LTN-92 Pilots Guide

TP92-04138

Pilot's Guide LTN - 92 Inertial Navigation System Basic /World Wide Data Base Program 92-0413

June 1995 Revision 3: April 1998

Litton Aero Products

Table of Contents Section

Title

Section 1

General System Description 1-1 Navigation Data Storage 1-4 Synthetic Magnetic Variation 1-4 Multiple System Operation 1-5 Mode Selector Unit 1-5 Mode Switch 1-5 MSU Annunciators 1-6 Control Display Unit 1-7

Page

CDU Operational Summary 1-9 Operating Cautions 1-11 Section 2

Predeparture Procedures 2-1 INS Startup and Data Base Validity Check 2-1 Present Position Entry 2-4 Local Ident Entry of Present Position 2-5 Present Position Entry by Latitude and Longitude 2-6 Present Position Entry by Range and Bearing From a Reference 2-8 GMT and Date Entry 2-10 Position Page Normal Display During Alignment 2-11 Alignment Status 2-12 Flight Plan Data Entry 2-15

April 1998

TP92-04138 page iii

Table of Contents

Section Me

Page

Flight Plan Assembly by Waypoint to Waypoint Entry 2-15 Duplicate Identifiers 2-17 Flight Plan Assembly by Route Entry 2-19

Crew Waypoint Entry or Correction 2-20 Latitude/Longitude Crew Waypoint Entry 2-21 Bearing /Range Reference Crew Waypoint Entry 2-23 Flight Plan Editing 2-26 Waypoint Substitution 2-26 Single Waypoint Deletion 2-28 Multiple Waypoint Deletion 2-30 Inserting a Waypoint or a Route Between Existing Waypoints 2-32 Initial Track Selection 2-34 Default Leg Selection 2-34 Enter Leg by Identifier 2-35 Enter Leg by Waypoint Number 2-37 WPT.Page Flight Plan Verification 2-39

Section 3 Enroute Procedures 3-1 Leg Switching 3-1 Automatic Leg Switching 3-1 Manual Leg Switches 3-4 Direct To Mode 3-6 Direct To Steering 3-10 Waypoint Bypassing 3-10 Crosstrack Offset Mode 3-11 Track Hold Mode 3-14 Flight Plan Data 3-16 page iv

TP92-04-13-B

Table of Contents

Section Title

Page

EFIS "To" Waypoint Change 3-18 Course Data 3-19 Instrument Data 3-20 Remote Range 3-20

Section 4 Post Flight Procedures, Rapid Realignment and Nay Update 4-1 Accuracy Test 4-1 Intermediate Stops 4-3 Post Flight Procedures 4-5 System Accuracy Removal Criteria 4-6 Rapid Realignment 4-6 Nav Update Mode 4-9 Section 5

Crossfill 5-1 Crossfill Procedures 5-2

Section 6 Position Updating 6-1 Easy On/Off Steering 6-1 Position Check 6-3 Automatic Position Updating 6-4 Radio Updating 6-6 Enabling Position Updating 6-9 RNAV Inhibit Functions 6-10 DME/VOR Related- Messages 6-11 DME Range Crossfill Related Messages 6-12 Other Messages 6-13 STS/Update Page Summary 6-14

page v

Table of`Contents

Section Title

Page

Triple System Mixing. (TM IX) 6-16 Disabling Triple System Mixing 6-17 Triple System Mixing Related

Messages 6-18 STS/Update Page Description 6-19 Manual Position Update 6-21 Flush Updates 6-24 Section 7

RNAV Approach Procedures 7-1 RNAV Approach Mode Characteristics 7-1 RNAV Approach Procedures 7-2 Missed Approach Point Entry 7-4

Section 8 Attitude Reference Mode 8-1 Section 9

Summary of Display Pages and Function Keys 9-1 Position Page 9-3 Course Page 9-4 Leg Page 9-5 Waypoint Page 9-6 Flight Plan Page 9-7 Direct. to Page 9-8 Instrument Data Page 9-9 Catalog Page 9-10 Creating and Deleting Routes and

Waypoints in Permanent Memory 9-11 Storing a Custom Route 9-11 Clearing Custom Routes from the ROUTES Catalog 9-12

page vi

Table of Contents

Section

Title

Page

Storing Waypoints , Stations and Airports in Permanent Memory 9-13 Deleting a Waypoint or Station from Permanent Memory 9-14 Remote Page 9-15 Status Page 9-16 Display Test 9-17 Accuracy Test 9-18 Dbase Type/Date 9-19 Autopilot/Flight Director Tests 9-20 HSI Operation 9-27 Section 10

Abnormal Operation 10-1 INS Warning Annunciations 10-1 Warning Annunciations 10-1 Action/Malfunction Messages 10-2

Section 11 Alphabetical Index 11-1 Section 12

February 1996

Quick Reference Guide 12-1 Alignment (With Local Ident Stored in Data Base) 12-2 Alignment (With Local Ident Not in Data Base) (LAT/LON Procedure) 12-3 Display Test 12-4 Waypoint Entry by Route Definition 12-4 Waypoint Loading 12-5 Crossfill (Remoting) 12-6 Flight Plan Verification 12-7 Initial Track Selection 12-7 Route Change 12-8 Inserting a Waypoint Between Waypoints 12-8 Waypoint Substitution/Deletion 12-9 TP92-04-13-B

page vii

Table of Contents Multiple Waypoint Deletion 12-9 Direct-To Mode (From Present Position to a Waypoint) 12-10 Crosstrack (Offset) 12-10

VOR/DME Cross Check 12-11 Time, ETA, and WPT Distance Displays 12-11 Position Check

12-12

Manual Position Update Remove All Position Updates

12-12 12-12

Remote Ranging Use of Crew (Temporary) Catalog

12-13 12-13

Catalog Inspection Accuracy Test

12-14 - 12-14

Leg Change - Track Selection 12-15 Status Malfunction Messages 12-15 Attitude Mode 12-16 Automatic Updates, Disable/Re-Enablel2-16

page viii TPS2-04-13- B February 1996

List of Illustrations Figure Title

Page

1-1 Inertial Navigation System 1-2 INS Typical Interface

1-2 1-3

1-3 Mode Selector Unit

1-5

1-4 Control Display Unit 1-5 Numeric Pushbuttons - Special Functions

1-7 1-10

3-1 Leg Switch Less Than 25 Degrees 3-2 Leg Switch Between 25 and 110 Degrees

3-2

3-3 Leg Switch Greater Than 110 Degrees

3-3

3-4 Direct To Modes 3-5 Crosstrack Offset Leg Change

3-6 3-13

3-6 Track Hold Mode

3-15

3-2

4-1 Radial Position Error

4-7

4-2 Drift Rate

4-8

9-1 Typical HSI Presentations

9-27

9-2 Summary

9-29

page ix

List of 111ustrations

List of Tables Table. Title 9-1 9-2 9-3

Synchro and Analog Test Output Values to HSI and ADI BCD Test Output Values (EFTS and WX Radar) Annunciator Test

10-1 Action/Malfunction Messages

page x

Page

9-24 9-25 9-26 10-3

A

t

Section 1 General System

Description

NOTE:

This document contains all configurations applicable to the LTN -92 navigation system. The user may use any portion of this document that is appropriate for a particular configuration.

The INS consists of three units (figure 1-1): • a Mode Selector Unit (MSU) • a Control Display Unit (CDU), and •

an Inertial Navigation Unit (INU).

An optional Battery Unit (BU) is available as a backup power source. The MSU and CDU are used for pilot control of the INS and are installed in the cockpit . The INU and BU are normally installed in the aircraft electronics bay. The Litton LTN- 92 inertial navigation system (INS) is a navigation system , with automatic GPS and radio update capabilities (VOR-DME, TACAN).

0

The INS may be operated as an Area Navigation System if position is periodically updated using GPS or range and bearing from selected VOR -DME or TACAN stations.

Section 1 - General System Description The system features a Control Display Unit (CDU) which functions as an intelligent data terminal and incorporates a Light- Emitting-Diode (LED) matrix display. The CDU keyboard has dual function pushbuttons for full alphanumeric data entry. The displays provide navigation data, operating status of the system, I and formatted messages to assist the pilot in data entry.

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Inertial Navigation System Figure 1-1

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TP92-04138

page 1-3

Section 1 - General System Desc^tion

NAVIGATION DATA STORAGE Crew Catalog (Temporary). Navigation data items (airports, waypoints , or stations) may be retrieved or entered at any time. This catalog can store a maximum of 120 data items. These data are lost when the system is turned off.

4

Custom Catalog (Permanent). Up to 2005 Navaids, Waypoints, and Airports, plus 100 routes of 98 waypoints can be stored in this memory. It remains unaffected by the cyclic database update. The facility exists to permanently store routes and other data entered via the CDU into this area of memory. The aircraft wiring determines whether the storage function is available. World Wide Data Base (Permanent). Navigation data items (airports, enroute waypoints, or stations) may be retrieved. This catalog can hold a maximum of 2 megabytes of data. Memory is consumed as follows: • Each Navaid requires 32 bytes

• Each Waypoint/NDB requires 16 bytes Each Airport requires 16 bytes.

r

Each route requires 16 bytes plus 4 bytes/waypoint A large airline will typically store two complete databases (the current cycle plus the next cycle's worldwide Navaids), waypoints/NDBs, airports, custom waypoints/ramp positions, 6000 routes, and airways with less than 50% of available memory used.

SYNTHETIC MAGNETIC VARIATION The system can be used to display magnetic heading, track, and desired track independent of the aircraft compass system. When latitude is greater than 73° Nor 60°S, the system will automatically revert to True Heading and digital magnetic outputs will be NCD (no computed data).

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TP92-0413B

April1998

Section 1 - General System Description MULTIPLE SYSTEM OPERATION Multiple systems may be integrated in dual or triple system configurations. A crossfill feature allows the pilot to transfer waypoint data, date, and time from one system to the remaining systems. A comparison warn feature alerts the pilot when a significant difference in position or ground speed occurs between systems. In e'triple system installation, the pilot may enable atriple system mix feature which combines the present position of all three systems for greater navigation accuracy. MODE SELECTOR UNIT The MSU controls the application of power to the INS and selects the Standby (STBY), Alignment (ALIGN), Navigation (NAV), and Attitude Reference (ATT REF) modes of operation. MODE BAIT FAIU ALIGN SWITCH ANNUNCIATOR ANNUNCIATOR

Y- ALIGN r NAV

O ALIGN

OFFS ATT REF

BATE

Mode Selector Unit Figure 1-3

Mode Switch OFF

Turns INS power off; MSU and CDU panel lighting may remain on.

c)

April 1998

TP92-04138

page 1-5

Section 1 - General System Description STBYIALIGN

Turns INS power on and selects Standby or Alignment mode. Pilot enters present position, GMT and date and display test may be performed. An automatic alignment sequence starts . The aircraft must remain stationary while the system is in Standby or Align.

NAV

Selects Navigation mode. This is the normal flight operating mode and must be selected prior to moving the aircraft. Initial track mcy be entered at this time. NAV may be selected directly from OFF, STBY, or ALIGN modes, but alignment must be completed prior to moving the aircraft. If NAV is selected before alignment is complete, the system will complete alignment before automatically sequencing to NAV.

NOTE: The mode switch is detented in the NAV position to prevent accidental INS shutdown. To deselect NAV, the knob must be pulled away from the panel and then turned. ATT REF

Selects Attitude Reference mode. In this mode, the INS provides pitch, roll, and platform heading outputs only, and the CDU displays only status data. ATT REF mode disables INS navigation capabilities until a full alignment is performed on the ground.

MSU Annunciators ALIGN (amber) Comes on during alignment to indicate that alignment sequence is in progress.. On completion of a valid alignment and selection of NAV, ALIGN light goes out. CAUTION: WHEN THE ALIGN LIGHT IS ON, THE AIRCRAFT MUST REMAIN STATIONARY TO COMPLETE A NORMAL GROUND ALIGNMENT.

page 1-6

TP92-0413B

BATT (FAIL)

Section 1 - General System Description (Battery fail) Comes on when DC backup voltage is insufficient for INS operation. If the battery is discharged, this light will come on during the battery test at tum -on, and remain on until the next tum -on with a charged battery.

CONTROL DISPLAY UNIT The CDU is used to enable the entry of data into the INU, to selectflight plans; and to display datafrom the INU database. UPDATING SOURCE INP TON (G. R. T E) (NO UPDATE IN PROGRESS)

ALPHA OR NUMERIC ALPHANUMERIC BRIGHTNESS MODE CONTROLS INDICATION PUSHBUTTON

CLEAR PUSHBUTTON ENTER PUSHBUTTON ALERT ANNUNCIATOR OFFSET ANNUNCIATOR DATA pN ^Y pE L^ TTRR BUTTONS

HOLD PUSHBUTTON

PUSHBUTTONS PUSHBUTTON

Control Display Unit Figure 1-4

The CDU LED alphanumeric display, annunciators, and pushbuttons function as follows: LED matrix display (display) - Displays five lines with 16 characters per line. When appropriate, lines can be slewed upward or downward by use of slew pushbuttons.

April 1998 TP92- 0413B

page 1-7

Section 1 - General System Description s Brightness controls (BRT and DiMpushbuttons) - When pressed , set brightness level of display . (Operable only in numeric mode). A • N (alphanumeric) pushbutton - An alternate action switch enabling alphabetic or numeric data entry. CLR (clear) pushbutton - When pressed before ENT is pressed , removes entered data from display.

ENT (enter) pushbutton - When pressed, enters data input via data entry pushbuttons into the computer. ALR (alert) annunciator - Comes on at a preset time before aircraft reaches each approaching To waypoint. When INS is in automatic mode , goes out to indicate that a leg change has been made automatically . When INS is in manual mode , flashes to indicate that a leg change must be made manually. Flashes when in track hold mode. OFS (offset) annunciator - On when INS is in the offset . (parallel track mode). Data entry pushbuttons - When pressed, enter data in the display line indicated between entry line markers. HLD (hold) pushbutton - When pressed, freezes present position display (except in CARP mode).

EXP (expand) pushbutton - Expands selected display categories. Slew pushbuttons - Enable slewing of appropriate lines of display. Normally, display will advance one line each time pushbutton is pressed or when continuously pressed will continuously slew. Data display select pushbuttons - Allow display of particular data category. (See Summary section).

•

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TP92-0413B

Section 1 - General System Description WRN (warn) annunciator - Comes on when a system malfunction occurs . Flashes if ALIGN error occurs.

BAT (battery on) annunciator - Comes on when INS is operating on-28 vdc backup power. Entry line markers - Indicate display line into which data may be entered (CDU line 3).

CDU OPERATIONAL SUMMARY

C

The CDU provides data entry and display based on pilot call-up of various " pages " selected by the function pushbuttons. The keyboard provides an alphabetic entry (shown on upper half of the pushbuttons) when the alpha entry mode is selected . The system will automatically switch to the alpha entry mode only when alpha entry is appropriate on a particular page. The alpha mode is annunciated by A in the upper right comer of the display. A return to the numeric mode may be selected at any time by pressing A • N. The numeric entry pushbuttons on the right side of the keyboard are arranged in the same manner as standard numeric keyboards. The normal data entries of North , South, East, West, Left, and Right are made using these pushbuttons (figure 1-5). The following conditions apply for data entry: 1. All numeric data entries (latitude , longitude, etc.) and all alphanumeric entries (flight plan , ident, etc.) are made left to right. 2. Leading zeros are not required. 3. Trailing zeros must be entered.

0

4. A • N selection is not necessary when entering position.

Section 1 - General System Description

i

NORTH

G 3

M 5 LEFT

z EXP

RIGHT

HLD SOUTH

Numeric Pushbuttons - Special Functions Figure 1-5 Display pages are arranged to provide a primary display of data. Where additional data relating to the primary page is available , the slew up or down pushbuttons are used. EXP (Expand ) is used to provide information relating to an Item displayed on the entry line (example : latitude and longitude of a waypoint). Refer to Section 12 for a summary of the CDU data pages.

page 1-10

TP92-04-13-B

January 1997

Section 1 - General System Description OPERATING CAUTIONS 1. UNLESS AN INS FAILURE OCCURS, THE MODE SWITCH SHOULD NOT BE DESELECTED FROM NAV ONCE NAV MODE IS ENABLED. 2. WHEN THE MSU ALIGN INDICATOR IS ON, THE SYSTEM IS PERFORMING AN ALIGNMENT. THE AIRCRAFT SHOULD REMAIN STATIONARY DURING THIS PERIOD. 3. IF CDU BAT ANNUNCIATOR COMES ON , THE INS IS OPERATING ON DC BACKUP POWER. NOTE:

C

There is a 5 second battery test at tum on when the BAT annunciator will normally come on.

IF THE BACKUP POWER SOURCE IS A BATTERY UNIT, 15 TO 30 MINUTES OF OPERATION WILL BE AVAILABLE WITH A FULLY CHARGED BATTERY. IF PRIMARY POWER IS NOT RESTORED PROMPTLY, THE BATTERY VOLTAGE WILL FALL BELOW THE LEVEL REQUIRED TO OPERATE THE INS.

4. IF THE MSU BATT ANNUNCIATOR COMES ON, THE DC BACKUP POWER IS INSUFFICIENT FOR INS OPERATION. 5. IN A DUAL OR TRIPLE INSTALLATION, IF ONE OF THE SYSTEMS HAS A LARGE INERTIAL POSITION OR VELOCITY ERROR, THE FOLLOWING MESSAGE WILL BE DISPLAYED ON THE CDU:

"THIS SYS POS OR G.S. DIFFERS FROM OTHERS BY >35 N.M. OR 50 KT. CLR:RETURN" THE PILOT HAS THE OPTION TO USE OR DISREGARD THAT INS.

Section 1 - General System Description ,I

6. IF AN ERROR IS DETECTED IN THE CUSTOM CATALOG DATA DURING FLIGHT, THE FOLLOWING MESSAGE WILL BE DISPLAYED ON THE CDU: "DATA BASE COMMUNICATION FAILURE OR CUST/RTE CATALOG CHECKSUM FAIL: CUST FLIGHT PLAN DATA INVALID. CLR: RETURN" THE PILOT SHOULD VERIFY THE DATA IN THE FLIGHT PLAN IS CORRECT. THE PILOT HAS THE OPTION TO USE OR DISREGARD FLIGHT PLAN DATA FROM THAT INS. THE SYSTEM WILL INHIBIT FURTHER LOADING OF CUSTOM DATA INTO THE FLIGHT PLAN . HOWEVER , CREW CATALOG DATA, CROSSFILL DATA AND, EXTERNAL DATA BASE (NDB) DATA MAY STILL BE USED.

7. AFTER THE MSU HAS BEEN TURNED TO OFF, THERE IS A 12 SECOND SHUTDOWN DELAY BEFORE THE INS SHUTS DOWN . DURING THIS TIME THE SYSTEM IS UPDATING MEMORY. DO NOT PULL CIRCUIT BREAKERS TO THE INS UNTIL THE CDU BLANKS. 8. WHEN SWITCHING TO ATT REF MODE , THE ATTITUDE (PITCH AND ROLL) AND ATTITUDE FLAG ARE INVALID FOR ABOUT 29 SECONDS (NAV TO ATT REF) OR 60 SECONDS (OFF TO ATT REF). PRIOR TO SELECTING ATT REF, SELECT A BACKUP SOURCE OF ATTITUDE. 9. A STATIC INERTIAL ALIGNMENT CAN BE PERFORMED AT LATITUDES UP TO 85 DEGREES; HOWEVER , STATIC INERTIAL ALIGNMENTS PERFORMED AT LATITUDES ABOVE 80 DEGREES NORTH OR SOUTH, CANNOT GUARANTEE AN ACCURACY OF 2NM/HR OR BETTER.

s

Section 2 Predeparture Procedures INS STARTUP AND DATA BASE VALIDITY CHECK Prior to using the data base , check to ensure the data is current (refer to step 3. of this procedure). ALIGN STBY NAV .__ _ Al

1. Ensure the MSU mode switch is set to OFF. 2: Set circuit breakers in (on).

ALIGN STBY

3. Set mode switch to NAV for automatic 10 minute alignment.

With WWDB

OFF

NAV ATT REF

Without WWDB

February 1996 TP92-04-13-B

page 2-1

Section 2 - Predeparture Procedures

Without WWDB .

With WWDB The CDU displays the INU program number on line 1. Line 2 is the customer identifier for the data base. Lines 3 and 4 show the effectivity dates for the two stored World Wide data bases. 4. Slew to the proper date cycle. R

4

4. After 3 seconds, display changes to custom data base title page where X's will identify the data base.

CUSTOM'OBAS'

Y

0

5. Press ENT. ENT

The CDU displays the program number 9204-13 on the top line.

If the Litton data base service is being used, the first two characters are the airline code, the third and fourth are the month of expiration , and the fifth and sixth are the day of expiration . (LC0731 is Lockheed, expiring July 31.)

5. Press CLR to continue. CLR

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TP92-0413- B January 1997

4

Section 2 - Predeparture Procedures

I-

6. The CDU changes to allow position entry (referto "Present Position Entry" in this section).

If an FMC is connected, then position and time entry is automatic. N FMC input received

NOTE: If the INU data base is out of date, stored waypoint data, used in a route to be flown, should be cross checked against the current flight planning documents , and the accuracy of every Latitude and Longitude confirmed. Additionally, when the data base is out of date, it is recommended that the stored VOR/DME data being used for RNAV position updating be cross checked for accuracy, or alternatively do not enable RNAV updating.

O

April 1998

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Section 2 - Predeparture Procedures

PRESENT POSITION ENTRY Aircraft present position must be entered into each INS before alignment can be completed . If a compatible GPS or flight management computer ( FMC) is connected to the INS, the position and time will automatically be displayed. The FMC position is automatically accepted . The GPS position is displayed and the pilot must accept or reject it. Upon entry of present position , the system checks the entry to ensure that it is within 3+3t (t=time in NAV ) of the aircraft's last present position at time of shutdown on previous flight. If these comparison limits are exceeded , the CDU WRN annunciator will flash and the message "CHECK PPOS ENTRY" will be displayed on the POSITION page (STATUS page will display " ENTER PPOS "). Pressing ENT will accept the displayed position entry , pressing CLR will reject the entry and prompts for a new latitude and longitude entry will be displayed. After 4.5 minutes of alignment , the system performs an additional check of the entered latitude against an inertial estimate of the aircraft 's latitude. The two must agree to within 30 nautical miles for the alignment to proceed. If the comparison limit fails , the CDU WRN annunciator will flash and- the messages ENTER PPOS and ALN FAIL will be displayed on the STS page to alert the pilot. Present position may be entered by: • Automatic download from FMS • Manual entry by IDENT • Manual entry by LAT/LON

• Manual range and bearing to a known reference

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TP92-0413B

i

Section 2 - Predeparture Procedures LOCAL IDENT ENTRY OF PRESENT POSITION POSITION page is displayed.

1. Slew LOC ID to entry line.

2. Enter LOCAL (DENT for present position.

3. Press ENT ENT

Latitude and longitude are displayed.

Section 2 - Predeparture Procedures NOTE: If the LOCAL IDENT is not valid; "IDENT NOT FOUND" will be displayed ; press CLR to return to local (DENT entry. If duplicate idents are found, the first one will be displayed . The pilot is prompted to press ENT to accept the displayed ident, press SLEW to display the other ident (s) or press CLR to return. 4. Enter GMT and date. Refer to GMT ENTRY.

PRESENT POSITION ENTRY BY LATITUDE AND LONGITUDE

POSITION page is displayed.

1. Select North (2N) or South (8S).

2. Enter latitude , including any trailing zeros.

page 2-6

F 2N

or

3 3 5 6 5 2

T as

Section 2 - Predeparture Procedures 3. Press ENT.

ENT

LAT flashes once; display slews LON to entry line.

4. Select West (W4) or East (6E). 5. Enter longitude , including any trailing zeros. 6. Press ENT.

P4 1 or

FN

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1182447

ENT

n

LON flashes once; display slews GMT to entry line. 7. Enter GMT HH:MM:SS, and date. Refer to GMT ENTRY

NOTE: Invalid present position coordinates (latitude greater than 90°, longitude greater than 180°, or arc-minutes greater than 59.9') will be rejected by the system . Line 3 will flash with the invalid data until CLR is pressed to clear the entry.

. Section 2 - Predeparture Procedures

PRESENT POSITION ENTRY BY RANGE AND BEARING FROM A REFERENCE POSITION page is displayed.

1. Press AN key.

CDU displays:

2. Enter reference identifier.

3. Press ENT

4. Enter magnetic bearing from the reference to present position.

A•N

Section 2 - Predeparture Procedures

R

5. Press ENT.

6. Enter the range from the reference to present position.

7. Press ENT.

ENT

8. View data to ensure it is correct.

9. Press ENT to accept the data or CLR to reenter the data. The data may also be changed by slewing the desired parameter to the entry line and keying in new data.

NOTE:

ENT

or

CLR

If the reference cannot be found or distance is greaterthan 300 nmi or bearing is greaterthan 359.9 deg, line 3 will flash and the corresponding error message will be displayed.

TP92-0413B

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Section 2 - Predeparture Procedures GMT AND DATE ENTRY NOTE:

Failure to enter GMT will invalidate INS calculations of ETA and Time initialize crossfill.

NOTE: If the aircraft is equipped with a compatible GPS, FMS or chronometer, the GMT and date will be automatically displayed . Time received from the GPS has priority and will overwrite manually entered time. 1. Enter GMT in hours, minutes , and seconds, 24 hour time.

m ouT :r " ...a LA7

4 32 ,r N

.

e.g., 1 2 4 51 0 2. Press ENT at instant preset time matches actual GMT. NOTE :

ENT

The INS will not accept afirst digit GMT entry other than 0, 1, or 2 . If invalid hours (greater than 23), minutes (greater than 59) or seconds (greater than 59) are entered , GMT line flashes and INVALID ENTRY is displayed . Press CLR and reenter GMT.

3. Enter date. e.g., 27 July 1993 enter as 270793

NOTE : Date entry is not required for navigation . It is necessary when an external navigation base is installed on the aircraft. NOTE : An entry of 00 will be read as year 2000. r

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TP92-0413B

April 1998

Section 2 - Predeparture Procedures POSITION PAGE NORMAL DISPLAY DURING ALIGNMENT The POS page will display the entered latitude and longitude and GMT (If entered). Position may be reentered at any time during ALIGN without affecting the ALIGN time. Once the system has sequenced into NAV, the inertial position cannot be changed.

Position page display during alignment. Nearest station range and bearing displayed on line 4.

NOTE: Bearing is True or Magnetic depending upon CDU selection of True or Magnetic data. 0

Section 2 - Predeparture Procedures

ALIGNMENT STATUS ALIGN

1. Mode switch : STBY ALIGN or first 10 minutes of NAV.

STBY^ NAV OFF ATT REF

ALIGN STBY OFF

NAV ATT REF

On the MSU, the ALIGN annunciator comes on. 2. The alignment process can be observed by pressing STS on the CDU . SYS STS/TEST page is displayed . Refer to Alignment Status Table 2-1.

CDU displays SYS STS/TEST pages during alignment.

v STS

STATUS 90

STATUS 80 60 50 10 2

NOTE : STBY and ALIGN positions are the same.

Section 2 - Predeaarture Procedures NOTE: The number (2 through 90) appearing on the ALIGN line indicates alignment status . 90 is generated at startup and decrements through 2 at completion of alignment (refer to Alignment Status Table 2-1). The time remaining (minutes and tenths) in align appears on the TIME line. The time required to complete a normal alignment is 10 minutes. AUGN NAV

3. Set mode switch to NAV.

NOTE:

The recommended operating procedure at turnon is to switch the MSU from OFF directly to NAV. The system will automatically sequence to NAV when the alignment is complete.

Alignment not complete : display remains in ALIGN until status 2 then shifts to NAV. Alignment complete : ALIGN annunciator goes out; ALIGN line changes to NAV, status 1 , TIME line changes to time in NAV. STATUS 1

CAUTION : DO NOT SET MODE SWITCH OUT OF NAV AFTER NAVIGATION MODE IS ENTERED. NOTE: See Abnormal Operation Section for explanation of action/malfunction messages. C

NOTE:

INS alignment accuracy will continue to improve even after entering NAV. No accuracy improvement is gained by leaving the INS in STBY or ALIGN. page 2-13

Section 2 - Predeparture Procedures

Table 2- 1. Alignment Status Table Status

Description

90 System high voltage sequence is performed. Accelerometer coarse leveling is accomplished (complete 24 seconds after turn -on).

80 System continues leveling (complete 30 seconds after turn -on). 70 Executed and displayed only if the system sensor block temperature is below 0°C. Indicates extended align. The system will remain in status 70 until the block temperature is above - 15°C and align time is less than 9 minutes. When STS 70 is displayed , alignment time will be more than 10 minutes.

60 System performs fine leveling and gyro compassing . System remains at status 60 until 5.5 minutes are remaining in align time. 50 Latitude is tested continually from 5 .5 minutes remaining in Align. If present position has not been entered the system remains at status 50. If the latitude test fails the system will reset to status 50 and position entry will be required. Otherwise, the system stays in status 50 for 10 seconds, then sequences to status 10. Fine leveling and gyro compassing continue in status 50. 10 System continues fine leveling and gyro compassing and remains in status 10 until the minimum align time has been completed. If NAV mode is selected, the system will automatically sequence into NAV mode. 2 The minimum align time has been completed. The system will cycle to NAV providing the MSU is set to NAV.

4

Section 2 - Predeparture Procedures FLIGHT PLAN DATA ENTRY The flight plan consists of a sequential waypoint list with up to 98 custom, crossflll, or pilot-entered waypoints (or a combination thereof) called up from various catalogs. Each waypoint is selected by entering an identifier (IDENT) which defines its coordinates. Refer to CATALOGS.

FLIGHT PLAN ASSEMBLY BY WAYPOINT TO WAYPOINT ENTRY 1. Press WPT.

WPT SELECT page is displayed.

NOTE: The symbol represents present position. 4

NOTE:

If present position has not been entered when the WPT key is pressed, the POS page is displayed.

2. Press AN to display entry prompts.

A•N

CDU displays:

3. Assemble Flight Plan:

Waypoint Entry a. Enter the waypoint IDENT by alphanumeric entry, (e.g. VNY). page 2-15

Section 2 - Predeparture Procedures b. Press ENT.

VNY is added to waypoint list. Prompt line for next waypoint.

c. Continue flight plan assembly by entry of up to 98 waypoints. Press CLR if no more waypoints to be entered. NOTES : If the entered IDENT does not exist in any of the systems catalogs, prompts for entry of latitude and longitude will be displayed. Refer to CREW WAYPOINT SELECTION AND ENTRY section of the PREDEPARTURE PROCEDURES. Use up and down slew keys to slew through the waypoints. Pressing the A • N key on the waypoint page will advance to the first available blank waypoint and display the entry prompt line. To jump to a particular waypoint, enter the waypoint number (e.g., 27) and press ENT Waypoints cannot be entered before present position is entered. Waypoint zero will hold the coordinates of the FROM waypoint whenever a DIRECT TO or LEG SWITCH FROM 00 is performed.

V

Section 2 - Predeparture Procedures DUPLICATE IDENTIFIERS When duplicate identifiers exist, the number of duplicates will be displayed in the upper right comer of the CDU. The country name will be displayed on line 4 . If the waypoint is a CUSTOM waypoint, then CUST will be displayed . The pilot must examine coordinates and country name of each duplicate identifier. 1. During flight plan construction , enter an (DENT that is used for more than one set of coordinates.

2. Press EM.

4

ENT

Examine the coordinates and country of the first duplicate (DENT.

NOTE: The alpha character located at the center of line 1 indicates the type of waypoint: A Airports S Stations W Waypoints The 1/2 indicates this is the first SMO of 2.

Section 2 - Predeparture Procedures 3. If the displayed coordinates are not desired, slew up once; the number in upper right comer increments by 1 and coordinates and country name change.

4. Repeat step 3 until the correct coordinates are found.

5. Press ENT.

Selected waypoint is entered into the waypoint list. The , prompt line is displayed to continue flight plan construction.

ENT

Section 2 - Predeparture Prgcedures FLIGHT PLAN ASSEMBLY BY ROUTE ENTRY 1. Press WPT.

H WPT

WPT SELECT page is displayed.

2. Pressing these four buttons will insert "-R" at the first WPT prompt. This will produce the Route prompt.

AN

LI

R

4

Prompt for route name appears.

Insert route name then press ENT.

J F K L A X 3 ENT

Route is now displayed.

NOTE: All routes can be listed by selecting the catalog page and slewing to ROUTE.

Section 2 - Predeparture Procedures

CREW WAYPOINT ENTRY OR CORRECTION The pilot may enter waypoint IDENTs not found in any catalog . These waypoints will be assigned by latitude/longitude coordinates , and will be stored in the CREW (temporary) catalog.

If a mistake is made while entering waypoint data into the CREW catalog , perform the following steps to rectify this error: 1. Delete the waypoint from the flight plan and the CREW catalog using the SINGLE WAYPOINT DELETION procedure in this section. 2. Re-enter the waypoint using one of the following CREW WAYPOINT ENTRY procedures.

Section 2 - Predeparture Procedures 0

LATITUDE/LONGITUDE CREW WAYPOINT ENTRY 1. Press WPT.

WPT SELECT page is displayed with the current flight plan.

2. Press AN to slew to first unassigned waypoint number.

3. Enter an (DENT for the waypoint (example NYK).

4. Press ENT ,

Because NYK is not in memory, prompts appear for LAT/LONG entry to define NYK' s position.

A•N

Section 2 - Pred

^ture Procedures

5. Select North or South, then enter waypoint latitude, including trailing zeros. 6. Press ENT; LAT stews to line 2, LON prompt slews to entry line. 7. Select East or West, then enter waypoint longitude, including trailing zeros.

N 4 3 4 4 5 4

ENT

W 1 1 8 3 5 6 0

8. Press ENT. CDU displays: (On some aircraft this waypoint information will be written into the INS permanent memory)

9. Press DIP to USE waypoint (crew waypoint in temporary memory), or press CLR to REJECT waypoint and return to WPT entry mode.

z EXP

Section 2 - Predeparture Procedures BEARING/RANGE REFERENCE CREW WAYPOINT ENTRY NOTE:

Bearing and range waypoints may be stored in the CREW CATALOG only.

1. Press WPT.

WPT SELECT page is displayed with the current flight plan.

2. Press A•N to slew to first unassigned waypoint number. 3. Enter an IDENT of the form AAANNN. It must be 3 alpha characters followed by 3 numeric characters.

(example: OLM234). 4. Press ENT. Waypoint IDENT appears on line 1 and the following prompt lines appear: DIST: line 2 , REF: entry line, BRG : line 4, CLR:RETURN, fine 5.

H WPT

Section 2 - Predeparture Procedures NOTE:

If an IDENT is found that matches the AAA entry, the display will default to REFERENCE WAYPOINT display with referenced waypoint defaulting to the AAA entry.

5. Enter the referenced waypoint IDENT.

O L M

6. Press ENT.

Reference IDENT slews to line 2, BRG prompt to entry line.

7. Enter the magnetic bearing from referenced waypointto new waypoint (0 to 359.9°).

2 3 4 7

8. Press ENT. ENT

BRG stews to line 2, DIST prompt to entry line.

9. Enter range from referenced waypoint to new waypoint (0.1 to 300.0 nmi).

2 5 6

Section 2 - Predenarture Procedures 10. Press ENT

EXP:USE CLR:REJ appear on line 5.

a. Press EXP to USE waypoint (crew waypoint in temporary memory).

n

OR

OR

b. Press CLFt to REJECT waypoint and return to the WPT entry mode.

cua

Section 2 - Prodeparture Procedures

FLIGHT PLAN EDITING The flight plan may be changed by waypoint substitution, insertion , or deletion. CAUTION: WHEN AN ACTIVE FROM/TO WAYPOINT IS DELETED, ALL AUTOPILOT, FLIGHT DIRECTOR AND HSI OUTPUTS ARE ZEROED; HSI FLAGS (NAV MODE) ARE INVALID.

WAYPOINT SUBSTITUTION 1. Press WPT.

WPT SELECT page is displayed, with the current flight plan.

2. Slew desired waypoint to entry line. (DEN is to be replaced by KLA)q.

3. Press CLA.

R Q

Section 2 - Predeparture Procedures

(DENT is removed; prompt line is displayed.

4. Enter new IDENT.

K L A X

5. Press ENT. ENT

NOTE: If FROM or TO waypoint # is changed , "FROM/ TO WAYPNT NO. WILL BE CHANGED " is displayed . Press ENT to make change or CLR to reject the change.

Section 2 - Predeparture Procedures

SINGLE WAYPOINT DELETION CAUTION:

WHEN AN ACTIVE FROM/TO WAYPOINT IS DELETED, ALL AUTOPILOT, FLIGHT DIRECTOR AND HSI OUTPUTS ARE ZEROED; HSI FLAGS (NAV MODE) ARE INVALID.

1. Press WPT.

WPT SELECT page is displayed, with the current flight plan.

2. Slew waypoint to entry line. (DEN is to be deleted).

CDU displays:

3. Press CLR.

IDENT is removed ; 14, prompt line is displayed.

page 2-28

I

I

a

Section 2 - Predeaarture Procedures 4. Press CLR again.

R Waypoint list closes up.

NOTE:

If FROM or TO waypoint # is changed, "FROM/ TO WAYPNT NO. WILL BE CHANGED " is displayed. Press ENT to make change or CLR to reject the change.

5. The following steps may be performed to delete the waypoint from the CREW catalog.

a. Press CAT.

b. Slew up until CREW is on the data entry line.

CDU displays:

c. Press EXP.

P CAT

Section 2 - Predeparture Procedures

d. Slew up until the waypoint for deletion is on the data entry line.

e. Press CLR to delete the selected waypoint.

MULTIPLE WAYPOINT DELETION 1. Press WPT.

FH WPT

WPT SELECT page is displayed.

2. Slew to first waypoint to be deleted, (e.g., UBG will be deleted).

R

4

Section 2 - Predeparture Procedures 3. Press CLR.

C LR

CDU displays:

4. Press -, D, and ENT.

ENT

0

Display will change to request the last WPT number to be cleared.

5. Enter last WPT number to be deleted. (You can delete backward or forward).

6. Press ENT. ENT

All waypoints between and Including the two entered numbers will be cleared and the waypoint list will close up.

Section 2 - Predeparture Procedures INSERTING A WAYPOINT OR A ROUTE BETWEEN EXISTING WAYPOINTS 1. Press WPT. PWPT

WPT SELECT page is displayed , with current flight plan.

2. Slew the waypoint that will precede the added waypoint to entry line (waypoint AEL is to be inserted between KSTL and KFWA).

3. Press ENT ENT

Preceding waypoint moves to line 2, prompt appears on entry line, and remaining waypoints are renumbered. NOTE:

page 2-32

If FROM or TO waypoint # is changed, "FROM/ TO WAYPNT NO.. WILL BE CHANGED " is displayed. Press ENT to make change or CLR to reject the change.

Section 2 - Predeparture Procedures C.

4. Enter new (DENT.

A E L

5. Press ENT. ENT

CDU displays:

NOTE: A route may be inserted by entering -R at step 4, then entering the route ident . Following waypoints are moved down in the flight plan to make room for all the route's waypoints.

Section 2 - Predeparture Procedures

INITIAL TRACK SELECTION A track leg must be selected to enable INS computations of steering and leg distances. Estimated . time enroute and ETA are zero until ground speed is greater than 100 knots. To select your present position as the FROM way, point, and the first waypoint listed in the flight plan as the TO waypoirt, simply press LEG then ENTer twice. If no waypoints have been entered in the flight plan, the message "ROUTE$7WPTS NOT SELECTED" will be displayed.

Default Leg Selection

1. Press LEG.

LEG page is displayed, with the ident of WPT 0 flashing over the underscores.

2. Press ENT.

The ident of the first waypoint in the flight plan will flash over the underscores.

C LEG

Section 2 - Predeparture Procedures 3. Press ENT again.

CDU displays:

CAUTION: PRESSING ENT ON THIS PAGE WILL SELECT THE MANUAL LEG SWITCH. BE AWARE OF INADVERTENT SELECTIONS.

The display will switch to the CRS page after five seconds.

Enter Leg by Identifier 1. Press LEG . (The flight plan must contain waypoints). LEG page is displayed.

c LEG

Section 2 - Predeperture Procedures 2. Enter FROM waypoint IDENT.

BFL

NOTE: If the IDENT occurs more than once on the flight plan (waypoints 01-98), the pilot is given the option to press ENT to select the displayed WPT number, slew to select a different WPT number, or press CLR to reject the IDENT.

3. Press ENT.

CDU displays:

4. Enter TO waypoint IDENT. When the first character is entered, the software searches the WPT list for the first IDENT after the current TO that begins with that letter., If one is found it is displayed on line four. Pressing the /HLD key will place that IDENT on the entry line. The pilot may also continue entering characters and ignore the suggested prompt.

NOTE: If the IDENT assigned to this waypoint is a duplicate, the pilot must examine the coordinates and country of each duplicate and select the desired one. NOTE:. A FROM and TO waypoint with the same waypoint number cannot be entered.

5. Press ENT.

CDU displays:

page 2-36

Section 2 - Predenarture Procedures

The display will switch to the CRS page after five seconds.

Enter Leg by Waypoint Number

c

1. Press LEG.

LEG

LEG page is displayed.

2. Press A.N. Slew waypoint number line to the entry line.

A•N

CDU displays:

3. Enter FROM waypoint number. NOTE:

If the waypoint number 00 is selected as the FROM waypoint, a DIRECT TO will be performed (see DIRECT TO MODE in the ENROUTE PROCEDURES section for more information). The waypoint number must have a corresponding waypoint entered in the flight plan.

Section 2 - Prodeparture Procedures 4. Press ENT.

ENT

CDU displays:

5. Enter TO waypoint number. NOTE: A FROM and TO waypoint with the same waypoint number cannot be entered. Also waypoint 00 and blank waypoints are invalid.

6. Press ENT.

CDU displays:

The display will switch to the CRS page after five seconds or select another page.

4

Section 2 - Predeparture Procedures

A

WPT PAGE FLIGHT PLAN VERIFICATION Verify waypoint data as follows: 1. Press WPT.

WPT FH

CDU displays the active flight plan.

2. Press EXP.

z EXP

CDU displays: Waypoint name and no., waypoint lat/long, course and distance from previous waypoint.

3. Verify the data. NOTE : If the true mode has been chosen, True Course (TC) will be displayed in place of Magnetic Course (MC). 4. Press slew -up key to view next waypoint data. 5. Repeat steps 3 and 4 to verify the flight plan.

R

4

Section 2 - Predeparture Procedures

w

Section 3 Enroute Procedures LEG SWITCHING Leg switching from one leg to the next is normally performed automatically by the INS; however, manual leg switching may be selected if desired.

AUTOMATIC LEG SWITCHING The annunciation of the automatic leg switching sequence varies between 1.5 and 3.0 minutes prior to reaching the next waypoint , and is determined by-the ground speed of the, aircraft and the change in the track angle between the new and the old track legs . When a leg change is to be made but no data for the next waypoint has been entered , the Alert lights will begin flashing 4 minutes prior to reaching the last entered waypoint . The alert lights will continue to flash until data is entered . The CDU will display the message "NO NEXT WAYPOINT" on all CDU pages until the pilot presses CLR to acknowledge the message. If the TO waypoint is overflown without a subsequent leg inputted , the system will revert to the MANUAL leg switch mode and continue on an extension of the previous track.

TP92- 04-13 -B

page 3-1

Section 3 - Enroute Procedures

•

LEG SWITCH LESS THAN 25 DEGREES The alert light will come on 90 seconds before the leg switch occurs. The leg switch will occur 22 seconds before the TO waypoint is reached, i.e., at Time To Go (TTG) = 225. WPT 6 ALERTLIGHT ON FLIGHT 90 SECONDS BEFORE PATH LEG SWVTCH I^ LEG SWTICH < 25'

WPT 4

WPT 5 LEG SWITCH OCCURS ATTTG = 22 SECS

Leg Switch Less Than 25 Degrees Figure 3-1

LEG SWITCH BETWEEN 25 AND 110 DEGREES The alert light will come on 90 seconds before the leg switch occurs. The leg switch will occur between 22 and 93 seconds before the TO waypoint is reached, dependent on ground speed and angle change. WPT 15

WPT 14 LEG SWITCH OCCURS ATTTG 22TO m SECS

Leg Switch Between 25 and 110 Degrees Figure 3-2

Section 3 - Enroute Procedures 0

LEG SWITCH GREATER THAN 110 DEGREES The ALERT light will come on 90 seconds before the TO waypoint is reached. The leg switch will occur when the TO waypoint is reached.

Leg Switch Greater Than 110 Degrees Figure 3-3

Section 3 - Enroute Procedures MANUAL LEG SWITCHES In the manual leg switching mode , the alert lights will illuminate 1 .5 to 3.0 minutes prior to reaching waypoints, depending on ground speed and track angle change. Once the system calculates that a leg switch should take place, the alert lights will start flashing and the leg switch must be entered manually. The CDU will display the message "SELECT NEXT WPT" until the pilot presses CLR. If the autopilot is engaged and a switch is not made , the aircraft will continue on an extension of the previous track.

CDU displays:

1. Press CLR to delete the "SELECT NEXT WPT" message.

2. Press LEG.

.

CLR

c LEG

The Leg Change page will be displayed with the IDENTs for the leg just flown on line 3 and the corresponding waypoint numbers on line 2. Example assumes aircraft has just flown from ALO and passed over IRK. 3. Press A • N and slew down one line to place the waypoint numerics on the entry line.

Y

0

Section 3 - Enroute Procedures 4. Input the number for the waypoint that was just overflown in the flashing prompt on the left side of the entry line. 5. Press ENT. The new FROM waypoint is accepted , and the next sequential waypoint from the flight plan will flash on the right side of the entry line. 6. Input the desired waypoint number in place of the flashing prompt (bypass this step if the flashing prompt is correct.) 7. Press ENT. The IDENTS for the new leg will be displayed on line 2. The system will automatically revert to automatic leg switching, and after 5 seconds the display will revert to the Course Data page. If manual leg switching is still desired, it must be selected again. NOTE: Manual leg switching may also be accomplished by inputting then entering the (DENTS for the next leg instead of using their corresponding waypoint numbers.

Section 3 - Enroute Procedures

DIRECT TO MODE When DIRECT TO mode is selected, the INS will fly the aircraft directly from present position to any established waypoint. This is equivalent to a 00 to XX leg switch. If the waypoint is not on the flight plan, it will automatically be assigned waypoint number 99 (see figure 3-4). DIRECT TO can be performed using waypoint numbers or IDENTs.

NOTE: Performing a DIRECT TO will automatically select Auto Leg Switch mode.

Direct Tb Modes Figure 3-4

Section 3 - Enroute Procedures To select DIRECT TO mode using waypoint IDENTs: 1. Press DIR.

J DIR

DIRECT TO page is displayed with DIRECT TO prompt on entry line, requesting the waypoint ident.

NOTE: During ALPHA entry, the software will search the remaining waypoint list after the TO waypoint for IDENTs having the same letters as those entered. If found , that IDENT is displayed on line four with a prompt indicating that the /HLD key may be used to select this IDENT as the DIRECT TO (DENT. Character entry can continue up to the six character limit to allow easy reference waypoint entry.

2. Enter desired waypoint (DENT.

Section 3 - Enroute Procedures w

3. Press ENT.

Coordinates of Direct to waypoint are displayed for acceptance.

ENT

After acceptance, the Direct to page displays for 5 seconds. Do not press ENT on this page unless you wish to terminate automatic leg switching.

After 5 seconds , the display changes to the normal CRS page. Line 1 confirms the system is in Automatic leg switch.

NOTE: If the IDENT assigned to this waypoint is a duplicate, the pilot must examine the coordinates and country of each duplicate and select the desired one. NOTE: If the IDENT occurs more than once on the flight plan (waypoints 01-98), the pilot is given the option to press ENT to select the displayed WPT number, slew to select a different WPT number, or press CLR to reject the IDENT.

Section 3 - Enroute Procedures To select DIRECT TO mode using waypoint numbers: J D

1. Press DIR.

2. Press A • N twice to select waypoint number only.

A•N

3. Enter the desired waypoint number (leading zero is not required) or press ENT to accept the flashing default.

ENT 4. Press ENT. The coordinates of the Direct to waypoint are displayed for acceptance.

5. Press ENT to accept.

February 1996

ENT

TP92-0413-B page 3-9

Section 3 - Enroute Procedures

r 6. If MANUAL leg switch mode is desired, press ENT. If no key is pressed , the display will switch to the CRS page after five seconds. If the system was in MANUAL mode, it will change to AUTO. NOTE: Invalid waypoint numbers include waypoint 00 or blank waypoints. If any of these are selected, error messages will result and no action will be taken by the system.

DIRECT TO STEERING When a Direct To leg switch is entered , the INS establishes a pseudo FROM waypoint at the exit from the turn, (thus avoiding S turns), and will capture and maintain a track leg from this new FROM point to the DIRECT TO waypoint ( refer to Figure 3-4). The pseudo FROM waypoint coordinates are stored in

waypoint zero .

WAYPOINT BYPASSING Waypoints may be bypassed either by a waypoint to waypoint leg switch or by a Direct To leg switch (see figure 3-4).

it

Section 3 - Enroute Procedures

CROSSTRACK OFFSET MODE To fly an offset track parallel to present track:

1. Press CRS.

B CRS F

CRS DATA page is displayed.

2. Press slew - up key and EXP.

z EXP

XTK OFFSET page is displayed with XTK OFFSET prompt on the entry line.

3. Select left offset (L7) or ❑ s or right offset (9R). L7

u 9R

Section 3 - Enroute Procedures

f

4. Enter offset distance (5.3 nm) to nearest 1/10 nm, including trailing zeros. (Maximum allowable value is 399.9 nm)...

5. Press ENT. Display returns to normal CRS page except XTK OFF is displayed in place of XTK.

OFS annunciator comes on. i NOTE: The XTK OFF value displayed on the CRS DATA page is the XTK from the original track. As the aircraft steers to the offset track, XTK OFF will increase.

6. To view the XTK OFFSET value entered, press EXP. If the aircraft is on the offset track, the value won't change.

The aircraft will be steered to the offset track using up to 45' intercept to capture the offset track (ref. Figure 3-5). The time to go and distance displays refer to the time and distance to the offset waypoint . The leg switches will occur at or before the offset waypoint and the aircraft will maintain the offset track.

Section 3 - Enroute Procedures

7. To return to original leg:

Make a DIRECT TO leg change ( see figure 3-4). OR Repeat steps 1 through 3 and press ENT to enter XTK OFFSET of 0.0 nm.

NOTE: Crosstrack offset is inhibited by: Descent below 10, 000 feet when RNAV or GPS is enabled (active or not).

APPROACH mode selected. Track Hold mode selected. DIR TO is performed. When the FROM waypoint # is 00.

do0 TAN b„

Crosstrack Offset Leg Change Figure 3-5

Section 3 - Enroute Procedures

TRACK HOLD MODE In track hold mode , the flight path is referenced to true or magnetic north rather than to a waypoint to waypoint track (figure 3-6). The system will steer the aircraft along the entered track.

1. Press CRS.

CRS DATA page is displayed.

z

2. Press EXP. l

CRS TRK HOLD page is displayed with DTK prompt on the entry line.

3. Enter desired track angle to nearest 1 /10 degree, including trailing zeros.

2 3 0

Section 3 - Enroute Procedures 4. Press EM.

ENT

Entry line flashes momentarily.

NOTE: The system will capture the track after flying a lateral displacement determined by maximum roll rate, airspeed , and type of autopilot. NOTE: LEG and DIRECT TO page will display TRACK HOLD MODE on line 5. The FLIGHT PLAN page will display NO TRACK LEG SELECTED. NOTE: Waypoint to waypoint mode may be resumed by entering a DIRECT TO or a LEG switch. NOTE: The alert (ALR) annunciator on the CDU will flash while Track Hold Mode is engaged.

Track Hold Mode Figure 3-6

Section 3 - Enroute Procedures

FLIGHT PLAN DATA 1. Press FPL.

I FPL

FLIGHT PLAN page is displayed with distance from present position to each waypoint. NOTE: If no waypoints have been entered into the flight plan, the message "ROUTE/WPTs NOT SELECTED" is displayed . If a leg has not been selected , the message "NO TRACK LEG SELECTED" is displayed.

DIST

Total distance along flight plan between present position and waypoints.

2. Slew waypoint list up or down to view flight plan.

Q

or

Y

3. Press EXP.

TIME to designated WPT is displayed in hours and minutes.

TIME.

Time from present position to waypoints ( following the flight plan). Time is based on actual ground speed , but if actual ground speed is less than 100 knots, the time display is blanked.

6

Section 3 - Enroute Procedures 4. Press EXP.

z EXP

ETA displayed (GMT must have been entered). The FROM waypoint will display the GMT at which the waypoint was overflown. ETA:

Estimated time of arrival at waypoints in Greenwich Mean Time. If ground speed is less than 100 knots, the ETA is blanked.

5. Press EXP.

Distance between waypoints (DBW) is displayed.

DBW.•

Distance Between Waypoints.

6. Press EXP

Display returns to FLIGHT PLAN distance page.

Section 3 - Enroute Procedures EFIS'10" WAYPOINT CHANGE When the INS is interfaced with a compatible EFIS, the pilot may change the TO waypoint via the EFIS joystick. The WPT display will change the current TO waypoint to EFIS. When an EFIS TO waypoint change is performed , the system will automatically perform a Direct To leg change to the EFIS waypoint.

To view the coordinates of the EFIS selected TO waypoint: 1. Initiate EFIS TO waypoint change operation on the EFIS. The TO waypoint ident is changed to +EFIS.

2. Press WPT.

WPT Page is displayed.

3. Slew the TO waypoint q (+EFIS) to the entry line.

V

.

Section 3 - Enroute Procedures 4. Press EXP The EFIS selected waypoint latitude and longitude are displayed.

z EXP

An EFIS waypoint may be canceled by performing a DIRECT TO, selecting a new leg , or by performing one of the waypoint deletion (Ref. Section 2) procedures.

COURSE DATA When the CRS key is pressed, the following information relating to the current leg is displayed (refer to section 12).

B CR5

Track Change Mode (Auto/Manual) FROM and TO waypoint IDENTs Desired track Crosstrack distance (crosstrack offset, if entered) Track angle error Distance to TO waypoint Time to TO waypoint

Section 3 - Enroute Procedures

INSTRUMENT DATA When .the DATA key is pressed , the following information relating to aircraft instruments is available . The Magnetic or True Heading display mode can also be selected (refer to section 12).

i

0 DATA

Track angle Ground speed Wind speed Wind direction Nose component of wind (head/tall) Aircraft heading True airspeed

Along track acceleration Drift angle Altitude (feet/meters) DMENOR frequency TACAN channel number Heading , pitch , and roll

•

S

REMOTE RANGE When the RMT key is pressed , the pilot can get track information listed below between 2 waypoints or present position and a waypoint (refer to section 12). Desired track (MAG or TRUE) Distance Time

Q RMT

Litton Section 4 Post Flight Procedures, Rapid Realignment and Nav Update ACCURACY TEST If INS accuracy monitoring is desired , the pilot may perform an accuracy check via the following procedure. This test can be performed at any time . It is for display purposes only and has no effect on INS computations. NOTE: This procedure should only be performed when an accurate ramp position is available or GPS data is available.

1. Press STS.

SYS STS/TEST page is displayed.

2. Press slew up key until ACCURACY TEST is on

the entry line.

R

4

Section 4 - Post Flight Proc, Rapld Realign, Nat' Update

3. Press EXP. The ACCURACY TEST page is displayed with prompts for latitude and longitude entry, or slew local ID to the entry line and insert ramp IDENT (VNY).

VNYF 4. Press ENT.

5. Press ENT to accept coordinates. UDT ERR (updated error), INS ERR (inertial error), INS DFT (inertial drift), and RESID GS (residual ground speed) are displayed. The INU compares the entered ramp position against: a. The updated position (UPD ERR) which comprises inertial position plus GPS/RNAVJT'MIX/MANUAL corrections. b. The pure inertial position (INS ERR) Pure inertial drift (INS DFT) and residual ground speed are also displayed , and are the two criteria to be used in the SYSTEM ACCURACY REMOVAL CRITERIA portion of Section 4.

Residual ground speed is zeroed if the aircraft remains stationary for 3 minutes, see NAV UPDATE MODE portion of Section 4.

n

Section 4 - Post Fllaht Prot, Rapld RnBgrr, Nav Update

INTERMEDIATE STOPS At intermediate stops three events can improve the accuracy of the INS. 1. Full Alignment A full 10 minute alignment can be performed by turning the MSU either to OFF or ALIGN, then either restarting the INS and/or entering the aircraft Present Position. A full alignment is preferable since it has the most accurate results. .2. Rapid Realign A rapid realign can be performed from the STATUS page in 30 seconds . Present position is entered without cycling the system to off. It is similar in result to the Full Alignment above except that it may not completely remove a heading error. 3. Nay Update No pilot action is required. If no motion is detected for three minutes , the INS will automatically zero any residual groundspeed , remove any platform tilt , apply a small correction to position and heading to correct for the tilt error that was found. Which of the above 3 to use is a judgement call by the operator. Perform an accuracy test. If the system is sufficiently accurate , then doing nothing will allow the Nav update to function . Other considerations are the length of the last leg and the length of the stop , as the position error will grow with time. If the stopover time allows, a full alignment is recommended.

Section 4 - Post Flight Proc, Rapid Realign, Nay Update

The following chart summarizes the alignment types: Type of

Position

Velocity

Heading

Tin

Time

Alignment

Corrected

Corrected

Corrected

Corrected

Required

Full Align

yes

yes

yes

yes

10 mins

Rapid Realign

yes

yes

partial

yes

30 secs

Nav Update

partial

yes

partial

yes

instant*

*Assuming the aircraft has been stationary for at least 3 minutes.

CAUTION:

In strong wind conditions , the aircraft may not be stable enough to allow a full alignment or a rapid realign. In this event leave the INS on, press POSition and manually correct any position error. A Nav update will occur when the aircraft is stationary for 3 minutes , and will correct the velocities and any platform tilt. This action is only applicable in extreme weather conditions.

Sac$ion 4 - Poet Flight Proc, Rapid RnJ iqn, Nav Update POST FLIGHT PROCEDURES At completion of flight, set mode switch to OFF. NOTE: There is a 12 -second shutdown delay before the INS shuts down. During this time the system is storing information into memory. Do not pull circuit breakers to the INS until the system CDU blanks after the MSU has been turned to OFF.

The INS may be left in NAV if: 1. This is an intermediate stop. 2. Primary operating power is continuously available. 3. System realignment is not required. CAUTION : WHEN PRIMARY OPERATING POWER IS INTERRUPTED, THE INS AUTOMATICALLY SWITCHES TO DC BACKUP POWER AND WILL DEPLETE AN INS BATTERY IN 15 TO 30 MINUTES (BATTERY DEPENDENT). PLACE MSU SWITCH TO OFF WHENEVER PRIMARY POWER:

• IS SHUT DOWN. • MAY BE SHUT DOWN. • IS OF DOUBTFUL DEPENDABILITY.

TP92-04138

page 4-5

Section 4 - Post Flight Proc, Rapid Realign, Nav Update

SYSTEM ACCURACY REMOVAL CRITERIA The INU should be removed from the aircraft iifeitherthe position or the ground speed is observed as follows: 1. Position

A. For radial position error, refer to figure 4-1. For drift rate refer to figure 4-2. B. For RNP-10 airspace radial position error, refer to figure 4-3. For RNP-10 airspace drift rate refer to figure 4-4. 2. If the residual ground speed exceeds 15 knots on two consecutive flights or 21 knots on a single flight. NOTE: When the aircraft is on the ground and no motipn is sensed for three minutes, the INS will automatically reset the residual ground speed to zero.

RAPID REALIGNMENT When making an intermediate stop and it is desired to increase system accuracy; a rapid realignment may be performed while the aircraft is stationary. 1. Ensure the MSU mode switch has not been moved out of NAV.

2. Ensure primary power will be continuously available. 3. Press STS.

STS/TEST page is displayed.

4. Slew RAPID REALIGN to entry line.

page 4-6

TP92-04138

April 1998

Seetlon 4 - Post t7fght Proc Rapid Resogn

0 33

30

25

20

is

10

7.5

a

0 1 2 3 4 5 6 7 6 9 10 11 12 13 14 15 16 17 18

NAV TIME (HOURS)

TPB2.OSO5 l

Radial Position Error Figure 4-1 April 1998 TP92-0413B

page 4-7

Sscton 4 - Post FYght Proq Rapid Realign, May Update

7

UNACCEPTABLE REMOVE INU 6

CHECK ON NEXT FLIGHT. IF STILL IN OR ABOVE THIS AREA AFTER 2ND FLIGHT, REMOVE INU

4

3

2

I

1

0 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 18 16 17 18 NAV TIME (HOURS)

Drift Rate Figure 4-2

page 4-8

TP92-04138

April 1998

Section 4 - Poet FUght Proc, Rapid Res i i _Nav Update 35

as

25

10

0 S

0 o

1

2

3

4

5 S 7 S 0 10 It 12 13 14 15 16 17 IS HAV7YE Q1011RS)

1P -0S13r 1

RNP-10Airspace Radial Position Error Figure 4-3

APr11 1998 TP92-0413B

page 4-9

Section 4 - Post Flight Proc, Rapid Realign, Nav Update 7

I

6

2

I

0 0 1 2 a

4 5 6 7 6 0 10 11 12 16 14 16. 16 17 16

NAV THE (HOURS) T §2-OItSSF2

RNP-10 Airspace Drift Rate Figure 4-4

page 4-10 TP92-0413B

April 1998

Sidon 4 - Post F9gM Proc. Rapid RnUgn. Nev Updab

5. Press ENT. The MSU ALIGN annunciator comes on , any current leg will be deselected, and the CDU displays the message "ENTER PPOS."

ENT

6. Select the Position page (POS) and enter present position . GPS position will be displayed for acceptance if valid.

30 seconds after present position is entered , the MSU ALIGN annunciator goes out and the system automatically re-enters NAV mode. CAUTION : THE AIRCRAFT MUST NOT BE MOVED DURING A RAPID REALIGN. NOTE: When a rapid realignment cannot be performed due to residual GS or aircraft movement, a message explaining the problem will be displayed. NOTE : The system must remain in the NAV mode for 69 seconds following an alignment before a rapid realign can be performed.

NAV UPDATE MODE The Nav Update mode is a function which automatically acts to remove residual errors from inertial computations once the aircraft is stationary for three minutes. Similar to selecting NAV for initial alignment, the Nav Update mode will remove all residual ground speed, eliminate any gyro biasing errors, and compute a heading update . The significance of this mode to the pilot is that if the aircraft is stationary for over three minutes , residual ground speed may be automatically zeroed before the pilot can determine if it is within tolerance. Although INS system drift errors are likely to be discovered through INS ERR and INS DFT readouts, residual ground speed should be noted from the DATA page before three minutes elapse during any aircraft stationary period..

April 1998 TP92- 0413B

page 4-11

Section 4 - Post Flight Proc, Rapid Realgn, Nav Update

page 4 - 12

TP92-04138

Section 5 Cross fill Crossfill is a transfer of data from one INS to another. Manually commanded, crossfill is used to sequentially transfer waypoints , routes, GMT and date. Crossfill is initiated using the Remote (RMT) key. The sending unit is designated "MASTER" and the receiving units are designated "SLAVES."

There are five selectable options of crossfill transfer: • Time Initialization - will transfer the GMT entered into the master unit.

• Date Initialization - will transfer the date entered into the master unit. • Aux Memory to Flight Plan - will transfer a stored route to the Flight Plan page of the receiving units. • Aux Memory to Aux Memory - will transfer a single waypoint from the master custom or crew catalog to the receiving unit crew catalog. • Flight Plan to Flight Plan Transfer - will erase the Waypoint Select page of the receiving unit(s), and then crossfill all 98 waypoints from the master to the slave(s) one by one, whether there is any data assigned for all the waypoints or not. Total time to transfer all 98 waypoints will take approximately 2 minutes. As each waypoint is crossfilled, the message 'WPT XX TRANSFER' will appear on the master and the slave page 5-1

Section 5 - Crossfill display. A cue "CLR: ABORT XFILL" will appear on line 5 to remind the pilot that the crossfill can be hafted at any time. NOTE: FROM/TO waypoint designations are not crossfilled. CAUTION: A FLIGHT PLAN TO FLIGHT PLAN CROSSFILL AUTOMATICALLY DELETES ALL WAYPOINTS FROM THE WAYPOINT SELECT PAGE OF THE SLAVE SYSTEM(S): IF THE AUTOPILOT IS COUPLED TO A SLAVE SYSTEM INS, THE AUTOPILOT WILL DISCONNECT WHEN THE CROSSFILL IS INITIATED. THEREFORE , IF PERFORMING A CROSSFILL WHILE AIRBORNE , ONLY THE MASTER SYSTEM SHOULD BE COUPLED TO THE AUTOPILOT.

CROSSFILL PROCEDURES 1. Press RMT on all CDUs.

CDU displays:

2. Slew "XFILL SLAVE" to entry line on receiving CDUs and press ENT.

CDU displays:

page 5-2

G RMT

Section 5 - Crossfill

3. Slew "XFILL MASTER" to entry line on the sending CDU and press ENT.

ENT

CDU displays:

4. Slew until desired crossfill option appears on entry line , and press ENT (see previous page for options). Display shows "READY" for each INS designated as a slave.

5. Press ENT on master CDU to initiate crossfill. Waypoint list will transfer one by one from 01 to 98 unless crossfill aborted. Use CLR to abort crossfill after required number of waypoints are transferred.

Crossfill complete:

ENT

ENT

Section 5 - Crossfill

utton

Section 6 Position Updating During NAV mode the INS position can be updated in three ways:

1. Automatic RNAV Position Update. 2. Automatic Triple Mix (TMIXJ Position Update. 3. Manual Position Update. This allows each INS to use an external source to correct inertial drift errors. NOTE: The acronym for Area Navigation (RNAV) is commonly used in the Pilots ' Guide and on the CDU displays to refer specifically to the use of Radio navigation aids (TACAN, VOR, etc.).

EASY ON/OFF .STEERING Whenever a position update occurs (due to RNAV, TMIX, or a Manual update) that corrects the INS Latitude and Longitude, the position page will slew to show this new Present Position . If this update corrects the position to a point which is off Desired Track, then the steering signal to the HSI/Autopilot will steer to bring the aircraft back onto track. To enable a smooth and easy transition , the HSI/Autopilot steering to recapture desired Track is limited to a maximum rate of 1. 9 nmi/min . This "Easy On/Off Steering " causes shallower slower maneuvering during track recapture.

April 1998

TP92-04138

page 6-1

Section 6 - Position Updating Easy On/Off Steering only operatesfortrack recapture following a position update; it is never used for normal turns at waypoints, it is not used when : in approach mode, (RNAV Approach); below 10,000 ft; or when ground speed is less than 250 knots.

page 6-2 TP92-0413B

Section 6 - Position Updating POSITION CHECK To compare . updated position to nonupdated (pure inertial) position or to check updated position against a known fix position , perform the following: 1. Press POS.

A POs

POSITION page is displayed.

< >

2. Press HLD.

HLD

Display freezes and nonupdated latitude and longitude are also displayed on lines 4 and 5.

< >

3. Press HLD.

HLD

Display unfreezes and returns to normal POSITION page.

NOTE: During the display freeze, the INS continues to calculate present position based on aircraft movements but they are not displayed.

TP92-0413B

page 6-3

Section 6 - Position Updating

4

AUTOMATIC POSITION UPDATING Automatic position updating allows the INS to make fine corrections to the calculated position by referencing position datafrom eitheroftwosources: Radio (TACAN orVOR/DME), or Triple system Mixing (TMIX). Each INS system uses a hierarchy in determining which system to use for updating, first it will select RNAV then TMIX. Whenever a position update is performed, the updated position will be used for all horizontal guidance computations. If desired , however, all updates can be flushed at any time to return to using the non updated (pure inertial) parameters. An indication of which system is currently being used by the INS for updating is given in the top left corner of the CDU display. A letter 'R' indicates Radio updating in progress, a'T' indicates TMIX updating in progress , and an ' E' indicates that although updating is Enabled no updates are currently being performed . The 'R' remains displayed for up to one minute following loss of update , preventing nuisance toggling of the display during signal interruptions. When an update is performed the INS present position changes to a new updated position. At INS turn- on, GPS updating is enabled (whether the aircraft is equipped with GPS or not). An "E" is displayed in the top left of the display to indicate this enable . RNAV and TMIX updating must be enabled when required (referto ENABLING POSITION UPDATING in this section).

4

page 6 -4

TP92-0413B

April 1998

Section 6 - Position Updating

The steering commands to the flight guidance system to correct for any new crosstrack error will vary with sensed altitude and airspeed of the aircraft . If the aircraft is below 10,000 feet immediate corrections will be made. Otherwise the steering corrections will be somewhat less pronounced (see Easy On/Off Steering). The flight guidance system will steer the aircraft using up to a 454 intercept to eliminate the crosstrack error.

RNAV updating can be monitored via the UPDATE / NO UPDATE annunciators on the instrument panel (where installed). UPDATE (green) illuminates when an RNAV update is in progress . NO UPDATE (amber) indicates that although RNAV updating is enabled, it is not currently being performed . To prevent nuisance warnings there is a one minute delay between sensor loss and a NO UPDATE annunciation.

Section 6 - Position Updating

RADIO UPDATING NOTE: The acronym for Area Navigation (RNAV) is commonly used in this pilots ' guide and on the CDU displays to refer specifically to the use of Radio navigation aids separate from GPS. RNAV updating allows the INS to correct the calculated position by referencing the position of the aircraft relative to the known latitude , longitude , elevation, and magnetic variation of selected radio navigation aids, and using the received range (R) and bearing (®) data from TACAN, VOR/DME. In dual or triple systems , navigation station data (bearing, distance, frequency) from VOR/DME/TACAN No. 1 is processed only through INS No . 1. DME or TACAN range data is then automatically crossfilled to INS 2 and 3. Similarly, navigation data from VOR/DME/TACAN No. 2 is processed only through INS No. 2 before range data is transferred to INS No. 1 and 3. Each INS uses a hierarchy when determining which navigation receivers and stations to use for RNAV updating. Range - Range (R/R) update is preferred. In autotune the INS will test for two DME or TACAN stations that are 900 off in position relative to each other and the aircraft . To perform a R/R update , the angle formed by drawing direct lines from each station to the aircraft must exceed 30°, but be less than 150'. If two DME or TACAN stations are not available, or the 300 - 150° geometry is not met, the INS will attempt to perform a range - bearing (R/O) update from a VOR/DME or TACAN station.

RNAV updating is not active during INS alignment. Number 3 INS only receives crossfill range information from INS #1, and INS #2, and can only perform a R/R update.

Section 6 - Position Updating When RNAV updating on aircraft equipped with autotune. capability, the VHF Nav radios may be tuned automatically from the INS . If the FGS AUTO TUNE switch is in the AUTO TUNE position the INS will select the desired stations out of the LOCAL STATION catalog , then update using those stations. The LOCAL STATION catalog is refreshed every ten minutes to include the forty closest stations to the aircraft. After using -a station for two minutes, the INS will retune to another station and update again . If no data is received on a frequency after 15 seconds the INS will retune to another stations. On aircraft without autotune capability , or if the FGS AUTO TUNE switch is in MANUAL, the pilot must select an appropriate station frequency. The INS will search all catalogs for the station that corresponds to the set frequency in the vicinity of the aircraft, then update based on stored information.

The received range and bearing data from the VOR/DME/TACAN equipment are required to pass reasonableness tests before being used for update. Each INS acts independently in when updating calculated position. RNAV updating is normally disabled . When required , it must be enabled using the procedure in this section. RNAV updating will not take place if GPS updating is in progress. Because of the increased accuracy of GPS, it is not recommended that RNAV updating be enabled during short GPS outages.

TACAN Auto Tune is enabled-by selecting TACAN channel 00.

Section 6 -Position Updating

RNAV Update Sources INS 1

INS2

INS3

DME VOR TACAN Offside DME (DME2) Offside TAC

DME VOR TACAN_ Offside DME (DME1 ) Offside TAC

-DMEI DME2 TACAN 1 TACAN 2

RNAV Update Priorities INS I and INS 2 1. DME 2. DME 3. DME2

DME 2 TACAN TACAN

TACAN

(R/R/R) (R/R) (R/R)

4. DME

DME2

(R/R)

5. TACAN 6. TACAN -

TACAN

(R/R)

7. DME VOR 8. VOR

(R/Q) (R/Q) TACAN

(Q/R)

9. Enabled (Not updating) INS 3 DME1

DME2

(R/R)

DME1

TACAN

(R/R)

TACAN TACAN Enabled (Not updating)

DME2 TACAN

(R/R) (R/R)

Section 6 - Position Updating

ENABLING POSITION UPDATING This procedure simultaneously enables all update modes (GPS, RNAV, and TMI)).

1. Press STS to display the System Status/Test page. CDU displays:

2. Press the slew down key once to move "UPDATE" to the entry line. The message "CHANGE UDT MODE" will appear on line 3.

3. Press EXP to select the update mode menu. Slew the display until "ENABLE UPDATE" is on the entry line.

Y

0

4. Press ENT To enable RNAV updating. To disable RNAV updating, follow the above procedure, then with "DISABLE RNAV" on the entry line in step 3, press ENTER.

ENT

page 6-9

Section 6 - Position Updating

RNAV INHIBIT FUNCTIONS The following is the full list of update mode functions.

DISABLE RNAV ENABLE UPDATE DISABLE GPS DISABLE TMIX FLUSH INHIBIT VOR. INHIBIT TACAN INHIBIT DME 2 INHIBIT DME This menu is accessed at step 3 on the previous page. The four inhibit functions when activated will inhibit the INS from using either VOR , or TACAN, or DME2 (DME data processed through the opposite INS), or the directly coupled DME.

Section 6 - Position Updating

DME/VOR RELATED MESSAGES DME INVAL

INS is not receiving the +28VDC VALID signal from analog DME.

AUTOTUNE FAIL

INS test of the NAV control head tuning lines has failed.

TAC CNTRL INVAL

TACAN control data indicates TACAN is in self-test or not in T/R mode.

D-STMT-STA NOT IN CAT

INS unable to find a station match for the selected frequency within a 200 mile radius of aircraft present position.

DME DATA INVAL or TACAN RNG INVAL

INS has detected a problem in the DME/TACAN range data. Data will not be used. (Ex.: >200 nmi slant range.)

DME ERR/ TAC RNG UNREAS

Received DME/TACAN range differs from INS estimated range by more than 40 nmi. Data will not be used.

AIRCRAFT ABOV STA

INS computes PPOS to be in a 60° cone above the VOR/DME/TACAN station. INS rejects data.

DME/T-RNG UDT UNREAS

INS detects a sudden DME/TACAN range error. Data is not used.

VORINVAL

INS is not seeing the analog VOR 26 VAC reference or VOR +28 VDC valid discrete.

VOR DATA/ TAC BRG INVAL

INS has detected a problem in the VOR/TACAN bearing data. Data is rejected.

Section 6 - Position Updating

DME/VOR RELATED MESSAGES (continued) Received VOR/TACAN bearing does not VOR ERR/ TAC BRG agree with the INS estimated bearing. UNREAS Data is rejected. VOR/T-BRG INS detects a sudden VOR/TACAN bearUDT UNREAS ing error. Data is not used.

DME RANGE CROSSFILL RELATED MESSAGES XFL A INVAL*

INS is not receiving a +28VDC valid from SYS A. DME range data from SYS A is rejected.

XFL B INVAL*

INS is not receiving a +28VDC valid from SYS B INS. DME range data from SYS B is rejected.

XFLARNG INVAL

INS is not receiving DME range data from SYS A INS. Crossfill A range data will not be used.

XFL B RNG INVAL

INS is not receiving DME range data from SYS B INS. Crossfill B range data will not be used.

XFL A RNG UNREAS

Range from INS differs from SYS A INS by more than 40 nmi. Crossfill A range data will not be used.

XFL B RNG UNREAS

Range from INS differs from SYS B INS by more than 40 nmi. Crossfill B range data will not be used.

XFL A UDT UNREAS

INS detects a sudden crossfill DME range error in data from SYS A INS.

*When RNAV is enabled, but not updating, these two messages will always appear.

f

Section 6 - Position Updating DME RANGE CROSSFILL RELATED MESSAGES (continued) XFL B UDT UNREAS

INS detects a sudden crossfill DME range error in data from SYS B INS.

2 RNG GEOM FAIL (DMEDME range update mode)

Aircraft is not within a 30° to 150° bearing of station area. INS will not perform a DME-DME range update.

OTHER MESSAGES ADS INVAL

INS is not receiving +28VDC valid from air data system . RNAV is inhibited.

ALT INVAL

INS does not detect altitude from ADS or is failing to compute valid baro- attitude. RNAV is inhibited.

LAT > 89°

INS computes the aircraft updated PPOS latitude as being above N/S 89 °. All updating will be inhibited until PPOS is below 89°, and will then resume in the previously selected mode.

SYS NOT IN NAV

RNAV updating rfiay only take place when the system is in NAV mode.

page 6-13

Section 6 - Position Updating

STS/UPDATE PAGE SUMMARY Updates disabled

RNAV updates enabled. Not updating.

RNAV updating:

Press slew-down key.

Y 0

CDU displays:

NOTE: If a TACAN is not present, the ident and channel # will be blank. If a DME that can tune multiple stations is being used , the display will automatically cycle to each frequency tuned.

Section 6 - Position Updating STS/UPDATE PAGE SUMMARY , (continued)

TMIX updates enabled, not updating.

TMIX updating.

April 1998

TP92-0413B

page 6-15

Section 6 - Position Updating

TRIPLE SYSTEM MIXING (TMIX) Triple system mixing is the averaging of the three INS positions . This averaged position is generally more accurate than just one INS position. Triple system mixing requires three INS positions . As all three INS's constantly talk to one another (whetherTMIX is enabled or not), any one INS can be selected to TMIX, and will calculate the average position . Each INS selected to TMIX will display and use the average position to navigate and steer by. The TMIX position calculation tends to discount the position of any one INS that appears to be drifting away from the other two, so that the further one INS position drifts , the less weight it has in the TMIX calculation. If one INS drifts away enough to generate a "comparison warning ," then triple system mixing is inhibited for the drifting system. The remaining two systems will continue mixing but will ignore the position of the drifted system. TMIX has the lowest priority in the hierarchy, and will only occur when RNAV updates are invalid or inhibited. TMIX is not enabled at system turn on , it can be enabled at anytime using the ENABLING POSITION UPDATING procedure in this section. Disabling TMIX assumes a problem with the triple mix solution and will flush the TMIX corrections from that INU (this has no effect on other INUs and does not flush previous RNAV corrections).

page 6-16

TP92-04138

Section 6 - Position Updating DISABLING TRIPLE SYSTEM MIXING 1. Press STS to display the System Status%Test page.

V STS

CDU displays:

2. Press the slew down key once to move "UPDATE" to the entry line. The message "CHANGE UDT MODE" will appear on line 3.

3. Press EXP to select the update mode menu. Slew the display until "DiSABLE TMIX" is on the entry line.

z EXP

4. Press ENT. To disable TMIX updating. To reenable TMIX updating follow the above procedure, then with "ENABLE UPDATE" on the entry line in step 3, press ENTER.

ENT

Section 6 - Position Updating

TRIPLE SYSTEM MIXING RELATED MESSAGES TMIX DATA INS is not receiving a +28VDC valid from INVAL the other INS systems, or, latitude/longi-

tude data is not present or not valid. Triple mixing is inhibited. INTERSYS COMP FAIL or CHECK SYSTEM ACCURACIES (STS page)

a. Latitude/longitude from one INS differs from other INS by more than 35 nmi for NAV time of 8 hours or less; 50 nmi for NAV time greater than 8 hours.

b. Ground speed from one INS differs from other INS by more than 50 kts. TMIX is inhibited if either of the above tests fail 1.

LAT>89°

INS computes the aircraft updated PPOS latitude as being above N/S 89°. All updating will be inhibited until PPOS is below 89°, and will then resume in the previously selected mode.

•

Section 6 - Position Updating STS/UPDATE PAGE DESCRIPTION The STS/UDT MODE page will display the update data listed below and indicated in the following figures. 1. UPDATE STATUS: G - GPS updates being (line 1 - left comer) performed R - RNAV updates being performed T - TMIX updates being performed E - Update enabled but not being performed Blank - no updates enabled 2. UPDATE MODE: INS - inertial ; no updates (line 1) being performed GPS - GPS updates being performed RNAV - RNAV updates being

MIX 3. RNAV UPDATE SOURCE: (line 2)

performed - triple mix updates being performed

All blank

- no source; no radio updates DME (slot 1) - using that

system's DME data VOR (slot 2) - using that system's VOR data

DME (slot 3)

using crossfill system's DME data

TAC (slot 3) - using crossfill system's TAC data TAC (slot 4) - using that system's TAC data

Section 6 - Position Updating NOTE: The third system displays only 2 slots and updates using DME or TACAN crossfill range data from the other 2 systems. DIV - ident of the DMENOR 4. STATION TUNED: (line 4) station tuned TAC - Went of the TACAN station tuned. NOTE: The DMENOR station frequency or TACAN channel number may be viewed by slewing down once.

5. ADVISORY MES- If updates are not occurring and SAGES: updating has been enabled, Ad(line 5) visory Messages that explain why the system isn't updating are displayed. If more than 1 condition exists, the messages will automatically cycle.

Section 6 - Position Updating

MANUAL POSITION UPDATE Manual updating must be performed over a known fix position. 1. Press POS. 2. Press HLD. "H" appears in top left comer to indicate the displayed position is frozen and comparison of updated position with pure inertial position is displayed. 3. Compare displayed position with known fix to determine need for update.

4. If an update is not required , press HLD. Display unfreezes and returns to normal POSITION page.

If only LAT or LON is to be updated , press HLD after entering the desired parameter.

< >

HLD

If an update is required, proceed to step 5. CAUTION: WHEN IN FLIGHT AND INS COUPLED TO AUTOPILOT, THE AIRCRAFT WILL BE STEERED TO ZERO CROSSTRACK DEVIATION.

Section 6 - Position Updating 5. Slew LAT to entry line.

Y

0 6. Select North (2N) or South (8S).

7. and enter correct latitude. 8. Press ENT; updated latitude is displayed preceded by an asterisk (*).

9. Select West (W4) or East (6E).

L W4

10. Enter correct longitude.

NOTE: Manual position updates are inhibited above 89° latitude. If latitude is greater than 89°, the message LAT > 89° will be displayed . Press CLR to return to original display.

Section 6 - Position Updating 11. Press ENT; display returns to POSITION page with updated latitude/ longitude.

NOTE: The INS permits manual position updates of up to 30 nmi . If an attempt is made to perform an update of greater than 30 nmi , the message "DELTA > 30 nmi" is displayed (line 3 flashing) on the CDU. Pressing CLR will return to the previously displayed coordinate before the update was attempted.

Section 6 - Position Updating

FLUSH UPDATES When the FLUSH mode is selected , all position updates (GPS, RNAV, TMIX, MANUAL) will be zeroed and all three automatic updates will be disabled . The system will use inertial position for horizontal guidance.

1. Press STS; SYS STS/ TEST page is displayed.

v STS

2. Slew down once to move 'UPDATE' to the entry line. I CHANGE UDT MODE is displayed on line 3.

3. Press EXP and slew

. FLUSH option to line 3.

z EXP

Section 6 - Position updating

4. Press ENT.

CDU displays:

5. Press ENT to flush all updates.

ENT

CAUTION: IF UPDATES HAD BEEN PERFORMED THAT UPDATED THE SYSTEM'S POSITION, THE SYSTEM WILL SLEW. TO THE INERTIAL POSITION. IF AUTOPILOT IS ENGAGED, THE AIRCRAFT WILL BE STEERED TO ZERO THE NEW CROSSTRACK DEVIATION.

page 6-25

Section 6 - Position Updating

0

U' Section 7 RNAV Approach Procedures RNAV APPROACH MODE CHARACTERISTICS The system provides special features for aiding the pilot in the execution of an RNAV approach. The RNAV approach mode is optional and depends on the aircraft installation . When the approach mode is selected, the system will: • Change from true north reference coordinates to synthetic magnetic north reference coordinates if that mode had not been previously selected. • Change HSI crosstrack deviation scaling from 3.75 nmi to 1.0 nmi per dot. Provide automatic cancellation and inhibit selection of offset mode. • Provide 10-second waypoint alert annunciation prior to automatic leg switching. NOTE : "LOAD NEXT WPT" and "SELECT NEXT. LEG" messages are not displayed in approach mode. • Provide special annunciation at the Missed Approach Point (-MAP) waypoint: The system automatically inhibits automatic leg change at the -MAP waypoint and provides guidance on the extension of the previous track ; the HSI To/From indicator switches from To to From when -MAP is overflown. The alert annunciator comes on 10 seconds prior to the -MAP waypoint and flashes for 10 seconds past -MAP. page 7-1

Section 7 - RNAVApproach Procedures

RNAV APPROACH PROCEDURES •

NOTE: If magnetic reference is inhibited by aircraft installation option , approach mode will also be inhibited. To initiate an RNAV approach:

1. Press WPT. 2. Press A•N; display slews first unassigned waypoint number to entry line.

3. Enter sequential waypoint IDENTs from the RNAV approach chart into flight plan. 4. Enter the missed approach (- MAP) point. (Refer to Missed Approach Point Entry portion of section 7.)

CAUTION : MAP WAYPOINT MUST BE DESIGNATED TO PREVENT AUTOMATIC LEG SWITCHING AT THE MAP WAYPOINT. NOTE: Only one -MAP waypoint may be entered using the waypoint page. If additional -MAP waypoints are required , they must be entered in the CREW catalog first, and then inserted into the flight plan. 5. Manually tune VHF NAV frequency of designated VORTAC station (if in autotune , NO UPDATE/UPDATE annunciators will flash). NOTE: In a dual or triple installation a second station may be tuned to improve position updating by DME-DME update. NOTE: GPS equipped aircraft will use the INS/GPS position solution for navigation during the approach mode.

page 7-2

Section 7 - RNAV Approach Procedures

6. Set aircraft ENROUTE/APPROACH switch to APPROACH; aircraft APPROACH annunciator comes on; HSI switches from TRUE to MAG. 7. Verify radio update enabled and station data via STS page (see AUTOMATIC POSITION UPDATE). NOTE:

Continuous radio updating should be maintained using reference VORTAC for a minimum of 5 minutes prior to final approach. Aircraft UPDATE annunciator must remain on throughout final approach. RNAV approach must be terminated if UPDATE goes out and NO UPDATE annunciator comes on. A one minute delay occurs between continuous update loss and annunciation of NO UPDATE to eliminate nuisance annunciation of momentary update dropouts.

CAUTION : SYSTEM POSITION ERROR WILL INCREASE FOLLOWING LOSS OF CONTINUOUS RADIO UPDATING. 8. Proceed on approach path , noting sequential leg changes as each waypoint is overflown. 9. Execute a normal visual approach prior to reaching MAP. NOTE:

When MAP is missed , and a go around is executed, the system will provide only lateral guidance along the extension of the previous track to MAP or guidance to any waypoint if a DIRECT TO leg change is made.

Section 7 - RNAVApproach Procedures

MISSED APPROACH POINT ENTRY A missed approach point (-MAP ) is entered the same way a normal waypoint is entered into the flight plan.

With waypoint entry line at required MAP point:

1. Press - ,M,A, P, ENT keys . The display will prompt for LAT and LON entry.

- M A P

2. Enter LAT and LON for the missed approach point.

3. Press EXP to USE the waypoint (stored in CREW-temporary catalog).

4. Press CLR to REJECT waypoint and return to WPT entry mode. NOTE:

page 7-4

If multiple -MAP waypoints need to be entered, they must be entered using the CREW CATALOG page (refer to section 12).

Section 8 Attitude Reference Mode Attitude reference (ATT REF) mode normally is used only when an INS malfunction occurs and the WRN annunciator comes on steady. CAUTION : WHEN ATT REF MODE IS SELECTED, NAVIGATION CAPABILITIES ARE LOST UNTIL THE SYSTEM IS REALIGNED. NOTE : If the CDU WRN annunciator does not go out, the INS has completely failed. ATT REF mode may also be used if all power to the INS (including battery backup) is lost during flight and then restored. The ATT REF mode alignment requires that the aircraft be flown straight and level for 60 seconds . After ATT REF mode alignment , the only outputs available are pitch, roll, and platform heading and the system may not be coupled-to the autopilot.

Section 8 - Attitude Reference Mode To enter ATT REF mode, pull MSU mode switch out from panel and place in ATT REF. The CDU will switch to the STS Page. This is the only page available in ATT REF mode.

AUGN

The CDU will switch to this display wheneverATT REF is selected.

NOTE: Other SYS STS/TEST page functions are displayed (i.e., the autopilot flight director tests), but are inoperative.

page 8-2

Section 9 Summary of Display Pages and Function Keys o5 ..^ c"•'Ly' .^ewp.,, "

Wto°w'iC':.Oy^`d:?'•ci'a ji"""^a' :4a•«,. '.u::: *r4 tw' : w:^:`

.'v::q;>..a3:«.:5

n

wN.y.. ,.

POS

•Local ID

•Manual POS

(Position Page)

• Present position

Inertial comparison

update (e) • GMT entry (a)

Position Position

CRS (Course • Data Page)

-Active leg switching mode

D - Dist to next WPT (:) T - Time to next

XTK expanded: Crosstrack offset entry

(LattLong) •GMT •Updated position (HOLD) -Inertial position (HOLD)

• From/To WPT IDENTS

WPT (a)

• Desired track (true or mag) •XTK (Crosstrack

Desired track expanded: Track hold entry

error) •TKE (Track Angle error) LEG (Leg Change Page)

•From/To WPT #'s and ID's • Leg change entry by ID •Active leg switching mode

•Leg change entry by # (e) • Leg switching mode selection (auto or man) (a)

WPT (Waypoint Select Page)

-All Waypoints in sequence • Waypoint entry •FronV TO WPT #'s and ID's

• Selected WPT slowing (tie)

• Waypoint list editing FPL (Flight Plan

Page)

-Current Fit Pin WPTs • From/To WPT #'s

and ID's •WPTDistfrom

WPTs expanded: WPT Lat/Long Course from last WPT Dist from last

WPT • Remaining WPTs(e) •WPT diet from

(.e)

WPTs expanded: TIME to go

ETA or time over last WPT DBW (Dist between WPTs)

Section 9 - Summary of Display Pages and Function Keys

DIR (Direct To Page)

• FronVTo WPT Numbers • Direct To by WPT

(DENT -Active leg switching mode DATA (Instrument Data Page)

• Track Angle • Ground speed

• Wind direction and speed • Heading •DrifAngle •True Airspeed CAT (Catalogs Page)

•Standard

• Routes •Crew

•Custom • Local Station

• Direct To by WPT ID (A•N)

• MAG/TRUE selection (+r) • Flight path accieration (a)

Wind expanded: Head/tail wind component

-Attitude • Nav Aid Freq (:) •True Hdg/Pitoh/Ro l

(I,) •Select desired

catalog (e/e) • Select desired WPT

(EXP)

Catalog WPT expanded: •Lat)Long • Freq (nav aid only) •Mag Var (nav aid only) • Elevation (nav aid only) • Sta. class (nav aid only)

RMT (Remote Function Page)

•Xfill slave

• Remote range .)fill master

STS (System Sta- •Update Status tus/Test Page) 'Align Status •riimeto NAV/in NAV •Action mega

• Select Xfill slave(s) • Select XfiN master (4) (Remote range entered) WPT-> WPT # -> WPT # -> IDENT IDENT -> IDENT)

• Change UDT Mode (a) 'Malfunction nags (:) •Rapid Realign (a) • Display Test (a) •Accuracy Ted (.&)

• Dbase Type/Date(e) •GPS Status •4 AP/FLT DIR Tests (a)

)(fill Master entured)

•FLT PUN --> FLT PLN 'TIME INITIAUZATION

•AUX MEM --> FLT PLN •AUX MEM --> AUX MEM Change UDT Mode expanded: • Disable RNAV • Enable Update • Disable GPS • Disable TMlX -Flush W 'Inhibit VOR (:) • Inhibit TACAN (:) 'Inhibit DME 2 (a) •lnhibkDME (:)

Section 9 - Summary of Display Pages and Wnction Kays

POSITION PAGE Displays aircraft latitude and longitude in degrees, minutes and tenths and hundredths of minutes. Displays GMT (Slew up to correct GMT entry.) If no track leg has been selected, line 4 displays range and bearing to the closest station in the local station catalog.

HLD

When hold is pressed the CDU position display freezes. The Inertial position is displayed as well as the updated position. 'H' displays in top left corner on all pages until Hold is released. NOTE: The LAT/LON displayed on CDU lines 2 and 3 is the update position . This position calculated by the INS is used for all INS steering and range computations. This LAT/LON contains any GPS, Radio, TMIX or Manual corrections.

To exit these position pages , press HLD to remove the °H" from the CDU top left comer, then press any other function key.

Section 9 - Summary of Display Pages and Function Keys

COURSE PAGE An initial leg must be selected before course data can be provided. Line 1 shows the leg change mode, AUTO or MANUAL or XTK OFFSET or TRK HOLD. Line 2 shows the TO and the FROM waypoints. Line 3 shows desired track angle prefixed by a T (T-DTK) in True mode, and by an M (M-DTK in Magnetic mode. Line 4 shows Crosstrack (XTK) distance Right or Left of desired track, in nautical miles. In crosstrack offset mode will display XTK OFF. Line 5 shows Track Angle Error (TI(E) in degrees, Right or Left of desired Track Angle. Slew up to display Distance and rime from the aircraft's present position to the TO waypoint. Time is calculated using current ground speed, and will be zero if ground speed is too low (below 10 knots).

e CRS

Secfon 9 - Summary of Display Pages and Function Kars

LEG PAGE Line 2 shows the FROM and TO waypoint numbers. Line 3 shows the FROM and TO waypoint identifiers.

Line 4 shows AUTO or MANUAL leg change selection. Line 3 flashes to allow entry of new FROM ident. Press ENT to accept flashing default, or type in new FROM ident or press A • N and slew-down key to enter waypoint number mode.

To exit this page, press A • N to display N for Numeric in RH comer of display. Then select desired page "POS", or "STS" or "WT", etc.

page 9-5

Section 9 - Summary of Display Pages and Function Keys t

WAYPOINT PAGE

Displays waypoint numbers and identifiers. Annotates FROM and TO waypoints if a LEG is selected. Waypoint 00 is normally reserved for present position . Waypoint 99 is reserved for a DIRECT TO waypoint which is not in the flight plan.

Press desired waypoint number and ENT to jump to any desired waypoint. Press A • N to jump to first unused waypoint and display prompt line. Press EXPand to show Waypoint Lat/Long and bearing/ distance from the previous waypoint. Use up and down slew keys to slew through expanded data.

page 9-8

H WPT

4

Section 9 - Summary of Display Pages and Function Keys

FLIGHT PLAN PAGE

I FPL

Line 2 displays column headers. Lines 3, 4 and 5 display waypoint number and identifier and cumulative distance to each waypoint.

Successive pushes of the EXPand key will change the right column to display cumulative time to each waypoint, ETA at each waypoint, Distance Between Waypoints (DBW), then back to cumulative distance. Slew up and down to move through waypoint list.

z DIP

Section 5 - Summary of Display Pages and Function Keys • J DIR

DIRECT TO PAGE Line 2 displays FROM and TO waypoint numbers:

AN

Line 3 prompts for the DIRECT TO waypoint IDENT. Insert the identifier of the DIRECT TO waypoint and press ENT or select the waypoint number mode

(A • N) and Insert the desired waypoint number in the flight plan.

FLM HM BFL

ENT I

The coordinates of the DIRECT TO waypoint are displayed for acceptance.

Do not press ENT a second time unless you wish to be in MANUAL leg change mode.

After 5 seconds, display reverts to CRS page.

page 9-8

Section 9 - Summary of Display Pages and Function Keys

INSTRUMENT DATA PAGE. Line 2 shows aircraft track, either magnetic or true referenced . Ground speed is shown in knots.

Line 3 shows wind direction and speed . Wind values are blank if True airspeed input to the INS is too low. Pressing EXPand will display Head or Tail wind.

z r7W

Line 4 displays aircraft heading in True or Magnetic.

Line 5 displays Drift Angle (DA) Right or Left of aircraft heading. Slew down once to select Magnetic or True mode (if not inhibited by installation). Successive stewing up will show ACCELeration, along track acceleration in Gs. ALTdude in feet and meters (reference data only, not for flight altimetry use.) FREQuency of tuned DME/VOR station. Channel number (CHN #) of tuned Tacan station.

Pitch, Roll and true heading displayed to ±0.01 degree.

Y

0

Section 9 - Summary of Display Pages and Function Keys

CATALOG PAGE

P CAT

W

A list of available catalogs is displayed . Only four catalogs may be displayed on a single screen. Slew to view the other. NOTE: The ROUTES catalog lists routes that are contained both in Custom memory and in the World Wide Data Base (WWDB). Custom Route names are preceded by CUST. Slew the desired catalog to entry line and press EXP to examine catalog contents. In this example, the ROUTES catalog is examined. The ROUTES catalog can be expanded once to show route list, a second expand will show route contents, and a third EXP to show the LAT/LON of the waypoint.

Four catalogs may be examined: 'ROUTES *CREW 'CUSTOM 'LAC STATION CREW catalog functions are identical to CUSTOM waypoint storage procedures, but CREW memory is cleared when

the INS is turned off. page 9-10

z EXP

Section 9 - Summary of Display Pages and Function Keys

CREATING AND DELETING ROUTES AND WAYPOINTS IN PERMANENT MEMORY This procedure allows permanent storage of route and waypoint data in the INS ROUTE and CUSTOM catalogs. The aircraft INU tray wiring (AA-28 wired to +28V) will determine if this function is available for your aircraft.

Storing a Custom Route Having created a flight plan in the normal manner, using the waypoint page , if the ENT key is pressed when the prompt line is displayed in the' Waypoint entry mode, the, pilot will be prompted to enter the route ident, and a route will be stored in EEROM , as shown below. It will always store from WPT1, it will store TO the point that you put the prompt line, and pressed ENT If a Crew, Crossfill, Radar, or EFIS waypoint is part of the Route, then an error message will appear.

Press ENT (or Al'!) key to create a prompt line, as if you were about to insert a waypoint.

Press ENT.

Press A, B, C, D, E, F Route names can be up to 8 characters in length.

ENT

Section 9 - Summary of Display Pages and Function Keys Press ENT This procedure will store a route called "ABCDEF "; it will be 14 waypoints long, from WPT 1 up to WPT 14 SMO.

CDU displays:

Clearing Custom Routes from the ROUTES Catalog NOTE:

The ROUTES catalog lists routes that are contained both in Custom memory and in the World Wide Data Base (WWDB). Custom Route names are preceded by CUST. Only the Custom routes may be cleared using this procedure, and only if aircraft wiring permits.

To clear a custom route from the ROUTES catalog , press CAT, slew to ROUTES , then press EXP. Slew the route to be cleared to the entry line . Press CLR then press ENT to accept. P Press CAT and slew to CAT ROUTES. ❑ R

Press M

Slew up twice.

4

Section 9 - Summary of Display Pages and Function Keys

Press CLR.

Press ENT.

c LR

F

ENT

Storing Waypoints, Stations and Airports in Permanent Memory To store Waypoints, Airports or Stations in the CUSTOM catalog, the following sequence of keystrokes is required:

Press CAT

Slew up to CUSTOM.

P CAT F

Q

M

Press ENT

ENT

Section 9 - Summary of Display Pages and Function Keys

Press A key for an Airport.

F

A

P05

Press K, A, P, D.

Press ENT

Press N, 3, 4, 1, 1, 5,2 ENT

and ENT

F

Press W, 1, 1, 8,.3, 5, 4, 7andENT.

At this point you can correct LAT/LON by using slew keys and overwriting or ENT to accept and store or CLR to reject and return.

Deleting a Waypoint or Station from Permanent Memory To delete a Waypoint, press CAT, slew to CUSTOM, then press EXP. Slew required waypoint to centerline, then press CLR.

page 9-14

Section 9 - Summary of Display Pages and Function Keys

REMOTE PAGE

Line 2 and Line 4 are used in Crossfill operations. See Crossfill section. Line 3 is used to select remote range operations. Press ENT to select remote range.

Four options are displayed in which the INS will calculate range and bearing information between:

A waypoint number and a waypoint number Present position and a waypoint number Present position and a waypoint ident A waypoint ident and a waypoint ident Slew the required option to the entry line and press ENT.

Section 9 - Summary of Display pages and Function Keys S

Input the required waypoint information and press EM.

17

R

Desired track (DTK) and DISTance between waypoints, and time at present ground speed are displayed.

If the aircraft ground speed is less than 50 knots, then TIME is calculated using a 200 knot ground speed.

STATUS PAGE

v STS

Line 3 shows system in NAV or ALIGN or ATT. Line 4 shows time in NAV mode or Align countdown time. Line 5 shows action required if a failure is detected. Refer to Abnormal Operation section.

Slew down to view GPS/RNAV/TMIX updating page. Refer to Updating section. Slew up once to display malfunctions. Refer to Abnormal Operation section 13. Successive stews up permit Rapid Realign, Display test, Accuracy test, Nav Data Base interrogation , Autopilot/Flight Director tests.

page 9-16

a

Section 9 - Summary of Display Pages and Function Keys

DISPLAY TEST Verifies the CDU and MSU annunciators and CDU display. 1. Set mode switch to STB1 ALIGN or NAV.

2. Press STS.

v STS

The SYS STS/TEST page is displayed.

3. Slew up four times.

The SYSTEM TEST is displayed on line one, DISPLAY TEST is on the entry line.

4. Press IXP.

Display pattern rotates through each of the five display lines.

R

Q

Section 9 - Summary of Display Pages and Function Keys •

WRN, ALR, BAT and OFS annunciators on CDU come on. NOTE: If in NAV, only remote ALERT comes on. 5. On MSU, press ALIGN and BATT annunciators. ALIGN comes on amber, BATT comes on red. 6. To end test , press any function key.

ACCURACY TEST At the conclusion of the flight , a check of the system accuracy can be performed by pressing EXP with ACCURACY TEST on the entry line. The system update error, inertial error, inertial drift rate and ground speed error will be displayed (see section 4).

page 9-18

it

Section 9 - Summary of Display Paaes and Function Keys

DBASE TYPE/DATE The system program number will be displayed on line 1. The external data base (NDB), if present, can be interrogated for its type and expiration date using the DBASE TYPE/DATE test. If a custom data base exists , its six character Ident will be displayed as AAMMDD where: AA - Airline code MM - Expiration month DD - Expiration day

v STS

1. Press STS.

The SYS STS/TEST page is displayed.

2. Slew up until DBASE TYPE/DATE is on the entry line.

z EXP

3. Press EXP.

The INU program number and the custom dbase identifier will be displayed on the CDU. 4. Press any function key to exit. January 1997

TP92-04-13-B

page 9-19

Section 9 - Summary of Display Pages and Function Keys 0

AUTOPILOT/FLIGHT DIRECTOR TESTS Verifies basic navigation outputs from the INS to aircraft flight indicators, allowing preflight verification of the ADI and HSI displays. The tests are disabled when the INS is in NAV mode. For a listing of AP/FLT DIR test outputs, refer to tables 9-1 through 9-3. ALIGN

1. Set mode switch to STBY or ALIGN.

OFF

REEF M

These tests can also be performed during the first 10 minutes after selecting NAV from OFF.

For AP/Flight Director Tests 1, 2 and 3 2. Press M.

v

W

STS

The SYS STS/TEST page is displayed.

3. Slew up until AP/FLT DIR #1 is on the entry line.

4 page 9-20

Section 9 - Summary of Display Pages and Function Keys

4. Press EXP.

Test output values displayed; HSI and ADI also display test values.

5. Press EXP.

Display returns to SYSTEM TEST page.

6. Repeat steps 3 and 4 for AP/FLT DIR #2 and 3.

For AP/Flight Director lest 4 7. Slew up until AP/FLT DIR #4 is on the entry line.

R Q

Section 9 - Summary of Display Pages and Function Keys

8. Press EXP.

z EXP

Display prompts for test value entry, see Table 9-1.

9. Enter DTK value. (In this example, 1, 8, 0, and 0 were used).

10. Press ENT. s

11. Enter TK value (1, 8, 5, and 0).

NOTE: DTK, TK, and HDG are referenced to true north unless MAG mode is selected.

Section 9 - Summery of Display Pages and Function Keys

12. Press ENT.

ENT

13. Enter XTK value (L7, 2, 0).

14. Press ENT

15. Enter GS value (4, 0, 0).

16. Press ENT.

17. Press any function key to end test.

April 1998

TP92.04-13- B page 9-23

Section 9 - Summary of Display Pages and Function Keys Table 9-1

Synchro and Analog Test Output Values to HSI and ADI

Synchro

FLT M Test 1

FLT M Tat 2

FLT M Testa

FLT M Test 4

ARINC 429

ROLL

'22.5°

-

-

-

45.0°

PITCH

•22.5°

-

-

-

5.0°

PHDG

11.3°

11 .3°

11.3°

11 .3°

15.0°

STR

0.0°

L19.9°

R15.0°

Comp. Str Value

TK

22.5°

22.5°

22.5°

Entered TK Value

DTK

50.1 °

44.0 °

5.0°

THDG

11.3°

11 .3°

11.3°

11 .3°

MHDG2

11.3°

11 .3°

11.3°

11.3°

XTK

R3.8NM

R7.5NM

L3.8NM

Entered XTK Value

Entered DTK Value

TAE+DA

L38.9°

1328°

R62°

Comp. TAE+DA Value

TAE

L27.6°

L21 .5°

R17.5°

Comp. TAE Value

DA

11.1 °

11.1 °

11.1 °

Comp. DA Value

RELBRG

15.0°

15.0°

15.0°

15.0°

10.0°

NOTE 'Polarity depends on INU orientation: DPX fwd/port - Roll is right, pitch is up DPX aft(stbd - Roll is left, pitch is down Steering (STR) is an output to the autopilot and cannot be viewed on flight instruments

page 9-24 TP92-04-13-B

April 1998

Section 9 - Summary of Display Peg" and Function Keys Table 9-2 BCD That Output Values (EFIS and WX Radar) Function DTG TTG

FLT DIR Test 1

FLT DIR Test 2

FLT DIR Test 3

3888.9 nm 3888.9 nm 3888 .9 nm 0 0 0

FLT DIR Test 4 3888.9 nm 0

GS

450 kts

450 kts

450 kts

Entered GS value

XTK

R3.8N

R7.5N

L3.8N

Entered XTK value

T-DTK

50.1 0

44.0°

5.0°

Entered T-DTK value

TKE

L27.6°

L21.50

R17.5°

DA

R11 .2°

R11 .2°

R11 .2°

Computed TKE value Computed DA value

TK

22.5°

22.5 °

22.5°

Entered TK value

HDG

11 .3°

11.3°

11 .3°

11.3°

Section 9 - Summary of Display Pagas and Function Keys

Annunciator Test Table 9-3 Discrete

Active State

RADIO UPDATE

NOTE 1

DIG. DAT VAL 1

VAUD (+28V)

DIG. OAT VAL 2

VAUD (+28V)

ALERT

ALERT (+28V)

APPR MODE OUT

APPROACH (+28V)

COMPARISON WARN

WARN (+28V)

NO UPDATE

NOTE 1

TRUE/MAG OUT

MAG (+28V)

MAG HDG #2 WARN

VAUD (+28V)

TRUE HDG WARN*

VAUD (+28V)

HSI WARN* .

VAUD (+28V)

MAG HDG #1 WARN*

VAUD (+28V)

AUX ATT WARN*

VAUD (+28V)

PRIM ATT WARN*

VAUD (+28V)

FROM/TO

TO

NOTE : Radio UPDATE and NO UPDATE will alternatively, cycle at 1 Hz.

NOTE: LEG switch is set Hi (+28V) for 1 second whenever the ENT key is pressed in F/D #1, 2, 3 or GS is entered in F/D #4. 1

page 9-26

Section 9 - Summary of Display Pages and Function Keys

HSI OPERATION The INS outputs maybe used to drive HSI displays . Figure 9-1 shows typical HSI presentations. 1D DEGREES 1RAQC-ANGLE ERROR M4E)

1Al£ NORTH

FROM VNPI

Typical HSI Presentations Figure 9-1 (Sheet I of 2)

Section 9 - Summary of Display Pages and Function Keys

True or Mag Heading Track

Lubber Line/Card Drift Angle Bug/Card

Track Angle Error + Drift Angle

TH TK DA DTK

None

TKE

Cross-Track Deviation

XTK

To/From Distance-To-Go

TO/FROM DIGITAL

Ground Speed

DIGITAL

Drift Angle or Rol Brg

Drift Angle Bug/Lubber Line Course Arrow/Card Course Arrow/Drift Angle Bug Lateral Deviation Bar To/From Pointer Direct Reading Direct Reading

Course Deviation Bar

9.75 nMdot

1.0 nm/dot

900 ft/dot

Miles No. 1

NMI

NMI

NMI

Alert Annunciator On

1.5 - 3.0 min. prior to waypoint

10 sec prior to leg switch below 10,000 feet

Speed and angle dependent Flashing after passing end of drop zone.

Desired Track I Desired Track I Magnetic Desired Track

Typical HSI Presentations Figure 9 - 1 (Sheet 2 of 2)

Desired Track through CARP and EXTE

5

Section 9 - Summary of Display Pages and Function Keys

Summary Figure 9-2

Section 9 - Summary of Display Pages and Function Kays

Litton

Section 10 Abnormal Operation

INS WARNING ANNUNCIATIONS When a warning indicator turns on or another malfunction occurs, the pilot can display the action/malfunction message on the CDU STS page.

WARNING ANNUNCIATIONS The INU applies signals to the MSU, CDU, and aircraft instruments to annunciate system malfunctions as follows: MSU BATT annunciator

Backup battery failed load test.

CDU BAT annunciator

INS operating on backup DC power.

CDU WARN annunciator INS failure. (Flashing WARN indi-

cates alignment failure). ADI flag

Primary or secondary pitch/roll failure while INS is providing attitude data to ADI.

HSI heading flag

Heading output failure.

HSI navigation flag

Navigation output failure.

Digital data warn

BCD or BNR data failure.

Accel Advisory annunciator (optional)

INS sensing > 2kts/sec vertical acceleration condition with altitude < 10,000 ft and GS > 100 kts.

Comparison Wam

Excessive position or velocity error.

April 1998 TP92-0413B

page 10-1

Section 10 - Abnormal Operation

w

ACTION/MALFUNCTION MESSAGES Action/malfunction messages may be displayed on the SYS STS/TEST page. The action messages are recommended actions that should be taken to rectify the problems indicated by the malfunction messages. Table 13- 1 lists the action/ malfunction messages and their definitions. To display the action/malfunction messages:

1. Press STS; SYS STS/TEST page is displayed with action messages on line 5. 2. Slew ACTION message to the entry line; MALF message appears on line 4. NOTE : When two or more malfunctions exist, the display cycles through the respective lines at a 2-second rate. Record warn indications , action/malfunction messages , and status for use by ground maintenance personnel before performing recommended action. Perform action recommended by action message. If action does not correct the malfunction , notify maintenance.

page 10-2 TP92-0413-B

r

Section 10 - Abnormal Operation 'table 10-1 (Sheet 1 of 4) Action/Malfunction Messages TYPICAL INDICATIONS

SYSTEM RECOMMENDED ACTION MALFUNCTION REMOVE INU RAM R/W -- NAV (Hard Failure; turn off RAM R/W -- I/O INU and remove for RAM RAN -- P/P DMA NAV - - I/O maintenance) DMA I/O -- P/P OPCODE -- NAV OPCODE -- I/O OPCODE -- P/P CHKSM -- NAV CHKSM -- I/O CHKSM -- P/P CHKSM - CAL EEROM CHKSM - QUANT ROM CNT COMP NAV -- I/O CNT COMP I/O -- PIP TOO -- PIP STACK FAIL -- NAV STACK FAIL -- I/O STACK FAIL -- P/P VEL OVFLW GNDSPD OVFLW DELTA VX REAS HlDELTA VY REAS HI* DELTA VZ REAS HI* X OUANT FAIL Y OUANT FAIL AUX QUANT FAIL OUANT RST FAIL AID REF FAIL ACCL TMP UNREAS• MOUNTPOSCHNG INVAL MODE SEL 561 DISC FAIL

Typical indications for 'HARD FAILURE' category malfunctions include master warn annunciation . CDU display may be frozen or blank.

Flight indicators and other systems receiving attitude and heading outputs from INS will be flagged. Digital Data Warn Annunciators will be Illuminated.

HI VOLT NO GO X GYRO MODE HOP Y GYRO MODE HOP Z GYRO MODE HOP X GYRO DITH FAIL Y GYRO DITH FAIL Z GYRO DITH FAIL X PLASMA CURB Y PLASMA CURB Z PLASMA CURR ADXSF OUT OF RNG ADXSF OUT OF RNG ADZSF OUT OF RNG X CLC SAH FAIL Y CLC SAH FAIL Z CLC SAH FAIL •Syatan will dad down 12 seconds aim, dal.Nng #M fa ra.

Section 10 - Abnormal Operation Table 10-1 (Sheet 2 of 4) Action/Malfunction Messages RECOMMENDED ACTION

TYPICAL INDICATIONS

SYSTEM MALFUNCTION

w

b

REMOVE INU X GYRO TMP HI* (continued) Y GYRO TMP HI* Z GYRO TMP HI* X GYRO HET FAIL Y GYRO HET FAIL Z GYRO HET FAIL X CLC ERR FAIL Y CLC ERR FAIL Z CLC ERR FAIL X GYRO CNT LO Y GYRO CNT LO Z GYRO CNT LO X GYRO CNT HI Y GYRO CNT HI Z GYRO CNT HI INCOMPATIBLE S/W DELAYED CHKSM -- CUST CAT MAINTENANCE CHKSM - - RTE CAT (Soft Failure; PROG PIN CHNG Service INU when TUNE WRAPARND convenient) ODB #1 WRAPARND ODB #2 WRAPARND ODB #3 WRAPARND RCVR #2 WRAPARND

RCVR #3 WRAPARND

System will not use custom waypoints System will not use route waypoints CDU aetion/Matiunction message

No usage of DMENOR data in autotune mode CDU Action/Malfunction message CDU Action/Malfunction message CDU Action/Malunction message

No usage of TACANNOR or INS sys "A dig. data No usage of DME, RADAR or INS sys 'B' dig. data

RCVR #4 WRAPARND SYN/DIG REF FAIL SYN#1 WRAPARND SYN #2 WRAPARND

No usage of NDB or DADS dig. data HSI:HDG and NAV flag. ADI:ATT flag ADIATT flag

SYN #3 WRAPARND

INS stab to RADAR , autothrottle flagged (TYP) Platform HOG output from INS flagged HSI:NAV flag (TYP) HSI:NAV flag (TYP) ADIATTflag INS stab to RADAR, autothrottle flagged INS stab to RADAR, autoCuottle flagged HSI:NAV flag (IYP) HSI:NAV flag (TYP) CDU Action/Malfunction message HSI:NAV flag (TYP) HSI:NAV flag (TYP) CDU Action/Malfunction message

SYN #4 WRAPARND SYN #5 WRAPARND SYN #6 WRAPARND SYN #7 WRAPARND SYN #8 WRAPARND SYN #9 WRAPARND SYN #10 WRAPARND SYN #11 WRAPARND SYN #12 WRAPARND ANLG #1 WRAPARND ANLG #2 WRAPARND ANLG #3

INS stab to RADAR, autothrottle flagged (n'P)

•Systsn w3l Ysd down 12 seoaals t datsdng thew faam.

page 10-4

a

h

J.

Section 10 - Abnormal Operation ,

Table 10-1 (Sheet 3 of 4)

Action/Malfunction Messages SYSTEM TYPICAL RECOMMENDED ACTION MALFUNCTION INDICATIONS

DELAYED VOR REASON No usage of VOR SIN/COS inputs MAINTENANCE PROG PIN INVAL HSI:NAV flag (TYP) (continued)

)FILL A PARITY No usage INS sys A dig data WILL B PARITY No usage INS sys 'B' dig data GPSIM SYNCH No GPS updating

FAd GPSIM CARD FAIL No GPS updating GPSWA COMM FAIL No GPS updating 15 3 FAILURE None VWYDB COMM FAIL Access to W WDB denied. GPS/WWDB ODB W/A No GPS or WWDB ENTER PROS 3+3T FAIL

Flashing CDU WARN and MSU ALIGN

ALN FAIL

Position page message 'CHECK PPOS ENTRY" Flashing MASTER WARN and MSU

ATTITUDE

X GYRO TMP FAIL

Typical indications: CDU WARN

(System

Y GYRO TMP FAIL

unusable for

Z GYRO TMP FAIL

ALIGN

SELECT HSI :HDG and NAV flag

navigation. System outputs: pitch, rail and platform HDG)

EXCESS MOTION (During ALIGN mode)

EXCESS MOTION

ALIGN mode automatically resequences to 10 minutes (32 seconds if in rapid realign mode) and flashing MASTER WARN and MSU ALIGN.

CHECK ADC DADS PARITY DADS DATA IN

No usage of some or all ADS info. CDU displays Blank for ALTITUDE, TM;

ADS INVAL ADC REF INVAL ALT, CRS REAS TM REAS

or WIND Information. CDU message displayed depends on air data system type installed on aircraft

REF #1 INVAL

ADI:ATT flag. INS pitch and roll outputs flagged

REF #2 INVAL

Platform HDG output from INS flagged

CHECK REF

REF #3 INVAL REF #4 INVAL REF #6 INVAL

HSI:NAV flag HSI:NAV flag HSI:NAVflag

REF #7 INVAL

HSI:NAV flag

CDU DATA IN FAIL

Frozen or Arabic display

REMOVE CDU CDU INVAL

Sect^DlT /a 'tonal Operation Table 10-1 (Sheet 4 of 4) Action/Malfunction Messages RECOMMENDED ACTION

SYSTEM MALFUNCTION

SYSTEM BELOW

TYPICAL INDICATIONS

-150C

ALIGN STS 70 DISPLAYED

Align time takes 16 minutes or bnger.

CHECK SYSTEM

INTERSYS COMP

'Comparison WARN ' message on CDU

REMOVE TEST CONN

REMOVE TEST CONN

Test connector is on INU

CHECK GPS

GPS #1 DATA FAIL

No GPS updating

GPS N2 DATA FAIL

No GPS updating

System wiU not go into NAV until INS sensor block is -15.0°C or higher.

ACCURACY

SENSOR

a

a

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Section 11 Alphabetical Index Page

Subject Accuracy Test Accuracy Test Display Page Action/Malfunction Messages

Alignment Status Attitude Reference Mode Autopilot/Flight Director Test Display Page

Bearing/Range Reference Crew Waypoint Entry Catalog Display Page Cautions , Operating CDU Course Data

Course Display Page Crew Catalog

Crew Waypoint Entry or Correction Crossfill Crosstrack Offset Mode

Data Base Validity Check Dbase Type/Date Direct To Display Page Direct To Mode Direct To Steering Disabling Triple System Mbdng Display Test Page Duplicate Identifiers

Easy On/Off Steering EFIS "To" Waypoint Change Flight Plan Assembly by Route Entry Assembly by Waypoint to Waypoint Entry Data

TP92404-13-B

4-1 9-18 10-2 2-12 8-1 9-20 2-23 9-10 1-11 1-7 3-19 9-4 1-4 2-20 5-1 3-11

2-1 9-19 9-8 3-6 3-10 6-17 9-17 2-17 6-1 3-18 2-15 2-19 2-15 3-16

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Section 11 - Alphabetical Index

Subject Data Entry Editing Display Page Verification

Flush Updates GMT Entry HSI Operation Display Page Initial Track Selection

Inserting a Waypoint Between Existing Waypoints Instrument Data Instrument Data Display Page Intermediate Stops Leg Display Page Leg Switch Malfunction Messages Missed Approach Point Entry MSU

Multiple System Operation NAV Update Navigation Data Storage CREW Catalog (Temporary) CUSTOM Catalog (Permanent) Parallel Track (see Crosstrack Offset) Position Updating Automatic Disable RNAV Updating Display Page

Easy On/Off Steering Flush

Page 2-15 2-26 9-7 2-39 6-24 2-10 9-27 2-34 2-32 3-20 9-9 4-3 9-5 3-1 10-2 7-4 1-5 1-4 4-9 1-4 1-4 1-4 3-11 6-1 6-4 6-10 9-3 6-1 6-24

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Section 11 - Alphabetical Index Subject Manual

Page 6-21

Position Check

6-3

RNAV Updating

6-6

Post Flight Procedures

4-5

Predeparture Procedures Present Position Entry by Latitude and Longitude

2-1 2-4 2-6

Entry by Local IDENT

Entry by Range and Bearing from a Reference Rapid Realignment Remote Display Page Remote Function

Removal Criteria , System Accuracy RNAV

2-5

2-8 4-6 9-15 3-20

4-6 6-6

Approach Mode

7-1

Disable Updating Updating

6-10 6-6

Start-up and Data Base Validity Check Status Display Page

2-1 9-16

STS/Update Page Description Synthetic Magnetic Variation

6-19 1-4

System Accuracy Removal Criteria System Status/Update Page

4-6 6-19

Track Hold Mode

3-14

Track Selection , Initial

2-34

Triple System Mbdng Warning Annunciations Waypoint Bypassing Deletion , Single Deletion , Multiple

6-16 10-1 2-15 3-10 2-28 2-30

Display Page -

Entry _ Bearing/Range Reference Crew Latitude/Longitude Crew Inserting Between :Ebsting Waypoints WPT Page Flight Plan Verification

9-6

2-20 2-23 2-21 2-32 2-39

Section 11 - Alphabetical Index

Section 12 Quick Reference Guide This quick reference guide is an addendum to the Pilot's Guide. Experienced users of the system may find this quicker to use and may wish to remove this section from the Pilot's Guide for quick reference use. It is, however, only a guide and for more detailed procedures and information , the main body of the Pilot 's Guide should be consulted.

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Section 12 - Quick Reference Guide ALIGNMENT (With LOCAL IDENT Stored in Data Base) 1. Place MSU switch to NAV (wait 6 seconds). Check the validity of the data base.

2. Follow the CDU prompts until the Position page appears. 3. Slew down once to move LOC ID display to entry line.

4. Type in LOCAL ID letters/numbers. (e.g., C22, S16, EWRRR EBBRRP, etc.) 5. Press ENT local LAT and LON are displayed. 6. Enter GMT as follows: a. Enter GMT in hours, minutes, and seconds, 24 hour time. b. Press ENT at instant preset time matches actual GMT time.

c. Enter DATE as DDMMYY. NOTE: If local ID is not in data base, IDENT NOT FOUND will be displayed . Press CLR twice and use LAT/ LON entry procedure on next page (step 3).

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Section 12 - Quick Reference Guide NOTE: Alignment status maybe observed by pressing STS. Status 90 through status 2 takes 10 minutes. Status 1 is displayed after alignment is complete (MSU amber light goes out).

ALIGNMENT (With LOCAL IDENTNot in Data Base) (LAT/ LON Procedure) 1. Place MSU switch to NAV (wait 6 seconds). Check the validity of the data base.

2. Follow the CDU prompts until the Position page appears. 3. Using green 2N key for N LAT or green 8S key for S LAT, type in latitude including trailing zeros , then press ENT 4. Using green W4 key for W LON or green 6E key for

E LON, type in longitude including trailing zeros, then press ENT. 5. Using green W4 key for W LON or green 6E key for E LON, type in longitude including trailing zeros, then press ENT. 6. Enter GMT as follows: a. Enter GMT in hours, minutes , and seconds, 24 hour time.

b. Press ENT at instant preset time matches actual GMT time. c. Enter DATE as DDMMYY. NOTE: Alignment status may be observed by pressing STS. Status 90 through status 2 takes 10 minutes. Status 1 is displayed after alignment is complete (MSU amber light goes out). April 1998 TP92-0413B

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Section 12 - Quick Reference Guide

DISPLAY TEST 1. After present position and GMT entry, press STS.

•

2. Slew up 4 times to DISPLAY TEST. 3. Press EXP and observe WRN, ALR, BAT, and OFS annunciators come on. Display pattern rotates through .5 line display. NOTE: If in NAV status 1, only ALR comes on.

4. Press to test MSU ALIGN and BATT annunciators. 5. End test by pressing any function key. WAYPOINT ENTRY BY ROUTE DEFINITION 1. Press WPT, then A•N. Verify an A in upper right corner of display.

2. Select route entry by pressing -, R, and ENT (RTE ID prompt line will appear). 3. Type in route ID. Check database catalog page or Blue book for routes available. (Ex: MEMLAX, PANCVHHH, 220, etc.) 4. Press ENT (waypoint ID's will be displayed in sequence.) NOTE: A•N must be pressed to differentiate between letters (top half of keys) and numbers (bottom half of keys) during all operations.

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S.

Section 12 - Quick Reference Guide WAYPOINT LOADING 1. Press WPT and A•N. 2. Type in WPT ID, then press ENT

3. If WPT not stored , blank LAT/LON prompts will be displayed . To load: a. Type in LAT of WPT, then press ENT b. Type in LON of WPT, then press ENT c. Verify coordinates , then press EXP to enter in Crew catalog.

4. After loading is complete, press CLR to enable new page selection.

April 1998 TP92-0413B

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Section 12 - Quick Reference Guide

CROSSFILL (Remoting) 1. Press RMT on all CDU's. 2. On F/O's CDU, slew XFIL Master to entry line and press ENT 3. Slew 98 waypoint option to entry line if not already there.

4. Press ENT on F/O's (master) CDU. 5. Slew XFILL SLAVE to entry line on other CDU's and press ENT

6. Press ENT on F/O's (master) CDU. NOTE: Crossfill modes may be aborted from the master system by pressing CLR. Waypoints transferred will be retained by slave units even if slave display shows FAIL. NOTE : Afterwaypoints are transferred (approx. 2-1/2 minutes for all 98 waypoints), CROSSFILL COMPLETE is displayed on all CDU 's. If a transmission error occurs, the slave CDU's display CHECKSUM FAIL.

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•

Section 12 - Quick Reference Guide FLIGHT PLAN VERIFICATION 1. Press WPT. 2, Press 1 , then ENT or slew to WPT #1. 3. Verify ID, then press EXP. 4. Verify coordinates and course /distance to flight plan. 5. To verify each subsequent waypoint, slew up once. NOTE: Flight plan accumulated distances may be checked

by pressing FPL and slewing each waypoint to entry line. INITIAL TRACK SELECTION 1. Press LEG. 2. Press ENT twice.

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Section 12 - Quick Reference Guide

%

ROUTE CHANGE NOTE: This procedure is for use when route changes are assigned after waypoint loading has been completed. By following these steps , an entire new route may be quickly reloaded.

1. Press WPT. 2. Slew to WPT # 1 (or press 1, then ENT), or slew to the TO waypoint If necessary. 3. Press CLR, then ENT. 4. Press - , R, then ENT.

5.. Type in new route ID, then press ENT. 6. Press LEG, then press ENT twice. INSERTING A WAYPOINT BETWEEN WAYPOINTS 1. Press WPT, then slew the waypoint preceding the added waypoint to entry line. 2. Press ENT (list will open up), then type in new ID. a

3. Press ENT.

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April 1998

Section 12 - Quick Reference Guide WAYPOINT SUBSTITUTION/DELETION 1. Press WPT. Slew desired WPT number to entry line or press WPT #, then ENT. 2. Press CLR, then type in new WPT ID. 3. Press ENT.

NOTE: To delete awaypoint , press CLR twice instep #2 (list closes).

MULTIPLE WAYPOINT DELETION 1. Press WPT, then slew first waypoint of group to be deleted to entry line.

2. Press CLR, -, D, then ENT. 3. Type in last waypoint number to be deleted. 4. Press ENT (list closes up).

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Section 12 - Quick Reference Guide

DIRECT- TO MODE ( From Present Position to a Waypoint) 1. Press DIR, then type in waypoint iDENT. ( if waypoint number is desired , A•N and s must be pressed first).

2. Press ENT. Verify coordinates are correct 3. Press ENT to accept. After 5 seconds the display changes to the CRS page. NOTE: After making a DIRECT-TO entry, TO will appear opposite the TO waypoint on the WPT page. If DIRTO is not part of the flight plan, it will appear in WPT #99. NOTE : Auto leg mode will be selected and crosstrack offset will be cleared.

CROSSTRACK ( Offset) NOTE : Crosstrack navigation is not possible if navigating in a DIR-TO mode. A track leg must be entered by pressing LEG and pressingENTtwice ( leg FROM 00 same as DIR TO).

0

1. Press CRS, slew XTK to entry line, press EXP. 2. Press L7 ( left crosstrack) or 9R (right crosstrack). 3. Type in crosstrack distance to 0.1 mile.

4. Press ENT (OFS annunciator comes on). NOTE: To return to original track , enter a 0 crosstrack by repeating steps 1 through 3 above and press ENT. Crosstrack can also be cancelled by a DIRECT-TO entry or LEG select from WPT 0:

6

S

page 12 - 10 TP92-04138 April 1998

Section 12 - Quick Reference Guide

VOR/DME CROSS CHECK 1. Select MAG HDG mode and press RMT on all CDU's. 2. With REMOTE RANGE on the entry line, press ENT 3. Slew present position to IDENT to entry line, then press ENT 4. Enter the cross-check VOR's IDENT (most accurate checks are accomplished between 30 and 100nm from a VOR with stations ahead or behind aircraft), then press ENT. 5. With HSI switch in VOR ( MAG), center course bar in HSI and read CRS. 6. Compare INS distance to DME and the M-DTKto the cross -check VOR radial (CRS). NOTE: Nominal error tolerances are 6 miles and/or 6 degrees.

TIME, ETA, AND WPT DISTANCE DISPLAYS 1. Press FPL. 2. Press UP to change from DIST, to TIME, to ETA, to DBW (distance between waypoints). 3. Slew up waypoints to view complete flight plan.

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Section 12 Quick Reference Guide

POSITION CHECK 1.. Press POS, then HLD. 2. Verify upper set of coordinates. 3. Press HLD again to return to POS page. NOTE: Anytime the letter H appears on the upper left comer of display, HLD has been pressed and the displays are frozen . Press HLD again to dear.

MANUAL POSITION UPDATE 1. Press POS, then press HLD when over known position. 2. Slew LAT down to entry line.

3. Type in updated position latitude, then press ENT 4. Type in updated longitude , then press ENT (display returns to POS page). REMOVE ALL POSITION UPDATES 1. Press STS, then slew UPDATE down to entry line (display now changes to CHANGE UDT MODE). 2. Press EXP ( list of options is displayed), then slew FLUSH to entry line. 3. Press ENT (entry line changes to ALL), then press ENT again ( updates are now removed).

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Section 12 - Quick Reference Guide

REMOTE RANGING 1. Press RMT, then ENT. 2. Slew desired option to entry line. 3. Press ENT.

4. If necessary, type in FROM ID or WPT #, then press ENT. 5. Type in TO ID or WPT #, then press ENT. 6. True desired track (Mag desired track if MAG mode is selected), distance, and time enroute will be displayed. USE OF CREW (TEMPORARY) CATALOG 1. Press CAT. 2. Slew to place CREW on the entry line, then press ENT (to examine contents of catalog , press EXP instead of ENT). 3. Prompt for type of entry is displayed . Key in A=Airport, W=Waypoint, or S = Station. 4. Prompt for station type is displayed if selected in step 3. Key in D=DME /VOR, V=VORTAC, or T=TACAN. Press ENT. 5. Prompt for station class is displayed if selected in step 3. Key in H = High , L = Low, T = Terminal, or U = Unrestricted . Press ENT. 6. Prompt line for IDENT entry is displayed. Key in IDENT, then press ENT. 7. Enter LAT and LON of the (DENT. If entry is a VOR station , enter the frequency, magnetic variation, and elevation (North or South key for plus or minus). Press ENT after each entry.

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Section 12 - Quick Reference Guide

CATALOG INSPECTION 1. Press CAT, then slew catalog to be observed to entry line. 2. Press EXP. 3. Slew through listing , or to bring a specific stored waypoint or route to entry line:

a. Press A•N, then type in route ID or waypoint ID: b. Press ENT, then EXP. NOTE: Pressing fXP additional times returns to original list. ACCURACY TEST 1. Press STS, then slew ACCURACY TEST up to entry line.

2. Press EXP. 3. Type in the gate coordinates or slew to bring LOC ID to the entry line. Type in the gate IDENT, then press ENT. 4. Verify the position displayed is correct , then press ENT. 5. UDT ERR (update error), INS ERR (inertial error), INS DFT (inertial drift ), and RESID GS ( residual ground speed) are displayed.

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r

Section 12 - Quick Reference Guide

LEG CHANGE - TRACK SELECTION 1. Using WPT.ID's: a. Press LEG. b. Type in FROM ID, then press ENT c. Type in TO ID, then press ENT. 2. Using WPT numbers: a. Press LEG , then A•N. b. Slew numeric display down to entry line, c. Type in FROM WPT #, then press ENT d. Type in TO WPT #, then press ENT. 3. After 5 seconds , display will Twitch to CRS.

STATUS MALFUNCTION MESSAGES 1. Press STS, then, if present, ACTION message appears on bottom display line. 2. Slew ACTION message up to entry line . MALFUNCTION message appears on line 4. NOTE: When two or more malfunctions exist, the display cycles through the respective lines at a 2 -second rate. 3. Record WARN indications, ACTION/MALFUNCTIONS messages , and, STATUS before performing recommended action.

April 1998 TP92-04138

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Section 12 - Quick Reference Guide

ATTITUDE MODE 1. Pull MSU switch out and turn to ATT REF.

2. Fly straight and level for 60 seconds or more. 3. CDU will switch to STS page and this is the only page available in ATT mode. 4. If WARN condition persists , cycle MSU switch to OFF, then directly to ATT REF. NOTE: INU attitude data becomes valid 30 seconds after selecting ATT REF from NAV, or 60 seconds after selecting ATT REF from OFF.

AUTOMATIC UPDATES , DISABLE/REENABLE At INS turn-on, GPS updating is enabled (whether the aircraft is equipped with GPS or not). An " E" is displayed in the top left of the display to indicate this enble . RNAV and TMIX updating must be enabled when required. Updating becomes effective in NAV mode . To deselect any one: 1. Press STS, and slew down once. 2. Press EXP with CHANGE UDT MODE : on entry line. 3. Slew item for deselection to entry line and press ENT. NOTE : The flush option will disable RNAV and TMIX updating and will also flush all previous update solutions, returning to pure inertial solutions. To reenable an update mode: • Perform steps 1. and 2 . above. • Slew ENABLE UPDATES to entry line and press'ENT NOTE: ENABLE UPDATES will reenable both (RNAV and TMIX) deselected functions (including any VOR/ DME/ TACAN inhibits). Repeat steps 1., 2. and 3. to disable any unwanted functions.

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Y