 105 112 121 14 4040 105 109 118 14 3960 105 108 116 14 3880 105 107 116 14 3810
119 119 130 9 7520 118 118 129 9 7060 117 117 126 9 6070 114 115 124 9 5230 109 112 121 11 4640 105 109 118 13 4230 105 108 116 13 4140 105 107 116 13 4050
119 119 130 8 11130 118 118 129 8 10060 117 117 126 9 8390 114 115 124 9 7170 112 112 121 9 6130 108 109 118 9 5120 105 108 116 12 4510 105 107 116 12 4380
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-9.1
PERFORMANCE
TEMP
TAKEOFF FLAPS 8°
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
TAKEOFF FLAPS 20°
TAKEOFF (FLAPS 8°) — 3000 FEET
PERFORMANCE
TAKEOFF (FLAPS 8°) — 3000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-10
°C
ANTI-ICE OFF
104
40
86.7
95
35
88.0
86
30
89.3
77
25
90.8
69.8
21
91.9
68
20
91.7
59
15
90.9
50
10
90.1
41
5
89.3
32
0
88.5
23
-5
87.7
14
-10
86.9
EFFECTIVITY CODE
B C D E
CL-126B October 2004
°F
°C WT (LB) DATA
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 120 120 130 9 5270 117 119 129 11 4970 113 117 126 11 4500 109 115 124 12 4070 105 112 121 13 3780 105 109 118 14 3710 105 108 116 14 3640 105 108 116 14 3580
120 120 130 9 5460 117 119 129 11 5150 113 117 126 11 4660 109 115 124 12 4220 105 112 121 14 3900 105 109 118 14 3830 105 108 116 14 3760 105 108 116 14 3700
120 120 130 9 5650 118 119 129 11 5390 113 117 126 12 4850 108 115 124 11 4370 105 112 121 13 4030 105 109 118 15 3950 105 108 116 14 3880 105 108 116 14 3810
120 120 130 9 6270 119 119 129 9 5830 114 117 126 11 5190 110 115 124 12 4680 105 112 121 12 4210 105 109 118 13 4110 105 108 116 14 4030 105 108 116 14 3960
120 120 130 9 8600 119 119 129 9 8020 117 117 126 9 6990 114 115 124 9 5970 111 112 121 11 5110 106 109 118 11 4520 105 108 116 13 4360 105 108 116 13 4260
119 119 129 8 12600 117 117 126 8 9760 115 115 124 8 8230 112 112 121 9 7040 109 109 118 9 5850 106 108 116 10 4910 105 108 116 12 4630
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-11.1
PERFORMANCE
TEMP
TAKEOFF FLAPS 8°
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
TAKEOFF FLAPS 20°
TAKEOFF (FLAPS 8°) — 4000 FEET
PERFORMANCE
TAKEOFF (FLAPS 8°) — 4000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-12
°C
ANTI-ICE OFF
104
40
86.5
95
35
87.7
86
30
89.1
77
25
90.6
68
20
92.0
64.4
18
92.6
59
15
92.1
50
10
91.3
41
5
90.5
32
0
89.7
23
-5
88.9
14
-10
88.1
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 120 120 131 11 5470 118 119 129 11 5220 113 118 127 11 4720 109 115 124 11 4260 105 113 121 13 3910 105 109 118 14 3840 105 108 116 14 3770 105 108 116 14 3700
120 120 131 11 5680 118 119 129 11 5420 114 118 127 11 4900 109 115 124 12 4430 105 113 121 14 4040 105 109 118 14 3960 105 108 116 14 3890 105 108 116 14 3820
120 120 131 11 5890 118 119 129 11 5620 114 118 127 12 5090 109 115 124 11 4590 105 113 121 13 4170 105 109 118 14 4090 105 108 116 14 4010 105 108 116 14 3940
120 120 131 9 7130 119 119 129 9 6650 116 118 127 9 5760 112 115 124 11 5160 107 113 121 12 4630 105 109 118 14 4330 105 108 116 14 4230 105 108 116 14 4150
120 120 131 8 9780 119 119 129 9 9180 117 118 127 9 7920 115 115 124 9 6840 112 113 121 9 5800 108 109 118 11 4990 105 108 116 13 4600 105 108 116 12 4480
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
118 118 127 8 12010 115 115 124 8 9460 112 113 121 8 7930 109 109 118 9 6720 108 108 116 10 5390 106 108 116 10 5000
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-13.1
TAKEOFF FLAPS 20°
TEMP
PERFORMANCE
TAKEOFF (FLAPS 8°) — 5000 FEET
PERFORMANCE
TAKEOFF (FLAPS 8°) — 5000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-14
°C
ANTI-ICE OFF
104
40
86.3
95
35
87.5
86
30
88.9
77
25
90.3
68
20
91.8
59
15
93.2
57.2
14
93.2
50
10
92.6
41
5
91.7
32
0
90.9
23
-5
90.1
14
-10
89.3
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 120 120 131 11 5670 118 119 129 11 5410 113 118 127 11 4900 109 115 124 12 4430 105 113 122 14 4050 105 109 118 14 3970 105 108 116 14 3900 105 108 116 14 3830
120 120 131 11 5910 118 119 129 11 5620 113 118 127 11 5080 109 115 124 11 4590 105 113 122 13 4190 105 109 118 14 4100 105 108 116 14 4030 105 108 116 14 3960
120 120 131 11 6130 118 119 129 10 5820 113 118 127 11 5280 109 115 124 11 4750 105 113 122 14 4330 105 109 118 14 4240 105 108 116 14 4160 105 108 116 14 4080
120 120 131 9 8070 119 119 129 9 7600 117 118 127 9 6590 114 115 124 11 5670 109 113 122 11 5070 105 109 118 13 4560 105 108 116 13 4460 105 108 116 13 4360
120 120 131 8 12120 119 119 129 8 10760 118 118 127 8 9060 114 115 124 9 7740 112 113 122 9 6630 109 109 118 9 5570 105 108 116 12 4870 105 108 116 12 4740
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
115 115 124 8 11620 113 113 122 8 9250 109 109 118 8 7640 108 108 116 8 6160 108 108 116 10 5500
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-15.1
TAKEOFF FLAPS 20°
TEMP
PERFORMANCE
TAKEOFF (FLAPS 8°) — 6000 FEET
PERFORMANCE
TAKEOFF (FLAPS 8°) — 6000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-16
°C
ANTI-ICE OFF
104
40
86.1
95
35
87.3
86
30
88.6
77
25
90.1
68
20
91.6
59
15
93.0
51.8
11
93.9
50
10
93.8
41
5
92.9
32
0
92.1
23
-5
91.3
14
-10
90.5
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 120 121 131 11 5940 118 120 130 11 5670 114 118 128 11 5130 110 116 125 12 4630 105 113 122 13 4190 105 110 119 14 4100 105 108 116 14 4030 105 108 116 14 3960
120 121 131 11 6180 118 120 130 11 5890 114 118 128 11 5320 110 116 125 11 4810 105 113 122 11 4340 105 110 119 14 4240 105 108 116 14 4160 105 108 116 14 4090
121 121 131 9 6880 120 120 130 9 6430 116 118 128 11 5790 111 116 125 11 5220 106 113 122 11 4680 105 110 119 13 4450 105 108 116 14 4350 105 108 116 14 4270
121 121 131 9 9310 120 120 130 9 8640 117 118 128 9 7560 115 116 125 9 6520 112 113 122 11 5630 107 110 119 11 4990 105 108 116 13 4700 105 108 116 13 4590
120 120 130 8 13760 118 118 128 8 10530 115 116 125 8 8910 113 113 122 8 7620 109 110 119 9 6420 106 108 116 11 5320 105 108 116 12 5010
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
TAKEOFF FLAPS 20°
TEMP
113 113 122 8 11630 110 110 119 8 9030 108 108 116 8 7220 108 108 116 8 6290
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed. The shaded areas are for interpolation only. CL-126B October 2004
EFFECTIVITY CODE
E
PERFORMANCE
TAKEOFF (FLAPS 8°) — 7000 FEET
P-17.1
PERFORMANCE
TAKEOFF (FLAPS 8°) — 7000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-18
°C
ANTI-ICE OFF
104
40
85.9
95
35
87.1
86
30
88.4
77
25
89.9
68
20
91.3
59
15
92.7
50
10
94.1
44.6
7
94.9
41
5
94.5
32
0
93.7
23
-5
92.8
14
-10
92.0
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 120 121 131 11 6150 118 120 130 11 5840 114 118 128 11 5300 109 116 125 11 4790 105 113 122 13 4340 105 110 119 15 4250 105 108 116 14 4170 105 108 116 14 4100
120 121 131 11 6400 118 120 130 10 6070 114 118 128 10 5500 109 116 125 11 4970 105 113 122 12 4490 105 110 119 15 4400 105 108 116 14 4310 105 108 116 14 4230
121 121 131 9 7710 120 120 130 9 7190 117 118 128 11 6300 113 116 125 11 5650 108 113 122 11 5070 105 110 119 12 4680 105 108 116 14 4570 105 108 116 14 4470
121 121 131 8 10830 120 120 130 8 10050 118 118 128 9 8620 115 116 125 9 7450 112 113 122 9 6380 109 110 119 11 5500 105 108 116 13 4990 105 108 116 13 4850
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
118 118 128 8 13450 116 116 125 8 10270 113 113 122 8 8670 110 110 119 8 7350 108 108 116 10 5850 106 108 116 10 5430
TAKEOFF FLAPS 20°
TEMP
110 110 119 8 10970 108 108 116 8 8320 108 108 116 8 7380
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed. The shaded areas are for interpolation only. CL-126B October 2004
EFFECTIVITY CODE
E
PERFORMANCE
TAKEOFF (FLAPS 8°) — 8000 FEET
P-19.1
PERFORMANCE
TAKEOFF (FLAPS 8°) — 8000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-20
°C
ANTI-ICE OFF
104
40
85.6
95
35
86.9
86
30
88.2
77
25
89.6
68
20
91.1
59
15
92.5
50
10
93.9
41
5
95.4
37.4
3
95.8
32
0
95.3
23
-5
94.4
14
-10
93.6
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 121 122 132 11 6510 119 121 131 11 6200 115 119 129 11 5600 110 117 126 11 5060 106 114 123 11 4560 105 111 120 13 4410 105 108 117 14 4320 105 108 116 14 4250
122 122 132 9 7030 120 121 131 11 6640 116 119 129 11 6010 111 117 126 10 5390 107 114 123 11 4860 105 111 120 14 4610 105 108 117 14 4500 105 108 116 14 4420
122 122 132 9 8910 121 121 131 9 8360 118 119 129 9 7260 115 117 126 11 6320 111 114 123 11 5650 106 111 120 11 5020 105 108 117 14 4830 105 108 116 13 4710
122 122 132 8 13080 121 121 131 8 11800 119 119 129 8 10020 116 117 126 8 8620 113 114 123 8 7390 110 111 120 9 6260 105 108 117 11 5350 105 108 116 11 5130
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
TAKEOFF FLAPS 20°
TEMP
117 117 126 8 12960 114 114 123 8 10210 111 111 120 8 8550 108 108 117 8 6930 108 108 116 9 6000
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
PERFORMANCE
TAKEOFF (FLAPS 8°) — 9000 FEET
P-21.1
PERFORMANCE
TAKEOFF (FLAPS 8°) — 9000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-22
°C
ANTI-ICE OFF
104
40
—
95
35
86.7
86
30
88.0
77
25
89.4
68
20
90.8
59
15
92.3
50
10
93.7
41
5
95.2
32
0
96.7
23
-5
95.9
14
-10
95.1
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 121 122 132 10 6800 119 121 131 11 6500 114 119 129 11 5870 110 117 126 11 5310 105 114 123 11 4770 105 111 120 13 4630 105 109 117 14 4530 105 108 116 14 4450
122 122 132 9 7750 121 121 131 9 7230 117 119 129 11 6490 112 117 126 10 5820 108 114 123 11 5240 105 111 120 12 4870 105 109 117 14 4760 105 108 116 14 4660
122 122 132 8 10300 121 121 131 9 9600 118 119 129 9 8410 116 117 126 9 7250 113 114 123 11 6290 107 111 120 11 5570 105 109 117 12 5170 105 108 116 13 5020
121 121 131 8 15760 119 119 129 8 11780 116 117 126 8 10050 113 114 123 8 8520 110 111 120 8 7190 107 109 117 10 5930 105 108 116 12 5510
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
TAKEOFF FLAPS 20°
TEMP
114 114 123 8 12720 111 111 120 8 9930 109 109 117 8 8050 108 108 116 8 6910
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed & APR armed. The distances presented include the required altitude correction as shown in the AFM. CL-126B October 2004 Change 1
EFFECTIVITY CODE
E
PERFORMANCE
TAKEOFF (FLAPS 8°) — 10000 FEET
P-23.1
PERFORMANCE
TAKEOFF (FLAPS 8°) — 10000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-24
°C
ANTI-ICE OFF
104
40
—
95
35
86.5
86
30
87.8
77
25
89.2
68
20
90.6
59
15
92.1
50
10
93.5
41
5
95.0
32
0
96.5
24.8
-4
97.6
23
-5
97.4
14
-10
96.6
EFFECTIVITY CODE
B C D E
CL-126B October 2004
PERFORMANCE TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
CREW NOTES
CL-126B October 2004
EFFECTIVITY ALL
P-25
PERFORMANCE
TAKEOFF WEIGHT LIMITS FLAPS 20° TEMPERATURE PRESSURE °F
14
32
ALTITUDE °C
-10
0
TAKEOFF FLAPS 8°
(FEET)
50
68
86
104
10
20
30
40
WEIGHT LIMIT ~ POUNDS 20520
18100
16010
5000
21400
18880
16720
4000
21500
6000
21500
21500
21500
19670
17440
3000
20540
18190
2000
21420
18930
1000
21500
19750 20570
TAKEOFF FLAPS 20°
S.L.
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed. DO NOT EXCEED MAXIMUM CERTIFIED TAKEOFF WEIGHT
P-26.1
EFFECTIVITY CODE
E
CL-126B October 2004
°F
°C WT (LB) DATA
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 115 115 125 8 4630 114 114 123 8 4300 110 112 121 10 3810 105 110 118 11 3450 106 108 116 12 3390 106 108 115 12 3330 106 108 115 12 3270 106 107 115 11 3230
115 115 125 8 4790 114 114 123 8 4450 110 112 121 10 3940 105 110 118 10 3560 105 108 116 12 3500 105 108 115 12 3440 106 108 115 12 3380 106 107 115 11 3330
115 115 125 8 4980 114 114 123 8 4600 110 112 121 10 4070 105 110 118 10 3670 105 108 116 12 3610 105 108 115 12 3540 105 108 115 12 3480 105 107 115 11 3430
115 115 125 8 5150 114 114 123 8 4750 110 112 121 10 4200 105 110 118 10 3790 105 108 116 12 3720 105 108 115 12 3650 105 108 115 12 3590 105 107 115 11 3530
115 115 125 8 5310 114 114 123 8 4890 110 112 121 10 4340 105 110 118 10 3910 105 108 116 12 3830 105 108 115 12 3760 105 108 115 11 3690 105 107 115 11 3640
115 115 125 8 7580 114 114 123 8 7050 112 112 121 8 5820 109 110 118 8 4870 105 108 116 10 4150 105 108 115 11 4040 105 108 115 10 3950 105 107 115 10 3870
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-27.1
PERFORMANCE
TEMP
TAKEOFF FLAPS 8°
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
TAKEOFF FLAPS 20°
TAKEOFF (FLAPS 20°) — SEA LEVEL
PERFORMANCE
TAKEOFF (FLAPS 20°) — SEA LEVEL TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-28
°C
ANTI-ICE OFF
104
40
87.3
95
35
88.6
87.8
31
89.6
86
30
89.5
77
25
88.7
68
20
87.9
59
15
87.1
50
10
86.3
41
5
85.6
32
0
84.8
23
-5
84.0
14
-10
83.3
EFFECTIVITY CODE
B C D E
CL-126B October 2004
°F
°C WT (LB) DATA
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 115 115 125 8 4770 114 114 123 8 4430 110 112 121 10 3930 105 111 119 11 3560 105 108 116 12 3490 105 108 115 12 3430 106 108 115 12 3380 106 107 115 11 3330
115 115 125 8 4970 114 114 123 8 4590 110 112 121 10 4070 105 111 119 10 3680 105 108 116 12 3610 105 108 115 12 3550 105 108 115 12 3490 105 107 115 11 3440
115 115 125 8 5150 114 114 123 8 4750 110 112 121 10 4210 105 111 119 10 3790 105 108 116 12 3720 105 108 115 12 3660 105 108 115 12 3600 105 107 115 11 3540
115 115 125 8 5320 114 114 123 8 4900 110 112 121 10 4350 105 111 119 10 3920 105 108 116 12 3840 105 108 115 12 3770 105 108 115 11 3710 105 107 115 11 3650
115 115 125 8 6070 114 114 123 8 5560 111 112 121 8 4730 107 111 119 10 4220 105 108 116 11 4010 105 108 115 11 3930 105 108 115 11 3850 105 107 115 11 3790
115 115 125 8 11290 114 114 123 8 8660 112 112 121 8 6870 110 111 119 8 5670 107 108 116 9 4540 105 108 115 10 4250 105 108 115 10 4150 105 107 115 10 4060
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-29.1
PERFORMANCE
TEMP
TAKEOFF FLAPS 8°
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
TAKEOFF FLAPS 20°
TAKEOFF (FLAPS 20°) — 1000 FEET
PERFORMANCE
TAKEOFF (FLAPS 20°) — 1000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-30
°C
ANTI-ICE OFF
104
40
87.1
95
35
88.4
86
30
89.8
82.4
28
90.4
77
25
90.0
68
20
89.2
59
15
88.4
50
10
87.6
41
5
86.8
32
0
86.0
23
-5
85.2
14
-10
84.5
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 115 115 125 8 4960 114 114 123 8 4580 110 112 121 10 4060 105 111 119 11 3680 105 108 116 12 3610 105 108 116 12 3550 105 108 116 12 3490 105 107 116 11 3440
115 115 125 8 5140 114 114 123 8 4740 110 112 121 10 4210 105 111 119 10 3800 105 108 116 12 3730 105 108 116 12 3660 105 108 116 12 3600 105 107 116 11 3550
115 115 125 8 5320 114 114 123 8 4910 110 112 121 10 4360 105 111 119 10 3920 105 108 116 12 3850 105 108 116 12 3780 105 108 116 12 3710 105 107 116 11 3660
115 115 125 8 5510 114 114 123 8 5110 110 112 121 10 4510 105 111 119 10 4050 105 108 116 12 3970 105 108 116 12 3890 105 108 116 11 3830 105 107 116 11 3770
115 115 125 8 6900 114 114 123 8 6370 112 112 121 8 5350 109 111 119 10 4590 105 108 116 11 4200 105 108 116 11 4110 105 108 116 11 4030 105 107 116 11 3950
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
112 112 121 8 8350 111 111 119 8 6700 108 108 116 8 5230 107 108 116 9 4630 105 108 116 10 4380 105 107 116 9 4270
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-31.1
TAKEOFF FLAPS 20°
TEMP
PERFORMANCE
TAKEOFF (FLAPS 20°) — 2000 FEET
PERFORMANCE
TAKEOFF (FLAPS 20°) — 2000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-32
°C
ANTI-ICE OFF
104
40
86.9
95
35
88.2
86
30
89.6
77
25
91.0
75.2
24
91.1
68
20
90.4
59
15
89.6
50
10
88.8
41
5
88.0
32
0
87.2
23
-5
86.4
14
-10
85.7
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 115 115 125 8 5110 114 114 123 8 4720 110 112 121 10 4200 105 111 119 12 3800 105 108 116 12 3730 105 108 116 12 3670 105 108 116 12 3610 105 107 116 11 3550
115 115 125 8 5310 114 114 123 8 4900 110 112 121 10 4350 105 111 119 10 3930 105 108 116 12 3860 105 108 116 12 3790 105 108 116 12 3720 105 107 116 11 3670
115 115 125 8 5500 114 114 123 8 5080 110 112 121 10 4510 105 111 119 10 4050 105 108 116 12 3980 105 108 116 12 3910 105 108 116 11 3840 105 107 116 11 3780
115 115 125 8 5900 114 114 123 8 5470 110 112 121 10 4760 106 111 119 10 4270 105 108 116 12 4120 105 108 116 11 4050 105 108 116 11 3980 105 107 116 11 3910
115 115 125 8 8240 114 114 123 8 7560 112 112 121 8 6240 110 111 119 8 5230 105 108 116 10 4450 105 108 116 11 4330 105 108 116 10 4240 105 107 116 10 4150
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
110 111 119 7 8080 108 108 116 8 6090 108 108 116 7 5170 106 108 116 8 4750 105 107 116 9 4500
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-33.1
TAKEOFF FLAPS 20°
TEMP
PERFORMANCE
TAKEOFF (FLAPS 20°) — 3000 FEET
PERFORMANCE
TAKEOFF (FLAPS 20°) — 3000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-34
°C
ANTI-ICE OFF
104
40
86.7
95
35
88.0
86
30
89.3
77
25
90.8
69.8
21
91.9
68
20
91.7
59
15
90.9
50
10
90.1
41
5
89.3
32
0
88.5
23
-5
87.7
14
-10
86.9
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 115 115 125 8 5270 114 114 123 8 4870 110 112 121 10 4350 105 111 119 12 3930 105 108 116 12 3860 105 108 116 12 3790 105 108 116 12 3730 105 108 116 11 3680
115 115 125 8 5480 114 114 123 8 5070 110 112 121 10 4510 105 111 119 10 4060 105 108 116 12 3990 105 108 116 12 3920 105 108 116 12 3850 105 108 116 11 3790
115 115 125 8 5690 114 114 123 8 5280 110 112 121 10 4670 105 111 119 10 4200 105 108 116 12 4120 105 108 116 12 4040 105 108 116 11 3980 105 108 116 11 3910
115 115 125 8 6390 114 114 123 8 5860 111 112 121 10 5020 106 111 119 10 4500 105 108 116 11 4290 105 108 116 11 4210 105 108 116 11 4130 105 108 116 11 4060
115 115 125 8 11580 114 114 123 8 9410 112 112 121 8 7340 110 111 119 8 6120 107 108 116 9 4910 105 108 116 10 4580 105 108 116 10 4470 105 108 116 10 4370
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
111 111 119 7 12460 108 108 116 7 7310 108 108 116 7 6030 108 108 116 7 5300 106 108 116 7 4870
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
P-35.1
TAKEOFF FLAPS 20°
TEMP
PERFORMANCE
TAKEOFF (FLAPS 20°) — 4000 FEET
PERFORMANCE
TAKEOFF (FLAPS 20°) — 4000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-36
°C
ANTI-ICE OFF
104
40
86.5
95
35
87.7
86
30
89.1
77
25
90.6
68
20
92.0
64.4
18
92.6
59
15
92.1
50
10
91.3
41
5
90.5
32
0
89.7
23
-5
88.9
14
-10
88.1
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 116 116 125 8 5500 114 114 124 8 5110 110 113 122 10 4560 106 111 119 10 4100 105 108 117 12 4000 105 108 116 12 3930 105 108 116 12 3860 105 108 116 11 3800
116 116 125 8 5700 114 114 124 8 5320 110 113 122 10 4730 106 111 119 10 4250 105 108 117 12 4130 105 108 116 12 4060 105 108 116 11 3990 105 108 116 11 3930
116 116 125 8 5930 114 114 124 8 5510 110 113 122 10 4910 106 111 119 10 4410 105 108 117 12 4260 105 108 116 12 4190 105 108 116 11 4110 105 108 116 11 4050
116 116 125 8 7420 114 114 124 8 6860 112 113 122 8 5800 109 111 119 10 5000 105 108 117 11 4530 105 108 116 11 4430 105 108 116 11 4340 105 108 116 11 4260
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
113 113 122 8 9020 111 111 119 8 7260 108 108 117 8 5830 107 108 116 9 5000 105 108 116 9 4720 105 108 116 10 4600
TAKEOFF FLAPS 20°
TEMP
108 108 117 7 10610 108 108 116 7 7270 108 108 116 6 6180 108 108 116 6 5410
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
PERFORMANCE
TAKEOFF (FLAPS 20°) — 5000 FEET
P-37.1
PERFORMANCE
TAKEOFF (FLAPS 20°) — 5000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-38
°C
ANTI-ICE OFF
104
40
86.3
95
35
87.5
86
30
88.9
77
25
90.3
68
20
91.8
59
15
93.2
57.2
14
93.2
50
10
92.6
41
5
91.7
32
0
90.9
23
-5
90.1
14
-10
89.3
EFFECTIVITY CODE
B C D E
CL-126B October 2004
TAKEOFF SPEEDS, TARGET PITCH ATTITUDE AND DISTANCES — APR ARMED
21,500
V1 VR V2 PITCH DIST
21,000
V1 VR V2 PITCH DIST
20,000
V1 VR V2 PITCH DIST
19,000
V1 VR V2 PITCH DIST
18,000
V1 VR V2 PITCH DIST
17,000
V1 VR V2 PITCH DIST
16,000
V1 VR V2 PITCH DIST
15,000
V1 VR V2 PITCH DIST
14
32
50
68
86
104
-10 0 10 20 30 40 TAKEOFF SPEEDS (KIAS), TARGET PITCH ATTITUDE (°) AND DISTANCE (FEET) 116 116 125 8 5690 114 114 124 8 5300 110 113 122 10 4730 106 111 119 10 4250 105 108 117 12 4140 105 108 116 12 4060 105 108 116 12 4000 105 108 116 11 3940
116 116 125 8 5910 114 114 124 8 5500 110 113 122 10 4910 106 111 119 10 4410 105 108 117 12 4280 105 108 116 12 4200 105 108 116 11 4130 105 108 116 11 4070
116 116 125 8 6160 114 114 124 8 5710 110 113 122 10 5100 106 111 119 10 4580 105 108 117 12 4420 105 108 116 12 4340 105 108 116 11 4260 105 108 116 11 4190
116 116 125 8 8720 114 114 124 8 8110 113 113 122 8 6760 110 111 119 8 5670 106 108 117 9 4890 105 108 116 11 4670 105 108 116 10 4570 105 108 116 10 4470
TAKEOFF FLAPS 8°
°F
°C WT (LB) DATA
110 111 119 7 8750 108 108 117 7 6820 108 108 116 7 5610 106 108 116 8 5140 105 108 116 9 4860
TAKEOFF FLAPS 20°
TEMP
108 108 116 7 9440 108 108 116 6 7380 108 108 116 6 6330
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, autospoilers armed, & APR armed.
CL-126B October 2004
EFFECTIVITY CODE
E
PERFORMANCE
TAKEOFF (FLAPS 20°) — 6000 FEET
P-39.1
PERFORMANCE
TAKEOFF (FLAPS 20°) — 6000 FEET TAKEOFF THRUST (N1) SETTING TAKEOFF THRUST — %N1 TEMPERATURE
TAKEOFF FLAPS 20°
TAKEOFF FLAPS 8°
°F
P-40
°C
ANTI-ICE OFF
104
40
86.1
95
35
87.3
86
30
88.6
77
25
90.1
68
20
91.6
59
15
93.0
51.8
11
93.9
50
10
93.8
41
5
92.9
32
0
92.1
23
-5
91.3
14
-10
90.5
EFFECTIVITY CODE
B C D E
CL-126B October 2004
51 49 47 45 43 41 39 37 35 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5 3 1 CLIMB SPEED:
WEIGHT 21,500 LB
CL-126B October 2004
PRESSURE ALTITUDE — 1000 FEET
ISA -10°C Dist Fuel N.M. Lb Time Min.
36.9 228.5 1004.6 38.2 23.9 143.8 776.3 25.9 19.4 114.1 688.2 21.4 16.6 95.7 628.4 18.5 14.5 82.3 581.1 16.5 13.0 72.4 542.6 14.9 11.8 64.3 508.2 13.6 10.5 56.1 469.5 12.2 9.4 49.0 432.6 10.9 8.5 43.1 398.9 9.8 7.7 38.3 367.7 8.8 7.0 34.1 337.9 7.9 6.3 30.3 309.3 7.1 5.7 27.0 281.6 6.3 5.2 24.0 254.7 5.6 4.7 21.3 228.2 4.9 4.1 18.7 201.6 4.3 3.6 16.0 174.1 3.7 3.0 13.3 145.5 3.1 2.4 10.5 115.8 2.5 1.8 7.6 84.6 1.8 1.1 4.6 51.8 1.1 0.4 1.5 17.6 0.4 250 KIAS up to 32,000 feet. 0.70 MI above 32,000 feet.
Time Min.
EFFECTIVITY CODE
B C D E
P-41
1066.3 842.4 751.3 688.9 639.4 598.8 561.3 517.8 476.4 438.0 402.0 367.7 334.9 303.2 272.2 241.8 211.8 182.0 152.1 121.2 88.5 54.1 18.4
Fuel Lb
42.8 29.9 25.0 22.1 20.1 18.3 16.3 14.5 12.8 11.4 10.1 8.9 7.9 6.9 5.9 5.0 4.2 3.4 2.6 1.8 1.1 0.4
274.2 185.4 152.3 132.2 118.4 106.4 92.5 79.9 69.2 60.2 52.3 45.3 39.1 33.4 28.3 23.6 19.3 15.3 11.6 8.2 4.9 1.6
1180.5 943.9 846.1 780.4 730.2 683.3 626.0 570.3 519.8 473.3 429.7 388.2 348.3 309.6 271.9 235.1 198.8 162.9 127.4 92.0 56.2 19.1
ISA +10°C Time Dist Fuel Min. N.M. Lb
CLIMB
240.8 158.8 128.4 109.3 95.5 85.2 76.3 66.7 58.4 51.3 45.2 39.8 34.9 30.6 26.7 23.1 19.8 16.7 13.8 10.9 7.9 4.8 1.6
ISA Dist N.M.
41.9 32.4 28.1 25.4 23.0 20.3 17.7 15.6 13.7 12.1 10.6 9.2 8.0 6.8 5.8 4.8 3.8 2.9 2.0 1.2 0.4
267.0 201.0 171.1 152.5 136.3 117.1 99.6 85.3 73.4 63.2 54.3 46.5 39.5 33.2 27.5 22.3 17.5 13.1 9.1 5.3 1.7
1196.8 1015.4 923.9 860.5 801.4 727.4 655.8 592.6 535.8 483.5 434.4 387.7 342.9 299.8 257.9 216.9 176.8 137.1 97.8 58.7 19.6
ISA +15°C Time Dist Fuel Min. N.M. Lb
48.8 39.4 35.1 31.4 26.9 22.9 19.7 17.1 14.9 12.9 11.2 9.6 8.2 6.8 5.6 4.5 3.4 2.4 1.4 0.4
312.2 247.0 216.4 190.6 158.9 131.1 109.8 92.9 78.9 67.1 56.8 47.9 40.0 32.9 26.6 20.8 15.5 10.7 6.2 2.0
1375.6 1191.4 1095.1 1007.5 894.2 788.7 701.6 626.9 560.3 499.4 442.7 389.2 338.5 290.0 243.1 197.5 152.7 108.5 64.8 21.4
ISA +20°C Time Dist Fuel Min. N.M. Lb
CLIMB PERFORMANCE TWO ENGINE
P-42 51 49 47 45 43 41 39 37 35 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5 3 1 CLIMB SPEED:
WEIGHT 21,000 LB
PRESSURE ALTITUDE — 1000 FEET
ISA -10°C Dist Fuel N.M. Lb Time Min.
31.4 193.2 896.0 33.1 22.5 134.7 738.0 24.4 18.5 108.8 661.2 20.4 15.9 91.9 606.3 17.8 14.0 79.4 561.9 15.9 12.6 70.0 525.4 14.4 11.4 62.3 492.5 13.2 10.2 54.3 455.3 11.8 9.2 47.5 419.8 10.6 8.3 41.9 387.2 9.5 7.5 37.1 357.0 8.6 6.8 33.1 328.2 7.7 6.2 29.5 300.4 6.9 5.6 26.2 273.5 6.2 5.0 23.3 247.3 5.5 4.5 20.6 221.7 4.8 4.0 18.1 195.8 4.2 3.5 15.6 169.1 3.6 2.9 12.9 141.3 3.0 2.4 10.2 112.4 2.4 1.7 7.4 82.1 1.8 1.1 4.5 50.2 1.1 0.4 1.5 17.1 0.4 250 KIAS up to 32,000 feet. 0.70 MI above 32,000 feet.
Time Min.
207.1 149.1 122.5 105.0 92.1 82.3 73.8 64.6 56.6 49.8 43.8 38.6 33.9 29.7 25.9 22.4 19.2 16.2 13.4 10.6 7.7 4.6 1.5
ISA Dist N.M.
959.8 801.3 721.6 664.3 617.8 579.2 543.4 501.7 461.8 424.8 390.0 356.9 325.1 294.3 264.3 234.8 205.7 176.7 147.7 117.7 85.9 52.5 17.8
Fuel Lb
37.8 28.2 23.9 21.2 19.3 17.7 15.8 14.0 12.4 11.0 9.8 8.7 7.6 6.6 5.7 4.9 4.0 3.3 2.5 1.8 1.1 0.4
240.4 174.7 145.5 126.9 113.9 102.5 89.3 77.2 67.0 58.2 50.6 43.9 37.9 32.4 27.4 22.9 18.7 14.8 11.3 7.9 4.7 1.6
1073.6 898.6 812.1 751.3 704.0 659.4 604.7 551.5 503.1 458.4 416.3 376.2 337.7 300.3 263.8 228.1 193.0 158.2 123.6 89.3 54.5 18.6
ISA +10°C Time Dist Fuel Min. N.M. Lb
CLIMB
38.5 30.7 26.8 24.3 22.1 19.5 17.1 15.0 13.2 11.7 10.2 8.9 7.7 6.6 5.6 4.6 3.7 2.8 2.0 1.2 0.4
244.0 190.4 163.4 146.0 130.7 112.6 96.0 82.3 70.9 61.1 52.6 45.0 38.2 32.1 26.6 21.6 17.0 12.7 8.8 5.1 1.7
1115.7 968.2 885.5 826.4 770.6 700.6 632.6 572.4 517.9 467.7 420.4 375.4 332.2 290.5 250.0 210.4 171.5 133.0 94.9 57.0 19.0
ISA +15°C Time Dist Fuel Min. N.M. Lb
45.1 37.3 33.3 29.9 25.7 22.0 19.0 16.5 14.3 12.5 10.8 9.3 7.9 6.6 5.4 4.3 3.3 2.3 1.3 0.4
287.5 232.9 205.0 181.1 151.6 125.6 105.5 89.4 76.1 64.8 54.9 46.3 38.7 31.9 25.7 20.2 15.1 10.3 6.0 1.9
1284.9 1130.7 1042.9 961.7 856.3 757.7 675.4 604.4 540.8 482.4 427.9 376.5 327.6 280.7 235.4 191.3 148.0 105.2 62.8 20.8
ISA +20°C Time Dist Fuel Min. N.M. Lb
CLIMB PERFORMANCE TWO ENGINE
EFFECTIVITY CODE
B C D E
CL-126B October 2004
51 49 47 45 43 41 39 37 35 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5 3 1 CLIMB SPEED:
WEIGHT 20,500 LB
CL-126B October 2004
PRESSURE ALTITUDE — 1000 FEET
ISA -10°C Dist Fuel N.M. Lb Time Min.
28.0 171.2 823.5 29.8 21.2 126.9 703.5 23.1 17.7 103.9 635.5 19.6 15.3 88.3 585.0 17.1 13.5 76.6 543.3 15.3 12.2 67.7 508.6 13.9 11.1 60.3 477.1 12.7 9.9 52.6 441.3 11.4 8.9 46.1 407.1 10.3 8.0 40.6 375.7 9.2 7.3 36.0 346.5 8.3 6.6 32.1 318.5 7.5 6.0 28.6 291.6 6.7 5.4 25.4 265.5 6.0 4.9 22.6 240.1 5.3 4.4 20.0 215.2 4.7 3.9 17.6 190.0 4.1 3.4 15.1 164.1 3.5 2.9 12.6 137.1 2.9 2.3 9.9 109.1 2.3 1.7 7.2 79.7 1.7 1.0 4.3 48.7 1.0 0.3 1.4 16.5 0.4 250 KIAS up to 32,000 feet. 0.70 MI above 32,000 feet.
Time Min.
EFFECTIVITY CODE
B C D E
P-43
886.4 764.1 693.4 640.5 596.8 560.2 525.9 485.8 447.5 411.9 378.2 346.2 315.4 285.6 256.5 227.9 199.6 171.5 143.4 114.2 83.4 51.0 17.3
Fuel Lb
34.3 26.7 22.9 20.4 18.6 17.0 15.2 13.5 12.0 10.7 9.5 8.4 7.4 6.4 5.5 4.7 3.9 3.2 2.4 1.7 1.1 0.4
217.1 165.2 139.1 121.9 109.6 98.7 86.1 74.5 64.7 56.3 49.0 42.5 36.7 31.4 26.6 22.2 18.1 14.4 10.9 7.7 4.6 1.5
995.5 857.0 779.7 723.3 678.6 636.1 584.0 533.1 486.7 443.7 403.2 364.5 327.2 291.1 255.8 221.2 187.2 153.4 120.0 86.7 52.9 18.0
ISA +10°C Time Dist Fuel Min. N.M. Lb
CLIMB
185.3 140.7 117.1 100.9 88.8 79.4 71.3 62.5 54.8 48.2 42.5 37.4 32.9 28.8 25.1 21.8 18.6 15.7 13.0 10.3 7.5 4.5 1.5
ISA Dist N.M.
35.7 29.2 25.7 23.3 21.2 18.8 16.5 14.5 12.8 11.3 9.9 8.7 7.5 6.4 5.4 4.5 3.6 2.7 1.9 1.1 0.4
225.6 180.7 156.1 139.8 125.4 108.2 92.4 79.4 68.4 59.0 50.8 43.5 37.0 31.1 25.8 20.9 16.5 12.3 8.5 5.0 1.6
1048.2 924.3 849.0 793.6 741.0 674.7 610.2 552.7 500.5 452.2 406.7 363.3 321.7 281.4 242.2 203.9 166.2 129.0 92.1 55.3 18.4
ISA +15°C Time Dist Fuel Min. N.M. Lb
42.0 35.3 31.7 28.5 24.6 21.1 18.2 15.9 13.8 12.0 10.4 9.0 7.6 6.4 5.3 4.2 3.2 2.2 1.3 0.4
266.8 220.1 194.5 172.3 144.8 120.4 101.4 86.1 73.4 62.5 53.0 44.7 37.4 30.8 24.9 19.5 14.6 10.0 5.8 1.8
1206.6 1074.5 993.9 918.4 820.2 727.9 650.1 582.5 521.7 465.8 413.5 364.0 316.9 271.7 227.9 185.3 143.3 101.9 60.8 20.1
ISA +20°C Time Dist Fuel Min. N.M. Lb
CLIMB PERFORMANCE TWO ENGINE
P-44 51 49 47 45 43 41 39 37 35 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5 3 1 CLIMB SPEED:
WEIGHT 20,000 LB
PRESSURE ALTITUDE — 1000 FEET
ISA -10°C Dist Fuel N.M. Lb Time Min.
ISA Dist N.M. Fuel Lb
25.6 155.6 768.9 27.3 169.5 829.6 20.1 119.9 672.0 21.9 133.1 730.0 17.0 99.3 611.2 18.7 112.0 666.5 14.8 84.9 564.4 16.5 97.0 617.6 13.1 73.9 525.1 14.8 85.6 576.4 11.8 65.4 492.1 13.5 76.7 541.5 10.7 58.3 461.9 12.3 68.9 508.8 9.6 51.0 427.6 11.1 60.5 470.3 8.6 44.6 394.6 9.9 53.0 433.4 7.8 39.4 364.3 8.9 46.7 399.1 7.0 34.9 336.0 8.1 41.2 366.6 6.4 31.1 309.0 7.2 36.3 335.6 5.8 27.7 282.9 6.5 31.9 305.9 5.3 24.7 257.6 5.8 28.0 277.0 4.7 21.9 233.0 5.1 24.4 248.8 4.3 19.4 208.8 4.5 21.1 221.1 3.8 17.1 184.4 3.9 18.1 193.6 3.3 14.7 159.2 3.4 15.3 166.4 2.8 12.2 133.0 2.8 12.6 139.1 2.2 9.6 105.8 2.3 10.0 110.8 1.6 6.9 77.3 1.7 7.2 80.9 1.0 4.2 47.3 1.0 4.4 49.4 0.3 1.4 16.1 0.3 1.5 16.8 250 KIAS up to 32,000 feet. 0.70 MI above 32,000 feet.
Time Min.
31.6 25.4 22.0 19.6 17.9 16.4 14.7 13.0 11.6 10.3 9.2 8.1 7.2 6.2 5.4 4.6 3.8 3.1 2.4 1.7 1.0 0.3
199.3 156.6 133.0 117.0 105.4 95.0 83.0 71.9 62.5 54.5 47.4 41.2 35.5 30.4 25.8 21.5 17.6 14.0 10.6 7.5 4.5 1.5
932.8 818.6 748.8 696.2 654.0 613.6 563.8 515.2 470.6 429.3 390.3 353.0 317.0 282.0 247.9 214.4 181.5 148.8 116.3 84.1 51.3 17.5
ISA +10°C Time Dist Fuel Min. N.M. Lb
CLIMB
33.4 27.8 24.6 22.3 20.4 18.1 15.9 14.0 12.4 10.9 9.6 8.4 7.3 6.2 5.2 4.3 3.5 2.6 1.9 1.1 0.4
210.3 171.7 149.2 133.9 120.3 104.0 89.0 76.6 66.1 57.0 49.1 42.1 35.8 30.1 25.0 20.3 16.0 12.0 8.3 4.8 1.6
989.6 883.1 814.2 762.2 712.5 649.6 588.3 533.4 483.5 437.1 393.3 351.5 311.3 272.4 234.6 197.5 161.1 125.0 89.2 53.6 17.9
ISA +15°C Time Dist Fuel Min. N.M. Lb
39.3 33.5 30.1 27.2 23.5 20.2 17.5 15.3 13.3 11.6 10.1 8.7 7.4 6.2 5.1 4.1 3.1 2.2 1.3 0.4
249.0 208.2 184.7 163.9 138.3 115.4 97.4 82.9 70.7 60.3 51.2 43.2 36.1 29.8 24.1 18.9 14.1 9.7 5.6 1.8
1137.4 1022.2 947.9 877.5 785.9 699.2 625.7 561.3 503.2 449.7 399.4 351.8 306.4 262.8 220.5 179.3 138.8 98.7 58.9 19.5
ISA +20°C Time Dist Fuel Min. N.M. Lb
CLIMB PERFORMANCE TWO ENGINE
EFFECTIVITY CODE
B C D E
CL-126B October 2004
51 49 47 45 43 41 39 37 35 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5 3 1 CLIMB SPEED:
WEIGHT 19,000 LB
CL-126B October 2004
PRESSURE ALTITUDE — 1000 FEET
ISA -10°C Dist Fuel N.M. Lb Time Min.
30.7 189.7 824.5 32.1 22.1 133.6 685.4 23.8 18.2 107.8 615.5 19.8 15.6 91.0 565.5 17.2 13.7 78.5 525.0 15.3 12.2 68.7 490.1 13.7 11.0 61.0 460.2 12.5 10.0 54.5 432.5 11.5 9.0 47.7 400.8 10.3 8.1 41.8 370.3 9.3 7.3 36.9 342.0 8.4 6.6 32.8 315.7 7.6 6.0 29.3 290.3 6.8 5.5 26.1 265.9 6.1 4.9 23.2 242.1 5.4 4.5 20.6 219.0 4.8 4.0 18.3 196.2 4.2 3.6 16.0 173.3 3.7 3.1 13.8 149.6 3.2 2.6 11.4 124.9 2.7 2.1 9.0 99.4 2.1 1.5 6.5 72.5 1.6 0.9 3.9 44.4 1.0 0.3 1.3 15.1 0.3 250 KIAS up to 32,000 feet. 0.70 MI above 32,000 feet.
Time Min.
EFFECTIVITY CODE
B C D E
P-45
880.4 741.1 668.5 616.2 573.8 537.1 505.5 475.5 440.1 406.0 374.1 343.9 315.0 287.2 260.2 233.7 207.7 181.9 156.3 130.6 104.0 75.9 46.4 15.8
Fuel Lb
39.3 27.6 23.0 20.2 18.1 16.6 15.2 13.6 12.1 10.8 9.7 8.6 7.6 6.7 5.8 5.0 4.3 3.6 2.9 2.2 1.6 1.0 0.3
252.9 172.8 141.4 121.9 107.9 97.4 88.0 77.1 67.0 58.3 50.9 44.3 38.5 33.3 28.5 24.2 20.2 16.5 13.1 10.0 7.0 4.2 1.4
1024.9 832.6 748.8 690.8 644.8 606.9 570.3 524.9 480.5 439.5 401.3 365.1 330.4 296.9 264.3 232.5 201.2 170.3 139.7 109.2 78.9 48.2 16.4
ISA +10°C Time Dist Fuel Min. N.M. Lb
CLIMB
202.0 146.5 120.0 102.6 89.7 79.4 71.4 64.3 56.5 49.6 43.8 38.6 34.0 29.9 26.3 22.9 19.8 17.0 14.3 11.8 9.4 6.8 4.1 1.4
ISA Dist N.M.
38.7 29.6 25.3 22.5 20.5 18.8 16.7 14.7 13.0 11.5 10.2 8.9 7.8 6.8 5.8 4.9 4.1 3.2 2.5 1.7 1.0 0.3
248.6 185.3 155.5 136.3 122.8 110.6 96.0 82.4 71.1 61.5 53.2 45.8 39.3 33.5 28.2 23.4 19.0 15.0 11.2 7.8 4.5 1.5
1046.9 889.9 807.5 748.9 702.9 658.4 601.8 546.4 496.4 450.5 407.8 367.3 328.6 291.2 255.0 219.7 185.1 151.0 117.2 83.7 50.3 16.8
ISA +15°C Time Dist Fuel Min. N.M. Lb
44.8 34.8 30.2 27.3 24.7 21.5 18.6 16.2 14.2 12.4 10.8 9.4 8.1 6.9 5.8 4.8 3.8 2.9 2.0 1.2 0.4
289.4 219.2 187.0 166.8 148.7 126.2 106.0 89.9 76.7 65.6 56.0 47.7 40.3 33.7 27.8 22.5 17.7 13.2 9.1 5.2 1.7
1196.3 1018.2 927.0 863.4 801.9 721.6 645.0 579.0 520.7 467.6 418.5 372.1 328.1 286.0 245.5 206.2 167.7 129.9 92.4 55.2 18.3
ISA +20°C Time Dist Fuel Min. N.M. Lb
CLIMB PERFORMANCE TWO ENGINE
P-46 51 49 47 45 43 41 39 37 35 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5 3 1 CLIMB SPEED:
WEIGHT 18,000 LB
PRESSURE ALTITUDE — 1000 FEET
ISA -10°C Dist Fuel N.M. Lb Time Min.
ISA Dist N.M. Fuel Lb
24.7 151.3 703.2 26.2 163.7 756.4 19.6 117.6 619.5 21.1 129.5 670.4 16.5 97.6 565.3 18.0 108.8 613.7 14.3 83.5 523.3 15.8 94.1 569.7 12.7 72.6 487.9 14.1 82.8 532.5 11.3 63.8 456.6 12.8 73.7 499.7 10.2 56.8 429.4 11.7 66.3 470.9 9.3 50.8 404.1 10.7 59.9 443.5 8.4 44.6 374.9 9.6 52.7 410.9 7.6 39.1 346.6 8.7 46.4 379.4 6.8 34.6 320.4 7.8 40.9 349.9 6.2 30.8 295.8 7.1 36.1 321.8 5.6 27.4 272.1 6.4 31.8 294.9 5.1 24.4 249.2 5.7 28.0 269.0 4.6 21.8 227.0 5.1 24.6 243.7 4.2 19.3 205.3 4.5 21.5 219.0 3.8 17.1 184.0 4.0 18.6 194.7 3.3 15.0 162.4 3.5 15.9 170.5 2.9 12.9 140.2 3.0 13.4 146.5 2.4 10.7 117.1 2.5 11.1 122.4 2.0 8.5 93.1 2.0 8.8 97.5 1.4 6.1 68.0 1.5 6.4 71.1 0.9 3.7 41.6 0.9 3.8 43.5 0.3 1.2 14.1 0.3 1.3 14.8 250 KIAS up to 32,000 feet. 0.70 MI above 32,000 feet.
Time Min.
31.3 199.4 864.2 24.5 152.8 751.7 20.9 128.3 686.3 18.5 111.7 637.1 16.7 99.4 596.6 15.3 90.0 562.5 14.1 81.5 529.2 12.7 71.5 488.0 11.3 62.2 447.2 10.1 54.3 409.6 9.0 47.4 374.4 8.0 41.4 340.9 7.1 36.0 308.7 6.3 31.1 277.6 5.5 26.7 247.2 4.7 22.6 217.5 4.0 18.9 188.3 3.3 15.5 159.5 2.7 12.3 130.8 2.1 9.3 102.4 1.5 6.6 74.0 0.9 3.9 45.2 0.3 1.3 15.4
ISA +10°C Time Dist Fuel Min. N.M. Lb
CLIMB
32.6 26.5 23.0 20.6 18.9 17.3 15.4 13.6 12.1 10.7 9.5 8.3 7.3 6.3 5.4 4.6 3.8 3.0 2.3 1.6 1.0 0.3
207.4 165.3 141.2 124.7 112.7 101.7 88.5 76.3 65.9 57.1 49.4 42.7 36.7 31.2 26.3 21.8 17.7 14.0 10.5 7.3 4.2 1.4
910.6 805.8 739.2 688.6 647.8 607.7 556.9 506.7 461.1 419.0 379.7 342.3 306.4 271.8 238.1 205.3 173.0 141.2 109.7 78.4 47.1 15.7
ISA +15°C Time Dist Fuel Min. N.M. Lb
37.9 31.0 27.3 24.8 22.5 19.7 17.1 15.0 13.1 11.5 10.0 8.7 7.5 6.4 5.4 4.4 3.5 2.7 1.9 1.1 0.4
242.6 194.8 168.5 151.0 135.1 115.3 97.4 82.9 70.9 60.8 52.0 44.3 37.5 31.4 26.0 21.0 16.5 12.3 8.5 4.9 1.6
1038.2 916.8 842.2 787.1 733.1 662.5 594.4 535.1 482.2 433.8 388.7 346.0 305.4 266.5 228.9 192.3 156.6 121.3 86.3 51.6 17.1
ISA +20°C Time Dist Fuel Min. N.M. Lb
CLIMB PERFORMANCE TWO ENGINE
EFFECTIVITY CODE
B C D E
CL-126B October 2004
51 49 47 45 43 41 39 37 35 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5 3 1 CLIMB SPEED:
WEIGHT 17,000 LB
CL-126B October 2004
PRESSURE ALTITUDE — 1000 FEET
ISA -10°C Dist Fuel N.M. Lb Time Min.
ISA Dist N.M. Fuel Lb
EFFECTIVITY CODE
B C D E
P-47
40.1 26.7 22.0 19.1 17.0 15.4 14.2 13.0 11.7 10.5 9.4 8.4 7.5 6.6 5.8 5.1 4.4 3.7 3.1 2.5 1.9 1.4 0.8 0.3
260.6 169.0 136.5 116.6 102.4 91.4 83.0 75.2 66.1 57.7 50.4 44.1 38.5 33.5 29.0 24.9 21.1 17.6 14.4 11.5 8.7 6.1 3.7 1.2
958.3 760.8 682.4 629.2 587.0 551.0 520.2 490.1 452.5 415.3 380.8 348.3 317.4 287.6 258.7 230.6 202.9 175.8 148.9 122.2 95.6 69.1 42.2 14.4
ISA +10°C Time Dist Fuel Min. N.M. Lb
CLIMB
28.4 176.4 731.5 30.0 189.9 785.3 21.2 128.9 623.3 22.6 140.3 671.8 17.5 104.9 563.5 18.9 115.7 609.8 15.0 88.7 519.6 16.4 98.9 563.8 13.2 76.6 483.7 14.5 86.4 526.1 11.7 67.0 452.6 13.1 76.4 493.4 10.5 59.1 424.5 11.8 68.2 463.8 9.5 52.7 399.8 10.8 61.5 437.7 8.7 47.3 376.6 9.9 55.6 412.6 7.8 41.5 349.7 9.0 49.0 382.8 7.1 36.5 323.6 8.1 43.2 353.7 6.4 32.3 299.3 7.3 38.1 326.4 5.8 28.7 276.4 6.6 33.7 300.3 5.3 25.6 254.4 5.9 29.7 275.4 4.8 22.8 233.0 5.3 26.2 251.2 4.3 20.3 212.3 4.8 23.0 227.7 3.9 18.1 192.0 4.2 20.1 204.7 3.5 16.0 172.0 3.7 17.4 181.9 3.1 14.1 151.8 3.2 14.9 159.4 2.7 12.1 131.0 2.8 12.6 137.0 2.3 10.0 109.4 2.3 10.4 114.4 1.8 7.9 87.0 1.9 8.2 91.1 1.3 5.7 63.5 1.4 5.9 66.4 0.8 3.4 38.8 0.8 3.6 40.6 0.3 1.2 13.2 0.3 1.2 13.8 250 KIAS up to 32,000 feet. 0.70 MI above 32,000 feet.
Time Min.
39.2 28.4 23.8 21.0 18.9 17.3 15.9 14.2 12.6 11.2 9.9 8.8 7.7 6.8 5.9 5.1 4.3 3.5 2.8 2.2 1.5 0.9 0.3
254.6 179.6 148.3 128.3 113.9 103.2 93.4 81.5 70.4 61.0 52.9 45.9 39.7 34.1 29.1 24.5 20.3 16.5 13.0 9.8 6.8 3.9 1.3
976.6 809.6 731.9 676.6 632.5 596.1 560.1 514.3 468.8 427.3 388.8 352.7 318.2 285.1 253.0 221.8 191.3 161.3 131.7 102.4 73.2 44.0 14.7
ISA +15°C Time Dist Fuel Min. N.M. Lb
45.0 32.9 27.8 24.7 22.5 20.5 18.0 15.7 13.8 12.1 10.6 9.3 8.1 7.0 6.0 5.0 4.1 3.3 2.5 1.8 1.0 0.3
294.2 209.8 174.0 152.0 136.8 122.7 105.3 89.3 76.3 65.4 56.2 48.1 41.1 34.8 29.2 24.1 19.5 15.4 11.5 7.9 4.6 1.5
1111.4 919.0 828.0 765.6 717.5 669.9 607.6 547.0 493.7 445.7 401.5 360.2 321.0 283.6 247.6 212.9 179.0 145.8 113.0 80.5 48.1 16.0
ISA +20°C Time Dist Fuel Min. N.M. Lb
CLIMB PERFORMANCE TWO ENGINE
P-48 51 49 47 45 43 41 39 37 35 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5 3 1 CLIMB SPEED:
WEIGHT 16,000 LB
PRESSURE ALTITUDE — 1000 FEET
ISA -10°C ISA Time Dist Fuel Time Dist Fuel Min. N.M. Lb Min. N.M. Lb 34.9 219.3 788.2 23.1 142.0 626.9 24.5 153.8 674.5 18.6 112.6 559.9 19.9 123.0 603.9 15.8 94.1 513.9 17.1 104.0 555.9 13.7 80.7 477.4 15.0 90.1 517.7 12.1 70.2 446.4 13.4 79.2 485.1 10.8 61.7 418.8 12.0 70.3 456.0 9.7 54.6 393.5 10.9 62.9 429.4 8.8 48.8 371.1 10.0 56.9 405.7 8.1 43.9 349.9 9.2 51.5 382.8 7.3 38.6 325.2 8.3 45.5 355.5 6.6 34.0 301.2 7.5 40.1 328.8 5.9 30.1 278.7 6.8 35.4 303.5 5.4 26.8 257.5 6.1 31.3 279.4 4.9 23.9 237.0 5.5 27.7 256.3 4.5 21.3 217.2 5.0 24.4 233.9 4.0 19.0 197.9 4.4 21.4 212.1 3.6 16.9 178.9 3.9 18.7 190.7 3.3 14.9 160.3 3.5 16.2 169.5 2.9 13.1 141.5 3.0 13.9 148.5 2.5 11.3 122.1 2.6 11.7 127.6 2.1 9.3 101.9 2.2 9.7 106.6 1.7 7.4 81.0 1.7 7.6 84.8 1.2 5.3 59.1 1.3 5.5 61.9 0.8 3.2 36.2 0.8 3.3 37.8 0.3 1.1 12.3 0.3 1.1 12.8 250 KIAS up to 32,000 feet. 0.70 MI above 32,000 feet. 30.5 23.4 19.8 17.4 15.6 14.2 13.0 12.0 10.8 9.7 8.7 7.8 6.9 6.1 5.4 4.7 4.1 3.5 2.9 2.3 1.8 1.3 0.8 0.3
195.6 147.2 122.6 106.1 93.7 84.0 76.3 69.3 61.1 53.3 46.7 40.9 35.7 31.1 26.9 23.1 19.6 16.4 13.4 10.7 8.1 5.7 3.4 1.1
784.8 680.2 620.7 576.5 539.7 507.8 480.0 452.7 418.6 384.6 353.0 323.1 294.6 267.2 240.5 214.4 188.8 163.6 138.6 113.8 89.0 64.4 39.3 13.4
ISA +10°C Time Dist Fuel Min. N.M. Lb
CLIMB
31.6 25.1 21.5 19.1 17.3 15.9 14.6 13.1 11.6 10.3 9.2 8.1 7.2 6.3 5.5 4.7 4.0 3.3 2.6 2.0 1.4 0.8 0.3
203.5 158.0 133.5 116.6 104.0 94.4 85.6 74.9 64.9 56.3 48.9 42.5 36.7 31.6 27.0 22.7 18.9 15.4 12.1 9.1 6.3 3.7 1.2
827.8 726.5 665.4 618.7 580.0 547.5 515.2 473.9 432.7 395.0 359.8 326.7 295.0 264.5 234.9 206.0 177.8 150.0 122.5 95.2 68.1 40.9 13.7
ISA +15°C Time Dist Fuel Min. N.M. Lb
36.5 29.0 25.0 22.3 20.4 18.7 16.5 14.4 12.7 11.1 9.8 8.6 7.5 6.5 5.5 4.7 3.8 3.1 2.3 1.6 1.0 0.3
236.3 184.1 155.9 137.2 123.8 111.5 96.0 81.8 70.0 60.2 51.8 44.5 38.0 32.2 27.0 22.4 18.1 14.3 10.7 7.3 4.2 1.4
939.6 820.4 748.7 695.6 653.5 611.5 556.3 502.3 454.3 410.9 370.7 332.9 297.0 262.6 229.5 197.4 166.1 135.3 104.9 74.7 44.7 14.8
ISA +20°C Time Dist Fuel Min. N.M. Lb
CLIMB PERFORMANCE TWO ENGINE
EFFECTIVITY CODE
B C D E
CL-126B October 2004
CL-126B October 2004
EFFECTIVITY CODE
B C D E
P-49
262.2 172.4 140.3 120.3 105.8 94.7 86.2 78.3 68.6 59.6 51.8 45.1 39.2 33.9 29.2 24.9 21.0 17.5 14.2 11.2 8.4 5.8 3.4 1.1
903.8 726.1 654.3 604.6 564.6 530.6 501.6 472.6 435.4 398.2 363.9 331.9 301.6 272.5 244.5 217.3 190.7 164.6 138.9 113.5 88.3 63.1 38.0 12.7
39.9 27.0 22.3 19.4 17.4 15.8 14.5 13.4 12.0 10.7 9.5 8.5 7.5 6.6 5.8 5.1 4.3 3.7 3.0 2.4 1.9 1.3 0.8 0.3
859.5 682.0 612.0 564.8 527.2 495.1 466.6 441.7 416.9 385.9 355.0 326.1 298.8 272.6 247.3 222.7 198.7 175.0 151.7 128.6 105.6 82.6 59.7 36.5 12.4
38.9 25.5 20.7 17.9 15.8 14.3 13.0 12.0 11.1 10.0 8.9 8.0 7.2 6.4 5.7 5.0 4.4 3.8 3.2 2.7 2.2 1.7 1.2 0.7 0.2
254.1 162.2 130.0 110.4 96.4 85.6 76.9 70.0 63.7 56.2 49.2 43.1 37.7 33.0 28.8 24.9 21.4 18.2 15.2 12.5 9.9 7.5 5.3 3.2 1.1
ISA +15°C Time Dist Fuel Min. N.M. Lb
ISA +10°C Time Dist Fuel Min. N.M. Lb
CLIMB
ISA -10°C ISA Time Dist Fuel Time Dist Fuel Min. N.M. Lb Min. N.M. Lb 25.4 157.5 631.0 27.4 173.8 684.7 51 19.7 120.7 553.9 21.0 131.2 596.4 49 16.5 99.6 505.7 17.7 109.1 545.6 47 14.2 84.7 468.8 15.4 93.8 507.0 45 12.5 73.4 438.0 13.7 82.0 474.6 43 11.1 64.3 410.9 12.2 72.5 446.1 41 9.9 56.7 386.4 11.1 64.6 420.3 39 9.0 50.3 363.6 10.1 57.9 396.3 37 8.2 45.1 343.3 9.3 52.5 374.9 35 7.5 40.6 324.0 8.5 47.5 354.0 33 6.7 35.7 301.4 7.7 42.0 329.0 31 6.1 31.5 279.3 7.0 37.1 304.5 29 5.5 27.9 258.6 6.3 32.8 281.3 27 5.0 24.8 239.0 5.7 29.0 259.1 25 4.6 22.2 220.1 5.1 25.7 237.7 23 4.1 19.8 201.7 4.6 22.6 217.0 21 3.7 17.6 183.7 4.1 19.9 196.8 19 3.4 15.7 166.2 3.7 17.3 177.0 17 3.0 13.9 148.9 3.2 15.0 157.4 15 2.7 12.2 131.4 2.8 12.9 137.9 13 2.3 10.4 113.3 2.4 10.9 118.5 11 2.0 8.7 94.6 2.0 9.0 99.0 9 1.6 6.8 75.2 1.6 7.1 78.8 7 1.2 4.9 54.9 1.2 5.1 57.4 5 0.7 3.0 33.6 0.7 3.1 35.1 3 0.2 1.0 11.4 0.2 1.0 11.9 1 CLIMB SPEED: 250 KIAS up to 32,000 feet. 0.70 MI above 32,000 feet. PRESSURE ALTITUDE — 1000 FEET
WEIGHT 15,000 LB
31.1 25.8 22.5 20.2 18.5 17.0 15.0 13.2 11.6 10.2 9.0 7.9 6.9 6.0 5.1 4.3 3.5 2.8 2.2 1.5 0.9 0.3
199.9 162.7 139.8 123.8 112.0 101.1 87.4 74.7 64.1 55.3 47.6 40.9 35.0 29.7 25.0 20.7 16.8 13.2 9.9 6.8 3.9 1.3
820.3 735.1 676.7 631.3 594.3 557.2 508.2 460.0 417.0 377.7 341.2 306.8 273.9 242.4 211.9 182.4 153.5 125.2 97.1 69.2 41.4 13.8
ISA +20°C Time Dist Fuel Min. N.M. Lb
CLIMB PERFORMANCE TWO ENGINE
CREW NOTES
EFFECTIVITY
P-50
ALL
CL-126B October 2004
LONG RANGE CRUISE TWO ENGINE
WEIGHT — 20,500 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
ISA -10
ALTITUDE — 1000 FEET
CL-126B October 2004
421 .385 418 .377 414 .367 400 .354 384 .341
423 .390 415 .384 414 .372 397 .359 379 .345
TEMPERATURE — °C ISA ISA +10 ISA +15
428 .377 424 .367 410 .354 393 .341
419 .354 402 .341
424 .354 406 .341
TEMPERATURE — °C ISA ISA +10 ISA +15
434 .391 425 .384 424 .372 406 .359 388 .345
433 .371 415 .358 396 .344
420 .359 401 .345
ISA +20
410 .340
ISA +20
LR CRUISE TWO ENGINE
ISA -10
ALTITUDE — 1000 FEET
WEIGHT — 21,000 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
405 .345
EFFECTIVITY CODE
B C D E
P-51
LONG RANGE CRUISE TWO ENGINE
ISA -10
WEIGHT — 19,500 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
ISA -10
ALTITUDE — 1000 FEET
LR CRUISE TWO ENGINE
ALTITUDE — 1000 FEET
WEIGHT — 20,000 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
397 .398 422 .397 414 .391 411 .376 393 .364 374 .349
412 .412 421 .406 415 .396 407 .382 387 .368 369 .353
TEMPERATURE — °C ISA ISA +10 ISA +15
433 .398 424 .390 421 .376 402 .363 383 .349
416 .364 396 .350
TEMPERATURE — °C ISA ISA +10 ISA +15
431 .406 425 .396 416 .381 397 .369 378 .354
EFFECTIVITY CODE
P-52
431 .377 411 .363 391 .349
B C D E
426 .382 406 .368 387 .354
410 .368 391 .354
ISA +20
400 .349
ISA +20
414 .368 395 .354
CL-126B October 2004
LONG RANGE CRUISE TWO ENGINE
WEIGHT — 18,500 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
ISA -10
ALTITUDE — 1000 FEET
CL-126B October 2004
420 .420 418 .413 415 .400 402 .387 381 .372 365 .358
423 .427 415 .421 415 .406 397 .392 376 .378 362 .363
TEMPERATURE — °C ISA ISA +10 ISA +15
428 .414 425 .400 411 .387 390 .372 374 .359
421 .387 399 .373 382 .358
425 .387 404 .373 386 .358
TEMPERATURE — °C ISA ISA +10 ISA +15
433 .427 425 .421 425 .406 407 .392 385 .378 370 .363
416 .392 394 .378 378 .362
421 .393 398 .378 383 .363
ISA +20
408 .373 390 .358
ISA +20
402 .378 387 .363
EFFECTIVITY CODE
B C D E
P-53
LR CRUISE TWO ENGINE
ISA -10
ALTITUDE — 1000 FEET
WEIGHT — 19,000 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
LONG RANGE CRUISE TWO ENGINE
ISA -10
WEIGHT — 17,500 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
ISA -10
ALTITUDE — 1000 FEET
LR CRUISE TWO ENGINE
ALTITUDE — 1000 FEET
WEIGHT — 18,000 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
400 .439 422 .436 417 .427 411 .412 393 .398 371 .384 358 .368
415 .454 419 .445 418 .433 406 .418 387 .404 366 .389 354 .373
TEMPERATURE — °C ISA ISA +10 ISA +15
432 .436 427 .427 421 .412 402 .397 380 .384 366 .367
416 .398 393 .384 379 .368
TEMPERATURE — °C ISA ISA +10 ISA +15
429 .445 428 .433 416 .419 396 .404 375 .389 363 .373
EFFECTIVITY CODE
P-54
431 .412 412 .398 388 .383 375 .368
B C D E
425 .418 405 .404 383 .388 371 .373
409 .403 387 .388 375 .373
ISA +20
397 .384 383 .368
ISA +20
414 .404 392 .389 379 .373
CL-126B October 2004
LONG RANGE CRUISE TWO ENGINE
WEIGHT — 16,500 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
ISA -10
ALTITUDE — 1000 FEET
CL-126B October 2004
422 .462 415 .455 418 .440 400 .424 380 .409 362 .395 350 .378
422 .473 417 .462 414 .446 395 .431 374 .416 358 .400 346 .383
TEMPERATURE — °C ISA ISA +10 ISA +15
425 .455 428 .439 410 .424 389 .409 370 .394 359 .378
419 .424 398 .409 379 .394 367 .378
424 .425 402 .409 383 .394 371 .378
TEMPERATURE — °C ISA ISA +10 ISA +15
432 .473 427 .462 424 .446 405 .431 383 .416 366 .400 354 .383
434 .446 414 .431 392 .416 375 .400 362 .383
419 .432 396 .416 379 .400 366 .383
ISA +20
407 .410 387 .394 375 .378
ISA +20
400 .415 383 .400 370 .383
EFFECTIVITY CODE
B C D E
P-55
LR CRUISE TWO ENGINE
ISA -10
ALTITUDE — 1000 FEET
WEIGHT — 17,000 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
LONG RANGE CRUISE TWO ENGINE
ISA -10
WEIGHT — 15,500 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
ISA -10
ALTITUDE — 1000 FEET
LR CRUISE TWO ENGINE
ALTITUDE — 1000 FEET
WEIGHT — 16,000 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
411 .492 419 .484 419 .470 409 .453 389 .438 369 .422 354 .406 342 .389
421 .504 415 .496 420 .477 402 .462 382 .445 364 .429 350 .412 338 .394
TEMPERATURE — °C ISA ISA +10 ISA +15
429 .484 429 .469 418 .453 398 .438 378 .422 362 .405 350 .388
412 .438 391 .422 375 .406 362 .389
TEMPERATURE — °C ISA ISA +10 ISA +15
425 .496 430 .477 411 .461 391 .445 373 .429 358 .411 346 .394
EFFECTIVITY CODE
P-56
428 .453 407 .438 386 .421 371 .406 358 .389
B C D E
421 .462 400 .445 381 .429 366 .412 354 .395
404 .445 385 .428 370 .412 358 .395
ISA +20
395 .422 379 .406 366 .389
ISA +20
408 .444 389 .428 374 .411 362 .395
CL-126B October 2004
LONG RANGE CRUISE TWO ENGINE
WEIGHT — 14,500 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
ISA -10 403 .533 419 .529 420 .512 409 .493 388 .477 370 .460 355 .442 344 .425 333 .405
ALTITUDE — 1000 FEET
CL-126B October 2004
422 .515 418 .504 416 .484 395 .469 375 .452 360 .436 346 .418 336 .400
TEMPERATURE — °C ISA ISA +10 ISA +15
432 .516 428 .504 426 .485 405 .469 384 .452 368 .435 354 .418 344 .400
414 .469 393 .452 377 .436 362 .418 351 .399
418 .468 397 .452 381 .435 366 .418 355 .399
TEMPERATURE — °C ISA ISA +10 ISA +15
429 .529 430 .513 419 .494 397 .477 379 .460 364 .443 352 .424 341 .405
429 .494 406 .477 387 .459 372 .442 360 .424 349 .406
411 .477 392 .460 376 .442 364 .424 352 .405
ISA +20
401 .452 385 .436 370 .418 359 .400
ISA +20
396 .460 380 .442 368 .424 356 .405
EFFECTIVITY CODE
B C D E
P-57
LR CRUISE TWO ENGINE
ISA -10
ALTITUDE — 1000 FEET
WEIGHT — 15,000 LB KTAS 51 NM/LB KTAS 49 NM/LB KTAS 47 NM/LB KTAS 45 NM/LB KTAS 43 NM/LB KTAS 41 NM/LB KTAS 39 NM/LB KTAS 37 NM/LB KTAS 35 NM/LB
CREW NOTES
EFFECTIVITY
P-58
ALL
CL-126B October 2004
CONSTANT MACH CRUISE
ALTITUDE — 1000 FEET
WEIGHT — 20,500 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr CL-126B October 2004
ISA -10
426 1105 426 1105 426 1139 426 1186 426 1246 428 1334 438 1617 448 1968
ISA -10
426 1078 426 1093 426 1125 426 1173 426 1235 428 1325 438 1610 448 1962
TEMPERATURE — °C ISA ISA +10 ISA +15
436 1167 436 1214 436 1276 438 1366 448 1654 457 2010
446 1305 448 1397
TEMPERATURE — °C ISA ISA +10 ISA +15
436 1120 436 1152 436 1201 436 1265 438 1356 448 1647 457 2004 EFFECTIVITY CODE
P-54 B C D E
ISA +20
ISA +20
446 1294 448 1387
CONSTANT MACH CRUISE
ALTITUDE — 1000 FEET
WEIGHT — 21,000 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr
P-59
CONSTANT MACH CRUISE
WEIGHT — 19,500 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr ALTITUDE — 1000 FEET
CONSTANT MACH CRUISE
ALTITUDE — 1000 FEET
WEIGHT — 20,000 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr
P-60
ISA -10
426 1054 426 1075 426 1111 426 1162 426 1225 428 1316 438 1603 448 1956
ISA -10
426 1032 426 1058 426 1097 426 1150 426 1215 428 1307 438 1597 448 1950
TEMPERATURE — °C ISA ISA +10 ISA +15
436 1101 436 1138 436 1189 436 1254 438 1347 448 1640 457 1998
446 1283 448 1378
TEMPERATURE — °C ISA ISA +10 ISA +15
436 1083 436 1124 436 1178 436 1244 438 1338 448 1633 457 1992 EFFECTIVITY CODE
P-54 B C D E
ISA +20
ISA +20
446 1273 448 1368
CL-126B October 2004
CONSTANT MACH CRUISE
ALTITUDE — 1000 FEET
WEIGHT — 18,500 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr CL-126B October 2004
ISA -10
426 1012 426 1012 426 1042 426 1084 426 1139 426 1207 428 1299 438 1590 448 1944
ISA -10
426 985 426 992 426 1028 426 1072 426 1128 426 1199 428 1292 438 1584 448 1938
TEMPERATURE — °C ISA ISA +10 ISA +15
436 1067 436 1110 436 1166 436 1236 438 1330 448 1626 457 1986
446 1264 448 1360 457 1661
TEMPERATURE — °C ISA ISA +10 ISA +15
436 1052 436 1097 436 1155 436 1228 438 1322 448 1619 457 1980 EFFECTIVITY CODE
P-54 B C D E
ISA +20
ISA +20
446 1256 448 1352 457 1654
CONSTANT MACH CRUISE
ALTITUDE — 1000 FEET
WEIGHT — 19,000 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr
P-61
CONSTANT MACH CRUISE
WEIGHT — 17,500 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr ALTITUDE — 1000 FEET
CONSTANT MACH CRUISE
ALTITUDE — 1000 FEET
WEIGHT — 18,000 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr
P-62
ISA -10
426 961 426 982 426 1013 426 1060 426 1118 426 1191 428 1284 438 1577 448 1933
ISA -10
426 939 426 964 426 1000 426 1048 426 1108 426 1184 428 1277 438 1571 448 1928
TEMPERATURE — °C ISA ISA +10 ISA +15
436 1005 436 1038 436 1085 436 1144 436 1220 438 1315 448 1613 457 1975
446 1170 446 1248 448 1344 457 1648
TEMPERATURE — °C ISA ISA +10 ISA +15
436 987 436 1024 436 1073 436 1135 436 1212 438 1307 448 1607 457 1970 EFFECTIVITY CODE
P-54 B C D E
ISA +20
446 1161 446 1240 448 1337 457 1642
ISA +20
453 1351
CL-126B October 2004
CONSTANT MACH CRUISE
ALTITUDE — 1000 FEET
WEIGHT — 16,500 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr CL-126B October 2004
ISA -10
426 914 426 919 426 949 426 986 426 1037 426 1100 426 1176 428 1270 438 1565 448 1923
ISA -10
426 889 426 906 426 934 426 974 426 1026 426 1092 426 1169 428 1263 438 1560 448 1918
TEMPERATURE — °C ISA ISA +10 ISA +15
436 972 436 1010 436 1062 436 1126 436 1204 438 1300 448 1601 457 1965
446 1152 446 1232 448 1329 457 1635
453 1344
TEMPERATURE — °C ISA ISA +10 ISA +15
436 928 436 957 436 998 436 1051 436 1118 436 1197 438 1293 448 1595 457 1960 EFFECTIVITY CODE
P-54 B C D E
446 1144 446 1224 448 1322 457 1629
ISA +20
ISA +20
451 1237 453 1336
CONSTANT MACH CRUISE
ALTITUDE — 1000 FEET
WEIGHT — 17,000 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr
P-63
CONSTANT MACH CRUISE
WEIGHT — 15,500 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr ALTITUDE — 1000 FEET
CONSTANT MACH CRUISE
ALTITUDE — 1000 FEET
WEIGHT — 16,000 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr
P-64
ISA -10
426 866 426 888 426 920 426 963 426 1017 426 1085 426 1161 428 1256 438 1554 448 1914
ISA -10 426 845 426 845 426 872 426 906 426 951 426 1009 426 1077 426 1154 428 1249 438 1548 448 1910
TEMPERATURE — °C ISA ISA +10 ISA +15
436 909 436 942 436 986 436 1042 436 1111 436 1189 438 1286 448 1589 457 1955
446 1065 446 1136 446 1216 448 1315 457 1623
451 1230 453 1329
TEMPERATURE — °C ISA ISA +10 ISA +15
436 893 436 928 436 974 436 1033 436 1103 436 1182 438 1279 448 1583 457 1951 EFFECTIVITY CODE
P-54 B C D E
446 1057 446 1128 446 1209 448 1308 457 1618
ISA +20
ISA +20
451 1222 453 1322
CL-126B October 2004
CONSTANT MACH CRUISE
WEIGHT — 14,500 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr
ISA -10 426 796 426 814 426 842 426 882 426 933 426 994 426 1063 426 1141 428 1237 438 1538 448 1901
ALTITUDE — 1000 FEET
CL-126B October 2004
TEMPERATURE — °C ISA ISA +10 ISA +15
436 852 436 877 436 915 436 964 436 1025 436 1095 436 1175 438 1272 448 1578 457 1946
446 1049 446 1120 446 1202 448 1301 457 1612
451 1215 453 1315
TEMPERATURE — °C ISA ISA +10 ISA +15
436 833 436 862 436 903 436 956 436 1017 436 1088 436 1168 438 1266 448 1573 457 1942 EFFECTIVITY CODE
P-54 B C D E
446 1041 446 1113 446 1195 448 1295 457 1607
ISA +20
ISA +20
451 1208 453 1309
CONSTANT MACH CRUISE
ISA -10 426 819 426 832 426 857 426 894 426 942 426 1001 426 1070 426 1147 428 1243 438 1543 448 1905
ALTITUDE — 1000 FEET
WEIGHT — 15,000 LB Mach — .76 MI KTAS 51 Fuel - Lb/Hr KTAS 49 Fuel - Lb/Hr KTAS 47 Fuel - Lb/Hr KTAS 45 Fuel - Lb/Hr KTAS 43 Fuel - Lb/Hr KTAS 41 Fuel - Lb/Hr KTAS 39 Fuel - Lb/Hr KTAS 37 Fuel - Lb/Hr KTAS 35 Fuel - Lb/Hr KTAS 30 Fuel - Lb/Hr KTAS 25 Fuel - Lb/Hr
P-65
CREW NOTES
EFFECTIVITY
P-66
ALL
CL-126B October 2004
ONE ENGINE
ISA -10
WEIGHT — 20,500 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ISA -10
ALTITUDE — 1000 FEET
ALTITUDE — 1000 FEET
WEIGHT — 21,000 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
CL-126B October 2004
210 301 1040 216 286 1055 226 276 1119 227 258 1150 228 240 1177
206 296 1002 216 286 1041 224 274 1097 223 253 1116 226 239 1158
TEMPERATURE — °C ISA ISA +10 ISA +15
210 308 1062 216 292 1077 226 282 1141 227 262 1172 228 245 1198
216 298 1099 226 287 1163 227 267 1194 228 249 1220
226 290 1174 227 270 1205 228 251 1230
TEMPERATURE — °C ISA ISA +10 ISA +15
206 303 1023 216 291 1063 224 279 1119 223 258 1138 226 243 1180
216 297 1084 224 284 1140 223 262 1159 226 247 1201
EFFECTIVITY CODE
P-54 B C D E
224 287 1151 223 265 1169 226 249 1211
ISA +20
227 272 1215 228 253 1241
ISA +20
223 267 1179 226 252 1221
P-67
LR CRUISE ONE ENGINE
LONG RANGE CRUISE
ONE ENGINE
ISA -10
WEIGHT — 19,500 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ISA -10
ALTITUDE — 1000 FEET
WEIGHT — 20,000 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ALTITUDE — 1000 FEET
LR CRUISE ONE ENGINE
LONG RANGE CRUISE
P-68
205 294 978 215 285 1026 221 271 1075 219 248 1084 224 236 1136
204 293 957 214 284 1010 218 267 1045 215 244 1053 222 234 1114
TEMPERATURE — °C ISA ISA +10 ISA +15
205 301 999 215 291 1047 221 276 1096 219 253 1105 224 241 1157
215 296 1068 221 282 1117 219 258 1125 224 245 1178
221 284 1128 219 260 1135 224 247 1188
TEMPERATURE — °C ISA ISA +10 ISA +15
204 299 977 214 290 1031 218 272 1066 215 249 1073 222 238 1134
EFFECTIVITY CODE
P-54 B C D E
214 295 1051 218 277 1087 215 253 1093 222 243 1155
218 280 1097 215 256 1102 222 245 1165
ISA +20
219 262 1145 224 249 1198
ISA +20
215 258 1112 222 247 1175
CL-126B October 2004
ONE ENGINE
ISA -10
WEIGHT — 18,500 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ISA -10
ALTITUDE — 1000 FEET
ALTITUDE — 1000 FEET
WEIGHT — 19,000 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
CL-126B October 2004
.509 293 899 203 292 939 212 281 988 214 262 1013 211 240 1023 219 231 1089
.525 303 909 203 291 922 210 278 963 210 257 981 209 237 999 216 228 1061
TEMPERATURE — °C ISA ISA +10 ISA +15
.509 300 919 203 298 959 212 287 1008 214 267 1033 211 245 1042 219 236 1109
203 305 979 212 293 1028 214 272 1053 211 249 1062 219 240 1129
214 275 1063 211 251 1071 219 242 1139
TEMPERATURE — °C ISA ISA +10 ISA +15
.525 309 929 203 297 942 210 283 983 210 262 1001 209 242 1018 216 232 1080
203 304 962 210 289 1003 210 267 1020 209 246 1037 216 236 1099
EFFECTIVITY CODE
P-54 B C D E
210 292 1012 210 269 1029 209 248 1046 216 238 1109
ISA +20
214 277 1072 211 253 1080 219 244 1148
ISA +20
210 272 1039 209 251 1055 216 240 1118
P-69
LR CRUISE ONE ENGINE
LONG RANGE CRUISE
ONE ENGINE
ISA -10
WEIGHT — 17,500 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ISA -10
ALTITUDE — 1000 FEET
WEIGHT — 18,000 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ALTITUDE — 1000 FEET
LR CRUISE ONE ENGINE
LONG RANGE CRUISE
P-70
.521 300 881 202 290 905 207 274 937 205 252 949 207 235 976 212 224 1032
.517 298 854 199 286 879 203 269 910 203 248 923 204 232 952 209 221 1004
TEMPERATURE — °C ISA ISA +10 ISA +15
.521 307 901 202 296 924 207 279 957 205 257 967 207 239 995 212 228 1051
202 302 943 207 285 976 205 262 986 207 244 1013 212 232 1070
207 288 985 205 264 995 207 246 1022 212 234 1079
TEMPERATURE — °C ISA ISA +10 ISA +15
.517 305 873 199 292 898 203 275 928 203 253 942 204 236 970 209 225 1023
EFFECTIVITY CODE
P-54 B C D E
199 298 916 203 281 947 203 258 960 204 241 988 209 229 1041
203 283 956 203 260 969 204 243 997 209 231 1050
ISA +20
205 266 1004 207 248 1031 212 236 1088
ISA +20
203 286 965 203 263 977 204 245 1006 209 233 1059
CL-126B October 2004
ONE ENGINE
ISA -10
WEIGHT — 16,500 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ISA -10
ALTITUDE — 1000 FEET
ALTITUDE — 1000 FEET
WEIGHT — 17,000 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
CL-126B October 2004
.514 296 828 196 282 851 200 265 883 200 245 898 202 229 929 206 217 978
.514 296 814 193 278 826 197 261 857 197 242 874 199 226 906 203 215 955
TEMPERATURE — °C ISA ISA +10 ISA +15
ISA +20
.514 303 846 196 288 870 200 271 901 200 250 916 202 234 947 206 221 997
200 282 937 200 259 951 202 242 982 206 229 1032
196 294 888 200 276 919 200 254 933 202 238 965 206 225 1014
196 297 897 200 279 928 200 257 942 202 240 973 206 227 1023
TEMPERATURE — °C ISA ISA +10 ISA +15
ISA +20
.514 303 832 193 284 844 197 267 875 197 247 892 199 231 923 203 219 972
197 277 909 197 256 926 199 239 957 203 226 1007
.514 310 850 193 290 861 197 272 892 197 251 909 199 235 940 203 223 990
EFFECTIVITY CODE
P-54 B C D E
193 293 870 197 275 901 197 254 917 199 237 949 203 225 998
P-71
LR CRUISE ONE ENGINE
LONG RANGE CRUISE
ONE ENGINE
ISA -10
WEIGHT — 15,500 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ISA -10
ALTITUDE — 1000 FEET
WEIGHT — 16,000 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ALTITUDE — 1000 FEET
LR CRUISE ONE ENGINE
LONG RANGE CRUISE
P-72
.514 296 798 191 275 806 194 257 831 195 239 851 197 224 883 201 212 932
.506 292 771 189 273 785 191 253 806 192 235 828 194 221 860 198 209 906
TEMPERATURE — °C ISA ISA +10 ISA +15
.514 303 816 191 281 823 194 263 848 195 243 868 197 228 900 201 216 950
.514 309 834 191 287 840 194 268 865 195 248 885 197 232 917 201 220 967
191 290 849 194 270 873 195 250 893 197 234 925 201 222 975
TEMPERATURE — °C ISA ISA +10 ISA +15
.506 298 788 189 278 802 191 259 823 192 240 844 194 225 876 198 213 923
EFFECTIVITY CODE
P-54 B C D E
.506 305 805 189 284 819 191 264 839 192 245 861 194 229 893 198 217 940
189 287 827 191 266 847 192 247 869 194 231 901 198 219 948
ISA +20
191 293 857 194 273 882 195 253 901 197 236 933 201 224 983
ISA +20
189 290 835 191 269 855 192 249 876 194 233 909 198 220 956
CL-126B October 2004
ONE ENGINE
ISA -10 .513 289 706 .496 286 741 187 270 764 188 249 781 189 232 805 192 218 838 195 206 881
TEMPERATURE — °C ISA ISA +10 ISA +15 .513 296 723 .496 .496 .496 292 299 302 757 774 782 187 187 187 275 281 284 780 797 805 188 188 188 254 260 262 797 813 820 189 189 189 237 241 244 821 836 844 192 192 192 222 226 228 854 869 877 195 195 195 210 213 215 897 913 921
WEIGHT — 14,500 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
ISA -10 .528 297 711 .492 284 721 184 266 740 185 245 756 186 229 781 190 215 817 192 203 856
TEMPERATURE — °C ISA ISA +10 ISA +15 .528 304 728 .492 .492 .492 290 296 299 738 754 762 184 184 184 271 277 280 756 772 780 185 185 185 251 255 258 772 787 795 186 186 186 233 238 240 796 812 819 190 190 190 220 224 226 832 848 855 192 192 192 206 210 212 872 887 895
ALTITUDE — 1000 FEET
ALTITUDE — 1000 FEET
WEIGHT — 15,000 LB Mach Ind 35 KTAS Fuel - Lb/Hr Mach Ind 30 KTAS Fuel - Lb/Hr KIAS 25 KTAS Fuel - Lb/Hr KIAS 20 KTAS Fuel - Lb/Hr KIAS 15 KTAS Fuel - Lb/Hr KIAS 10 KTAS Fuel - Lb/Hr KIAS 5 KTAS Fuel - Lb/Hr
CL-126B October 2004
EFFECTIVITY CODE
P-54 B C D E
ISA +20
187 287 813 188 265 828 189 246 852 192 230 885 195 217 928
ISA +20
184 282 787 185 260 802 186 242 826 190 228 863 192 214 903
P-73
LR CRUISE ONE ENGINE
LONG RANGE CRUISE
CREW NOTES
EFFECTIVITY
P-74
P-54
ALL
CL-126B October 2004
DESCENT PERFORMANCE SCHEDULE TIME Min.
DISTANCE N.M.
FUEL Lb.
51 49 47 45 43 41 39 37 35 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5
15.7 14.6 13.5 12.5 11.7 10.9 10.2 9.6 9.1 8.7 8.3 8.0 7.7 7.2 6.8 6.4 6.0 5.5 5.1 4.7 4.3 3.4 2.7 1.9
100 92 85 78 71 66 61 56 53 49 47 44 42 39 36 33 30 27 24 22 19 15 12 8
117 108 100 92 86 80 75 70 66 63 60 58 55 52 49 46 44 41 38 36 33 27 21 16
DESCENT SPEED:
LANDING
ALTITUDE 1000 Ft.
DESCENT & HOLDING
NORMAL DESCENT
51,000 to 28,000 feet ............................0.76 MI 28,000 to 10,000 feet ........................ 300 KIAS 10,000 feet and below ....................... 250 KIAS
CL-126B October 2004
EFFECTIVITY ALL
P-75
MAXIMUM RANGE DESCENT
LANDING
DESCENT & HOLDING
ONE ENGINE
ALTITUDE — FT
DESCENT SPEED
51,000 to 49,000
0.70 MI
49,000 to 29,000
170 KIAS
29,000 to 21,000
0.45 MI
21,000 and below
200 KIAS
NOTE This table represents the minimum sink-rate speed above the single-engine service ceiling and approximates the best rate-of-climb speed below the singleengine service ceiling.
P-76
EFFECTIVITY ALL
CL-126B October 2004
HOLDING OPERATIONS
39 37
ALTITUDE — 1000 FEET
35 33 31 29 25 20 15 10 5
CL-126B October 2004
16
17
18
19
20
21
.607
.623
.639
.655
.671
.687
.703
.718 1080
Fuel - Lb/Hr
737
782
829
876
925
974
1024
Mach Ind
.581
.596
.612
.627
.643
.658
.673
.688
Fuel - Lb/Hr
735
777
823
869
918
966
1015
1065
Mach Ind
.556
.571
.585
.600
.615
.630
.644
.659
Fuel - Lb/Hr
734
775
818
864
911
959
1007
1057
Mach Ind
.531
.546
.560
.574
.589
.603
.617
.631
Fuel - Lb/Hr
738
780
822
867
914
960
1008
1057
Mach Ind
.508
.522
.536
.550
.563
.577
.591
.604
Fuel - Lb/Hr
747
788
831
876
921
968
1016
1063
Mach Ind
.487
.500
.513
.526
.540
.553
.566
.579
Fuel - Lb/Hr
757
798
839
882
930
976
1023
1071
Mach Ind
.466
.479
.492
.504
.517
.530
.543
.555
Fuel - Lb/Hr
766
807
850
891
938
985
1033
1079
KIAS
150
155
160
165
170
175
180
185
Fuel - Lb/Hr
711
752
793
835
877
919
962
1007
KIAS
150
155
160
165
170
175
180
185
Fuel - Lb/Hr
737
778
819
861
903
946
990
1034
KIAS
150
155
160
165
170
175
180
185
Fuel - Lb/Hr
767
808
849
891
934
978
1023
1068
KIAS
150
155
160
165
170
175
180
185
Fuel - Lb/Hr
799
841
884
928
971
1015
1060
1106
KIAS
150
155
160
165
170
175
180
185
Fuel - Lb/Hr
841
885
929
973
1018
1065
1112
1159
EFFECTIVITY ALL
P-77
LANDING
41
Mach Ind
15
DESCENT & HOLDING
WEIGHT — 1000 LB 14
LANDING WEIGHT LIMITS ANTI-ICE OFF
DESCENT & HOLDING
TEMPERATURE PRESSURE °F
14
32
ALTITUDE °C
-10
0
(FEET)
50
68
86
104
10
20
30
40
WEIGHT LIMIT ~ POUNDS
10000
19140
18720
18340
17970
17550
9000
19200
19200
18800
18430
18070
19200
18880
18510
19200
18980
8000 7000
19200
LANDING
6000
18470 19200
5000 4000 3000 2000 1000 S.L.
These data were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed. DO NOT EXCEED MAXIMUM CERTIFIED LANDING WEIGHT
EFFECTIVITY CODE
P-78
P-54 B C D E
CL-126B October 2004
LANDING — SEA LEVEL LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
19,200
19,000
18,000
17,000
16,000
15,000
14,000
14 -10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
32
50
68
86
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET)
104 40
123 132 2480 4134
123 132 2550 4250
123 132 2620 4367
123 132 2700 4500
123 132 2770 4617
123 132 2840 4734
122 132 2460 4100
122 132 2530 4217
122 132 2600 4334
122 132 2680 4467
122 132 2750 4584
122 132 2820 4700
119 129 2380 3967
119 129 2440 4067
119 129 2510 4184
119 129 2580 4300
119 129 2650 4417
119 129 2710 4517
116 125 2290 3817
116 125 2350 3917
116 125 2410 4017
116 125 2470 4117
116 125 2540 4234
116 125 2600 4334
113 122 2220 3700
113 122 2270 3784
113 122 2320 3867
113 122 2380 3967
113 122 2430 4050
113 122 2490 4150
110 119 2140 3567
110 119 2190 3650
110 119 2240 3734
110 119 2290 3817
110 119 2340 3900
110 119 2400 4000
106 115 2050 3417
106 115 2100 3500
106 115 2150 3584
106 115 2200 3667
106 115 2240 3734
106 115 2290 3817
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
CL-126B October 2004
EFFECTIVITY ALL
P-79
DESCENT & HOLDING
WT (LB)
°F °C
LANDING
TEMP
LANDING — 1000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
LANDING
DESCENT & HOLDING
TEMP WT (LB)
19,200
19,000
18,000
17,000
16,000
15,000
14,000
°F
14
°C
-10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
32
50
68
86
104
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET)
40
123 132 2550 4250
123 132 2630 4384
123 132 2700 4500
123 132 2780 4634
123 132 2860 4767
123 132 2930 4884
122 132 2530 4217
122 132 2610 4350
122 132 2680 4467
122 132 2760 4600
122 132 2830 4717
122 132 2910 4850
119 129 2440 4067
119 129 2510 4184
119 129 2580 4300
119 129 2650 4417
119 129 2720 4534
119 129 2800 4667
116 125 2350 3917
116 125 2410 4017
116 125 2480 4134
116 125 2550 4250
116 125 2610 4350
116 125 2680 4467
113 122 2270 3784
113 122 2330 3884
113 122 2380 3967
113 122 2440 4067
113 122 2500 4167
113 122 2560 4267
110 119 2190 3650
110 119 2240 3734
110 119 2300 3834
110 119 2350 3917
110 119 2400 4000
110 119 2460 4100
106 115 2100 3500
106 115 2150 3584
106 115 2200 3667
106 115 2250 3750
106 115 2300 3834
106 115 2350 3917
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
P-80
EFFECTIVITY ALL
CL-126B October 2004
LANDING — 2000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
19,200
19,000
18,000
17,000
16,000
15,000
14,000
14 -10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
123 132 2630 4384 122 132 2610 4350 119 129 2520 4200 116 125 2420 4034 113 122 2330 3884 110 119 2250 3750 106 115 2150 3584
32
50
68
86
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET) 123 132 2710 4517 122 132 2690 4484 119 129 2590 4317 116 125 2480 4134 113 122 2390 3984 110 119 2300 3834 106 115 2200 3667
123 132 2790 4650 122 132 2760 4600 119 129 2660 4434 116 125 2550 4250 113 122 2450 4084 110 119 2360 3934 106 115 2260 3767
123 132 2870 4784 122 132 2840 4734 119 129 2730 4550 116 125 2620 4367 113 122 2510 4184 110 119 2410 4017 106 115 2310 3850
123 132 2950 4917 122 132 2920 4867 119 129 2810 4684 116 125 2690 4484 113 122 2570 4284 110 119 2470 4117 106 115 2360 3934
104 40 123 132 3030 5050 122 132 3000 5000 119 129 2880 4800 116 125 2760 4600 113 122 2640 4400 110 119 2520 4200 106 115 2410 4017
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
CL-126B October 2004
EFFECTIVITY ALL
P-81
DESCENT & HOLDING
WT (LB)
°F °C
LANDING
TEMP
LANDING — 3000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
LANDING
DESCENT & HOLDING
TEMP WT (LB)
19,200
19,000
18,000
17,000
16,000
15,000
14,000
°F
14
°C
-10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
123 132 2710 4517 122 132 2690 4484 119 129 2590 4317 116 125 2490 4150 113 122 2390 3984 110 119 2310 3850 106 115 2210 3684
32
50
68
86
104
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET) 123 132 2790 4650 122 132 2770 4617 119 129 2670 4450 116 125 2560 4267 113 122 2450 4084 110 119 2360 3934 106 115 2260 3767
123 132 2870 4784 122 132 2850 4750 119 129 2740 4567 116 125 2630 4384 113 122 2520 4200 110 119 2420 4034 106 115 2320 3867
123 132 2960 4934 122 132 2930 4884 119 129 2820 4700 116 125 2700 4500 113 122 2580 4300 110 119 2480 4134 106 115 2370 3950
123 132 3040 5067 122 132 3020 5034 119 129 2900 4834 116 125 2770 4617 113 122 2650 4417 110 119 2540 4234 106 115 2430 4050
40 123 132 3130 5217 122 132 3100 5167 119 129 2980 4967 116 125 2850 4750 113 122 2720 4534 110 119 2590 4317 106 115 2480 4134
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
P-82
EFFECTIVITY ALL
CL-126B October 2004
LANDING — 4000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
19,200
19,000
18,000
17,000
16,000
15,000
14,000
14 -10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
123 132 2800 4667 122 132 2770 4617 119 129 2670 4450 116 125 2560 4267 113 122 2460 4100 110 119 2370 3950 106 115 2270 3784
32
50
68
86
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET) 123 132 2880 4800 122 132 2860 4767 119 129 2750 4584 116 125 2640 4400 113 122 2520 4200 110 119 2430 4050 106 115 2320 3867
123 132 2970 4950 122 132 2950 4917 119 129 2830 4717 116 125 2710 4517 113 122 2590 4317 110 119 2490 4150 106 115 2380 3967
123 132 3060 5100 122 132 3030 5050 119 129 2910 4850 116 125 2790 4650 113 122 2660 4434 110 119 2550 4250 106 115 2440 4067
123 132 3150 5250 122 132 3120 5200 119 129 2990 4984 116 125 2860 4767 113 122 2730 4550 110 119 2610 4350 106 115 2490 4150
104 40 123 132 3240 5400 122 132 3210 5350 119 129 3080 5134 116 125 2940 4900 113 122 2800 4667 110 119 2670 4450 106 115 2550 4250
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
CL-126B October 2004
EFFECTIVITY ALL
P-83
DESCENT & HOLDING
WT (LB)
°F °C
LANDING
TEMP
LANDING — 5000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
LANDING
DESCENT & HOLDING
TEMP WT (LB)
19,200
19,000
18,000
17,000
16,000
15,000
14,000
°F
14
°C
-10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
123 133 2910 4850 123 132 2880 4800 120 129 2770 4617 117 126 2660 4434 114 123 2540 4234 110 119 2440 4067 107 115 2340 3900
32
50
68
86
104
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET) 123 133 3000 5000 123 132 2970 4950 120 129 2860 4767 117 126 2730 4550 114 123 2610 4350 110 119 2510 4184 107 115 2400 4000
123 133 3090 5150 123 132 3060 5100 120 129 2940 4900 117 126 2810 4684 114 123 2690 4484 110 119 2570 4284 107 115 2460 4100
123 133 3180 5300 123 132 3160 5267 120 129 3030 5050 117 126 2890 4817 114 123 2760 4600 110 119 2630 4384 107 115 2520 4200
123 133 3280 5467 123 132 3250 5417 120 129 3110 5184 117 126 2970 4950 114 123 2840 4734 110 119 2700 4500 107 115 2570 4284
40 123 133 3370 5617 123 132 3340 5567 120 129 3200 5334 117 126 3050 5084 114 123 2910 4850 110 119 2770 4617 107 115 2630 4384
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
P-84
EFFECTIVITY ALL
CL-126B October 2004
LANDING — 6000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
19,200
19,000
18,000
17,000
16,000
15,000
14,000
14 -10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
123 133 3000 5000 123 132 2980 4967 120 129 2860 4767 117 126 2740 4567 114 123 2620 4367 110 119 2510 4184 107 115 2400 4000
32
50
68
86
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET) 123 133 3100 5167 123 132 3070 5117 120 129 2950 4917 117 126 2820 4700 114 123 2690 4484 110 119 2580 4300 107 115 2460 4100
123 133 3200 5334 123 132 3170 5284 120 129 3040 5067 117 126 2900 4834 114 123 2770 4617 110 119 2640 4400 107 115 2530 4217
123 133 3290 5484 123 132 3270 5450 120 129 3130 5217 117 126 2990 4984 114 123 2850 4750 110 119 2720 4534 107 115 2590 4317
123 133 3400 5667 123 132 3360 5600 120 129 3220 5367 117 126 3070 5117 114 123 2930 4884 110 119 2790 4650 107 115 2650 4417
104 40 123 133 3500 5834 123 132 3460 5767 120 129 3310 5517 117 126 3160 5267 114 123 3000 5000 110 119 2860 4767 107 115 2710 4517
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
CL-126B October 2004
EFFECTIVITY ALL
P-85
DESCENT & HOLDING
WT (LB)
°F °C
LANDING
TEMP
LANDING — 7000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
LANDING
DESCENT & HOLDING
TEMP WT (LB)
19,200
19,000
18,000
17,000
16,000
15,000
14,000
°F
14
°C
-10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
124 134 3120 5200 123 133 3100 5167 120 130 2970 4950 117 127 2840 4734 114 123 2720 4534 111 120 2590 4317 107 116 2480 4134
32
50
68
86
104
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET) 124 134 3230 5384 123 133 3200 5334 120 130 3070 5117 117 127 2930 4884 114 123 2800 4667 111 120 2670 4450 107 116 2540 4234
124 134 3330 5550 123 133 3300 5500 120 130 3160 5267 117 127 3020 5034 114 123 2880 4800 111 120 2740 4567 107 116 2610 4350
124 134 3440 5734 123 133 3400 5667 120 130 3260 5434 117 127 3110 5184 114 123 2960 4934 111 120 2820 4700 107 116 2670 4450
124 134 3540 5900 123 133 3510 5850 120 130 3360 5600 117 127 3190 5317 114 123 3040 5067 111 120 2890 4817 107 116 2740 4567
40 124 134 3650 6084 123 133 3620 6034 120 130 3450 5750 117 127 3290 5484 114 123 3120 5200 111 120 2970 4950 107 116 2810 4684
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed. The shaded areas are for interpolation only.
P-86
EFFECTIVITY ALL
CL-126B October 2004
LANDING — 8000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
19,200
19,000
18,000
17,000
16,000
15,000
14,000
14 -10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
124 134 3230 5384 123 133 3200 5334 120 130 3070 5117 117 127 2930 4884 114 123 2800 4667 111 120 2670 4450 107 116 2550 4250
32
50
68
86
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET) 124 134 3340 5567 123 133 3310 5517 120 130 3170 5284 117 127 3020 5034 114 123 2880 4800 111 120 2750 4584 107 116 2620 4367
124 134 3450 5750 123 133 3420 5700 120 130 3270 5450 117 127 3120 5200 114 123 2970 4950 111 120 2830 4717 107 116 2680 4467
124 134 3560 5934 123 133 3530 5884 120 130 3370 5617 117 127 3210 5350 114 123 3060 5100 111 120 2910 4850 107 116 2750 4584
124 134 3680 6134 123 133 3640 6067 120 130 3480 5800 117 127 3300 5500 114 123 3140 5234 111 120 2990 4984 107 116 2820 4700
104 40 124 134 3790 6317 123 133 3750 6250 120 130 3580 5967 117 127 3400 5667 114 123 3230 5384 111 120 3070 5117 107 116 2890 4817
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed. The shaded areas are for interpolation only.
CL-126B October 2004
EFFECTIVITY ALL
P-87
DESCENT & HOLDING
WT (LB)
°F °C
LANDING
TEMP
LANDING — 9000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
LANDING
DESCENT & HOLDING
TEMP WT (LB)
19,200
19,000
18,000
17,000
16,000
15,000
14,000
°F
14
°C
-10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
124 135 3370 5617 124 134 3340 5567 121 131 3200 5334 118 128 3050 5084 115 124 2910 4850 111 121 2770 4617 108 117 2630 4384
32
50
68
86
104
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET) 124 135 3480 5800 124 134 3450 5750 121 131 3300 5500 118 128 3140 5234 115 124 3000 5000 111 121 2850 4750 108 117 2700 4500
124 135 3600 6000 124 134 3570 5950 121 131 3410 5684 118 128 3240 5400 115 124 3090 5150 111 121 2930 4884 108 117 2770 4617
124 135 3720 6200 124 134 3680 6134 121 131 3520 5867 118 128 3340 5567 115 124 3180 5300 111 121 3020 5034 108 117 2850 4750
40
124 135 3840 6400 124 134 3800 6334 121 131 3630 6050 118 128 3440 5734 115 124 3270 5450 111 121 3100 5167 108 117 2930 4884
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
P-88
EFFECTIVITY ALL
CL-126B October 2004
LANDING — 10000 FEET LANDING SPEEDS AND DISTANCES — AUTOSPOILERS
19,200
19,000
18,000
17,000
16,000
15,000
14,000
14 -10
DATA VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED VREF VAPP ACTUAL FACTORED
124 135 3490 5817 124 134 3460 5767 121 131 3310 5517 118 128 3150 5250 115 124 3000 5000 111 121 2860 4767 108 117 2700 4500
32
50
68
86
0 10 20 30 LANDING SPEEDS (KIAS) AND DISTANCE (FEET) 124 135 3610 6017 124 134 3580 5967 121 131 3420 5700 118 128 3250 5417 115 124 3090 5150 111 121 2940 4900 108 117 2780 4634
124 135 3740 6234 124 134 3700 6167 121 131 3530 5884 118 128 3360 5600 115 124 3190 5317 111 121 3030 5050 108 117 2860 4767
124 135 3860 6434 124 134 3820 6367 121 131 3650 6084 118 128 3460 5767 115 124 3290 5484 111 121 3120 5200 108 117 2940 4900
104 40
124 135 3990 6650 124 134 3950 6584 121 131 3760 6267 118 128 3570 5950 115 124 3380 5634 111 121 3210 5350 108 117 3020 5034
These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.
CL-126B October 2004
EFFECTIVITY ALL
DESCENT & HOLDING
WT (LB)
°F °C
LANDING
TEMP
P-89
EMERGENCY PROCEDURES This section contains those operating procedures requiring the use of special systems and/or regular systems in order to protect the occupants and the aircraft from harm during a critical situation requiring immediate response. The procedures located in this section are to be used when an emergency condition exists. Sound judgement as well as thorough knowledge of the aircraft, its characteristics, and the flight manual procedures are essential in the handling of any emergency situation. In addition to the outlined items in the emergency procedure, the following steps are considered part of all emergency situations: • Maintain Airplane Control • Analyze the Situation • Take Proper Action
Memory Items Procedures in this checklist emphasized by enclosure in a box such as this should be memorized for crew accomplishment without reference to the procedure.
Voice
and Crew Warning Panel (CWP) Annunciations
Voice annunciations will be preceded by an audio symbol (headings only) and in all capital letters within quotes. CWP annunciations will be presented by all capital letters and are usually accompanied by a CAS.
Symbols and “If” Statements Certain procedures are dependent on prescribed conditions. These conditions are presented in bold as independent “If” statements. “If” statements preceded by a symbol (e.g. ●, ■ or ▲) indicate more than one condition for that step. Other conditions for that step will be indicated by repeating that step and symbol. Procedures completed at any substep level will be noted. (e.g. This checklist is complete.) Procedures not completed at a substep level will direct the user to the next applicable step. (e.g. Go to step 3.) The last procedure of any substep will either state “This checklist is complete.” or “Go to step #.”, or refer the user to another appropriate procedure.
Circuit Breakers Many procedures involve manipulating circuit breakers. The following criteria should be followed during “Circuit Breaker” steps. Circuit breakers that are “Set” should be checked for that normal condition. If the circuit breaker is not “Set”, it may be reset only once. If the circuit breaker opens again, do not reset. Circuit breakers that “Pull” should only be pulled and not reset. Circuit breakers that “Pull and Reset” should be pulled, delay for several seconds, and reset only once. Allow sufficient cooling time for circuit breakers that are “Reset” or cycled through a “Pull and Reset.” CL-126B October 2004
EFFECTIVITY ALL
E-i
EMERGENCY
FlightSafety
EMERGENCY
Emergency EICAS Index CAS or (EI) Message L R L R
APU FIRE BATT OVHT BATT OVHT BLEED AIR LEAK BLEED AIR LEAK
LR BLEED AIR LEAK CABIN ALTITUDE DEP (EI) EMER/PARK BRK L ENG PYLON OVHT R ENG PYLON OVHT LR ENG PYLON OVHT ENTRY DOOR FIRE (EI) L FUEL PRESS LOW R FUEL PRESS LOW LR FUEL PRESS LOW GEAR LR GEN FAIL NORM BRK FAIL L OIL PRESS LOW R OIL PRESS LOW
L R
1 3 3 7 7 7 5 14 14 8 8 8 3 5 10 10 10 12 3 12 6 6
PIT TRIM BIAS PIT TRIM MSCMP REV UNSAFE (CWP) REV UNSAFE (CWP) SPOILERS EXT STAB OVHT
14 14 14 14 14 1
TAKEOFF TRIM UNL (EI) WING OVHT WING/STAB LEAK
14 14 1 1
EFFECTIVITY
E-ii
Tab
ALL
CL-126B October 2004
EMERGENCY PROCEDURES
TAB
ANTI-ICING
1
STAB OVHT WING OVHT
1
WING/STAB LEAK
AUXILIARY POWER UNIT (APU)
2 3
APU FIRE
CABIN/COCKPIT FIRE & SMOKE DOOR
2
4 5
ENTRY DOOR
ELECTRICAL
3 6
BATT OVHT LR GEN FAIL
7
EMERGENCY DESCENT “CABIN ALTITUDE” Voice Activates
8
CABIN ALTITUDE
EMERGENCY EVACUATION
5
ENGINE “ENGINE FIRE” Voice Activates
9 10
Engine FIRE OIL PRESS LOW
6
Engine Failure
11 12
Immediate Engine Airstart
ENVIRONMENTAL/PRESSURIZATION
7 13
BLEED AIR LEAK ENG PYLON OVHT
14
FLIGHT CONTROLS PIT TRIM BIAS PIT TRIM MSCMP
8
SPOILERS EXT
16
TAKEOFF TRIM Aileron Control Jam
17
Elevator Control Jam
TAB CL-126B October 2004
15
EFFECTIVITY ALL
E-1
TAB 2
FLIGHT CONTROLS (Cont)
3
“OVERSPEED” Voice Activates
Pitch Axis Uncommanded Motion
9
Recovery from Inadvertent Overspeed
4
Roll or Yaw Axis Uncommanded Motion Rudder Control Jam
5
FUEL FUEL PRESS LOW
6 7 8 9 10 11 12 13
INSTRUMENTS/AVIONICS Multi-Function Display (MFD) Annunciations HDG FAIL HDG TEST RA NO BRG TERR TEST Primary Flight Display (PFD) Annunciations AP ATT FAIL HDG FAIL HDG TEST WIND SHR PULL UP RA FAIL
10
11
LANDING GEAR/BRAKES 12
14
EMER/PARK BRK “GEAR” Voice Activates
15
GEAR “BRAKES FAIL” Voice Activates NORM BRK FAIL
16 17
TAB EFFECTIVITY
E-2
ALL
CL-126B October 2004
LANDING GEAR/BRAKES (Cont)
TAB
Emergency Braking Nose Wheel Steering Malfunction
1 13
LANDINGS Ditching Forced Landing — Both Engines Inoperative
2 3
STALL “STALL” Voice Activates
4
TAKEOFFS Aborted Takeoff Takeoff “CONFIGURATION” Voice Activates EMER/PARK BRK PIT TRIM BIAS PIT TRIM MSCMP SPOILERS EXT TAKEOFF TRIM UNL or DEP (EI)
5 6 14
7 8 9
THRUST REVERSER “LEFT” or “RIGHT REVERSER UNSAFE” Voice Activates L REV UNSAFE (CWP) R REV UNSAFE (CWP) UNL or DEP (EI)
10 11 12 13 14 15 16 17 TAB
CL-126B October 2004
EFFECTIVITY ALL
E-3
STABOVHT OVHT STAB 2 3 4 5 6 7 8 9
STAB OVHT
1. WING/STAB .................................................................................. Off 2. Fly out of icing conditions. 3. L & R WING/STAB HT Circuit Breakers (respective ANTI-ICE group)........................................................Pull If approach & landing must be made with any ice or suspected ice: a. Refer to Abnormal Landings, Wing & Stabilizer Heat Failure Landing procedure, TAB 32, Abnormal Checklist.
WINGOVHT OVHT WING
WING OVHT
1. WING/STAB .................................................................................. Off 2. Fly out of icing conditions. 3. L & R WING/STAB HT Circuit Breakers (respective ANTI-ICE group)........................................................Pull If approach & landing must be made with any ice or suspected ice: a. Refer to Abnormal Landings, Wing & Stabilizer Heat Failure Landing procedure, TAB 32, Abnormal Checklist.
10 11 12 13 14
WING/ STAB LEAK
WING/STABLEAK LEAK WING/STAB
1. WING/STAB .................................................................................. Off 2. Fly out of icing conditions. 3. L & R WING/STAB HT Circuit Breakers (respective ANTI-ICE group)........................................................Pull If approach & landing must be made with any ice or suspected ice: a. Refer to Abnormal Landings, Wing & Stabilizer Heat Failure Landing procedure, TAB 32, Abnormal Checklist.
15 16 17
EFFECTIVITY
E-4
ALL
CL-126B October 2004
APUFIRE FIRE APU
FIRE PUSH
On the ground: 1. 2. 3. 4. 5. 6. 7. 8.
APU FIRE ..................................................................... FIRE PUSH APU MASTER ............................................................................ Off Stop the aircraft. EMERGENCY/PARKING BRAKE .............................................. Set Thrust Levers .................................................................... CUTOFF EMER LIGHTS .......................................................................... ON EMER BATT, L and R BATT ...................................................... OFF Evacuate the aircraft: a. Cabin Entry Door ................................................... Open & Exit b. Aft Emergency Exit................................................. Open & Exit
1 2 3 4 5 6 7
In flight: 1. APU FIRE .......................................................................FIRE PUSH 2. R STBY (Fuel) ..................................................Off, Unless Required 3. Land as soon as possible.
8 9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
E-5
Cabin/Cockpit Fire, Smoke or Fumes 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
1. 2. 3. 4. 5.
Crew Oxygen Masks ................................................... Don & 100% Smoke Goggles.........................................................................Don EMER DEPRESS ........................................................................ ON Pilot & Copilot MIC/MASK .................................................... MASK Pilot & Copilot INPH................................................................ INPH
Whether or not smoke has dissipated, if it cannot be visibly verified that the fire has been extinguished: 6. Cockpit Door/Curtain................................................................. Open 7. Land as soon as possible. 8. ●Source is not known: a. Isolate source of smoke or fumes, and go to one of the following procedures: Bleed Air System Normal Electrical System Emergency Electrical System 8. ●Source is known: a. Extinguish fire using hand-held extinguisher or eliminate the source of smoke or fumes. b. ■If fire is not extinguished: (1) Land as soon as possible. (2) This checklist is complete. b. ■If fire is extinguished and can visibly be verified: (1) Land as soon as practical. (2) This checklist is complete.
Bleed Air System Is Suspected Source 1. R BLEED.................................................................................... OFF 2. ●If smoke or fumes continue: a. R BLEED ............................................................................... On b. L BLEED..............................................................................OFF c. ■If smoke or fumes continue: (1) L BLEED ........................................................................ On (2) Refer to one of the following procedures: - Normal Electrical System Is Suspected Source - Emergency Electrical System Is Suspected Source
(Procedure Continued)
EFFECTIVITY
E-6
ALL
CL-126B October 2004
c. ■If smoke or fumes are eliminated: (1) Maintain 41,000 feet or below. Avoid flight in icing conditions. (2) Land as soon as practical. (3) This checklist is complete. 2. ●If smoke or fumes are eliminated: a. Maintain 41,000 feet or below. Avoid flight in icing conditions. b. Land as soon as practical. c. This checklist is complete.
L & R NON-ESS .........................................................................OFF FLOOD Light .................................................On for Night Operation L & R MAIN.................................................................................OFF ●If smoke or fumes continue, operate on EMER BATT as follows: a. On aircraft 45-002 thru 45-225 not modified by SB 45-55-6, maintain 33,000 ft or below. b. Airspeed ................................................... ≤ 200 KIAS or 0.7 MI Slower If Necessary c. If conditions permit, select flaps 20° (maximum) and retrim as necessary for landing. d. L & R ENG CMPTR............................................................ MAN e. L & R GEN .......................................................................... OFF f. L & R BATT ......................................................................... OFF g. Refer to the Battery Duration table, TAB 4, this checklist, for emergency battery duration. h. RADIO CTL HOT BUS ..........................................................ON i. CLR DLY MODES ........................................................... EMRG j. Use the clearance delivery radio. k. Use RMU 1 for engine pages. l. ■If smoke or fumes continue: The malfunctioning system is connected to the EMER BATT bus. (1) L & R BATT .................................................................... On (2) L & R GEN .................................................................... On (3) L & R MAIN ................................................................... On (4) L & R ENG CMPTR .......................................................ON (5) Allow attitude & air data display flags to clear. (6) Refer to Emergency Electrical System Is Suspected Source procedure, next page.
(Procedure Continued) CL-126B October 2004
EFFECTIVITY ALL
2 3 4
Normal Electrical System Is Suspected Source 1. 2. 3. 4.
1
E-7
5 6 7 8 9 10 11 12 13 14 15 16 17
2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
l. ■If smoke or fumes dissipate: (1) Land as soon as possible. (2) Refer to Abnormal Landings, Normal Electrical System Failure Landing procedure, TAB 32, Abnormal Checklist. 4. ●If smoke or fumes dissipate: a. Land as soon as possible. b. This checklist is complete.
Emergency Electrical System Is Suspected Source 1. EMER BATT............................................................................... OFF 2. BUS Circuit Breaker (pilot’s ELECTRICAL group [EMER BUS]) ...............................................................................Pull 3. Standby Instruments ..................................... Cage Attitude Indicator Use Primary Instruments 4. DAU [REVERSION] ..........................................................Channel B 5. Yaw Damper .................................................................As Required 6. Land as soon as practical. 7. Refer to Landing Gear Free Fall procedure, TAB 31, Abnormal Checklist, to extend landing gear prior to landing. 8. Refer to Abnormal Landings, Emergency Brake Landing procedure, TAB 33, Abnormal Checklist.
ENTRYDOOR DOOR ENTRY
ENTRY DOOR
ENTRY DOOR Accompanied by Evidence of Door Failure 1. NO SMOKING BELTS ..................................................................On 2. EMER DEPRESS ........................................................................ ON The cabin altitude will climb to approximately 13,700 feet & stabilize. 3. Airspeed........................................................... ≤ 250 KIAS or 0.7 MI Slower If Necessary 4. Establish descent to reduce cabin delta pressure, but not lower than the minimum safe altitude. 5. Land as soon as practical.
ENTRY DOOR Not Accompanied by Evidence of Door Failure 1. NO SMOKING BELTS ..................................................................On 2. Continue flight. The most probable cause is a latch pin switch malfunction.
EFFECTIVITY
E-8
ALL
CL-126B October 2004
BATTOVHT OVHT LLBATT R BATT OVHT R BATT OVHT
L BATT OVHT
R BATT OVHT
1
(Nickel-Cadmium Batteries Only)
2
1. EICAS ......................................................... Select ELEC or SUMRY Monitor Battery Temperature 2. Respective L or R BATT ...................................................Verify OFF
3 4
If battery temperature does not decrease: a. Land as soon as possible.
5 6
LRGEN GENFAIL FAIL LR
GEN FAIL
1. L & R GEN Circuit Breakers (respective ELECTRICAL group) ................................................ Set 2. Electrical Load ...................................................................... Reduce 3. Engine N2 ................................................................... 80% or Above 4. L & R GEN .......................... One at a Time, Depress (Approx 1 Sec) If a generator does not come on-line: 5. FLOOD Light ............................................... On for Night Operations 6. Use standby attitude indicator for attitude & magnetic compass for directional reference. Use standby airspeed/Mach indicator & altimeter. 7. RMU 1 ............................................... Select PGE, ENGINE PAGE 1 for Engine Indications 8. RMU 2: a. Select [1/2] for side 1 radios (COM 2, NAV 2, ADF 2, ATC 2 inoperative). b. Select PGE, NAVIGATION for NAV 1 course indication & tuning. c. Tune COM 1 as required using clearance delivery radio. Clearance delivery radio tuning may be achieved by selecting: RADIO CTL HOT BUS switch — ON CLR DLY MODES switch — EMRG. 9. L & R AV MSTR ..........................................................................OFF 10. L & R ENG CMPTR ................................................................... MAN 11. DU 2 ...........................................................................................OFF
(Procedure Continued) Change 1
CL-126B October 2004 Change 1
EFFECTIVITY ALL
E-9
7 8 9 10 11 12 13 14 15 16 17
2 3 4 5 6
12. L & R WSHLD ............................................................................ OFF On Prior to Landing (Max 5 Minutes) 13. EMER LIGHTS........................................................................... OFF ON Prior to Landing (Max 10 Minutes) 14. Standby Pitot Heat ................................................. Use As Required 15. The following conditions will exist (L & R MAIN — OFF): L & R pitot heat inoperative (avoid visible moisture); standby pitot heat operative. Recognition & landing/taxi lights inoperative. COM 2, NAV 2, ATC 2 inoperative. Automatic temperature control inoperative. Use MANUAL TEMP — ON. Battery duration with the generators off is as follows: MAIN
7 8 9 10 11 12 13 14 15 16 17
EMERGENCY
Amp-hr
Time12
Amp-hr
Time1
27 (Ni-Cad) 28 (Lead-Acid)
30 minutes
10 (Lead-Acid)
1.0 hour
38 (Ni-Cad)
1.0 hour
—
—
1 Time durations predicated upon operation on batteries only. 2 Time duration predicated upon the following conditions: DU 2 — OFF. Standby Pitot Heat (R PROBES Switch) — ON for no more than 30 minutes. L & R AV MSTR — OFF. EMER LIGHTS — ON for no more than 10 minutes. L & R MAIN — Remain OFF. L & R ENG CMPTR — MAN. 16. On aircraft 45-002 thru 45-225 not modified by SB 45-55-6, maintain 33,000 feet or below. 17. ●If time to the landing airport will exceed main battery duration: a. Airspeed ................................................... ≤ 200 KIAS or 0.7 MI Slower if Necessary b. Provided adequate fuel is available, prior to depleting the main batteries; select flaps 20° (maximum) & trim as desired for landing.
(Procedure Continued)
EFFECTIVITY
E-10
ALL
CL-126B October 2004 Change 1
c.
Once the main batteries are depleted, the emergency battery will provide power to emergency bus services. The following conditions will exist (EMER BATT only): Operative equipment associated with flight: Standby airspeed, altimeter & vibrator, and lighting. Standby attitude and lighting. RMU 1 Engine Display: N1, N2, OIL °C, and EMER (bus volts). Right cabin pressure control; use MANUAL rate control. Nacelle heat fails ON. Landing gear. Inboard brakes only. Inoperative equipment associated with flight: Primary displays. Pitch, aileron, and rudder trims. Flaps. Spoilers/spoilerons. Probe heats. Wing/Stab and windshield heat. External lights. Transponder. Stall warning system. d. Land as soon as possible. e. Refer to Abnormal Landings, Normal Electrical System Failure Landing procedure, TAB 32, Abnormal Checklist. 17. ●If time to the landing airport will NOT exceed main battery duration: a. This checklist is complete.
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
E-11
Emergency Emergency Descent Descent “CABIN ALTITUDE” 2 3 4 5 6 7
“CABIN ALTITUDE”
CABIN ALTITUDE
CABIN ALT
Cabin Altitude Exceeds 10,000 Feet 1. 2. 3. 4. 5. 6. 7. 8.
Crew Oxygen Masks ................................................... Don & 100% Thrust Levers .......................................................................... IDLE Autopilot ........................................................................ Disengage SPOILER ....................................................................................EXT Descend at MMO/VMO, but not below minimum safe altitude. DEPLOY ...................................................................................... ON Pilot & Copilot MIC/MASK .................................................... MASK Pilot & Copilot INPH................................................................ INPH
9. Yaw Damper ....................................................................As Required
8
10
If time & conditions permit: 10. Transponder...............................................................................7700 11. Notify controlling agency. 12. Check condition of passengers & provide assistance if conditions permit.
11
Emergency Evacuation
9
12 13
1. 2. 3. 4.
EMERGENCY/PARKING BRAKE............................................... Set Thrust Levers .................................................................... CUTOFF EMER LIGHTS ............................................................................ ON EMER BATT, L & R BATT ......................................................... OFF
14 15
5. Evacuate the aircraft: a. Cabin Entry Door.....................................................Open & Exit b. Aft Emergency Exit..................................................Open & Exit
16 17
EFFECTIVITY
E-12
ALL
CL-126B October 2004
IRE
(E
Engine FIRE
“RIGHT ENGINE FIRE LEFT ENGINE FIRE”
FIRE PUSH
Affected engine:
1 2
1. Thrust Lever ............................................................................IDLE Unless a Critical Thrust Situation Exists 2. ●If fire continues more than 15 seconds or there are other indications of fire: a. Thrust Lever ...............................................................CUTOFF b. Applicable FIRE (ENGINE)....................................FIRE PUSH c. EXTINGUISHER #1 (ENGINE) ........................... ARMED Push d. ■If fire continues: (1) EXTINGUISHER #2 (ENGINE) ..................... ARMED Push (2) Land as soon as possible. (3) Go to step e. d. ■If fire extinguishes: (1) Land as soon as practical. (2) Go to step e. e. ENG SYNC ......................................................................... OFF f. Rudder Trim ........................................................... As Required g. Yaw Damper........................................................... As Required h. Autopilot ................................................................... As Desired i. Applicable STBY (FUEL)....................................................... Off j. Refer to Engine Shutdown in Flight procedure, TAB 10, Abnormal Checklist. 2. ●If fire extinguishes in less than 15 seconds: a. Leave thrust lever at IDLE, unless a critical thrust situation exists. b. ENG SYNC ......................................................................... OFF c. Rudder Trim ........................................................... As Required d. Yaw Damper........................................................... As Required e. Autopilot ................................................................... As Desired f. Monitor fuel balance. Crossflow as required. STBY (FUEL) pump may be used. g. Land as soon as practical. h. Refer to Abnormal Landings, Single-Engine Landing, TAB 33, Abnormal Checklist.
3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
E-13
2
L OIL PRESS LOW
OILPRESS PRESSLOW LOW LLOIL R OIL PRESS LOW R OIL PRESS LOW
R OIL PRESS LOW
1. Respective Engine OIL PSI & OIL °C ..................................... Check
3 4 5 6 7 8 9 10
2. ●If OIL PSI is below 50 PSI and/or OIL °C is high: a. Reduce affected engine to idle. If flight conditions permit: A precautionary engine shutdown is advised. Refer to Engine Shutdown in Flight procedure, TAB 10, Abnormal Checklist. b. Land as soon as practical. c. Refer to Abnormal Landings, Single-Engine Landing procedure, TAB 33, Abnormal Checklist. 2. ●If OIL PSI is between 50 & 65 PSI & OIL °C is normal: a. Reduce affected engine to idle. b. Land as soon as practical. c. Refer to Abnormal Landings, Single-Engine procedure, TAB 33, Abnormal Checklist.
Landing
2. ●If OIL PSI & OIL °C are normal: a. Continue & monitor OIL PSI & OIL °C.
11 12 13 14 15 16 17
EFFECTIVITY
E-14
ALL
CL-126B October 2004
Engine Failure During takeoff:
1
Below V1 Speed
2
1. Brakes..................................................................................... Apply 2. Thrust Levers ...........................................................................IDLE 3. Spoilers..................................................................... Verify Extended If spoilers are not extended automatically: a. SPOILER Lever................................................................... EXT 4. Thrust Reversers ...............................................Deploy, if Necessary
3 4 5
Above V1 Speed 1. 2. 3. 4. 5.
Attitude Control ..........................................................As Required Accelerate to VR. Keep nose wheel on the ground. Rotate at VR to target takeoff pitch attitude; Climb at V2. Gear ............................................................................................. UP Climb to 1500 feet AGL or Obstacle Clearance Altitude (as appropriate), accelerate to V2 + 25, retract flaps, then accelerate to 200 KIAS en route climb speed.
6. Refer to Engine Shutdown in Flight procedure, TAB 10, Abnormal Checklist.
In flight:
8 9 10
EFFECTIVITY ALL
12 13 14 15 16 17
(Procedure Continued)
CL-126B October 2004 Change 1
7
11
1. Control Wheel Master (MSW)............................. Depress & Release Yaw damper & autopilot will disengage. On aircraft 45-002 thru 45-294 not modified by SB 45-27-20, the spoilers will blow down while the MSW is depressed. 2. Attitude Control ...............................................................As Required 3. Thrust Lever (operative engine)....................... Increase as Required 4. ENG SYNC ................................................................................. OFF 5. Rudder Trim ....................................................................As Required 6. Yaw Damper ...................................................................As Required 7. Autopilot............................................................................As Desired 8. Refer to Engine Shutdown in Flight procedure, TAB 10, Abnormal Checklist. Change 1
6
E-15
During approach:
2 3 4 5 6 7
1. Control Wheel Master (MSW)......................... Depress & Release Yaw damper & autopilot will disengage. On aircraft 45-002 thru 45-294 not modified by SB 45-27-20, the spoilers will blow down while the MSW is depressed. 2. Attitude Control ......................................................... As Required 3. Thrust Lever (Operative Engine) ............... Increase as Required 4. Flaps ............................................................................................. 8° 5. Airspeed....................................................................................VAPP 6. 7. 8. 9. 10.
8 9 10 11 12 13 14 15 16 17
ENG SYNC ................................................................................ OFF Rudder Trim ................................................................... As Required Yaw Damper................................................................... As Required Autopilot ........................................................................... As Desired Refer to either of the following procedures as applicable: Abnormal Landings, Single-Engine Landing, TAB 33, Abnormal Checklist. Go Around, Page N-13, Normal Checklist & Engine Shutdown in Flight, TAB 10, Abnormal Checklist.
Immediate Engine Airstart Affected engine: 1. Thrust Lever ............................................................................ IDLE IGN will automatically activate 2. STBY (FUEL)............................................................................... ON 3. ●If ITT is approaching the limit & rising rapidly: a. Thrust Lever ................................................................ CUTOFF b. Perform Engine Airstart procedure, TAB 7, or Engine Shutdown in Flight procedure, TAB 10, Abnormal Checklist. c. This checklist is complete. 3. ●If no indication of light-off is obtained within 20 seconds: a. Thrust Lever ................................................................ CUTOFF b. Perform Engine Airstart procedure, TAB 7, or Engine Shutdown in Flight procedure, TAB 10, Abnormal Checklist. c. This checklist is complete. 3. ●If airstart is complete: a. Thrust Lever ................................................................. Advance b. This checklist is complete.
EFFECTIVITY
E-16
ALL
CL-126B October 2004 Change 1
L BLEED AIR LEAK
BLEEDAIR AIRLEAK LEAK LLBLEED R BLEED AIR LEAK R BLEED AIR LEAK LR BLEED AIR LEAK LR BLEED AIR LEAK
R BLEED AIR LEAK
1
On the ground:
2
L or R BLEED AIR LEAK, or LR BLEED AIR LEAK Illuminated
3
1. APU START/STOP (if installed) .................................................... Off 2. Respective L or R BLEED ..........................................................OFF
4
If BLEED AIR LEAK remains illuminated: a. Shut down respective engine.
5
In flight:
6
L or R BLEED AIR LEAK Illuminated
7
1. Respective L or R BLEED ..........................................................OFF 2. Maintain 41,000 feet or below. Avoid flight in icing conditions. If BLEED AIR LEAK remains illuminated: a. Reduce engine N1 on respective engine. b. Land as soon as possible.
8 9 10
LR BLEED AIR LEAK Illuminated 1. EMER PRESS ............................................................................. ON 2. One L or R BLEED .....................................................................OFF 3. Adjust engine N1 on engine supplying EMER air to modulate cabin temperature. 4. Maintain 41,000 feet or below. Avoid flight in icing conditions. 5. Land as soon as possible.
11 12 13 14 15 16 17
CL-126B October 2004 Change 1
EFFECTIVITY ALL
E-17
2
ENGPYLON PYLONOVHT OVHT LLENG R ENG PYLON OVHT R ENG PYLON OVHT LR ENG PYLON OVHT LR ENG PYLON OVHT
3
L or R ENG PYLON OVHT
4 5 6 7 8 9
L ENG PYLON OVHT
R ENG PYLON OVHT
1. Respective L or R NAC .................................................................Off 2. Reduce engine N1 on respective engine. 3. Fly out of icing conditions. If L or R ENG PYLON OVHT remains illuminated: a. Shut down respective engine. Refer to Engine Shutdown in Flight procedure, TAB 10, Abnormal Checklist.
LR ENG PYLON OVHT 1. L & R NAC ....................................................................................Off 2. Reduce engine N1 on both engines as low as possible, unless a critical thrust situation exists. 3. Fly out of icing conditions. If LR ENG PYLON OVHT remains illuminated: a. Land as soon as possible.
10 11 12 13 14 15 16 17
EFFECTIVITY
E-18
ALL
CL-126B October 2004
PIT TRIM BIAS PIT TRIM MSCMP
1
SPOILERS EXT
2
TAKEOFF TRIM
3
Refer to Takeoff “Configuration”, TAB 14, this checklist.
4
Aileron Control Jam
5
1. Attitude Control ..........................................................As Required Use Rudder & Thrust as Necessary 2. ROLL DISC Lever...................................................................... Pull a. Pilot — Control aircraft with the spoilerons. b. Do Not use the copilot control. c. Do Not use AIL TRIM. d.
Do Not Reconnect. The most likely occurrence of a jam would be expected in the aileron control system (copilot’s control wheel). 3. Airspeed .........................................................Reduce as Necessary 4. Land as soon as possible. 5. Refer to Abnormal Landings, Aileron Jammed Landing, TAB 33, Abnormal Checklist.
Elevator Control Jam
c. Do Not Reconnect. 4. Land as soon as possible. 5. Refer to Abnormal Landings, Elevator Jammed Landing procedure, TAB 34, Abnormal Checklist.
CL-126B October 2004 Change 1
7 8 9 10 11 12
1. Attitude Control ..........................................................As Required Use Pitch Trim & Thrust as Necessary 2. ELEV DISC................................................................. Pull & Rotate 3. Determine elevator without the jam & transition flight control to that pilot. a. Do Not apply additional control force to the jammed control. b. Do Not use PIT TRIM BIAS.
Change 1
6
EFFECTIVITY ALL
E-19
13 14 15 16 17
Pitch Axis Uncommanded Motion 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16
1. Control Wheel Master (MSW)............................... Depress & Hold 2. Attitude Control.......................................................... As Required 3. Thrust Levers ............................................................. As Required 4. Airspeed ................≤ Mach Trim Off MMO, but not less than 0.65 MI 5. zIf control force continues with the MSW depressed: a. PITCH TRIM........................................................................OFF b. Malfunctioning PRI PITCH or SEC PITCH Circuit Breaker (respective pilot’s or copilot’s FLIGHT group [TRIM]) .............................Pull c. Control Wheel Master (MSW) .......................................Release d. Yaw Damper .................................................................. Engage e. If the malfunction occurred in the Primary trim: (1) PITCH TRIM ................................................................ SEC (2) SEC (pedestal [PITCH TRIM]) ........................ As Required (3) Refer to PRI TRIM FAIL procedure, TAB 15, Abnormal Checklist. (4) This checklist is complete. e. If the malfunction occurred in the Secondary trim: (1) PITCH TRIM ..................................................................PRI (2) Control Wheel Trim .......................................... As Required (3) Refer to SEC TRIM FAIL procedure, TAB 15, Abnormal Checklist. (4) This checklist is complete. 5. zIf control force relieves with MSW depressed: a. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) ..........................................................Pull b. Control Wheel Master (MSW) .......................................Release c. Control Wheel Trim................................................. As Required d. Maintain 33,000 feet or below. e. Airspeed ............................... ≥ 0.65 MI Until Below 33,000 Feet f. Refer to PFD Annunciations, AP procedure, TAB 11, this checklist or TAB 25, Abnormal Checklist as appropriate. g. This checklist is complete.
17
E-20
EFFECTIVITY 45-002 thru 45-225 not modifiedALL by SB 45-55-6
CL-126B October 2004
PIT TRIM BIAS PIT TRIM MSCMP
1
SPOILERS EXT
2
TAKEOFF TRIM
3
Refer to Takeoff “Configuration”, TAB 14, this checklist.
4
Aileron Control Jam
5
1. Attitude Control ..........................................................As Required Use Rudder & Thrust as Necessary 2. ROLL DISC Lever...................................................................... Pull a. Pilot — Control aircraft with the spoilerons. b. Do Not use the copilot control. c. Do Not use AIL TRIM. d.
Do Not Reconnect. The most likely occurrence of a jam would be expected in the aileron control system (copilot’s control wheel). 3. Airspeed .........................................................Reduce as Necessary 4. Land as soon as possible. 5. Refer to Abnormal Landings, Aileron Jammed Landing, TAB 33, Abnormal Checklist.
Elevator Control Jam
c. Do Not Reconnect. 4. Land as soon as possible. 5. Refer to Abnormal Landings, Elevator Jammed Landing procedure, TAB 34, Abnormal Checklist.
CL-126B October 2004 Change 1
7 8 9 10 11 12
1. Attitude Control ..........................................................As Required Use Pitch Trim & Thrust as Necessary 2. ELEV DISC................................................................. Pull & Rotate 3. Determine elevator without the jam & transition flight control to that pilot. a. Do Not apply additional control force to the jammed control. b. Do Not use PIT TRIM BIAS.
Change 1
6
EFFECTIVITY ALL
E-19
13 14 15 16 17
Pitch Axis Uncommanded Motion 2 3 4 5 6 7 8 9 10 11 12 13 14 15
1. Control Wheel Master (MSW)............................... Depress & Hold 2. Attitude Control.......................................................... As Required 3. Thrust Levers ............................................................. As Required 4. Airspeed ......................................................≤ Mach Trim Off MMO 5. zIf control force continues with the MSW depressed: a. PITCH TRIM........................................................................OFF b. Malfunctioning PRI PITCH or SEC PITCH Circuit Breaker (respective pilot’s or copilot’s FLIGHT group [TRIM]) .............................Pull c. Control Wheel Master (MSW) .......................................Release d. Yaw Damper ............................................................. As Desired e. If the malfunction occurred in the Primary trim: (1) PITCH TRIM ................................................................ SEC (2) SEC (pedestal [PITCH TRIM]) ........................ As Required (3) Refer to PRI TRIM FAIL procedure, TAB 15, Abnormal Checklist. (4) This checklist is complete. e. If the malfunction occurred in the Secondary trim: (1) PITCH TRIM ..................................................................PRI (2) Control Wheel Trim .......................................... As Required (3) Refer to SEC TRIM FAIL procedure, TAB 15, Abnormal Checklist. (4) This checklist is complete. 5. zIf control force relieves with MSW depressed: a. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) ..........................................................Pull b. Control Wheel Master (MSW) .......................................Release c. Control Wheel Trim................................................. As Required d. Refer to PFD Annunciations, AP procedure, TAB 11, this checklist or TAB 25, Abnormal Checklist as appropriate. e. This checklist is complete.
16 17
E-20.1
EFFECTIVITY 45-226 & on, and prior aircraft ALL modified by SB 45-55-6
CL-126B October 2004
Recovery from Inadvertent Overspeed 1
“OVERSPEED” 1. 2. 3. 4. 5. 6.
Thrust Levers ...........................................................................IDLE Autopilot .........................................................................Disengage SPOILER .................................................................................... EXT Identify aircraft pitch & roll attitude. Level wings. Elevator & Pitch Trim..................................................As Required
7. Yaw Damper .................................................................... As Desired
1. Control Wheel Master (MSW)............................... Depress & Hold 2. Attitude Control ..........................................................As Required 3. Airspeed ................. ≤ Mach Trim Off MMO, but not less than 0.65 MI 4. ●If accompanied by SPOILERS FAIL amber CAS or SPOILER JAM amber CAS: a. Control Wheel Master (MSW) ....................................... Release b. Yaw Damper ...................................................................Engage c. Refer to respective SPOILERS FAIL or SPOILER JAM procedure, Tab 15 or Tab 16 respectively, Abnormal Checklist. d. This checklist is complete. 4. ●If control force continues with MSW depressed: a. EICAS/SUMRY or FLT Page ...................... Select, Check Trims b. AIL or RUD Circuit Breaker (respective copilot’s or pilot’s FLIGHT group [TRIM]) ....... Pull Affected Axis c. Control Wheel Master (MSW) ....................................... Release d. Use asymmetric thrust & decrease airspeed as required to minimize mistrim. e. Autopilot ................................................................... As Desired f. Yaw Damper ...................................................................Engage g. Refer to Abnormal Landings for the respective Rudder or Aileron Trim Tab Jammed Landing procedure, TAB 35 or TAB 34 respectively, Abnormal Checklist. h. This checklist is complete.
(Procedure Continued) CL-126B October 2004 Change 1
EFFECTIVITY 45-002 thru 45-225 not modifiedALL by SB 45-55-6
3 4 5 6
Roll or Yaw Axis Uncommanded Motion
Change 1
2
E-21
7 8 9 10 11 12 13 14 15 16 17
2 3 4 5 6 7 8 9 10
4. zIf control force relieves with MSW depressed: a. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) ..........................................................Pull b. RUD BOOST .......................................................................OFF c. Control Wheel Master (MSW) .......................................Release d. Maintain 33,000 feet or below. e. Airspeed ............................... ≥ 0.65 MI Until Below 33,000 Feet f. Refer to PFD Annunciations, AP procedure, TAB 11, this checklist or TAB 25, Abnormal Checklist as appropriate. g. Land as soon as practical. h. This checklist is complete.
Rudder Control Jam 1. Attitude Control.......................................................... As Required Use Roll Control & Thrust as Necessary 2. 3. 4. 5. 6. 7. 8.
11 12 13 14 15 16 17
Yaw Damper......................................... Off (Use Glareshield Button) RUD BOOST.............................................................................. OFF Do Not use RUDDER TRIM. Use asymmetric thrust if required to minimize sideslip. Airspeed......................................................... Reduce as Necessary Land as soon as possible. Refer to Abnormal Landings, Rudder Jammed Landing, TAB 35, Abnormal Checklist.
FUELPRESS PRESSLOW LOW LLFUEL R FUEL PRESS LOW R FUEL PRESS LOW LR FUEL PRESS LOW LR FUEL PRESS LOW
L FUEL PRESS LOW
R FUEL PRESS LOW
Affected engine: 1. STBY (FUEL) ............................................................................... ON 2. IGN .............................................................................................. ON 3. XFLOW (FUEL)...................................................................... Closed If FUEL PRESS LOW remains illuminated: a. A descent to a lower altitude, but not below the minimum safe altitude, is recommended. This will improve the suction feed capability of the engine driven fuel pump. b. Flight can be continued at altitude if engines are operating properly. Make thrust lever movements slow & cautious at high altitudes.
E-22
EFFECTIVITY 45-002 thru 45-225 not modifiedALL by SB 45-55-6
CL-126B October 2004
Recovery from Inadvertent Overspeed 1
“OVERSPEED” 1. 2. 3. 4. 5. 6.
Thrust Levers ...........................................................................IDLE Autopilot .........................................................................Disengage SPOILER .................................................................................... EXT Identify aircraft pitch & roll attitude. Level wings. Elevator & Pitch Trim..................................................As Required
7. Yaw Damper .................................................................... As Desired
1. Control Wheel Master (MSW)............................... Depress & Hold 2. Attitude Control ..........................................................As Required 3. Airspeed ......................................................... ≤ Mach Trim Off MMO 4. ●If accompanied by SPOILERS FAIL amber CAS or SPOILER JAM amber CAS: a. Control Wheel Master (MSW) ....................................... Release b. Yaw Damper ............................................................. As Desired c. Refer to respective SPOILERS FAIL or SPOILER JAM procedure, Tab 15 or Tab 16 respectively, Abnormal Checklist. d. This checklist is complete. 4. ●If control force continues with MSW depressed: a. EICAS/SUMRY or FLT Page ...................... Select, Check Trims b. AIL or RUD Circuit Breaker (respective copilot’s or pilot’s FLIGHT group [TRIM]) ....... Pull Affected Axis c. Control Wheel Master (MSW) ....................................... Release d. Use asymmetric thrust & decrease airspeed as required to minimize mistrim. e. Autopilot ................................................................... As Desired f. Yaw Damper ............................................................. As Desired g. Refer to Abnormal Landings for the respective Rudder or Aileron Trim Tab Jammed Landing procedure, TAB 35 or TAB 34 respectively, Abnormal Checklist. h. This checklist is complete.
(Procedure Continued) EFFECTIVITY 45-226 & on, and prior aircraft ALL modified by SB 45-55-6
3 4 5 6
Roll or Yaw Axis Uncommanded Motion
CL-126B October 2004 Change 1
2
E-21.1
7 8 9 10 11 12 13 14 15 16 17
2 3 4 5 6 7 8 9
4. zIf control force relieves with MSW depressed: a. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) ..........................................................Pull b. RUD BOOST .......................................................................OFF c. Control Wheel Master (MSW) .......................................Release d. Refer to PFD Annunciations, AP procedure, TAB 11, this checklist or TAB 25, Abnormal Checklist as appropriate. e. This checklist is complete.
Rudder Control Jam 1. Attitude Control.......................................................... As Required Use Roll Control & Thrust as Necessary 2. 3. 4. 5. 6. 7. 8.
Yaw Damper......................................... Off (Use Glareshield Button) RUD BOOST.............................................................................. OFF Do Not use RUDDER TRIM. Use asymmetric thrust if required to minimize sideslip. Airspeed......................................................... Reduce as Necessary Land as soon as possible. Refer to Abnormal Landings, Rudder Jammed Landing, TAB 35, Abnormal Checklist.
10 11 12 13 14 15 16 17
FUELPRESS PRESSLOW LOW LLFUEL R FUEL PRESS LOW R FUEL PRESS LOW LR FUEL PRESS LOW LR FUEL PRESS LOW
L FUEL PRESS LOW
R FUEL PRESS LOW
Affected engine: 1. STBY (FUEL) ............................................................................... ON 2. IGN .............................................................................................. ON 3. XFLOW (FUEL)...................................................................... Closed If FUEL PRESS LOW remains illuminated: a. A descent to a lower altitude, but not below the minimum safe altitude, is recommended. This will improve the suction feed capability of the engine driven fuel pump. b. Flight can be continued at altitude if engines are operating properly. Make thrust lever movements slow & cautious at high altitudes.
E-22.1
EFFECTIVITY 45-226 & on, and prior aircraft ALL modified by SB 45-55-6
CL-126B October 2004
Multi-Function Display (MFD) Annunciations 1
HDG FAIL Refer to Loss of PFD Attitude or Heading Displays procedure, TAB 23, Abnormal Checklist.
2 3
HDG TEST Indicates the AHRS is in the power-up alignment mode and illuminates in the center of the heading display. Alignment requires approximately 2 minutes on the ground or 20 seconds in flight.
4 5
RA NO BRG Located in upper right corner of TCAS zoom window and indicates that an RA has been encountered, but no bearing to that RA is available for display.
6
1. Attempt to visually acquire intruder aircraft. 2. Request assistance from air traffic control in acquiring the intruder aircraft.
7 8
TERR TEST Located in the upper left corner of the MFD and indicates the EGPWS self test is in progress.
9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
E-23
Primary Flight Display (PFD) Annunciations 2 3 4 5 6 7 8 9 10 11
AP AP 1. Control Wheel Master (MSW) .................................. Depress & Hold Until WHEEL MSTR white CAS is Illuminated, then Release 2. ●If the amber AP remains illuminated & is accompanied by an amber YD or RB: a. Maintain 33,000 feet or below. b. Airspeed ............................ ≥ 0.65 MI Until Below 33,000 Feet c. Land as soon as practical. d. This checklist is complete. 2. ●If the amber AP remains illuminated & is not accompanied by an amber YD or RB: a. Yaw Damper.................................................................. Engage b. This checklist is complete. 2. ●If the amber AP extinguishes: a. Yaw Damper.................................................................. Engage b. Autopilot ..................................................... Engage, as Desired c. This checklist is complete.
ATT FAIL Refer to Loss of PFD Attitude or Heading Displays procedure, TAB 23, Abnormal Checklist.
HDG FAIL
12
Refer to Loss of PFD Attitude or Heading Displays procedure, TAB 23, Abnormal Checklist.
13 HDG TEST
14 15
Indicates the AHRS is in the power-up alignment mode and illuminates in the center of the heading display. Alignment requires approximately 2 minutes on the ground or 20 seconds in flight.
16 17
E-23.1 E-24
EFFECTIVITY 45-002 thru 45-225 not modified by ALL SB 45-55-6
CL-126B October 2004
Multi-Function Display (MFD) Annunciations HDG FAIL
1
Refer to Loss of PFD Attitude or Heading Displays procedure, TAB 23, Abnormal Checklist.
2
HDG TEST Indicates the AHRS is in the power-up alignment mode and illuminates in the center of the heading display. Alignment requires approximately 2 minutes on the ground or 20 seconds in flight.
RA NO BRG Located in upper right corner of TCAS zoom window and indicates that an RA has been encountered, but no bearing to that RA is available for display. 1. Attempt to visually acquire intruder aircraft. 2. Request assistance from air traffic control in acquiring the intruder aircraft.
3 4 5 6 7
TERR TEST
8
Located in the upper left corner of the MFD and indicates the EGPWS self test is in progress.
9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
E-23.2 E-23
Primary Flight Display (PFD) Annunciations 2 3 4 5 6 7 8
AP 1. Control Wheel Master (MSW)...................................Depress & Hold Until WHEEL MSTR white CAS is Illuminated, then Release 2. ●If the amber AP remains illuminated & is accompanied by an amber YD or RB: a. This checklist is complete. 2. ●If the amber AP remains illuminated & is not accompanied by an amber YD or RB: a. Yaw Damper..............................................................As Desired b. This checklist is complete. 2. ●If the amber AP extinguishes: a. Yaw Damper..............................................................As Desired b. Autopilot ......................................................Engage, as Desired c. This checklist is complete.
9 ATT FAIL
10
Refer to Loss of PFD Attitude or Heading Displays procedure, TAB 23, Abnormal Checklist.
11 HDG FAIL
12
Refer to Loss of PFD Attitude or Heading Displays procedure, TAB 23, Abnormal Checklist.
13 HDG TEST
14 15
Indicates the AHRS is in the power-up alignment mode and illuminates in the center of the heading display. Alignment requires approximately 2 minutes on the ground or 20 seconds in flight.
16 17
E-24.1 E-23.3
EFFECTIVITY 45-226 & on, and prior aircraft modified by SB ALL 45-55-6
CL-126B October 2004
WIND SHR “WINDSHEAR, WINDSHEAR, WINDSHEAR”
1
During takeoff: 1. Thrust Lever(s) ...............................Select T/O or APR, As Required 2. Maintain take-off target pitch attitude and wings level, allowing airspeed to decrease if necessary. Do not retract flaps or gear. 3. If the aircraft continues to descend, increase pitch target attitude smoothly and in small increments, bleeding airspeed as necessary to stop the descent. Use stall warning onset (stick shaker) as the upper limit of pitch attitude. 4. Maintain escape attitude and thrust and delay retracting flaps or landing gear until safe climb-out is assured.
2 3 4 5 6
During final approach:
7 1. Immediately initiate go-around procedure except do not retract flaps or landing gear. 2. Thrust Lever(s) ...............................Select T/O or APR, As Required 3. Rotate smoothly to the go-around/take-off pitch attitude, allowing airspeed to decrease if necessary. Maintain wings level. 4. If the aircraft continues to descend, increase pitch target attitude smoothly and in small increments, bleeding airspeed as necessary to stop the descent. Use stall warning onset (stick shaker) as the upper limit of pitch attitude. 5. Maintain escape attitude and thrust and delay retracting flaps or landing gear until safe climb-out is assured.
8 9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
E-25 E-23.4
PULL PULLUP UP
2
“PULL UP” “TERRAIN, TERRAIN, PULL UP”
3 4 5 6 7 8 9 10 11 12
“OBSTACLE, OBSTACLE, PULL UP 1. 2. 3. 4. 5. 6. 7.
Autopilot ........................................................................ Disengage Thrust Lever(s)...........................Select T/O or APR, As Required Increase pitch attitude and climb as required to avoid terrain. SPOILER Lever......................................................................... RET Flaps ............................................Retract (8° or UP), As Required Gear............................................................................................. UP Flaps ........................................................................................... UP
8. EGPWS Terrain Awareness Display ......................................Monitor 9. Maintain climb attitude until the warning ceases. 10. Notify the controlling agency.
RA RA FAIL FAIL Located below the VSI display and indicates resolution advisory information from the TCAS computer is corrupt. This can occur with or without an actual intruder aircraft being present. 1. Attempt to visually acquire possible intruder aircraft. 2. RMU (ATC/TCAS)..........................................Select TA ONLY Mode
13 14 15 16 17
EFFECTIVITY
E-23.5 E-26
ALL
CL-126B October 2004
EMER/PARKBRK BRK EMER/PARK 1
Refer to Takeoff “Configuration”, TAB 14, this checklist.
GEAR GEAR
“GEAR”
GEAR
1. ●If adequate time is available to extend gear: a. AUX HYD ..............................................................................ON b. Gear ..................................................................................... DN c. This checklist is complete. 1. ●If adequate time is not available to extend gear: a. Execute a go-around. b. This checklist is complete.
2 3 4 5 6
NORMBRK BRKFAIL FAIL NORM
“BRAKES FAIL”
NORMAL BRAKES FAIL
1. ●If failure occurs just after gear extension and conditions permit: a. Gear ...................................................................................... UP b. INBD BRAKES (pilot’s GEAR/HYDRAULICS group) & OUTBD BRAKES (copilot’s GEAR/HYD group) Circuit Breakers............................................Set or Pull & Reset c. AUX HYD ..............................................................................ON d. Gear ...................................................................................... DN e. ■If NORM BRK FAIL red CAS & NORMAL BRAKES FAIL red CWP extinguish: (1) This checklist is complete. e. ■If NORM BRK FAIL red CAS & NORMAL BRAKES FAIL red CWP remain illuminated: (1) Go to step 2. 1. ●If failure is not associated with gear extension: a. Go to step 2. 2. Refer to one of the following: Emergency Braking procedure, next page. Abnormal Landings, Emergency Brake Landing procedure, TAB 33, Abnormal Checklist.
7 8 9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
E-27
Emergency Braking 2
1. EMERGENCY/PARKING BRAKE.............................Pull Smoothly
3
Nose Wheel Steering Malfunction 4 5 6 7 8 9 10 11 12 13 14 15 16 17
Change 1
1. Control Wheel Master (MSW)......................... Depress & Release 2. Thrust Levers .......................................................................... IDLE 3. Brake to a stop. Use differential brakes as necessary. 4. Taxi using differential brakes & thrust.
Ditching 1. If time & conditions permit: a. Head toward nearest land or vessel. b. Notify controlling agency. c. Transponder ....................................................................... 7700 d. ELT (if installed).................................................................... ON e. Crew Life Vests...................................................................... On f. Shoulder Harnesses....................................................... Locked g. Brief passengers as required. (1) Use of available flotation equipment. Inform passengers not to inflate life vests (if applicable) while inside aircraft. (2) Location & operation of emergency exits. Do not open lower half of cabin door. (3) Secure all loose items. (4) Emergency landing brace position. (5) Several impacts may be felt, depending on the sea conditions. Do not release seat belts after first impact is felt. h. NO SMOKING BELTS ........................................................... On i. Seat belts ............................................... On Until Aircraft Stops 2. Gear .............................................................................................UP 3. FLAPS ........................................................................................ DN 4. PACK.......................................................................................... OFF 5. Perform normal approach at VREF. 6. Thrust Levers ............................................... CUTOFF at Touchdown 7. L & R FIRE (ENGINE).......................................................... Depress 8. EMER BATT, L & R BATT .......................................................... OFF 9. Emergency Exit(s)....................................Open After Airplane Stops Do Not Open Lower Half of Cabin Door EFFECTIVITY
E-28
ALL
CL-126B October 2004 Change 1
Forced Landing — Both Engines Inoperative Airplane Best Glide Speed (Gear — UP, FLAPS — UP) is 160 KIAS (approximately 2 nm per 1000 feet of altitude)
1 2
1. If time & conditions permit: a. Transponder ....................................................................... 7700 b. Advise controlling agency. c. Prepare passengers for emergency landing. d. NO SMOKING BELTS........................................................... On 2. GEAR FREEFALL..............................PUSH DOWN & Lock Forward 3. AUX HYD ..................................................................................... ON 4. Gear .............................................................................................DN 5. HYD XFLOW ............................................................................... ON 6. FLAPS .........................................................................................DN 7. HYD XFLOW ................................................................................ Off 8. Shoulder Harnesses .............................................................. Locked 9. L & R FIRE (ENGINE) ....................................................FIRE PUSH 10. Touch down in normal landing attitude. After airplane comes to a complete stop: 11. EMERGENCY/PARKING BRAKE................................................ Set 12. Thrust Levers...................................................................... CUTOFF 13. EMER LIGHTS ............................................................................ ON 14. EMER BATT, L & R BATT ...........................................................OFF 15. Evacuate the aircraft: a. Cabin Entry Door .................................................... Open & Exit b. Aft Emergency Exit.................................................. Open & Exit
3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
E-29
“STALL” Voice Activates “STALL” 2 3
1. 2. 3. 4.
Lower the pitch attitude to reduce angle of attack. Thrust Levers .................................T/O (Manual APR if Required) Level the wings. Accelerate out of stall condition.
4 5 6 7 8
Aborted Takeoff 1. Brakes .....................................................................................Apply 2. Thrust Levers .......................................................................... IDLE 3. Spoilers .................................................................... Verify Extended If spoilers are not extended automatically: a. SPOILER Lever .................................................................. EXT 4. Thrust Reversers .............................................. Deploy, if Necessary 5. Refer to the AFM for further disposition.
9 10
Takeoff “CONFIGURATION” “CONFIGURATION” Voice Activates
11
EMER/PARK BRK
12
PIT TRIM BIAS
13
PIT TRIM MSCMP
14
SPOILERS EXT
15
TAKEOFF TRIM
16 17
UNL OR DEP (EI) 1. Brakes.......................................................................................Apply 2. Thrust Levers .............................................................................IDLE 3. After stopping, check takeoff configuration.
Change 1 EFFECTIVITY
E-30
ALL
CL-126B October 2004 Change 1
L REV UNSAFE UNL ORUNSAFE DEP (EI) R REV
L REV R REV “LEFT” or UNSAFE UNSAFE “RIGHT REVERSER UNSAFE”
1
During takeoff:
2
Below V1 Speed
3
1. Brakes..................................................................................... Apply 2. Thrust Levers ...........................................................................IDLE 3. Spoilers.....................................................................Verify Extended If spoilers are not extended automatically: a. SPOILER Lever.................................................................. EXT Above V1 Speed: 1. 2. 3. 4. 5.
Attitude Control ..........................................................As Required Accelerate to VR. Keep nose wheel on the ground. Rotate at VR; Climb at V2. Gear ............................................................................................ UP Climb to 1500 feet AGL or Obstacle Clearance Altitude (as appropriate), accelerate to V2 + 25, then retract flaps.
6. Respective Engine Thrust Lever................................................ IDLE 7. Respective DEPLOY Circuit Breaker (ENGINE group [L or R REVERSER])......................................... Pull 8. Respective ANN & STOW Circuit Breakers (ENGINE group [L or R REVERSER])......................................... Set 9. ●If REV UNSAFE red CWP, & UNL or DEP red EI remain illuminated: a. Respective Thrust Lever ..............................................CUTOFF Refer to Engine Shutdown in Flight procedure, TAB 10, Abnormal Checklist, & Abnormal Landings, Thrust Reverser Deployed Landing procedure, TAB 38, Abnormal Checklist. b. This checklist is complete. 9. ●If REV UNSAFE red CWP, & UNL or DEP red EI extinguish: a. Respective Thrust Lever ........................................ As Required b. This checklist is complete.
(Procedure Continued)
4 5 6 7 8 9 10 11 12 13 14 15 16 17
Change 1
CL-126B October 2004 Change 1
EFFECTIVITY ALL
E-31
In flight:
2 3 4 5 6 7 8 9 10 11 12 13
1. Control Wheel Master (MSW) .............................Depress & Release Yaw damper & autopilot will disengage. On aircraft 45-002 thru 45-294 not modified by SB 45-27-20, spoilers will blow down while the MSW is depressed. 2. Attitude Control .............................................................. As Required 3. Thrust Lever (operative engine) ...................... Increase as Required 4. Thrust Lever (deployed engine) .................................................IDLE 5. Airspeed .................................................................... ≤ 160 KIAS As Required to Maintain Flight 6. Maintain 30,000 feet or below, or minimum safe altitude. 7. Respective DEPLOY Circuit Breaker (ENGINE group [L or R REVERSER]) .........................................Pull 8. Respective ANN & STOW Circuit Breakers (ENGINE group [L or R REVERSER]) ......................................... Set 9. Respective Thrust Reverser Lever.............................................Stow 10. ●If REV UNSAFE red CWP, & UNL or DEP red EI remain illuminated: a. Thrust Lever (deployed engine)................................... CUTOFF b. ENG SYNC Switch ..............................................................OFF c. Rudder Trim............................................................ As Required d. Yaw Damper ........................................................... As Required e. Refer to Engine Shutdown in Flight procedure, TAB 10, Abnormal Checklist, & Abnormal Landings, Thrust Reverser Deployed Landing procedure, TAB 38, Abnormal Checklist. f. This checklist is complete. 10. ●If REV UNSAFE red CWP, & UNL or DEP red EI extinguish: a. Thrust Levers ......................................................... As Required b. Yaw Damper ........................................................... As Required c. This checklist is complete.
14 15 16 17 Change 1
EFFECTIVITY
E-32
ALL
CL-126B October 2004 Change 1
ABNORMAL PROCEDURES This section contains those operating procedures requiring the use of special systems and/or alternate use of regular systems which, if followed, will maintain an acceptable level of airworthiness or reduce operational risk resulting from a failure condition. The procedures located in this section are to be used when a failure condition exists. Sound judgement as well as thorough knowledge of the aircraft, its characteristics, and the flight manual procedures are essential in the handling of any failure condition. In addition to the outlined items in the Abnormal Procedures, the following steps are considered part of all abnormal situations: • Maintain Airplane Control • Analyze the Situation • Take Proper Action
Voice
and Crew Warning Panel (CWP) Annunciations
Voice annunciations will be preceded by an audio symbol (headings only) and in all capital letters within quotes. CWP annunciations will be presented by all capital letters and are usually accompanied by a CAS.
Symbols and “If” Statements Certain procedures are dependent on prescribed conditions. These conditions are presented in bold as independent “If” statements. “If” statements preceded by a symbol (e.g. ●, ■ or ▲) indicate more than one condition for that step. Other conditions for that step will be indicated by repeating that step and symbol. Procedures completed at any substep level will be noted. (e.g. This checklist is complete.) Procedures not completed at a substep level will direct the user to the next applicable step. (e.g. Go to step 3.) The last procedure of any substep will either state “This checklist is complete.” or “Go to step #.”, or refer the user to another appropriate procedure.
-
-
Circuit breakers that are “Set” should be checked for that normal condition. If the circuit breaker is not “Set”, it may be reset only once. If the circuit breaker opens again, do not reset. Circuit breakers that “Pull” should only be pulled and not reset. Circuit breakers that “Pull and Reset” should be pulled, delay for several seconds, and reset only once.
Allow sufficient cooling time for circuit breakers that are “Reset” or cycled through a “Pull and Reset.” EFFECTIVITY CL-126B October 2004
ALL
A-i
CAS or (EI) Message
Tab
ABNORMAL
Circuit Breakers Many procedures involve manipulating circuit breakers. The following criteria should be followed during “Circuit Breaker” steps.
Abnormal EICAS Index CAS or (EI) Message
ABNORMAL
AHRS 1 OVHT
Tab
CAS or (EI) Message
19
DEFUEL OPEN
Tab 16
AHRS 2 OVHT AHRS 1-2 OVHT ANTI-SKID FAIL L AOA HT FAIL R AOA HT FAIL LR AOA HT FAIL
19 19 29 1 1 1
DU 1 OVHT DU 2 OVHT DU 3 OVHT DU 4 OVHT LR ECS FAIL L ECS FAULT
20 20 20 20 12 13
AP AIL MISTRIM AP ELEV MISTRIM APU AMPS HIGH APU FAIL AUX HYD PMP LO AUX HYD QTY LO L BATT OVHT R BATT OVHT LR BATT OVHT L BLEED OVHT R BLEED OVHT
3 3 3 4 18 18 4 4 4 11 11
R
ECS FAULT EICAS CHK (MFD) ELEVATOR DISC EMER BATT LOW EMER BUS VOLTS EMER LIGHTS L EMER PRESS ON R EMER PRESS ON LR EMER PRESS ON EMERGENCY EXIT L ENG FIRE FAIL
13 24 14 4 5 6 13 13 13 4 6
LR BLEED OVHT BRK ACUM PRESS CAB DELTA P CAB DUCT OVHT LR CAB PRESS FAIL CAB PRESS MAN
11 18 11 11 12 12
R LR L R LR L
ENG FIRE FAIL ENG FIRE FAIL ENGCMPTR FAULT ENGCMPTR FAULT ENGCMPTR FAULT ENGINE CHIP
6 6 6 6 6 6
CABIN ALTITUDE CKPT DUCT OVHT CNFG MISMATCH CPLT BRK FAULT DAU 1A FAIL DAU 1B FAIL
12 12 19 29 19 19
R LR L R LR L
ENGINE CHIP ENGINE CHIP ESS BUS FAULT ESS BUS FAULT ESS BUS FAULT ESS BUS VOLTS
6 6 5 5 5 5
DAU 1A-1B FAIL DAU 2A FAIL DAU 2B FAIL DAU 2A-2B FAIL DAU ENG MISCMP DAU ENG MISCMP DAU SYS MISCMP DAU SYS MISCMP
19 19 19 19 20 20 20 20
R ESS BUS VOLTS LR ESS BUS VOLTS EXTERNAL DOORS FLAPS FAIL FLAPS FAULT L FUEL FILTER R FUEL FILTER LR FUEL FILTER
L R L R
5 5 4 14 14 16 16 16
EFFECTIVITY
A-ii
ALL
CL-126B October 2004
Abnormal EICAS Index (Cont) CAS or (EI) Message L
Tab
CAS or (EI) Message
Tab
FUEL HEATER
17
LR NAC HT FAIL ON
R FUEL HEATER LR FUEL HEATER FUEL IMBALANCE L FUEL QTY LOW R FUEL QTY LOW LR FUEL QTY LOW
17 17 17 17 17 17
L R LR L R
FUEL XFLO L FWSOV FAULT R FWSOV FAULT LR FWSOV FAULT GEAR L GEN AMPS HIGH R GEN AMPS HIGH LR GEN AMPS HIGH L GEN FAIL R GEN FAIL IC 1 OVHT
17 17 17 17 29 6 6 6 6 6 21
LR OUTBD BRK FAIL OXYGEN OFF OXYGEN QTY LOW OXY PRESS HI PACK OVHT PAX OXY FAIL L PFD CHECK R PFD CHECK LR PFD CHECK L PITOT HT R PITOT HT
30 13 13 14 14 14 21 21 21 1 1
21 21 1 1 9 30
LR PITOT HT PLT BRK FAULT PRI TRIM FAIL REV (EI) ROLL DISC RUD BOOST INOP
1 30 15 9 15 15
30 30 21 14 18 9
SAT HT FAIL SEC TRIM FAIL L SPOILER JAM R SPOILER JAM LR SPOILER JAM SPOILERS EXT
1 15 16 16 16 15
9 1 1 1 1 1
SPOILERS FAIL STAB TEMP LOW L STALLWARN FAIL R STALLWARN FAIL LR STALLWARN FAIL START (EI)
15 2 16 16 16 9
L
IC 2 OVHT IC BUS FAIL ICE DET FAIL ICE DETECTED IGN (EI) INBD BRK FAIL
R INBD BRK FAIL LR INBD BRK FAIL LBS/KGS CONFIG MACH TRIM FAIL MAIN HYD PRESS MAN (EI) L R LR L R
NAC (EI) NAC HT NAC HT NAC HT NAC HT FAIL ON NAC HT FAIL ON
NWS FAIL OIL FILTER OIL FILTER OIL FILTER OUTBD BRK FAIL OUTBD BRK FAIL
1 30 6 6 6 30 30
EFFECTIVITY CL-126B October 2004
ALL
A-iii
Abnormal EICAS Index (Cont) CAS or (EI) Message STBY PITOT HT SYNC (EI) UNL (EI) WARN AUDIO LR WARN PWR FAIL WING TEMP LOW
Tab
CAS or (EI) Message
Tab
2
L
WSHLD HT FAIL
2
10 10 21 21 2
R LR L R LR
WSHLD HT FAIL WSHLD HT FAIL WSHLD OVHT WSHLD OVHT WSHLD OVHT
2 2 3 3 3
EFFECTIVITY
A-iv
ALL
CL-126B October 2004
ABNORMAL PROCEDURES
TAB 1
ANTI-ICING AOA HT FAIL
2
ICE DET FAIL
1
ICE DETECTED
3
NAC HT NAC HT FAIL ON
4
PITOT HT SAT HT FAIL
5
STAB TEMP LOW STBY PITOT HT
2
WING TEMP LOW WSHLD HT FAIL
6 7
WSHLD OVHT Windshield Outer Ply Shattered or Cracked
8
Engine Ice Ingestion
9
Inadvertent Icing Encounter
3
AUTOPILOT
10
AP AIL MISTRIM AP ELEV MISTRIM
11
AUXILIARY POWER UNIT (APU) APU AMPS HIGH
12
APU FAIL
DOOR
13
EMERGENCY EXIT
4
EXTERNAL DOORS
14
ELECTRICAL BATT OVHT
15
EMER BATT LOW EMER BUS VOLTS
5
ESS BUS FAULT ESS BUS VOLTS
17 TAB
CL-126B October 2004
16
EFFECTIVITY ALL
A-1
TAB
ELECTRICAL (Cont) GEN AMPS HIGH
2 3 4
GEN FAIL
EMERGENCY LIGHTS 6
EMER LIGHTS
ENGINE ENG FIRE FAIL ENGCMPTR FAULT
5 6
ENGINE CHIP OIL FILTER Engine Airstart
7 8
7
ENG CMPTR ON (Auto Mode)
8
ENG CMPTR - MAN or OFF Engine Indications (EIs) IGN
9
MAN
9
NAC REV
10
START
11
SYNC UNL
12
10
Engine Overspeed Engine Shutdown in Flight
13
ENVIRONMENTAL/PRESSURIZATION BLEED OVHT
14 15 16 17
11
CAB DELTA P CAB DUCT OVHT CAB PRESS FAIL CAB PRESS MAN
12
CABIN ALTITUDE CKPT DUCT OVHT ECS FAIL
18 TAB EFFECTIVITY
A-2
ALL
CL-126B October 2004
ENVIRONMENTAL/PRESSURIZATION (Cont)
TAB
ECS FAULT
1
EMER PRESS ON
13 2
Inadvertent Activation of Emergency Airflow OXYGEN OFF
3
OXYGEN QTY LOW OXY PRESS HI
4
PACK OVHT PAX OXY FAIL
14
FLIGHT CONTROLS
5
ELEVATOR DISC
6
FLAPS FAIL FLAPS FAULT
7
MACH TRIM FAIL PRI TRIM FAIL
8
ROLL DISC RUD BOOST INOP
15
SEC TRIM FAIL SPOILERS EXT
9 10
SPOILERS FAIL SPOILER JAM
11
STALLWARN FAIL Jammed Stabilizer PRI TRIM FAIL & SEC TRIM FAIL
FUEL
12 16
13
DEFUEL OPEN
14
FUEL FILTER FUEL HEATER
15
FUEL IMBALANCE FUEL QTY LOW FUEL XFLO
17
16
FWSOV FAULT
17
STBY PUMP Fails ON
TAB CL-126B October 2004
EFFECTIVITY ALL
A-3
TAB HYDRAULICS AUX HYD PMP LO
2 3 4 5
AUX HYD QTY LO
18
BRK ACUM PRESS MAIN HYD PRESS
INSTRUMENTS/AVIONICS AHRS OVHT
19
CNFG MISMATCH DAU 1 FAIL
6
DAU 2 FAIL
7
DAU SYS MISCMP
DAU ENG MISCMP
20
DU OVHT
8
IC OVHT IC 1 or 2 Failure
9
IC BUS FAIL
21
LBS/KGS CONFIG
10
PFD CHECK WARN AUDIO
11 12 13 14 15
WARN PWR FAIL Air Data Computer (ADC) Failure — Single Air Data Computer (ADC) Failure — Dual
22
Display Unit Failure Erroneous Pitot-Static Indications Loss of PFD Attitude or Heading Displays
23
Loss of Standby Attitude Indicator Multi-Function Display (MFD) Annunciations EICAS CHK DGX
16
24
MAGX MENU INOP
17
STAB
18
TA NO BRG TCAS FAIL
TAB EFFECTIVITY
A-4
ALL
CL-126B October 2004
INSTRUMENTS/AVIONICS (Cont)
TAB
TERR FAIL TERR N/A
24
TGT
1 2
WX Primary Flight Display (PFD) Annunciations
3
ADCX ALT
4
AOA AP (flash)
5
AP (steady)
25
AP FAIL
6
AP TEST
7
ATT CAS MSG
8
DGX FD FAIL
9
GND PROX GS
26
HDG IAS
10 11
ILS LOC
12
MACH MAGX
13
MAXSPD MIN
27
PIT
14 15
RA —RA—
16
RA FAIL RB
17
CL-126B October 2004
EFFECTIVITY ALL
TAB A-5
TAB
INSTRUMENTS/AVIONICS (Cont) 2 3 4 5 6
ROL SGX TCAS FAIL TGT WIND SHR WX YD (flash) YD (steady) Radio Management Unit (RMU) Failure
LANDING GEAR/BRAKES
29
ANTI-SKID FAIL
7
28
CPLT BRK FAULT GEAR
8
INBD BRK FAIL
30
NWS FAIL
9 10 11 12 13 14 15 16 17 18
OUTBD BRK FAIL PLT BRK FAULT Landing Gear AUX HYD Extension Landing Gear Free Fall
LANDINGS
31
ANTI-ICING Stabilizer Heat Failure Landing (STAB TEMP LOW) Wing & Stabilizer Heat Failure Landing (STAB & WING TEMP LOW) Wing Heat Failure Landing (WING TEMP LOW)
32
ELECTRICAL Normal Electrical System Failure Landing EMERGENCY BRAKE Emergency Brake Landing (NORM BRK FAIL red CAS) (INBD BRK FAIL amber CAS) (OUTBD BRK FAIL amber CAS)
33
TAB EFFECTIVITY
A-6
ALL
CL-126B October 2004
LANDINGS (Cont)
TAB 1
ENGINE Single-Engine Landing
33
FLIGHT CONTROLS Aileron Jammed Landing (ROLL DISC white CAS)
2 3
Aileron Trim Tab Jammed Landing
4
Elevator Jammed Landing (ELEVATOR DISC white CAS)
34
Partial Flap Landing (FLAPS FAIL)
5
Rudder Jammed Landing
6
Rudder Trim Tab Jammed Landing Spoilers Extended Landing (SPOILER EXT or SPOILER FAIL)
35
7 8
Spoiler Jammed Landing (L SPOILER JAM) (R SPOILER JAM)
9
Stabilizer Jammed Landing
36
HYDRAULIC FAILURE
10
Main Hydraulic System Failure Landing (MAIN HYD PRESS) GEAR UP
11 37
Gear Up Landing THRUST REVERSER Thrust Reverser Deployed Landing
38
12 13 14 15 16 17
TAB Change 1 CL-126B October 2004 Change 1
EFFECTIVITY ALL
A-7
19
AOAHT HTFAIL FAIL LLAOA R AOA HT FAIL R AOA HT FAIL LR AOA HT FAIL LR AOA HT FAIL
20
1. Respective AOA Circuit Breaker (ANTI-ICE group [L or R PROBES HT]) ............ Set, or Pull & Reset
21
If AOA HT FAIL remains illuminated: a. Fly out of icing conditions as soon as practical.
22 23 24 25 26 27 28 29
ICEDET DETFAIL FAIL ICE 1. ICE DETECT Circuit Breaker (copilot’s ANTI-ICE group)................................. Set, or Pull & Reset If SAT is between +10° C & -40° C, & visible moisture or night: a. Thrust Levers ............................................................ ≤ MCT b. WING/STAB.......................................................................... ON c. L & R NAC............................................................................ ON
ICEDETECTED DETECTED ICE 1. 2. 3. 4. 5.
Thrust Levers ................................................................... ≤ MCT WING/STAB ................................................................................ ON L & R NAC .................................................................................. ON L & R WSHLD ...................................................................Check On HI FLOW ......................................................................................Off
30 31 32 33 34 18
NACHT HT LLNAC NACHT HT RRNAC LRNAC NACHT HT LR Affected engine: 1. IGN .............................................................................................. ON 2. Engine N1 .............................................. Increase to Improve Airflow 3. NAC Circuit Breaker (ANTI-ICE group [L or R HEAT]).................................................... Set, or Pull & Reset If NAC HT remains illuminated: a. Fly out of icing conditions as soon as possible. EFFECTIVITY ALL
A-8
CL-126B October 2004
NACHT HTFAIL FAILON ON LLNAC R NAC HT FAIL ON R NAC HT FAIL ON LR NAC HT FAIL ON LR NAC HT FAIL ON
1
Affected engine: 1. NAC Circuit Breaker (ANTI-ICE group [L or R HEAT])................................................... Set, or Pull & Reset
2
PITOTHT HT LLPITOT R PITOT HT R PITOT HT LR PITOT HT LR PITOT HT
4
3
5
1. Respective L or R PROBES .............................................. Check On 2. Respective PITOT Circuit Breaker (ANTI-ICE group [L or R PROBES HT]) ............ Set, or Pull & Reset If PITOT HT remains illuminated: a. Fly out of icing conditions as soon as possible. b. Cross-check the three pitot-static systems.
6 7 8
If PITOT HT is accompanied by erroneous pitot-static indications: (1) Refer to Erroneous Pitot-Static Indications procedure, TAB 23, this checklist.
9 10 11
SATHT HTFAIL FAIL SAT
12
1. SAT Circuit Breaker (copilot’s ANTI-ICE group [R PROBES HT])............................................... Set, or Pull & Reset
13
If SAT HT FAIL remains illuminated: a. Fly out of icing conditions as soon as practical.
14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
A-9
STABTEMP TEMPLOW LOW STAB 2 3 4 5
1. Engine N1 ............................................................................ Increase 2. L & R WING/STAB HT Circuit Breaker (ANTI-ICE group) ............................................... Set, or Pull & Reset If STAB TEMP LOW remains illuminated: a. Fly out of icing conditions as soon as possible. b. Do not extend flaps beyond 8°. c. Refer to Abnormal Landings, Stabilizer Heat Failure Landing procedure, TAB 31, this checklist.
6 7 8 9 10
STBYPITOT PITOTHT HT STBY 1. R PROBES ........................................................................Check On 2. STBY PITOT Circuit Breaker (copilot’s ANTI-ICE group [R PROBES HT])...... Set, or Pull & Reset If STBY PITOT HT remains illuminated: a. Fly out of icing conditions as soon as practical. b. Cross-check the three pitot-static systems. If STBY PITOT HT is accompanied by erroneous pitot-static indications: (1) Refer to Erroneous Pitot-Static Indications procedure, TAB 23, this checklist.
11 12 13 14 15 16 17 18
EFFECTIVITY
A-10
ALL
CL-126B October 2004
WINGTEMP TEMPLOW LOW WING 1. L & R IGN .................................................................................... ON 2. Engine N1 ............................................................................ Increase 3. L & R WING/STAB HT Circuit Breaker (ANTI-ICE group)............................................... Set, or Pull & Reset If WING TEMP LOW remains illuminated: a. Fly out of icing conditions as soon as possible. b. Do not extend flaps beyond 8°. c. Refer to Abnormal Landings, Wing Heat Failure Landing procedure, TAB 32, this checklist. d. Visually inspect wing for ice accumulation if possible. Use WING INSP light at night.
1 2 3 4 5 6 7
WSHLDHT HTFAIL FAIL LLWSHLD WSHLDHT HTFAIL FAIL RRWSHLD LR WSHLD HT FAIL LR WSHLD HT FAIL
8
1. Respective L or R IGN............................... ON, if in Icing Conditions 2. Respective WSHLD Circuit Breaker (ANTI-ICE group [L or R HEAT])........................ Set, or Pull & Reset 3. Respective L or R WSHLD .......................................... OFF, then On 4. ●If WSHLD HT FAIL remains illuminated: a. Fly out of icing conditions as soon as possible. b. Moving the COCKPIT & CABIN TEMPERATURE knobs to HOT will help reduce fogging. c. This checklist is complete. 4. ●If respective L or R WSHLD OVHT amber CAS is also illuminated: a. Refer to WSHLD OVHT procedure, TAB 3, this checklist.
9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
A-11
2 3 4 5 6 7 8 9 10
WSHLDOVHT OVHT LLWSHLD WSHLDOVHT OVHT RRWSHLD LR WSHLD OVHT LR WSHLD OVHT 1. Respective L or R WSHLD ........................................................ OFF 2. Fly out of icing conditions as soon as practical. 3. Moving the COCKPIT & CABIN TEMPERATURE knobs to HOT will help reduce fogging.
Windshield Outer Ply Shattered or Cracked Windshield structural integrity is maintained (outer ply is not structural). 1. 2. 3. 4. 5. 6.
Respective L or R WSHLD ........................................................ OFF Respective L or R IGN ............................... ON, if in Icing Conditions Fly out of icing conditions as soon as practical. Maintain 25,000 feet or below or minimum safe altitude. MANUAL PRESS......................................................................... ON MANUAL Rate Control..........................UP, to Reduce Delta P ≤ 6.5 Maintain Cabin Altitude ≤ 8000 Feet 7. Moving the COCKPIT & CABIN TEMPERATURE knobs to HOT will help reduce fogging. 8. Land as soon as practical.
11
Engine Ice Ingestion 12 13 14 15
1. L & R IGN....................................................ON for Duration of Flight 2. Avoid any abrupt changes in pitch, yaw, or roll. To determine extent of engine damage due to ice ingestion, proceed as follows: a. Thrust Levers (one at a time): Slowly & cautiously retard to IDLE, then slowly & cautiously advance & check for vibration/abnormal noise on each engine. If either engine flames out: (1) Airstart in accordance with Engine Airstart procedure, TAB 7, this checklist. After restart, repeat step 2, but stay below engine speed at which engine flamed out.
16 17 18
If ice damage has been experienced: (1) Engine N1 ..................................................Low as Possible Sufficient for Anti-icing & Cabin Pressure (2) Land as soon as practical. 3. Fly out of icing conditions as soon as possible. EFFECTIVITY
A-12
ALL
CL-126B October 2004
Inadvertent Icing Encounter 1. 2. 3. 4. 5. 6.
Thrust Levers .................................................................... ≤ MCT WING/STAB ................................................................................ ON L & R NAC .................................................................................. ON L & R WSHLD ................................................................... Check On HI FLOW ...................................................................................... Off Do not extend flaps beyond 8° until the wing/stab anti-ice system has been on for 2 minutes.
APAIL AILMISTRIM MISTRIM AP
1 2 3 4 5
If condition persists: 1. Flight Controls .................................................................Hold Firmly 2. Airspeed ....................................................................... ≤ 0.78 MI 3. Autopilot..................... Use Control Wheel Trim Switch to Disengage 4. Fuel Balance............................................................Check & Correct 5. Retrim aircraft if necessary. 6. Autopilot........................................................................... As Desired 7. Airspeed .......................................................................... As Desired If AP AIL MISTRIM recurs and condition persists: 8. Airspeed ....................................................................... ≤ 0.78 MI 9. Obtain maintenance before next flight.
6 7 8 9 10 11
APELEV ELEVMISTRIM MISTRIM AP If condition persists: 1. Flight Controls .................................................................Hold Firmly 2. Autopilot..................... Use Control Wheel Trim Switch to Disengage 3. Retrim aircraft if necessary.
12 13 14
APUAMPS AMPSHIGH HIGH APU
15
1. Electrical Load ..................................................Reduce As Required
16 17
Change 1
CL-126B October 2004 Change 1
EFFECTIVITY ALL
A-13
APUFAIL FAIL APU
APU FAIL
2 3 4 5
1. APU MASTER...............................................................................Off 2. ●If APU FAIL indication extinguishes: a. Inspect APU and aircraft tailcone area prior to flight to ensure airworthiness. b. APU Fire Bottle.................................................Proper Pressure 2. ●If APU FAIL indication remains illuminated: a. Do not take off.
6
EMERGENCYEXIT EXIT EMERGENCY
7
DO NOT APPROACH HATCH
8 9 10 11 12
1. NO SMOKING BELTS.............................................................BELTS
EXTERNALDOORS DOORS EXTERNAL In flight: 1. Avoid slips or skids that could open doors.
13
BATTOVHT OVHT LLBATT R BATT OVHT R BATT OVHT LRBATT BATTOVHT OVHT LR
14
(Nickel-Cadmium Batteries Only)
15 16
1. Respective L or R BATT............................................................. OFF 2. EICAS ......................................................... Select ELEC or SUMRY Monitor Battery Temperature If the respective battery temperature continues to increase: a. Land as soon as practical.
17 18
A-14
EFFECTIVITY 45-002 ALL& on not modified by SB 45-72-1
CL-126B October 2004
EMERBATT BATTLOW LOW EMER 1
On the ground: 1. EICAS ......................................................... Select ELEC or SUMRY 2. In order to ensure adequate emergency power endurance in the event of a dual generator failure, allow time for battery to charge & EMER BATT LOW illumination to extinguish prior to flight. 3. This checklist is complete.
2 3 4
In flight: 1. EICAS ......................................................... Select ELEC or SUMRY 2. Land as soon as practical.
5
If conditions permit: a. Pull circuit breakers, pilot’s & copilot’s circuit breaker panels, with red rings (EMER BATT bus) one at a time to isolate a possible faulted component. Allow time after pulling each circuit breaker for battery to recharge. 3. This checklist is complete.
6 7 8 9 10 11 12 13 14 15 16 17
Change 1
CL-126B October 2004 Change 1
EFFECTIVITY ALL
A-15
EMERBUS BUSVOLTS VOLTS EMER 2 3 4 5 6 7 8 9 10 11
1. EICAS ......................................................... Select ELEC or SUMRY 2. ●If EMER-V bus voltage is greater than 29.6 VDC: a. ■On the ground: (1) Respective L or R, or APU (if installed) GEN ...............OFF or EXT PWR .................................................................. AVAIL or EXT PWR Source...................................................... Adjust (2) This checklist is complete. a. ■In flight: (1) Respective L or R GEN ................................................OFF (2) Land as soon as practical. (3) This checklist is complete. 2. ●If EMER-V bus voltage is less than 22 VDC: a. ■On the ground: (1) Allow time for EMER BATT to recharge prior to flight. (2) This checklist is complete. a. ■In flight: (1) BUS Circuit Breaker (pilot’s ELECTRICAL group [EMER BUS]) .................... Set (2) EMER BATT .................................................................. On (EMER illuminated) (3) Land as soon as practical.
12
If flight time will exceed the emergency battery duration, refer to LR GEN FAIL procedure, TAB 3, Emergency Checklist, for emergency battery duration: (4) Notify passengers of oxygen mask deployment. Instruct passengers to “Do not pull lanyard. Do not use the masks unless instructed otherwise”. (5) DEPLOY (PAX OXYGEN).............................................. ON (6) DAU (REVERSION)............................................... Select B (7) Standby Attitude ............................................... Pull & Cage Standby Attitude will be Inoperative (8) Standby altimeter vibrator will be inoperative. Do not reference this instrument for primary altitude. (9) Refer to Landing Gear Free Fall procedure, TAB 31, this checklist. Normal landing gear control will be inoperative. (10) Refer to Emergency Braking procedure, TAB 13, Emergency Checklist. Inboard brakes are inoperative. (11) This checklist is complete.
13 14 15 16 17 18
A-16
EFFECTIVITY 45-002 ALL& on not modified by SB 45-72-1
CL-126B October 2004
ESSBUS BUSFAULT FAULT LLESS R ESS BUS FAULT R ESS BUS FAULT LR ESS BUS FAULT LR ESS BUS FAULT
1
The respective essential bus contactor has failed open on the ground.
2 3
ESSBUS BUSVOLTS VOLTS LLESS R ESS BUS VOLTS R ESS BUS VOLTS LRESS ESSBUS BUSVOLTS VOLTS LR
4
1. EICAS ......................................................... Select ELEC or SUMRY 2. ●If respective L or R ESS bus voltage is greater than 29.6 VDC: a. ■On the ground: (1) Respective L or R, or APU (if installed) GEN ...............OFF or EXT PWR.................................................................. AVAIL or EXT PWR Source ..................................................... Adjust (2) This checklist is complete. a. ■In flight: (1) Respective L or R GEN ................................................OFF (2) Refer to LR GEN FAIL procedure, TAB 3, Emergency Checklist, or single (L or R) GEN FAIL procedure, next page. (3) Land as soon as practical. (4) This checklist is complete. 2. ●If respective L or R ESS bus voltage is less than 22 VDC: a. ■On the ground: (1) Connect an EXT PWR source or switch on a generator to charge the batteries. Allow time for batteries to recharge prior to flight. (2) This checklist is complete. a. ■In flight: (1) BUS Circuit Breaker (pilot’s or copilot’s ELECTRICAL group [L or R ESS BUS]) ........................Set (2) Respective L or R GEN ....................................... Check On (3) Land as soon as practical. (4) This checklist is complete.
5 6 7 8 9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
A-17
2 3 4 5 6 7
GENAMPS AMPSHIGH HIGH LLGEN R GEN AMPS HIGH R GEN AMPS HIGH LRGEN GENAMPS AMPSHIGH HIGH LR 1. EICAS ......................................................... Select ELEC or SUMRY 2. Respective L or R NON-ESS ..................................................... OFF 3. Respective Electrical Load.................................................... Reduce If GEN AMPS HIGH remains illuminated & AMPS are greater than 350 & aircraft load has been reduced: a. Respective L or R BATT......................................................OFF If GEN AMPS HIGH remains illuminated & AMPS are greater than 350: (1) Respective L or R GEN ................................................OFF (2) BUS-TIE ..................................................................... Open The respective main and main avionics buses will not be powered.
8 9 10 11 12 13 14 15
GENFAIL FAIL LLGEN R GEN FAIL R GEN FAIL 1. Respective L or R GEN Circuit Breaker (ELECTRICAL group)........................................ Set, or Pull & Reset 2. Engine N2 ..........................................................................≥ 80% 3. Respective L or R GEN............................... Depress (Approx 1 Sec) If GEN FAIL remains illuminated: a. L & R NON-ESS ....................................................... As Desired b. Remaining (non-affected) GEN AMPS...........................Monitor
EMERLIGHTS LIGHTS EMER 1. EMER LIGHTS...........................................................................ARM
16 17 18
EFFECTIVITY
A-18
ALL
CL-126B October 2004
ENGFIRE FIREFAIL FAIL LLENG R ENG FIRE FAIL R ENG FIRE FAIL LR ENG FIRE FAIL LR ENG FIRE FAIL
1
The engine fire detection system has detected a fault on the ground that may not allow the detection system to indicate a fire.
2 3
ENGCMPTRFAULT FAULT LLENGCMPTR R ENGCMPTR FAULT R ENGCMPTR FAULT LR ENGCMPTR FAULT LR ENGCMPTR FAULT 1. 2. 3. 4.
4 5
Engine Instruments................................................................ Monitor ENG SYNC .................................................................................OFF Respective Thrust Lever........................................................ ≤ MCR Respective L or R ENG CMPTR..................................OFF, then ON
If ENGCMPTR FAULT remains illuminated: a. Respective L or R ENG CMPTR ............MAN & Continue Flight Engine acceleration & deceleration in MAN mode will be slower than normal. The slower response should be considered in a go-around condition. Refer to applicable thrust setting performance data, Performance Checklist, to obtain rated thrust. The thrust lever detents do not automatically set thrust in MAN mode.
6 7 8 9 10 11
ENGINECHIP CHIP LLENGINE R ENGINE CHIP R ENGINE CHIP LR ENGINE CHIP LR ENGINE CHIP
12 13
Metal particles have been detected in the oil while on the ground.
14
OILFILTER FILTER LLOIL R OIL FILTER R OIL FILTER LR OIL FILTER LR OIL FILTER
15 16
The engine oil filter has an impending bypass while on the ground.
CL-126B October 2004
17
EFFECTIVITY ALL
A-19
Engine Airstart 2
ENG CMPTR ON (Auto Mode)
3
Auto Mode Airstart Envelope
4
45-178
35000
5 30000
6
8 9 10
PRESSURE ALTITUDE — FEET
25000
7
WINDMILL OR STARTER ASSISTED
20000
STARTER ASSISTED
15000
10000
11 5000
12 0
13
50
100
150
200
250
300
350
AIRSPEED — KIAS
14 15 16 17 18
EFFECTIVITY
A-20
ALL
CL-126B October 2004
ENG CMPTR ON (Auto Mode) (Cont) Before Start Affected engine: 1. Assure that aircraft is within appropriate Airstart Envelope. 2. ENG CMPTR ............................................................................... ON 3. Fuel Supply..............................................................................Check a. Fuel available from wing tank. 4. FUEL Panel as Follows: a. XFLOW (FUEL)...............................................................Closed b. STBY (FUEL) ........................................................................ON 5. FIRE (ENGINE) ............................................................. Check Open 6. WSHLD.......................................................................................OFF 7. Electrical Load ...................................................................... Reduce 8. WING/STAB.................................................................................. Off 9. NAC .............................................................................................. Off 10. BLEED........................................................................................OFF 11. Conduct the following windmill or starter assisted airstart.
1 2 3 4 5 6 7
Start
8
Windmill Airstart Affected engine: 1. Thrust Lever (at minimum 10% N2) ........................................... IDLE 2. IGN & FUEL FLOW .................................................................Check 3. ITT .................................................................................. Check Rise If no indication of light-off is obtained within 20 seconds of achieving thrust lever movement to idle: a. Thrust Lever .................................................................CUTOFF b. Repeat airstart or refer to Engine Shutdown in Flight procedure, TAB 10, this checklist. 4. Engine Instruments................................................................ Normal
9 10 11 12 13
Starter Assisted Airstart Affected engine: 1. START ......................................................................................... ON 2. Thrust Lever (at minimum 10% N2) ........................................... IDLE 3. IGN & FUEL FLOW .................................................................Check 4. ITT .................................................................................. Check Rise
14 15 16
(Procedure Continued)
17
CL-126B October 2004
EFFECTIVITY ALL
A-21
ENG CMPTR ON (Auto Mode) (Cont)
2 3
If no indication of light-off is obtained within 20 seconds of achieving thrust lever movement to idle: a. Thrust Lever ................................................................ CUTOFF b. Repeat airstart or refer to Engine Shutdown in Flight procedure, TAB 10, this checklist. 5. Engine Instruments ................................................................ Normal
4 After Start
5 6 7 8 9
Affected engine: 1. FUEL Panel as Follows: a. STBY (FUEL) ..................................................... Off, as Desired b. XFLOW (FUEL) ........................................................ As Desired 2. GEN ..............................................................................................On 3. WSHLD .........................................................................................On 4. WING/STAB ..................................................................As Required 5. NAC ...............................................................................As Required 6. BLEED ..........................................................................................On 7. RMU (ATC/TCAS)............................................................ As Desired
10 11 12 13 14 15 16 17 18
EFFECTIVITY
A-22
ALL
CL-126B October 2004
ENG CMPTR - MAN or OFF Manual Mode Airstart Envelope 45-179
35000
1 2
30000
PRESSURE ALTITUDE — FEET
3 25000
4 20000
5 15000
6
10000
7
WINDMILL OR STARTER ASSISTED
STARTER ASSISTED
8 5000
9 0 50
100
150
200
250
300
350
10
AIRSPEED — KIAS
Before Start Affected engine: 1. Assure that aircraft is within appropriate Airstart Envelope. 2. ENG CMPTR ............................. MAN or OFF (MAN recommended) 3. Fuel Supply..............................................................................Check a. Fuel available from wing tank. 4. FUEL Panel as Follows: a. XFLOW (FUEL)...............................................................Closed b. STBY (FUEL) ........................................................................ON 5. FIRE (ENGINE) ............................................................. Check Open 6. WSHLD.......................................................................................OFF 7. Electrical Load ...................................................................... Reduce 8. WING/STAB.................................................................................. Off 9. NAC .............................................................................................. Off 10. BLEED........................................................................................OFF 11. Conduct the following windmill or starter assisted airstart.
(Procedure Continued) CL-126B October 2004
EFFECTIVITY ALL
A-23
11 12 13 14 15 16 17
ENG CMPTR - MAN or OFF (Cont) Start
2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18
Windmill Airstart Affected engine: 1. IGN .............................................................................................. ON 2. Thrust Lever (at minimum 10% N2) ...........................................IDLE 3. IGN & FUEL FLOW................................................................. Check 4. ITT .................................................................................. Check Rise If no indication of light-off is obtained within 20 seconds of achieving thrust lever movement to idle: a. Thrust Lever ................................................................ CUTOFF b. IGN ........................................................................................ Off c. Repeat airstart or refer to Engine Shutdown in Flight procedure, TAB 10, this checklist. 5. Engine Instruments ................................................................ Normal Starter Assisted Airstarts Affected engine: 1. IGN .............................................................................................. ON 2. START ......................................................................................... ON 3. Thrust Lever (at minimum 10% N2) ...........................................IDLE 4. IGN & FUEL FLOW................................................................. Check 5. ITT .................................................................................. Check Rise If no indication of light-off is obtained within 20 seconds of achieving thrust lever movement to idle: a. Thrust Lever ................................................................ CUTOFF b. START................................................................................... Off c. IGN ........................................................................................ Off d. Repeat airstart or refer to Engine Shutdown in Flight procedure, TAB 10, this checklist. 6. Engine Instruments ................................................................ Normal After Start Affected engine: 1. IGN ............................................................................................... Off 2. FUEL Panel as Follows: a. STBY (FUEL) ..................................................... Off, as Desired b. XFLOW (FUEL) ........................................................ As Desired 3. GEN ..............................................................................................On 4. WSHLD .........................................................................................On 5. WING/STAB ...................................................................As Required 6. NAC ...............................................................................As Required 7. BLEED ..........................................................................................On 8. RMU (ATC/TCAS)............................................................ As Desired EFFECTIVITY
A-24
ALL
CL-126B October 2004
Engine Indications (EIs) 1
IGN IGN 1. CH A & CH B Circuit Breakers (respective L or R IGN group [ENGINE]) .......... Set, or Pull & Reset
2
If IGN remains illuminated: a. Airstarts will not be possible.
3
MAN MAN
4
Refer to L or R ENGCMPTR FAULT procedure, TAB 6, this checklist.
5
NAC NAC Refer to L or R NAC HT or L or R NAC HT FAIL ON procedure, TAB 1, this checklist.
6
REV REV
7
Thrust reverser is armed in flight or on the ground with a TLA (thrust lever angle) greater than MCR.
8
In flight: 1. Respective Thrust Reverser Lever ............................................ Stow 2. Respective DEPLOY Circuit Breaker (ENGINE group) ............... Pull 3. Continue flight.
10
START START
11
Ground Start 1. Respective START ....................................................................... Off
12
If START remains illuminated, the starter is still engaged. Affected engine: a. Thrust Lever ................................................................CUTOFF b. Turn off all electrical power. Starter-Assisted Airstart 1. Complete airstart procedure.
9
13 14 15
If START remains illuminated, the starter is still engaged. a. Continue flight.
16
At shutdown: b. L & R BATT ......................................................................... OFF
17
CL-126B October 2004
EFFECTIVITY ALL
A-25
SYNC 2
1. ENG SYNC ................................................................................ OFF
UNL UNL 3 4
On the ground, the thrust reverser is in transition between stow and deploy. It will temporarily illuminate during normal thrust reverser deployment. If illumination continues for more than 3 seconds, an abnormal condition exists & the master caution is tripped.
5 6 7 8
Engine Overspeed Affected engine: 1. Thrust Lever............................................................................Retard If engine does not respond: a. Thrust Lever ................................................................ CUTOFF If engine does not respond: (1) FIRE (ENGINE) ................................................FIRE PUSH (2) After engine has shut down, ENG CMPTR ................. MAN (3) Refer to Engine Shutdown in Flight procedure, TAB 10, this checklist.
9 10 11 12 13 14 15 16 17 18
EFFECTIVITY
A-26
ALL
CL-126B October 2004
Engine Shutdown in Flight Affected engine: 1. ENG SYNC .................................................................................OFF 2. Thrust Lever........................................................................ CUTOFF 3. Rudder Trim ................................................................... As Required 4. Yaw Damper .................................................................. As Required 5. Autopilot........................................................................... As Desired 6. Electrical Load ............................... Reduce, Within Generator Limits 7. WSHLD ......................................................................................OFF Avoid flight in icing conditions 8. 9. 10. 11. 12.
BLEED ........................................................................................OFF RMU (ATC/TCAS)............................................................... TA ONLY Monitor fuel balance. Crossflow as required. Land as soon as practical. Refer to En Route Climb Gradient — Single Engine chart, Section V of the AFM. 13. Refer to Engine Airstart, TAB 7, if applicable, or Single-Engine Landing procedure, TAB 33, this checklist, or Thrust Reverser Deployed Landing procedure, TAB 38, this checklist, as appropriate.
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
A-27
2 3 4 5 6 7
BLEEDOVHT OVHT LLBLEED R BLEED OVHT R BLEED OVHT LR BLEED OVHT LR BLEED OVHT L or R BLEED OVHT Illuminates 1. Respective BLEED .................................................................... OFF Allow Time for System to Cool 2. ●If BLEED OVHT continues: a. Reduce N1 on respective engine. b. Maintain 41,000 feet or below. Avoid flight in icing conditions. c. Land as soon as practical. d. This checklist is complete. 2. ●If BLEED OVHT extinguishes: a. Respective BLEED may be selected On. If BLEED OVHT recurs: (1) Respective BLEED .......................................................OFF (2) Maintain 41,000 feet or below. Avoid flight in icing conditions. (3) This checklist is complete.
8 9 10 11 12 13 14 15 16 17 18
LR BLEED OVHT Illuminates 1. L BLEED .................................................................................... OFF 2. Reduce N1 on right engine. Allow time for system to cool. 3. ●If LR BLEED OVHT continues: a. L BLEED................................................................................ On b. Right Engine N1...................................................... As Required c. R BLEED .............................................................................OFF d. Reduce N1 on left engine. Allow time for system to cool. e. ■If LR BLEED OVHT continues: (1) Maintain 41,000 feet or below. Avoid flight in icing conditions. (2) Land as soon as practical. (3) This checklist is complete. e. ■If either L or R BLEED OVHT extinguishes: (1) BLEED (on side that caution extinguished) .................... On (2) Refer to the L or R BLEED OVHT procedure above. 3. ●If either L or R BLEED OVHT extinguishes: a. BLEED (on side that caution extinguished) ........................... On b. Refer to the L or R BLEED OVHT procedure above.
Change 1
A-28
EFFECTIVITY 45-002 & on not modified by SB 45-72-1
CL-126B October 2004 Change 1
Engine Shutdown in Flight Affected engine: 1. ENG SYNC .................................................................................OFF 2. Thrust Lever........................................................................ CUTOFF 3. Rudder Trim ................................................................... As Required 4. Yaw Damper .................................................................. As Required 5. Autopilot........................................................................... As Desired 6. Electrical Load ............................... Reduce, Within Generator Limits 7. WSHLD ......................................................................................OFF Avoid flight in icing conditions 8. 9. 10. 11. 12.
BLEED ........................................................................................OFF RMU (ATC/TCAS)............................................................... TA ONLY Monitor fuel balance. Crossflow as required. Land as soon as practical. Refer to En Route Climb Gradient — Single Engine chart, Section V of the AFM. 13. Refer to Engine Airstart, TAB 7, if applicable, or Single-Engine Landing procedure, TAB 33, this checklist, or Thrust Reverser Deployed Landing procedure, TAB 38, this checklist, as appropriate.
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
A-27
2 3 4 5 6 7 8 9 10 11 12 13 14 15
BLEEDOVHT OVHT LLBLEED R BLEED OVHT R BLEED OVHT LRBLEED BLEEDOVHT OVHT LR L or R BLEED OVHT Illuminates 1. Affected Thrust Lever...........................................Advance or Retard 2. ●If BLEED OVHT continues: a. Go to step 3. 2. ●If BLEED OVHT extinguishes: a. This checklist is complete. 3. Respective BLEED .................................................................... OFF Allow Time for System to Cool 4. ●If BLEED OVHT continues: a. Reduce N1 on respective engine. b. Maintain 41,000 feet or below. Avoid flight in icing conditions. c. Land as soon as practical. d. This checklist is complete. 4. ●If BLEED OVHT extinguishes: a. Respective BLEED may be selected On. If BLEED OVHT recurs: (1) Respective BLEED .......................................................OFF (2) Maintain 41,000 feet or below. Avoid flight in icing conditions. (3) This checklist is complete.
LR BLEED OVHT Illuminates 1. Thrust Levers .......................................................Advance or Retard 2. ●If BLEED OVHT continues: a. Go to step 3. 2. ●If BLEED OVHT extinguishes: a. This checklist is complete. 3. L BLEED .................................................................................... OFF 4. Reduce N1 on right engine. Allow time for system to cool.
16 (Procedure Continued)
17 18 Change 1
A-28.1 A-28
EFFECTIVITY 45-002 & on modified by SB 45-72-1
CL-126B October 2004 Change 1
5. ●If LR BLEED OVHT continues: a. L BLEED ............................................................................... On b. Right Engine N1 ..................................................... As Required c. R BLEED............................................................................. OFF d. Reduce N1 on left engine. Allow time for system to cool. e. ■If LR BLEED OVHT continues: (1) Maintain 41,000 feet or below. Avoid flight in icing conditions. (2) Land as soon as practical. (3) This checklist is complete. e. ■If either L or R BLEED OVHT extinguishes: (1) BLEED (on side that caution extinguished).................... On (2) Refer to the L or R BLEED OVHT procedure above. 5. ●If either L or R BLEED OVHT extinguishes: a. BLEED (on side that caution extinguished)........................... On b. Refer to the L or R BLEED OVHT procedure above.
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
CL-126B October 2004 Change 1
EFFECTIVITY 45-002 & on modified by SB 45-72-1
A-28A A-28.1
CABDELTA DELTAPP CAB 1. EICAS ............................................... Select ECS & Check DELTA P 2. L & R PRESS Circuit Breakers (pilot’s & copilot’s ENVIRONMENTAL & ENVIR group) ............................. Pull & Reset 3. ●If DELTA P is greater than 9.5 psid: a. MANUAL PRESS ..................................................................ON b. MANUAL Rate Control ........................... UP, to Reduce Delta P If CAB DELTA P remains illuminated: (1) One L or R BLEED....................................................... OFF (2) Adjust N1 on opposite engine to control cabin pressurization. (3) Maintain 41,000 feet or below. Avoid flight in icing conditions. (4) This checklist is complete.
1 2 3 4 5 6
If still unable to regulate the overpressurization: (i) EMER DEPRESS ....................................................ON (ii) Descend to reduce differential pressure, but not below minimum safe altitude. (iii) This checklist is complete.
7
3. ●If DELTA P is less than -0.5 psid: a. MANUAL PRESS ..................................................................ON b. MANUAL Rate Control ..........................DN, to increase Delta P
9
If CAB DELTA P remains illuminated: (1) Decrease aircraft descent rate. (2) This checklist is complete.
12
1. 2. 3. 4.
EICAS ............................................................................. Select ECS MANUAL TEMP........................................................................... ON CABIN TEMPERATURE COLD-HOT Knob...................... Full COLD TEMP CONT (ECS Page) ............................... Verify CAB Moving to or at C (cold) Position If CAB DUCT OVHT remains illuminated: a. L BLEED Circuit Breaker (pilot’s ENVIRONMENTAL group)........................................ Pull Allow time for air to cool Maintain 41,000 feet or below. With L BLEED — On, anti-ice airflow is available to the respective anti-ice valves.
(Procedure Continued) CL-126B October 2004
10 11
CABDUCT DUCTOVHT OVHT CAB
b.
8
EFFECTIVITY ALL
A-29
13 14 15 16 17
If CAB DUCT OVHT remains illuminated: (1) R BLEED Circuit Breaker (copilot’s ENVIR group)........Pull Allow time for air to cool. Avoid flight in icing conditions. (2) Adjust N1 to control cabin pressurization. Spoilers may be required for descent.
2 3
If CAB DUCT OVHT remains illuminated or icing conditions cannot be avoided: (i) L & R BLEED Circuit Breakers (pilot’s & copilot’s ENVIRONMENTAL & ENVIR group)....................... Set (ii) EMER PRESS......................................................... ON (iii) One L or R BLEED.................................................OFF (iv) Reduce N1 on engine with bleed air on.
4 5 6
LRCAB CABPRESS PRESSFAIL FAIL LR 7 8 9 10 11 12
1. L & R PRESS Circuit Breakers (pilot’s & copilot’s ENVIRONMENTAL & ENVIR group) .............................Pull & Reset If LR CAB PRESS FAIL remains illuminated: a. Maintain below 8000 feet or minimum safe altitude. Land below 8000 feet field elevation, if possible. When below 8000 feet: b. PACK...................................................................................OFF
CABPRESS PRESSMAN MAN CAB 1. MANUAL Rate Control ..................................................As Required
13
CABINALTITUDE ALTITUDE CABIN 14 15 16 17 18
Cabin Altitude Exceeds 8500 Feet 1. Crew Oxygen Masks...................................................... Don &100% 2. If aircraft is climbing, stop climbing and level off at (or descend to) the nearest appropriate altitude. 3. Pilot & Copilot MIC/MASK....................................................... MASK 4. Pilot & Copilot INPH.................................................................. INPH 5. PACK .................................................................................Check On 6. L & R BLEED .....................................................................Check On 7. EICAS ........................................... Select ECS & Check CABIN ALT (Procedure Continued) EFFECTIVITY
A-30
ALL
CL-126B October 2004
8. ●If cabin altitude continues to climb: a. MANUAL PRESS ..................................................................ON b. MANUAL Rate Control Knob............................ DN As Required If cabin altitude continues to climb: (1) EMER PRESS................................................................ON 8. ●If cabin altitude stabilizes at a safe altitude: a. Continue flight. Continued use of the oxygen system is at the crew’s discretion.
CKPTDUCT DUCTOVHT OVHT CKPT EICAS ............................................................................. Select ECS MANUAL TEMP........................................................................... ON COCKPIT TEMPERATURE COLD-HOT Knob................. Full COLD TEMP CONT (ECS Page) .............................Verify CKPT Moving to or at C (cold) Position If CKPT DUCT OVHT remains illuminated: a. L BLEED Circuit Breaker (pilot’s ENVIRONMENTAL group)........................................ Pull Allow time for air to cool Maintain 41,000 feet or below. With L BLEED — On, anti-ice airflow is available to the respective anti-ice valves. If CKPT DUCT OVHT remains illuminated: (1) R BLEED Circuit Breaker (copilot’s ENVIR group)........ Pull Allow time for air to cool. Avoid flight in icing conditions. (2) Adjust N1 to control cabin pressurization. Spoilers may be required for descent. If CKPT DUCT OVHT remains illuminated or icing conditions cannot be avoided: (i) L & R BLEED Circuit Breakers (pilot’s & copilot’s ENVIRONMENTAL & ENVIR group) .......................Set (ii) EMER PRESS .........................................................ON (iii) One L or R BLEED................................................. OFF (iv) Reduce N1 on engine with bleed air on.
3
5 6 7 8 9 10 11 12 13 14 15
LRECS ECSFAIL FAIL LR 1. L & R BLEED Circuit Breakers (pilot’s & copilot’s ENVIRONMENTAL & ENVIR group)................. Set, or Pull & Reset If LR ECS FAIL remains illuminated: a. Maintain 41,000 feet or below. CL-126B October 2004
2
4
1. 2. 3. 4.
b.
1
EFFECTIVITY ALL
A-31
16 17
2 3 4 5
ECSFAULT FAULT LLECS R ECS FAULT R ECS FAULT 1. Respective L or R BLEED Circuit Breaker (respective ENVIRONMENTAL or ENVIR group) ................. Set, or Pull & Reset
EMERPRESS PRESSON ON LLEMER R EMER PRESS ON R EMER PRESS ON LR EMER PRESS ON LR EMER PRESS ON Inadvertent Activation of Emergency Airflow
6 7 8 9
If cabin altitude is below 9500 feet: 1. EMER PRESS...............................................................................Off 2. ●If L or R EMER PRESS ON remains illuminated: a. Respective L or R BLEED .................................................. OFF If Emergency Flow Stops, Leave Switch OFF b. Maintain 41,000 feet or below. Avoid flight in icing conditions. c. This checklist is complete. 2. ●If LR EMER PRESS ON remains illuminated:
10
a. b.
11
c. d.
12
One L or R BLEED ............................................................. OFF Adjust N1 on engine supplying EMER air to modulate cabin temperature. Maintain 41,000 feet or below. Avoid flight in icing conditions. Land as soon as practical.
If emergency airflow continues: (1) Reduce N1 on respective engine as low as practical. (2) Respective L or R BLEED Circuit Breaker (respective ENVIRONMENTAL or ENVIR group) ......... Pull Emergency pressurization may not be available through the affected side. The corresponding EMER PRESS ON amber CAS will extinguish, however, the emergency valve may not close. (3) Respective L or R BLEED .............................................On Allows anti-ice airflow to the respective anti-ice valves. (4) Land as soon as possible. (5) This checklist is complete.
13 14 15 16 17 18
EFFECTIVITY
A-32
ALL
CL-126B October 2004
OXYGENOFF OFF OXYGEN 1
On the ground: 1. Select Oxygen Bottle Pressure Regulator ON prior to flight or service oxygen bottle. 2. This checklist is complete.
2 3
In flight: 1. 2. 3. 4.
EICAS ............................................................................. Select ECS OXY QTY .................................................................................Check Crew Masks ................................................................................ Test ●If oxygen quantity is satisfactory: a. Continue flight. b. This checklist is complete. 4. ●If oxygen quantity is not satisfactory: a. Maintain below 25,000 feet or minimum safe altitude. Replan flight as necessary. b. This checklist is complete.
4 5 6 7 8 9
OXYGEN QTY LOW
10
On the ground: 1. EICAS ............................................................................. Select ECS 2. OXY QTY .................................................................................Check 3. Using the oxygen quantity mission planning table on page S-7, determine if the oxygen quantity is sufficient for the planned mission. If oxygen quantity is not satisfactory: 4. Refer the problem to maintenance personnel for correction.
In flight:
Change 1
12 13 14
1. EICAS ............................................................................. Select ECS 2. OXY QTY .................................................................................Check 3. Using the oxygen duration chart on page S-6, determine if the oxygen quantity is sufficient based on the cabin altitude and the number of passengers. If oxygen quantity is not satisfactory: 4. Maintain below 25,000 feet or minimum safe altitude. 5. Replan flight as necessary.
CL-126B October 2004 Change 1
11
EFFECTIVITY ALL
A-33
15 16 17
OXYPRESS PRESSHI HI OXY 2 3 4
Oxygen bottle is over serviced. Oxygen quantity digits will be amber dashed.
On the ground: 1. Refer problem to maintenance personnel for correction.
In flight:
5 6
1. Continue flight.
PACKOVHT OVHT PACK
7
1. HI FLOW .......................................................................................Off 2. APU BLEED (if installed) ..............................................................Off
8
If PACK OVHT remains illuminated: a. L or R BLEED....................................................Select one OFF b. Reduce N1 on opposite engine as low as practical. c. Maintain 41,000 feet or below. Avoid flight in icing conditions.
9
If PACK OVHT remains illuminated: (1) EMER PRESS ............................................................... ON (2) PACK ............................................................................OFF (3) Adjust thrust lever on engine supplying EMER PRESS air to modulate cabin temperature.
10 11 12 13 14 15 16 17
PAXOXY OXYFAIL FAIL PAX 1. Notify passengers of mask deployment and mask use if necessary. 2. DEPLOY (PAX OXYGEN) ............................................................ ON 3. ●If passenger oxygen masks deploy: a. Continue flight. b. This checklist is complete. 3. ●If passenger oxygen masks do not deploy: a. Maintain below 25,000 feet or minimum safe altitude. b. Replan flight as necessary. c. This checklist is complete.
18
A-34
EFFECTIVITY 45-002 ALL& on not modified by SB 45-72-1
CL-126B October 2004
ELEVATORDISC DISC ELEVATOR 1. Obtain maintenance prior to flight.
1
FLAPSFAIL FAIL FLAPS 1. 2. 3. 4. 5. 6.
2
EICAS .............................................................................. Select FLT FLAP CTRL Circuit Breaker (copilot’s FLIGHT group) ................ Set FLAPS .................................. Detent Closest to Actual Flap Position SYS TEST/RESET (FLAP RESET) ......................................... Press SYS TEST/RESET (FLAPS).................................................... Press SYS TEST/RESET (FLAP RESET) ......................................... Press
If FLAPS FAIL remains illuminated: a. Refer to Partial Flap Landing procedure, TAB 34, this checklist.
3 4 5 6
FLAPSFAULT FAULT FLAPS 1. EICAS .............................................................................. Select FLT 2. FLAP CTRL Circuit Breaker (copilot’s FLIGHT group) ............... Set 3. FLAPS ................................................................Select New Detent, Then Detent Closest to Actual Flap Position 4. ●If FLAPS FAULT extinguishes: a. Select flaps as desired. b. This checklist is complete. 4. ●If FLAPS FAULT remains illuminated: a. SYS TEST/RESET (FLAP RESET)...................................Press b. This checklist is complete.
MACHTRIM TRIMFAIL FAIL MACH
8 9 10 11 12
1. PITCH TRIM ................................................................................PRI 2. PRI PITCH Circuit Breaker (pilot’s FLIGHT group [TRIM])...................................................... Set If MACH TRIM FAIL remains illuminated: a. ●If autopilot is disengaged: (1) Airspeed ............................................. ≤ Mach trim off MMO (2) This checklist is complete. a. ●If autopilot disengagement is desired: (1) Airspeed ............................................. ≤ Mach trim off MMO (2) Autopilot .............................................................Disengage Engage yaw damper as required. (3) This checklist is complete.
CL-126B October 2004
7
EFFECTIVITY ALL
A-35
13 14 15 16 17
PRITRIM TRIMFAIL FAIL PRI 2 3
1. PITCH TRIM .............................................................................. SEC 2. SEC NDN-NUP ................................... As Required to Maintain Trim 3. PRI PITCH Circuit Breaker (pilot’s FLIGHT group [TRIM]) ..........Pull
4
If neither PRI nor SEC pitch trim is available: 4. Refer to Jammed Stabilizer procedure, TAB 16, this checklist
5 6 7 8 9 10
ROLLDISC DISC ROLL 1. Align control wheels. 2. Push the small roll disconnect lever forward. 3. Verify ROLL DISC CAS extinguishes
RUDBOOST BOOSTINOP INOP RUD On the ground: 1. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) ....................................... Set, or Pull & Reset 2. Control Wheel Master Switch (MSW) .................Depress & Release 3. Nose Steer Switch ...................................................................... ON If RUD BOOST INOP remains illuminated: a. RUD BOOST Switch ..............................................................OFF Refer to RUD BOOST INOP procedure, page A/S-8.
11 12 13 14 15
In flight: 1. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) ....................................... Set, or Pull & Reset 2. Control Wheel Master Switch (MSW) .................Depress & Release 3. Yaw Damper ..................................................................As Required
SECTRIM TRIMFAIL FAIL SEC
17
1. PITCH TRIM ................................................................................PRI 2. Control Wheel Trim Switch.................. As Required to Maintain Trim 3. SEC PITCH Circuit Breaker (copilot’s FLIGHT group [TRIM]) ..................................................Pull 4. Do not engage autopilot.
18
If neither PRI nor SEC pitch trim is available: 5. Refer to Jammed Stabilizer procedure, TAB 16, this checklist
16
EFFECTIVITY
A-36
ALL
CL-126B October 2004
SPOILERSEXT EXT SPOILERS Depending on conditions: 1. Perform one of the following: - SPOILER ............................................................................... RET - FLAPS...................................................................................... UP
4
On the ground: 1. Complete Starting Engines procedure, page N-7. 2. SPOILER Lever ..........................................................................RET 3. SPLR CTRL and SPLR IND Circuit Breakers (respective pilot’s and copilot’s FLIGHT group) ..................Pull, Wait 5 Seconds and Reset Allow 20 seconds for the system to restart. 4. EICAS............................................................................... Select FLT 5. SPOILER Lever ......................................................................... EXT Check for equal extension rate and position. 6. SPOILER Lever ........................................................................ ARM Check for spoilers retracted. (AUTOSPLR ARM white CAS) If SPOILERS FAIL remains illuminated: a. Do not take off. Refer the problem to maintenance personnel for correction. 1. SPOILER ....................................................................................RET 2. SPLR CTRL & SPLR IND Circuit Breakers (respective pilot’s & copilot’s FLIGHT group)................................Set 3. EICAS.....................................Select FLT & Check Spoiler Positions 4. SYS TEST/RESET (SPLRN RESET)................. Depress & Release
Change 1
6 7 8 9 10 11
Spoilers & spoilerons will be inoperative in flight. Maintain 35,000 feet or below. Refer to Abnormal Landings, Spoilers Extended Landing procedure, TAB 35, this checklist.
EFFECTIVITY ALL
13 14 15
If SPOILERS FAIL remains illuminated:
CL-126B October 2004 Change 1
5
12
In flight:
b.
2 3
SPOILERSFAIL FAIL SPOILERS
a.
1
A-37
16 17
2 3
SPOILERJAM JAM LLSPOILER R SPOILER JAM R SPOILER JAM LRSPOILER SPOILERJAM JAM LR
7
L or R SPOILER JAM Illuminated 1. Control aircraft with roll control. 2. Autopilot ............................................. Disengage (Do not use MSW) 3. SPOILER .................................Deploy as Required to Minimize Roll 4. EICAS .....................................Select FLT & Check Spoiler Positions 5. Slow aircraft as necessary to reduce roll control forces. Do not reset spoiler system with SYS TEST/RESET (SPLRN RESET). 6. Land as soon as possible. 7. Refer to Abnormal Landings, Spoiler Jammed Landing procedure, TAB 36, this checklist.
8
LR SPOILER JAM Illuminated 1. Refer to SPOILERS FAIL procedure, TAB 15, this checklist.
4 5 6
9 10 11 12 13
STALLWARNFAIL FAIL LLSTALLWARN R STALLWARN FAIL R STALLWARN FAIL LR STALLWARN FAIL LR STALLWARN FAIL 1. Respective L or R STALL WARN Circuit Breaker (FLIGHT group).................................... Set, or Pull & Reset 2. Maintain airspeed at least 25 knots above stall speeds shown in Section V of the AFM. VREF may be maintained on final approach in the landing configuration. 3. Limit bank angles to 30° maximum.
14 15 16 17 18
A-38
EFFECTIVITY 45-002 ALL& on not modified by SB 45-72-1
CL-126B October 2004
Jammed Stabilizer PRI TRIM FAIL and SEC TRIM FAIL
1
Elevator Pull Force Is Encountered If the stabilizer jams during a high-speed condition: 1. Delay reducing airspeed as long as possible to minimize the time out of trim. Do not re-engage autopilot. 2. Move C.G. aft if possible. 3. Land as soon as possible to minimize forward C.G. movement. 4. PIT TRIM BIAS .......................................................................... NUP 5. Refer to Stabilizer Jammed Landing procedure, TAB 36, this checklist.
2 3 4 5
Elevator Push Force Is Encountered If the stabilizer jams during a low-speed condition: 1. Do not increase airspeed to minimize the time out of trim. Do not reengage autopilot. 2. Move C.G. forward if possible. 3. Land as soon as possible. 4. Refer to Stabilizer Jammed Landing procedure, TAB 36, this checklist.
DEFUELOPEN OPEN DEFUEL
6 7 8 9 10
On the ground: 1. DEFUEL on Refueling Panel ......................................................OFF If DEFUEL OPEN remains illuminated: a. Close defuel valve (tailcone) prior to takeoff. b. This checklist is complete.
11 12
In flight:
13
1. Check EICAS or select FUEL page. 2. Monitor fuel quantities. 3. This checklist is complete.
14
FUELFILTER FILTER LLFUEL FUELFILTER FILTER RRFUEL LR FUEL FILTER LR FUEL FILTER
15
Either the respective engine or aircraft fuel filter has an impending bypass on the ground.
17
CL-126B October 2004
16
EFFECTIVITY ALL
A-39
2 3
FUELHEATER HEATER LLFUEL R FUEL HEATER R FUEL HEATER LRFUEL FUELHEATER HEATER LR 1. Fly to warmer conditions if possible. 2. Respective L or R STBY (FUEL) ................................................ ON
4 5 6 7 8 9
FUELIMBALANCE IMBALANCE FUEL 1. Check EICAS or select FUEL page. 2. Check trim. 3. Fuel Quantities........................................................................ Check Correct fuel distribution, if required: a. XFLOW (FUEL) ................................................................. Open b. L or R STBY (FUEL) (Heavy Wing)...................................... ON c. Monitor wing fuel quantity. When fuel balance is achieved: d. e.
10
L or R STBY (FUEL).............................................................. Off XFLOW (FUEL) .................................................................Close
11 12 13 14
FUELQTY QTYLOW LOW LLFUEL FUELQTY QTYLOW LOW RRFUEL LR FUEL QTY LOW LR FUEL QTY LOW 1. 2. 3. 4.
Check EICAS or select FUEL page. Fuel Quantities........................................................................ Check Respective L or R STBY (FUEL) ................................................. ON Replan flight if necessary.
15 16 17 18
EFFECTIVITY
A-40
ALL
CL-126B October 2004
FUELXFLO XFLO FUEL 1. 2. 3. 4.
Check EICAS or select FUEL page. Fuel Quantities ........................................................................Check XFLO Switch............................................................................. Cycle ●If XFLO valve fails to open: a. Maintain wing fuel balance by adjusting power setting. b. This checklist is complete. 4. ●If XFLO valve fails to close: a. Appropriate L or R STBY (FUEL)....................... ON to Maintain Wing Fuel Balance b. This checklist is complete.
1 2 3 4 5 6
FWSOVFAULT FAULT LLFWSOV FWSOVFAULT FAULT RRFWSOV LR FWSOV FAULT LR FWSOV FAULT
7
1. Respective L or R STBY (FUEL) .................................................. Off
8 9
STBY PUMP Fails ON
10
Fuel will normally remain balanced without opening the FUEL XFLO valve. Fuel balance can be maintained by use of the FUEL XFLO and the PWR and CTRL circuit breakers [respective L or R STBY PUMP group] on the “failed ON” pump.
11 12 13 14 15 16 17
CL-126B October 2004
EFFECTIVITY ALL
A-41
AUXHYD HYDPMP PMPLO LO AUX 2 3 4 5 6
1. EICAS ........................................................... Select HYD or SUMRY 2. HYD XFLOW................................................................................. Off 3. PWR Circuit Breaker [pilot’s AUX HYD PUMP group] .................................................. Set 4. Check B-ACUM pressure. 5. ●If B-ACUM pressure is normal: a. Emergency/parking brakes will operate normally. b. This checklist is complete. 5. ●If B-ACUM pressure is low (BRK ACUM PRESS amber CAS): a. Emergency/parking brakes may not be operational. b. This checklist is complete.
7 8 9 10 11 12
AUXHYD HYDQTY QTYLO LO AUX 1. 2. 3. 4.
HYD XFLOW................................................................................. Off EICAS ........................................................... Select HYD or SUMRY Check B-ACUM pressure. ●If B-ACUM pressure is normal: a. Emergency/parking brakes will operate normally. b. This checklist is complete. 4. ●If B-ACUM pressure is low (BRK ACUM PRESS amber CAS): a. Emergency/parking brakes may not be operational. b. AUX HYD ............................. ON to Charge B-ACUM Pressure c. This checklist is complete.
13 14 15 16 17 18
EFFECTIVITY
A-42
ALL
CL-126B October 2004
BRKACUM ACUMPRESS PRESS BRK 1. EICAS ........................................................... Select HYD or SUMRY 2. Check B-ACUM pressure. 3. ●If B-ACUM pressure is accompanied with an AUX HYD QTY LO amber CAS: a. Landing gear extension will turn the AUX HYD pump ON. b. HYD XFLOW ........................................................................ Off c. AUX HYD ............................................................................ Off d. AUX HYD .......................................... ON, Just Before Landing e. This checklist is complete. 3. ●If B-ACUM pressure is high: a. AUX HYD .............................................................................. Off b. Cycle EMERGENCY/PARKING BRAKE handle to reduce pressure. c. This checklist is complete. 3. ●If B-ACUM pressure is low: a. AUX HYD ..............................................................................ON If B-ACUM pressure remains low, reduced emergency/parking brake capability will exist. (1) This checklist is complete.
18 19 20 21 22 23 24 25 26 27
MAINHYD HYDPRESS PRESS MAIN
28
1. EICAS ........................................................... Select HYD or SUMRY 2. Check MAIN & B-ACUM hydraulic pressures. 3. ●If MAIN pressure is high: a. Obtain maintenance prior to next flight. b. This checklist is complete. 3. ●If MAIN pressure is low: a. Do not use HYD XFLOW system to retract gear or flaps. b. Maintain 35,000 feet or below. c. Refer to Abnormal Landings, Main Hydraulic System Failure Landing procedure, TAB 36, this checklist.
29 30 31 32 33 34
EFFECTIVITY CL-126B October 2004
ALL
A-43
19 20 21 22 23 24 25 26 27 28 29
AHRS11OVHT OVHT AHRS AHRS 2 OVHT AHRS 2 OVHT AHRS1-2 1-2OVHT OVHT AHRS 1. AHRS NORM (REVERSION panel)............. Select Operative AHRS 2. Monitor standby attitude & heading indicator. 3. ●AHRS 1 OVHT a. # 1 PRI & # 1 SEC Circuit Breaker (respective pilot’s & copilot’s INSTRUMENTS group [AHRS PWR])..................................Pull b. Refer to Loss of PFD Attitude or Heading Displays procedure, TAB 23, this checklist. 3. ●AHRS 2 OVHT a. # 2 SEC & # 2 PRI Circuit Breaker (respective pilot’s & copilot’s INSTRUMENTS group [AHRS PWR])..................................Pull b. Refer to Loss of PFD Attitude or Heading Displays procedure, TAB 23, this checklist. 3. ●AHRS 1-2 OVHT a. # 2 SEC & # 2 PRI Circuit Breaker (respective pilot’s & copilot’s INSTRUMENTS group [AHRS PWR])..................................Pull b. # 1 PRI & # 1 SEC Circuit Breaker (respective pilot’s & copilot’s INSTRUMENTS group [AHRS PWR])..................................Pull c. Refer to Loss of PFD Attitude or Heading Displays procedure, TAB 23, this checklist.
30 31
CNFGMISMATCH MISMATCH CNFG
32
The configuration between the IM-600s (Integrated Computer Configuration Modules) does not agree. Obtain maintenance.
33 34 18 EFFECTIVITY ALL
A-44
CL-126B October 2004
DAU1A 1AFAIL FAIL DAU DAU1B 1BFAIL FAIL DAU DAU1A-1B 1A-1BFAIL FAIL DAU
18
1. Respective CH A and/or CH B Circuit Breaker(s) (pilot’s INSTRUMENTS/INDICATIONS group [DAU 1]) .............. Set 2. ●DAU 1A FAIL a. DAU NORM (REVERSION panel) ................. Select Channel B b. This checklist is complete. 2. ●DAU 1B FAIL a. Do not revert to DAU B. b. This checklist is complete. 2. ●DAU 1A-1B FAIL a. Match left thrust lever to the right. b. Monitor right engine displays. c. Land as soon as practical. d. This checklist is complete.
19 20 21 22 23 24 25
DAU2A 2AFAIL FAIL DAU DAU2B 2BFAIL FAIL DAU DAU2A-2B 2A-2BFAIL FAIL DAU
26
1. Respective CH A and/or CH B Circuit Breaker(s) (copilot’s INSTRUMENTS/INDICATIONS group [DAU 2]) .......... Set 2. ●DAU 2A FAIL a. Do not revert to DAU B (DAU 2A not normally displayed). b. This checklist is complete. 2. ●DAU 2B FAIL a. DAU NORM (REVERSION panel) ................. Select Channel A b. This checklist is complete. 2. ●DAU 2A-2B FAIL a. Match right thrust lever to the left. b. Monitor left engine displays. c. Land as soon as practical. d. This checklist is complete.
27 28 29 30 31 32 33 34
EFFECTIVITY CL-126B October 2004
ALL
A-45
19 20 21 22 23
DAUENG ENGMISCMP MISCMP LLDAU R DAU ENG MISCMP R DAU ENG MISCMP 1. DAU NORM (REVERSION panel) ............ Select Channel A, then B Compare engine data between left & right N1, ITT, & N2 indications to determine which channel is presenting good data. 2. ●If valid channel is known: a. DAU NORM (REVERSION panel) ............Select Valid Channel b. This checklist is complete. 2. ●If valid channel is not known: a. DAU NORM (REVERSION panel) .................................. NORM b. This checklist is complete.
24 25 26 27 28 29 30
DAUSYS SYSMISCMP MISCMP LLDAU R DAU SYS MISCMP R DAU SYS MISCMP 1. EICAS ........................................................................Select SUMRY 2. DAU NORM (REVERSION panel) ............ Select Channel A, then B Evaluate system parameters to determine which channel is presenting valid data. 3. ●If valid channel is known: a. DAU NORM (REVERSION panel) ............Select Valid Channel b. This checklist is complete. 3. ●If valid channel is not known: a. DAU NORM (REVERSION panel) .................................. NORM b. This checklist is complete.
31 32 33 34 18 EFFECTIVITY ALL
A-46
CL-126B October 2004
DU11OVHT OVHT DU DU22OVHT OVHT DU DU 3 OVHT DU 3 OVHT DU 4 OVHT DU 4 OVHT
18
1. INSTR FAN Circuit Breaker (pilot’s ENVIRONMENTAL group)..................... Set, or Pull & Reset If the temperature continues to increase, the display will blank. It is recommended to perform the following procedure, conditions permitting, prior to the display blanking. 2. ●DU 1 OVHT a. DU 2 Reversion .................................................................. PFD EICAS will automatically revert to DU 3. b. DU 1 Circuit Breaker (pilot’s INSTRUMENTS group [DISPLAY])...................................... Pull c. This checklist is complete. 2. ●DU 2 OVHT a. DU 2 Reversion .................................................................. OFF EICAS will automatically revert to DU 3. b. DU 2 Circuit Breaker (pilot’s INSTRUMENTS group [DISPLAY])...................................... Pull c. This checklist is complete. 2. ●DU 1-2 OVHT a. DU 2 Reversion .................................................................. OFF EICAS will automatically revert to DU 3. b. DU 1 & DU 2 Circuit Breakers (pilot’s INSTRUMENTS group [DISPLAY]) .......................... Pull Rely on the copilot’s flight displays & standby instruments. c. This checklist is complete. 2. ●DU 3 OVHT a. DU 3 Reversion..................................Push (if DU 3 is presently in EICAS format) b. DU 3 Circuit Breaker (copilot’s INSTRUMENTS group [DISPLAY])...................................... Pull c. This checklist is complete. 2. ●DU 4 OVHT a. DU 3 Reversion...................................................................PFD EICAS will automatically revert to DU 2. b. DU 4 Circuit Breaker (copilot’s INSTRUMENTS group [DISPLAY])...................................... Pull c. This checklist is complete.
(Procedure Continued) EFFECTIVITY CL-126B October 2004
ALL
A-47
19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34
19 20 21 22 23 24 25 26
2. ●DU 3-4 OVHT a. DU 3 Reversion ......... Push as Required to get EICAS on DU 2 b. DU 3 & DU 4 Circuit Breakers (copilot’s INSTRUMENTS group [DISPLAY]) ......................................Pull Rely on the pilot’s flight displays & standby instruments. c. This checklist is complete.
OVHT ICIC11OVHT OVHT ICIC22OVHT If conditions permit (before IC shutdown, or after IC shutdown has occurred): 1. Autopilot ........................................................................... Disengage Engage yaw damper as required. 2. Monitor standby instruments. 3. IC/SG NORM (REVERSION).........................................Select Other (unaffected) IC/SG 4. Respective IC/SG 1 or 2 Circuit Breaker (INSTRUMENTS/INDICATIONS group) ......................................Pull 5. Refer to IC 1 or 2 Failure procedure, this page.
IC 1 or 2 Failure Procedure 27 28 29
IC 1 Failure 1. 2. 3. 4. 5.
30 31 32 33 34 18
Control Wheel Master (MSW) .............................Depress & Release Monitor standby instruments. Yaw Damper ..................................................................As Required Airspeed............................................................ ≤ Mach trim off MMO IC/SG 1 Circuit Breaker (INSTRUMENTS/INDICATIONS group) ............ Set, or Pull & Reset
If IC 1 remains failed: a. IC/SG NORM (REVERSION) ........................................Select 2 Use copilot’s PFD/EICAS bezel controls. MFD display and functions will not be available. b. Airspeed .................................................... ≤ Mach trim off MMO
IC 2 Failure 1. Control Wheel Master (MSW) .............................Depress & Release 2. Monitor standby instruments. 3. IC/SG 2 Circuit Breaker (INSTRUMENTS/INDICATIONS group) ........... Set, or Pull & Reset 4. Yaw Damper ..................................................................As Required Do not re-engage autopilot, even if IC2 is restored.
(Procedure Continued) EFFECTIVITY ALL
A-48
CL-126B October 2004
If IC 2 remains failed: a. IC/SG NORM (REVERSION)........................................ Select 1 Use pilot’s PFD/EICAS bezel controls. MFD display and functions will not be available. b. Maintain 33,000 feet or below. c. Airspeed ............................... ≥ 0.65 MI Until Below 33,000 Feet d. Land as soon as practical.
ICBUS BUSFAIL FAIL IC
18 19 20
1. Yaw Damper ........................................................................ Engage 2. IC/SG NORM (REVERSION) ................... Select to Pilot Flying Side Use pilot flying side PFD/EICAS bezel controls.
21 22
LBS/KGSCONFIG CONFIG LBS/KGS The pounds/kilograms configuration of the IC-600 (Integrated Computer) disagrees with the configuration of the DAU 1 or DAU 2 on the ground.
23 24
PFDCHECK CHECK LLPFD PFDCHECK CHECK RRPFD LRPFD PFDCHECK CHECK LR
25
1. DU 2 (or DU 3 for R PFD CHECK) Reversion ............................PFD EICAS will be displayed on the opposite inboard DU.
26
If condition remains: a. DU 2 (or DU 3 for R PFD CHECK) Reversion ................ NORM b. Monitor opposite PFD & standby instruments. c. AP XFR .................................... Select to Functioning PFD Side d. Autopilot ................................................................... As Desired e. Land as soon as practical.
27
WARNAUDIO AUDIO WARN
29 30
1. Monitor EFIS/CAS displays for related visual warning indications.
LRWARN WARNPWR PWRFAIL FAIL LR
If LR WARN PWR FAIL remains illuminated: a. Monitor EFIS/CAS displays & pressurization controller for related visual warning indications. b. Land as soon as practical. EFFECTIVITY 45-002 thru 45-225 ALL not modified by SB 45-55-6
31 32
1. L & R WARN PANEL Circuit Breakers (pilot’s and copilot’s INSTRUMENTS/INDICATIONS group) ......................... Set
CL-126B October 2004
28
A-49
33 34
Air Data Computer (ADC) Failure — Single 19 20 21 22 23
1. ADC NORM (REVERSION panel) .............. Select Operational ADC If time & conditions permit: 2. Respective ADC Circuit Breaker (INSTRUMENTS group) .................................... Set, or Pull & Reset 3. ADC NORM (REVERSION)....................................................NORM 4. Cross-check airspeed & altitude indications with the standby instruments. Refer to Airspeed/Mach Calibrations — Standby System or Altitude Position Corrections — Standby System charts, Section V in the AFM. If air data computer is not recovered: a. ADC NORM (REVERSION) .................Select Operational ADC b. Airspeed ..................................... ≤ Mach Trim Off MMO, Prior to Disengaging the Autopilot
24 25 26
Air Data Computer (ADC) Failure — Dual
27 28 29
1. Maintain aircraft control by reference to the standby airspeed/Mach indicator & altimeter. Roll control authority may be less than normal. 2. Pilot’s & copilot’s ADC 1 & 2 Circuit Breakers (respective INSTRUMENTS/INDICATIONS group) ................................................................ Set, or Pull & Reset If neither ADC operation is restored: a. Monitor the standby attitude indicator. b. Airspeed ..................................... ≤ Mach Trim Off MMO, Prior to Disengaging the Autopilot c. Autopilot ................................................................... As Desired PIT, ROL, HDG, NAV & APP Only d. MANUAL Rate Control (PRESSURIZATION) ....... As Required e. Land as soon as possible.
30 31 32 33 34 35
EFFECTIVITY
A-50
ALL
CL-126B October 2004
If IC 2 remains failed: a. IC/SG NORM (REVERSION)........................................ Select 1 Use pilot’s PFD/EICAS bezel controls. MFD display and functions will not be available.
ICBUS BUSFAIL FAIL IC
18 19
1. Yaw Damper ................................................................... As Desired 2. IC/SG NORM (REVERSION) ................... Select to Pilot Flying Side Use pilot flying side PFD/EICAS bezel controls.
20
LBS/KGSCONFIG CONFIG LBS/KGS
21
The pounds/kilograms configuration of the IC-600 (Integrated Computer) disagrees with the configuration of the DAU 1 or DAU 2 on the ground.
22
PFDCHECK CHECK LLPFD PFDCHECK CHECK RRPFD LRPFD PFDCHECK CHECK LR
23 24
1. DU 2 (or DU 3 for R PFD CHECK) Reversion ............................PFD EICAS will be displayed on the opposite inboard DU. If condition remains: a. DU 2 (or DU 3 for R PFD CHECK) Reversion ................ NORM b. Monitor opposite PFD & standby instruments. c. AP XFR .................................... Select to Functioning PFD Side d. Autopilot ................................................................... As Desired e. Land as soon as practical.
WARNAUDIO AUDIO WARN
25 26 27 28 29
1. Monitor EFIS/CAS displays for related visual warning indications.
30
LRWARN WARNPWR PWRFAIL FAIL LR 1. L & R WARN PANEL Circuit Breakers (pilot’s and copilot’s INSTRUMENTS/INDICATIONS group) ......................... Set If LR WARN PWR FAIL remains illuminated: a. Monitor EFIS/CAS displays & pressurization controller for related visual warning indications. b. Land as soon as practical.
31 32 33 34
CL-126B October 2004
EFFECTIVITY 45-226 & on, and prior ALL aircraft modified by SB 45-55-6
A-49.1
Air Data Computer (ADC) Failure — Single 19 20 21 22 23
1. ADC NORM (REVERSION panel) .............. Select Operational ADC If time & conditions permit: 2. Respective ADC Circuit Breaker (INSTRUMENTS group) .................................... Set, or Pull & Reset 3. ADC NORM (REVERSION)....................................................NORM 4. Cross-check airspeed & altitude indications with the standby instruments. Refer to Airspeed/Mach Calibrations — Standby System or Altitude Position Corrections — Standby System charts, Section V in the AFM. If air data computer is not recovered: a. ADC NORM (REVERSION) .................Select Operational ADC b. Airspeed ..................................... ≤ Mach Trim Off MMO, Prior to Disengaging the Autopilot
24 25 26
Air Data Computer (ADC) Failure — Dual
27 28 29
1. Maintain aircraft control by reference to the standby airspeed/Mach indicator & altimeter. Roll control authority may be less than normal. 2. Pilot’s & copilot’s ADC 1 & 2 Circuit Breakers (respective INSTRUMENTS/INDICATIONS group) ................................................................ Set, or Pull & Reset If neither ADC operation is restored: a. Monitor the standby attitude indicator. b. Airspeed ..................................... ≤ Mach Trim Off MMO, Prior to Disengaging the Autopilot c. Autopilot ................................................................... As Desired PIT, ROL, HDG, NAV & APP Only d. MANUAL Rate Control (PRESSURIZATION) ....... As Required e. Land as soon as possible.
30 31 32 33 34 35
EFFECTIVITY
A-50
ALL
CL-126B October 2004
Display Unit Failure 18
●DU 1 Failure 1. DU 2 Reversion ..........................................................................PFD The pilot’s PFD will be displayed on DU 2, the EICAS will be displayed on DU 3 and the MFD will not be available.
19 20
●DU 2 Failure 1. DU 2 Reversion ..........................................................................OFF The EICAS will be displayed on DU 3 and the MFD will not be available. ●DU 3 Failure 1. ■If DU 3 is displaying EICAS: a. DU 3 Reversion..................................................................Push The EICAS will be displayed on DU 2 and the MFD will not be available. 1. ■If DU 3 is displaying MFD: a. Continue. The MFD will not be available.
21 22 23 24 25
●DU 4 Failure 1. DU 3 Reversion ..........................................................................PFD The copilot’s PFD will be displayed on DU 3, the EICAS will be displayed on DU 2 and the MFD will not be available.
26 27 28 29 30 31 32 33 34
CL-126B October 2004
EFFECTIVITY ALL
A-51
Erroneous Pitot-Static Indications 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33
1. Maintain safe aircraft attitude & thrust setting. Using the autopilot in PIT, ROL, HDG, NAV or APP modes will help reduce work load. Do not use ALT, SPD, FLC, VS or VNAV modes. Minimize large changes in thrust setting unless they are necessary to control the aircraft. If an L or R PITOT HT or STBY PITOT HT amber CAS is illuminated, that system should be the suspected system: a. L & R PROBES .................................................................... On b. PITOT & STBY PITOT Circuit Breakers (respective ANTI-ICE group [L & R PROBES HT]) .............. Set c. Fly out of icing conditions as soon as possible. 2. Compare pilot’s, copilot’s, & standby airspeed, Mach & altitude. 3. ●If the malfunction is known or suspected in the pilot’s or copilot’s pitot-static system: a. ADC NORM (REVERSION) ............................Select Valid ADC b. Autopilot ................................................................... As Desired c. Land as soon as practical. d. This checklist is complete. 3. ●If the malfunction is known or suspected in both the pilot’s & copilot’s pitot-static systems: a. Refer to the standby system. The standby system indications must be corrected before comparison to the ADC indications. Refer to Airspeed/Mach Calibrations & Altitude Position Corrections — Standby System charts, Section V in the AFM. b. Autopilot ................................................................... As Desired Use PIT, ROL, HDG, NAV or APP modes. Do not use ALT, SPD, FLC, VS or VNAV modes. c. Land as soon as possible. d. This checklist is complete. 3. ●If the malfunction is known or suspected in the standby pitotstatic system: a. Refer to the normal ADC displays. b. Autopilot ................................................................... As Desired c. Land as soon as practical. d. This checklist is complete.
34 35
EFFECTIVITY
A-52
ALL
CL-126B October 2004
Loss of PFD Attitude or Heading Displays 1. 2. 3. 4. 5.
AHRS NORM (REVERSION panel) ............ Select Operative AHRS Monitor standby attitude & heading indicator. Maintain 33,000 feet or below. Airspeed ......................................≥ 0.65 MI Until Below 33,000 Feet Land as soon as practical.
If time & conditions permit: 6. Establish aircraft in straight & level, unaccelerated flight. 7. ●If the loss is associated with the pilot’s PFD: a. Pilot’s #1 PRI & Copilot’s #1 SEC Circuit Breakers (respective INSTRUMENTS/ INDICATIONS group [AHRS PWR]) ............................Pull Both b. Pilot’s #1 PRI & Copilot’s #1 SEC Circuit Breakers ..............Set c. Go to step 8. 7. ●If the loss is associated with the copilot’s PFD: a. Pilot’s #2 SEC & Copilot’s #2 PRI Circuit Breakers (respective INSTRUMENTS/ INDICATIONS group [AHRS PWR]) ............................Pull Both b. Pilot’s #2 SEC & Copilot’s #2 PRI Circuit Breakers ..............Set c. Go to step 8. 8. AHRS NORM (REVERSION panel) ....................................... NORM Maintain aircraft attitude by monitoring the operating side flight display & the standby attitude indicator. Initialization should occur within approximately 20 seconds. Successful initialization is indicated by attitude & heading displays. If initialization does not occur within approximately 20 seconds: a. AHRS NORM (REVERSION panel)......Select Operative AHRS
18 19 20 21 22 23 24 25 26 27 28 29
Loss of Standby Attitude Indicator
30
If EMER BUS VOLTS amber CAS is illuminated, refer to the EMER BUS VOLTS procedure, TAB 5, this checklist. 1. EMER BATT ................................................................................. On 2. BUS Circuit Breaker (pilot’s ELECTRICAL group [EMER BUS]) ............................................. Set 3. Establish aircraft in straight & level, unaccelerated flight. 4. Standby Attitude Indicator ................................... Cage then Uncage
31
If standby attitude is not recovered: a. Standby Attitude Indicator ................................................ Cage b. Land as soon practical.
34
CL-126B October 2004
EFFECTIVITY 45-002 thru 45-225 ALL not modified by SB 45-55-6
A-53
32 33
Multi-Function Display (MFD) Annunciations 19 20 21 22
EICASCHK CHK EICAS 1. DU 2 or DU 3 Reversion ........................................................... Push 2. ●If EICAS CHK extinguishes: a. Leave EICAS display on current DU until landing. b. This checklist is complete. 2. ●If EICAS CHK remains illuminated: a. Monitor engine instruments (N1, ITT or N2) for abnormal indications. b. This checklist is complete.
23
DG X DGx
24
Located to the right of the heading readout, this illumination indicates AHRS or IC/SG reversion has been selected & the respective HEADING switch is in the unslaved (FREE) mode.
25
MAG X MAGx
26 27
Located to the right of the heading readout, this illumination indicates the source of AHRS data. MAGx will be displayed with AHRS or IC/SG reversion, indicating a single AHRS source being displayed to both pilots’ displays.
MENUINOP INOP MENU 28 29 30 31
Located above the bezel controller, this illumination indicates the MFD bezel menu is inoperative. 1. L & R CTRL Circuit Breaker (pilot’s & copilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]) ..................... Set If condition persists: 2. DU 2 or DU 3 Reversion ................................................Push if MFD Functionality Required The EICAS will now have the MENU INOP condition.
32
STAB STAB
33
Located on the lower left of the heading display, this illumination indicates weather radar stabilization is off.
34 35
TANO NOBRG BRG TA Located in the upper right corner of the TCAS zoom window, this annunciation indicates that a TA has been encountered, but no bearing to that TA is available for display.
EFFECTIVITY
A-54
ALL
CL-126B October 2004
Loss of PFD Attitude or Heading Displays 1. AHRS NORM (REVERSION panel) ............ Select Operative AHRS 2. Monitor standby attitude & heading indicator. 3. Land as soon as practical. If time & conditions permit: 4. Establish aircraft in straight & level, unaccelerated flight. 5. ●If the loss is associated with the pilot’s PFD: a. Pilot’s #1 PRI & Copilot’s #1 SEC Circuit Breakers (respective INSTRUMENTS/ INDICATIONS group [AHRS PWR]) ............................Pull Both b. Pilot’s #1 PRI & Copilot’s #1 SEC Circuit Breakers ..............Set c. Go to step 6. 5. ●If the loss is associated with the copilot’s PFD: a. Pilot’s #2 SEC & Copilot’s #2 PRI Circuit Breakers (respective INSTRUMENTS/ INDICATIONS group [AHRS PWR]) ............................Pull Both b. Pilot’s #2 SEC & Copilot’s #2 PRI Circuit Breakers ..............Set c. Go to step 6. 6. AHRS NORM (REVERSION panel) ....................................... NORM Maintain aircraft attitude by monitoring the operating side flight display & the standby attitude indicator. Initialization should occur within approximately 20 seconds. Successful initialization is indicated by attitude & heading displays. If initialization does not occur within approximately 20 seconds: a. AHRS NORM (REVERSION panel)......Select Operative AHRS
18 19 20 21 22 23 24 25 26 27 28 29
Loss of Standby Attitude Indicator
30
If EMER BUS VOLTS amber CAS is illuminated, refer to the EMER BUS VOLTS procedure, TAB 5, this checklist. 1. EMER BATT ................................................................................. On 2. BUS Circuit Breaker (pilot’s ELECTRICAL group [EMER BUS]) ............................................. Set 3. Establish aircraft in straight & level, unaccelerated flight. 4. Standby Attitude Indicator ................................... Cage then Uncage If standby attitude is not recovered: a. Standby Attitude Indicator ................................................ Cage b. Land as soon practical.
CL-126B October 2004
EFFECTIVITY 45-226 & on, and prior ALL aircraft modified by SB 45-55-6
A-53.1
31 32 33 34
Multi-Function Display (MFD) Annunciations 19 20 21 22
EICASCHK CHK EICAS 1. DU 2 or DU 3 Reversion ........................................................... Push 2. ●If EICAS CHK extinguishes: a. Leave EICAS display on current DU until landing. b. This checklist is complete. 2. ●If EICAS CHK remains illuminated: a. Monitor engine instruments (N1, ITT or N2) for abnormal indications. b. This checklist is complete.
23
DG X DGx
24
Located to the right of the heading readout, this illumination indicates AHRS or IC/SG reversion has been selected & the respective HEADING switch is in the unslaved (FREE) mode.
25
MAG X MAGx
26 27
Located to the right of the heading readout, this illumination indicates the source of AHRS data. MAGx will be displayed with AHRS or IC/SG reversion, indicating a single AHRS source being displayed to both pilots’ displays.
MENUINOP INOP MENU 28 29 30 31
Located above the bezel controller, this illumination indicates the MFD bezel menu is inoperative. 1. L & R CTRL Circuit Breaker (pilot’s & copilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]) ..................... Set If condition persists: 2. DU 2 or DU 3 Reversion ................................................Push if MFD Functionality Required The EICAS will now have the MENU INOP condition.
32
STAB STAB
33
Located on the lower left of the heading display, this illumination indicates weather radar stabilization is off.
34 35
TANO NOBRG BRG TA Located in the upper right corner of the TCAS zoom window, this annunciation indicates that a TA has been encountered, but no bearing to that TA is available for display.
EFFECTIVITY
A-54
ALL
CL-126B October 2004
Multi-Function Display (MFD) Annunciations (Cont) TCAS TCASFAIL FAIL
18
Located in the upper left corner of the TCAS zoom window, this annunciation indicates that TCAS is failed.
19
1. TCAS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ........................ Pull & Reset 2. Verify correct transponder operation. Select opposite transponder. 3. Select ATC ALT mode on the RMU (ATC/TCAS) until the failed condition is resolved.
20 21 22
TERRFAIL FAIL TERR Located in the upper left corner of the MFD and indicates the Terrain Mode is inoperative. 1. FMS 1 and FMS 2 (if installed) ......................................... Check ON 2. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ......................... Pull & Reset
23 24 25
TERRN/A N/A TERR Located in the upper left corner of the MFD, and indicates that terrain information cannot be displayed because of an uncertain FMS position or loss of inputs required for terrain awareness alerting and display functions.
26 27
TGT TGT Located on the lower left of the heading display, this illumination indicates a weather radar target alert is activated. Take appropriate action to verify the weather radar alert.
28 29
WX WX Located on the lower left of the heading display, this illumination indicates an invalid weather radar.
30 31 32 33 34
CL-126B October 2004
EFFECTIVITY ALL
A-54.1 A-55
Primary Flight Display (PFD) Annunciations 19 20 21 22
ADCx Located to the left of the attitude sphere, this illumination indicates both pilot & copilot displayed air data sources are the same.
ALT ALT 1. Check that both pilot’s altimeters are set to the same value. If mismatch persists: a. Refer to Erroneous Pitot-Static Indications procedure, TAB 23, this checklist.
AOA 23 24
Located next to the airspeed scale, this illumination indicates invalid angleof-attack data. The Low Speed Awareness (LSA) cue will not be displayed. Cross reference the other PFD LSA cue. This illumination may be accompanied by an L (R) STALLWARN FAIL amber CAS (refer to the L (R) STALLWARN FAIL procedure, TAB 16, this checklist).
25
APflash (flash) AP
26
Illuminates above the attitude sphere for 5 seconds & clears. Indicates the autopilot has disengaged & is accompanied by the aural “cavalry charge” alert.
27
AP(steady) (steady) AP
28 29 30 31 32 33 34 35
1. ●If accompanied by an amber YD: a. Maintain 33,000 feet or below b. Airspeed .............................. ≥ 0.65 MI Until Below 33,000 Feet c. If conditions permit: (1) IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ....... Pull & Reset to Regain Autopilot d. ■If amber YD remains illuminated: (1) Land as soon as practical. (2) This checklist is complete. d. ■If amber YD extinguishes: (1) Yaw Damper ........................................................... Engage (2) This checklist is complete. 1. ●If not accompanied by an amber YD: a. Yaw Damper.................................................................. Engage b. This checklist is complete.
APFAIL FAIL AP 1. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) .............. Set 2. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)..........................Pull & Reset
A-56 A-55
EFFECTIVITY 45-002 thru 45-225 ALL not modified by SB 45-55-6
CL-126B October 2004
Multi-Function Display (MFD) Annunciations (Cont) TCAS TCASFAIL FAIL
18
Located in the upper left corner of the TCAS zoom window, this annunciation indicates that TCAS is failed.
19
1. TCAS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ........................ Pull & Reset 2. Verify correct transponder operation. Select opposite transponder. 3. Select ATC ALT mode on the RMU (ATC/TCAS) until the failed condition is resolved.
20 21 22
TERRFAIL FAIL TERR Located in the upper left corner of the MFD and indicates the Terrain Mode is inoperative. 1. FMS 1 and FMS 2 (if installed) ......................................... Check ON 2. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ......................... Pull & Reset
23 24 25
TERRN/A N/A TERR Located in the upper left corner of the MFD, and indicates that terrain information cannot be displayed because of an uncertain FMS position or loss of inputs required for terrain awareness alerting and display functions.
26 27
TGT TGT Located on the lower left of the heading display, this illumination indicates a weather radar target alert is activated. Take appropriate action to verify the weather radar alert.
28 29
WX WX Located on the lower left of the heading display, this illumination indicates an invalid weather radar.
30 31 32 33 34
CL-126B October 2004
EFFECTIVITY ALL
A-55.1 A-55
Primary Flight Display (PFD) Annunciations 19 20 21 22 23 24 25
ADCx ADC X Located to the left of the attitude sphere, this illumination indicates both pilot & copilot displayed air data sources are the same.
ALT ALT 1. Check that both pilot’s altimeters are set to the same value. If mismatch persists: a. Refer to Erroneous Pitot-Static Indications procedure, TAB 23, this checklist.
AOA AOA Located next to the airspeed scale, this illumination indicates invalid angleof-attack data. The Low Speed Awareness (LSA) cue will not be displayed. Cross reference the other PFD LSA cue. This illumination may be accompanied by an L (R) STALLWARN FAIL amber CAS (refer to the L (R) STALLWARN FAIL procedure, TAB 16, this checklist).
APflash (flash) AP 26 27
Illuminates above the attitude sphere for 5 seconds & clears. Indicates the autopilot has disengaged & is accompanied by the aural “cavalry charge” alert.
(steady) APstead AP 28 29 30 31 32 33 34
1. ●If accompanied by an amber YD and conditions permit: a. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group).............. Pull & Reset to Regain Autopilot b. ■If amber YD remains illuminated: (1) This checklist is complete. b. ■If amber YD extinguishes: (1) Yaw Damper.......................................................As Desired (2) This checklist is complete. 1. ●If not accompanied by an amber YD: a. Yaw Damper .............................................................As Desired b. This checklist is complete.
APFAIL FAIL AP 1. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group)...............Set 2. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ......................... Pull & Reset
35
EFFECTIVITY
A-56.1 A-55.2
45-226 & on, and prior ALL aircraft modified by SB 45-55-6
CL-126B October 2004
Primary Flight Display (PFD) Annunciations (Cont) AP APTEST TEST Located above the attitude sphere, this illumination indicates test mode for the AP during ground power-up of the AHRS.
19
ATT ATT 1. Compare indications with standby attitude indicator to determine faulty system. 2. Autopilot & Yaw Damper...................................................Disengage 3. AHRS NORM (REVERSION panel) ............ Select Operative AHRS 4. Do not re-engage autopilot or yaw damper. 5. Maintain 33,000 feet or below. 6. Airspeed ......................................≥ 0.65 MI Until Below 33,000 Feet 7. Land as soon as practical.
20 21 22 23
CASMSG MSG CAS 1. Note existing CAS messages. 2. DU 2 or DU 3 Reversion .......................... Push & Compare the CAS Messages on the Reverted EICAS 3. Take the appropriate CAS message action for any new messages.
DG X DGx Located to the right of the heading readout, this illumination indicates AHRS or IC/SG reversion has been selected & the respective HEADING switch is in the unslaved (FREE) mode.
FD FDFAIL FAIL
24 25 26 27 28
Display of the FD FAIL on the PFD & removal of the flight director steering commands indicate a failure in the flight director system or loss of sensor data required for the active modes on that side. If FD FAIL appears because of internal failure, loss of AHRS data, or selection of AHRS reversion, the autopilot will disconnect. If FD FAIL appears because of invalid sensor data, the autopilot will not disconnect. If the autopilot remains engaged to the failed flight director, operation will be in basic PIT & ROL mode: 1. Monitor aircraft attitude. 2. Select XFR on the guidance controller to the opposite side. If conditions permit: a. Respective IC/SG 1 or 2 Circuit Breaker (INSTRUMENTS/INDICATIONS group)............. Pull & Reset to Regain Autopilot b. Yaw Damper........................................................... As Required CL-126B October 2004
18
EFFECTIVITY 45-002 thru 45-225 ALL not modified by SB 45-55-6
A-57 A-56
29 30 31 32 33 34
Primary Flight Display (PFD) Annunciations (Cont) 19 20 21 22 23 24 25 26
GND GNDPROX PROX “CAUTION OBSTACLE, CAUTION OBSTACLE” or
“OBSTACLE AHEAD, OBSTACLE AHEAD”
1. EGPWS Terrain Awareness Display ......................................Monitor 2. Stop any descent and climb as required.
GND GNDPROX PROX “CAUTION TERRAIN, CAUTION TERRAIN” or
“TERRAIN AHEAD, TERRAIN AHEAD”
1. EGPWS Terrain Awareness Display ......................................Monitor 2. Stop any descent and climb as required.
GND GNDPROX PROX “DON’T SINK” 1. Arrest sink rate as required.
GNDPROX PROX GND 27 28 29 30 31 32 33
“GLIDESLOPE” 1. Fly aircraft to glideslope. Once triggered, alerts may be cancelled by selecting G/S Switch OFF.
GND GNDPROX PROX “SINK RATE” 1. Arrest sink rate as required.
GND GNDPROX PROX “TERRAIN, TERRAIN” 1. EGPWS Terrain Awareness Display ......................................Monitor 2. Stop any descent and climb as required.
GND GNDPROX PROX “TOO LOW, FLAPS”
34
1. FLAPS ............................................................. DN, Check Indication
35
EFFECTIVITY
A-58 A-56.1
ALL
CL-126B October 2004
Primary Flight Display (PFD) Annunciations (Cont) APTEST TEST AP Located above the attitude sphere, this illumination indicates test mode for the AP during ground power-up of the AHRS.
18 19
ATT ATT 1. Compare indications with standby attitude indicator to determine faulty system. 2. Autopilot & Yaw Damper...................................................Disengage 3. AHRS NORM (REVERSION panel) ............ Select Operative AHRS 4. Do not re-engage autopilot or yaw damper.
CASMSG MSG CAS 1. Note existing CAS messages. 2. DU 2 or DU 3 Reversion .......................... Push & Compare the CAS Messages on the Reverted EICAS 3. Take the appropriate CAS message action for any new messages.
20 21 22 23 24
DG X DGx
25
Located to the right of the heading readout, this illumination indicates AHRS or IC/SG reversion has been selected & the respective HEADING switch is in the unslaved (FREE) mode.
26 27
FD FDFAIL FAIL Display of the FD FAIL on the PFD & removal of the flight director steering commands indicate a failure in the flight director system or loss of sensor data required for the active modes on that side. If FD FAIL appears because of internal failure, loss of AHRS data, or selection of AHRS reversion, the autopilot will disconnect. If FD FAIL appears because of invalid sensor data, the autopilot will not disconnect. If the autopilot remains engaged to the failed flight director, operation will be in basic PIT & ROL mode: 1. Monitor aircraft attitude. 2. Select XFR on the guidance controller to the opposite side. If conditions permit: a. Respective IC/SG 1 or 2 Circuit Breaker (INSTRUMENTS/INDICATIONS group)............. Pull & Reset to Regain Autopilot b. Yaw Damper........................................................... As Required
CL-126B October 2004
EFFECTIVITY 45-226 & on, and prior ALL aircraft modified by SB 45-55-6
A-56.2 A-57.1
28 29 30 31 32 33 34
Primary Flight Display (PFD) Annunciations (Cont) 19 20 21 22 23 24 25 26
GND GNDPROX PROX “CAUTION OBSTACLE, CAUTION OBSTACLE” or
“OBSTACLE AHEAD, OBSTACLE AHEAD”
1. EGPWS Terrain Awareness Display ......................................Monitor 2. Stop any descent and climb as required.
GND GNDPROX PROX “CAUTION TERRAIN, CAUTION TERRAIN” or
“TERRAIN AHEAD, TERRAIN AHEAD”
1. EGPWS Terrain Awareness Display ......................................Monitor 2. Stop any descent and climb as required.
GND GNDPROX PROX “DON’T SINK” 1. Arrest sink rate as required.
GNDPROX PROX GND 27 28 29 30 31 32 33
“GLIDESLOPE” 1. Fly aircraft to glideslope. Once triggered, alerts may be cancelled by selecting G/S Switch OFF.
GND GNDPROX PROX “SINK RATE” 1. Arrest sink rate as required.
GND GNDPROX PROX “TERRAIN, TERRAIN” 1. EGPWS Terrain Awareness Display ......................................Monitor 2. Stop any descent and climb as required.
GND GNDPROX PROX “TOO LOW, FLAPS”
34
1. FLAPS ............................................................. DN, Check Indication
35
EFFECTIVITY
A-58 A-56.3
ALL
CL-126B October 2004
Primary Flight Display (PFD) Annunciations (Cont) GND GNDPROX PROX
18 “TOO LOW, GEAR”
1. ●If adequate time is available to extend gear: a. GEAR .................................................................................... DN b. This checklist complete. 1. ●If adequate time is not available to extend gear: a. Execute go-around. b. This checklist complete.
GND GNDPROX PROX
19 20 21 22
“TOO LOW, TERRAIN” Fly out of the warning envelope or reconfigure as required.
23
GS GS
24
Indicates a comparator mismatch of the pilot’s & copilot’s glideslope data. Illuminates below the attitude sphere on the left side. 1. NAV Source .......................Determine Correct NAV Source & Select If unable to determine correct source: a. Use localizer approach minimums.
HDG HDG 1. Establish aircraft in straight & level, unaccelerated flight. 2. Compare indications with magnetic compass. 3. ●If single system is in error: a. Autopilot .................................................................... Disengage b. Associated HEADING ................................... FREE, then Slave If heading split cannot be corrected: (1) AHRS NORM (REVERSION panel) ............... Select AHRS with Correct Heading (2) This checklist is complete. 3. ●If heading cannot be determined: a. Autopilot .................................................................... Disengage b. Both HEADING ............................................. FREE, then Slave c. This checklist is complete.
25 26 27 28 29 30 31 32
IAS IAS
33
Vertically illuminated within the airspeed tape at the upper corner, this illumination indicates a mismatch of the pilot’s & copilot’s airspeed data. Refer to Erroneous Pitot-Static Indications procedure, TAB 23, this checklist.
34
CL-126B October 2004
EFFECTIVITY ALL
A-56.4 A-59
Primary Flight Display (PFD) Annunciations (Cont) 19 20 21 22 23 24
ILS ILS Located below the attitude sphere on the left side, this illumination indicates a comparator mismatch of the pilot’s & copilot’s localizer & glideslope data. 1. NAV Source ...................... Determine Correct NAV Source & Select If unable to determine correct source: a. Execute missed approach.
LOC LOC Located below the attitude sphere on the left side, this illumination indicates a comparator mismatch of the pilot’s & copilot’s localizer data. 1. NAV Source ...................... Determine Correct NAV Source & Select If unable to determine correct source: a. Execute missed approach.
MACH 25 26 27
Vertically illuminated within the Mach tape at the upper corner, this illumination indicates a mismatch of the pilot’s & copilot’s Mach number data. Refer to Erroneous Pitot-Static Indications procedure, TAB 23, this checklist.
MAGx MAGx
28
Located to the right of the heading readout, this illumination indicates the source of AHRS data. MAGx will be displayed with AHRS or IC/SG reversion, indicating a single AHRS source being displayed to both pilots’ displays.
29
MAX SPD MAXSPD
30
Vertically illuminated left of the attitude sphere, this illumination indicates the autopilot overspeed mode is active.
31
MIN MIN
32 33
Located in the lower right corner of the attitude sphere, this illumination indicates capture of the BARO or RA minimums when the barometric altitude is equal to or less than the BARO minimums readout, or the radio altitude is equal to or less than the RA minimums readout (whichever one, BARO or RA, is displayed on the PFD).
34 35
EFFECTIVITY
A-60 A-56.5
ALL
CL-126B October 2004
Primary Flight Display (PFD) Annunciations (Cont) PIT 1. Compare indications with standby attitude indicator to determine faulty system. 2. Autopilot & Yaw Damper...................................................Disengage 3. AHRS NORM (REVERSION panel) ............ Select Operative AHRS 4. Do not re-engage autopilot or yaw damper. 5. Maintain 33,000 feet or below. 6. Airspeed ...................................... ≥ 0.65 MI Until Below 33,000 Feet 7. Land as soon as practical.
RA RA
18 19 20 21 22
Located below the attitude sphere on the left side, this illumination indicates a comparator mismatch of the displayed pilot’s & copilot’s radio altitude. 1. Use BARO minimums for approach.
RA —RA—
23 24
Illuminated & boxed at the bottom of the attitude sphere, this illumination indicates invalid radio altitude. RA minimums & TCAS (if installed), and EGPWS (if installed) are inoperative. The radio altitude function of the gear warning system is inoperative. 1. RAD ALT 1 or 2 (If Installed) Circuit Breaker (pilot’s or copilot’s INSTRUMENTS/INDICATIONS group) ......... Set 2. Refer to GEAR procedure, TAB 29, this checklist. The takeoff & landing CAS inhibit function is disabled.
RA RAFAIL FAIL Located below the VSI display, this annunciation indicates resolution advisory information from the TCAS computer is invalid or not received. This can occur with or without an actual intruder aircraft being present. 1. Attempt to visually acquire possible intruder aircraft.
25 26 27 28 29 30
If annunciation persists: 2. RMU (ATC/TCAS)............................................................... TA ONLY
31
RB RB
32
Located above the attitude sphere, this illumination indicates the rudder boost system has disengaged due to a monitor. Do not takeoff. 1. RUD BOOST ..............................................................................OFF 2. Control Wheel Master (MSW)............................. Depress & Release (Procedure Continued) CL-126B October 2004
EFFECTIVITY 45-002 thru 45-225 ALL not modified by SB 45-55-6
A-56.6 A-61
33 34
19 20 21 22
3. ●If RB extinguishes: a. Yaw Damper ................................................................. Engage b. This checklist is complete. 3. ●If RB remains illuminated: a. Maintain 33,000 feet or below. Yaw damper is not operative. b. Airspeed .............................. ≥ 0.65 MI Until Below 33,000 Feet c. If conditions permit: (1) IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ....... Pull & Reset to Regain Autopilot d. ■If RB remains illuminated: (1) Land as soon as practical. (2) This checklist is complete.
23
d. ■If RB extinguishes: (1) Yaw Damper ........................................................... Engage (2) This checklist is complete.
24 25 26 27 28 29
ROL ROL 1. Compare indications with standby attitude indicator to determine faulty system. 2. Autopilot & Yaw Damper .................................................. Disengage 3. AHRS NORM (REVERSION panel)............. Select Operative AHRS 4. Do not re-engage autopilot or yaw damper. 5. Maintain 33,000 feet or below. 6. Airspeed...................................... ≥ 0.65 MI Until Below 33,000 Feet 7. Land as soon as practical.
30
SG X SGx
31
Located to the left of the attitude sphere & accompanied by the ADCX & ATTX annunciators, this illumination indicates both pilot & copilot are displaying the same AHRS, air data, & navigation sources from one IC/SG.
32
TCASFAIL FAIL TCAS
33
Located below the VSI display, this annunciation indicates that TCAS is failed.
34
1. TCAS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ........................Pull & Reset 2. Verify correct transponder operation. Select opposite transponder. 3. Select ATC ALT mode on the RMU (ATC/TCAS) until the failed condition is resolved.
35
A-62 A-56.7
EFFECTIVITY 45-002 thru 45-225 ALL not modified by SB 45-55-6
CL-126B October 2004
Primary Flight Display (PFD) Annunciations (Cont) PIT PIT 1. Compare indications with standby attitude indicator to determine faulty system. 2. Autopilot & Yaw Damper...................................................Disengage 3. AHRS NORM (REVERSION panel) ............ Select Operative AHRS 4. Do not re-engage autopilot or yaw damper.
RA RA Located below the attitude sphere on the left side, this illumination indicates a comparator mismatch of the displayed pilot’s & copilot’s radio altitude. 1. Use BARO minimums for approach.
18 19 20 21 22
RA Illuminated & boxed at the bottom of the attitude sphere, this illumination indicates invalid radio altitude. RA minimums & TCAS (if installed) and EGPWS (if installed) are inoperative. The radio altitude function of the gear warning system is inoperative. 1. RAD ALT 1 or 2 (If Installed) Circuit Breaker (pilot’s or copilot’s INSTRUMENTS/INDICATIONS group) ......... Set 2. Refer to GEAR procedure, TAB 29, this checklist. The takeoff & landing CAS inhibit function is disabled.
RA RAFAIL FAIL
23 24 25 26
Located below the VSI display, this annunciation indicates resolution advisory information from the TCAS computer is invalid or not received. This can occur with or without an actual intruder aircraft being present. 1. Attempt to visually acquire possible intruder aircraft.
27
If annunciation persists: 2. RMU (ATC/TCAS)............................................................... TA ONLY
29
RB RB
30
Located above the attitude sphere, this illumination indicates the rudder boost system has disengaged due to a monitor. Do not takeoff. 1. RUD BOOST ..............................................................................OFF 2. Control Wheel Master (MSW)............................. Depress & Release 3. ●If RB extinguishes: a. Yaw Damper ............................................................ As Desired b. This checklist is complete. 3. ●If RB remains illuminated and conditions permit: a. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group).............. Pull & Reset to Regain Autopilot (Procedure Continued) CL-126B October 2004
EFFECTIVITY 45-226 & on, and prior ALL aircraft modified by SB 45-55-6
A-56.8 A-61.1
28
31 32 33 34
b. ■If RB remains illuminated: (1) This checklist is complete. b. ■If RB extinguishes: (1) Yaw Damper ...................................................... As Desired (2) This checklist is complete.
19 20 21 22 23 24
ROL ROL 1. Compare indications with standby attitude indicator to determine faulty system. 2. Autopilot & Yaw Damper .................................................. Disengage 3. AHRS NORM (REVERSION panel)............. Select Operative AHRS 4. Do not re-engage autopilot or yaw damper.
SG X SGx
25
Located to the left of the attitude sphere & accompanied by the ADCX & ATTX annunciators, this illumination indicates both pilot & copilot are displaying the same AHRS, air data, & navigation sources from one IC/SG.
26
TCASFAIL FAIL TCAS
27 28 29
Located below the VSI display, this annunciation indicates that TCAS is failed. 1. TCAS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ........................Pull & Reset 2. Verify correct transponder operation. Select opposite transponder. 3. Select ATC ALT mode on the RMU (ATC/TCAS) until the failed condition is resolved.
30 31 32 33 34 35
A-62.1 A-56.9
EFFECTIVITY 45-226 & on, and prior ALL aircraft modified by SB 45-55-6
CL-126B October 2004
Primary Flight Display (PFD) Annunciations (Cont) TGT TGT Located on the lower left of the heading display, this illumination indicates a weather radar target alert is activated. Take appropriate action to verify the weather radar alert.
WIND WINDSHR SHR Indicates increasing head wind (or decreasing tail wind) and vertical up drafts typically associated with the leading edge of microburst windshears. During takeoff: 1. Thrust Lever(s) ....................Select T/O Detent or APR As Required 2. Takeoff/go-around target pitch attitude should be maintained until safe climb-out is assured. During approach: 1. Add wind and gust allowances to the approach speed. Increase thrust if necessary. 2. Avoid getting low on the approach glide path or letting the thrust levers remain at flight idle for extended periods of time.
WX WX
18 19 20 21 22 23 24 25
Located on the lower left of the heading display, this illumination indicates an invalid weather radar.
26
(flash) YD(flash) YD
27
Illuminates above the attitude sphere for 5 seconds & clears. This illumination indicates the yaw damper has been disengaged by the pilot.
28 29 30 31 32 33 34
CL-126B October 2004
EFFECTIVITY ALL
A-63
Primary Flight Display (PFD) Annunciations (Cont) 19
YD (steady)
20
Located above the attitude sphere, this illumination indicates the yaw damper has failed and is disengaged. Autopilot and rudder boost are inoperative.
21
On the ground:
22 23 24 25 26 27 28 29
1. Control Wheel Master Switch (MSW) .................Depress & Release 2. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)..........................Pull & Reset 3. NOSE STEER Switch .................................................................. ON 4. ●If amber YD extinguishes: a. This checklist is complete. 4. ●If amber YD remains illuminated: a. Do not take off. The yaw damper and rudder boost are inoperative.
In flight: 1. Control Wheel Master Switch (MSW) .................Depress & Release 2. ●If amber YD extinguishes: a. Yaw Damper.................................................................. Engage b. This checklist is complete. 2. ●If amber YD remains illuminated: a. Maintain 33,000 feet or below. b. Airspeed .............................. ≥ 0.65 MI Until Below 33,000 Feet
30
c.
If conditions permit: (1) IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ........... Pull & Reset d. ■If amber YD remains illuminated: (1) Land as soon as practical. (2) This checklist is complete. d. ■If amber YD extinguishes: (1) Yaw Damper ........................................................... Engage (2) This checklist is complete.
31 32 33 34 35
A-64
EFFECTIVITY 45-002 thru 45-225 ALL not modified by SB 45-55-6
CL-126B October 2004
Primary Flight Display (PFD) Annunciations (Cont) TGT TGT
18
Located on the lower left of the heading display, this illumination indicates a weather radar target alert is activated. Take appropriate action to verify the weather radar alert.
19
WIND WINDSHR SHR
20
Indicates increasing head wind (or decreasing tail wind) and vertical up drafts typically associated with the leading edge of microburst windshears.
21
During takeoff: 1. Thrust Lever(s) ....................Select T/O Detent or APR As Required 2. Takeoff/go-around target pitch attitude should be maintained until safe climb-out is assured. During approach: 1. Add wind and gust allowances to the approach speed. Increase thrust if necessary. 2. Avoid getting low on the approach glide path or letting the thrust levers remain at flight idle for extended periods of time.
WX WX Located on the lower left of the heading display, this illumination indicates an invalid weather radar.
22 23 24 25 26 27
(flash) YD(flash) YD Illuminates above the attitude sphere for 5 seconds & clears. This illumination indicates the yaw damper has been disengaged by the pilot.
28 29 30 31 32 33 34
CL-126B October 2004
EFFECTIVITY ALL
A-64.1 A-63
Primary Flight Display (PFD) Annunciations (Cont) 19 20 21 22 23 24 25 26 27 28 29 30 31 32
YD (steady) Located above the attitude sphere, this illumination indicates the yaw damper has failed & is disengaged. Autopilot and rudder boost are inoperative. On the ground: 1. Control Wheel Master Switch (MSW) .................Depress & Release 2. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)..........................Pull & Reset 3. NOSE STEER Switch ................................................................. ON 4. ●If amber YD extinguishes: a. This checklist is complete. 4. ●If amber YD remains illuminated: a. Do not take off. The yaw damper and rudder boost are inoperative. In flight: 1. Control Wheel Master Switch (MSW) .................Depress & Release 2. ●If amber YD extinguishes: a. Yaw Damper............................................................. As Desired b. This checklist is complete. 2. ●If amber YD remains illuminated and conditions permit: a. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) .................. Pull & Reset to Regain Autopilot b. ■If amber YD remains illuminated: (1) This checklist is complete. b. ■If amber YD extinguishes: (1) Yaw Damper ...................................................... As Desired (2) This checklist is complete.
33 34 35
A-65 A-64.1
EFFECTIVITY 45-226 & on, and prior ALL aircraft modified by SB 45-55-6
CL-126B October 2004
Radio Management Unit (RMU) Failure 1. Respective PRI & SEC Circuit Breakers (AVIONICS group [COMMUNICATIONS RMU 1 or 2 PWR])........................................................ Pull & Reset If RMU failure remains: 2. Tune radios using the cross-side RMU’s 1/2 function or through the FMS CDU, or use the Clearance Delivery Radio (Com 1 & Nav 1 only, no DME is available with Clearance Delivery Radio in EMRG).
18 19 20 21
ANTI-SKIDFAIL FAIL ANTI-SKID
22
1. ANTI-SKID ...................................................................OFF, then On 2. Refer to Section V in the AFM for increased stopping distances for anti-skid OFF landing. 3. Cautiously apply brakes as required.
23 24
CPLTBRK BRKFAULT FAULT CPLT
25
1. Use pilot’s brakes.
26
GEAR GEAR
“GEAR”
27
1. ●If the gear is in transit & airspeed is greater than 210 KIAS: a. Slow to below 200 KIAS. b. This checklist is complete. 1. ●If the Radio Altimeter is inoperative, airspeed is less than 170 KIAS, altitude is below 14,500 feet, thrust levers are less than MCR, & the landing gear is not down & locked: a. RAD ALT 1 Circuit Breaker (pilot’s INSTRUMENTS/INDICATIONS group)................................. Set b. Extend gear prior to landing. c. This checklist is complete.
28 29 30 31 32 33 34
CL-126B October 2004
EFFECTIVITY ALL
A-65 A-67
19 20 21 22 23 24 25 26 27
INBDBRK BRKFAIL FAIL LLINBD R INBD BRK FAIL R INBD BRK FAIL LRINBD INBDBRK BRKFAIL FAIL LR 1. ●If failure occurs just after gear extension and conditions permit: a. Gear ......................................................................................UP b. INBD BRAKES Circuit Breaker (pilot’s GEAR/HYDRAULICS group)...................... Set, or Pull & Reset c. AUX HYD ............................................................................. ON d. Gear ......................................................................................DN e. ■If INBD BRK FAIL remains illuminated: (1) Go to step 2. e. ■If INBD BRK FAIL extinguishes: (1) This checklist is complete. 1. ●If failure is not associated with gear extension: a. Go to step 2. 2. Refer to Emergency Braking procedure, TAB 13, Emergency Checklist, or Abnormal Landings, Emergency Brake Landing procedure, TAB 33, this checklist. Emergency brakes should be available on ALL brakes.
NWSFAIL FAIL NWS 28 29 30 31 32 33 34 35
During taxi: 1. Maintain directional control using differential braking. 2. Nose Wheel Steering .................................... Disengage (use MSW) 3. Thrust Levers .............................................................................IDLE 4. Brake to a stop. 5. NOSE STEER .......................................................................... ON Taxi is possible using differential braking & thrust. Avoid sharp turns. If a sharp turn is made, it may not be possible to straighten the nose wheel by differential braking. During takeoff or landing: 1. Maintain directional control using differential braking. 2. Nose Wheel Steering .................................... Disengage (use MSW) In flight: 1. After gear is down, NOSE STEER .............................................. ON If NWS FAIL remains illuminated: a. Maintain directional control using rudder and differential braking on landing. EFFECTIVITY
A-68 A-66
ALL
CL-126B October 2004
OUTBDBRK BRKFAIL FAIL LLOUTBD R OUTBD BRK FAIL R OUTBD BRK FAIL LR OUTBD BRK FAIL LR OUTBD BRK FAIL
18
1. ●If failure occurs just after gear extension and conditions permit: a. Gear ...................................................................................... UP b. OUTBD BRAKES Circuit Breaker (copilot’s GEAR/HYD group) .......................Set, or Pull & Reset c. AUX HYD ..............................................................................ON d. Gear ...................................................................................... DN e. ■If OUTBD BRK FAIL remains illuminated: (1) Go to step 2. e. ■If OUTBD BRK FAIL extinguishes: (1) This checklist is complete. 1. ●If failure is not associated with gear extension: a. Go to step 2. 2. Refer to Emergency Braking procedure, TAB 13, Emergency Checklist, or Abnormal Landings, Emergency Brake Landing procedure, TAB 33, this checklist. Emergency brakes should be available on ALL brakes.
PLTBRK BRKFAULT FAULT PLT
19 20 21 22 23 24 25 26 27
1. Use copilot’s brakes.
28 29 30 31 32 33 34
CL-126B October 2004
EFFECTIVITY ALL
A-67
Landing Gear AUX HYD Extension 19 20 21 22 23 24 25
The landing gear free fall procedure should be used to extend the landing gear in case of electrical or hydraulic problems. Use of landing gear free fall is recommended to reserve hydraulic pressure for flaps and brakes. The AUX HYD pump and HYD XFLOW valve can also operate the landing gear system. If main hydraulic system has failed, do not use the AUX HYD system to retract landing gear, unless a critical performance situation exists. To use AUX HYD system to extend landing gear: 1. Airspeed.................................................... 180 KIAS Recommended 2. GEAR FREEFALL Lever (copilot’s side pedestal) ...........................Check Normal Up Position 3. HYD XFLOW................................................................................ ON 4. AUX HYD ..................................................................................... ON 5. Gear ............................................................................................ DN
26
After gear has extended: 6. HYD XFLOW.................................................................................Off 7. AUX HYD ......................................................................................Off
27
Landing Gear Free Fall
28 29 30 31 32 33 34 35
1. 2. 3. 4.
Airspeed.................................................... 180 KIAS Recommended Gear ............................................................................................ DN AUX HYD ......................................................................................Off ●If Landing Gear Free Fall is conducted because of an electrical problem: a. GEAR Circuit Breaker (pilot’s GEAR/ HYDRAULICS group) ...........................................................Pull b. Go to step 5. 4. ●If Landing Gear Free Fall is conducted because of a hydraulic system problem: a. GEAR Circuit Breaker (pilot’s GEAR/ HYDRAULICS group) ........................................................... Set b. Go to step 5. 5. GEAR FREEFALL Lever (copilot’s side pedestal) ................ Push Full Down & Latch Forward 6. Gear ......................................................Check Three Green DOWN The two white (main gear) in-transit lights may also be illuminated. If any of the three green DOWN lights fail to illuminate: a. ■Refer to Abnormal Landings, Gear Up Landing procedure, TAB 37, this checklist.
(Procedure Continued) EFFECTIVITY
A-68
ALL
CL-126B October 2004 Change 1
Change 1
a. ■If there is no indication of a hydraulic system fluid loss, the Landing Gear AUX HYD Extension procedure, previous page, may be attempted. a. ■If there is indication of a hydraulic system fluid loss, the Landing Gear AUX HYD Extension procedure, previous page, may still be attempted. However, depending on where the hydraulic fluid loss occurred, may result in loss of auxiliary hydraulic fluid. In this case, normal braking may not be available upon landing. Refer to Emergency Braking Procedure, TAB 13, Emergency Checklist.
18 19 20
Stabilizer Heat Failure Landing (STAB TEMP LOW)
21
If approach & landing must be made with any ice (or suspected ice) on the horizontal stabilizer:
22
1. Complete Descent procedure, Normal Checklist. 2. Final Approach Speed .........................VLND8 + 30, Computed & Set Refer to Approach Speeds — Abnormal Landings, this page. 3. Normal Landing Distance ........................................... Multiply by 2.2 4. Approach Setup & Crew Briefing ....................................... Complete 5. ENG SYNC .................................................................................OFF 6. HI FLOW....................................................................................... Off 7. FLAPS .............................................................. 8°, Check Indication 8. SPOILER ................................................................................... ARM 9. AUX HYD ..................................................................................... ON 10. Gear .............................................................................................DN Three Green DOWN 11. L & R LDG/TAXI Lights .............................................On as Required 12. L & R IGN .................................................................................... ON 13. FLAP (EGPWS) ..........................................................................OFF 14. EICAS/SUMRY Page...............................................................Check
Approach Speeds — Abnormal Landings (Gear Down)
23 24 25 26 27 28 29 30
VLNDX (X = FLAPS) — KIAS
31
ALT FEET
WEIGHT LB
UP (0°)
FLAPS 8°
20°
4000 and BELOW
14,000 15,000 16,000 17,000 18,000 19,000 19,200 20,000 21,000 21,500
117 121 125 128 132 135 135 138 140 142
115 119 122 125 129 132 132 134 137 138
110 114 118 121 124 127 127 130 132 133
32 33 34
For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight.
Change 1
CL-126B October 2004 Change 1
EFFECTIVITY ALL
A-69
Wing and Stabilizer Heat Failure Landing (STAB and WING TEMP LOW) 19
If approach and landing must be made with any ice on the wing leading edge and any ice on the horizontal stabilizer:
20
1. Complete Descent procedure, Normal Checklist. 2. Final Approach Speed .........................VLND8 + 30, Computed & Set Refer to Approach Speeds — Abnormal Landings, next page. 3. Normal Landing Distance ...........................................Multiply by 2.2 4. Approach Setup & Crew Briefing ....................................... Complete 5. ENG SYNC ................................................................................ OFF 6. HI FLOW .......................................................................................Off 7. FLAPS ..............................................................8°, Check Indication 8. SPOILER ...................................................................................ARM 9. AUX HYD ..................................................................................... ON 10. Gear ........................................................................................... DN Three Green DOWN 11. L & R LDG/TAXI Lights ............................................ On as Required 12. L & R IGN..................................................................................... ON 13. FLAP (EGPWS) ......................................................................... OFF 14. EICAS/SUMRY Page ...............................................................Check
21 22 23 24 25 26 27 28
Wing Heat Failure Landing (WING TEMP LOW)
29
If approach and landing must be made with any ice (or suspected ice) on the wing leading edge:
30 31 32 33 34 35
Change 1
1. Complete Descent procedure, Normal Checklist. 2. Final Approach Speed .........................VLND8 + 30, Computed & Set Refer to Approach Speeds — Abnormal Landings, next page. 3. Normal Landing Distance ...........................................Multiply by 2.2 4. Approach Setup & Crew Briefing ....................................... Complete 5. ENG SYNC ................................................................................ OFF 6. HI FLOW .......................................................................................Off 7. FLAPS ..............................................................8°, Check Indication 8. SPOILER ...................................................................................ARM 9. AUX HYD ..................................................................................... ON 10. Gear ........................................................................................... DN Three Green DOWN 11. L & R LDG/TAXI Lights ............................................ On as Required 12. L & R IGN..................................................................................... ON 13. FLAP (EGPWS) ......................................................................... OFF 14. EICAS/SUMRY Page ...............................................................Check EFFECTIVITY
A-70
ALL
CL-126B October 2004 Change 1
Approach Speeds — Abnormal Landings (Gear Down) VLNDX (X = FLAPS) — KIAS
18
ALT FEET
WEIGHT LB
UP (0°)
FLAPS 8°
20°
4000 and BELOW
14,000 15,000 16,000 17,000 18,000 19,000 19,200 20,000 21,000 21,500
117 121 125 128 132 135 135 138 140 142
115 119 122 125 129 132 132 134 137 138
110 114 118 121 124 127 127 130 132 133
19 20 21
For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight.
22
Normal Electrical System Failure Landing
23
This procedure would be used for landing with a normal electrical system failure & operation on emergency battery. -
-
Operative equipment associated with landing: Right cabin pressure control; use MANUAL Rate to control. Standby airspeed, altimeter & vibrator, and lighting. Standby attitude. RMU1 Engine Display: N1, N2, OIL °C, and EMER (bus volts). Inboard brakes with anti-skid. Emergency brakes. Inoperative equipment associated with landing: Windshield heat. All external and LDG/TAXI lights. Pitch, aileron and rudder trim. Flaps. Spoilers/spoilerons. Outboard brakes. Thrust Reversers. Nose wheel steering. Stall warning system.
1. MANUAL Rate Control.............Depressurize Cabin Prior to Landing 2. Standby Altimeter ........................................................................ Set 3. Cabin Check ...................................................................... Complete a. Brief passengers of no smoking & seat belt requirements. b. Swivel Seats................ Forward or Aft and in Outboard Position Headrests in Place for Occupied Aft Facing Seats
(Procedure Continued) Change 1
CL-126B October 2004 Change 1
EFFECTIVITY ALL
A-71
24 25 26 27 28 29 30 31 32 33 34
19
4.
20
5. 6. 7.
21 22 23 24 25 26 27 28 29 30 31 32 33 34 35
c. Work Tables and Toilet Doors..............................Check Stowed d. Emergency Exit ....................................................... Aisle Clear Final Approach Speed ......... VLNDX for the Flap Extension Obtained Refer to Approach Speeds — Abnormal Landings, next page. Normal Landing Distance ...........................................Multiply by 2.2 Approach Setup & Crew Briefing ....................................... Complete Gear ........................................................................................... DN Three Green DOWN
After touchdown: 8. EMERGENCY/PARKING BRAKE Handle ...................Pull Smoothly Increasing Extension Increases Brake Pressure
Emergency Brake Landing (NORM BRK FAIL red CAS) (INBD BRK FAIL amber CAS) (OUTBD BRK FAIL amber CAS) This procedure would be used for landing with emergency brake for stopping. All other systems (flaps, spoilers, etc.) are operational. This procedure may be used in association with the following CAS procedures: red NORM BRK FAIL (or NORMAL BRAKES FAIL red CWP), amber INBD BRK FAIL & amber OUTBD BRK FAIL. 1. Complete Descent procedure, Normal Checklist. 2. Final Approach Speed ...................................VREF, Computed & Set 3. Normal Landing Distance ................ Use Anti-Skid OFF Corrections Refer to Section V in the AFM 4. Approach Setup & Crew Briefing ....................................... Complete 5. ENG SYNC ................................................................................ OFF 6. HI FLOW .......................................................................................Off 7. FLAPS .................................................................................8° or 20° 8. SPOILER ...................................................................................ARM 9. AUX HYD ..................................................................................... ON 10. Gear .........................................................DN, Three Green DOWN 11. L & R LDG/TAXI Lights .................................................................On 12. L & R IGN..................................................................................... ON 13. FLAPS ............................................................. DN, Check Indication 14. EICAS/SUMRY Page ...............................................................Check After touchdown: 15. EMERGENCY/PARKING BRAKE Handle ...................Pull Smoothly Increasing Extension Increases Brake Pressure
Change 1
EFFECTIVITY
A-72
ALL
CL-126B October 2004 Change 1
Single-Engine Landing 1. Complete Descent procedure, Normal Checklist. 2. Final Approach Speeds .......................................VLND20 & VAPP, Set Refer to Approach Speeds — Abnormal Landings, this page. 3. Normal Landing Distance ........................................... Multiply by 1.2 4. Approach Setup & Crew Briefing ....................................... Complete 5. ENG SYNC .................................................................................OFF 6. HI FLOW....................................................................................... Off 7. FLAPS ......................................................................................... 20° 8. SPOILER ................................................................................... ARM 9. AUX HYD ..................................................................................... ON 10. Gear ............................................................................................DN Three Green DOWN 11. L & R LDG/TAXI Lights .............................................On as Required 12. Operating Engine IGN ................................................................. ON 13. FLAP (EGPWS) ..........................................................................OFF 14. EICAS/SUMRY Page...............................................................Check
18 19 20 21 22 23 24 25
Approach Speeds — Abnormal Landings (Gear Down) VLNDX (X = FLAPS) — KIAS ALT FEET
WEIGHT LB
4000 and BELOW
14,000 15,000 16,000 17,000 18,000 19,000 19,200 20,000 21,000 21,500
26
UP (0°)
FLAPS 8°
20°
117 121 125 128 132 135 135 138 140 142
115 119 122 125 129 132 132 134 137 138
110 114 118 121 124 127 127 130 132 133
27 28 29 30
For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight.
31
Aileron Jammed Landing (ROLL DISC white CAS) 1. 2. 3. 4.
32
Complete Descent procedure, Normal Checklist. Final Approach Speed ................................... VREF, Computed & Set Normal Landing Distance ................................................. Computed Approach Setup & Crew Briefing ....................................... Complete
(Procedure Continued) CL-126B October 2004 Change 1
EFFECTIVITY ALL
A-73
33 34
19 20 21 22
5. 6. 7. 8. 9. 10.
ENG SYNC ................................................................................ OFF HI FLOW .......................................................................................Off FLAPS .................................................................................8° or 20° SPOILER ...................................................................................ARM AUX HYD ..................................................................................... ON Gear ............................................................................................ DN Three Green DOWN L & R LDG/TAXI Lights .................................................................On L & R IGN..................................................................................... ON FLAPS ............................................................. DN, Check Indication EICAS/SUMRY Page ...............................................................Check
11. 12. 13. 14.
23 24 25 26 27 28
Aileron Trim Tab Jammed Landing 1. 2. 3. 4. 5. 6. 7. 8. 9. 10.
Complete Descent procedure, Normal Checklist. Final Approach Speed ...................................VREF, Computed & Set Normal Landing Distance ................................................. Computed Approach Setup & Crew Briefing ....................................... Complete ENG SYNC ................................................................................ OFF HI FLOW .......................................................................................Off FLAPS .................................................................................8° or 20° SPOILER ...................................................................................ARM AUX HYD ..................................................................................... ON Gear ............................................................................................ DN Three Green DOWN L & R LDG/TAXI Lights .................................................................On L & R IGN..................................................................................... ON FLAPS ............................................................. DN, Check Indication EICAS/SUMRY Page ...............................................................Check
29 30 31
11. 12. 13. 14.
Approach Speeds — Abnormal Landings (Gear Down) VLNDX (X = FLAPS) — KIAS
32
ALT FEET
WEIGHT LB
UP (0°)
FLAPS 8°
20°
4000 and BELOW
14,000 15,000 16,000 17,000 18,000 19,000 19,200 20,000 21,000 21,500
117 121 125 128 132 135 135 138 140 142
115 119 122 125 129 132 132 134 137 138
110 114 118 121 124 127 127 130 132 133
33 34 35
For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight. EFFECTIVITY
A-74
ALL
CL-126B October 2004 Change 1
Elevator Jammed Landing (ELEVATOR DISC white CAS)
18
1. Complete Descent procedure, Normal Checklist. 2. Final Approach Speed ......................... VLND8 + 10, Computed & Set Refer to Approach Speeds — Abnormal Landings, previous page. 3. Normal Landing Distance ........................................... Multiply by 1.6 4. Approach Setup & Crew Briefing ....................................... Complete 5. ENG SYNC .................................................................................OFF 6. HI FLOW....................................................................................... Off 7. FLAPS ............................................................... 8°, Check Indication 8. SPOILER ................................................................................... ARM 9. AUX HYD ..................................................................................... ON 10. Gear .............................................................................................DN Three Green DOWN 11. L & R LDG/TAXI Lights ................................................................. On 12. L & R IGN .................................................................................... ON 13. FLAP (EGPWS) ..........................................................................OFF 14. EICAS/SUMRY Page...............................................................Check
21 22 23 24 25
27
1. Complete Descent procedure, Normal Checklist. 2. Final Approach Speed ......... VLNDX for the Flap Deflection Obtained Refer to Approach Speeds — Abnormal Landings, previous page. Use the lesser flap deflection VLNDX speed for flap settings between the detent values. 3. Normal Landing Distance ........................................... Multiply by 1.3 4. Approach Setup & Crew Briefing ....................................... Complete 5. ENG SYNC .................................................................................OFF 6. HI FLOW....................................................................................... Off 7. FLAPS ........................................................................... As Obtained 8. SPOILER ................................................................................... ARM 9. AUX HYD ..................................................................................... ON 10. Gear .............................................................................................DN Three Green DOWN 11. L & R LDG/TAXI Lights ................................................................. On 12. L & R IGN .................................................................................... ON 13. FLAP (EGPWS) ..........................................................................OFF 14. EICAS/SUMRY Page...............................................................Check CL-126B October 2004 Change 1
20
26
Partial Flap Landing (FLAPS FAIL)
Change 1
19
EFFECTIVITY ALL
A-75
28 29 30 31 32 33 34
Rudder Jammed Landing 19 20 21 22 23 24 25 26 27 28 29 30 31
1. 2. 3. 4. 5. 6. 7. 8. 9. 10.
Complete Descent procedure, Normal Checklist. Final Approach Speed ...................................VREF, Computed & Set Normal Landing Distance ................................................. Computed Approach Setup & Crew Briefing ....................................... Complete ENG SYNC ................................................................................ OFF HI FLOW .......................................................................................Off FLAPS .................................................................................8° or 20° SPOILER ...................................................................................ARM AUX HYD ..................................................................................... ON Gear ............................................................................................ DN Three Green DOWN NOSE STEER....................................................................Check Off L & R LDG/TAXI Lights .................................................................On L & R IGN..................................................................................... ON FLAPS ............................................................. DN, Check Indication EICAS/SUMRY Page ...............................................................Check Carry power down to touchdown to aid in directional control. Yaw Damper..................................................................................Off
11. 12. 13. 14. 15. 16. 17.
After landing: 18. Maintain directional control with differential braking.
Approach Speeds — Abnormal Landings (Gear Down) VLNDX (X = FLAPS) — KIAS ALT FEET
WEIGHT LB
UP (0°)
FLAPS 8°
20°
4000 and BELOW
14,000 15,000 16,000 17,000 18,000 19,000 19,200 20,000 21,000 21,500
117 121 125 128 132 135 135 138 140 142
115 119 122 125 129 132 132 134 137 138
110 114 118 121 124 127 127 130 132 133
32 33
For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight.
34 35
EFFECTIVITY
A-76
ALL
CL-126B October 2004
Rudder Trim Tab Jammed Landing 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15.
Complete Descent procedure, Normal Checklist. Final Approach Speed ................................... VREF, Computed & Set Normal Landing Distance ................................................. Computed Approach Setup & Crew Briefing ....................................... Complete ENG SYNC .................................................................................OFF HI FLOW....................................................................................... Off FLAPS .................................................................................8° or 20° SPOILER ................................................................................... ARM AUX HYD ..................................................................................... ON Gear .............................................................................................DN Three Green DOWN L & R LDG/TAXI Lights ................................................................. On L & R IGN .................................................................................... ON FLAPS ............................................................. DN, Check Indication EICAS/SUMRY Page...............................................................Check Yaw Damper ................................................................................. Off
35 36 37 38 39 40 41 42 43
Spoilers Extended Landing (SPOILER EXT or SPOILER FAIL)
44
1. Complete Descent procedure, Normal Checklist. 2. SPOILER ....................................................................................RET 3. Final Approach Speed ........................... VLND8 + 5, Computed & Set Refer to Approach Speeds — Abnormal Landings, previous page. 4. Normal Landing Distance ........................................... Multiply by 1.6 5. Approach Setup & Crew Briefing ....................................... Complete 6. ENG SYNC .................................................................................OFF 7. HI FLOW....................................................................................... Off 8. FLAPS ............................................................... 8°, Check Indication 9. AUX HYD ..................................................................................... ON 10. Gear .............................................................................................DN Three Green DOWN 11. L & R LDG/TAXI Lights ................................................................. On 12. L & R IGN .................................................................................... ON 13. FLAP (EGPWS) ..........................................................................OFF 14. EICAS/SUMRY Page...............................................................Check
Change 1
CL-126B October 2004 Change 1
EFFECTIVITY ALL
A-77
45 46 47 48 49 50 51
36 37 38 39 40 41 42 43 44
Spoiler Jammed Landing (L SPOILER JAM) (R SPOILER JAM) 1. Complete Descent procedure, Normal Checklist. 2. SPOILER ................................ Deploy, as Required to Minimize Roll 3. Final Approach Speed ...........................VLND8 + 5, Computed & Set Refer to Approach Speeds — Abnormal Landings, this page. 4. Normal Landing Distance ...........................................Multiply by 1.6 5. Approach Setup & Crew Briefing ....................................... Complete 6. ENG SYNC ................................................................................ OFF 7. HI FLOW .......................................................................................Off 8. FLAPS ...............................................................8°, Check Indication 9. AUX HYD ..................................................................................... ON 10. Gear ............................................................................................ DN Three Green DOWN 11. L & R LDG/TAXI Lights .................................................................On 12. L & R IGN..................................................................................... ON 13. FLAP (EGPWS) ......................................................................... OFF 14. EICAS/SUMRY Page ...............................................................Check
Approach Speeds — Abnormal Landings (Gear Down) VLNDX (X = FLAPS) — KIAS
45
ALT FEET
WEIGHT LB
UP (0°)
FLAPS 8°
20°
4000 and BELOW
14,000 15,000 16,000 17,000 18,000 19,000 19,200 20,000 21,000 21,500
117 121 125 128 132 135 135 138 140 142
115 119 122 125 129 132 132 134 137 138
110 114 118 121 124 127 127 130 132 133
46 47 48 49
For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight.
50
Stabilizer Jammed Landing
51 52
If elevator pull force is encountered — Stabilizer jammed in nose-down trim position (aircraft in climb, cruise, or descent configuration): 1. Complete Jammed Stabilizer (PRI TRIM FAIL & SEC TRIM FAIL) procedure, TAB 16, this checklist. 2. Complete Descent procedure, Normal Checklist.
(Procedure Continued) EFFECTIVITY ALL
A-78
CL-126B October 2004
3. Final Approach Speed ................................. VLND0, Computed & Set Refer to Approach Speeds — Abnormal Landings, previous page. 4. Normal Landing Distance ........................................... Multiply by 1.3 5. Approach Setup & Crew Briefing ....................................... Complete 6. ENG SYNC .................................................................................OFF 7. HI FLOW....................................................................................... Off 8. FLAPS .......................................................UP (0°), Check Indication 9. SPOILER ................................................................................... ARM 10. AUX HYD ..................................................................................... ON 11. Gear .............................................................................................DN Three Green DOWN 12. L & R LDG/TAXI Lights ................................................................. On 13. L & R IGN .................................................................................... ON 14. FLAP (EGPWS) ..........................................................................OFF 15. EICAS/SUMRY Page...............................................................Check If elevator push force is encountered — Stabilizer jammed in nose-up trim position (aircraft in takeoff or landing configuration): 1. Move C.G. forward if possible. Conduct normal landing. 2. Complete Descent procedure, Normal Checklist. 3. Complete Approach procedure, Normal Checklist. 4. Complete Before Landing procedure, Normal Checklist.
Main Hydraulic System Failure Landing (MAIN HYD PRESS)
36 37 38 39 40 41 42 43 44
1. Complete Descent procedure, Normal Checklist. 2. Complete Landing Gear Free Fall procedure, TAB 31, this checklist.
45
If AUX HYD is available: a. AUX HYD ............................ ON (to Charge B-ACUM Pressure) b. HYD XFLOW.........................................................................ON c. FLAPS...................................................... 20°, Check Indication (Do not extend beyond 20°)
46
When flaps reach their maximum extension: d. HYD XFLOW......................................................................... Off e. AUX HYD .............................................................................. Off 3. Final Approach Speed ..........VLNDX for the Flap Extension Obtained Refer to Approach Speeds — Abnormal Landings, previous page. 4. Normal Landing Distances: a. ●If emergency braking is used: (1) Multiply by 2.2 (2) Go to step 5.
48
(Procedure Continued) Change 1
35
CL-126B October 2004 Change 1
EFFECTIVITY ALL
A-79
47
49 50 51
36 37
5. 6. 7. 8.
38 39 40 41 42 43 44 45 46
9. 10. 11. 12.
a. ●If normal braking is used with AUX HYD pressure available: (1) Multiply by 1.4 (2) Go to step 5. Approach Setup & Crew Briefing ....................................... Complete ENG SYNC ................................................................................ OFF HI FLOW .......................................................................................Off Gear ......................................................Check Three Green DOWN The two white (main gear) in-transit lights may also be illuminated. L & R LDG/TAXI Lights .................................................................On L & R IGN..................................................................................... ON FLAP (EGPWS) ......................................................................... OFF EICAS/SUMRY Page ...............................................................Check
Prior to touchdown: 13. AUX HYD ..................................................................................... ON After touchdown: 14. ●If AUX HYD pressure is available, normal anti-skid braking should be available from the auxiliary pump. Be prepared to use EMERGENCY BRAKING. This checklist is complete. 14. ●If AUX HYD pressure is not available, use EMERGENCY BRAKING. a. EMERGENCY/PARKING BRAKE Handle............ Pull Smoothly Increasing Extension Increases Brake Pressure b. Rudder and/or Nose Wheel Steering .............................. As Required for Directional Control c. This checklist is complete.
47 48 49 50 51 52 EFFECTIVITY
Change 1
ALL
A-80
CL-126B October 2004 Change 1
Gear Up Landing 1. Brief passengers as required. a. Location & operation of emergency exits. b. Secure all loose items. c. Shoulder Harness & Seat Belts.......................................Secure d. Emergency landing brace position. 2. Complete Descent procedure, Normal Checklist. 3. PACK ..........................................................................................OFF 4. FLAPS ..........................................................................................DN 5. Perform normal power-on approach at VREF & touch down at the lowest possible airspeed with minimum sink rate. Do not decelerate below shaker speed. 6. ●If no landing gear has extended: a. Plan to land slightly nose high. b. Go to step 7. 6. ●If the nose gear fails to extend: a. Relocate passengers aft to obtain aft C.G., if possible. b. SPOILER............................................................................ ARM c. AUX HYD ..............................................................................ON d. EICAS/SUMRY Page ....................................................... Check e. Hold the nose off the runway as long as elevator control is available. f. ■If hydraulic pressure is not available: (1) Use EMERGENCY/PARKING BRAKE. (2) Go to step 7. f. ■If hydraulic pressure is available: (1) Normal braking may be used & spoilers deployed. Use rudder and/or brakes for directional control. Be prepared to use EMERGENCY/PARKING BRAKE. (2) Go to step 7. 6. ●If a main gear fails to extend: a. Plan to land on the same side of the runway as the extended gear. b. ANTI-SKID .......................................................................... OFF Heavy brake pressures may skid the tires & cause tire blowout. c. NOSE STEER ............................................. Check ON to Assist in Maintaining Directional Control d. AUX HYD ..............................................................................ON e. EICAS/SUMRY Page ....................................................... Check
(Procedure Continued) CL-126B October 2004
EFFECTIVITY ALL
A-81
35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51
f. Hold the applicable wing up as long as possible. Maintain directional control with rudder & nose wheel steering. g. ■If hydraulic pressure is not available: (1) Use EMERGENCY/PARKING BRAKE. (2) Go to step 7. g. ■If hydraulic pressure is available: (1) Normal braking may be used & spoilers deployed. Use rudder and/or brakes for directional control. Be prepared to use EMERGENCY/PARKING BRAKE. (2) Go to step 7.
36 37 38 39 40 41 42 43
At touchdown: 7. Thrust Levers ...................................................................... CUTOFF 8. FIRE (L & R ENGINE).................................................... FIRE PUSH After aircraft stops: 9. EMER LIGHTS............................................................................. ON 10. EMER BATT, L & R BATT .......................................................... OFF 11. Evacuate the aircraft: a. Cabin Entry Door.....................................................Open & Exit b. Aft Emergency Exit..................................................Open & Exit
44 45 46 47 48 49 50 51 52 EFFECTIVITY ALL
A-82
CL-126B October 2004
Thrust Reverser Deployed Landing 1. Complete Descent procedure, Normal Checklist. 2. Final Approach Speed ......................... VLND8 + 10, Computed & Set Refer to Approach Speeds — Abnormal Landings, this page. 3. Normal Landing Distance ........................................... Multiply by 1.6 4. Approach Setup & Crew Briefing ....................................... Complete 5. ENG SYNC .................................................................................OFF 6. HI FLOW....................................................................................... Off 7. FLAPS ..............................................................8°, Check Indication 8. SPOILER ................................................................................... ARM 9. AUX HYD..................................................................................... ON 10. Gear .............................................................................................DN Three Green DOWN 11. L & R LDG/TAXI Lights ................................................................. On 12. Operating Engine IGN ................................................................. ON 13. FLAP (EGPWS) ..........................................................................OFF 14. EICAS/SUMRY Page...............................................................Check 15. Yaw Damper ................................................................................. Off
Approach Speeds — Abnormal Landings (Gear Down)
35 36 37 38 39 40 41 42 43
VLNDX (X = FLAPS) — KIAS ALT FEET
WEIGHT LB
UP (0°)
FLAPS 8°
20°
4000 and BELOW
14,000 15,000 16,000 17,000 18,000 19,000 19,200 20,000 21,000 21,500
117 121 125 128 132 135 135 138 140 142
115 119 122 125 129 132 132 134 137 138
110 114 118 121 124 127 127 130 132 133
44 45 46 47
For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight.
48 49 50 51
CL-126B October 2004
EFFECTIVITY ALL
A-83
Advisory/Status EICAS Index Page
AHRS 1 BASIC AHRS 2 BASIC AHRS 1-2 BASIC AP ELEV MISTRIM
A/S-18 A/S-18 A/S-18 A/S-8
APR (EI) APR (EI outbd N1s) L APR FAULT R APR FAULT LR APR FAULT APR ON (EI inbd N1s) APU AVAILABLE AUTOSPLR ARMED BRAKE FAULT BUS TIE CLSD BUS TIE MANUAL L CAB PRESS FAIL R CAB PRESS FAIL CAB PRESS MAN L CHECK EDS R CHECK EDS LR CHECK EDS CKLST MISMATCH CVR FAIL DAU A REV DAU B REV DEP (EI) DU 1 FAN FAIL DU 2 FAN FAIL DU 1-2 FAN FAIL DU 3 FAN FAIL DU 4 FAN FAIL DU 3-4 FAN FAIL L ECS FAULT R ECS FAULT ELEVATOR DISC EMER DEPRESS
CL-126B October 2004
CAS or (EI) Message
Page
L R
EMER LIGHTS EMER/PARK BRK ENG FIRE FAIL ENG FIRE FAIL
A/S-24 A/S-24 A/S-9 A/S-9
A/S-12 A/S-12 A/S-9 A/S-9 A/S-9 A/S-12
LR L R LR L R
ENG FIRE FAIL ENG SHUTDOWN ENG SHUTDOWN ENG SHUTDOWN ENG VIB MON ENG VIB MON
A/S-9 A/S-10 A/S-10 A/S-10 A/S-10 A/S-10
A/S-8 A/S-13 A/S-24 A/S-9 A/S-9 A/S-13 A/S-13 A/S-13 A/S-25 A/S-25 A/S-25 A/S-18 A/S-24 A/S-18 A/S-18 A/S-12 A/S-18 A/S-18 A/S-18 A/S-19 A/S-19 A/S-19 A/S-13 A/S-13 A/S-14 A/S-13
LR L R LR L R LR
ENG VIB MON ENGCMPTR FAULT ENGCMPTR FAULT ENGCMPTR FAULT ENGINE CHIP ENGINE CHIP ENGINE CHIP ENTRY DOOR PIN ESS BUS FAULT ESS BUS FAULT ESS BUS FAULT EXTERNAL POWER FDR FAIL FUEL BAY LOW FUEL BAY LOW FUEL BAY LOW FUEL FILTER FUEL FILTER FUEL FILTER FUEL HEATER FUEL HEATER FUEL HEATER FUEL QTY FAULT FUEL QTY FAULT FUEL QTY FAULT FUEL XFLO OPEN
A/S-10 A/S-10 A/S-10 A/S-10 A/S-11 A/S-11 A/S-11 A/S-8 A/S-9 A/S-9 A/S-9 A/S-9 A/S-24 A/S-16 A/S-16 A/S-16 A/S-16 A/S-16 A/S-16 A/S-16 A/S-16 A/S-16 A/S-16 A/S-16 A/S-16 A/S-16
L R LR
L R LR L R LR L R LR L R
EFFECTIVITY ALL
Advisory/ Status-i
ADVISORY/STATUS
CAS or (EI) Message
Advisory/Status EICAS Index (Cont) CAS or (EI) Message L FWSOV CLSD R FWSOV CLSD LR FWSOV CLSD GND PROX FAIL
ADVISORY/STATUS
L R
GPWS FAIL GPWS FLAP OVRD GPWS G/S INHIB GPWS SYS FAIL HYD PUMP LOW HYD PUMP LOW
LR HYD PUMP LOW HYD XFLOW ON IC 1 CNFG FAIL IC 2 CNFG FAIL IC 1 FAN FAIL IC 2 FAN FAIL IC 1-2 FAN FAIL IC 1 WOW INOP IC 2 WOW INOP IC 1-2 WOW INOP ICE DETECTED IGN (EI) IGN (EI) INSTR PNL TEMP LBS/KGS CONFIG MACH TRIM FAIL MAIN HYDQTY LO MAN (EI) MCR (EI) MCT (EI) NAC (EI) NOSE BAY TEMP NWS FAULT L OIL FILTER R OIL FILTER LR OIL FILTER PACK HIGH FLOW
Advisory/ Status-ii
Page
CAS or (EI) Message
A/S-17 A/S-17 A/S-17 A/S-20
PAX OXY DEPLOY PIT TRIM BIAS PIT TRIM MSCMP PITCH TRIM OFF
Page A/S-13 A/S-14 A/S-14 A/S-14
A/S-20 A/S-20 A/S-20 A/S-20 A/S-17 A/S-17
PRI TRIM FAULT REV (EI) L REV AUTOSTOW R REV AUTOSTOW LR REV AUTOSTOW L REV FAULT
A/S-14 A/S-12 A/S-25 A/S-25 A/S-25 A/S-25
A/S-17 A/S-17 A/S-20 A/S-20 A/S-20 A/S-20 A/S-20 A/S-21 A/S-21 A/S-21 A/S-7 A/S-12 A/S-12 A/S-21 A/S-21 A/S-8 A/S-17 A/S-12 A/S-12 A/S-12 A/S-12 A/S-21 A/S-24 A/S-11 A/S-11 A/S-11 A/S-13
R REV FAULT LR REV FAULT ROLL DISC RUD BOOST INOP SEC PITCH TRIM SEC TRIM FAULT SPOILERS EXT STAB TMP FAULT START (EI) L STBY PUMP ON R STBY PUMP ON LR STBY PUMP ON SYNC (EI) T/O (EI) TAKEOFF TRIM TERR FAIL TERR INHIB WARN AUDIO L WARN PWR FAIL R WARN PWR FAIL WG/STAB HT OK WHEEL MSTR WINDSHEAR FAIL WING TMP FAULT L WSHLD HT FAULT R WSHLD HT FAULT LR WSHLD HT FAULT
A/S-25 A/S-25 A/S-14 A/S-8 A/S-14 A/S-15 A/S-15 A/S-7 A/S-12 A/S-17 A/S-17 A/S-17 A/S-12 A/S-12 A/S-15 A/S-21 A/S-22 A/S-26 A/S-26 A/S-26 A/S-7 A/S-15 A/S-22 A/S-7 A/S-7 A/S-7 A/S-7
EFFECTIVITY ALL
CL-126B October 2004
ADVISORY/STATUS ANNUNCIATIONS All of the following CAS & EI illuminations are white unless otherwise indicated. ANTI-ICING ................................................................................... A/S-7 ICE DETECTED ......................................................................... A/S-7 L WSHLD HT FAULT R WSHLD HT FAULT LR WSHLD HT FAULT ............................................................... A/S-7 STAB TMP FAULT...................................................................... A/S-7 WG/STAB HT OK ....................................................................... A/S-7 WING TMP FAULT ..................................................................... A/S-7 AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS).................... A/S-8 AP ELEV MISTRIM .................................................................... A/S-8 MACH TRIM FAIL ...................................................................... A/S-8 RUD BOOST INOP .................................................................... A/S-8 AUXILIARY POWER UNIT (APU) ............................................... A/S-8 APU AVAILABLE ........................................................................ A/S-8 DOOR............................................................................................ A/S-8 ENTRY DOOR PIN .................................................................... A/S-8 ELECTRICAL................................................................................ A/S-9 BUS TIE CLSD........................................................................... A/S-9 BUS TIE MANUAL ..................................................................... A/S-9 L ESS BUS FAULT R ESS BUS FAULT LR ESS BUS FAULT .................................................................. A/S-9 EXTERNAL POWER.................................................................. A/S-9 ENGINE......................................................................................... A/S-9 L APR FAULT R APR FAULT LR APR FAULT .......................................................................... A/S-9 CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-1
ENGINE (Cont) L ENG FIRE FAIL R ENG FIRE FAIL LR ENG FIRE FAIL .................................................................... A/S-9 L ENG SHUTDOWN R ENG SHUTDOWN LR ENG SHUTDOWN ................................................................ A/S-10 L ENG VIB MON R ENG VIB MON LR ENG VIB MON ...................................................................... A/S-10 L ENGCMPTR FAULT R ENGCMPTR FAULT LR ENGCMPTR FAULT ............................................................. A/S-10 L ENGINE CHIP R ENGINE CHIP LR ENGINE CHIP ...................................................................... A/S-11 L OIL FILTER R OIL FILTER LR OIL FILTER ........................................................................... A/S-11 EIs (Green).................................................................................... A/S-12 APR ............................................................................................A/S-12 MCR ........................................................................................... A/S-12 MCT............................................................................................A/S-12 T/O ............................................................................................. A/S-12 EIs (Green/White)......................................................................... A/S-12 APR ON...................................................................................... A/S-12 APR ............................................................................................A/S-12 DEP ............................................................................................A/S-12 IGN ............................................................................................. A/S-12 MAN ........................................................................................... A/S-12 NAC ............................................................................................A/S-12 REV ............................................................................................A/S-12 START ........................................................................................ A/S-12 SYNC ......................................................................................... A/S-12
Advisory/ Status-2
EFFECTIVITY ALL
CL-126B October 2004
ENVIRONMENTAL/PRESSURIZATION L CAB PRESS FAIL R CAB PRESS FAIL................................................................... A/S-13 CAB PRESS MAN...................................................................... A/S-13 L ECS FAULT R ECS FAULT ............................................................................ A/S-13 EMER DEPRESS....................................................................... A/S-13 PACK HIGH FLOW .................................................................... A/S-13 PAX OXY DEPLOY .................................................................... A/S-13 FLIGHT CONTROLS .................................................................... A/S-13 AUTOSPLR ARMED .................................................................. A/S-13 ELEVATOR DISC ....................................................................... A/S-14 PIT TRIM BIAS........................................................................... A/S-14 PIT TRIM MSCMP ..................................................................... A/S-14 PITCH TRIM OFF ...................................................................... A/S-14 PRI TRIM FAULT........................................................................ A/S-14 ROLL DISC ................................................................................ A/S-14 SEC PITCH TRIM ...................................................................... A/S-14 SEC TRIM FAULT ...................................................................... A/S-15 SPOILERS EXT ......................................................................... A/S-15 TAKEOFF TRIM ......................................................................... A/S-15 WHEEL MSTR ........................................................................... A/S-15 FUEL ............................................................................................. A/S-16 L FUEL BAY LOW R FUEL BAY LOW LR FUEL BAY LOW ................................................................... A/S-16 FUEL XFLO OPEN .................................................................... A/S-16 L FUEL FILTER R FUEL FILTER LR FUEL FILTER ....................................................................... A/S-16 L FUEL HEATER R FUEL HEATER LR FUEL HEATER ..................................................................... A/S-16
CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-3
FUEL (Cont) L FUEL QTY FAULT R FUEL QTY FAULT ..................................................................A/S-16 FUEL QTY FAULT ...................................................................... A/S-16 L FWSOV CLSD R FWSOV CLSD LR FWSOV CLSD ...................................................................... A/S-17 L STBY PUMP ON R STBY PUMP ON LR STBY PUMP ON................................................................... A/S-17 HYDRAULICS ...............................................................................A/S-17 HYD XFLOW ON........................................................................A/S-17 L HYD PUMP LOW R HYD PUMP LOW LR HYD PUMP LOW..................................................................A/S-17 MAIN HYDQTY LO..................................................................... A/S-17 INSTRUMENT/AVIONICS ............................................................. A/S-18 AHRS 1 BASIC AHRS 2 BASIC AHRS 1-2 BASIC ....................................................................... A/S-18 CKLST MISMATCH .................................................................... A/S-18 DAU A REV DAU B REV ................................................................................ A/S-18 DU 1 FAN FAIL DU 2 FAN FAIL DU 1-2 FAN FAIL........................................................................A/S-18 DU 3 FAN FAIL DU 4 FAN FAIL DU 3-4 FAN FAIL........................................................................A/S-19 GND PROX FAIL ........................................................................A/S-20 GPWS FLAP OVRD ................................................................... A/S-20 GPWS G/S INHB........................................................................A/S-20 GPWS FAIL OR GPWS SYS FAIL ........................................................................A/S-20 IC 1 CNFG FAIL IC 2 CNFG FAIL ......................................................................... A/S-20
Advisory/ Status-4
EFFECTIVITY ALL
CL-126B October 2004
INSTRUMENT/AVIONICS (Cont) IC 1 FAN FAIL IC 2 FAN FAIL IC 1-2 FAN FAIL ......................................................................... A/S-20 IC 1 WOW INOP IC 2 WOW INOP IC 1-2 WOW INOP ..................................................................... A/S-21 INSTR PNL TEMP ..................................................................... A/S-21 LBS/KGS CONFIG..................................................................... A/S-21 NOSE BAY TEMP ...................................................................... A/S-21 TERR FAIL ................................................................................. A/S-21 TERR INHB OR TERR INHIB............................................................................... A/S-22 WINDSHEAR FAIL..................................................................... A/S-22 Multi-Function Display (MFD) .................................................... A/S-22 ABV ............................................................................................ A/S-22 BLW............................................................................................ A/S-22 DGx ............................................................................................ A/S-22 FL ............................................................................................... A/S-22 TA ONLY .................................................................................... A/S-22 TCAS.......................................................................................... A/S-22 TCAS FAILURES ....................................................................... A/S-23 TCAS OFF ................................................................................. A/S-23 TCAS TEST ............................................................................... A/S-23 TERR ......................................................................................... A/S-23 TERR INHIB ............................................................................... A/S-23 Primary Flight Display (PFD) Annunciations ............................. A/S-23 DGx ............................................................................................ A/S-23 TA ONLY .................................................................................... A/S-23 TCAS INOP................................................................................ A/S-23 TCAS OFF ................................................................................. A/S-23 TCAS TEST ............................................................................... A/S-23 CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-5
LANDING GEAR/BRAKES ...........................................................A/S-24 BRAKE FAULT ........................................................................... A/S-24 EMER/PARK BRK ...................................................................... A/S-24 NWS FAULT ...............................................................................A/S-24 MISCELLANEOUS........................................................................A/S-24 CVR FAIL ................................................................................... A/S-24 EMER LIGHTS ........................................................................... A/S-24 FDR FAIL (if installed) ................................................................ A/S-24 L CHECK EDS R CHECK EDS LR CHECK EDS ......................................................................... A/S-25 THRUST REVERSER ................................................................... A/S-25 L REV AUTOSTOW R REV AUTOSTOW LR REV AUTOSTOW................................................................. A/S-25 L REV FAULT R REV FAULT LR REV FAULT........................................................................... A/S-25
WARN ........................................................................................ A/S-26 L WARN PWR FAIL R WARN PWR FAIL ................................................................... A/S-26 WARN AUDIO ............................................................................ A/S-26
Advisory/ Status-6
EFFECTIVITY ALL
CL-126B October 2004
ANTI-ICING
ICE DETECTED ICE DETECTED Ice is being detected with the WING/STAB & L & R NAC heat anti-ice systems selected ON.
WSHLDHT HTFAULT FAULT LLWSHLD R WSHLD HT FAULT R WSHLD HT FAULT LR WSHLD HT FAULT LR WSHLD HT FAULT The temperature modulating function of the windshield system is operating in a degraded mode. The system will automatically operate in a full on/off mode. The system will provide effective anti-icing.
STABTMP TMPFAULT FAULT STAB One of the two horizontal stabilizer temperature sensors has failed. The stabilizer anti-ice system should function normally using the opposite stabilizer sensor.
WG/STABHT HTOK OK WG/STAB The wing & horizontal stabilizer anti-ice controller & sensors have been properly tested with pilot activation of the SYS TEST/RESET switch.
WINGTMP TMPFAULT FAULT WING One or more of the four wing temperature sensors have failed. The wing anti-ice system should function normally using the opposite wing sensor.
CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-7
AUTOMATIC FLIGHT CON- AP ELEV MISTRIM AP ELEV MISTRIM TROL SYSTEM The autopilot pitch servo is holding excessive torque & the pitch trim system is not operating normally. If the autopilot is to be disengaged with this CAS illuminated: 1. Flight Controls................................................................Hold Firmly 2. Autopilot .................. Use Control Wheel Trim Switch to Disengage 3. Retrim aircraft if necessary. 4. Autopilot .......................................................... Engage As Desired
MACHTRIM TRIMFAIL FAIL MACH The Mach trim function is disabled & the Mach number is less than 0.76 MI. 1. PITCH TRIM ............................................................................. PRI 2. PRI PITCH Circuit Breaker (pilot’s FLIGHT group [TRIM]) ....... Set If autopilot disengagement is desired: 3. Airspeed ............................................Mach Trim Off MMO or Below 4. Autopilot ......................................................................... Disengage Engage yaw damper as required.
RUDBOOST BOOSTINOP INOP RUD Rudder boost is selected OFF. Do not takeoff. APU
APU AVAILABLE
The auxiliary power unit is operating and is available for bleed air and electrical power.
DOOR
ENTRYDOOR DOORPIN PIN ENTRY There is a disagreement between one or more entry door pins with the door open. This CAS will only appear while the aircraft is on the ground & will also be accompanied by an ENTRY DOOR red CAS & CWP.
Advisory/ Status-8
EFFECTIVITY ALL
CL-126B October 2004
LECTRICAL
BUSTIE TIECLSD CLSD BUS BUS TIE switch is closed (either automatically or manually). The BUS TIE switch will illuminate with a white bar.
BUSTIE TIEMANUAL MANUAL BUS Pilot has manually selected the MAN position of the BUS TIE switch. The bus tie position changes & prevents automatic operation of the bus tie. MAN & a white bar (if generator buses are tied) on the switch will illuminate. Pressing the BUS TIE switch a second time restores automatic control; MAN on the switch & BUS TIE MANUAL white CAS will extinguish.
ESSBUS BUSFAULT FAULT LLESS R ESS BUS FAULT R ESS BUS FAULT LR ESS BUS FAULT LR ESS BUS FAULT The respective essential bus contactor has failed open in flight.
EXTERNALPOWER POWER EXTERNAL The external power source is connected to the aircraft (regardless of whether it is powering the aircraft). The external power source is powered if the EXT PWR switch on the ELEC ENGINE panel has a green AVAIL illuminated.
APRFAULT FAULT LLAPR APRFAULT FAULT RRAPR LR APR FAULT LR APR FAULT The respective DEEC has detected a fault within the APR function of the computer. Refer to APR OFF performance data, Section V in the AFM.
ENGFIRE FIREFAIL FAIL LLENG ENGFIRE FIREFAIL FAIL RRENG LR ENG FIRE FAIL LR ENG FIRE FAIL The engine fire detection system has detected a fault during flight that may not allow the detection system to indicate a fire. CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-9
ENGSHUTDOWN SHUTDOWN LLENG R ENG SHUTDOWN R ENG SHUTDOWN LR ENG SHUTDOWN LR ENG SHUTDOWN This collector message indicates the engine is shutdown with the thrust lever at CUTOFF. The respective OIL PRESS LOW (red), FUEL PRESS LOW (red), GEN FAIL (amber), & HYD PUMP LO (white) CAS are inhibited. When the thrust lever is moved out of CUTOFF, the inhibited CAS will flash & may be reset with the Master WARN/CAUT switches.
LR ENG SHUTDOWN LR GEN FAIL (red) CAS will be inhibited on the ground & will illuminate in flight.
ENGVIB VIBMON MON LLENG R ENG VIB MON R ENG VIB MON LR ENG VIB MON LR ENG VIB MON A higher than normal level of vibration has been sensed in the respective engine. 1. Engine Instruments ...................... Monitor for Abnormal Indications If ENG VIB MON remains illuminated for more than 30 seconds and if conditions permit: 2. Respective Thrust Lever ........................................................Adjust 3. Refer problem to maintenance personnel for correction after landing.
ENGCMPTRFAULT FAULT LLENGCMPTR R ENGCMPTR FAULT R ENGCMPTR FAULT LR ENGCMPTR FAULT LR ENGCMPTR FAULT The respective DEEC has detected a minor malfunction on the ground. The engine computer retains engine control & operation is not affected. This procedure may be used prior to takeoff to clear the fault. 1. Respective Thrust Lever ..........................................................IDLE 2. Respective ENG CMPTR...........................................OFF, then ON
Advisory/ Status-10
EFFECTIVITY ALL
CL-126B October 2004
ENGINECHIP CHIP LLENGINE R ENGINE CHIP R ENGINE CHIP LR ENGINE CHIP LR ENGINE CHIP Metal particles have been detected in the oil during flight.
OILFILTER FILTER LLOIL R OIL FILTER R OIL FILTER LR OIL FILTER LR OIL FILTER The engine oil filter has an impending bypass during flight. 1. Monitor oil pressure & temperature.
CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-11
ENGINE INDICATIONS (EIS) The following illuminations appear in the EI displays outboard of the N1 digital display of the EICAS. EIs (Green)
EIs (Green/ White)
APR
The associated thrust lever is in the Automatic Performance Reserve (APR) detent.
MCR
The associated thrust lever is in the Maximum Cruise (MCR) detent.
MCT
The associated thrust lever is in the Maximum Continuous Thrust (MCT) detent.
T/O
The associated thrust lever is in the Takeoff (TO) detent.
The following illuminations appear in the EI displays of the EICAS. APR ON
The Automatic Performance Reserve (APR) has activated.
APR
The APR is armed in both DEECs.
DEP
The thrust reverser is deployed with aircraft on the ground.
IGN
The ignition is ON (either manually or automatically).
IGN
The ignition is ON, either manually or automatically, & one ignitor plug has failed. The other plug is functioning normally.
MAN
The DEEC is in the MANual mode or OFF mode as selected by the pilot.
NAC
The NAC anti-ice switch is ON & the system is functioning normally.
REV
The thrust reverser hydraulic control unit is receiving hydraulic pressure & the thrust reversers are armed with aircraft on the ground.
START
A vertical START illumination indicates that the engine starter is engaged.
SYNC
The ENG SYNC is ON (adjacent to either N1 or N2).
Advisory/ Status-12
EFFECTIVITY ALL
CL-126B October 2004
ENVIRONMENTAL/PRESSUR-LLCAB CABPRESS PRESSFAIL FAIL IZATION R CAB PRESS FAIL
R CAB PRESS FAIL
The left or right pressurization control has failed & will automatically switch operation to the opposite control. 1. Respective L or R PRESS Circuit Breaker (respective ENVIRONMENTAL group) .............Set, or Pull & Reset
CABPRESS PRESSMAN MAN CAB The crew has selected manual rate control of the pressurization system.
ECSFAULT FAULT LLECS R ECS FAULT R ECS FAULT A fault has been detected in the respective channel of the ECS controller during flight. 1. Respective L or R BLEED Circuit Breaker (respective ENVIRONMENTAL group) .............Set, or Pull & Reset 2. Monitor cabin altitude.
EMERDEPRESS DEPRESS EMER Emergency depressurization has been selected by the crew. Emergency depressurization commands both outflow valves full open, but will attempt to limit the cabin altitude to approximately 13,700 ft.
PACKHIGH HIGHFLOW FLOW PACK HI FLOW has been selected ON.
PAXOXY OXYDEPLOY DEPLOY PAX An electrical command (automatic or manual) has been provided to the FLIGHT CONpassenger oxygen deploy valve to deploy the masks. TROLS
AUTOSPLRARMED ARMED AUTOSPLR Autospoilers have been armed.
CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-13
ELEVATORDISC DISC ELEVATOR The elevator disconnect has split the elevator controls during flight. Do not reconnect. The pilot’s control column moves the left elevator. The copilot’s control column moves the right elevator. Autopilot will disengage & not reengage.
PITTRIM TRIMBIAS BIAS PIT The pitch trim bias system is moved from the normal position. PIT TRIM BIAS should only be used for jammed stabilizer conditions in flight. If the pitch trim bias system has moved from the normal position without pilot action, a normal landing may be accomplished.
PITTRIM TRIMMSCMP MSCMP PIT The stabilizer pitch trim indications between IC-600s (Integrated Computers) do not agree while on the ground.
PITCHTRIM TRIMOFF OFF PITCH PITCH TRIM selector switch is OFF. Autopilot, configuration trim & Mach trim will be inoperative.
PRITRIM TRIMFAULT FAULT PRI An IC-600 (Integrated Computer) trim fault has been detected. Primary trim may be available, however, operation may be at a lower trim rate. The configuration & Mach trim will be inoperative. 1. ●If primary trim is available: a. PRI PITCH Circuit Breaker (pilot’s FLIGHT group [TRIM]) ................................ Pull & Reset b. Control Wheel Master Switch (MSW) ......... Depress & Release to Attempt to Clear Fault 1. ●If primary trim is not available: a. Refer to PRI TRIM FAIL procedure, TAB 15, Abnormal Checklist.
ROLLDISC DISC ROLL Roll disconnect has occurred during flight. The pilot’s control wheel controls the spoilerons & the copilot’s control wheel controls the ailerons. Autopilot will disengage & not re-engage.
SECPITCH PITCHTRIM TRIM SEC Secondary pitch trim has been selected. Autopilot is available. Change 1
Advisory/ Status-14
EFFECTIVITY ALL
CL-126B October 2004 Change 1
SECTRIM TRIMFAULT FAULT SEC A power-up stabilizer actuator fault has been detected. If conditions permit: 1. SEC PITCH Circuit Breaker (copilot’s FLIGHT group [TRIM])................................... Pull & Reset 2. Control Wheel Master Switch (MSW) ................ Depress & Release to Attempt to Clear Fault 3. SEC TRIM ...................................................................... As Desired Trim will operate normally even if CAS remains illuminated.
SPOILERSEXT EXT SPOILERS Spoilers are not fully retracted. Spoileron extension will not activate this CAS.
TAKEOFFTRIM TRIM TAKEOFF Pitch, aileron, or rudder trim is not set for takeoff while the aircraft is on the ground & thrust levers are less than MCR.
WHEELMSTR MSTR WHEEL The Control Wheel Master Switch (MSW) has been depressed or power to one of the MSWs has been lost. This CAS will be accompanied by the PRI TRIM FAULT white CAS. The MSW will interrupt the pitch, aileron, rudder trims, configuration trim, Mach trim, PIT TRIM BIAS, & rudder boost systems. The autopilot, yaw damper & nose wheel steering (on the ground) will disconnect. On aircraft 45-002 thru 45-294 not modified by SB 45-27-20, the spoiler control valve will close which causes the spoiler & spoilerons to retract to the float position. The MACH TRIM FAIL white & amber CAS messages will not illuminate, & the MMO overspeed red limit bar on the PFD will not reduce to the Mach trim off MMO. 1. Respective L or R WHL MSTR Circuit Breaker (respective FLIGHT group) ..........................................................Set If either WHL MSTR circuit breaker remains pulled: 2. The following systems are inoperative: autopilot, yaw damper, rudder boost, Mach trim & configuration trim. Refer to the appropriate system failed procedures. The primary manual trim will be in the slow mode. The respective MSW will be inoperative. Change 1 CL-126B October 2004 Change 1
EFFECTIVITY ALL
Advisory/ Status-15
FUEL
FUELBAY BAYLOW LOW LLFUEL R FUEL BAY LOW R FUEL BAY LOW LR FUEL BAY LOW LR FUEL BAY LOW A float switch has detected low fuel in the collector bay. This may be an indication of a scavenge pump (motive flow) system failure or sideslip. The CAS will be displayed with the respective engine shut down. 1. Minimize sideslips & uncoordinated maneuvering.
FUELXFLO XFLOOPEN OPEN FUEL The wing fuel crossflow valve is open.
FUELFILTER FILTER LLFUEL R FUEL FILTER R FUEL FILTER LR FUEL FILTER LR FUEL FILTER Either the respective engine or aircraft fuel filter has an impending bypass during flight. 1. Respective L or R STBY ........................................................... ON
FUELHEATER HEATER LLFUEL R FUEL HEATER R FUEL HEATER LR FUEL HEATER LR FUEL HEATER The respective fuel heater/oil cooler has failed to the hot condition.
FUELQTY QTYFAULT FAULT LLFUEL R FUEL QTY FAULT R FUEL QTY FAULT Indicates the left or right channel has detected a fault or a loss of compensation.
FUELQTY QTYFAULT FAULT FUEL The FUEL QTY FAULT indicates that the attitude input from the AHRS is inoperative & the quantity may not be as accurate as normal, or that a fuselage probe is inoperative or invalid. This CAS will also illuminate during AHRS alignment. A probe failure may result in a FUEL IMBALANCE amber CAS due to calculation in the fuel quantity indicating conditioner.
Advisory/ Status-16
EFFECTIVITY ALL
CL-126B October 2004
FWSOVCLSD CLSD LLFWSOV R FWSOV CLSD R FWSOV CLSD LR FWSOV CLSD LR FWSOV CLSD The respective fuel firewall shutoff valve is closed.
STBYPUMP PUMPON ON LLSTBY R STBY PUMP ON R STBY PUMP ON LR STBY PUMP ON LR STBY PUMP ON Electrical power has been provided to the respective standby pump. The pumps may be turned on manually, & will automatically turn on during starter-assisted engine starts. The right standby pump will automatically turn on during APU starts (if installed) and will remain on during APU HYDRAULICSoperation.
HYDXFLOW XFLOWON ON HYD Hydraulic crossflow valve is open.
HYDPUMP PUMPLOW LOW LLHYD R HYD PUMP LOW R HYD PUMP LOW LR HYD PUMP LOW LR HYD PUMP LOW The left or right engine hydraulic pressure is less than 1900 psi. The hydraulic pump symbol on the HYD page will be amber with this CAS message displayed. 1. EICAS .............................................. Select HYD or SUMRY Page 2. Monitor MAIN hydraulic pressure.
MAINHYDQTY HYDQTYLO LO MAIN Main hydraulic quantity is low.
CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-17
INSTRUMENT/ AVIONICSAHRS AHRS11BASIC BASIC
AHRS22BASIC BASIC AHRS AHRS 1-2 BASIC AHRS 1-2 BASIC The Attitude Heading Reference System, AHRS 1 or 2, has reverted to basic mode due to a loss of true airspeed from both air data computers. The attitude displays, autopilot, FMS, & radar stabilization will operate normally. Minimize sustained shallow bank turns (less than 6° bank) to minimize small AHRS errors.
CKLSTMISMATCH MISMATCH CKLST Indicates that the checklists loaded in IC 1 & IC 2 do not match.
DAUAAREV REV DAU DAU B REV DAU B REV Pilot has selected DAU Reversion to Channel A or B. In reversion, both ICs use the same channel (A or B) of both DAUs. Some loss of redundancy & comparison monitoring occurs during reversion, & DAU REV should not be selected unless a DAU fault or failure is detected.
DU11FAN FANFAIL FAIL DU DU 2 FAN FAIL DU 2 FAN FAIL DU 1-2 FAN FAIL DU 1-2 FAN FAIL Indicates that the respective Display Unit (DU) cooling fan has failed. If conditions permit: DU 1 FAN FAIL 1. DU 2 Reversion Switch .............................................................PFD EICAS will automatically revert to DU 3. 2. DU 1 Circuit Breaker (pilot’s INSTRUMENTS/INDICATIONS group [DISPLAY])....................Pull
(Procedure Continued) Advisory/ Status-18
EFFECTIVITY ALL
CL-126B October 2004
DU 2 FAN FAIL 1. DU 2 Reversion Switch ............................................................ OFF EICAS will automatically revert to DU 3. 2. DU 2 Circuit Breaker (pilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]).........Pull DU 1-2 FAN FAIL 1. DU 2 Reversion Switch ............................................................ OFF EICAS will automatically revert to DU 3. 2. DU 1 & DU 2 Circuit Breakers (pilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]).........Pull Rely on the copilot’s flight displays & standby instruments.
DU33FAN FANFAIL FAIL DU DU 4 FAN FAIL DU 4 FAN FAIL DU 3-4 FAN FAIL DU 3-4 FAN FAIL Indicates that the respective Display Unit (DU) cooling fan has failed. DU 3 FAN FAIL 1. DU 3 Reversion Switch .............................................................Push if DU 3 is Presently in EICAS Format 2. DU 3 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group [DISPLAY])......Pull DU 4 FAN FAIL 1. DU 3 Reversion Switch ..............................................................PFD EICAS will automatically revert to DU 2. 2. DU 4 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group [DISPLAY])......Pull DU 3-4 FAN FAIL 1. DU 3 Reversion Switch ........................................Push As Required to get EICAS on DU 2 2. DU 3 & DU 4 Circuit Breakers (copilot’s INSTRUMENTS/INDICATIONS group [DISPLAY])......Pull Rely on the pilot’s flight displays & standby instruments.
CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-19
GND PROX FAIL One or more of the GPWS modes 1 - 5 are inoperative. 1. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)........................ Pull & Reset
GPWS FLAP OVRD FLAP switch has been selected OFF. Flap input is forced to 40° flaps into the EGPWS computer.
GPWS G/S INHB G/S switch has been selected OFF.
GPWSFAIL FAIL OR GPWS GPWS SYS FAIL All modes of the GPWS system have failed. 1. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)........................ Pull & Reset
CNFGFAIL FAIL ICIC11CNFG IC 2 CNFG FAIL IC 2 CNFG FAIL A communication failure has occurred between the IC-600 (Integrated Computer) and IM-600 (Integrated Computer Configuration Module). The IC-600 will continue to function properly, and will power up with the configuration stored at the last power-down.
IC11FAN FANFAIL FAIL IC IC 2 FAN FAIL IC 2 FAN FAIL IC 1-2 FAN FAIL IC 1-2 FAN FAIL The respective IC (Integrated Computer) 1 or 2 cooling fan has failed. Monitor for deteriorating IC functionality & select IC/SG REVERSION as necessary.
Advisory/ Status-20
EFFECTIVITY ALL
CL-126B October 2004
WOWINOP INOP ICIC11WOW IC 2 WOW INOP IC 2 WOW INOP IC 1-2 WOW INOP IC 1-2 WOW INOP The respective IC (Integrated Computer) has tripped the Weight-On-Wheel monitor by a detected mismatch between the Weight-On-Wheel inputs & airspeed logic. Weight-On-Wheel logic is used by the IC for internal logic tests & external tests. The monitor check is performed once after takeoff, & once after landing. On the ground: 1. Respective IC/SG 1 or 2 Circuit Breaker (pilot’s or copilot’s INSTRUMENTS/INDICATIONS group).......... Pull & Reset In flight: 1. Continue flight.
INSTRPNL PNLTEMP TEMP INSTR An instrument panel thermal switch has tripped. 1. INSTR FAN Circuit Breaker (pilot’s ENVIRONMENTAL group) ....................Set, or Pull & Reset
LBS/KGSCONFIG CONFIG LBS/KGS The pounds/kilograms configuration of the IC-600 (Integrated Computer) disagrees with the configuration of DAU 1 & 2 during flight.
NOSEBAY BAYTEMP TEMP NOSE A nose bay thermal switch has tripped.
TERR FAIL The Terrain Mode is inoperative. 1. FMS 1 and FMS 2 (if installed) ....................................... Check ON 2. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ....................... Pull & Reset
CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-21
TERRINHB INHB OR TERR TERR INHIB TERR switch has been selected OFF. Terrain display, annunciations of alerts and warnings, and TCFs are all disabled.
WINDSHEARFAIL FAIL WINDSHEAR 1. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)........................ Pull & Reset
Multi-Function Display (MFD) ABV Located in the upper left corner of the TCAS zoom window, this annunciation indicates traffic will be displayed at relative altitudes of -2,700 feet to +7,000 feet. BLW Located in the upper left corner of the TCAS zoom window, this annunciation indicates traffic will be displayed at relative altitudes of -7,000 feet to +2,700 feet. DGx Located to the right of the MFD or PFD heading readout and indicates the respective HEADING switch is in the unslaved (FREE) mode. FL Located in the upper left corner of the TCAS zoom window, this annunciation indicates that Flight Level mode has been selected by the pilot. All traffic altitudes will be displayed in 3-digit flight level format (e.g., 19,000 feet will be displayed as 190). TA ONLY Located in the upper left corner of the TCAS zoom window, this annunciation indicates no resolution advisory information or guidance will be provided. TCAS Located in the upper left corner of the TCAS zoom window, this annunciation indicates normal TCAS system operation. It is the default TCAS message.
Advisory/ Status-22
EFFECTIVITY ALL
CL-126B October 2004
TCAS FAILURES Located in the upper right corner of the TCAS zoom window at the end of each self test, this annunciation is just a header. If any part of the self test fails, a description of the failure will be displayed below this header. TCAS OFF Located in the upper left corner of the TCAS zoom window, this annunciation indicates that the system is functional but in standby mode, or nonfunctional due to incorrect or failed ADC operation. TCAS TEST Located in the upper left corner of the TCAS zoom window, this annunciation indicates that the TCAS system self test is in progress. TERR Located in the upper left corner of the MFD and indicates Terrain is selected for display. TERR INHIB Located in the upper left corner of the MFD and indicates the TERR switch has been selected OFF.
Primary Flight Display (PFD) Annunciations DGx Located to the right of the PFD heading readout and indicates the respective HEADING switch is in the unslaved (FREE) mode. TA ONLY Located below the VSI display, this annunciation indicates no resolution advisory information or guidance will be provided. TCAS INOP Located below the VSI display, this annunciation indicates that TCAS is not enabled, but the system has been strapped to accept it. TCAS OFF Located below the VSI display, this annunciation indicates that the system is functional but in standby mode, or non-functional due to incorrect or failed ADC operation. TCAS TEST Located below the VSI display, this annunciation indicates that the TCAS system self test is in progress.
CL-126B October 2004
EFFECTIVITY ALL
Advisory/ Status-23
BRAKEFAULT FAULT BRAKE A brake system fault has been sensed that results in minor system degradation. Increase the takeoff & landing distances as follows: - Dry Runway Aircraft not modified by SB 45-11-4 — Add 300 feet (91 meters). Aircraft modified by SB 45-11-4 — Add 500 feet (153 meters). - Wet Runway — Add 600 feet (183 meters).
EMER/PARKBRK BRK EMER/PARK The emergency brake is being used or the parking brake valve is not fully released, & thrust levers are less than MCR.
NWSFAULT FAULT NWS NWS FAULT may indicate a loss of pedal force steering. 1. NOSE STEER .............................................................Off, then ON
CVRFAIL FAIL CVR The cockpit voice recorder has failed. 1. CVR Circuit Breaker (pilot’s INSTRUMENTS/INDICATIONS group) ........................... Set If circuit breaker remains pulled: 2. The CWP tone/voice volume will be at a fixed (high) level.
EMERLIGHTS LIGHTS EMER The emergency lights are on.
FDRFAIL FAIL(IF INSTALLED) FDR The flight data recorder has failed. 1. FDR Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ........................ Set If DAU 1A amber CAS is also illuminated, the FDR may still operate. Change 1
Advisory/ Status-24
EFFECTIVITY ALL
CL-126B October 2004 Change 1
CHECKEDS EDS LLCHECK R CHECK EDS R CHECK EDS LR CHECK EDS LR CHECK EDS One of the following conditions of the applicable Engine Diagnostic System (EDS) (part of the Engine Condition Trend Monitor (ECTM) system) has occurred. - The EDS has lost power. - The EDS built-in test equipment (BITE) has detected a system failure. - The EDS memory is 85% full. - The system has detected an engine condition which was out of acceptable parameters.
REVAUTOSTOW AUTOSTOW LLREV REVAUTOSTOW AUTOSTOW RRREV LR REV AUTOSTOW LR REV AUTOSTOW The respective thrust reverser autostow function has activated & applied hydraulic pressure to the stow side of the actuator.
REVFAULT FAULT LLREV REVFAULT FAULT RRREV LR REV FAULT LR REV FAULT A fault has been detected in the respective thrust reverser system. On the ground: 1. Respective DEPLOY, ANN and STOW Circuit Breakers (ENGINE group [L or R REVERSER])........... Pull & Reset 2. ●If respective REV FAULT remains illuminated: a.
Do not take off. Refer the problem to maintenance personnel for correction. 2. ●If respective REV FAULT extinguishes: a.
This checklist is complete.
In flight: 1. Land as soon as practical. Change 1 CL-126B October 2004 Change 1
EFFECTIVITY ALL
Advisory/ Status-25
WARN
WARNPWR PWRFAIL FAIL LLWARN R WARN PWR FAIL R WARN PWR FAIL The respective Crew Warning Panel (CWP) power supply has failed or lost power. The CWP is still operational from the opposite power supply; however, the CWP annunciators may look dim. 1. Respective L or R WARN PANEL Circuit Breaker (respective INSTRUMENTS/INDICATIONS group).................... Set
WARNAUDIO AUDIO WARN The Crew Warning Panel (CWP) has detected a fault in either one of the output audio channels, or in the Automatic Gain Control (AGC) input. The CWP is still operational, & the tone/voice volume will be at a fixed (high) level.
Advisory/ Status-26
EFFECTIVITY ALL
CL-126B October 2004
SUPPLEMENTAL DATA CONTENTS CONVERSIONS TEMPERATURE CONVERSION............................................... S-2 LINEAR CONVERSION............................................................. S-3 VOLUME CONVERSION .......................................................... S-4
ENVIRONMENTAL OXYGEN DURATION................................................................ S-6 OXYGEN QUANTITY MISSION PLANNING............................. S-7
ELECTRICAL DC POWER DISTRIBUTION (DUAL GENERATOR FAILURE) ............................................... S-9
SCHEMATICS .......................................................................... S-10 ELECTRICAL ELECTRICAL SYSTEM (DUAL GENERATOR FAILURE) ........ S-10 ELECTRICAL SYSTEM (NORMAL) .......................................... S-11 ENGINE ENGINE FIRE EXTINGUISHING SYSTEM............................... S-12 ENVIRONMENTAL/PRESSURIZATION BLEED AIR SYSTEM ................................................................ S-13 TEMPERATURE CONTROL SYSTEM ..................................... S-14 PRESSURIZATION SYSTEM ................................................... S-15 FUEL FUEL SYSTEM.......................................................................... S-16 HYDRAULICS HYDRAULIC SYSTEM ............................................................. S-17 HYDRAULIC SYSTEM (HYD XFLOW ON) ............................... S-18 LANDING GEAR/BRAKES LANDING GEAR EXTENDED ................................................... S-19 LANDING GEAR RETRACTED................................................. S-20 BRAKE SYSTEM....................................................................... S-21
APU OPERATING PROCEDURES ................................... S-22 MASTER EICAS INDEX........................................................ S-24 CL-126B October 2004
EFFECTIVITY ALL
S-1
SUPPLEMENTAL DATA
WEIGHT CONVERSION ........................................................... S-5
TEMPERATURE CONVERSION •
To convert from Celsius to Fahrenheit, find, in bold face columns, the number representing the Celsius temperature to be converted. The equivalent Fahrenheit temperature is read in the adjacent column headed °F.
•
To convert from Fahrenheit to Celsius, find, in bold face columns, the number representing the Fahrenheit temperature to be converted. The equivalent Celsius temperature is read in the adjacent column headed °C.
SUPPLEMENTAL DATA
°F
°C
°F
°C
°F
°C
°C
°F
°C
-73.3 -72.8 -72.2 -71.7 -71.1
-58.0 -56.2 -54.4 -52.6 -50.8
-50 -49 -48 -47 -46
-45.6 -45.0 -44.4 -43.9 -43.3
32.0 33.8 35.6 37.4 39.2
0 1 2 3 4
-17.8 -17.2 -16.7 -16.1 -15.6
122.0 123.8 125.6 127.4 129.2
50 51 52 53 54
10.0 10.6 11.1 11.7 12.2
212.0 213.8 215.6 217.4 219.2
100 101 102 103 104
37.8 38.3 38.9 39.4 40.0
-139.0 -137.2 -135.4 -133.6 -131.8
-95 -94 -93 -92 -91
-70.6 -70.0 -69.4 -68.9 -68.3
-49.0 -47.2 -45.4 -43.6 -41.8
-45 -44 -43 -42 -41
-42.8 -42.2 -41.7 -41.1 -40.6
41.0 42.8 44.6 46.4 48.2
5 6 7 8 9
-15.0 -14.4 -13.9 -13.3 -12.8
131.0 132.8 134.6 136.4 138.2
55 56 57 58 59
12.8 13.3 13.9 14.4 15.0
221.0 222.8 224.6 226.4 228.2
105 106 107 108 109
40.6 41.1 41.7 42.2 42.8
-130.0 -128.2 -126.4 -124.6 -122.8
-90 -89 -88 -87 -86
-67.8 -67.2 -66.7 -66.1 -65.6
-40.0 -38.2 -36.4 -34.6 -32.8
-40 -39 -38 -37 -36
-40.0 -39.4 -38.9 -38.3 -37.8
50.0 51.8 53.6 55.4 57.2
10 11 12 13 14
-12.2 -11.7 -11.1 -10.6 -10.0
140.0 141.8 143.6 145.4 147.2
60 61 62 63 64
15.6 16.1 16.7 17.2 17.8
230.0 231.8 233.6 235.4 237.2
110 111 112 113 114
43.3 43.9 44.4 45.0 45.6
-121.0 -119.2 -117.4 -115.6 -113.8
-85 -84 -83 -82 -81
-65.0 -64.4 -63.9 -63.3 -62.8
-31.0 -29.2 -27.4 -25.6 -23.8
-35 -34 -33 -32 -31
-37.2 -36.7 -36.1 -35.6 -35.0
59.0 60.8 62.6 64.4 66.2
15 16 17 18 19
-9.4 -8.9 -8.3 -7.8 -7.2
149.0 150.8 152.6 154.4 156.2
65 66 67 68 69
18.3 18.9 19.4 20.0 20.6
239.0 240.8 242.6 244.4 246.2
115 116 117 118 119
46.1 46.7 47.2 47.8 48.3
-112.0 -110.2 -108.4 -106.6 -104.8
-80 -79 -78 -77 -76
-62.2 -61.7 -61.1 -60.6 -60.0
-22.0 -20.2 -18.4 -16.6 -14.8
-30 -29 -28 -27 -26
-34.4 -33.9 -33.3 -32.8 -32.2
68.0 69.8 71.6 73.4 75.2
20 21 22 23 24
-6.7 -6.1 -5.6 -5.0 -4.4
158.0 159.8 161.6 163.4 165.2
70 71 72 73 74
21.1 21.7 22.2 22.8 23.3
248.0 249.8 251.6 253.4 255.2
120 121 122 123 124
48.9 49.4 50.0 50.6 51.1
-103.0 -101.2 -99.4 -97.6 -95.8
-75 -74 -73 -72 -71
-59.4 -58.9 -58.3 -57.8 -57.2
-13.0 -11.2 -9.4 -7.6 -5.8
-25 -24 -23 -22 -21
-31.7 -31.1 -30.6 -30.0 -29.4
77.0 78.8 80.6 82.4 84.2
25 26 27 28 29
-3.9 -3.3 -2.8 -2.2 -1.7
167.0 168.8 170.6 172.4 174.2
75 76 77 78 79
23.9 24.4 25.0 25.6 26.1
257.0 258.8 260.6 262.4 264.2
125 126 127 128 129
51.7 52.2 52.8 53.3 53.9
-94.0 -92.2 -90.4 -88.6 -86.8
-70 -69 -68 -67 -66
-56.7 -56.1 -55.6 -55.0 -54.4
-4.0 -2.2 -0.4 1.4 3.2
-20 -19 -18 -17 -16
-28.9 -28.3 -27.8 -27.2 -26.7
86.0 87.8 89.6 91.4 93.2
30 31 32 33 34
-1.1 -0.6 0.0 0.6 1.1
176.0 177.8 179.6 181.4 183.2
80 81 82 83 84
26.7 27.2 27.8 28.3 28.9
266.0 267.8 269.6 271.4 273.2
130 131 132 133 134
54.4 55.0 55.6 56.1 56.7
-85.0 -83.2 -81.4 -79.6 -77.8
-65 -64 -63 -62 -61
-53.9 -53.3 -52.8 -52.2 -51.7
5.0 6.8 8.6 10.4 12.2
-15 -14 -13 -12 -11
-26.1 -25.6 -25.0 -24.4 -23.9
95.0 96.8 98.6 100.4 102.2
35 36 37 38 39
1.7 2.2 2.8 3.3 3.9
185.0 186.8 188.6 190.4 192.2
85 86 87 88 89
29.4 30.0 30.6 31.1 31.7
275.0 276.8 278.6 280.4 282.2
135 136 137 138 139
57.2 57.8 58.3 58.9 59.4
-76.0 -74.2 -72.4 -70.6 -68.8
-60 -59 -58 -57 -56
-51.1 -50.6 -50.0 -49.4 -48.9
14.0 15.8 17.6 19.4 21.2
-10 -9 -8 -7 -6
-23.3 -22.8 -22.2 -21.7 -21.1
104.0 105.8 107.6 109.4 111.2
40 41 42 43 44
4.4 5.0 5.6 6.1 6.7
194.0 195.8 197.6 199.4 201.2
90 91 92 93 94
32.2 32.8 33.3 33.9 34.4
284.0 285.8 287.6 289.4 291.2
140 141 142 143 144
60.0 60.6 61.1 61.7 62.2
-67.0 -65.2 -63.4 -61.6 -59.8
-55 -54 -53 -52 -51
-48.3 -47.8 -47.2 -46.7 -46.1
23.0 24.8 26.6 28.4 30.2
-5 -4 -3 -2 -1
-20.6 -20.0 -19.4 -18.9 -18.3
113.0 114.8 116.6 118.4 120.2
45 46 47 48 49
7.2 7.8 8.3 8.9 9.4
203.0 204.8 206.6 208.4 210.2
95 96 97 98 99
35.0 35.6 36.1 36.7 37.2
293.0 294.8 296.6 298.4 300.2
145 146 147 148 149
62.8 63.3 63.9 64.4 65.0
EFFECTIVITY
S-2
°F
-148.0 -100 -146.2 -99 -144.4 -98 -142.6 -97 -140.8 -96
ALL
CL-126B October 2004
LINEAR CONVERSION • To convert from meters to feet, find, in the bold face columns, the number of meters to be converted. The equivalent number of feet is read in the adjacent column headed FEET. • To convert from feet to meters, find, in the bold face columns, the number of feet to be converted. The equivalent number of meters is read in the adjacent column headed METERS. METERS
FEET
METERS
FEET
METERS
FEET
304.8
1000
3280.8
1341.1
4400
14435.5
2377.5
7800
25590.2
335.3
1100
3608.9
1371.6
4500
14763.6
2407.9
7900
25918.3
365.8
1200
3937.0
1402.1
4600
15091.7
2438.4
8000
26246.4
396.2
1300
4265.0
1432.6
4700
15419.8
2468.9
8100
26574.5
426.7
1400
4593.1
1463.1
4800
15747.8
2499.4
8200
26902.6
457.2
1500
4921.2
1493.5
4900
16075.9
2529.9
8300
27230.6
487.7
1600
5249.3
1524.0
5000
16404.0
2560.4
8400
27558.7
518.2
1700
5577.4
1554.5
5100
16732.1
2590.8
8500
27886.8
548.6
1800
5905.4
1585.0
5200
17060.2
2621.3
8600
28214.9
579.1
1900
6233.5
1615.5
5300
17388.2
2651.8
8700
28543.0
609.6
2000
6561.6
1645.9
5400
17716.3
2682.3
8800
28871.0
640.1
2100
6889.7
1676.4
5500
18044.4
2712.8
8900
29199.1
670.6
2200
7217.8
1706.9
5600
18372.5
2743.2
9000
29527.2
701.0
2300
7545.8
1737.4
5700
18700.6
2773.7
9100
29855.3
731.5
2400
7873.9
1767.9
5800
19028.6
2804.2
9200
30183.4
762.0
2500
8202.0
1798.3
5900
19356.7
2834.7
9300
30511.4
792.5
2600
8530.1
1828.8
6000
19684.8
2865.2
9400
30839.5
823.0
2700
8858.2
1859.3
6100
20012.9
2895.6
9500
31167.6
853.5
2800
9186.2
1889.8
6200
20341.0
2926.1
9600
31495.7
883.9
2900
9514.3
1920.3
6300
20669.0
2956.6
9700
31823.8
914.4
3000
9842.4
1950.7
6400
20997.1
2987.1
9800
32151.8
944.9
3100
10170.5
1981.2
6500
21325.2
3017.6
9900
32479.9
975.4
3200
10498.6
2011.7
6600
21653.3
3048.0
10000
32808.0
1005.9
3300
10826.6
2042.2
6700
21981.4
3352.8
11000
36088.8
1036.3
3400
11154.7
2072.7
6800
22309.4
3657.6
12000
39369.6
1066.8
3500
11482.8
2103.1
6900
22637.5
3962.4
13000
42650.4
1097.3
3600
11810.9
2133.6
7000
22965.6
4267.3
14000
45931.2
1127.8
3700
12139.0
2164.1
7100
23293.7
4572.1
15000
49212.0
1158.3
3800
12467.0
2194.6
7200
23621.8
4876.9
16000
52492.8
1188.7
3900
12795.1
2225.1
7300
23949.8
5181.7
17000
55773.6
1219.2
4000
13123.2
2255.5
7400
24277.9
5486.5
18000
59054.4
1249.7
4100
13451.3
2286.0
7500
24606.0
5791.3
19000
62335.2
1280.2
4200
13779.4
2316.5
7600
24934.1
6096.1
20000
65616.0
1310.7
4300
14107.4
2347.0
7700
25262.2
6400.9
21000
68896.8
CL-126B October 2004
EFFECTIVITY ALL
S-3
VOLUME CONVERSION • To convert from liters to gallons, find, in the bold face columns, the number of liters to be converted. The equivalent number of gallons is read in the adjacent column headed GALLONS. • To convert from gallons to liters, find, in the bold face columns, the number of gallons to be converted. The equivalent number of liters is read in the adjacent column headed LITERS. LITERS
GALLONS
LITERS
GALLONS
LITERS
GALLONS
18.9 37.9 75.7 113.6 151.4 189.3 227.1 265.0 302.8 340.7 378.5 416.4 454.2 492.1 529.9 567.8 605.6 643.5 681.3 719.2
5 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190
1.3 2.6 5.3 7.9 10.6 13.2 15.9 18.5 21.1 23.8 26.4 29.1 31.7 34.3 37.0 39.6 42.3 44.9 47.6 50.2
1476.2 1514.0 1551.9 1589.7 1627.6 1665.4 1703.3 1741.1 1779.0 1816.8 1854.7 1892.5 1930.4 1968.2 2006.1 2043.9 2081.8 2119.6 2157.5 2195.3
390 400 410 420 430 440 450 460 470 480 490 500 510 520 530 540 550 560 570 580
103.0 105.7 108.3 111.0 113.6 116.2 118.9 121.5 124.2 126.8 129.5 132.1 134.7 137.4 140.0 142.7 145.3 148.0 150.6 153.2
2952.3 2990.2 3028.0 3065.9 3103.7 3141.6 3179.4 3217.3 3255.1 3293.0 3330.8 3368.7 3406.5 3444.4 3482.2 3520.1 3557.9 3595.8 3633.6 3671.5
780 790 800 810 820 830 840 850 860 870 880 890 900 910 920 930 940 950 960 970
206.1 208.7 211.4 214.0 216.6 219.3 221.9 224.6 227.2 229.9 232.5 235.1 237.8 240.4 243.1 245.7 248.3 251.0 253.6 256.3
757.0 794.9 832.7 870.6 908.4 946.3 984.1 1022.0 1059.8 1097.7 1135.5 1173.4 1211.2 1249.1 1286.9 1324.8 1362.6 1400.5 1438.3
200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 360 370 380
52.8 55.5 58.1 60.8 63.4 66.1 68.7 71.3 74.0 76.6 79.3 81.9 84.5 87.2 89.8 92.5 95.1 97.8 100.4
2233.2 2271.0 2308.9 2346.7 2384.6 2422.4 2460.3 2498.1 2536.0 2573.8 2611.7 2649.5 2687.4 2725.2 2763.1 2800.9 2838.8 2876.6 2914.5
590 600 610 620 630 640 650 660 670 680 690 700 710 720 730 740 750 760 770
155.9 158.5 161.2 163.8 166.4 169.1 171.7 174.4 177.0 179.7 182.3 184.9 187.6 190.2 192.9 195.5 198.2 200.8 203.4
3709.3 3747.2 3785.0 4163.5 4542.0 4920.5 5299.0 5677.5 6056.0 6434.5 6813.0 7191.5 7570.0 7948.5 8327.0 8705.5 9084.0 9462.5 9841.0
980 990 1000 1100 1200 1300 1400 1500 1600 1700 1800 1900 2000 2100 2200 2300 2400 2500 2600
258.9 261.6 264.2 290.6 317.0 343.5 369.9 396.3 422.7 449.1 475.6 502.0 528.4 554.8 581.2 607.7 634.1 660.5 686.9
S-4
EFFECTIVITY ALL
CL-126B October 2004
WEIGHT CONVERSION • To convert from kilograms to pounds, find, in the bold face columns, the number of kilograms to be converted. The equivalent number of pounds is read in the adjacent column headed POUNDS. • To convert from pounds to kilograms, find, in the bold face columns, the number of pounds to be converted. The equivalent number of kilograms is read in the adjacent column headed KILOGRAMS. KILOGRAMS 4.5 9.1 13.6 18.1 22.7 27.2 31.8 36.3 40.8 45.4 49.9 54.4 59.0 63.5 68.0 72.6 77.1 81.6 86.2 90.7 95.3 99.8 104.3 108.9 113.4 117.9 122.5 127.0 131.5 136.1 140.6 145.2 149.7 154.2 158.8 163.3 167.8 172.4 176.9 181.4 186.0 190.5 195.0 199.6 204.1
CL-126B October 2004
POUNDS 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 360 370 380 390 400 410 420 430 440 450
22.0 44.1 66.1 88.2 110.2 132.3 154.3 176.4 198.4 220.5 242.5 264.6 286.6 308.6 330.7 352.7 374.8 396.8 418.9 440.9 463.0 485.0 507.1 529.1 551.1 573.2 595.2 617.3 639.3 661.4 683.4 705.5 727.5 749.6 771.6 793.7 815.7 837.7 859.8 881.8 903.9 925.9 948.0 970.0 992.1
KILOGRAMS 208.7 213.2 217.7 222.3 226.8 231.3 235.9 240.4 244.9 249.5 254.0 258.6 263.1 267.6 272.2 276.7 281.2 285.8 290.3 294.8 299.4 303.9 308.4 313.0 317.5 322.1 326.6 331.1 335.7 340.2 344.7 349.3 353.8 358.3 362.9 367.4 371.9 376.5 381.0 385.6 390.1 394.6 399.2 403.7 408.2
POUNDS KILOGRAMS 460 470 480 490 500 510 520 530 540 550 560 570 580 590 600 610 620 630 640 650 660 670 680 690 700 710 720 730 740 750 760 770 780 790 800 810 820 830 840 850 860 870 880 890 900
1014.1 1036.2 1058.2 1080.3 1102.3 1124.3 1146.4 1168.4 1190.5 1212.5 1234.6 1256.6 1278.7 1300.7 1322.8 1344.8 1366.9 1388.9 1410.9 1433.0 1455.0 1477.1 1499.1 1521.2 1543.2 1565.3 1587.3 1609.4 1631.4 1653.4 1675.5 1697.5 1719.6 1741.6 1763.7 1785.7 1807.8 1829.8 1851.9 1873.9 1896.0 1918.0 1940.0 1962.1 1984.1
412.8 417.3 421.8 426.4 430.9 435.5 440.0 444.5 449.1 453.6 499.0 544.3 589.7 635.0 680.4 907.2 1134.0 1360.8 1587.6 1814.4 2041.2 2268.0 2494.8 2721.6 2948.4 3175.2 3402.0 3628.8 3855.6 4082.4 4309.2 4536.0 4989.6 5443.2 5896.8 6350.4 6804.0 7257.6 7711.1 8164.7 8618.3 9071.9 9525.5 9979.1 10432.7
POUNDS 910 920 930 940 950 960 970 980 990 1000 1100 1200 1300 1400 1500 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 8500 9000 9500 10000 11000 12000 13000 14000 15000 16000 17000 18000 19000 20000 21000 22000 23000
2006.2 2028.2 2050.3 2072.3 2094.4 2116.4 2138.5 2160.5 2182.6 2204.6 2425.1 2645.5 2866.0 3086.4 3306.9 4409.2 5511.5 6613.8 7716.1 8818.4 9920.7 11023.0 12125.3 13227.6 14329.9 15432.2 16534.5 17636.8 18739.1 19841.4 20943.7 22046.0 24250.6 26455.2 28659.8 30864.4 33069.0 35273.6 37478.2 39682.8 41887.4 44092.0 46296.6 48501.2 50705.8
EFFECTIVITY ALL
S-5
OXYGEN DURATION for PURITAN-BENNETT SWEEP-ON 2000 or EROS Crew Masks
CREW MASKS set to NORM
CREW MASKS set to 100%
Cabin Altitude — 1000 FT
10
15
Cabin Altitude — 1000 FT
20
0
0
0
25 0
5
5
5
5
10
10
10
15
15
15
20
20
NUMBER OF PASSENGERS
20
10
15
10
0
0
0
5
5
5
10
10
9 8
15
10
15 20
15
6
20
0
0
0
0
10
10
10
10
20
20
20
20
30
30
30
30
40
40
40
15
20
5
25
50
25 0
10
25
25
45-136C
20
25
50
60
60
70
70
80
80
90
90
50 60
0 NUMBER OF PASSENGERS
10
0
20 30
2
50
40
1
50
60
70
20
30 40
0
80 90
Example
90 200
300
400
600
700
35
60
50
Example: OXY QTY........................500 LTR
Cabin Altitude ............ 25,000 feet
Passengers................................ 6
Duration ......... 13.5 min. @ 100% 14 min. @ NORM
S-6
40
DURATION — MINUTES
OXYGEN — LTR
EFFECTIVITY EFFECTIVITY Aircraft 45-002 thru 45-169 without Altitude CompensatedALL Oxygen System
25
40
70 80
500
15
30 50
80
10
20
30
60
70
0 5
10
20 4
40
DURATION — MINUTES
10
0
CL-126B October 2004
WEIGHT CONVERSION • To convert from kilograms to pounds, find, in the bold face columns, the number of kilograms to be converted. The equivalent number of pounds is read in the adjacent column headed POUNDS. • To convert from pounds to kilograms, find, in the bold face columns, the number of pounds to be converted. The equivalent number of kilograms is read in the adjacent column headed KILOGRAMS. KILOGRAMS 4.5 9.1 13.6 18.1 22.7 27.2 31.8 36.3 40.8 45.4 49.9 54.4 59.0 63.5 68.0 72.6 77.1 81.6 86.2 90.7 95.3 99.8 104.3 108.9 113.4 117.9 122.5 127.0 131.5 136.1 140.6 145.2 149.7 154.2 158.8 163.3 167.8 172.4 176.9 181.4 186.0 190.5 195.0 199.6 204.1
CL-126B October 2004
POUNDS 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 360 370 380 390 400 410 420 430 440 450
22.0 44.1 66.1 88.2 110.2 132.3 154.3 176.4 198.4 220.5 242.5 264.6 286.6 308.6 330.7 352.7 374.8 396.8 418.9 440.9 463.0 485.0 507.1 529.1 551.1 573.2 595.2 617.3 639.3 661.4 683.4 705.5 727.5 749.6 771.6 793.7 815.7 837.7 859.8 881.8 903.9 925.9 948.0 970.0 992.1
KILOGRAMS 208.7 213.2 217.7 222.3 226.8 231.3 235.9 240.4 244.9 249.5 254.0 258.6 263.1 267.6 272.2 276.7 281.2 285.8 290.3 294.8 299.4 303.9 308.4 313.0 317.5 322.1 326.6 331.1 335.7 340.2 344.7 349.3 353.8 358.3 362.9 367.4 371.9 376.5 381.0 385.6 390.1 394.6 399.2 403.7 408.2
POUNDS KILOGRAMS 460 470 480 490 500 510 520 530 540 550 560 570 580 590 600 610 620 630 640 650 660 670 680 690 700 710 720 730 740 750 760 770 780 790 800 810 820 830 840 850 860 870 880 890 900
1014.1 1036.2 1058.2 1080.3 1102.3 1124.3 1146.4 1168.4 1190.5 1212.5 1234.6 1256.6 1278.7 1300.7 1322.8 1344.8 1366.9 1388.9 1410.9 1433.0 1455.0 1477.1 1499.1 1521.2 1543.2 1565.3 1587.3 1609.4 1631.4 1653.4 1675.5 1697.5 1719.6 1741.6 1763.7 1785.7 1807.8 1829.8 1851.9 1873.9 1896.0 1918.0 1940.0 1962.1 1984.1
412.8 417.3 421.8 426.4 430.9 435.5 440.0 444.5 449.1 453.6 499.0 544.3 589.7 635.0 680.4 907.2 1134.0 1360.8 1587.6 1814.4 2041.2 2268.0 2494.8 2721.6 2948.4 3175.2 3402.0 3628.8 3855.6 4082.4 4309.2 4536.0 4989.6 5443.2 5896.8 6350.4 6804.0 7257.6 7711.1 8164.7 8618.3 9071.9 9525.5 9979.1 10432.7
POUNDS 910 920 930 940 950 960 970 980 990 1000 1100 1200 1300 1400 1500 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 8500 9000 9500 10000 11000 12000 13000 14000 15000 16000 17000 18000 19000 20000 21000 22000 23000
2006.2 2028.2 2050.3 2072.3 2094.4 2116.4 2138.5 2160.5 2182.6 2204.6 2425.1 2645.5 2866.0 3086.4 3306.9 4409.2 5511.5 6613.8 7716.1 8818.4 9920.7 11023.0 12125.3 13227.6 14329.9 15432.2 16534.5 17636.8 18739.1 19841.4 20943.7 22046.0 24250.6 26455.2 28659.8 30864.4 33069.0 35273.6 37478.2 39682.8 41887.4 44092.0 46296.6 48501.2 50705.8
EFFECTIVITY ALL
S-5
OXYGEN DURATION for PURITAN-BENNETT SWEEP-ON 2000 or EROS Crew Masks CREW MASKS set to NORM Cabin Altitude — 1000 FT
10 0 5 10 15 20 25 30 35 40 45 50 55 60 65
15 0
20 0
5
5
10 15
15
25
20
30
25
25 0
20 0
15 0
5
5
5
5
10
10
10
10
15
15
20
20
25
25
45-137B
15
NUMBER OF PASSENGERS
20
30
40 45
Cabin Altitude — 1000 FT
25 0
10
10
20
35
CREW MASKS set to 100%
35
50
40
55
45
9 8
25 30
6
35
5
10 20 30 40 50 60 70 80 90 100
10 20 30 40 50 60 70 80 90 100
10
80
60
10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160
10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160
10 20 30 40 50 60 70 80 90 100 110 120 130
10
30
40 50
NUMBER OF PASSENGERS
40
DURATION — MINUTES
20 25
30
10
10
20
20
30
4
60 70
40
50 2
30 40
10 15 20 25
5 10 15 20
30
25
35
30
50 10
20
10
5 10 10
20
30
20
40
NUMBER OF PASSENGERS
50
30 40
60 70
50
1
80
20 30 40
200
300
400
500
0 600
700
50 70
40
35
DURATION — MINUTES
Example: OXY QTY........................500 LTR
Cabin Altitude ............ 25,000 feet
Passengers................................ 6
Duration ............ 20 min. @ 100% 22 min. @ NORM
EFFECTIVITY AircraftEFFECTIVITY 45-170 & on, and prior ALL Compensated aircraft with Altitude Oxygen System
25 30
60 Example
90
15 20
30
OXYGEN — LTR
S-6.1
15
20
5
30
10
30
10 20
5
25
20 30
15
0
CL-126B October 2004
OXYGEN QUANTITY MISSION PLANNING MINIMUM OXYGEN QUANTITY — LITERS (as required by regulations)
0 228
1 269
2 311
Number of Passengers 3 4 5 6 353 395 437 479
7 520
8 562
9 604
TIME (hours:minutes) Light face numbers indicate one crew member using oxygen above FL410 Bold face numbers indicate one crew member using oxygen above FL350
OXY QTY LTR 670 623 604 562 520 479 437 395 353 311 269 228 NOTE:
0 8:11 6:42 7:19 6:00 6:58 5:42 6:12 5:03 5:25 4:26 4:39 3:48 3:52 3:09 3:06 2:32 2:19 1:54 1:33 1:16 0:46 0:38 0:00 0:00
1 7:25 6:03 6:33 5:22 6:12 5:03 5:25 4:26 4:39 3:48 3:52 3:09 3:06 2:32 2:19 1:54 1:33 1:16 0:46 0:38 0:00 0:00
2 6:38 5:26 5:46 4:44 5:25 4:26 4:39 3:48 3:52 3:09 3:06 2:32 2:19 1:54 1:33 1:16 0:46 0:38 0:00 0:00
Number of Passengers 3 4 5 6 5:52 5:05 4:19 3:32 4:48 4:10 3:32 2:54 5:00 4:13 3:27 2:40 4:05 3:28 2:50 2:12 4:39 3:52 3:06 2:19 3:48 3:09 2:32 1:54 3:52 3:06 2:19 1:33 3:09 2:32 1:54 1:16 3:06 2:19 1:33 0:46 2:32 1:54 1:16 0:38 2:19 1:33 0:46 0:00 1:54 1:16 0:38 0:00 1:33 0:46 0:00 1:16 0:38 0:00 0:46 0:00 0:38 0:00 0:00 0:00
7 2:46 2:16 1:54 1:34 1:33 1:16 0:46 0:38 0:00 0:00
8 1:59 1:38 1:07 0:56 0:46 0:38 0:00 0:00
9 1:13 1:00 0:21 0:17 0:00 0:00
The time obtained from this table may exceed the fuel endurance available.
Conditions: • Cabin Pressure — Normal • One crew member using oxygen (crew mask in normal mode)
CL-126B October 2004
EFFECTIVITY EFFECTIVITY Aircraft 45-002 thru ALL 45-169 without Altitude Compensated Oxygen System
S-6.2 S-7
CREW NOTES
S-6.3 S-8
EFFECTIVITY ALL
CL-126B October 2004
OXYGEN QUANTITY MISSION PLANNING MINIMUM OXYGEN QUANTITY — LITERS (as required by regulations)
0 228
1 248
2 267
Number of Passengers 3 4 5 6 287 307 327 347
7 367
8 387
9 407
TIME (hours:minutes) Light face numbers indicate one crew member using oxygen above FL410 Bold face numbers indicate one crew member using oxygen above FL350
OXY QTY LTR 670 623 569 515 407 387 367 347 327 307 287 267 248 228 NOTE:
0 8:11 6:42 7:19 5:59 6:19 5:10 5:19 4:21 3:19 2:43 2:57 2:25 2:35 2:07 2:13 1:49 1:50 1:31 1:28 1:13 1:06 0:54 0:44 0:36 0:22 0:18 0:00 0:00
1 7:49 6:24 6:57 5:41 5:57 4:52 4:57 4:02 2:57 2:25 2:35 2:07 2:13 1:49 1:50 1:31 1:28 1:13 1:06 0:54 0:44 0:36 0:22 0:18 0:00 0:00
2 7:27 6:05 6:34 5:23 5:34 4:34 4:34 3:45 2:35 2:07 2:13 1:49 1:50 1:31 1:28 1:13 1:06 0:54 0:44 0:36 0:22 0:18 0:00 0:00
Number of Passengers 3 4 5 6 7:05 6:42 6:20 5:58 5:48 5:30 5:11 4:53 6:12 5:50 5:28 5:06 5:04 4:47 4:29 4:10 5:12 4:50 4:28 4:06 4:16 3:58 3:40 3:21 4:12 3:50 3:28 3:06 3:27 3:08 2:50 2:32 2:13 1:50 1:28 1:06 1:49 1:31 1:13 0:54 1:50 1:28 1:06 0:44 1:31 1:13 0:54 0:36 1:28 1:06 0:44 0:22 1:13 0:54 0:36 0:18 1:06 0:44 0:22 0:00 0:54 0:36 0:18 0:00 0:44 0:22 0:00 0:36 0:18 0:00 0:22 0:00 0:18 0:00 0:00 0:00
7 5:36 4:35 4:43 3:52 3:43 3:02 2:43 2:14 0:44 0:36 0:22 0:18 0:00 0:00
8 5:14 4:17 4:21 3:34 3:21 2:45 2:21 1:56 0:22 0:18 0:00 0:00
9 4:51 3:59 4:00 3:16 3:00 2:27 2:00 1:38 0:00 0:00
The time obtained from this table may exceed the fuel endurance available.
Conditions: • Cabin Pressure — Normal • One crew member using oxygen (crew mask in normal mode) CL-126B October 2004
EFFECTIVITY EFFECTIVITY ALL Aircraft 45-170 & on, and prior aircraft with Altitude Compensated Oxygen System
S-7.1 S-6.4
CREW NOTES
S-6.3 S-8
EFFECTIVITY ALL
CL-126B October 2004
CL-126B October 2004
ALL [R HEAT] WSHLD ** ICE DETECT [R PROBES HT] STBY PITOT
R BLEED, [TEMP CTRL] MAN R EMER PRESS
L ESS AV*
SPPR Baggage Lights Tailcone Utility Light TOILET Service Emergency Lighting
REAR HOT BUS
CLR DEL RAD OVRHD Cockpit Lights ENTRY Lights
R HOT BUS
R TAXI/LDG CTRL Light NAV LIGHT-FWD NAV LIGHTS-AFT
R GEN BUS
[DISPLAY] DU 3 [DISPLAY] DU 4
R ESS AV*
L TAXI/LDG CTRL Light
L GEN BUS
[DISPLAY] DU 1
***Main Battery Duration: Size 27 & 28 Amp-Hr: 30 Min. Size 38 Amp-Hr: 1 Hr
R FUEL FLOW [R IGN] CH A/B R CMPTR ** [R FIRE] DET [R REVERSER] DEPLOY, ANN, STOW R OIL PRESS/Temperature R QTY (Fuel) [R STBY PUMP] PWR/CTRL (Fuel) XFLOW VALVE CTRL (Fuel)
[R ESS BUS] BUS, VOLTS/START
R STALL WARN SPLR IND (Spoiler Indicator) R FLAP POS, FLAP CTRL [TRIM] PIT TRIM BIAS, SEC PITCH, RUD RUD FORCE R WHL MSTR
R SQUAT Switch OUTBD BRAKES/Anti-Skid BRAKE ACCUM PRESS
AUDIO 2 [RMU 2 PWR] SEC R WARN PANEL (CWP), FDR [DISPLAY] R CTRL IC/SG 2, ADC 2 [DAU 2] CH B [AHRS PWR] #1 SEC [AHRS PWR] #2 PRI
R ESS BUS
***Emergency Battery Duration: Size 10 Amp-Hr: 1 Hr
[R FIRE] EXT, FWSOV
R EMER HOT BUS
[L FIRE] EXT, FWSOV
L EMER HOT BUS
[EMER BUS] BUS, VOLTS [DAU 1] CH A [DAU 2] CH A [STBY] GYRO, ALT VIB GEAR Control Indicator PAX OXY [RMU 1 PWR] SEC INBD BRAKES/Anti-Skid [CKPT INSTRS] EMER PWR (Lights) R PRESS
EMER BATT BUS
* NOTE 1: L and R Essential Avionics Buses will also remain powered until L and R AV MSTR switches are selected OFF, as per AFM procedure. ** NOTE 2: AFM procedure calls for turning L & R WSHLD - OFF (until 5 min. before landing), L & R ENG CMPTR - MAN, and DU 2 - OFF. ** NOTE 3: Battery duration from time both generators are off.
Environmental/Pressurizatiom L BLEED, LEAK DETECT, PACK L EMER PRESS Anti-Icing [L HEAT] WSHLD ** Lights [COCKKPIT] FLOOD, MAP [CKPT INSTRS] L ESS PWR DOOR
Instrument/Avionics COMM 1, AUDIO 1/CLR DLY, CABIN PA, ADF 1, DME 1, NAV 1, FMS 1, ATC 1, [RMU 1 PWR] PRI [DISPLAY] L CTRL, DU 2** IC/SG 1, ADC 1 [DAU 1] CH B [AHRS PWR] #1 PRI, [AHRS PWR] #2 SEC CVR, L WARN PANEL (CWP) Landing Gear/Brakes L SQUAT Switch MAIN HYD PRESS Indicator [AUX HYD PUMP] PWR, CTRL [NOSE SYEER] MOTOR, CMPTR Flight Controls L STALL WARN SPLR CTRL (Spoiler Control) L FLAP POS [TRIM] AIL, PRI PITCH ELEV DISC (Disconnect) L WHL MSTR Electrical [L ESS BUS] BUS, VOLTS/START Engine L FUEL FLOW [L IGN] CH A/B L CMPTR ** [L FIRE] DET [L REVERSER] DEPLOY, ANN, STOW L OIL PRESS/Temperature L QTY (Fuel) [L STBY PUMP] PWR/CTRL (Fuel)
L ESS BUS
DC POWER DISTRIBUTION (Dual Generator Failure)
EFFECTIVITY
S-9
S-10
EFFECTIVITY ALL GCU
L MAIN BATT
20A (Tailcone)
REAR HOT BUS
EMER BATTERY POWER
BATTERY POWER
CIRCUIT BREAKER DIODE CONTACTOR
FUSE CURRENT SENSOR (SHUNT)
LEGEND
R MAIN BATT
R GEN BUS
OFF
R START GEN
OFF
R NON-ESS
R NON-ESS BUS
R MAIN AV BUS
R MAIN
R MAIN BUS
OFF
R AV MSTR
R ESS AV BUS
GCU
OFF
L START GEN
15A R HOT BUS (copilot's ELECTRICAL)
R HOT BUS
R EMER HOT BUS
15A (Nose Compartment)
EMER BATT
R ESS BUS 80A (copilot's ELECTRICAL)
R ESS BUS
R GEN
L GEN BUS
L HOT BUS 15A (pilot's ELECTRICAL)
L HOT BUS
L EMER HOT BUS
OFF
EMER
EMER BATT
EMER BUS 15A (pilot's ELECTRICAL)
EMER BATT BUS
OFF OFF
OFF
OFF
L ESS BUS 80A (pilot's ELECTRICAL)
L ESS BUS
L GEN
L MAIN
L MAIN BUS
L NON-ESS
L NON-ESS BUS
L MAIN AV BUS
OFF
L AV MSTR
L ESS AV BUS
ELECTRICAL SYSTEM (Dual Generator Failure)
CL-126B October 2004
CL-126B October 2004
ALL
L ESSENTIAL* CONTACTOR
20A
15A (COCKPIT)
MAN
BUS-TIE
L HOT BUS
REAR HOT BUS
CIRCUIT BREAKER
15A (COCKPIT)
R HOT BUS
APU START GEN
R MAIN BATT
R GEN BUS
R ESSENTIAL* CONTACTOR
OFF
R BATT
OFF
R MAIN
R START GEN
OFF
R GEN
OFF
R NON-ESS
R NON-ESS BUS
R MAIN AV BUS
OFF
R AV MSTR
GCU
GEN/GPU/APU POWER
BATTERY POWER
*
DIODE CONTACTOR
FUSE CURRENT SENSOR (SHUNT)
AUTO OPN ONLY
LEGEND
GCU
ON
ANTI–FLASH CONTACTOR
GPU
35A
R MAIN BUS
35A
R ESS AV BUS
ON
L MAIN BATT
R EMER HOT BUS
ON AVAIL
ON AVAIL
APU GEN
RUN
START
START/STOP
EXT PWR 15A
EMER BATT
R ISOLATION* CONTACTOR
80A
R ESS BUS
R START
OFF
OFF
EMER
EMER BATT
L EMER HOT BUS
L ISOLATION* CONTACTOR
15A
EMER BATT BUS
L START
L BATT
80A
L ESS BUS
L GEN BUS
OFF OFF
OFF
OFF
L GEN
L MAIN
L NON-ESS
L START GEN
35A
L MAIN BUS
35A
L NON-ESS BUS
L MAIN AV BUS
OFF
L AV MSTR
L ESS AV BUS
ELECTRICAL SYSTEM (Normal)
EFFECTIVITY
S-11
ENGINE FIRE EXTINGUISHING SYSTEM
L ENGINE EXTINGUISHER #1 #2
ARMED
ARMED
BLEED AIR SHUTOFF VALVE
FUEL SHUTOFF VALVE
FIRE
FIRE
CLOSED
CLOSED
FIRE PUSH
FIRE PUSH
PRESSURE GAGE
PRESSURE GAGE
TWO-WAY CHECK VALVES
CONTAINER #1 RELIEF VALVE
LH NACELLE
CONTAINER #2
R ENGINE EXTINGUISHER #2 #1
ARMED
ARMED
BLEED AIR SHUTOFF VALVE
FUEL SHUTOFF VALVE
RELIEF VALVE HYDRAULIC SHUTOFF VALVE
HYDRAULIC SHUTOFF VALVE
RH NACELLE
TR ISOLATION VALVE
TR ISOLATION VALVE
LEGEND ENGINE DISCHARGE MANUAL DISCHARGE THERMAL DISCHARGE THERMAL DISCHARGE INDICATOR
S-12
EFFECTIVITY ALL
MANUAL DISCHARGE INDICATOR
CL-126B October 2004
BLEED AIR SYSTEM
RIGHT ENGINE
LEGEND HP BLEED AIR
HP BLEED PORTS
LP BLEED AIR HP PRESS SW (130 PSI)
HP/LP BLEED AIR CONDITIONED AIR
LP BLEED PORT
VALVE NAC A/I VALVE
CHECK VALVE TEMP/PRESS SENSOR
A/I PRSOV
PYLON TEMP SENSOR ON
ELECTRICAL
R NAC ECS CONTROLLER
R BLEED 28 VDC
3
EMER PRESS VALVE
HP SOV 1
680° F
ECS PRSOV CPCS
RIGHT CH
PACK BI-LEVEL PRSOV
EXHAUST
COCKPIT
WING LOAD CONTROL ANTI-ICE VALVE
RH CABIN
APU BLEED PACK
ON
PACK LEFT CH
OFF
APU
HI FLOW
28 VDC L BLEED ON
WING/STAB
LH CABIN COCKPIT/ CABIN GASPERS
STAB ANTI-ICE
2
RAM AIR
ON
A/I CONTROL CIRCUIT
ON
ECS PRSOV 3
EMER PRESS VALVE
1
680° F HP SOV
EMER PRESS
L NAC ON
OFF
A/I PRSOV
OFF
NAC A/I VALVE
L BLEED R BLEED
CAS MESSAGES 1
"LR BLEED OVHT" > 680°F
2
"PACK HIGH FLOW"
3
"LR EMER PRESS" ON "LR ENG PYLON OVHT" > 250° F
CL-126B October 2004
HP PRESS SW (130 PSI)
LP BLEED PORT
HP BLEED PORTS
LEFT ENGINE
EFFECTIVITY ALL
S-13
EFFECTIVITY ALL C
ELEC
CKPT
HYD
ECS
OXY C +10 OXY PSI 1800
CABIN RATE DELTA P CABIN ALT
FUEL
1000 9.4 8750
CAS
MANUAL RATE 2200 LDG ALT 10 000
FLT
50
35
N
38
3
28.0
315 47.0
300 TAS +15 SAT 245 GSPD
R ESS VOLT
50
Honeywell
M/P FLT FUEL RNG
R GEN APU A 0 AMPS 200 AMPS
BATT TEMPS C
28.0
EMER BUS VOLTS
KDVT #TOC FL300
*PBD01 LL01
RTN SUMRY ELEC HYD ECS
GEN L 200AMPS
28.2
PLAB1
33
CHK EICAS
360 MAG2
MFD
PLAB2
L ESS VOLT
STAB TGT WX -16
25
FMS1 KDVT 12.5 NM 12 MIN
Honeywell
HOT
CONDITIONED AIR (HEAT)
CONDITIONED AIR (COLD)
LH SIDE CABIN
GASPERS CKPT & CABIN 2
CABIN TEMP SENSOR/FAN
2
RH SIDE CABIN
COCKPIT
1
2 "CAB DUCT OVHT" > 300° F
1 "CKPT DUCT OVHT" > 300° F
CAS MESSAGES
OVER TEMP LIMITER
LP BLEED-AIR HP/LP BLEED-AIR
TEMP SENSOR
LEGEND
COCKPIT TEMP SENSOR
SUMRY
CABN
TEMP CONT H
CAB TEMP 78 F
6.5
FLAPS
LBS
4450 20
-15
SAT C PITCH TRIM
60 1002
OIL C FF PPH
60
END
L R BLEED AIR LEAK L R ENG PYLON OVHT L R BLEED OVHT L R CAB DUCT OVHT L R CKPT DUCT OVHT L R EMER PRESS ON
984
80
76
FUEL
50.0
550
50.0
L 1700 F 1000 R 1750
75.0
550
N1
ITT
N2 OIL PSI
75.0
EICAS
COLD
CABIN TEMPERATURE
6
HP BLEED-AIR
ON
MANUAL TEMP
INTEGRATED ECS TEMP CONTROLLER
AFT PRESSURE BULKHEAD (REF)
EMER PRESS VALVE
RAM AIR
EMER PRESS VALVE
LP
PACK BI-LEVEL PRSOV
ENGINE BLEED-AIR
ECS PRSOV
PACK
EXHAUST
CAB TEMP CONT VALVE
RAM AIR
ECS PRSOV
ENGINE BLEED-AIR
CKPT TEMP CONT VALVE
LP
HP
HP SOV
FROM APU
HP SOV
HP
;; ; ;;; ;;;;; ;;; ; ; ; ; ; HOT
COCKPIT TEMPERATURE
30
S-14 COLD
; ; TEMPERATURE CONTROL SYSTEM
CL-126B October 2004
CL-126B October 2004
ALL PRI OUTFLOW VALVE
SEC OUTFLOW VALVE
CABIN AIR
DISCHARGE JET PUMP
TORQUE MOTOR
CABIN ALT LIMITER (13,700 FT.)
DELTA P LIMITERS (9.7 PSID)
CABIN ALT LIMITER (13,700 FT.)
TORQUE MOTOR
ENGINE SERVO BLEED-AIR
UP EMER DEPRESS
DN
ON
OFF OFF
ON
UP
ON
MANUAL PRESS
MANUAL
EMER BATT BUS
L PRESS
L MAIN BUS
THROTTLE SW (82% N1)
LDG GEAR SW
ADC1/ADC2
CABIN PRESSURE
ACM BYPASS RELAY (40,000 FT.)
R PRESS
THROTTLE SW (82% N1)
LDG GEAR SW
CABIN PRESSURE CONTROLLER
APU BLEED
DN
LDG ALT
PSID FT CAB ALT
FPM
DELTA P
CAB RATE
R BLEED
ON
HI FLOW
OFF
PACK
ON
CABIN PRESSURE CONTROL
PRESSURIZATION
PRIMARY (LEFT) CHANNEL
SECONDARY (RIGHT) CHANNEL
L BLEED
ON
EMER PRESS
OFF
DEPLOY
PAX OXYGEN OXY/AUTO
PAX
EMER PRESSURE 9,500 FT. OR 14,500 FT.
"CABIN ALTITUDE" CABIN ALTITUDE (CAS) CABIN ALT (CWP) 10,000 FT. OR 14,500 FT.
CABIN OXYGEN ON 14,500 FT.
EICAS
CABIN PRESSURE ADC1/ADC2
PRESSURIZATION SYSTEM
EFFECTIVITY
S-15
FORWARD PRESSURE BULKHEAD
FUEL SYSTEM FUEL L STBY XFLOW R STBY
ON
ON
COLLECTOR TANK
COLLECTOR TANK CROSSFLOW VALVE
1680# LEFT WING FUEL TANK
1680# RIGHT WING FUEL TANK
SHUTOFF VALVES
FILLER PORT
FUSELAGE FUEL TANK 2700#
LEFT ENGINE
RIGHT ENGINE
SPPR ADAPTER
LEGEND ENGINE DRIVEN FUEL PUMP
FUEL FILTER
MOTOR DRIVEN VALVE
PRESSURE SWITCH
STANDBY PUMP
CHECK VALVE
FLOAT SWITCH
JET PUMP
LOW FUEL SENSOR
HIGH PRESSURE
FUEL
4250
LOW PRESSURE
LBS
4250 LBS
495 USED
L STBY
CLOSED
ON
ON M A N
R STBY
FIRE
ON
CLOSED FIRE PUSH
TOTALIZER RESET
OFF
EDS RECORD
R ENG CMPTR
ENG SYNC N1
APR
N2
ARM
ON
OFF
M A N OFF
R ENG
FUEL SYSTEM SCHEMATIC ON EICAS/MFD DISPLAY
S-16
XFLOW
L ENG CMPTR
R WING 1650 FUSELAGE 1000
L ENG
FIRE
FIRE PUSH
FUEL QUANTITY INDICATION ON EICAS
TOTAL
TRANSFER
FUEL
L 1600 F 1000 R 1650
L WING 1600
STORAGE
EFFECTIVITY ALL
ENGINE/FUEL CONTROL PANEL
CL-126B October 2004
CL-126B October 2004
ALL MAIN HYD PRESS BRK ACUM PRESS
6 7
AUX HYD QTY LOW MAIN HYD PRESS B-ACUM
4 6 7
EICAS/MFD SUMRY HYD INDICATIONS
AUX HYD QTY LO MAIN HYDQTY LO
AUX HYD PUMP LO
3
5
L HYD PUMP LOW
2
4
R HYD PUMP LOW
1
CAS MESSAGES
LDG GEAR FREE-FALL LEVER
DOOR CONTROL VALVE
LDG GEAR CONTROL VALVE
LANDING GEAR CONTROL VALVE MODULE
AUX
MAIN
EMER/PARK BRAKE PRESSURE
BRAKES
MAIN/AUX
HYD XFLOW
FLAP DRIVE
EMER/PARK BRAKE VALVE
7
BRAKE ACCUM
SPOILERS/ SPOILERONS MAIN SYSTEM ACCUM
6
1
SUPPLY BLEED AIR
MECHANICAL
AUX PRESSURE
MAIN RETURN
MAIN PRESSURE
HYD FLUID LEVEL SENSOR
RESERVOIR FULL (GSP INDICATOR)
AUX RETURN
DC MOTOR DRIVEN AUX PUMP
FIRE PUSH
CLOSED
SHUTOFF VALVES
4
5
OVERFULL (GSP INDICATOR)
ELECTRICAL
LEGEND
ON
AUX HYD
ENGINE PUMPS
FIRE PUSH
CLOSED
PASS THROUGH
PRESS MODULE
PRESSURE TRANSDUCER
EMERGENCY/ PARKING BRAKE
AUX FILTER MANIFOLD
3
GROUND SERVICING VALVE
2
MAIN FILTER MANIFOLD
TR'S
ENGINE BLEED AIR
HYDRAULIC SYSTEM
SOL
EFFECTIVITY
S-17
S-18
EFFECTIVITY ALL L HYD PUMP LOW AUX HYD PUMP LO AUX HYD QTY LO MAIN HYDQTY LO MAIN HYD PRESS BRK ACUM PRESS
2 3 4 5 6 7
AUX HYD QTY LOW MAIN HYD PRESS B-ACUM
4 6 7
EICAS/MFD SUMRY HYD INDICATIONS
R HYD PUMP LOW
1
CAS MESSAGES
LDG GEAR FREE-FALL LEVER
DOOR CONTROL VALVE
LDG GEAR CONTROL VALVE
LANDING GEAR CONTROL VALVE MODULE
AUX
MAIN
EMER/PARK BRAKE PRESSURE
BRAKES
MAIN/AUX
ON
HYD XFLOW
FLAP DRIVE
EMER/PARK BRAKE VALVE
7
BRAKE ACCUM
SHUTTLE VALVE
SPOILERS/ SPOILERONS
6
MAIN SYSTEM ACCUM
1
SUPPLY BLEED AIR
MECHANICAL
AUX PRESSURE
MAIN RETURN
MAIN PRESSURE
HYD FLUID LEVEL SENSOR
AUX RETURN
DC MOTOR DRIVEN AUX PUMP
FIRE PUSH
CLOSED
SHUTOFF VALVES
4
5
RESERVOIR FULL (GSP INDICATOR)
OVERFULL (GSP INDICATOR)
ELECTRICAL
LEGEND
ON
AUX HYD
ENGINE PUMPS
FIRE PUSH
CLOSED
PRESS MODULE
PRESSURE TRANSDUCER
EMERGENCY/ PARKING BRAKE
AUX FILTER MANIFOLD
3
GROUND SERVICING VALVE
2
MAIN FILTER MANIFOLD
TR'S
ENGINE BLEED AIR
HYDRAULIC SYSTEM HYD XFLOW ON
SOL
CL-126B October 2004
CL-126B October 2004 MECHANICAL
ELECTRICAL
AUX RETURN HYD
AUX HYD PRESS
MAIN RETURN HYD
MAIN HYD PRESS
LEGEND
SOL EXTEND
DOOR CONTROL VALVE
EXTEND
SOL
RETRACT
SOL
FREE-FALL VALVE
RETRACT
LDG GEAR CONTROL VALVE
LANDING GEAR CONTROL VALVE MODULE
SOL
HYD XFLOW VALVE
FLAP DRIVE
ALL
VLO 200 VLE 260
DN
UP
R
DOWN
DOWN
DOWN
L
N
GEAR / HYD
CENTER PEDESTAL
HYD XFLOW
ON
AUX HYD
ANTI-SKID
ON
NOSE STEER
LANDING GEAR FREE-FALL LEVER
LANDING GEAR EXTENDED
SOL
EFFECTIVITY
S-19
S-20 MECHANICAL
ELECTRICAL
AUX RETURN HYD
AUX HYD PRESS
MAIN RETURN HYD
MAIN HYD PRESS
LEGEND
SOL
SOL
EXTEND
DOOR CONTROL VALVE
EXTEND
SOL
RETRACT
SOL
FREE-FALL VALVE
RETRACT
LDG GEAR CONTROL VALVE
LANDING GEAR CONTROL VALVE MODULE
HYD XFLOW VALVE
FLAP DRIVE
EFFECTIVITY ALL
VLO 200 VLE 260
L
DN
UP
R
DOWN
DOWN
N
GEAR / HYD
CENTER PEDESTAL
HYD XFLOW
AUX HYD
ANTI-SKID
NOSE STEER
LANDING GEAR FREE-FALL LEVER
LANDING GEAR RETRACTED
SOL
CL-126B October 2004
BRAKE SYSTEM
EICAS/CWP PILOT
COPILOT
PEDAL TRANSDUCERS (4) SQUAT SWITCH LEGEND MAIN HYD SYSTEM PRESS METERED BRAKE PRESS
BRAKE CONTROL UNIT (BCU)
SQUAT SWITCH
PRESSURE XDUCER
OFF ANTI-SKID MAIN PRESSURE
PRESSURE XDUCER
RETURN AUX HYD SYSTEM PRESS
RETURN
ELECTRICAL BRAKE SHUTOFF VALVES
MECHANICAL CHECK VALVE BRAKE ACCUM TRANSDUCER BRAKE FUSE
INBOARD BRAKE CONTROL VALVES (3) (2)
OUTBOARD BRAKE CONTROL VALVES (1) (4)
AUX PRESSURE
BRAKE ACCUMULATOR
EMERGENCY/ PARKING BRAKE
EMERGENCY/ PARKING BRAKE VALVE PRESSURE TRANSDUCERS (4)
BRAKE FUSES (5) WHEEL SPEED TRANSDUCERS (4)
CL-126B October 2004
EFFECTIVITY ALL
S-21
APU OPERATING PROCEDURES These procedures are intended for start-up and shutdown of the APU separate from the airplane normal checklist. If the APU is operated in line with the airplane normal checklist, refer to the Normal Procedures Checklist for the appropriate procedures.
APU PRE-START CHECK 1. 2. 3. 4.
5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17.
L & R BATT .........................................................On, Simultaneously EMER BATT............................................................................ EMER APU MASTER.............................................................................. ON Tailcone Interior Check: a. OIL TEST ........................................... Select & Check Indicator b. APU FAN FAIL..................................................................Check c. APU Fire Bottle.................................................................Check APU Exhaust............................................................................. Clear APU Inlet................................................................................... Clear APU Firebox Drains ................................................................ Check Fuel Quantity (right wing)........................................................ Check PACK Circuit Breaker (pilot’s ENVIRONMENTAL group) ............ Set APU Circuit Breakers (copilot’s APU group) ................................ Set L & R BLEED Circuit Breakers (pilot’s and copilot’s ENVIRONMENTAL & ENVIR group) ........... Set MAN & AUTO Circuit Breakers (copilot’s ENVIR group) ............. Set L & R BLEED ............................................................................. OFF PACK ......................................................................................... OFF HI FLOW ....................................................................................... Off MANUAL TEMP ............................................................................ Off COCKPIT & CABIN TEMPERATURE COLD-HOT ................................................ Mid (12 o’clock) Position
APU START UP 1. L INSTR Lights..............................................................................On 2. BCN/STROBE............................................................................ BCN 3. APU Fire Detection System ........................................................ Test a. SYSTEM TEST ................................... FIRE DET, Press & Hold b. Verify: - APU FIRE red CAS activates. - Master WARN tone & lights activate. - APU FIRE switch/indicator illuminates. - APU fire warning horn will sound after 13 to 18 seconds. c. SYSTEM TEST .............................................................Release 4. APU START/STOP ................................................. Press & Release 5. APU GEN..................................................................................... ON 6. APU BLEED................................................................................. ON 7. PACK ............................................................................................On
S-22
EFFECTIVITY ALL
CL-126B October 2004
APU SHUTDOWN 1. 2. 3. 4. 5.
APU START/STOP ................................................. Press & Release APU MASTER (after 30-second delay) ........................................ Off BCN/STROBE ............................................................................OFF EMER BATT ...............................................................................OFF L & R BATT.................................................................................OFF
CL-126B October 2004
EFFECTIVITY ALL
S-23
Master EICAS Index This GO/NO GO guide contains data for quick reference. This guide in no way supersedes data outlined in the current Minimum Equipment List. In case of conflict, the MEL takes precedence. After performing the applicable checklist procedure and the message persists, check dispatchability as follows: CAS or (EI) Message AHRS 1 BASIC AHRS 2 BASIC AHRS 1-2 BASIC AHRS 1 OVHT AHRS 2 OVHT AHRS 1-2 OVHT ANTI-SKID FAIL L AOA HT FAIL R AOA HT FAIL LR AOA HT FAIL AP AIL MISTRIM AP ELEV MISTRIM AP ELEV MISTRIM APR (EI) APR (EI outbd N1s) L APR FAULT R APR FAULT LR APR FAULT APR ON (EI inbd N1s) APU AVAILABLE APU AMPS HIGH APU FAIL APU FIRE AUTOSPLR ARMED AUX HYD PMP LO AUX HYD QTY LO L BATT OVHT R BATT OVHT L BATT OVHT R BATT OVHT LR BATT OVHT
S-24
Tab
NO GO or MEL RELIEF
A/S-18 A/S-18 A/S-18 19 19 19 29 1 1 1 3 3 A/S-8 A/S-12 A/S-12 A/S-9 A/S-9 A/S-9 A/S-12 A/S-8 3 4 1 A/S-13 18 18 3 3 4 4 4
N/A N/A N/A NO GO NO GO NO GO 32-1 30-1 30-1 30-1 NO GO NO GO NO GO N/A N/A 76-3 76-3 76-3 N/A N/A NO GO NO GO NO GO N/A NO GO NO GO NO GO NO GO NO GO NO GO NO GO
EFFECTIVITY ALL
CL-126B October 2004
Master EICAS Index (Cont) Tab
NO GO or MEL RELIEF
7 7 7 11 11 11 A/S-24 18 A/S-9 A/S-9 11 11 12 A/S-13 A/S-13 12 A/S-13 5 12 A/S-25 A/S-25 A/S-25 A/S-18 12 19 29 A/S-24 19 19 19 19 19 19 A/S-18 A/S-18 20 20 20 20
NO GO NO GO NO GO NO GO NO GO NO GO N/A NO GO N/A N/A NO GO NO GO NO GO 21-1 21-1 NO GO N/A NO GO NO GO N/A N/A N/A N/A NO GO NO GO NO GO 23-16 NO GO NO GO NO GO NO GO NO GO NO GO N/A N/A NO GO NO GO NO GO NO GO
CAS or (EI) Message L R LR L R LR
BLEED AIR LEAK BLEED AIR LEAK BLEED AIR LEAK BLEED OVHT BLEED OVHT BLEED OVHT BRAKE FAULT BRK ACUM PRESS BUS TIE CLSD BUS TIE MANUAL CAB DELTA P CAB DUCT OVHT LR CAB PRESS FAIL L CAB PRESS FAIL R CAB PRESS FAIL CAB PRESS MAN CAB PRESS MAN CABIN ALTITUDE CABIN ALTITUDE L CHECK EDS R CHECK EDS LR CHECK EDS CKLST MISMATCH CKPT DUCT OVHT CNFG MISMATCH CPLT BRK FAULT CVR FAIL DAU 1A FAIL DAU 1B FAIL DAU 1A-1B FAIL DAU 2A FAIL DAU 2B FAIL DAU 2A-2B FAIL DAU A REV DAU B REV L DAU ENG MISCMP R DAU ENG MISCMP L DAU SYS MISCMP R DAU SYS MISCMP CL-126B October 2004
EFFECTIVITY ALL
S-25
Master EICAS Index (Cont) CAS or (EI) Message
LR L R L R
L R LR
L R LR L R LR
S-26
DEFUEL OPEN DEP (EI) DEP (EI) DU 1 OVHT DU 2 OVHT DU 3 OVHT DU 4 OVHT DU 1 FAN FAIL DU 2 FAN FAIL DU 1-2 FAN FAIL DU 3 FAN FAIL DU 4 FAN FAIL DU 3-4 FAN FAIL ECS FAIL ECS FAULT ECS FAULT ECS FAULT ECS FAULT EICAS CHK (MFD) ELEVATOR DISC ELEVATOR DISC EMER BATT LOW EMER BUS VOLTS EMER DEPRESS EMER LIGHTS EMER LIGHTS EMER PRESS ON EMER PRESS ON EMER PRESS ON EMER/PARK BRK EMER/PARK BRK EMERGENCY EXIT ENG FIRE FAIL ENG FIRE FAIL ENG FIRE FAIL ENG FIRE FAIL ENG FIRE FAIL ENG FIRE FAIL
Tab
NO GO or MEL RELIEF
16 14 A/S-12 20 20 20 20 A/S-18 A/S-18 A/S-18 A/S-19 A/S-19 A/S-19 12 13 13 A/S-13 A/S-13 24 14 A/S-14 4 5 A/S-13 6 A/S-24 13 13 13 14 A/S-24 4 6 6 6 A/S-9 A/S-9 A/S-9
NO GO NO GO N/A NO GO NO GO NO GO NO GO NO GO NO GO NO GO NO GO NO GO NO GO NO GO NO GO NO GO N/A N/A NO GO NO GO N/A NO GO NO GO N/A N/A N/A N/A N/A N/A N/A N/A 52-1 NO GO NO GO NO GO N/A N/A N/A
EFFECTIVITY ALL
CL-126B October 2004 Change 1
Change 1
Master EICAS Index (Cont) Tab
NO GO or MEL RELIEF
8 8 8 A/S-10 A/S-10 A/S-10 A/S-10 A/S-10 A/S-10 6 6 6 A/S-10 A/S-10 A/S-10 6 6 6 A/S-11 A/S-11 A/S-11 3 A/S-8 5 5 5 A/S-9 A/S-9 A/S-9 5 5 5 4 A/S-9 A/S-24 5 14 14
NO GO NO GO NO GO N/A N/A N/A N/A N/A N/A NO GO NO GO NO GO N/A N/A N/A NO GO NO GO NO GO N/A N/A N/A 52-1 52-1 NO GO NO GO NO GO N/A N/A N/A NO GO NO GO NO GO 52-1 N/A 31-4 N/A NO GO NO GO
CAS or (EI) Message L R LR L R LR L R LR L R LR L R LR L R LR L R LR
ENG PYLON OVHT ENG PYLON OVHT ENG PYLON OVHT ENG SHUTDOWN ENG SHUTDOWN ENG SHUTDOWN ENG VIB MON ENG VIB MON ENG VIB MON ENGCMPTR FAULT ENGCMPTR FAULT ENGCMPTR FAULT ENGCMPTR FAULT ENGCMPTR FAULT ENGCMPTR FAULT ENGINE CHIP ENGINE CHIP ENGINE CHIP ENGINE CHIP ENGINE CHIP ENGINE CHIP ENTRY DOOR ENTRY DOOR PIN L ESS BUS FAULT R ESS BUS FAULT LR ESS BUS FAULT L ESS BUS FAULT R ESS BUS FAULT LR ESS BUS FAULT L ESS BUS VOLTS R ESS BUS VOLTS LR ESS BUS VOLTS EXTERNAL DOORS EXTERNAL POWER FDR FAIL FIRE (EI) FLAPS FAIL FLAPS FAULT
CL-126B October 2004 Change 1
EFFECTIVITY ALL
S-27
Master EICAS Index (Cont) CAS or (EI) Message L R LR L R LR L R LR L R LR L R LR L R LR L R L R LR
L R LR L R LR
L R LR
S-28
FUEL BAY LOW FUEL BAY LOW FUEL BAY LOW FUEL FILTER FUEL FILTER FUEL FILTER FUEL FILTER FUEL FILTER FUEL FILTER FUEL HEATER FUEL HEATER FUEL HEATER FUEL HEATER FUEL HEATER FUEL HEATER FUEL IMBALANCE FUEL PRESS LOW FUEL PRESS LOW FUEL PRESS LOW FUEL QTY FAULT FUEL QTY FAULT FUEL QTY FAULT FUEL QTY LOW FUEL QTY LOW FUEL QTY LOW FUEL XFLO FUEL XFLO OPEN FWSOV CLSD FWSOV CLSD FWSOV CLSD FWSOV FAULT FWSOV FAULT FWSOV FAULT GEAR GEAR GEN AMPS HIGH GEN AMPS HIGH GEN AMPS HIGH
Tab
NO GO or MEL RELIEF
A/S-16 A/S-16 A/S-16 16 16 16 A/S-16 A/S-16 A/S-16 17 17 17 A/S-16 A/S-16 A/S-16 17 10 10 10 A/S-16 A/S-16 A/S-16 17 17 17 17 A/S-16 A/S-17 A/S-17 A/S-17 17 17 17 12 29 6 6 6
N/A N/A N/A NO GO NO GO NO GO N/A N/A N/A NO GO NO GO NO GO NO GO NO GO NO GO N/A NO GO NO GO NO GO 28-4 28-3 NO GO N/A N/A N/A NO GO N/A N/A N/A N/A NO GO NO GO NO GO N/A N/A N/A N/A N/A
EFFECTIVITY ALL
CL-126B October 2004 Change 1
Master EICAS Index (Cont) Tab
NO GO or MEL RELIEF
3 6 6 A/S-20 A/S-20 A/S-20 A/S-20 A/S-20 A/S-17 A/S-17 A/S-17 A/S-17 21 21 21 A/S-20 A/S-20 A/S-20 A/S-20 A/S-20 A/S-21 A/S-21 A/S-21 1 1 A/S-7 9 A/S-12 A/S-12 30 30 30 A/S-21 21 A/S-21 14 A/S-8 18 A/S-17
NO GO NO GO NO GO 34-15 34-15 N/A N/A 34-15 NO GO NO GO NO GO N/A NO GO NO GO NO GO N/A N/A NO GO NO GO NO GO NO GO NO GO NO GO 30-12 N/A N/A NO GO 74-1 N/A NO GO NO GO NO GO N/A NO GO N/A 22-2 22-2 NO GO NO GO
CAS or (EI) Message LR GEN FAIL L GEN FAIL R GEN FAIL GND PROX FAIL GPWS FAIL GPWS FLAP OVRD GPWS G/S INHB GPWS SYS FAIL L HYD PUMP LOW R HYD PUMP LOW LR HYD PUMP LOW HYD XFLOW ON IC 1 OVHT IC 2 OVHT IC BUS FAIL IC 1 CNFG FAIL IC 2 CNFG FAIL IC 1 FAN FAIL IC 2 FAN FAIL IC 1-2 FAN FAIL IC 1 WOW INOP IC 2 WOW INOP IC 1-2 WOW INOP ICE DET FAIL ICE DETECTED ICE DETECTED IGN (EI) IGN (EI) IGN (EI) L INBD BRK FAIL R INBD BRK FAIL LR INBD BRK FAIL INSTR PNL TEMP LBS/KGS CONFIG LBS/KGS CONFIG MACH TRIM FAIL MACH TRIM FAIL MAIN HYD PRESS MAIN HYDQTY LO CL-126B October 2004
EFFECTIVITY ALL
S-29
Master EICAS Index (Cont) CAS or (EI) Message
L R LR L R LR
L R LR L R LR L R L R LR
L R LR
S-30
MAN (EI) MAN (EI) MCR (EI) MCT (EI) NAC (EI) NAC (EI) NAC HT NAC HT NAC HT NAC HT FAIL ON NAC HT FAIL ON NAC HT FAIL ON NORM BRK FAIL NOSE BAY TEMP NWS FAIL NWS FAULT OIL FILTER OIL FILTER OIL FILTER OIL FILTER OIL FILTER OIL FILTER OIL PRESS LOW OIL PRESS LOW OUTBD BRK FAIL OUTBD BRK FAIL OUTBD BRK FAIL OXYGEN OFF OXYGEN QTY LOW OXY PRESS HI PACK HIGH FLOW PACK OVHT PAX OXY DEPLOY PAX OXY FAIL PFD CHECK PFD CHECK PFD CHECK PIT TRIM BIAS PIT TRIM BIAS
Tab
NO GO or MEL RELIEF
9 A/S-12 A/S-12 A/S-12 9 A/S-12 1 1 1 1 1 1 12 A/S-21 30 A/S-24 6 6 6 A/S-11 A/S-11 A/S-11 6 6 30 30 30 13 13 14 A/S-13 14 A/S-13 14 21 21 21 14 A/S-14
NO GO NO GO N/A N/A 30-7 N/A 30-7 30-7 30-7 N/A N/A N/A NO GO N/A 32-2 32-2 NO GO NO GO NO GO N/A N/A N/A NO GO NO GO NO GO NO GO NO GO NO GO N/A NO GO N/A 21-6 N/A 35-3 NO GO NO GO NO GO NO GO NO GO
EFFECTIVITY ALL
CL-126B October 2004 Change 1
Change 1
Master EICAS Index (Cont) Tab
NO GO or MEL RELIEF
14 A/S-14 A/S-14 1 1
NO GO NO GO N/A 30-9 30-9
LR PITOT HT PLT BRK FAULT PRI TRIM FAIL PRI TRIM FAULT REV (EI) REV (EI)
1 30 15 A/S-14 9 A/S-12
30-9 NO GO NO GO NO GO NO GO N/A
L R LR L R LR L R
REV AUTOSTOW REV AUTOSTOW REV AUTOSTOW REV FAULT REV FAULT REV FAULT REV UNSAFE (CWP) REV UNSAFE (CWP) ROLL DISC ROLL DISC RUD BOOST INOP
A/S-25 A/S-25 A/S-25 A/S-25 A/S-25 A/S-25 14 14 15 A/S-14 15
N/A N/A N/A 78-1 78-1 78-1 78-1 78-1 NO GO N/A NO GO
RUD BOOST INOP SAT HT FAIL SEC PITCH TRIM SEC TRIM FAIL SEC TRIM FAULT SPOILER JAM
A/S-8 1 A/S-14 15 A/S-15 16
N/A 30-2 N/A NO GO NO GO NO GO
R SPOILER JAM LR SPOILER JAM SPOILERS EXT SPOILERS EXT SPOILERS EXT SPOILERS FAIL STAB OVHT STAB TEMP LOW STAB TMP FAULT L STALLWARN FAIL R STALLWARN FAIL
16 16 14 15 A/S-15 15 1 2 A/S-7 16 16
NO GO NO GO N/A N/A N/A NO GO NO GO 30-4 30-4 NO GO NO GO
CAS or (EI) Message
L R
L
CL-126B October 2004
PIT TRIM MISCMP PIT TRIM MSCMP PITCH TRIM OFF PITOT HT PITOT HT
EFFECTIVITY ALL
S-31
Master EICAS Index (Cont) CAS or (EI) Message LR STALLWARN FAIL
NO GO or MEL RELIEF
16
NO GO
START (EI) START (EI) STBY PITOT HT L STBY PUMP ON R STBY PUMP ON LR STBY PUMP ON
9 A/S-12 2 A/S-17 A/S-17 A/S-17
NO GO N/A 30-9 N/A N/A N/A
SYNC (EI) SYNC (EI) T/O (EI) TAKEOFF TRIM TAKEOFF TRIM TERR FAIL TERR INHB TERR INHIB UNL (EI) UNL (EI) WARN AUDIO
10 A/S-12 A/S-12 14 A/S-15 A/S-21 A/S-22 A/S-22 14 10 21
N/A N/A N/A N/A N/A 34-15 N/A N/A 78-1 N/A NO GO
A/S-26 21 A/S-26 A/S-26 A/S-7 A/S-15
NO GO NO GO NO GO NO GO N/A N/A
L
WINDSHEAR FAIL WING OVHT WING TEMP LOW WING TMP FAULT WING/STAB LEAK WSHLD HT FAIL
A/S-22 1 2 A/S-7 1 2
34-15 NO GO 30-4 30-4 NO GO 30-10
R LR L R LR L R LR
WSHLD HT FAIL WSHLD HT FAIL WSHLD HT FAULT WSHLD HT FAULT WSHLD HT FAULT WSHLD OVHT WSHLD OVHT WSHLD OVHT
2 2 A/S-7 A/S-7 A/S-7 3 3 3
30-10 30-10 30-10 30-10 30-10 NO GO NO GO NO GO
WARN AUDIO LR WARN PWR FAIL L WARN PWR FAIL R WARN PWR FAIL WG/STAB HT OK WHEEL MSTR
S-32
Tab
EFFECTIVITY ALL
CL-126B October 2004
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