Manual Operations BELL-212- Helicopter

BHT-212IFR-FM-1

ROTORCRAFT FLIGHT MANUAL

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

COPYRIGHT NOTICE COPYRIGHT 2002 BELL ® HELICOPTER TEXTRON INC. AND BELL HELICOPTER TEXTRON CANADA LTD. ALL RIGHTS RESERVED

POST OFFICE BOX 482

FORT WORTH, TEXAS 76101

14 AUGUST 1995 REVISION 4 — 02 DECEMBER 2002

BHT-212IFR-FM-1

NOTICE PAGE

PROPRIETARY RIGHTS NOTICE Manufacturer’s Data portion of this manual is proprietary to Bell Helicopter Textron Inc. Disclosure, reproduction, or use of these data for any purpose other than helicopter operation is forbidden without prior written authorization from Bell Helicopter Textron Inc.

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P.O. Box 482 Fort Worth, Texas 76101-0482 NP

BHT-212IFR-FM-1

LOG OF REVISIONS Original ....................... 0.................... 29 JUN 73 Reissue ....................... 0....................14 AUG 95 Revision ...................... 1....................29 MAY 96

Revision ......................2 .................... 12 SEP 97 Revision ......................3 ................... 01 MAY 98 Revision ......................4 ................... 02 DEC 02

LOG OF PAGES PAGE

REVISION NO.

Cover......................................................... 0 Title............................................................ 4 NP .............................................................. 0 A/B............................................................. 4 C/D............................................................. 4 i — ii .......................................................... 0 iii/iv ............................................................ 0 1-1 — 1-2 ................................................... 2 1-3 — 1-4 ................................................... 4 1-4A/1-4B .................................................. 2 1-5.............................................................. 2 1-6.............................................................. 0 1-7 — 1-9 ................................................... 2 1-10............................................................ 4 1-11/1-12.................................................... 0 1-13............................................................ 1 1-14 — 1-15 ............................................... 0 1-16 — 1-22 ............................................... 1 1-23/1-24.................................................... 1 2-1/2-2........................................................ 0 2-3.............................................................. 2 2-4.............................................................. 0 2-5.............................................................. 3 2-6.............................................................. 0 2-7.............................................................. 4 2-8 — 2-9 ................................................... 0 2-10............................................................ 2 2-11 — 2-13 ............................................... 0 2-14............................................................ 2

REVISION NO.

PAGE

2-15 ........................................................... 0 2-16 ........................................................... 2 2-16A/2-16B .............................................. 2 2-17 — 2-18 .............................................. 0 2-19/2-20 ................................................... 0 3-1 — 3-2 .................................................. 2 3-3 — 3-4 .................................................. 4 3-5 — 3-9 .................................................. 2 3-10 ........................................................... 4 3-11 — 3-13 .............................................. 0 3-14 — 3-15 .............................................. 2 3-16 — 3-17 .............................................. 0 3-18 ........................................................... 2 3-19 — 3-24 .............................................. 2 4-1/4-2 ....................................................... 0 4-3 — 4-4 .................................................. 0 4-5/4-6 ....................................................... 0 4-7 — 4-8 .................................................. 1 4-8A — 4-8B ............................................. 1 4-9 — 4-24 ................................................ 0 4-25 — 4-76 .............................................. 2 4-77/4-78 ................................................... 2 5-1 — 5-2 .................................................. 0 5-3 — 5-4 .................................................. 0 5-5/5-6 ....................................................... 0 5-7 — 5-24 ................................................ 0 5-25/5-26 ................................................... 0 A-1/A-2 ...................................................... 2 A-3 — A-4 ................................................. 2

NOTE Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

02 DEC 2002

Rev. 4

A/B

BHT-212IFR-FM-1

LOG OF FAA APPROVED REVISIONS Original ....................... 0.................... 29 JUN 73 Reissue ....................... 0....................14 AUG 95 Revision ..................... 1....................29 MAY 96

APPROVED:

Revision ......................2 .................... 12 SEP 97 Revision ......................3 ................... 01 MAY 98 Revision ......................4 ................... 02 DEC 02

DATE:

MANAGER

ROTORCRAFT CERTIFICATION OFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170 02 DEC 2002

Rev. 4

C/D

BHT-2121FR-FM-1

FAA APPROVED GENERAL INFORMATION

ORGANIZATION

TERMINOLOGY

This flight manual is divided into five 1 Section 2 Section 3 Section

Section 4 Section 5 Appendix A

CAUTIONS,

WARNINGS,

sections and an appendix as follows:

AND

NOTES

LIMITATIONS NORMAL PROCEDURES EMERGENCY AND MAL-

Warnings,

FUNCTIONPROCEDURES

throughout

PERFORMANCE DATA WEIGHT AND BALANCE OPTIONAL EQUIPMENT SUPPLEMENTS

important and critical used as follows:

and notes are used

cautions,

this manual to emphasize instructions

and are

WARNING

1 through 4 contain FAA data necessary to operate

AN OPERATING PROCEDURE

helicopter in a safe and efficient manner. Sections 5 contains Weight and Balance data.

PRACTICE, ETC., WHICH, IF NOT CORRECTLY FOLLOWED, COULD RESULT IN PERSONAL INJURY

Sections approved

Appendix

a list of approved

A contains

supplements for optional equipment,

OR LOSS OF LIFE.

which shall be used in conjunction with basic flight manual when respective optional equipment kits are installed.

CAUTION

Manufacturer's data manual (BHT-212-MD1) contains additional information to be used in conjunction with flight manual and

AN OPERATING PROCEDURE, PRACTICE, ETC., WHICH, IF NOT STRICTLY OBSERVED, COULD

optional

applicable.

equipment

supplements,

Manufacturer's

divided into four sections as follows: Section 1 Section 2 Section 3 Section 4

as

data manual is

SYSTEMS DESCRIPTION HANDLING AND SERVICING CONVERSION CHARTS AND TABLES EXPANDED PERFORMANCE

RESULT IN DAMAGE TO OR DESTRUCTION OF EQUIPMENT NOTE procedure, An operating condition, etc., which is essential to highlight.

USE OF PROCEDURALWORDS Procedural word usage and intended meaning which has been adhered to in preparing this manual is as follows:

SHALL has been used only when

application mandatory.

of a procedure

is

BHT-2121FR-FM-1

FAA APPROVED

SHOULD has been used only when

application

of a procedure

recommended. recommended.

is

HD HP

MAY and NEED NOT have been used

HSI

Density altitude Pressure altitude Horizontal situation

only when application of a procedureindicator is optional.

HTR

Heater

WILL has been used only to indicate futurity, never to indicate a mandatory

HV

Height-velocity

HYDRSYS IFR

Hydraulic system Instrument flight

procedure.

ABBREVIATIONS

Abbreviations

AND ACRONYMS

and acronyms used

throughout this manual are defined as follows:

IGE

In ground effect

IMC

Instrument

INCR

Increase

INTCON

Interconnect

INV

Inverter

ITT

Interturbine temperature Knots calibrated airspeed

AC AFCS

Alternating current Automatic flight control system

AGL

Above ground level

ATTD

Attitude

BLWR

Blower

C

Celsius

KG

CDP

Critical decision

KIAS

point

rules

KCAS

Meteorological Conditions

Kilogram(s) Knots indicated

airspeed

CG

Center of gravity

LB

Pound(s)

CMD

LDP

DC

Command Direct current

Landing decision point

DECR DSENGA

Decrease Disengage

M MCP

ELT

Emergency locator transmitter

Meter(s) Maximum continuous power

MIN

Minimum, minute(s)

ENG ENGA

Engine Engage

NAV

Navigation

NON ESS

Non essential

ENG RPM (N2 )

NORMNormal OAT

F FT

Engine power turbine rpm Fahrenheit Foot, feet

GAS PROD (N1)

Gas producer rpm

GEN GOV GW ii

OEI

Outside air temperature One engine

OGE

inoperative Out of ground effect Out of ground effect

Generator

PART SEP

Particle separator

Governor

PLT

Pilot

Gross weight

PRI

Primary

FAA APPROVED

.

BHT-2121FR-FM-1

REL ROTOR (N)

Release Rotor RPM

RPM

Revolutions per minute

VMI N

SCAS STA

Stability and control augmentation system Station Station

VNE VTOCS

TEMP CONT

Temperature control

Never exceed speed Takeoff climbout speed

VCAL VFR

Calibrated airspeed Visual flight rules

VTOSS XFEED

Takeoff safety speed Crossfeed

VG

Vertical gyro

VIAS

Indicated airspeed

VMC

Visual Meteorological

Conditions

Minimum speed for instrument (IFR)

flight

BHT-2121FR-FM-1

FAA APPROVED

Section 1 TABLE OF CONTENTS Page Number

Paragraph

Subject

1-1 ........... INTRODUCTION ................................................. 1-2 ........... BASIS OF CERTIFICATION 1-3 ........... TYPES OF OPERATION ......................................... 1-4........... FLIGHT CREW ................................................... 1-4-A ........ IFR OPERATION ........................................... ................................... 1-4-B ........ IFR CARGO OPERATION 1-4-C ........ VFR OPERATION ........................................... 1-4-D ........ VFR CARGO OPERATION ..................................

1-3 1-3 1-3 1-3 1-3 1-3 1-3 1-4

1-5...........

1-4

1-5-A ........ 1-5-B ........

1-4 1-4

1-5-C ........ 1-5-D ....... 1-5-E ........ 1-6........... 1-6-A ........ 1-6-B ........

1-4 1-4 1-4A 1-5 1-5 1-5

AIRSPEED....................................................... ALTITUDE .......................................................

1-7........... 1-8...........

1-5 1-6

MANEUVERING.................................................. PROHIBITED MANEUVERS ............................... CLIMB AND DESCENT ..................................... HEIGHT-VELOCITY ............................................. AMBIENT TEMPERATURES ................................... ELECTRICAL ................................................... BATTERY ................................................... GENERATOR ...............................................

1-9........... 1-9-A ·....... 1-9-B ........ 1-10 ......... 1-11 ......... 1-12 ......... 1-12-A ....... 1-12-B .......

1-6 1-6 1-6 1-6 1-6 1-6 1-6 1-7

STARTER...................................................

1-12-C.......

1-7

GROUND POWER UNIT .................................... POWER PLANT .................................................. GAS PRODUCER RPM (N) ................................. POWER TURBINE RPM..................................... INTERTURBINE TEMPERATURE ........................... ENGINE TORQUE ...........................................

1-12-D....... 1-13 ......... 1-13-A ....... 1-13-B ...... 1-13-C ...... 1-13-D .......

1-7 1-7 1-7 1-8 1-8 1-8

1-13-F 1-13-G 1-13-H 1-13-J

1-9 1-9 1-9 1-9

................................ CONFIGURATION

.............

.................................... REQUIRED EQUIPMENT OPTIONAL EQUIPMENT .................................... DOORS OPEN/REMOVED (VMC ONLY) .............................. .. PASSENGERS .............................................. CARGO .................................................. WEIGHT AND CENTER OF GRAVITY ........................... WEIGHT .................................................... CENTER OF GRAVITY ......................................

FUELPRESSURE.....................................

ENGINE OIL PRESSURE ................................... ENGINE OIL TEMPERATURE .............................. COMBINING GEARBOX OIL PRESSURE .................. COMBINING GEARBOX OIL TEMPERATURE ..............

1-13-E ... ..... ...... ....... ....... ....... Rev. 2

1-9

1-1

FAA APPROVED

BHT-2121FR-FM-1

TABLE OF CONTENTS (Cont) Page Number

Subject

Paragraph

TRANSMISSION ................................................. TRANSMISSION OIL PRESSURE........................... TRANSMISSION OIL TEMPERATURE ...................... TRANSMISSION TORQUE .................................. ROTOR .......................................................... ROTOR RPM - POWER ON ................................ ROTOR RPM - POWER OFF ............................... HYDRAULIC ..................................................... HYDRAULIC PRESSURE ................................... HYDRAULIC TEMPERATURE .............................. FUEL AND OIL .................................................. FUEL ........................................................ OIL ENGINE AND COMBINING GEARBOX................ OIL TRANSMISSION, INTERMEDIATE AND TAIL ROTOR GEARBOX .................................................. ROTOR BRAKE.................................................. LANDING GEAR ................................................. INSTRUMENT MARKINGS AND PLACARDS ................... HEATER .........................................................

1-14 ......... 1-14-A ....... 1-14-B ....... 1-14-C ....... 1-15 ......... 1-15-A ....... 1-15-B ....... 1-16 ......... 1-16-A ....... 1-16-B ....... 1-17 ......... 1-17-A ....... 1-17-B .......

1-9 1-9 1-9 1-9 1-10 1-10 1-10 1-10 1-10 1-10 1-10 1-10 1-10

1-17-C ....... 1-18 ......... 1-19 ......... 1-20 ......... 1-21 .........

1-10 1-11 1-11 1-11 1-11

LIST OF FIGURES Title

Figure Number

Instrument markings ............................................

1-1...........

1-13

Placards and decals ............................................

1-2...........

1-19

Gross weight center of gravity chart .......................... Weight-altitude temperature limitations for takeoff, landing and in ground effect maneuvers chart ......................... Single engine height velocity chart ............................

1-3...........

1-21

1-4........... 1-5...........

1-22 1-23

1-2

Rev. 2

Page Number

FAA APPROVED

BHT-212IFR-FM-1

Section 1 LIMITATIONS 1-1.

INTRODUCTION NOTE

Compliance with limitations in this section is required by appropriate operating rules. Minimum and maximum limits, and normal and cautionary operating ranges for helicopter and subsystems are indicated by instrument markings and placards. Instrument markings and p laca rds represent ae rody namic calculations that are substantiated by flight test data. Anytime an operating limit is exceeded, an appropriate entry shall be made in helicopter log book. Entry shall state which limit was exceeded, duration of time, extreme value attained, and any additional information essential in determining maintenance action required.

1-2. BASIS OF CERTIFICATION This helicopter is certified under FAR Part 29, Category B.

1-3.

1-4. 1-4-A.

FLIGHT CREW IFR OPERATION

Minimum flight crew for IFR operation, except as noted below, shall consist of two pilots, e a ch o f w h ic h mu s t h o ld a h e l ic o p te r instrument rating.

1-4-B.

IFR CARGO OPERATION NOTE

Refer to applicable operating rules for internal cargo operations.

1-4-C.

VFR OPERATION

Minimum cockpit (FS 47.0) weight is 170 pounds (77.1 kilograms). Refer to Section 5. Minimum flight crew consists of one pilot who shall operate helicopter from right crew seat. Left crew seat may be used for an additional pilot for VFR day and night operations when approved dual controls and copilot instrument kits are installed.

TYPES OF OPERATION

This helicopter is certified for VFR and Category 1 IFR operations under IFR day and night, non-icing conditions.

02 DEC 2002

Rev. 4

1-3

BHT-212IFR-FM-1

1-4-D.

FAA APPROVED

VFR CARGO OPERATION NOTE

Refer to applicable operating rules for internal cargo operations.

1-5.

CONFIGURATION

1-5-A.

REQUIRED EQUIPMENT

(*) Designates required equipment for VFR flight.

1-5-B.

OPTIONAL EQUIPMENT

Refer to appropriate Flight Manual Supplement(s) for additional limitations, procedures, and performance data with optional equipment installed. See Appendix A.

1-5-C. DOORS OPEN/REMOVED (VMC ONLY) Helicopter may be flown with doors open or removed only with Bell Standard interior installed. Flight operation is approved for the following alternative configurations during VMC only:

(*)Operable force trim system. Both crew doors removed. (*)Heated pitot-static system. (*)Pilot windshield wiper.

Both sliding doors locked open or removed with both hinged panels installed or removed.

Operational AFCS. Two VHF communication radios Two navigation receivers with auxiliary equipment appropriate for intended route of flight.

NOTE Opening or removing doors shifts helicopter center of gravity and reduces VNE. Refer to Section 5 and to Airspeed Limitations. In all cases, door configuration shall be symmetrical.

DME equipment. ATC transponder.

1-5-D.

PASSENGERS

Marker beacon receiver. Standby attitude indicator or gyro rate of turn indicator. Pilot IVSI. Roof window blackout curtains Dual controls. Copilot instruments. Copilot clock.

1-4

Rev. 4

02 DEC 2002

NOTE R efe r to S ec tion 5 for lo ad ing tables to be used in weight/CG computations. With the passenger seat kit installed, the helicopter is certified for operations as a fifteen place aircraft. The above loading does not apply if cargo or a combination of cargo and passengers a re b e in g tr a n s p o r t ed . I t s h a ll b e th e responsibility of the pilot to ensure

FAA APPROVED

helicopter is properly loaded so entire flight is conducted within the limits of gross weight center of gravity charts

BHT-2121FR-FM-1

1-5-E.

CARGO

1-5-E-1. INTERNAL CARGO

(Figure 1-3).

CONFIGURATION Allowable deck loading for cargo is 100 pounds per square foot (4.9 kilograms/100

square centimeters). tiedown

Deck mounted

fittings are provided and have an

airframe structural capacity of 1250

Rev. 2

1-4A/1-4B

FAA APPROVED pounds (567.0 kilograms)

BHT-2121FR-FM-1 vertical and 500

NOTE

pounds (226.8 kilograms) horizontal per fitting. Provisions for installation of cargo tiedown fittings are incorporated in aft cabin bulkhead and transmission support structure

Station 0 (datum) is located 20 inches (508.0 millimeters) aft of most forward point of cabin nose.

and have an airframe structural

capacity of 1250 pounds (567.0 kilograms) at 90 degrees to bulkhead and 500 pounds (226.8 kilograms) In any direction parallel to bulkhead. Cargo shall be secured by an

approved restraint method that will not impede access to cargo in an emergency. All cargo and equipment must be securely

tied down when operating with aft cabin doors open or removed.

1-6-B-2.

LATERAL CENTER OF GRAVITY

Lateral

CG limits

are 3.5 inches

(88.9

millimeters) from fuselage centerline for IFR.

Lateral CG limits are 4.7 inches (119.4 millimeters)

left

and 6.5 inches

(165.1

millimeters) right of fuselage centerline for

I

1-5-E-2.

BAGGAGE

VFR.

The baggage compartment maximum allowable loading is 400 pounds (181.4 not to exceed 100 pounds per

kilograms),

1-7. AIRSPEED VMIN

(IFR) -

40 KIAS.

square foot (4.9 kilograms/100 square centimeters).

NOTE

1-6. WEIGHT AND CENTER OF GRAVITY 1-6-A. Maximum

Due to control authorities required for flight at airspeeds below 40 KIAS, AFCS ATTD mode

should not be utilized except for ground checks.

WEIGHT

VNE (IFR or VFR) -

GW is 11,200 pounds (5080.3

kilograms).

120 KIAS from sea

level up to and including

3000 feet HD at

8800 pounds (3991.6 kilograms)

or less

GW decreasing linearly to VNE of 100 KIAS

Refer to Weight-altitude-temperature limitations for takeoff, landing and in ground effect maneuvers chart (figure 1-4).

at (5080.3 GW, CG11,200 of 132.0pounds to 142.5. Referkilograms) to LIMITATIONS decal figure OPERATING 1-2 V decreases 3 KIAS per 1000 feet above 3000 feet HD.

1-6-B. 1-6-B-1.

CENTER OF GRAVITY LONGITUDINAL OF GRAVITY

VNE (VFR only)(CG

CENTER

Longitudinal CG operational range Is variable (figure 1-3), depending upon GW, and shall be computed from weight and

balance data.

Longitudinal CG limits are from station 132.0 to 142.5 for IFR. Longitudinal CG limits 132.0 to 144.0 for VFR.

142.5 to 144.0) - 110 KIAS from sea level up to and Including 3000 feet H D at 10,000 pounds (4536 kilograms) or less GW decreasing linearly to VNE of 100 KIAS at 11,200 pounds (5080.3 kilograms) GW, CG of 142.5 to 144.0. Refer to OPERATING LIMITATIONS decal, igure 1-2. VNE decreases 3 KIAS per 1000 feet above 3000 feet H VNE (VFR only) doors open or removed -

100 KIAS for any GW. Refer to Type of

Operation. are from

station

Maximum airspeed when above maximum continuous torque (87.5%) is 80 KIAS. Rev.2

1-5

BHT-2121FR-FM-1

FAA APPROVED

1-8. ALTITUDE Maximum operating-

which a safe power off landing can be made. 20,000 feet Hp.

Refer to applicable operating rules for high altitude oxygen requirements.

When takeoffs are made in accordance with HV charts, proceed as follows: Determine hover torque at a four foot skid height. Perform takeoff with no more than 15% torque above hover power while

accelerating to Takeoff Climbout MONITOR ITT WHEN STARTING

Speed (VTOCs). Refer to Section 4 for

ENGINE

VTOCS.

IN MANUAL

FUEL

CONTROL MODE

Above 15,000 feet Hp, restart shall be accomplished in manual fuel control mode only. (No airspeed restrictions.) Below 15,000 Hp, restart may be attempted

in either manual or automatic fuel control mode.

1-9. MANEUVERING

NOTE Downwind takeoffs are not recommended since published takeoff distance performance will not be achieved.

When near zero

wind conditions prevail, determine true direction of wind.

1-11. AMBIENT TEMPERATURES

1-9-A.

PROHIBITED MANEUVERS

Maximum sea level ambient air temperature for operation is +52 °C (+125 °F) and decreases with altitude at standard

Aerobatic maneuvers are prohibited.

lapse rate (2 °C per 1000 feet Hp). Minimum ambient air temperature at all altitudes is -54 °C (-65 °F). Refer to Weight-altitude-temperature limitations for

1-9-B. CLIMBAND DESCENT Refer to Section 4, PERFORMANCE.

takeoff, landing and in ground effect maneuvers chart (figure 1-4).

1-10. HEIGHT-VELOCITY The height-velocity

limitations

are critical

in the event of a single engine failure during takeoff, landing, or other operation near the surface (figure

1-5).

The AVOID

1-12. ELECTRICAL 1-12-A. BATTERY

area of the Height-Velocity chart defines the combinations of airspeed and height above the ground from which safe singleNG engine landing on a smooth, level, firm surface cannot be assured. BATTERY SHALL NOT BE USED

The H-V chart is valid only when the Weight-Altitude-Temperature limitations

FOR ENGINE START AFTER ILLUMINATION OF BATTERY

are not exceeded (figure 1-4). The diagram

TEMP

does not define the conditions assure

continued

flight

following

which an

engine failure nor the conditions from 1-6

LIGHT(IF

INSTALLED).

BATTERY SHALL BE REMOVED AND SERVICED IN ACCORDANCE

WITH

MANUFACTURER

FAA APPROVED

BHT-2121FR-FM-1

INSTRUCTIONS RETURNING

PRIOR TO

BATTERY

TO

28 vdc ground power units for starting shall be rated at a minimum of 400 amps and limited to a maximum of 1000 amps.

SERVICE. Maximum battery case temperature Maximum battery

internal

1-13. POWER PLANT PRATT AND WHITNEY CANADA PT6T3B and PT6T-3.

62.7 °C (145 °F) )

internal

1-12-B.

54.5 °C (130 °F)

GENERATOR

Maximum -

NOTE

Operation in 2 1/2 minute or 30

150 amps per ammeter.

minute OEI range is intended for emergency use only, when one

engine becomes inoperative due

NOTE

to actual malfunction.

To attain published single engine

OEI ranges

shall not be used for training.

performance, generator loads should not exceed 75 amps each

during twin engine operation.

1-13-A. GAS PRODUCER RPM (N1)

Ammeter needle may deflect full

1-13-A-1.

scale momentarily during

generator assisted start of second engine.

Limit starter energizing time to:

Maximum transient (not to exceed 30 seconds)

ON. OFF. ON. OFF. - ON. -

Either

15 minutes - OFF. Above energizing repeated.

Above

15,000

accomplished

cycle

OPERATION

PT6T-3B (Gage P/N 212-075-037-101) 61 to 100.8% Continuous operation Maximum continuous 100.8% Maximum for takeoff 100.8%

1-12-C. STARTER

30 seconds 60 seconds 30 seconds 5 minutes 30 seconds

TWIN ENGINE

102.4%

NOTE gage shall be installed

in

pairs. may then

Hp, restart

shall

be

be

in manual fuel control mode

Below 15,000 Hp, restart may be attempted

PT6T-3B (Gage P/N 212-075-037-113) Continuous operation 61 to 101.8% Maximum continuous 101.8%

101.8%

Maximum Maximum

Maximum transient (not to exceed 30 seconds)

103.4%

in either manual or automatic fuel control mode.

1-12-D.

GROUND POWER UNIT

PT6T-3 Maximum continuous Maximum transient (not to exceed 10 seconds)

100% 101.5%

Rev.2

1-7

FAA APPROVED

BHT-2121FR-FM-1

PT6T-3B (SINGLE ENGINE OPERATION)

ONE ENGINE

1-13-A-2.

30 Minute OEI

INOPERATIVE (OEI) PT6T-3B(Gage P/N 212-075-037-101) 100.8 to 102.4% 21/2 Minute range 102.4% Maximum

PT6T-3B(Gage P/N 212-075-037-113) 101.8 to 103.4% 103.4% Maximum

21/2 Minute range

range 2'/2 Minute OEI range Maximum OEI

765 to 822 °C 822 to 850 °C 850 °C

PT6T-3 5 Minute range (twin engine operation) 30 Minute range (OEI)

765 to 810 °C 765 to 810 °C

Maximum continuous limit (Single or twin engine operation transient limit

POWER TURBINE RPM

1-13-B.

PT6T-3B or PT6T-3 Takeoff

100%

97%

Minimum

97 to 100%

Continuous Operation Maximum continuous

765

(Max 5 second above 810 °C)

850 °C I

Starting transient limit (Not to exceed 2 seconds above 810°C).

1090 °C.

100%

operation Transient (not to

101.5%

exceed 10 seconds)

1-13-D.

ENGINE

NOTE For normal twin engine operation,

1-13-C. INTERTURBINE TEMPERATURE

maximum permissible torque

PT6T-3B (TWIN ENGINE OPERATION) 300 to 765 °C Continuous operation

765 °C

Maximum continuous

split is 4% total needle needle split is 4% total 1-13-D-1.

Maximum for takeoff Maximum transient (Not to exceed 5 seconds) Maximum for starting (Not to exceed 2 seconds above 960 °C

ONE ENGINE INOPERATIVE

765 to 810 °C

5 Minute takeoff range

TORQUE

(OEI)

810 °C

(ENGINE SCALE)

850 °C

PT6T-3B - TORQUEMETERS MARKED 71.8% Maximum 63.9% continuous 63.9% to 71.8% 30 Minute power 71.8% Maximum

1090 °C

NOTE If ITT remains above 810 °C longer

than 15 seconds or exceeds other limits,

ITT and duration

shall be

recorded in helicopter logbook. Refer to Pratt and Whitney

Maintenance

Manual for

inspection requirements. 1-8

Rev. 2

PT6T-3B - TORQUEMETERS MARKED

79.4% Maximum

continuous 30 Minute power

Maximum

63.9% 63.9% to 79.4%

79.4%

BHT-212IFR-FM-1

FAA APPROVED

1-15. ROTOR

1-17. FUEL AND OIL

1-15-A. ROTOR RPM – POWER ON

1-17-A. FUEL

Minimum Maximum

97% 100%

1-15-B. ROTOR RPM – POWER OFF Minimum Maximum

91% 104.5%

1-16. HYDRAULIC

NOTE Refer to BHT-212-MD-1 for approved fuels list. Fuel conforming to ASTM D-1655 Type B, NATO F-40, or MIL-T-5624, Grade JP-4 may be used at all ambient air temperatures. Fuel conforming to ASTM D-1655 Type A or A-1, NATO F-44 MIL-T-5624, Grade JP-5, NATO F-34, or MIL-T-83133, Grade JP-8 may be used at ambient air temperatures above -30°C (-22°F).

NOTE Refer to BHT-212-MD-1 for approved fluids and vendors. Hydraulic fluid type MIL-H-5606 (NATO H-515) shall be used at all ambient temperatures. Both hydraulic systems shall be operative prior to takeoff.

1-16-A. HYDRAULIC PRESSURE Minimum Caution range Normal Operating Maximum

600 PSI 600 — 900 PSI 900 — 1100 PSI 1100 PSI

NOTE Refer to BHT-212-MD-1 for approved vendors. Oil conforming to PWA Specification No. 521 Type 1 and MIL-L-7808 (NATO 0-148) may be used at all ambient air temperatures. Oil conforming to PWA Specification No. 521 Type 2 and MIL-L-23699 (NATO 0-156) or DODL-8 57 34 m ay b e us ed at all am b ient air temperatures above -40°C (-40°F).

1-17-C. OIL – TRANSMISSION, INTERMEDIATE AND TAIL ROTOR GEARBOXES

1-16-B. HYDRAULIC TEMPERATURE Maximum

1-17-B. OIL – ENGINE AND COMBINING GEARBOX

88°C

Oil conforming to MIL-L-7808 (NATO 0-148) may be use d at all approve d ambient temperatures. Oil conforming to, DOD-L-85734AS (Turbine Oil 555) and MIL-L-23699 (NATO 0-156), may be used at all ambient air temperatures above -40 °C (-40 °F).

1-10

Rev. 4

02 DEC 2002

BHT-2121FR-FM-1

FAA APPROVED NOTE DOD-L-85734AS or MIL-L-23699 is recommended.

1-20. INSTRUMENT MARKINGS AND PLACARDS

1-18. ROTOR BRAKE

Refer to Figure 1-1 and 1-2 for Instrument range markings, placards, and decals.

Engine starts with rotor brake engaged are

1-21. HEATER

prohibited.

Rotor brake application is

limited to ground operation and shall not be applied until engines have been shut down and ROTOR RPM (NR) has decreased

Heater shall not be operated when OAT is above 21 °C.

to 40% or less.

Refer to Appendix A for listing of Flight Manual Supplements (FMS) covering optional equipment kits available.

1-19. LANDING GEAR No Flight Manual Limitations

1-11/1-12

FAA APPROVED

BHT-2121FR-FM-1

(TYPICAL)

PANEL AFT END OF OVERHEAD CONSOLE

(if installed)

Figure 1-2.

Placards and decals

2121FR-FM-1-2-1

(Sheet

1 of 2)

Rev.

1-19

FAA APPROVED

BHT-2121FR-FM-1

NOTES: USEDWITH GAS PRODUCER GAGEP/N 212-075-037-101 USEDWITH GAS PRODUCER GAGEP/N 212-075-037-113 2121FR-FM-1-2-2

LOCATION: 212-IFR-FM-1-4-2

Figure 1-2.

1-20

Rev.1

Placards and decals (Sheet 2 of 2)

BHT-2121FR-FM-1

FAA APPROVED

11,000

8.000

6,000

5,000

132

134

136

138

140

142

144

LONGITUDINALCG STATION- INCHES

2121FR-FM-1-3

Figure 1-3.

Gross weight center of gravity chart

Rev. 1

1-21

BHT-2121FR-FM-1

FAA APPROVED

NOTE: ALLOWABLE GROSS WEIGHTS OBTAINED FROM THIS CHART MAY EXCEED CONTINUOUS HOVER CAPABILITY UNDER CERTAIN AMBIENT CONDITIONS. REFER TO HOVER CEILING CHARTS IN SECTION 4

14,000 FT. DEN. ALT. UNIT

/

-

14,000

6000

2000

-40

-20

0 20 OAT - °C

40

60

8 -38

9 42

10 46

11 50

12 LB X 1000 1 KG X 100 54

GROSSWEIGHT

2121FR-FM1-4

Figure 1-4. Weight-altitude temperature limitations for takeoff, landing and in ground effect maneuvers chart 1-22

Rev. 1

FAA APPROVED

BHT-2121FR-FM-1

450 NOTE: THEHELICOPTERCONFIGURATION SHALLCOMPLYWITHTHEWEIGHTALTITUDE-TEMPERATURECHART

400

FOR HEIGHT-VELOCITY DIAGRAM TO BE VALID

350

250 250

1000 LBLESS THAN

0 200

150

50

0

10

Figure 1-5.

20 30 40 INDICATEDAIRSPEED -

50 KNOTS

60

70

Single engine height velocity chart

Rev. 1

1-23/1-24

FAA APPROVED

BHT-2121FR-FM-1

Section 2 TABLE OF CONTENTS Subject

Paragraph

INTRODUCTION...........................

2-1...

.............

FLIGHT PLANNING ............................ 2-2..................... TAKEOFF AND LANDING ......... .................... 2-2-A ........ WEIGHT AND BALANCE ................................... 2-2-B ........ PREFLIGHT CHECK ............................ ..................... BEFORE EXTERIOR CHECK .............................. 2-3-A ....... EXTERIOR CHECK ......................................... 2-3-B ....... INTERIOR AND PRESTART CHECK ............................ 2-4........ ENGINE START . ............................................. 2-5 ENGINE 1 START........................................... 2-5-A ...... ENGINE 2 START........................................... 2-5-B ...... POST START ............................................... 2-5-C ...... ENGINE FAILS TO START ................................. 2-5-D ..... DRY MOTORING RUN ............................ ........ 2-5-E ..... SYSTEMS CHECK ............................ 26................... . .. FORCE TRIM CHECK...................................... 2-6-A . ..... PRELIMINARY HYDRAULIC CHECK ....................... 2-6-B .... . ENGINE FUEL CONTROL CHECK....................... 2... 2-6-C ...... GOVERNOR CHECK ........................................ 2-6-D ........ FUEL CROSSFEED VALVE CHECK........................ 2-6-E ....... ELECTRICAL SYSTEMS CHECK ........................... 2-6-F........ AFCS CHECK ............................ . ....... 2-....... 2-6-G....... CABIN HEATER CHECK.................................... 2-6-H ....... HYDRAULIC SYSTEM CHECK.............................. 2-6-J......... BEFORE TAKEOFF ......... ................... ......... .........2-7 POWER ASSURANCE CHECK ............................. 2-7-A ....... PROLONGED GROUND OPERATION ...................... 2-7-B ....... TAKEOFF ........................................................ ........... INFLIGHT OPERATIONS ....................................... . DESCENT AND LANDING ............ ........................ . 2-10......... ENGINE SHUTDOWN ............................................ 2-11 POSTFLIGHT CHECK ........................................... 2-12 .........

Page Number

2-3 2-3 2-3 2-3 2-3 2-3 2-4 2-6 2-7 2-8 2-9 2-9 2-10 2-10 2-10 2-10 2-11 2-11 2-11 2-11 2-11 2-12 2-14 2-14 2-15 2-16 2-16 2-16 2-16 2-17 2-17 2-18

LIST OF FIGURES Figure Number

Title Exterior check diagram ............................

........

2-1 ...........

Page Number 2-19 2-1/2-2

FAA APPROVED

BHT-2121FR-FM-1

Section 2 2-1.

INTRODUCTION

Consult applicable weight and balance instructions provided in Section 5.

This section contains instructions and and This contains section instructions procedures for operating helicopter from planning stage, through actual flight conditions, to securing helicopter after landing.

Normal and standard conditions are assumed in these procedures. Pertinent

Determine weight of fuel, oil, load, etc.,

takeoff and anticipatated landing

GW, and check helicopterCG locations. Ensure weight and balance limitations Section 1 are not exceeded.

in

data in other sections is referenced when

2-3.

Instructions

whether helicopter is in condition for safe

applicable.

and procedures contained

herein are written for purpose

of

standardization and are not applicable to all situations.

PREFLIGHT CHECK

Pilot is responsible for determining

flight.

NOTE

2-2.

FLIGHT PLANNING

Planning of mission to be accomplished

will provide pilot with data to be used during flight. Information to be used can be compiled as follows: Check type of mission to be performed

Preflight check is not intended to

be a detailed

mechanical

Inspection, but a guide to check

condition of helicopter.

This

check may be made as comprehensive as conditions warrant.

and destination.

All areas checked shall include a

Select appropriate performance charts

corrosion,

to be used from Section 4.

2-2-A.

visual check for evidence of helicopter

particularly is flown

when

near or over

salt water or in areas of high industrial emissions.

TAKEOFF AND LANDING

Refer to Section 1 for takeoff and landing

weight limits and to Section 4 for takeoff

2-3-A. BEFORE EXTERIOR

CHECK

and landing data.

Flight planning - Completed. 2-2-B.

WEIGHT AND BALANCE

Determine proper weight and balance of helicopter as follows:

Publications-

Check.

Ensure helicopter has been serviced as required. Rev. 2

2-3

FAA APPROVED

BHT-2121FR-FM-1

2-3-B. EXTERIOR CHECK

(left and

Fuel sump drain buttons

right) - Press.

Fuel filters - Drain before first flight of day as follows: IF HELICOPTER

ENGINE 1 BOOST PUMP and ENGINE2 BOOSTPUMPswitches -

HAS BEEN

ON.

EXPOSED TO SNOW OR ICING CONDITIONS, SNOW AND ICE SHALL BE REMOVED PRIOR TO FLIGHT. 1. FUSELAGE-

ENGINE 1 FUEL and ENGINE2 FUEL switches - ON.

FRONT

Rotor blade -

Fuel filters (left and right) -

Condition and

cleanliness.

ENGINE 1 FUEL and ENGINE 2 FUEL

Cabin area clean.

Condition, all glass

unobstructed.

Covers removed,

Static ports (left and right) -

1 BOOST

Remote hydraulic filter Indicator - Check green.

bypass

Cabin nose ventilators Unobstructed.

-

PUMP and

ENGINE 2 BOOST PUMP switches -

OFF.

BATTERY BUS 1 switch 2. FUSELAGE -

Unobstructed.

OFF.

CABIN LEFT SIDE

Copilot and passenger doors -

Condition and operation, glass clean.

Security of emergency release

handles.

Position lights - Condition.

Nose compartment doors secured.

Condition and

Battery vent and drain tubes Unobstructed. and landing

light

-

Drain samples as

follows:

ENGINE 1 BOOST PUMP and ENGINE2 BOOSTPUMPswitches OFF. ENGINE 1 FUEL and ENGINE 2 FUEL

switches - OFF. BATTERY BUS 1 switch -

Condition, ground

ON.

Engine air intake -

unobstructed.

Antenna - Condition, security. Fuel sumps -

Landing gear -

handling wheels removed.

Battery vent and drain tubes -

2-4

switches - OFF. ENGINE

Pitot tubes -

Searchlight

Drain

samples.

Cover removed,

3. FUSELAGE- AFT LEFT SIDE Drain lines -

Clean, unobstructed.

Engine compartment

-

Check.

Engine oil level - Verify presence of oil in sight gage and proper oil level.

Engine governor spring -

Condition.

Engine fire extinguisher -

Bottle

pressure gage and temperature range.

BHT-2121FR-FM-1

FAA APPROVED

Combining gearbox filter indicator retracted.

Bypass

Access doors and engine cowling -

Engine compartment - Check. Engine oil level - Verify presence of oil and proper level in sight gage.

Secured.

Engine exhaust ejector tubes Covers removed, unobstructed.

Check fuel quantity,

secure cap.

6. FUSELAGE -

Condition.

Tail rotor driveshaft covers Secured. *secured.

Synchronized elevator z security

Condition,

Main rotor blade - Condition, cleanliness. Removetiedown. Tail rotor gearbox -

Secured.

Fuel filler -

4. FUSELAGE -AFT Tailboom -

Access doors and engine cowling -

Verify presence

CABIN RIGHT SIDE

removed, Engine air intake - Cover removed, unobstructed.

Transmission oil - Verify presence of oil and proper level in sight gage.

Pilot and passenger

doors-

Condition and operation, glass clean. Security of emergency release

of oil and proper level in sight gage,

handles.

security.

Position lights -

Tail rotor - Condition, free movement on flapping axis.

Landing gear - Condition, ground handling wheels removed.

filler cap and chip detector plug

Tail rotor yoke - Evidence of static stop contact damage (deformed static stop yield indicator). presence of oil and proper level in

sight

gage. Filler cap and chip

detector plug security. Tail skid -

Condition,

smoke detector -

-

Check

Condition and

security. Cargo and door secured. 5. FUSELAGE -

AFT RIGHT SIDE

Engine fire extinguisher

SNOW AND ICE SHALL BE REMOVED PRIOR TO FLIGHT

CONDITIONS. Main rotor and controls - Condition, fluid levels in all reservoirs.

Tailboom - Condition. Baggage compartment

CAUTION

WHEN HELICOPTER HAS BEEN EXPOSED TO SNOW OR ICING

Condition, security.

Synchronized elevator security.

7. CABIN TOP

Verify

Intermediate gearbox -

Condition.

-

Transmission oil filler cap - Secured. Hydraulic oil reservoirs - Check sight glasses for proper fluid levels. Caps secured.

Bottle

Antenna(s)-

Condition and security.

pressure gage and temperature range.

Combining gearbox oil level - Verify presence of oil and proper level In

Combining gearbox oil filler cap Secured

sight gage. Close access door. Rev. 3

2-5

FAA APPROVED

BHT-2121FR-FM-1

Condition and

light -

Anticolllsion security.

Shoulder harness inertia reel and lockCheck. Flight controls - Freedom of movement, position for start.

CAUTION

Cyclic - Centered,.friction as desired. IF ANY TEMP-PLATE IS MISSING

Collective - Full down.

DOTS, OR HAS BLACK MAINTENANCE PERSONNEL SHALL ASSIST IN DETERMINING

Transmission chip detector indicators (if installed) -

AIRWORTHINESS.

-

and coupling

Main driveshaft

Condition, security, and grease leakage. Check Temp-Plates (four places each coupling) for evidence of elevated temperature indicated

by dot

Check.

Lower pedestal circuit breakers - In. Collective control head switches - OFF. COMPASS CONTROL slaving swltch(es)

changing color to black.

- MAG (slave position).

Engine air intakes - Unobstructed, particle separator doors closed.

Radio equipment - OFF. Fuel INTCON switch -

NORM.

Engine and transmission cowling Secured.

Fresh air inlet screen -

Unobstructed.

ENGINE 1 BOOST PUMP and ENGINE 2 BOOST PUMP switches - OFF. FUEL XFEED switch -

NORM.

2-4. INTERIOR AND

ENGINE 1 FUEL and ENGINE 2 FUEL

PRESTART CHECK

switches

Cabin interior equipment.

Cleanliness,

Portable fire extinguishers charge, secured. Passenger

seats

-

security -

Secured,

of

-

OFF.

ENGINE NO. 1 PART SEP and ENGINE NO. 2 PART SEP switches - NORM.

Proper

ENGINE NO. 1 GOV and ENGINE NO. 2 GOV switches - AUTO.

each

HYDR SYS NO. 1 and HYDR SYS NO. 2

occupied seat equipped with seat belt.

switches -

Crew and passenger doors - Secured.

STEP switch (if Installed) - As desired.

Cargo load -

FORCE TRIM switch -

Secured.

Protective breathing equipment (if required) - Condition and properly serviced.

ON.

ON, cover down.

Instruments- Staticcheck. STATIC SOURCEswitch (if installed) PRI.

Seat and pedals -

Adjust.

Seat belt and shoulder harness Fasten and adjust.

Altimeter(s) - Set. Clock -

Set and running.

FIRE EXT switch 2-6

OFF.

FAA APPROVED

BHT-212IFR-FM-1

FIRE PULL handles — In (forward). AFT DOME LT rheostat and switch — OFF.

e x t i n g u i s h e x c e p t C AU T I O N PA N E L segment and MASTER CAUTION light. (Both ENG OUT lights and RPM light will dim during test.)

PITOT STATIC HEATERS switch — OFF.

CAUTION

WIPERS switch — OFF. CARGO REL switch (if installed) — OFF. VENT BLWR switch — OFF. HEAT AFT OUTLET switch — OFF. SYSTEM SELECTOR switch — OFF. AIR COND TEMP CONT switch (if installed) — As desired. NAV AC switch — NORM. Overhead circuit breakers — In. All light rheostats — OFF. EXTERIOR LIGHT POSITION switch — OFF. EXTERIOR LIGHT ANTI COLL switch — OFF.

ROTOR BRAKE HANDLE SHALL BE IN DETENT POSITION (OFF) AT ALL TIMES WHEN ENGINES ARE RUNNING. ROTOR BRAKE lights — Test. Pull brake lever and check that both lights illuminate; return to off and check lights extinguish. FIRE PRESS TO TEST switch — Press and release. FIRE PULL 1 and FIRE PULL 2 warning lights illuminate when switch is pressed and extinguish when switch is released. BAGGAGE FIRE warning light TEST button — Press to test (verify light flashes). CARGO RELEASE ARMED light (if installed) — TEST.

INV 1, INV 2, and INV 3 switches — OFF. Caution panel lights — TEST and RESET. NON ESS BUS switch — NORMAL. GEN 1 and GEN 2 switches — OFF. External power — Connect (as desired). Check DC voltmeters for 27 ± 1 volts. Adjust external power source, if required. BATTERY BUS 1 and BATTERY BUS 2 switches — ON, check BATTERY caution light illuminates.

NOTE Test all lights when night flights are planned or anticipated. Accomplish light tests with external power connected or during engine runup. MASTER CAUTION switch (overhead) — TES T, check a ll c autio n p anel lights

INV 1 switch — ON, check no. 1 AC voltmeter for 104 to 122 volts. INV 2 switch — ON, check no. 2 AC voltmeter for 104 to 122 volts. FUEL QTY SEL switch — LEFT, then RIGHT; check fuel quantity gauge indicates lower fuel cell quantity of 270 to 300 pounds (each).

2-5.

ENGINE START NOTE

If helicopter has been cold soaked in ambient temperature of -18 °C ....

02 DEC 2002

Rev. 4

2-7

FAA APPROVED

BHT-2121FR-FM-1

GAS PROD RPM (N,) - Check 61 ± 1% when throttle is on idle stop.

If battery start: GAS PROD RPM (N1) GEN 1 switch AMPS 1 -

71%.

ON.

Check at or below 150 amps.

Engine 2 throttle - Open to Idle at 12% GAS PROD RPM (N1 ) minimum.

Engine 2 ITT limitations.

Monitor. Observe ITT

START switch RPM (N1)

Off at 55% GAS PROD

GAS PROD RPM (N1) - Check 61 + 1% when engine 2 throttle is on Idle stop.

NOTE CAUTION

During extremely cold ambient temperatures, idle rpm will be high and ENGINE OIL, XMSN OIL, and GEAR BOX OIL pressures may exceed maximum limits for up to 2 minutes after starting.

ENSURE SECOND ENGINE ENGAGES AS THROTTLE IS INCREASED. A NON-ENGAGED ENGINE IS INDICATED BY 10 TO 15% ENG RPM (N2) HIGHER THAN ENGAGED ENGINE AND NEAR

Do not increase ROTOR RPM (NR)

above

80% until

XMSN OIL

ZERO TORQUE.

temperature is above 15 °C. ENGINE OIL, XMSN OIL, AND GEAR BOX OIL pressures - Check. ENG 1 PART SEP OFF caution Extinguished.

IF A NON-

ENGAGEMENT OCCURS, CLOSE THROTTLE OF NON-ENGAGED ENGINE. WHEN NON-ENGAGED ENGINE HAS STOPPED, SHUT DOWN ENGAGED ENGINE.

light IF S U D D E N ( H A R D) ENGAGEMENT OCCURS, SHUT

Engine 1 throttle - Increase to 85% ENG RPM (N2). Friction as desired.

BOTH DOWN MAINTENANCE

ENGINES. ACTION IS

REQUIRED.

2-5-B.

ENGINE 2 START

ENGINE 2 BOOST PUMP switch - ON, check ENG 2 FUEL BOOST caution light

Engine 2 throttle - Increase slowly to 85% ENG RPM (N2). Monitor tachometer and torquemeter to verify engagement of second engine.

extinguished (FUEL XFEEDcaution light will illuminate momentarily).

Engine 2 ENGINE OIL pressure -

ENGINE 2 FUEL switch - ON. (ENG 2 FUELVALVE caution light will illuminate momentarily.)

ENG 2 PART SEP OFF light Extinguished.

Engine 2 FUEL PRESS -

START switch

-

2-5-C.

Check.

ENG 2 position.

Observe starter limitations. Engine

2 ENGINE

Indicating.

OIL pressure

-

POST START

External power GEN 1 switch -

-

Check.

GEN 2 switch -

Disconnect if used,

ON. ON (BATTERY BUS 1

will switch OFF automatically).

2-9

FAA APPROVED

BHT-2121FR-FM-1

2-5-E.

CAUTION

DRY MOTORING RUN

Following procedure is used to clear an engine whenever it Is deemed necessary to remove internally trapped fuel and vapor:

IF OPERATING ON BATTERY BUS 1, POSITION INV 3 SWITCH TO ON DC BUS 1.

Throttle -

ONLY ONE BATTERY SWITCH SHALL BE ON DURING FLIGHT.

Caution lights -

ENGINE (1 or 2) BOOST PUMP switch ON.

Check all extinguished.

ENGINE OIL, XMSN OIL, and GEAR BOX

OIL temperatures Within limits.

and pressures

AMPS 1 and AMPS 2 -

-

ON.

ENG IGN SYS circuit breaker-Pull

ENGINE (1 or 2) FUEL switch -

ENG IGN SYS circuit

for

Check

OFF.

ENGINE (1 or 2) BOOST PUMP switch OFF.

ON as required.

ELT (if installed) inadvertent transmission.

breaker -

In.

Allow required cooling period for starter before proceeding. Follow normal start sequence as described on preceding pages. Refer to SECTION 1, STARTER LIMITATIONS.

ENGINE FAILS TO START

When engine fails to light off within 15 seconds after throttle

action is

recommended:

IDLE STOP REL switch - Actuate. Throttle -

2-6.

SYSTEMS CHECK

has been opened

to idle, following

Fully closed.

2-6-A. FORCE TRIM CHECK Flight controls -

Friction off; collective

lock removed. Cyclic and pedals -

Move slightly each

START switch - OFF.

direction to check force gradients.

ENGINE (1 or 2) BOOST PUMP switch

Cyclic

-

out.

START switch - Engage for 15 seconds,

AMPS 2 will indicate a higher load than AMPS 1 until battery is fully charged.

2-5-D.

ENGINE (1 or 2) FUEL switch -

then disengage.

Within limits,

NOTE

Radios -

Fully closed.

OFF.

ENGINE (1 or 2) FUEL switch -

FORCE TRIM release button -

Press; check trim releases with button

pressed, reengages with button OFF.

released.

After GAS PROD RPM (N 1) has decreased to zero, allow 30 seconds for fuel to drain from engine. Conduct a

FORCE TRIM switch - OFF; check trim disengages and FT OFF caution light illuminates.

DRY MOTORING RUN before attempting another start.

FORCE TRIM switch -

2-10

Rev. 2

ON.

FAA APPROVED

2-6-B.

BHT-2121FR-FM-1

PRELIMINARY HYDRAULIC

CHECK Throttles -

NOTE

INCR to 100%

2-6-E. FUEL CROSSFEED VALVE CHECK

Set to idle.

Uncommanded control

RPM INCR DECR switch (N2 ).

NOTE movement

FUEL XFEED test switch and hold.

TEST BUS 1

or motoring with either hydraulic system off may indicate hydraulic system malfunction.

NOTE

HYDR SYS NO. 1 switch HYDR SYS NO. 2 switch ON.

-

OFF, then OFF, then

2-6-C. ENGINE FUEL CONTROL CHECK Throttles -

Idle. NOTE

Do not allow GAS PROD RPM (N1) to decrease below 50%. Around 8000 feet Hp, GAS PROD

RPM (N 1 ) may not change significantly when manual fuel control is selected.

If, after turning either boost pump off, fuel pressure remains 4 to 6

psi below normal (10 ± 4 psi), appropriate check valve is not functioning

properly.

ENGINE 1 BOOST PUMP switch - OFF. Check no. 1 FUEL PRESS decreases,

then returns to normal. (This indicates that crossfeed valve has opened by bus

no. 1 power and check valve is functioning properly.) PUMP switch - ON.

ENGINE 1 BOOST

FUEL XFEED test switch and hold.

TEST BUS 2

ENGINE 2 BOOST PUMP switch - OFF. Check no. 2 FUEL PRESS decreases, then returns to normal. ENGINE 2

BOOSTPUMPswitch - ON. FUEL XFEED test switch -

NORM.

GOV switch (ENGINE NO. 1 or 2) MANUAL, observe change in GAS PROD RPM (N1 ). Open respective throttle carefully to assure GAS PROD RPM (N1 )

FUEL XFEED switch -

idle. Return GOV switch to AUTO. Check for return to original GAS PROD RPM (N1 ). Check other governor in same manner.

ENGINE 1 (or ENGINE 2) BOOST PUMP switch - ON.

responds upward, then return throttle to

2-6-D.

GOVERNOR CHECK

No. 1 throttle - Full open. Check ENG RPM (N2 ) stabilizes at 95 ± 1%. No. 2 throttle - Full open. Check no. 1 engine ENG RPM (N2 ) increases 2% and both engines stabilize at 97 ± 1% N2 .

OVRD CLOSE.

ENGINE 1 (or ENGINE 2) BOOST PUMP switch - OFF. Check fuel pressure

drops to zero on selected system.

FUEL XFEED switch -

NORM.

2-6-F. ELECTRICAL SYSTEMS CHECK DC voltmeters -

Check 27 ± 1 vdc.

AC voltmeters -

Check 104 to 122 vac.

Ammeters -

Check within limits. 2-11

BHT-2121FR-FM-1

FAA APPROVED

AC system - Check as follows:

light illuminates, then extinguishes after several seconds.

INV 3 switch -

ON DC BUS 2, check

INVERTER extinguishes.

3 caution

light

Cyclic - Move laterally and hold. Check that roll NO GO light Illuminates, then extinguishes after several seconds.

INV 2 switch - OFF, INVERTER 2 caution light illuminates. Check no. 2

Return to neutral.

inverter no. 3 has assumed load. INV

yaw NO GO light

2 switch -

extinguishes

AC voltmeter

for indication

that

ON. INVERTER2 caution

Pedals -

Move and hold. Check that illuminates,

light extinguishes.

Return pedals to neutral.

INV 3 switch -

SCAS switch

OFF, then ON DC BUS

1, check INVERTER 3 caution light extinguishes. INV 1 switch - OFF, INVERTER 1 caution light illuminates. Check no. 1

-

ENGA, SCAS lights

illuminate. SCAS switch extinguish.

DSENGA, SCAS lights

AC voltmeter for indication that

SCAS switch -

inverter no. 3 has assumed load. INV 1 switch - ON. INVERTER 1 caution light extinguishes.

illuminate.

INV 3 switch

INV 1 switch

-

OFF, INVERTER 3

caution light illuminates. INV 3 switch -

ON DC BUS 2, INVERTER 3 caution

light extinguishes. 2-6-G.

ENGA, SCAS lights

OFF, SCAS disengages. -

ON, check

voltmeter for 104to 122 volts.

NOTE

NOTE

SCAS switch -

illuminate.

is

annunciated on instrument panel by a three segment light (PITCH, ROLL, YAW). AFCS functions In

steering.

AFCS

SCAS switch -

illuminate.

Press, SCAS

ENGA, SCAS lights

Copilot AFCS RELEASE disengages.

two modes - automatic with turn and trim functions, and pilot

no. 1 AC

ENGA, SCAS lights

Pilot AFCS RELEASE disengages.

AFCS mode operation

cyclic

INV 1 switch -

SCAS switch illuminate.

AFCS CHECK

then

after several seconds.

Press, SCAS

ENGA, SCAS lights

annunciation is applicable to both modes. AFCS power -

FORCE TRIM ON.

ATTD switch

Channel arm switches -

ATTD switch -

should extinguish

Illuminated,

within several

seconds to Indicate system null. for lights to extinguish.

-

ENGA, AFCS lights

illuminate, SCAS lights extinguish.

ATTD.

SCAS NO GO lights -

ON, cover down.

DSENGA, AFCS lights

extinguish, SCAS lights Illuminate.

Wait

ATTD switch - ENGA, AFCS lights illuminate, SCAS lights extinguish.

Cyclic - Move forward and hold, then aft and hold. Check that pitch NO GO

Pilot AFCS RELEASE - Press, AFCS lights extinguish, SCAS disengages.

2-12

FAA APPROVED

BHT-2121FR-FM-1

SCAS switch illuminate.

ENGA, SCAS lights

Center cyclic using cyclic FORCE

ATTD switch - ENGA, AFCS lights illuminate, SCAS lights extinguish. Copilot Copilot

laterally. Cyclic should follow and AFCS ROLL light remain illuminated.

Press, Press, AFCS AFCS

AFCS AFCS RELEASE RELEASE --

lights extinguish, SCAS disengages.

TRIM switch. Turn -

Actuate turn knob through

follow and AFCS Cyclic should cycle. PITCH remainremain PITCH and and ROLL ROLL lights

illuminated,

AFCS YAW light

extinguishes. Center cyclic using cyclic FORCE TRIM switch. CAUTION

AFCS pilot cyclic steering mode Check as follows:

MONITOR ALL CONTROLS TO CONTROL E NS U R E DEFLECTIONS ARE NOT EXCESSIVE DURING AFCS

CHECK.

Pitch - Displace cyclic slightly forward and release. AFCS PITCH light extinguishes and SCAS PITCH

light illuminates.

Displace cyclic

switch - ENGA. ENGA. SCAS switch-

slightly aft and release. AFCS PITCH light extinguishes and SCAS PITCH

ATTD switch -

Roll - Displace cyclic slightly left and

light illuminates.

ENGA. NOTE

Cyclic friction must be properly set for proper AFCS operation, Friction adjust ring must neither be tightly compressed against minimum friction bracket nor be excessively tight. Cyclic friction AFCS automatic follows:

Adjust. mode -

Check as

Pitch - Actuate pitch trim wheel through cycle. Cyclic should follow

and AFCS PITCH light illuminated.

AFCS ROLL light

extinguishes

and SCAS ROLL light

illuminates. Displace cyclic slightly right right and and release. release. AFCS AFCS ROLL ROLL light light

extinguishes and SCAS ROLL light

Yaw - Displace left pedal slightly forward and release. AFCS YAW light extinguishes and SCAS YAW light illuminates. Displace right pedal slightly forward and release. AFCS YAW light extinguishes and SCAS YAW light illuminates.

CAUTION

remain

Center cyclic using cyclic

FORCE TRIM switch.

release.

Actuate AFCS

TRIM switch forward and aft. Cyclic should follow and AFCS PITCH light

CYCLIC CONTROLS MAY MOTOR

TO STOP IF AFCS IS LEFT ENGAGED AND UNMONITORED DURING GROUND OPERATIONS.

remain illuminated. Center cyclic using cyclic FORCETRIM switch.

FOR PROLONGED

Roll -

OPERATION, AFCS SHALL NOT BE OPERATED IN ATTD MODE.

Actuate roll trim wheel through

GROUND

cycle. Cyclic should follow and AFCS ROLL light remain illuminated.

Center

cyclic using cyclic FORCE TRIM switch.

Actuate AFCS TRIM switch

2-13

FAA APPROVED

BHT-2121FR-FM-1

VENT BLOWERswitch -

DSENGAprior to takeoff.

ATTD switch -

2-6-H. CABIN HEATER CHECK GAS PROD RPM (N,) minimum (both engines).

75%

Check

As desired.

2-6-J. HYDRAULIC SYSTEM CHECK NOTE

AIR COND TEMP CONT switch -

Fully

COOL.

CAUTION SYSTEM SELECTOR SWITCH SHALL BE TURNED OFF WHEN HEATED AIRFLOW DOES NOT SHUT OFF AFTER AIR COND TEMP CONT SWITCH IS TURNED TO FULLY COLD, HEATER AIR

LINE

CAUTION

This check is to determine proper operation of hydraulic actuators for each flight control system. If abnormal forces, unequal forces, control binding, or motoring is encountered, it may be an indication of a malfunction of a flight control actuator. FORCE TRIM switch Collective -

LIGHT

OFF.

Down, friction

removed.

ROTORRPM (NR)- Set to 100%.

OR CABIN HTR ILLUMINATES, CIRCUIT BREAKER TRIPS.

Cyclic -

Centered, friction removed.

DO NOT OPERATE HEATER Hydraulic system -

ABOVE 21 °C OAT. SYSTEM SELECTOR switch -

HEATER.

AIR COND TEMP CONT switch -

Rotate

counterclockwise and observe heatedyclic airflow. DEFOG lever -

ON; check airflow is

diverted from pedestal outlets to windshield nozzles. OFF.

Return lever to

AFT OUTLET switch -

ON; check

airflow distributed equally between pedestal outlets switch to OFF.

and aft outlets.

Check

-

OFF.

MASTER CAUTION and

HYDRAULIC caution lights Illuminate and hydraulic system no. 1 pressure

ON.

VENT BLOWERswitch -

Check as follows:

HYDR Check SYS NO. 1 switch

decreases.

Check normal operation by Cyclic -- Check normal operation by

moving cyclic in an 'X' pattern right forward to left aft, then left forward to right aft (approximately 1 inch).

Centercyclic.

Collective - Check normal operation by Increasing collective slightly (1 to 2 inches). Return to down position.

Return NOTE

Boost for tail rotor controls is furnished

NOTE

Heater operation affects performance. Refer to Hover Ceiling and Rate of Climb charts for HEATER ON in Section 4.

SYSTEM SELECTOR switch desired. 2-14

Rev. 2

-

by hydraulic system no.

1 only. When hydraulic system no. 1 is being checked, tail rotor controls will be unboosted.

As

FAA APPROVED

BHT-2121FR-FM-1

Pedals - Displace slightly left and right. Note an increase in force required to move pedals.

WARNING BOTH HYDRAULIC SYSTEMS SHALL BE OPERATIONAL PRIOR TO TAKEOFF.

WARNING

DO NOT TURN BOTH HYDRAULIC SYSTEMS OFF AT SAME TIME DUE TO EXCESSIVE FORCE REQUIRED TO MOVE FLIGHT CONTROLS. HYDR SYS NO. 1 switch - ON. Check MASTER CAUTION and HYDRAULIC

caution lights extinguish and hydraulic system returns to normal.

no. 2 pressure

HYDR SYS NO. 2 switch

-

OFF.

Check MASTER CAUTION and HYDRAULIC caution lights illuminate and hydraulic decreases.

Cyclic -

system no. 2 pressure

NOTE System 1 will normally operate 10 to 20 °C cooler than system 2.

2-7.

BEFORE

TAKEOFF

Engine, transmission, gearbox,

hydraulic, and electrical Instruments Check readings within operational range.

Flight instruments and set. Attitude indicators -

Check operation Erect and set.

Check normal operation by

moving cyclic

in an 'X' pattern, right

NOTE

Check normal operation

If fast slaving is desired,set roll trim to null, push and hold VG FAST ERECT switch (if installed) until attitude indicator displays

forward to left aft, then left forward to right aft (approximately 1 Inch). Center cyclic. Collective -

by increasing collective slightly (1 to 2 inches). Return to down position.

Pedals - Displace slightly left and right. Note no increase in force required to move pedals. HYDR SYS NO. 2 switch - ON. Check MASTER CAUTION and HYDRAULIC

caution lights extinguish and hydraulic system returns to normal.

no. 1 pressure

Cyclic and collective friction - As desired.

FORCE TRIM switch-ON.

zero degrees bank angle.

Turn and slip indicators - Operative. HSls -

Slaved and heading correct,

course bar and bearing pointers set to

proper navigation receivers.

CAUTION

INDICATOR IS

CPLT/PLT

INDICATOR IS ILLUMINATED, CHANGING COURSE SETTING ON

HSI OF COPILOT/PILOT

IN

COMMAND WILL CHANGE

COURSE

SETTING

ON

REMAINING HSI (IF INSTALLED).

Magnetic compasses heading.

Fluid level and 2-15

FAA APPROVED

BHT-2121FR-FM-1 Altimeters -

2-7-B.

Set.

Vertical speed indicators Clocks -

Zero.

OPERATION NOTE

Set and running.

and navigation Communication equipment - Set and functioning. Position lights -

As required.

Anti-collision lights - As required. Pitot heater -

Cyclic -

PROLONGED GROUND

As required.

For prolonged ground operation, AFCS shall not be operated in ATTD mode.

2-8. TAKEOFF ENG RPM (N2) -

100%.

Fiction as desired. NOTE

NOTE Moderate friction shall be applied to each throttle to overcome follow-through coupling between twist grips. Throttles -

Full open, friction adjusted.

ENG RPM (N 2) -

No more than 15% torque above hover power shall be used accelerating to Takeoff Climbout Speed. Collective - Initiate takeoff from a hover height of 4 feet.

100% (both engines).

FORCE TRIM switch -

As desired.

COCKPIT VOICE RECORDER TEST switch (if installed)-- press and hold for

3 seconds. Verify meter indicates GOOD.

OBSER VE

VMINITS

IN

SECTION 1 FOR IFR OPERATION.

NOTE

Passenger STEP switch (if installed)As desired.

Passenger seat belts - Fastened.

All doors - Secured.

Caution and warning lights Extinguished. 2-7-A.

Takeoff must be executed in accordance with Height-Velocity limitations for type of operation

being conducted.

Refer to

Section 1.

Refer to Section 4 for additional climb performance data.

POWER ASSURANCE

CHECK

ATTD switch 40 KIAS.

Perform power assurance check daily. Referto Section 4.

ENGA as desired above

2-9. IN-FLIGHT OPERATIONS Maneuvering with AFCS on may be accomplished by one of following methods:

2-16

Rev. 2

BHT-2121FR-FM-1

FAA APPROVED

NOTE If ROLL trim wheel is used during

turn, helicopter may not return to level flight (in roll) when turn is terminated. Method 1:

necessary to maintain balanced flight. Use PITCHtrim as necessary to maintain desired attitude.

Method 2: Move cyclic to desired bank angle and pitch attitude. Apply pedal as necessary

Press TURN knob and select desired

angle of bank.

Apply pedal as

Rev. 2

2-16A/2-16B

FAA APPROVED

BHT-2121FR-FM-1

to maintain balanced flight during turning maneuver.

CAUTION

Method 3: Method 3:

CYCLIC CONTROLS MAY MOTOR

Press cyclic FORCE TRIM switch and

TO STOP IF AFCS IF LEFT

maneuver as desired. Release switch when maneuver is complete and with helicopter at level attitude.

ENGAGED AND UNMONITORED DURING GROUND OPERATIONS.

2-10. DESCENT AND 2-10 .LANDIN Flight controls -

desired.

Throttles -

Collective - Down. Cyclic control and frictioned.

Adjust friction as

FORCE TRIM switch -

Centered

ON.

Throttles - Idle. ITT -

Full open.

and pedals -

Stabilize for one minute at idle

prior to shut down.

ENG RPM (N2) - 100%.

Engine instruments - Within limits.

FORCETRIMswitch- As desired.

ELT (if installed)

Passenger STEP switch -

As desired.

Radios WARNING OBSERVE VMIN LIMITS IN SECTION 1 FOR IFR OPERATION.

-

Check for

inadvertent transmission. OFF.

IDLE STOP REL switch -

ENG 1.

Engine 1 throttle - Closed. Check ITT and GAS PROD RPM (N1 ) decreasing. BATTERY BUS 1 switch -

ON.

Flight path - Establish in accordance with Height-Velocity diagram. Single engine balked landings can be made

IDLE STOP REL switch - ENG 2.

from a landing decision point (LDP) of 100 feet altitude, 40 knots airspeed, and

Engine 2 throttle - Closed. Check ITT and GAS PROD RPM (N.) decreasing.

500 feet rate of descent. Anticipated single engine landings initiated from these conditions require reference to

GEN 1 and GEN 2 switches -

landing performance data in Section 4.

INV 1, INV 2, and INV 3 switches -

ATTD switch -

ENGINE 1 FUEL switch -

DSENGA as desired.

OFF.

OFF.

ENGINE 1 BOOST PUMP switch NOTE ATTD switch must be disengaged below 40 knots.

2-11.

ENGINE 2 FUEL switch -

OFF.

OFF.

OFF.

ENGINE 2 BOOST PUMP switch -

OFF.

ENGINE SHUTDOWN

AFCS power -

OFF. 2-17

BHT-2121FR-FM-1

FAA APPROVED

CAUTION OF AVOIDRAPIDENGAGEMENT ROTOR BRAKE IF HELICOPTER IS ON ICE OR OTHER SLIPPERY OR LOOSE SURFACE TO PREVENT ROTATION OF HELICOPTER.

Rotor brake -

Apply at or below 40%

ROTOR RPM (NR), return

to stowed

position after main rotor stops. Pilot -

Remain at flight controls until

rotor has come to a complete stop. Lighting and miscellaneous OFF.

BATTERYswitches -

2-18

OFF.

switches -

2-12. POSTFLIGHT CHECK Main rotor and tail rotor blades Tiedown when any of following conditions exist: Thunderstorms are forecast.

exist in local area or

Winds in excess of 20 knots or a gust spread of 15 knots exist or is forecast. Helicopter Is parked within 150 feet of

hovering or taxiing aircraft that are in excess of basic helicopter GW. Helicopter is to be left unattended. Protective

covers

(engine exhaust and

pitot tube) - Install.

FAA APPROVED

BHT-2121FR-FM-1

2121FR-FM-2-1

Figure 2-1.

Exterior check diagram

2-19/2-20

FAA APPROVED

BHT-2121FR-FM-1

Section 3 TABLE

OF CONTENTS

Subject

Paragraph

Page Number

INTRODUCTION .................................................

3-1 ...........

3-3

3-2........... 3-3...........

3-3 3-3

3-3-A ........ 3-3-B ........ 3-3-C ....... 3-3-D ........

3-3 3-4 3-5 3-6

3-3-E ........ 3-3-F......... 3-3-G ........ 3-3-H .......

3-7 3-8 3-9 3-9

FIRE .......................................................

3-4..........

3-9

ENGINE FIRE ............................................... CABIN SMOKE OR FUMES................................. BAGGAGE COMPARTMENT FIRE.......................... TAIL ROTOR..................................................... COMPLETE LOSS OF TAIL ROTOR THRUST ............. LOSS OF TAIL ROTOR THRUST AT HOVER .............. LOSS OF TAIL ROTOR THRUST IN CLIMB ................ LOSS OF TAIL ROTOR THRUST IN LEVEL FLIGHT OR DESCENT ................................................... LOSS OF TAIL ROTOR COMPONENTS .................... TAIL ROTOR FIXED PITCH FAILURES .................... FIXED PITCH FAILURE AT A HOVER...................... FIXED PITCH FAILURE IN FLIGHT......................... LOSS OF PITCH CHANGE CONTROL LINKAGE .......... HYDRAULIC SYSTEM ........................................... ELECTRICAL SYSTEM .......................................... DC POWER FAILURE....................................... AC FAILURE TO PRODUCE POWER...................... AC FAILURE SYSTEM NO.1 ............................... AC FAILURE SYSTEM NO. 2 .................................................... FUEL SYSTEM...................................... FUEL BOOST PUMP FAILURE ............................. FUEL FILTER PARTIALLY BLOCKED ...................... FUEL QUANTITY INDICATION MALFUNCTIONS ........ AUTOMATIC FLIGHT CONTROLS SYSTEM .................... AFCS WILL NOT ENGAGE ANY CHANNEL ...............

3-4-A ....... 3-4-B ...... .. 3-4-C ........ 3-5 .......... 3-5-A ....... 3-5-B ....... 3-5-C ........

DEFINITIONS.................................................... ENGINE.......................................................... SINGLE ENGINE FAILURE ................................. ENGINE RESTART IN FLIGHT ............................. DUAL ENGINE FAILURE ................................... ENGINE UNDERSPEED .................................... ENGINE OVERSPEED FUEL CONTROLGOVERNOR FAILURE .................................................... ENGINE OVERSPEED DRIVESHAFT FAILURE ........... ENGINE COMPRESSOR STALL ............................ ENGINE HOT START/SHUTDOWN .........................

3-9 3-10 3-10 3-11 3-11 3-11 3-11

3-5-D ....... 3-5-E ....... 3-5-F......... 3-5-G ....... 3-5-H ........ 3-5-J......... 3-6.......... 3-7 .......... 3-7-A ....... ..3-7-B .... 3-7-C ........

3-12 3-12 3-12 3-12 3-12 3-14 3-14 3-14 3-14 3-14 3-14

... 3-7-D........ 3-8...........33-8-A ........ 3-8-B ........ ...3-8-C ........ 3-9........... 3-9-A ........

3-14 3-15 3-15 3-15 3-15 3-15 3-15 Rev. 2

3-11

FAA APPROVED

BHT-2121FR-FM-1

TABLE OF CONTENTS (Cont) Subject AFCS WILL NOT ENGAGE YAW CHANNEL ONLY ....... FEEDBACK FELT IN CYCLIC DURING SCAS ONLY

FLIGHT...................................................... OSCILLATIONS IN AFCS ANY CHANNEL................. HYDRAULIC FAILURE SYSTEM NO. 1 .................... SYSTEM REENGAGE AFTER DISENGAGE ................ INOPERATIVE CHANNEL SCAS ........................... INOPERATIVE CHANNEL AFCS ........................... INOPERATIVE ATTITUDE GYRO COPILOT ............... INOPERATIVE HEADING GYRO COPILOT ................ HYDRAULIC FAILURE SYSTEM NO. 2 .................... AFCS RUNAWAY, HARDOVER, OR OTHER UNUSUAL CHARACTERISTIC .......................................... EMERGENCY EVASIVE MANEUVER ....................... COMMUNICATION SYSTEM ..................................... NAVIGATION RADIO FAILURE ............................. INTERCOM FAILURE ....................................... CABIN HEATER ................................................. LANDING GEAR ................................................. STATIC PORT OBSTRUCTION ..................................

Paragraph

Page Number

3-9-B ........

3-16

3-9-C ........

3-16

3-9-D ........ 3-9-E ........ 3-9-F......... 3-9-G ........ 3-9-H ........ 3-9-J......... 3-9-K ........ 3-9-L.........

3-16 3-16 3-16 3-16 3-16 3-16 3-17 3-17

3-9-M ........ 3-9-N ........ 3-10 ......... 3-10-A ....... 3-10-B ....... 3-11 ......... 3-12 ......... 3-13 .........

3-17 3-17 3-17 3-17 3-17 3-17 3-18 3-18

LIST OF FIGURES Figure Number

Page Number

Title

Table Number

Page Number

WARNING LIGHTS .............................................. CAUTION LIGHTS ...............................................

3-1 ........... 3-2...........

Title

LIST OF TABLES

3-2

Rev.2

3-19 3-21

FAA APPROVED

BHT-212IFR-FM-1

Section 3 EMERGENCY/MALFUNCTION PROCEDURES 3-1. INTRODUCTION Following procedures contain indications of equipment or system failure or malfunction, use of emergency features of primary and backup systems, and appropriate warnings, cautions, and explanatory notes. Table 3-1 lists fault conditions and corrective actions required for illumination of red warning lights. Table 3-2 addresses malfunction procedures associated with yellow caution lights. Corrective action procedures listed herein assume pilot gives first priority to helicopter control and a safe flight path. Helicopter should not be operated following any precautionary landing until cause of m a lfu n c tio n h a s b e e n d e te rm in e d a n d corrective maintenance action taken.

3-2. DEFINITIONS Following terms indicate degree of urgency in landing helicopter. LAND AS SOON AS POSSIBLE — Land without delay at nearest suitable area (i.e., open field) at which a safe approach and landing is reasonably assured. LAND AS SOON AS PRACTICAL — Duration of flight and landing site are at discretion of pilot. Extended flight beyond nearest approved landing area is not recommended. F o l low i n g t e r m s a re u s e d t o d e s c ri b e operating condition of a system, subsystem, assembly, or component:

AFFECTED — Fails to operate in intended or usual manner. NORMAL — Operates in intended or usual manner.

3-3. ENGINE 3-3-A. SINGLE ENGINE FAILURE ENG RPM (N2) of operating engine is allowed to droop to 97% during transition from twin engine operation to single engine operation. When best rate of climb airspeed (58 KIAS) is attained, ENG RPM (N2) should be increased to 100% if possible. Flight can be continued on remaining engine until a desirable landing site is available. There are certain combinations of GW, altitude, and ambient air temperatures that will result in OEI torque limit being exceeded. A run-on landing at 20 to 30 knots is recommended. Loss of an engine while hovering at high GW and extremely cold conditions is likely to result in exceeding OEI torque limit. If an overtorque is observed or suspected, an entry shall be made in log book. Refer to performance charts in Section 4.

NOTE Refer to ENGINE RESTART if an engine restart is to be attempted. INDICATIONS: ENG 1 OUT or ENG 2 OUT warning light illuminated.

02 DEC 2002

Rev. 4

3-3

BHT-212IFR-FM-1

FAA APPROVED

GAS PROD RPM (NI) below 61 ± 1% and decreasing. ENG RPM (N2) below 85% and decreasing.

ENGINE (1 or 2) FUEL switch — OFF. GEN (1 or 2) switch — OFF. MASTER CAUTION light — Reset.

ITT below 400 °C and decreasing. Land as soon as practical. ENG 1 or ENG 2 OIL PRESSURE, DC GENERATOR, and PART SEP OFF caution lights illuminated.

If no. 2 engine failed: INV 3 to DC BUS 1 (if installed).

PROCEDURES:

BATTERY BUS 2 switch — OFF. WARNING

BATTERY BUS 1 switch — ON. MASTER CAUTION light — Reset.

DO NOT ALLOW ROTOR RPM (NR) TO DECAY BELOW MINIMUM LIMITS.

Land as soon as practical.

3-3-B. ENGINE RESTART IN FLIGHT CAUTION DURING COLD WEATHER OPERATIONS, MONITOR TORQUE OF OPERATING ENGINE WHEN ONE ENGINE FAILS OR IS SHUT DOWN IN FLIGHT. Shut down affected engine as follows: Collective — Reduce as required to maintain ROTOR RPM (NR) within limits and power within OEI limits.

NOTE Airspeed — 55 to 65 KIAS for Minimum Power for level flight. RPM INCR DECR switch — INCR, set remaining ENG RPM (N2) at 100% if possible. Throttle — Closed.

Conditions which would warrant an attempt to restar t an engine would probably be a f la m e o u t , c a u s e d by a m a l f u n c ti o n o f automatic mode of fuel control unit. Decision to attempt an engine restart during flight is pilot responsibility. If an engine restart is to be made, proceed as follows:

CAUTION MONITOR ITT WHEN RESTARTING ENGINE IN MANUAL FUEL CONTROL MODE. ENGINE RESTART NO. 1 Engine 1 throttle — Closed. ENGINE 1 BOOST PUMP switch — ON. Fuel Crossfeed switch — Normal. ENGINE 1 FUEL switch — ON. ENGINE NO. 1 GOV switch — MANUAL.

Fuel Crossfeed switch — Override Close.

BATTERY BUS 2 switch — OFF.

Fuel Interconnect switch — OPEN.

BATTERY BUS 1 switch — ON.

ENGINE (1 or 2) BOOST PUMP switch — OFF.

INV 1 and 2 switches — ON.

Verify FUEL BOOST caution light and FUEL switch to be turned off are all for affected engine.

3-4

Rev. 4

02 DEC 2002

INV 3 switch (if equipped) — ON DC BUS 1.

BHT-2121FR-FM-1

FAA APPROVED START switch-ENG

1.

PROD RPM (N.) is attained. Adjust engine to desired power level. Care

After 12% GAS PROD RPM (N|) is attained and oil pressure is indicating, slowly open throttle until a rise is seen in ITT which indicates engine is self sustaining. Do not open throttle farther until GAS PROD RPM (N|) and ITT are stabilized. Continue to open

must be taken to make small with throttle as adjustments compressor stall may result. GEN 2 switch -

ON.

throttle slowly to complete start.

FAILURE 3-3-C. DUAL ENGINE

Center START switch after 55% GAS Adjust PROD RPM (N|) is attained.

INDICATIONS:

engine to desired power level. Care must be taken to make small

adjustments

with throttle

GEN 1 switch -

ON.

as

compressor stall may result.

ROTOR RPM audio on. OFF.

BATTERY BUS 2 switch -

ON.

GAS PROD RPM (N|) below 61 ± 1% and decreasing (both engines).

ENG RPM (N 2 ) below decreasing (both engines).

ENGINERESTART(NO. 2) Closed.

ENGINE 2 BOOST PUMP switch Fuel Crossfeed switch -

Normal

ENGINE2 FUEL switch -

ON.

ENGINE

lights illuminated.

RPM caution light illuminated.

BATTERY BUS 1 switch -

Engine 2 throttle -

ENG 1 OUT and ENG 2 OUT warning

NO. 2 GOV switch

ON.

85% and

ITT below 400 "C and decreasing (both engines). ENG 1 and ENG 2 OIL PRESSURE, DC

GENERATOR, and PART SEP OFF caution lights illuminated. -

PROCEDURES:

MANUAL. BATTERY BUS 1 switch -

OFF.

BATTERY BUS 2 switch -

ON.

INV 1 and 2 switches INV 3 switch

BUS2.

DO NOT ALLOW ROTOR RPM (NR) TO DECAY BELOW MINIMUM LIMITS.

ON.

(if installed)

WARNING

-

ON DC

Collective - Reduce, establish autorotative

START switch After

ENG 2.

glide. Minimum rate of

descent (65 KIAS) or maximum glide (90 KIAS).

12% GAS PROD RPM (N|) is

attained and oil pressure is indicating, slowly open throttle until a rise is seen in ITT which Indicates engine is self sustaining. Do not open throttle farther until GAS PROD RPM (N|) and ITT are stabilized. Continue to open

throttle slowly to complete start.

Center START switch after 55% GAS

Autorotative landing - Accomplish. If time permits before landing and a restart will not be attempted, proceed as follows: Throttles -

Closed. Rev. 2

3-5

FAA APPROVED

BHT-2121FR-FM-1 ENGINE 1 and ENGINE 2 FUEL switches - OFF.

audio if power demand is in excess of single engine power available).

ENGINE 1 and ENGINE 2 BOOST PUMP switches - OFF.

TORQUE split demand).

After landing:

Low GAS PROD RPM (N1), ITT, and TORQUE on affected engine.

Engine shutdown Helicopter 3-3-D.

Complete.

to power

(proportional

PROCEDURES:

Exit.

ENGINE UNDERSPEED NOTE

Normal deviations of ROTOR RPM

(NR) from the governed setting may occur when large collective changes are made but should not

be confused with fuel control

failure, unless a large steady-state TORQUEsplit occurs. If there is a low power demand (less than

single engine power available) at time of low side failure, ROTOR RPM (NR) and ENG

ROTOR RPM (NR) CAN DECAY EXCESSIVELY IF CORRECTIVE ACTION IS NOT IMMEDIATELY

Collective -

Adjust as necessary to

mantan ROTORRPM(NR). Airspeed - 55 to 65 KIAS for Minimum Power for level flight. Affected engine -

Identify. Tighten on normal

RPM (N2) of affected engine will decrease

Throttle friction -

(N1)of affected engine will also decrease.

Throttle (affected engine) -

and stabilize, at or slightly below governed value. TORQUE, ITT, and GAS PROD RPM As ROTOR RPM (NR) decreases,

normal

engine will increase TORQUE output to assume load. If power demand is near zero, there might not be a significant TORQUE split.

engine, reduce on affected engine.

Reduce to

idle.

GOV switch MANUAL.

If there is a high power demand (greater

(affected

engine)

CAUTION

than single engine power available) at time of low side failure, ROTOR RPM (NR) will decrease along with ENG RPM (N 2 ), TORQUE, ITT, and GAS PROD RPM (N1) of

WHEN OPERATING IN MANUAL FUEL CONTROL MODE, MAKE

affected engine. As ROTOR RPM (NR) decreases, normal engine will increase to

SLOW, SMOOTH THROTTLE MOVEMENTS TO AVOID

maximum power to assume load, causing significant increases in TORQUE, ITT, and GAS PROD RPM (N1) while ENG RPM (N2 ) will remain below governed value. INDICATIONS:

COMPRESSOR STALL, OVERTEMPERATURE, OVERSPEED, AND POSSIBLE DRIVETRAIN DAMAGE. COORDINATE

COLLECTIVE Low ENG RPM (N2 ) and ROTOR RPM (NR)

(possibly with RPM caution light and 3-6

Rev. 2

THROTTLE

CHANGES

AVOID OVERLOADING

ENGINE.

AND

TO

NORMAL

-

FAA APPROVED

BHT-2121FR-FM-1

Throttle (affected engine) - Increase slowly. Adjust throttle and collective as required to maintain TORQUEof affected

Definite TORQUE split (proportional to power demand).

engine slightly below TORQUE of normal

High

engine.

TORQUEon affected engine.

MASTER CAUTION light -

Reset.

Land as soon as practical.

3-3-E. ENGINE OVERSPEED - FUEL CONTROL/GOVERNOR FAILURE

Return

GAS PROD RPM (N),

ITT, and

of ENG RPM (N2 ) and ROTOR

RPM (NR) to governed value (if power demand is very high). PROCEDURES: CAUTION

NOTE

Normal deviations of ROTOR RPM (NR) from the governed setting may occur when large collective changes are made but should not

be confused with fuel control

failure, unless a large steady-state TORQUE split occurs,

ROTOR RPM ( N) CAN OVERSPEED EXCESSIVELY IF CORRECTIVE ACTION IS NOT IMMEDIATELY INITIATED.

Collective -

Adjust as necessary to

maintain ROTOR RPM (NR).

If there is a low power demand (less than

single engine power available) at time of high side failure, ROTOR RPM (NR) and ENG RPM (N2 ) of affected engine will increase considerably above governed value. TORQUE, ITT, and GAS PROD RPM

Affected enine

-

Identify

Throttle (affected engine) - Reduce to maintain TORQUE at or slightly below TORQUEof normal engine.

(No)of affected engine will also increase.

Throttle friction -

As ENG RPM (N2 ) and ROTOR RPM (NR)

engine, reduce on affected engine.

increase above governed value, normal engine will reduce power to keep itself

from overspeeding and will indicate

Tighten on normal

Throttle (affected engine) -

idle.

Reduce to

significantly lower TORQUE, ITT, and GAS PROD RPM (N|) than affected engine. If there is a high power demand (greater than single engine power available) at time. of high side failure, ROTOR RPM (NR) and ENG RPM (N2 ) of affected engine will surge initially along with TORQUE, ITT, and GAS PROD RPM (N,). As ENG RPM (N 2 ) and ROTOR RPM (NR) increase, normal engine

CAUTION ................. WHEN OPERATING IN MANUAL FUEL CONTROL MODE, MAKE

will reduce power to keep itself from overspeeding. Affected engine then tries to assume all of load, which is beyond its capability due to high power demand. ENG RPM (N2) of affected engine and

SLOW, SMOOTH THROTTLE TO AVOID MOVEMENTS COMPRESSOR STALL, OVERTEMPERATURE, OVERSPEED, AND POSSIBLE

ROTOR RPM (NR) will then decrease and

DRIVETRAIN DAMAGE.

rejoin ENG RPM (N,) of normal engine,

COORDINATE THROTTLE AND

stabilizing

at or slightly

above governed

value as normal engine adjusts power output to share load. INDICATIONS: High ENG RPM (N 2) and ROTOR RPM

(NR)possibly with RPM caution light.

AVOID OVERLOADING

NORMAL

Throttle (affected engine) slowly.

Increase

Adjust throttle and collective,

required, to maintain TORQUE of Rev. 2

as

3-7

FAA APPROVED

BHT-2121FR-FM-1

affected engine slightly below TORQUE of normal engine. MASTER CAUTION light-

Reset.

DRIVESHAFT

FAILURE

ARE

SOMEWHAT COMPARABLE TO A DUAL ENGINE FAILURE, IT IS T H A T I M P E R A T I V E

AUTOROTATIVE

FLIGHT

PROCEDURES BE ESTABLISHED

IMMEDIATELY.

NOTE If values of overspeed parameters

LIGHT,

CAUTION

are unknown, or if NR exceeds

AND

TACHOMETER WILL RESULT IN LOSS OF CONTROL.

110%, or If engine torque exceeds 104%, land as soon as possible.

Land as soon as practical. ENGINE OVERSPEED-

FAILURE TO

REACT IMMEDIATELY TO LOW ROTOR RPM (NR)AUDIO SIGNAL,

GOVERNOR

This is a situation involving a break in drive system, such as a severed main driveshaft to transmission. A failure of this

ACTUATOR FAILURE

type In powered flight will result in nose of

INDICATIONS:

and usually a roll of fuselage. attitude may also be present.

helicopter swinging to left (right side slip)

and ROTOR RPM (NR) ENG (N2) RPM increase to approximately 101%.

initial reaction will be affected by airspeed, HD, GW, CG,and power being used. INDICATIONS:

RPM INCR DECR switch inoperative.

Left yaw.

PROCEDURES: If this failure

Nose down Severity of

occurs

during takeoff

or

landing, no immediate corrective action to complete either is necessary

Rapid decrease in ROTOR RPM (NR).

Rapid increase in ENG RPM (N2).

maneuver. Illumination

As soon as practical, roll back both throttles to maintain 97 to 100% ENG RPM (N 2 ). Further adjustment of collective and throttles simultaneously will allow full power at pilot discretion.

Land as soon as practical. 3-3-F. ENGINE OVERSPEED DRIVESHAFT FAILURE

of ROTOR RPM (NR) caution

light with audio. Possible increase in noise due to: Overspeeding engine turbines. Overspeeding combining gearbox.

-

Driveshaft breakage. PROCEDURES:

Collective - As required to establish autorotative descent. FAILURE OF MAIN DRIVESHAFT TO TRANSMISSION WILL RESULT IN COMPLETE LOSS OF POWER ALTHOUGH TO MAIN ROTOR.

COCKPIT INDICATIONS FOR A 3-8

Rev. 2

Airspeed - Establish for minimum rate of descent (65 KIAS) or maximum glide (90 KIAS).

Throttles -

Close, if time permits.

BHT-212IFR-FM-1

FAA APPROVED

FIRE EXT switch — MAIN. If FIRE warning light remains illuminated for more than 10 seconds: FIRE EXT switch — RESERVE. ENG RPM (N2) (remaining engine) — Set at 100%.

If a landing site is not readily available, proceed as follows: FIRE PULL handle — In. GEN (1 or 2) switch — OFF.

If no. 2 engine was shut down:

Land as soon as possible. Engine shutdown — Complete. Helicopter — Exit.

INV 3 to DC BUS 1 (if installed). BATTERY BUS 2 switch — OFF. BATTERY BUS 1 switch — ON.

3-4-A-3. ENGINE FIRE IN FLIGHT INDICATIONS:

After landing: Engine shutdown — Complete. Helicopter — Exit.

FIRE 1 and/or FIRE 2 PULL handle illuminated. PROCEDURES:

3-4-B. CABIN SMOKE OR FUMES

Immediately initiate emergency descent, if possible.

INDICATIONS:

Shut down affected engine (1 or 2) as follows:

PROCEDURES:

FIRE PULL handle — Pull. FIRE EXT switch — Main. Throttle — Closed. Fuel Crossfeed switch — Override Close. Fuel Interconnect switch — OPEN. Engine BOOST PUMP — OFF. Verify FIRE handle light, FUEL BOOST caution light, and FUEL switch to be turned off are all for affected engine. ENGINE FUEL switch — OFF. If FIRE warning light remains illuminated for more than 10 seconds: FIRE EXT switch — RESERVE. ENG RPM (N2) (remaining engine) — Set at 100%. Land as soon as possible.

3-10

Rev. 4

02 DEC 2002

Smoke, toxic fumes, etc. in cabin. VENT BLOWER switch — ON. Vents and accessible windows — Open. If additional ventilation is required: Airspeed — Reduce to 60 KIAS or less. Passenger doors, windows, vents — Open. If time and altitude permit and source is suspected to be electrical: Affected system — Attempt to identify and isolate. Land as soon as possible.

3-4-C. BAGGAGE COMPARTMENT FIRE INDICATIONS: BAGGAGE FIRE warning light illuminated. PROCEDURES: Reduce power to minimum required.

FAA APPROVED

BHT-2121FR-FM-1

Land as soon as possible. Inspect tailboom area for damage.

due to higher power and antitorque settings. PROCEDURES:

3-5. TAIL ROTOR NOTE The key to successful

Close throttles and lower collective immediately. Establish a glide speed

slightly above normal autorotation approach speed. handling of

a tail rotor emergency lies In pilot ability to quickly recognize type of malfunction and to select proper

If a turn is required to reach a more desirable place to land or to align into wind, make it to right if possible. A turn

emergency procedure. Following is a discussion of some types of

to right can be more nearly streamlined by use of a little power.

tail rotor malfunctions and their probable effects. 3-5-A. COMPLETE LOSS OF TAIL ROTOR THRUST

INDICATION: This is a situation

Once aligned for landing, yaw can be controlled in following manner: * Right Yaw If nose yaws right with power off, a pulse of up collective will produce

more friction

in mast thrust

bearings, creating a left moment. involving

a break in

drive system, such as a severed driveshaft, wherein tail rotor stops turning and delivers no thrust. A failure of this type in powered flight will result in nose of helicopter swinging to right (left side slip) and usually a roll of fuselage. Nose down attitude may also be present. Severity of Initial reaction will be affected by airspeed, HD, GW, CG, and power being used.

3-5-B. LOSS OF TAIL ROTOR THRUST AT HOVER PROCEDURES:

The greater the input of pulse, the

more the response will be. WARNING

DO NOT ALLOW ROTOR RPM (NR) TO DECAY BELOW MINIMUM LIMITS.

Moving collective upward abruptly increases rotor loading. Do not hold collective up as rotor rpm will decrease lower than desirable. It is essential that collective be returned

Close throttles immediately and make a

to down position for autorotation. This cycle Is one pulse. Pulse

hovering autorotation landing. Yawing can be expected on touchdown.

should be rapid (up and down) but should not be used at low altitudes.

3-5-C. LOSS OF TAIL ROTOR THRUST IN CLIMB Degree of right yaw upon failure will be greater than that expected in level flight

· Left Yaw If nose yaws left with power off, a

slight addition

of power should

arrest it. Further increase in power results in more right yaw increase. *Landing 3-11

FAA APPROVED

BHT-2121FR-FM-1

technique

is same as

During final stages of approach, a

Landing

mild flare should be executed and all

prescribed for climb condition above.

power to rotor should be off. Maintain helicopter in a slight flare and use collective smoothly to execute a soft,

slightly nose high landing. Landing on aft portion of skids will tend to correct side drift. If helicopter starts

3-5-E. LOSS OF TAIL ROTOR

COMPONENTS

to turn, move cyclic as necessary to

Loss of any tail rotor component will result

landing.

complete loss of tail rotor thrust as

follow turn until helicopter comes to a complete stop. This technique will, in most cases, result in a run on type

Other than in a forward CG shift. additional nose down pitching, this situation would be quite similar to discussed above.

3-5-F. TAIL ROTOR FIXED PITCH FAILURES

CAUTION

FOR ZERO GROUND SPEED LANDING, FLARE AND ABRUPT USE OF COLLECTIVE MAY CAUSE

TO YAW LEFT. DO NOT NOSE NOSE TO YAW LEFT. DO NOT CORRECT WITH THROTTLE. APPLICATION ALTHROUGHWILL RESULT OF IN THROTTLE YAWING TO RIGHT, ADDITION OF POWER YAWING RESPONSE MEASURE AND IS SENSITIVE TOO FOR PILOT TOO SENSITIVE FOR PILOT TO DO NOT MANAGE PROPERLY.

ADD POWER AT THIS TIME. YAWING Z3-5-G. UPON SLIGHT

TOUCHDOWN AT ZERO GROUND SPEED MAY BE EXPECTED.

3-5-D. LOSS OF TAIL ROTOR THRUST IN LEVEL FLIGHT OR

DESCENT PROCEDURES:

Close throttles and reduce collective

INDICATIONS: Tail rotor pitch change control failures are

characterized either by a lack of directional response when a pedal is pushed or by locked pedals. If pedals can a moderate amount of force, do not attempt to apply a maximum effort since a more serious malfunction could result.

FIXED PITCH FAILURE AT A

HOVER PROCEDURES: Do not close throttles unless a severe If pedals lock in any right yaw occurs. position at a hover, landing from a hover can be accomplished with greater safety under power controlled flight rather than

by closing throttles and entering autorotation.

immediately. Attain an airspeed slightly above normal autorotative glide speed.

3-5-H. FIXED PITCH FAILURE IN If altitude permits with AIRSPEED above 60 KIAS, throttle and collective may be

gently applied to determine if some

degree of powered flight

can be

resumed. If unacceptable yawing Is experienced, re-enter autorotation and continue descent to a landing. 3-12

FLIGHT

If tail rotor fixed pitch failure occurs during climb (left pedal applied), cruise neutral pedals), and (approximately descent (right pedal applied), a descent

FAA APPROVED

BHT-2121FR-FM-1

and landing can be effected safely by use

of power and throttle changes.

Reduce power and maintain ENG RPM

(N2) within green arc. Normal turns can be safely made under these conditions, although helicopter nose

PROCEDURES:

may be displaced to left.

If helicopter is in a trimmed condition when malfunction is discovered, engine

On final approach,

power and airspeed should be noted and

deceleration so as to arrive at a point

helicopter flown to a suitable landing area. Combinations of ENG TORQUE, ROTOR RPM (NR), and AIRSPEED will correct

or

Pedal Locked

of

aggravate yaw attitude and these should be adjusted as required to control yaw during landing. Right Neutral

Forward

begin a slow

about four to five feet above intended

touchdown area as effective translational lift is lost.

Apply collective to stop rate of descent and forward speed, and to align helicopter with intended landing path. Allow helicopter to touch down

at near zero ground speed, maintaining alignment with throttle. Pedals Locked in Neutral

Power should be reduced and ENG RPM (N2 ) maintained within green arc.

Reduce power and maintain ENG RPM

turns.

conditions

This will help streamline helicopter in flight. Right turns are easier than left

AIRSPEED should

maintained at or above 60 KIAS.

be

Execute a normal to steep approach adjusting power as necessary to minimize or prevent right yaw. Maintain ENG RPM (N 2 ) and an AIRSPEED of 60 KIAS during initial part of approach. At 60 to 75 feet AGL and when landing area can be made, start a slow

deceleration

to arrive at intended

landing point with AIRSPEED at about

25 KIAS. At 2 to 5 feet AGL, slowly reduce throttle to overcome yaw effect and

allow helicopter to settle. When aligned with landing area, allow helicopter to touch down.

Execute a normal to shallow approach,

holding AIRSPEEDat 60 KIAS during initial part of approach. Adjust power as necessary to minimize or prevent right yaw.

At 50 to 75 feet AGL and when landing area can be made, start a deceleration to arrive at intended landing point with AIRSPEED at 25 KIAS. At 2 to 5 feet AGL, use throttle slowly

as necessary to maintain alignment with landing area and to control yaw; do not allow helicopter to settle until alignment is assured, then touch

down.

After ground contact, use collective

and throttle as necessary to minimize

After ground contact, use collective and throttle

(N2) within green arc. Normal turns can be safely made under these

as necessary to maintain

forward alignment.

speed and to maintain Move cyclic as necessary

alignment with landing strip, and to

to follow turn until helicopter has

minimize forward speed.

come to a complete stop.

If helicopter

starts to turn, move cyclic

as

necessary to follow turn until helicopter comes to a complete stop.

Left Pedal Locked Forward of Neutral 3-13

FAA APPROVED

BHT-2121FR-FM-1

3-5-J.

LOSS OF PITCH CHANGE

any inverter fails to produce power,

CONTROL

AC circuit breakers in.

check appropriate

CONTROLS LINKAGE

3-7-C.

INDICATIONS:

In this type of failure, pitch change mechanism is broken at some point and

AC FAILURE - SYSTEM

NO.1

tail rotor will assume a blade angle determined by aerodynamic and

NOTE

counterbalance forces.

No. 3 inverter will supply power to

PROCEDURES:

either bus If failure of no. 1 or no. 2 Inverter should occur (SN 30554 and sub.).

Corrective action procedures are in FIXED PITCH FAILURES

described

above. Specific procedure to be used

If no power available on no.1 bus, proceed

as follows:

depends on yaw change experienced. Pitch, roll, and yaw channel ARM switches

3-6. HYDRAULIC SYSTEM

OFF CAUTION

has two hydraulic powered

The helicopter

......

flight control systems (1 and 2). Both systems supply power to collective and cyclic

but tail rotor is powered

only

by

AC

C O P I LOT

system 1.

INSTRUMENTS

If system pressure or temperature exceeds limits, affected system should be turned

INSTRUMENTS INOPERATIVE.

off.

Continued flight

maneuvers

and normal

can be accomplished

on

remaining system. If system no. 1 fails and

is turned off, tail rotor control forces will increase but no change in limitations result.

3-7.

ELECTRICAL SYSTEM

NO. 2

is open, reset generator by moving generator

of no. 1 or no. 2 inverter

should occur. If no power is available proceed as follows:

operation,

AC - FAILURE TO PRODUCE POWER 3-14

Rev. 2

OFF.

PitchchannelARMswitch-OFF.

by

moving NON ESS BUS switch from NORMAL to MANUAL. Monitor to ensure loads are within limits. 3-7-B.

on no. 2 bus,

Roll channel ARM switch -

generator switch to RESET, then ON. busses may be restored

will

(if installed) supply power to either bus If

If either generator has not failed but circuit

nonessential

BE

NOTE No. 3 inverter

DC POWER FAILURE

For single

WILL

AC FAILURE - SYSTEM

failure

3-7-A.

NO. 1

PRESSURE

ENGINE 3-7-D.

PO W E R

AND

CAUTION .

PILOT

AC POWERED 2

AND INSTRUMENTS ENGINE PRESSURE

NO.

BHT-2121FR-FM-1

FAA APPROVED INSTRUMENTS

WILL

BE

INOPERATIVE.

3-8.

FUEL SYSTEM

3-8-C. FUEL QUANTITY INDICATION MALFUNCTIONS. INDICATIONS: Fuel quantity indication

freezes in place.

(Possible power failure to the fuel quantity 3-8-A. FUEL BOOST PUMP FAILURE

indicator.)

INDICATIONS:

FUEL QTY circuit breaker -

Recycle.

FUEL Interconnect switch--

OPEN.

PROCEDURE:

NO.1 or NO.2 FUEL BOOST Caution Light

illuminates.

NOTE

A failure In the fuel quantity

PROCEDURE:

indicating system will have no effect on fuel low caution light, fuel interconnect, fuel crossfeed,

fuel boost, or fuel valve operations and indications. IF EITHER FUEL BOOST PUMP

FAILS, FUEL EXHAUSTION

COULD OCCUR AT 60 POUNDS INDICATED ON FUEL QUANTITY GAGE. If practical, descend below 5000 feet H to in the prevent possible fuel starvation

event remaining boost pump fails. Fuel Interconnect

switch -

OPEN.

3-9.

AUTOMATIC

CONTROLS

FLIGHT

SYSTEM

3-9-A. AFCS WILL NOT ENGAGE -

ANY CHANNEL

FORCE TRM switch -

Channel ARM switches NOTE

heck on.

-

Check in

ATTD position.

If FUEL crossfeed switch is in NORM position, crossfeed valve opened will be automatically

SCAS ENGAGEswitch -

ON.

Copilot attitude gyro -

Wait until fully

allowing remaining pump to

erect.

supply supply fuel fuel to to both both engines. engines.

AFCS circuit breakers - Check in.

Land as soon as practical.

3-8-B. FUEL FILTER PARTIALLY BLOCKED. Land as soon as practical. Rev. 2

3-15

FAA APPROVED

BHT-2121FR-FM-1

3-9-B. AFCS WILL NOT ENGAGE YAW CHANNEL ONLY TURN trim knob -

Check in centered

position and not pressed.

Pedals -

again

AFCS HDG circuit breaker -

reset, do not attempt further

resetting. ON.

Check in.

gyro -

Check

Move

appropriate flight control and observe Do not that each light illuminates. attempt to engage a channel that did not illuminate when control was moved.

Individual channel NO GO lights -

Extinguished (do not attempt to engage channel if light is illuminated).

Individual channel ARM switches

NOTE

SCAS or ATTD

AFCS yaw channel will disengage

(operative channels) as desired.

switch (*/-) on copilot

SCAS ENGAGE switch -

if pilot uses manual slaving CONTROL panel.

after

Individual channel NO GO lights -

Check in

Yaw channel ARM switch ATTD position,

Copilot directional

attempting

has

If breaker

SCAS/AFCS power switch -

Centered.

operative.

Circuit breakers - In. and opens opened

COMPASS

ENGAGE.

If

any unusual control input occurs, disengage SCAS.

3-9-C. FEEDBACK FELT IN CYCLIC DURING SCAS ONLY FLIGHT

Insufficient cyclic friction applied. If unable to apply sufficient friction, correct malfunction prior to next flight.

ATTD ENGADE switch

- ENGAGE(if

ATTD ENGAGE switch - ENGAGE (if desired). If any unusual control input occurs, disengage AFCS.

3-9-G. INOPERATIVE CHANNEL SCAS

3-9-D. OSCILLATIONS IN AFCS ANY CHANNEL Disengage affected channel. malfunction

Disengage affected channel by turning appropriate channel ARM switch to OFF.

Correct

3-9-H. INOPERATIVE CHANNEL -

prior to next flight.

AFCS 3-9-E. HYDRAULIC FAILURE SYSTEM NO. 1

-

Disengage affected channel by turning appropriate channel ARM switch to OFF.

Disengage yaw channel by turning YAW select switch OFF.

3-9-F. SYSTEM REENGAGE AFTER DISENGAGE Inverters - Check for proper AC voltage

3-9-J. INOPERATIVE ATTITUDE GYRO - COPILOT Disengage ATTD pitch and roll channels.

NOTE

on bus no. 1. If unable to get voltage on

bus no. 1, channels will be inoperative.

SCAS will work normally on all channels unless gyro failure was caused by AC system failure.

3-16

FAA APPROVED

3-9-K.

BHT-2121FR-FM-1

INOPERATIVE HEADING

GYRO - COPILOT

3-10.

COMMUNICATION

SYSTEM

Disengage ATTD yaw channel.

3-10-A. NAVIGATION RADIO FAILURE

NOTE SCAS will work

normally

on all

channels unless gyro failure was

NAV AC switch -

BUS NO. 2.

caused by AC system failure.

3-10-B. 3-9-L. HYDRAULIC FAILURE SYSTEM NO. 2 Disengage pitch and roll channels by turning OFF.

PITCH and ROLL select switches

INTERCOM FAILURE

INDICATIONS: Weak or no reception in headsets. PROCEDURE: Check headset connection.

3-9-M. AFCS RUNAWAY, HARDOVER, OR HARDOVER, OR OTHER OTHER UNUSUAL UNUSUAL CHARACTERISTIC

set

erify volume and ICS controls properly. Cycle ICS circuit breaker out and in.

Helicopter attitude - Correct with cyclic

and pedals.

3-11. CABIN HEATER

AFCS release switch -

Press, check

AFCS control panel for SCAS ENGAGE

switch disengagement.

SCAS channel switches (3) - OFF.

NOTE A malfunction in the bleed air heater controls may or may not

cause heater to become NOTE Channels of SCAS and AFCS can

be reengaged, after resuming straight and level flight. 3-9-N. EMERGENCY EVASIVE MANEUVER Flight controls

-

HEATER AIR LINE illuminates.

caution

light

Heated airflow does not shut off when thermostat knob is turned to full cold position. PROCEDURES:

FORCE TRIM release switch - Press and hold until back to desired attitude to resume AFCS control. attitude.

INDICATIONS:

Use as needed to

maneuver helicopter.

AFCS trim panel -

inoperative

HEATERswitch -

OFF immediately.

CABIN HTR circuit breaker -

Check; if

out, do not reset. Use to attain desired

Check prior to next flight. 3-17

FAA APPROVED

BHT-2121FR-FM-1

3-12. LANDING GEAR

Windows and vents -

Not applicable for skid gear equipped

Heater

helicopters.

3-13. STATIC PORT OBSTRUCTION

Close.

installed) - OFF. STATIC SOURCEswitch (if installed)ALTN. NOTE

Erratic readings from airspeed indicator, vertical speed Indicator, and altimeter may occur when operating in rain with STATIC SOURCEswitch (if Installed) in PRI. If this occurs, proceed as follows:

3-18

Rev. 2

an selects This procedure alternate static source (cabin air) for pilot instruments only.

FAA APPROVED

BHT-2121FR-FM-1

Table 3-1. WARNING LIGHTS PANEL WORDING

FAULT CONDITION

CORRECTIVE

FIRE 1 PULL/ FIRE 2 PULL

F i r e i n compartment.

Pull FIRE PULL handle, position FIRE EXT switch to MAIN, close

e n g i n e

ACTION

throttle, position FIRE EXT switch to RESERVE, if necessary. Land as soon as possible. ENG 1 OUT/ENG OUT

2

Engine GAS PROD RPM (Ni) below 53 ± 2%.

Check engine torque, GAS PROD RPM (N|), ENG RPM (N 2 ), and ITT. Adjust power and airspeed. Reset remaining ENG RPM (N2 ) to 100% if

possible. Close throttle of affected engine. Refer to ENGINE FAILURE and ENGINE RESTART. Land as

soon as practical. BAGGAGE FIRE

Smoke

in

baggage

Reduce power to minimum required.

compartment.

Land as soon as possible. Inspect tailboom area for damage.

XMSNOIL PRESS

Transmission oil pressure Reduce power. below limit, possible.

Land as soon as

XMSN OIL TEMP

Transmission

Check XMSN OIL

oil

temperature above limit,

Reduce

power.

temperature.

If not within limits,

land as soon as possible. C BOX OIL PRESS

Combining

gearbox

oil

pressure below limit, C BOX OIL TEMP

Combining

Reduce

power.

Land as soon as

possible.

gearbox

oil

temperature above limit.

Reduce power.

temperature.

Check GEAR BOX

If not within limits,

land as soon as possible. BATTERY

installed)

TEMP (If

Battery

limit.

temperature

above

Position BATTERY switches to OFF.

Ensure BATTERY caution segment

illuminates.

Land as soon as

practical. If Battery segment does not Illuminate, turn GEN 2 OFF. Land as soon as possible.

Rev. 2

3-19

FAA APPROVED

BHT-2121FR-FM-1

Table 3-1. WARNING LIGHTS (Cont) PANEL WORDING

FAULT CONDITION

CORRECTIVE

ACTION

WARNING

BATTERY

SHALL

FOR ENGINE

NOT BE USED

START

AFTER

ILLUMINATION OF BATTERY TEMP

LIGHT. BATTERY SHALL BE REMOVED AND SERVICED

ACCORDANCE

IN

WITH

MANUFACTURER'S INSTRUCTIONS PRIOR TO RETURN TO SERVICE. ROTOR BRAKE

Rotor brake retracted.

linings

not

Check rotor brake handle in detent. If light remains illuminated, land as

soon as possible.

3-20

Rev. 2

BHT-2121FR-FM-1

FAA APPROVED

CAUTION LIGHTS

Table 3-2.

PANEL WORDING

FAULT CONDITION

CORRECTIVE

ACTION

ENG 1 OIL PRES- Engine oil pressure below

Shut down no. 1 engine. Position

SURE

limit.

INV 3 switch (if installed) to ON DC BUS 2.

ENG 2 OIL PRES- Engine oil pressure below

Shut down no. 2 engine. Position

limit.

INV 3 switch (if installed) to ON DC BUS 1 and BATTERY BUS 2 switch to OFF. Position BATTERY BUS 1

SURE

switch to ON. ENG

1 DC

GEN-

Position

Failure of DC generator.

ENG

2 DC

GEN 1 switch

to RESET

then ON. Position to OFF if reset not possible.

ERATOR GEN-

Position

Failure of DC generator.

GEN 2 switch

to RESET

then ON. Position to OFF if reset not possible. Position INV 3 switch

ERATOR

(if installed) to ON DC BUS 1 and BATTERY BUS 2 switch to OFF. Position BATTERY BUS 1 switch to ON. ENG 1 PART

SEP

Separator

OFF/ENG 2 PART closed. SEP OFF

ENG 1 FUEL BOOST/ ENG 2 FUEL BOOST

bypass

door

Ice and dust

circuit breakers in.

Position PART

SEP switch to OVRD ON.

system

protection

Check RPM WARN and PART SEP If PART

inoperative.

SEP OFF light remains illuminated, correct malfunction prior to next flight.

pump pressure Applicable is low or pump has failed.

If practical, descend to 5000 feet Hp or below for remainder of flight due

to possible fuel starvation of engine if remaining boost pump fails. If

either fuel boost pump fails,

crossfeed valve is opened by a pressure switch, allowing remaining pump to furnish pressure to both

engine fuel systems.

Above

sequence is possible with FUEL XFEED switch in NORM. If this automatic function is not desired, FUEL XFEED switch should be positioned to OVRD CLOSE and INTCON switch to OPEN. ENG 1 FUEL FILTER/

Filter

ENG 2 FUEL FILTER

partially clogged,

and/or

heater

is

Land as soon as practical. Correct

malfunction prior to next flight.

Rev. 2

3-21

FAA APPROVED

BHT-2121FR-FM-1

Table 3-2.

CAUTION LIGHTS (Cont)

PANEL WORDING

FAULT CONDITION

ENG 1 FUEL LOW/ Fuel remaining is approxENG 2 FUEL LOW

imately 140 pounds.

CORRECTIVE

ACTION

Fuel INTCON switch position

(closed)

in NORM

separates

two

lower fuel cells. When either FUEL INTCON LOW light illuminates,

switch should be positioned to

OPEN. This will allow fuel quantity in lower tanks to equalize. In event a fuel boost failure has occurred, or

occurs after INTCON switch is positioned to OPEN, fuel in lower

tanks will be available to both engines, through either boost pump. G O V 1 E N G MANUAL/ENG 2 GOV MANUAL

GOV switch in MANUAL.

ENG 1 CHIP/ENG 2 Metal particles in engine oil. CHIP

ENG 1 FUEL VALVE/ ENG 2 FUEL VALVE

Fuel valve not properly breaker seated or circuit

open.

ENG RPM, TORQUE, and ITT must manually by throttle be controlled and collective.

Reduce power and shut down engine as soon as practical to Land as

preclude engine damage. soon as practical.

Check FUEL VALVE circuit breakers in. Land as soon as practical. If on

ground, position FUEL switch to OFF then ON.

ENG 1 GEN OVHT/

Generator overheating.

CAUTION PANEL

GEN switch

Position

to

OFF.

Correct malfunction prior to next flight.

ENG 2 GEN OVHT Caution panel inoperative.

Check

MASTER

breaker in.

CAUTION

circuit

Monitor instruments.

Land as soon as practical. INVERTER #1

Failure of no. 1 inverter.

Check

no.

1 AC voltmeter

to

determine that no. 3 inverter (If

installed) has automatically assumed no. 1 inverter load.

EXTERNALPOWER

External power connected to helicopter or external

power door not closed properly.

DOOR LOCK

Rev. 2

powerdoor.

or Check doors closed and latched. Cabin aft door(s) baggage compartment door not locked.

3-22

Disconnect external power if still applied, close and latch external

_

FAA APPROVED

BHT-2121FR-FM-1

Table 3-2. CAUTION LIGHTS (Cont) PANEL WORDING

FAULT CONDITION

CORRECTIVE

BATTERY

Both battery switches` relays in same position.

Position both BATTERY switches to OFF. Position BATTERY switch to

ACTION

ON DC BUS 1.

If light

does not

extinguish, position switch to OFF, and position other switch to ON DC BUS 2. If light does not extinguish, position switch to OFF. CHIP C BOX

Metal particles in combining gearbox oil.

Reduce power. practical.

Land as soon as

CHIP XMSN

Metal particles mission oil.

in trans-

Reduce power. practical.

Land as soon as

CHIP 42/90 BOX

Metal

in inter-

Land as soon as practical.

particles

mediate and/or tail rotor gearbox.

HYDRAULIC

Hydraulic pressure low or Verify fault from gage readings. If temperature above limit. pressure is low or temperature Is high, turn affected system off. Land

INVERTER #2

Failure of no. 2 inverter.

as soon as practical. Check

no.

2 AC voltmeter

to

determine that no. 3 inverter (if

installed) has automatically assumed no. 2 inverter load. FUEL XFEED

Fuel crossfeed

valve

fully open or closed,

not

Check FUEL XFEED circuit

breakers

or in. Cycle FUEL XFEEDswitch.

FUEL XFEED circuit breaker open.

HEATERAIR LINE

Heater mixing malfunction.

INVERTER#3

Failure of no. 3 inverter.

RPM (with audio)

Rotor RPM at or below 95%.

valve

Turn heater off immediately. Position inverter switch to other DC BUS. If light stays illuminated, turn inverter no. 3 OFF. Adjust collective and/or RPM INCR DECR switch as required. Refer to

Engine Fuel Control Malfunction procedures. RPM (without audio)

Rotor RPM at or above

Adjust collective and/or RPM INCR

105%.

DECR switch as required.

Refer to

Engine Fuel Control Malfunction procedures.

Rev. 2

3-23

FAA APPROVED

BHT-2121FR-FM-1

Table 3-2. CAUTION LIGHTS (Cont) PANEL WORDING

FAULT CONDITION

FDR SYS FAIL(If installed)

data Flight inoperative.

3-24

Rev. 2

recorder

CORRECTIVE

ACTION

Refer to applicable regulations for operation with flight data recorder inoperative.

FAA APPROVED

BHT-2121FR-FM-1

Section 4 TABLE OF CONTENTS Subject

Paragraph

Page Number

INTRODUCTION.................................................

4-1...........

4-3

4-2........... 4-2-A ........ 4-2-B ....... 4-3........... 4-4........... 4-5........... 4-6 .......... 4-7.......... 4-7-A ....... 4-7-B ........ 4-7-C....... 4-7-D....... 4-8 ......... 4-9........... ......4-10 ........ 4-11 ......... 4-12 ........

4-3 4-3 4-3 4-3 4-4 4-4 4-4 4-4 4-4 4-4 4-4 4-4 4-4 4-5 4-5 4-5 4-5

Title

Figure Number

Page Number

Power assurance check chart - PT6T-3B ......................

4-1...........

4-7

4-2........... 4-3 .......... 4-4........... 4-5........... 4-6..........

4-9 4-10 4-11 4-14 4-22

4-7..........

4-23

4-8...........

4-24

4-9...........

4-25

4-10 4-11 4-12 4-13

........ ......... ......... .........

4-55 4-65 4-75 4-76

4-14 .........

4-77

POWER ASSURANCE CHECK .................................. POWER ASSURANCE CHECKS PT6T3B.................. POWER ASSURANCE CHECK PT6T3 ..................... DENSITY ALTITUDE ............................................. HEIGHT VELOCITY ENVELOPE ................................ HOVER CEILING ................................................ TAKEOFF DISTANCE ........................................... CLIMB AND DESCENT .......................................... TWIN ENGINE TAKEOFF CLIMBOUT SPEED.............. TWIN ENGINE RATE OF CLIMB............................ SINGLE ENGINE RATE OF CLIMB PT6T3B ............... SINGLE ENGINE RATE OF CLIMB PT6T3 ................ AIRSPEED CALIBRATION....................................... LANDING DISTANCE ............................................ NOISE LEVELS ............................................ SAMPLE PERFORMANCE PROBLEM........................... SOLUTION ....................................................... LIST OF FIGURES

Power assurance check chart - PT6T-3........................ Density altitude chart ........................................... Hover ceiling in ground effect ................................. Hover ceiling out of ground effect ................... .......... Critical relative wind azimuths for hover flight ................ Takeoff distance over a 50 foot (15.2 meter) obstacle .

Twin engine takeoff climbout speed ........................... Twin engine rate of climb ......................................

Single engine rate of climb - PT6T-3B......................... Single engine rate of climb - PT6T-3........................... Pilot airspeed system calibration .............................. Copilot airspeed system calibration ...........................

Single engine landing distance over a 50 foot (15.2 meter)

obstacle .........................................................

.......

4-1/4-2

FAA APPROVED

BHT-2121FR-FM-1

Section 4 4-1.

INTRODUCTION

Performance data presented herein are derived from engine manufacturer's specification power for engine less installation losses. These data are applicable to basic helicopter without any optional equipment that would appreciably affect lift, drag, or power available.

4-2-B. POWER ASSURANCE CHECK- PT6T-3 Power assurance check chart (figure 4-2) is provided to determine if engines can produce installed specification power. A power assurance check should be performed daily. Additional checks should be made if unusual operating conditions or

indications

4-2. POWER ASSURANCE CHECK

arise. Ground check is

performed prior to takeoff.

If either

4-2-A. POWER ASSURANCE CHECKS - PT6T-3B Power assurance check charts (figure 4-1) are provided to determine if engines can produce installed specification power.

engine

does not meet

requirements of ground power assurance check, published performance may not be achievable. Cause of engine power loss, or excessive ITT or GAS PROD RPM (N1) should be determined as soon as practical.

4-3.

DENSITY ALTITUDE

A power assurance check should be

A Density Altitude Chart (figure 4-3) is

be made if unusual operating conditions or indications arise. Hover check is

performance and limitations. Density altitude in an expression of the density of

performeddaily. Additionalchecksshould

performed prior to takeoff and in-flight check is provided for periodic in-flight

monitoring of engine performance. Either power assurance check may be selected at

discretion of pilot. It is pilot responsibility to accomplish procedure safely, considering passenger load, terrain being overflown, and qualifications of persons on board to assist in watching for other air traffic and to record power check data.

If If either either requirements

engine engine does does not not meet meet of hover or in-flight

power

assurance check, published performance may not be achievable. Cause of engine power loss, or excessive ITT or GAS PROD RPM (N1) should be determined as soon as

provided

to aid in calculation

of

the air in terms of height above sea level; hence, the less dense the air, the higher

the density conditions

altitude.

of temperature

For standard

and pressure,

density altitude is the same as pressure altitude. As temperature increases above standard for any altitude, the density altitude will also increase to values higher than pressure altitude. The chart expresses density altitude as a function of

pressurealtitudeand temperature. The chart also includes the inverse of the

square root of the density ratio (1/a),

practical.

4-3

FAA APPROVED

BHT-2121FR-FM-1

which is used to calculate KTAS by the relation: KTAS = KCAS x 1/No

4-7.

CLIMB

AND DESCENT

4-7-A. TWINENGINETAKEOFF

EXAMPLE If ambient temperature

is -15 °C and the

CLIMBOUT SPEED

pressure altitude is 6000 feet, find the density altitude, 1/No, and true airspeed for

Twin engine takeoff climbout speed (VTocs) is that indicated airspeed which will allow

100 KCAS.

takeoff distance over a 50 foot (15.2 meter)

obstacle to be realized and will comply with HV restrictions to allow a safe landing in case of an engine failure (figure 4-8.)

SOLUTION Enter the bottom of the chart at -15 °C. Move vertically to the 6000 foot pressure altitude line.

4-7-B. TWIN ENGINE RATE OF CLIMB

From this point, move horizontally to the

Twin engine rate of climb charts are

and move horizontally to the right and

continuous power for GW ranging from

left and read a density altitude of 4000 feet

provided for takeoff power and maximum

read 1/No = 100 x 1.06 = 106 KTAS.

7000 to 11,200 pounds (figure 4-9).

4-4.

HEIGHT

ENVELOPE

- VELOCITY

ENVELOPE

4-7-C. SINGLE ENGINE RATE OF CLIMB - PT6T-3B Single engine rate of climb charts are

Refer to SECTION 1.

provided for 21/2 minute OEI power and 30

4-5. HOVER CEILING

7000 to 11,200 pounds (figure 4-10).

IGE and OGE hover ceiling charts (figure

4-7-D. SINGLE ENGINE RATE OF CLIMB- PT6T-3

conditions of Hp and OAT.

Single engine minute power power for GW pounds (figure

4-4, and figure 4-5) present hover performance as allowable GW for

minute OEI power for GW ranging from

Published IGE hover performance can be achieved with adequate tail rotor control

rate of climb charts for 30 and maximum continuous ranging from 7000 to 11,200 4-11)

margins in relative winds up to 20 knots from any direction. More favorable tail

4-8

winds are outside critical relative wind

CALIBRATION

rotor control margins will be realized when 4-8. azimuth area (figure 4-6).

Downwind takeoffs and landings are not recommended.

4-6.

TAKEOFF DISTANCE

Takeoff distance required to clear a 50 foot (15.2 meter) obstacle is presented in figure 4-7 as a function of OAT, Hp, and GW. 4-4

AIRSPEED

Indicated airspeed (IAS) corrected for position and instrument error equals calibrated airspeed (CAS). Determine corrected airspeed from figures 4-12 and 4-13.

FAA APPROVED

4-9.

LANDING

BHT-2121FR-FM-1

Single engine landing

distance

takeoff GW at airport over a 50

foot (15.2 meter) obstacle is shown in figure 4-14 as a function GW.

of OAT, Hp, and

4-10. NOISE LEVELS 4-11. SAMPLE PERFORMANCE PROBLEM Helicopter is chartered to transport cargo from airport A (elevation 3000 feet, temperature 30 °C) to airport B (elevation 8500 feet, temperature 19 °C). Duration of flight will be 30 minutes and a 30 minute

fuel reserve at cruise power Is required. Average fuel consumption

11,000 pounds

Maximum allowable

DISTANCE

A (5676 feet HD)

Maximum allowable

9250 pounds

landing GW at airport B (10,861 feet HD) Estimated fuel burnoff during flight (30 minutes at 545 pounds per hour)

272 pounds

If pilot takes off at 11,000 pounds, he will arrive at destination 10,728 pounds (11,000

- 272 pounds). This exceeds maximum allowable landing weight by 1478 pounds (10,728 pounds - 9250 pounds); therefore, maximum allowable payload must be based on allowable landing weight for this

particular flight.

is determined

from helicopter historical records to be 545 pounds per hour at 8000 feet Hp, 20 °C OAT, and cruise power (approximately 55% torque). Crew consists of one 190 pound pilot. Determine maximum allowable cargo

payload for flight.

Maximum allowable

9250 pounds

landing GW GW at landing: Empty weight Oil

6482 pounds (5942 pounds) (22 pounds)

Pilot

(190 pounds)

Fuel (600 - 272)

4-12. 4-12.

SOLUTION SOLUTION

(328 pounds)

2768 pounds

allowable Maximum cargo payload cargo payload

Fuel required for 30 minute flight plus 30

minute reserve is 545 pounds. Considering fuel needed for start, runup, taxi, and takeoff, pilot elects to refuel to

Although it is permissible to take off from airport A at 11,000 pounds GW upon landing at airport B helicopter would have

600 pounds.

exceeded allowable

According to Weight-altitude-temperature

pounds due to higher HDat

limitations for takeoff, landing, and in

landing

GW by 1478

destination.

ground effect maneuvers chart (Section 1),

maximum allowable GW for existing ambient conditions

are as follows:

4-5/4-6

FAA APPROVED

BHT-2121FR-FM-1

PT6T-3B POWERASSURANCE CHECK(HOVER) (WITHGASPRODUCERGAGEP/N212-075-037-101) HEATER/ECU - OFF. THROTTLES: TEST ENGINE - FULL OPEN, FRICTIONED. OTHER ENGINE - IDLE. ENG RPM (N2) - 97%. COLLECTIVE - INCREASE UNTIL LIGHT ON SKIDS OR HOVERING. DO NOT EXCEED 810 ° ITT OR 100.8% GAS PROD (N1) RPM.

STABILIZE POWER ONE MINUTE. THEN RECORD Hp, OAT, ENGINE TORQUE, ITT, AND GAS PROD (N1) RPM.

IF INDICATED ITT OR GAS PROD (N1) RPM EXCEEDS MAXIMUM ALLOWABLE, REPEAT CHECK, STABILIZING POWERFOUR MINUTES.

ENTER CHART AT INDICATED ENGINE TORQUE, MOVE UP TO INTERSECT Hp, PROCEED TO RIGHT TO INTERSECT OAT, THEN MOVE UP TO READ VALUES FOR MAXIMUM ALLOWABLE ITT AND GAS PROD (N1) RPM.

REPEATCHECK USING OTHER ENGINE.

MAXIMUM ALLOWABLE ITT - °C

500

550

600

650

700

IF EITHER ENGINE EXCEEDS ALLOWABLE ITT OR GAS PROD (N1) RPM AFTER STABILIZING FOUR MINUTES, PUBLISHED PERFORMANCE MAY NOT BE ACHIEVABLE. CAUSE SHOULD BE DETERMINED AND CORRECTED AS SOON AS PRACTICAL.

MAXIMUM ALLOWABLE GAS PROD (N 1) RPM -

750

800

85

90

95

PERCENT

100

105

OPENS-

40 50 60 70 80 ENGINE TORQUE - PERCENT (INDICATED)

MAXIMUM FOR

TA

KEOFF -MAXIMUM

CONTINUOUS

2121FR-FM-4-1-1-1

Figure 4-1.

Power assurance check chart - PT6T-3B (Sheet 1 of 4)

Rev.1

4-7

FAA APPROVED

BHT-2121FR-FM-1

PT6T-3B POWERASSURANCE CHECK(IN-FLIGHT) GAGEP/N 212-075-037-101) (WITHGAS PRODUCER ENGRPM(N2)- 97%.

LEVELFLIGHTABOVE1000FEET ESTABLISH AGL.

STABILIZEPOWERONE MINUTEIN LEVELFLIGHT, THENRECORDHp,OAT,ENGINETORQUE,ITT,AND GASPROD(N1) RPM.

AIRSPEED- 100 KIAS(OR VNE,IF LESS). HEATER/ECU-- OFF. THROTTLES: TESTENGINE- FULLOPEN,FRICTIONED. OTHER ENGINE - DECREASESLOWLY UNTIL TEST ENGINE TORQUE IS WITHIN TEST RANGE. DO NOT EXCEED810°C ITTOR 100.8%GASPROD(N1) RPM.

ENTER CHART AT INDICATEDENGINE TORQUE, PROCEEDTORIGHTTO MOVEUPTOINTERSECTHp INTERSECT OAT,THENMOVEUPTO READVALUES FORMAXIMUMALLOWABLE ITTANDGASPROD(N1) RPM.

MAXIMUM ALLOWABLE ITT -

500

550

600

650

REPEATCHECKUSINGOTHERENGINE. IF EITHERENGINEEXCEEDSALLOWABLEITTORGAS PROD(N1) RPMAFTERSTABILIZINGFOURMINUTES, PUBLISHED PERFORMANCE MAYNOTBEACHIEVABLE. CAUSESHOULDBE DETERMINED ANDCORRECTED AS SOONAS PRACTICAL.

MAXIMUM ALLOWABLE GAS PROD (N 1) RPM - PERCENT

°C

700

IF INDICATED ITTOR GASPROD(N1) RPMEXCEEDS MAXIMUMALLOWABLE, REPEATCHECK,STABILIZING POWERFOURMINUTES.

750

800

85

90

95

105

100

BLEED VALVE

OPENS BLEED

'

40 50 ENGINE TORQUE -

60

70

80

MAXIMUMh FOR TAKEOFF

MAXIMUMCONTINUOU

PERCENT (INDICATED)

Figure 4-1.

4-8 4-8

Rev.1 Rev.

Power assurance check chart - PT6T-3B (Sheet 2 of 4)

FAA APPROVED

BHT-2121FR-FM-1

PT6T-3B POWERASSURANCECHECK(HOVER) (WITHGASPRODUCERGAGEP/N 212-075-037-113) HEATER/ECU - OFF. THROTTLES: TEST ENGINE - FULL OPEN, FRICTIONED. OTHER ENGINE - IDLE. ENG RPM (N2)-

97%.

COLLECTIVE - INCREASE UNTIL LIGHT ON ° SKIDS OR HOVERING. DO NOT EXCEED 810 ITT OR 101.8% GAS PROD (N1) RPM.

STABILIZE POWER ONE MINUTE, THEN RECORD Hp, OAT, ENGINE TORQUE, ITT, AND GAS PROD (N1) RPM.

IF INDICATED ITT OR GAS PROD (N1) RPM EXCEEDS MAXIMUM ALLOWABLE, REPEAT CHECK, STABILIZING POWER FOUR MINUTES.

ENTERCHART AT INDICATED ENGINE TORQUE, MOVE UP TO INTERSECT Hp, PROCEED TO RIGHT TO INTERSECT OAT, THEN MOVE UP TO READ VALUES FOR MAXIMUM ALLOWABLE ITT AND GAS PROD (N1)RPM.

REPEATCHECK USING OTHER ENGINE.

MAXIMUM ALLOWABLE ITT - °C

500

550

600

650

700

IF EITHER ENGINE EXCEEDS ALLOWABLE ITT OR GAS PROD (N1) RPM AFTER STABILIZING FOUR MINUTES, PUBLISHED PERFORMANCE MAY NOT BE ACHIEVABLE. CAUSE SHOULD BE DETERMINED AND CORRECTED AS SOON AS PRACTICAL.

MAXIMUM ALLOWABLE GAS PROD (N1) RPM - PERCENT

750

800

86

91

96

101

106

BLEED VALVE BLEED

VALVE

40

50

ENGINE TORQUE -

60

70

80

MAXIMUMFORTAKEOFFMAXIMUM

CONTINUOUS

PERCENT (INDICATED) 2121FR-FM-4-1-1-3

Figure 4-1.

Power assurance check chart - PT6T-3B (Sheet 3 of 4)

Rev. 1

4-8A

BHT-2121FR-FM-1

FAA APPROVED

PT6T-3B POWERASSURANCECHECK(IN-FUGHT) (WITHGASPRODUCERGAGEP/N212-075-037-113) ESTABLISHLEVELFLIGHTABOVE1000FEET AGL.

ENGRPM(N2)- 97%.

AIRSPEED- 100KIAS(OR VNE,IF LESS). - OFF. HEATER/ECU

STABILIZEPOWERONE MINUTE IN LEVELFLIGHT, THENRECORDHP,OAT,ENGINETORQUE,ITT,AND GASPROD(N1) RPM.

THROTTLES: TESTENGINE- FULLOPEN,FRICTIONED. OTHER ENGINE - DECREASESLOWLYUNTIL TEST ENGINE TORQUE IS WITHIN TEST RANGE. DO NOT EXCEED810°C ITTOR 101.8%GASPROD(N1) RPM.

ENTER.CHART AT INDICATEDENGINE TORQUE, MOVEUPTOINTERSECT HP,PROCEEDTO RIGHTTO INTERSECT OAT,THENMOVEUP TO READVALUES FORMAXIMUMALLOWABLEITTANDGASPROD(N1) RPM.

550

600

650

700

REPEATCHECKUSINGOTHERENGINE. IF EITHERENGINEEXCEEDSALLOWABLEITT OR GAS PROD (N1) RPM AFTER STABILIZINGFOUR MINUTES, PUBLISHEDPERFORMANCE MAYNOTBE ACHIEVABLE. CAUSESHOULDBE DETERMINED AND CORRECTED AS SOONAS PRACTICAL.

MAXIMUM ALLOWABLE GAS PROD (N1) RPM - PERCENT

MAXIMUM ALLOWABLE ITT - °C

500

IF INDICATED ITTOR GASPROD(N1) RPMEXCEEDS MAXIMUMALLOWABLE,REPEATCHECK,STABILIZING POWERFOURMINUTES.

750

800

86

91

96

106

101

BLEED VALVE OPENS VALVE

ENGINE TORQUE -PERCENT

(INDICATED) 2121FR-FM-4-1-1-4

Figure 4-1. Power assurance check chart - PT6T-3B (Sheet 4 of 4)

4-8B

Rev. 1

BHT-2121FR-FM-1

FAA APPROVED POWERASSURANCECHECK(GROUND) PT6T-3 CHART A

Hp

-500 -1000 -1500

% TORQUE 50.5 Hp % TORQUE 495

8. 9. 10. 11.

52.5

500

1000

1500 2000

2500

3000 3500 4000

48.5

480

470

46.0

45.0

44.0

8000 8500

9000

9500 10,000

10,500

36.0

35.0

34.5

34.0

33.0

6000 6500

HP

% TORQUE 39.5

1. 2. 3. 4. 5. 6. 7.

51.5

38.5

7000 7500 38.0

37.5

36.5

43.5

4500

5000

5500

420

41.0

40.5

42.5

11,000 32.5

EXAMPLE 29.92 IN HG ALTIMETER ............................................. 1500 FT ........................ ........... OBSERVEDHp .......... 47.0% OBSERVEDCHART A TORQUE.................................... STARTBOTHENGINES TURN HEATEROFF ON GROUND,ENGINENO. 2 TO IDLE STABILIZENO. 1 ENGINE,4 MINUTESMINIMUM, AT 97% (N2) ENG RPMAND CHART A TORQUEAND OBSERVE 95.2% RPM GAS PROD(N1) 710C ITT 20°C OAT OBSERVEDGAS PROD(N 1) RPMAND ITT MUST BELESSTHAN CHART GAS PROD(N1) RPM AND ITT FOROBSERVEDOAT. REPEATCHECKON NO. 2 ENGINEWITH NO. 1 ENGINEAT IDLE. If OBSERVEDGAS PROD (N1) RPM AND/OR ITT ARE GREATERTHAN CHART B GAS PROD (N1) RPMAND/OR ITT FOROBSERVEDOAT. HOVERIGEAND CHECKNO. 1 AND NO. 2 ENGINETORQUENEEDLESPLITNO GREATER THAN 4%. CHART B

52 OAT- °C GASPROD RPM 100

50 100

45 99.8

40 99.1

35 98.4

30 97.7

25 97.0

20 96.3

15 95.6

10 94.8

5 94.1

0 93.4

°C

810

810

805

795

780

765

750

735

720

705

690

675

°C

-5

-10

-15

-20

-25

-30

-35

-40

-45

-50

-54

92.0

91.3

90.6

89.9

89.2

88.5

87.8

87.1

86.4

85.8

645

630

615

605

590

575

560

545

530

520

ITT OAT -

GAS PROD

(N1)-

ITT -

RPM 92.7 °C

660

2 212IFR-FM-4

Figure 4-2.

Power assurance check chart - PT6T-3

4-9

361.78_

FAA APPROVED

BHT-2121FR-FM-1

1.80

(11.0)

1.78 EXAMPLE: IF AMBIENT TEMP IS 15 C AND PRESSUREALT IS 6,000 FEET. THE 1.76 DENSITY ALT IS 4,000 FEETAND IS 1.06

34 (10.0)

(9.0)

1.74

32

-1.72 -1.68

30

-- 1.64

70 162 1 58

1.54

8 (7.0)

-

1.44

1.38 -

1.34

_1.30 1.30 1.28

1

(4.0)

(1.0)

(0.5)

-

-

1.02

FAA APPROVED

BHT-2121FR-FM-1 HOVER CEILING INGROUNDEFFECT SKIDHEIGHT4 FT HEATER ONOROFF KITHTRONOROFF WINTERIZATION

POWER: SEENOTEBELOW ENGRPM100% IN2) GENERATOR 150 AMPSEACH 0 TO 52°C 14,000 FT HD LIMIT-

NOTE:THESEIGE HOVERCEIUNGS ARE

ON

BASED

DENSITY

LIMITS FOR ALTITUDE TAKEOFF AND LANDING. THIS HELICOPTER CAN BE

HOVERED IGE AT THE INDICATEDGROSSWEIGHTS WITH LESS THAN TAKEOFF POWER.

HOT DAY LIMIT

MAXIMUM GW LIMIT

- MAXIMUM OATHEATERON (211C)

11,200 (5080) 0

10 20 30 40 50

8000 (3629)

9000 10,000 11,000 12,000 (4082) (4536) (4989) 5443) GW - LB (KG) 2121FR-FM-4-4-1

Figure 4-4.

Hover ceiling in ground effect (Sheet 1 of 3)

4-11

FAA APPROVED

BHT-2121FR-FM-1 HOVER CEILING IN GROUNDEFFECT

SKIDHEIGHT4 FT HEATER ONOROFF WINTERIZATION KIT HTRONOROFF

POWER: SEENOTEBELOW ENGRPM100% (N2) GENERATOR 150 AMPSEACH 0 ° TO -54°C 14,000 FT HD LIMIT

NOTE:THESEIGE HOVERCEIUNGS ARE BASED ON DENSITY ALTITUDE LIMITS FOR TAKEOFF AND LANDING. THIS HELICOPTERCAN BE HOVERED IGE AT THE INDICATEDGROSSWEIGHTS WITH LESS THAN TAKEOFF POWER.

MAXIMUM GW LIMIT-

11.200

-60-50-40-30-20-10 OAT-°C OAT -- °C

Figure 4-4.

4-12

0

10,00011.000 12,000

8000

9000

(3629) 1

(4082) (4536) (4989) (5443) GW -GW--LB(KG) LB(KG) 2121FR-FM-4-4-2

Hover ceiling in ground effect (Sheet 2 of 3)

FAA APPROVED

BHT-2121FR-FM-1 HOVER CEILING IN GROUND EFFECT

MAXIMUM CONTINUOUS POWER ENGRPM100% (N2) GENERATOR 150 AMPSEACH 0 ° TO 52° C

SKIDHEIGHT4 FT HEATER ONOROFF WINTERIZATION KIT HTRONOROFF

14,000 FTH D LIMIT

MAXIMUM GW LIMIT

HOT DAY LIMIT--

(5080} 0

10 20 30 40 50 OAT - °C

8000 (3629)

9000 10,000 11,000 12,000 (4082) 14536) (4989) (5443) GW - LB (KG)

2121FR-FM-4-4-3

Figure 4-4.

Hover ceiling in ground effect (Sheet 3 of 3)

4-13

FAA APPROVED

BHT-2121FR-FM-1

HOVER CEILING OUTOFGROUNDEFFECT SKIDHEIGHT60 FT OFF HEATER 0° TO52°C

TAKEOFFPOWER ENGRPM100% (N2) 150 AMPSEACH GENERATOR

14,000 FT HD LIMIT

30°C

HOT DAY

(5080) 10 20 30 40 50

8000

9000 10,000 11,000 12,000 GW - LB (KG) 2121FR-FM-4-5-1

Figure 4-5.

4-14

Hover ceiling out of ground effect (Sheet 1 of 8)

FAA APPROVED

BHT-212IFR-FM-1 HOVER CEILING OUT OF GROUND EFFECT SKID HEIGHT 60 FT HEATEROFF

TAKEOFF POWER ENG RPM 100% (N2)

0 ° TO-54°C

GENERATOR 150 AMPSEACH 14,000 FT HD LIMIT MAXIMUM GW LIMIT OAT -40 TO

(5080) -60-50-40-30-20-10 OAT- °C

0 8000 9000 10,000 11,000 12,000 (3629) (4082) (4536) (4989) (5443) GW - LB (KG) 2121FR-FM-4-5-2

Figure 4-5. Hover ceiling out of ground effect (Sheet 2 of 8)

4-15 4-15

FAA APPROVED

BHT-2121FR-FM-1 HOVER CEILING EFFECT OUTOFGROUND

SKIDHEIGHT60 FT ON HEATER ° 0 TO20°C

TAKEOFFPOWER ENGRPM100% (N2) 150 AMPSEACH GENERATOR 14,000 FT HD LIMIT14,000FT

OAT- °C

M A XIMUM GW LIMIT

(3629) (4082) (4536) (4989) (5443) GW - LB (KG) 2121FR-FM-4-5-3

Figure 4-5. Hover ceiling out of ground effect (Sheet 3 of 8)

4-16 4-16

FAA APPROVED

BHT-2121FR-FM-1 HOVER CEILING OUTOFGROUND EFFECT

TAKEOFFPOWER ENGRPM100% (N2) GENERATOR 150 AMPSEACH

SKIDHEIGHT60 FT HEATER ON 0 ° TO-54°C

14,000 FT HD LIMIT MAXIMUM GW LIMIT

-50'C

OAT -

C

(3629) (4082)

(4536) (4989)

GW - LB (KG)

Figure 4-5.

(5443) 2121FR-FM-4-5-4

Hover ceiling out of ground effect (Sheet 4 of 8)

4-17

FAA APPROVED

BHT-2121FR-FM-1 HOVER CEILING OUTOFGROUNDEFFECT

SKIDHEIGHT60 FT HEATER OFF ° 0 TO 52°C

POWER MAXIMUMCONTINUOUS ENGRPM100% (N2) 150 AMPSEACH GENERATOR 14,000 FT HD LIMIT

OAT

0 20 C

30C

HOT

0

4.18

4-18

10 20 30 40 50 OAT - 'C

Figure 4-5.

9000 10.000 11.000 12.000 8000 (3629) (4082) (4536) (4989) (5443) 2121FR-FM-4-5-5 GW - LB(KG)

Hover ceiling out of ground effect (Sheet 5 of 8)

BHT-2121FR-FM-1

FAA APPROVED

HOVER CEILING OUTOFGROUNDEFFECT SKIDHEIGHT60 FT OFF HEATER 0° TO -54°C

POWER MAXIMUMCONTINUOUS ENGRPM100% (N2) 150 AMPSEACH GENERATOR 14,000 FT HD LIMIT

-10°

0 -20 TO -40 C

_MAXIMUM GW

-20-10 -60-50-40-30 OAT- °C

0 8000 9000 10,000 11,000 12,000 (3629) (4082) (4536) (4989) (5443) GW - LB (KG)

Figure 4-5.

2121FR-FM4-5-6

Hover ceiling out of ground effect (Sheet 6 of 8)

4-19

BHT-2121FR-FM-1

FAA APPROVED HOVER CEILING OUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWER ENG RPM 100% (N2)

SKID HEIGHT 60 FT HEATERON

0 ° TO20°C

GENERATOR 150 AMPS EACH 14,000 FT HD LIMIT

0 10 20 30 40 50 OAT - °C

8000 (3629)

9000 10,000 11.000 12,000 (4082) (4536) (4989) (5443) GW - LB (KG)

Figure 4-5.

4-20

2121FR-FM-4-5-7

Hover ceiling out of ground effect (Sheet 7 of 8)

FAA APPROVED

BHT-2121FR-FM-1 HOVER CEILING OUTOFGROUNDEFFECT

MAXIMUMCONTINUOUS POWER ENGRPM100% (N2) GENERATOR 150 AMPSEACH

SKIDHEIGHT60 FT HEATER ON 0° TO-54°C

14,000 FT HD LIMIT

OAT 0

-50-40-30-20-10 0 8000

9000 GW

10,000 11,000 12.000 -

LB (KG)

2121FR-FM-4-5-8

Figure 4-5. Hover ceiling out of ground effect (Sheet 8 of 8)

4-21

BHT-2121FR-FM-1

FAA APPROVED

90°

CRITICAL RELATIVE

WIND AZIMUTHS

40° TO 135°

135°

180 °

2121FR-FM-4-6

0 Figure 4-6.

4-22

Critical relative wind azimuths for hover flight

FAA APPROVED

BHT-2121FR-FM-1

TAKEOFF DISTANCE OVER 50 FT (15.2m) OBSTACLE HOVERPOWER + 15% TORQUE ENG RPM 100% (N2) GENERATOR150 AMPS

INITIATED FROM 4 FT SKID HEIGHT HEATERON OR OFF WINTERIZATION KIT HTR ON OR OFF

REFERTO VTOCS CHART FOR TAKEOFF SPEED

14,000

FT HD LIMIT

HOT DAY .TEMPERATURE

-60-40-20

0

OAT -

20 40 60 C

FOR TAKEOFF

LIMIT

200

400

600

800

1000

1200

(61)

(122)

(183)

(244)

(305)

(366)

TAKEOFF DISTANCE -

FT (M) 2121FR-FM-4-7

Figure 4-7.

Takeoff distance over a 50 foot (15.2 meter) obstacle

4-23

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE TAKEOFF CLIMBOUT SPEED- KIAS GW-LB HD- FT* 0

8000

9000

10,000

10,500

11,000

11,200

(3175)

(3629)

(4082)

(4536)

(47631

(4989)

(5080)

30

30

30

35

38

40

40

35

38

40

40 40

30

1000

(KG)

7000

30

30

2000

30

30

30

35

38

40

3000

30

30

30

36

38

40

42

4000

30

30

32

36

40

42

5000

30

30

32

38

40

42 42

6000

30

30

34

38

42

-

7000

30

30

34

40

42

8000

30

30

34

40

-

9000

30

30

36

-.

10,000

30

32

36

-

-

-

_

11,000

30

32

38

-

-

-

-

12,000

30

34

38

-

-

-

-

-

-

-

-

13,000

30

34

-

14,000

30

36

-

-

-

Refer to Density Altitude Chart.

2121FR-FM-4-8

Figure 4-8.

4-24

Twin engine takeoff climbout speed

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 7000 (3175 LB KG) TAKEOFFPOWER ENG RPM 100% (N2) GENERATOR 150 AMPS

58 KIAS HEATER OFF

WITHALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

16,000

14,000

Rev. 2

12,000

4-25

10,000

8,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATEOF CLIMB- FT/MIN

3,200 2121FR-FM-4-9.1

Figure 4-9. Twin engine rate of climb (Sheet 1 of 30)

Rev. 2

4-25

FAA APPROVED

BHT-2121FR-FM-1 TWIN ENGINE RATE OF CLIMB GW7000 LB (3175 KG) TAKEOFFPOWER ENGRPM100%(N2) 150 AMPS GENERATOR

58 KIAS HEATERON RATE OF WITHALL DOORSOPENOR REMOVED. CLIMBWILL DECREASE 200 FT/MIN

20,000

16,000

14,000

12,000

8,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB - FT/MIN

Figure 4-9.

4-26

Rev.2

Twin engine rate of climb (Sheet 2 of 30)

3,200 2121FR-FM-4-9-2

FAA APPROVED

BHT-2121FR-FM-1 TWIN ENGINE RATE OF CLIMB GW 8000 LB (3629 KG)

TAKEOFFPOWER ENG RPM100%(N2) GENERATOR 150 AMPS

HEATEROFF WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

20,000

18,000

4,000 4,000

0

400

800

1,200

1,600

2,000

RATE OF CLIMB - FT/MIN

2,400

2,800

3,200 2121FRFM-4-9-3

Rev. 2

4-27

FAA APPROVED

BHT-2121FR-FM-1 TWIN ENGINE RATE OF CLIMB GW 8000 LB (3629 KG) TAKEOFFPOWER ENG RPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATERON WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

20,000

16,000

14,000

4,000 000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB - FT/MIN

Figure 4-9.

4-28 4-28

Rev. Rev. 2

Twin engine rate of climb (Sheet 4 of 30)

3,200 2121FR.FM-4.9-4

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 9000 LB (4082 KG) TAKEOFFPOWER ENG RPM100%(N21) 150 AMPS GENERATOR

58 KIAS HEATEROFF WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

20,000

18,000

16,000

50 40

14,000

8,000 12.000 10,000 8,000

LIMIT

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB- FT/MIN

3,200 2121FR-FM-4-9-5

Figure 4-9. Twin engine rate of climb (Sheet 5 of 30)

Rev. 2

4-29

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 9000 LB (4082 KG) TAKEOFFPOWER ENG RPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATERON WITHALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

20,000

18,000

16,000

12,000

10,000

8,000

2,000

0 0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB - FT/MIN

Figure 4-9.

4-30

Rev. 2

Twin engine rate of climb (Sheet 6 of 30)

2121FR-FM-4-8-6

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB 10.000 LB (4536 KG) TAKEOFFPOWER ENGRPM100% N2) 150 AMPS GENERATOR

58 KIAS HEATEROFF WITHALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

20,000

18,000

-

30C 16,000

16000 14,000

12,000

Rev. 2

8,000 8.000

4-31

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB- FT/MIN

3,200 2121FR-FM.4.9-7

Figure 4-9. Twin engine rate of climb (Sheet 7 of 30)

Rev. 2

4-31

FAA APPROVED

BHT-2121FR-FM-1 TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG) TAKEOFFPOWER ENG RPM100% IN2) GENERATOR 150 AMPS

58 KIAS HEATERON WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

20,000

18,000

---

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB - FT/MIN

Figure 4-9.

4-32

Rev. 2

Twin engine rate of climb (Sheet 8 of 30)

3,200 2121FR-FM-4-9-8

FAA APPROVED

BHT-2121FR-FM-1 TWIN ENGINE RATE OF CLIMB GW 11,200LB (5080 KG)

TAKEOFFPOWER ENG RPM100%(N21 GENERATOR 150 AMPS

HEATER OFF WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

0

200

400

600

800

1,000

1,200

1,400

RATE OF CLIMB - FT/MIN 2121FR-FM-4-9-9

Figure 4-9. Twin engine rate of climb (Sheet 9 of 30)

Rev. 2

4-33

BHT-2121FR-FM-1

FAA APPROVED

TWIN ENGINE RATE OF CLIMB GW 11,200 LB (5080 KGI TAKEOFFPOWER ENGRPM 100%(N2) GENERATOR 150 AMPS

58 KIAS HEATERON WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

18,000

16,000

14,000

12,000

10,000

6,000

4,000

2,000

0

200

400

600

800

100

1,200

1,400

RATEOF CLIMB- FT/MIN 2121FR-FM-4-9-10

Figure 4-9.

4-34

Rev. 2

Twin engine rate of climb (Sheet 10 of 30)

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 7000 LB (3175KG) MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATEROFF

WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN 20,000

18,000

16,000

14,000

12,000 OAT

8.000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB - FT/MIN

Figure 4-9.

2121FR-FM-4-911

Twin engine rate of climb (Sheet 11 of 30)

Rev. 2

4-35

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 7000 LB (3175KG) 83 KIAS HEATEROFF

POWER MAXIMUMCONTINUOUS ENG RPM100%(N2) GENERATOR150 AMPS RATE OF WITH ALL DOORSOPENOR REMOVED, CLIMBWILL DECREASE 200 FT/MIN 20,000

18,000

16,000

14,000

12,000

10,000

OAT

8,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB - FT/MIN

Figure 4-9.

4-36

Rev. 2

Twin engine rate of climb (Sheet 12 of 30)

2121FR-FM-4-9-12

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 7000 LB (3175 KG) MAXIMUMCONTINUOUS POWER ENGRPM100% (N2) GENERATOR 150 AMPS

58 KIAS HEATERON

WITHALL DOORSOPENOR REMOVED, RATE OF CLIMB WILL DECREASE 200 FT/MIN 20,000

OAT

6,000

4,000

2,000

400

800

1,200

1,600

2,000

2,400

2,800 Rev. 2

4-37

Rev. 2

4-37

FAA APPROVED

BHT-2121FR-FM-1 TWIN ENGINE RATE OF CLIMB GW 7000 LB (3175 KG)

83 KIAS KIT ON HEATERORWINTERIZATION

POWER MAXIMUMCONTINUOUS ENGRPM100%(N2) 150 AMPS GENERATOR

RATEOF WITH ALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMBWILL DECREASE 20,000

18,000

16,000

12,000

8,000

4,000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB - FT/MIN

Figure 4-9.

4-38 4-38

Rev. 2 Rev.

Twin engine rate of climb (Sheet 14 of 30)

2121FR-FM-4-9-14

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW8000 LB (3629 KG) MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATEROFF

WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMB WILL DECREASE 200 FT/MIN 20,000

18,000

14,000

OAT LIMIT

12,000

10,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB- FT/MIN

Figure 4-9.

2121FR.FM-4-9.15

Twin engine rate of climb (Sheet 15 of 30)

Rev. 2

4-39

FAA APPROVED

BHT-2121FR-FM-1 TWIN ENGINE RATE OF CLIMB GW 8000 LB (3629 KG)

83 KIAS HEATEROFF

POWER MAXIMUMCONTINUOUS ENG RPM100%(N21 150 AMPS GENERATOR WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE200 FT/MIN 20,000

18.000

16,000

14,000

12,000

4,000 2,000 6,000

4,000

0

OAT

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-40

Rev. 2

Twin engine rate of climb (Sheet 16 of 30)

2121FR-FM-4-9-16

FAA APPROVED

BHT-212IFR-FM-1

TWIN ENGINE RATE OF CLIMB GW8000 LB (3629 KG) MAXIMUMCONTINUOUS POWER ENGRPM100% (N2) GENERATOR 150 AMPS

58 KIAS HEATERON

WITHALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN 20.000 18,000

OAT

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

RATEOF CLIMB- FT/MIN

Figure 4-9.

2121FR-FM-4-9-17

Twin engine rate of climb (Sheet 17 of 30)

Rev. 2

4-41

FAA APPROVED

BHT-2121FR-FM-1 TWIN ENGINE RATE OF CLIMB GW 8000 LB (3629 KG)

83 KIAS HEATEROR KIT ON WINTERIZATION

POWER MAXIMUMCONTINUOUS ENGRPM100%(N2) 150 AMPSEACH GENERATOR

RATE OF WITH ALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMBWILL DECREASE 20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-42

Rev. 2

Twin engine rate of climb (Sheet 18 of 30)

2121FR-FM-4-9-18

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 9000 LB (4082 KGI MAXIMUMCONTINUOUS POWER ENG RPM100%(N21 GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF

WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMB WILL DECREASE 200 FT/MIN 20,000

16,000

14,000

8.000 OAT 6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

RATEOF CLIMB- FT/MIN Figure 4-9.

2121FR-FM-4-9-1

Twin engine rate of climb (Sheet 19 of 30)

Rev. 2

4-43

FAA APPROVED

BHT-2121FR-FM-1 TWIN ENGINE RATE OF CLIMB GW9000 LB (4082 KG)

83 KIAS HEATEROFF

POWER MAXIMUMCONTINUOUS ENGRPM100%(N2) 150 AMPS EACH GENERATOR RATE OF WITHALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMBWILL DECREASE 20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000 OAT LIMIT

2,000

0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-44

Rev. 2

Twin engine rate of climb (Sheet 20 of 30)

2121FR-FM-4-9.20

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 9000 LB (4082 KG) MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPSEACH

58 KIAS HEATERON

WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMB WILL DECREASE 200 FT/MIN 20,000

18,000

16,000

14,000

12,000

Rev. 2

10,000

4-45

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

RATEOF CLIMB- FT/MIN

2121FR-FM.4.9-21

Figure 4-9. Twin engine rate of climb (Sheet 21 of 30)

Rev. 2

4-45

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW9000 LB (4082 KG) 83 KIAS HEATEROR KIT ON WINTERIZATION

POWER MAXIMUMCONTINUOUS ENGRPM100% (N2) 150 AMPS EACH GENERATOR

RATEOF WITH ALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMBWILL DECREASE 20,000

18,000

16,000

14,000

12,000

10,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB- FT/MIN Figure 4-9.

4-46

Rev. 2

Twin engine rate of climb (Sheet 22 of 30)

2121FR-FM-4-9-22

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG) MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF

WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN 20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

OAT LIMIT

4,000

2,000

0

200

400

600

800

1,000

1,200

1,400

RATE OF CLIMB- FT/MIN

1,600 2121FR-FM-4.9-23

Figure 4-9. Twin engine rate of climb (Sheet 23 of 30)

Rev. 2

4-47

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG) 83 KIAS HEATEROFF

POWER MAXIMUMCONTINUOUS ENGRPM100% (N2) 150 AMPS EACH GENERATOR RATEOF WITHALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMB WILL DECREASE 20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000 OAT LIMIT

2,000

0

200

400

600

800

1,000

1,200

1,400

RATE OF CLIMB- FT/MIN Figure 4-9. Twin engine rate of climb (Sheet 24 of 30)

4-48

Rev. 2

2121FR-FM-4-g-24

BHT-2121FR-FM-1

FAA APPROVED

TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG) MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) AMPS EACH 150 GENERATOR

58 KIAS HEATERON

WITH ALL DOORSOPENOR REMOVED, RATE OF 200 FT/MIN CLIMBWILL DECREASE 20,000

18,000

16,000

14,000

12,000

10,000 6,000

6,000

2,000

0

200

400

600

800

1,000

1,200

1,400

RATEOF CLIMB- FT/MIN Figure 4-9.

1,600 2121FR.FM-4-9.25

Twin engine rate of climb (Sheet 25 of 30)

Rev. 2

4-49

BHT-2121FR-FM-1

FAA APPROVED

TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG) MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS EACH

83 KIAS WINTERIZATION KIT O

WITH ALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN 20,000

18,000

16,000

14,000

12,000

8,000

4,000

2,000

0

200

400

600

800

1,000

1,200

RATE OF CLIMB- FT/MIN Figure 4-9.

4-50

Rev. 2

Twin engine rate of climb (Sheet 26 of 30)

1,400 2121FR-FM-4-9-26

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 11,200LB (5080 KG) MAXIMUMCONTINUOUS POWER ENG RPM100%IN2) GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF

WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

18.000

16,000

14,000 14,000 12,000

10,000

,000

6,000

LIMIT

2,000

0

200

400

600

800

1,000

1,200

1,400

RATE OF CLIMB- FT/MIN 2121FR-FM-4-9-27

Figure 4-9.

Twin engine rate of climb (Sheet 27 of 30)

Rev. 2

4-51

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 11,200LB (5080 KG) MAXIMUMCONTINUOUS POWER ENGRPM100% (N2) 150 AMPS EACH GENERATOR

83 KIAS HEATEROFF

WITH ALL DOORSOPENOR REMOVED. RATEOF CLIMBWILL DECREASE 200 FT/MIN

18,000

16,000

14,000

12,000

10,000

8,000

4,000

0

200

400

600

800

1,000

1,200

RATE OF CLIMB- FT/MIN 212FR-FM4-9-28

Figure 4-9.

4-52

Rev. 2

Twin engine rate of climb (Sheet 28 of 30)

FAA APPROVED

BHT-2121FR-FM-1

TWIN ENGINE RATE OF CLIMB GW 11,200LB (5080 KG) MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS EACH

58 KIAS HEATERON

WITHALL DOORSOPENOR REMOVED. RATEOF CLIMBWILL DECREASE200 FT/MIN

18,000

16,000

14,000

12,000

2,000

0

200

400

600

800

1,000

1,200

1,400

RATE OF CLIMB- FT/MIN 2121FR-FM-4-9-2

Figure 4-9.

Twin engine rate of climb (Sheet 29 of 30)

Rev. 2

4-53

BHT-2121FR-FM-1

FAA APPROVED

TWIN ENGINE RATE OF CLIMB GW 11,200LB(5080 KG) MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS EACH

83 KIAS HEATEROR WINTERIZATION KIT ON

WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

0

200

400

600

800

1,000

1,200

RATEOF CLIMB- FT/MIN 2121FR-FM-4-9-30

Figure 4-9.

4-54

Rev. 2

Twin engine rate of climb (Sheet 30 of 30)

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 7000 LB(3175 KG) 2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITHALL DOORSOPENORREMOVED, RATE OFCLIMBWILL DECREASE 200 FT/MIN

NOTE

OAT -50°C

OPERATION ABOVE 71.8%

-40°C

18,000

TORQUE REQUIRES THE TORQUEMETER

16,000

14,000

71.8% 79.4%

00

00

400

800

6000 2000

-400

0

RATE OF CLIMB Figure 4-10.

1200 FT/MIN

1600

2000 212IFR-FM-4-10-1

Single engine rate of climb - PT6T-3B (Sheet 1 of 10)

Rev. 2

4-55

FAA APPROVED

BHT-2121FR-FM-1 SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW8000 LB (3629KG)

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) 150 AMPSEACH GENERATOR

RATE WITHALL DOORSOPENORREMOVED, 200 FT/MIN OFCLIMBWILL DECREASE 20,000

|OAT

NOTE

-50°C- OPERATIONABOVE 71 8% 0° C TORQUE REQUIRES THE -4

18,000

-30°C

OR -103 212.070.160-101 TORQUEMETER.

16,000

14,000

TORQUE LIMITS

71.8%

12,000

79.4%

8000

4000

OAT

LIMIT

2000

-800

-400

0

400

800

RATE OF CLIMB - FT/MIN Figure 4-10.

4-56

Rev. 2

1200

1600 121FR-FM-4-10-2

Single engine rate of climb - PT6T-3B (Sheet 2 of 10)

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 9000 LB(4082 KG) 2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITHALL DOORSOPENORREMOVED. RATE OFCLIMBWILL DECREASE 200 FT/MIN

20,000 20.000

OAT

NOTE OPERATIONABOVE 71 8%

-40°C

18,000

TORQUEREQUIRES THE 212-070-160-101 OR -103 TORQUEMETER.

16,000

14,000. TORQUE LIMITS

12,000

2000

6000

2000

OAT LIMIT

RATE OF CLIMB - FT/MIN Figure 4-10.

2121FR-FM-4-10-3

Single engine rate of climb - PT6T-3B (Sheet 3 of 10)

Rev. 2

4-57

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW10,000 LB(4536 KG) 58 KIAS HEATEROFF ENGINESECURED INOPERATIVE

2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) 150 AMPS GENERATOR

RATEOF WITHALL DOORSOPENORREMOVED. 200 FT/MIN CLIMBWILLDECREASE

20,000

NOTE

0AT 18,000

-40°C

OPERATIONABOVE 71.8% TORQUE REQUIRES THE 212-070-160-101 OR -103 TORQUEMETER

16,000

TORQUE LIMITS

71.8%

6000 4000 2000

RATE OF CLIMB -FT/MIN

2121FR-FM4-10-4

Figure 4-10. Single engine rate of climb - PT6T-3B(Sheet 4 of 10)

4-58

Rev. 2

BHT-2121FR-FM-1

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 11,200 LB(5080 KG) 2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) 150 AMPS GENERATOR

58 KIAS HEATEROFF INOPERATIVEENGINESECURED RATEOF WITH ALLDOORSOPENORREMOVED, CLIMBWILL DECREASE 200 FT/MIN

20,000

NOTE OPERATIONABOVE 71.8% TORQUE REQUIRES THE

OR 103 212-070-160-101

18,000 OAT

16,000

TORQUEMETER

-40C

14,000 14.000

8000 8000

OATLIMIT

-1200

-800

-400

0

400

RATE OF CLIMB - FT/MIN

Figure 4-10.

800 2121FR-FM-4-10-5

Single engine rate of climb - PT6T-3B (Sheet 5 of 10)

Rev.2

4-59

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW7000 LB(3175 KG) 30 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS

58KIAS HEATEROFF INOPERATIVE ENGINESECURED WITH ALL DOORSOPENORREMOVED. RATEOF CLIMBWILL DECREASE 200 FT/MIN

20,000

OAT

NOTE -50°C -40°C

18,000

OPERATIONABOVE 71.8% TORQUE REQUIRES THE 212-070-160-101 OR .103 TORQUEMETER.

16,000

14,000

TORQUE

_

12,000

8000

-400

0

400

800 1200

RATE OF CLIMB - FT/MIN Figure 4-10.

4-60

Rev. 2

1600 212FR-FM-4-10-6

Single engine rate of climb - PT6T-3B (Sheet 6 of 10)

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW8000 LB13629KG) 30 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS

58 KIAS HEATEROFF INOPERATIVE ENGINESECURED WITH ALLDOORSOPENORREMOVED, RATEOF CLIMBWILLDECREASE 200 FT/MIN

20,000

OAT

NOTE

C

TORQUEMETER

18,000

OPERATION ABOVE 71.8%

16,000 14.000 TORQUE

12,000

OAT LIMIT

8000

4000

-800

-400

0

400

800

RATE OF CLIMB - FT/MIN

1200

1600 2121FRFM-4-107

Figure 4-10. Single engine rate of climb - PT6T-3B (Sheet 7 of 10)

Rev. 2 Rev.

4-61

FAA APPROVED

BHT-2121FR-FM-1 SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW9000 LB(4082 KG)

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

30 MINUTEOEIPOWER ENGRPM97% (N2) 150 AMPS GENERATOR

RATEOF WITH ALLDOORSOPENORREMOVED, 200 FT/MIN CLIMBWILLDECREASE

20.000 NOTE

OAT

18,000 -50

0

OPERATION ABOVE 71.8% REQUIRES THE TORQUE OR 103 TOROUEMETER

212-070-160-101 C

16.000

14,000

TORQUE LiMITS

12,000

10,000

OAT LIMIT

RATE OF CLIMB Figure 4-10.

4-62

Rev. 2

FT/MIN

2121FR-FM-4-10-8

Single engine rate of climb - PT6T-3B (Sheet 8 of 10)

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW10,000 LB(4536 KG) 30 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS

58 KIAS HEATEROFF INOPERATIVEENGINESECURED RATEOF WITHALL DOORSOPENORREMOVED. CLIMBWILLDECREASE 200 FT/MIN

20,000

NOTE OAT

18,000

50°C -40°C

OPERATIONABOVE 71 8% TORQUE REQUIRES THE

212-070-160-101 OR 103 TORQUEMETER.

-30°C

16,000

14,000 TORQUE

Rev. 2 Rev. 2

4-63 4-63

FAA APPROVED

BHT-2121FR-FM-1 SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 11,200 LB (5080KG)

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

30 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS

WITHALL DOORSOPENORREMOVED, RATEOF 200 FT/MIN CLIMBWILL DECREASE 20,000 NOTE OPERATIONABOVE 71.8% TORQUE REQUIRES THE 212-070-160-101 OR -103

18,000 OAT

-5

16,00 0

TORQUEMETER

C

30C 14,000 12.000 TORQUE

8000

OAT LIMIT

-12

00

-400 RATE OF CLIMB -

Figure 4-10.

4-64

Rev. 2

800 FT/MIN

2121FR-FM-4-10-10

Single engine rate of climb - PT6T-3B (Sheet 10 of 10)

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW 7000LB(3175 KG) 30 MINUTEPOWER

58KIAS

ENG RPM 97% (N2)

HEATER OFF

GENERATOR 150 AMPSEACH

INOPERATIVE ENGINESECURED

WITH ALL DOORS OPEN OR REMOVED. RATE OF CLIMB WILL DECREASE200 FT/MIN

20,000 18,000

--

16,000 14,000 12,000 10,000 8000 6000

OAT LIMIT

4000 2000

-600

-400 -200

0

200 400 600

800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

2121FR-FM-4-11-1

Figure 4-11.

Single engine rate of climb - PT6T-3 (Sheet 1 of 10)

Rev. 2

4-65

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW8000 LB(3629 KG) 58 KIAS HEATEROFF INOPERATIVE ENGINESECURED

30 MINUTEPOWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

WITHALLDOORSOPENORREMOVED, RATE OFCLIMBWILLDECREASE 200 FT/MIN

20,000 18,000 OAT 16,000

12,000 10,000 8000

OAT LIMIT

6000

2000

-1000-800--600--400---00

0

200

400

600

800 600

1200 1400

2121FR-FM-4 11-2

Figure 4-11.

4-66

Rev. 2

Single engine rate of climb - PT6T-3 (Sheet 2 of 10)

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATEOF CLIMB - PT6T-3 GW 9000 LB (4082 KG)

30 MINUTEPOWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

58 KIAS HEATEROFF INOPERATIVE ENGINESECURED

WITH ALL DOORS OPENOR REMOVED, RATE OF CLIMB WILL DECREASE200 FT/MIN

20.000 18.000 16.000 OAT

14,000 14,000

MAXIMUMCONTINUOUS ,

6000

2000

0 1200-1000

-800

-600

-400

-200

0

200

400

600

800

1000 1200

RATE OF CLIMB - FT/MIN 2121FR-FM-4-11-3

Figure 4-11.

Single engine rate of climb - PT6T-3 (Sheet 3 of 10)

Rev. 2

4-67

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW10,000 LB(4536 KG) 58 KIAS HEATEROFF INOPERATIVE ENGINESECURED

30 MINUTEPOWER ENGRPM97% (N2) 150 AMPSEACH GENERATOR

WITH ALL DOORS OPENOR REMOVED, RATE OF CLIMB WILL DECREASE200 FT/MIN

20.000

18.000

16000 OAT

14.000

--

12,000 000 8000 TWINENGINE

6000

POWER ABSOLUTE CEILING

4000

2000

-1000

-800

-600

-400

-200

0

200

400

RATE OF CLIMB - FT/MIN

Figure 4-11.

4-68

Rev. 2

600

800

1000

2121FR-FM-4-11-4

Single engine rate of climb - PT6T-3 (Sheet 4 of 10)

FAA APPROVED

BHT-2121FR-FM-1 SINGLE ENGINE RATE OF CLIMB-PT6T-3 GW 11,200LB 15080KG)

30 MINUTEPOWER ENGRPM97%(N2) GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

18,000

TWINENGINE

MAXIMUMCONTINUOUS POWER ABSOLUTECEILING

16,000

14,000

12,000

10,000

8,000 6,000

4.000 OAT

2,000

-1,000

-800

-600

-400

-200

0

200

400

RATEOF CLIMB- FT/MIN 2121FR-FM-4-11-6

Figure 4-11.

Single engine rate of climb - PT6T-3 (Sheet 5 of 10)

Rev. 2

4-69

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATEOF CLIMB - PT6T-3 GW7000 LB(3175 KG) MAXIMUMCONTINUOUS POWER ENGRPM97% (N2) 150 AMPSEACH GENERATOR

58 KIAS HEATEROFF ENGINESECURED INOPERATIVE

RATE WITH ALLDOORSOPENORREMOVED, 200 FT/MIN OFCLIMBWILLDECREASE

18000 18000 16000 14000

10000 8000

RATE OF CLIMB - FT/MIN 2000

Figure 4-11.

4-70

Rev. 2

2121FR-FM-4-11-6

Single engine rate of climb - PT6T-3 (Sheet 6 of 10)

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATEOF CLIMB - PT6T-3 GW8000 LB(3629 KG) MAXIMUMCONTINUOUS POWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

58 KIAS HEATEROFF INOPERATIVE ENGINESECURED

WITHALL DOORSOPENORREMOVED, RATE OFCLIMBWILLDECREASE 200 FT/MIN

20.000

Figure 4-11. Single engine rate of climb - PT6T-3 (Sheet 7 of 10) Rev.2

4-71

FAA APPROVED

BHT-2121FR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW9000 LB(4082 KG) 58 KIAS HEATEROFF INOPERATIVEENGINESECURED

POWER MAXIMUMCONTINUOUS ENGRPM97% (N2) 150 AMPS EACH GENERATOR

WITH ALL DOORS OPENOR REMOVED. RATE OF CLIMB WILL DECREASE200 FT/MIN

20,000 OAT

16,000 14,000 12,000

.

10,000

.

TWINENGINE MAXIMUMCONTINUOUS POWERABSOLUTECEILING

8000 6000

OAT' LIMIT

4000 2000

-1800-1600-1400-1200-1000-800 -600 -400 -200

0

200 400 600 800 1000

RATE OF CLIMB - FT/MIN

2121FR-FM-4-11-8

Figure 4-11.

4-72

Rev.2

Single engine rate of climb - PT6T-3 (Sheet 8 of 10)

FAA APPROVED

BHT-2121FR-FM-1 SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW 10,000 LB(4536 KG)

MAXIMUM CONTINUOUS POWER

58 KIAS

ENG RPM 97% (N2)

HEATER OFF

GENERATOR 150 AMPSEACH

INOPERATIVE ENGINESECURED

WITH ALL DOORS OPENOR REMOVED, RATE OF CLIMB WILL DECREASE200 FT/MIN

20000

OAT

18000

16000 12000

10000

8000

ENGINE MAXIMUM CONTINUOUS POWER ABSOLUTE CEILING

6000

OAT LIMIT

4000

2000

-1200

-1000

-800

-600 -400 -200 0 RATE OF CLIMB - FT/MIN

200

400 600 2121FR-FM-4-11-9

Figure 4-11. Single engine rate of climb - PT6T-3 (Sheet 9 of 10)

Rev. 2

4-73

FAA APPROVED

BHT-2121FR-FM-1 SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW 11,200LB (5080 KG)

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

POWER MAXIMUMCONTINUOUS ENG RPM97% IN2) 150 AMPS EACH GENERATOR

RATEOF WITHALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMBWILL DECREASE TWIN ENGINE M.C.P. ABSOLUTECEILING

18,000

16,000

14,000

12,000

10,000

8,000

6,000

OAT LIMIT

2,000

-1,000

-800

-600

200 0 -200 -400 RATEOF CLIMB- FT/MIN

400

2121FR-FM-4-11-10

Figure 4-11.

4-74

Rev. 2

Single engine rate of climb - PT6T-3 (Sheet 10 of 10)

BHT-2121FR-FM-1

FAA APPROVED PILOT AIRSPEED SYSTEM CALIBRATION

CLIMB LEVELFLIGHT AUTOROTATION SKID GEAR IAS-ERROR VCAL

120 LEVEL FLIGHT

100

AUTO

60 CLIMB

40

20

--------

0 0

20

40

60

80

100

120

140

INDICATED AIRSPEED - KNOTS 2211FRFM-4-12

Figure 4-12.

Pilot airspeed system calibration

Rev. 2

4-75

BHT-2121FR-FM-1

FAA APPROVED COPILOT AIRSPEED SYSTEM CALIBRATION

CLIMB LEVELFLIGHT AUTOROTATION SKID GEAR IAS - ERROR VCAL

140 LEVELFLIGHT

60

INDICATEDAIRSPEED- KNOTS

Figure 4-13. Copilot airspeed system calibration

4-76 4-76

Rev.2 Rev. 2

221FR-FM-4-13

BHT-2121FR-FM-1

FAA APPROVED SINGLE ENGINE LANDING DISTANCE 50 FT (15.2 M) OBSTACLE

40 KIAS RATEOF DESCENT500 FPM HARD SURFACEDRUNWAY

AS REQUIRED POWER ENGRPM97% (N2) 150 AMPS GENERATOR INOPERATIVEENGINESECURED

14,000 FT HD LIMIT

HOT DAY LIMIT

-60-40-20

0

OAT-

20 40 60

200

400

600

800

1000

°C

(61)

(122)

(183)

(244)

(305)

LANDING DISTANCE - FT (M)

.

2121FR-FM-4-14

Figure 4-14. Single engine landing distance over a 50 foot (15.2 meter) obstacle

Rev. 2

4-77/4-78

MANUFACTURER'S DATA

BHT-2121FR-FM-1

Section 5 TABLE OF CONTENTS Subject

Paragraph

INTRODUCTION ............................................... EMPTY WEIGHT CENTER OF GRAVITY ........................ GROSS WEIGHT CENTER OF GRAVITY........................ DOORS OPEN OR REMOVED .................................. COCKPIT AND CABIN LOADING ............................ CABIN DECK LOADING .................................... INTERNAL CARGO LOADING TABLE...................... BAGGAGE COMPARTMENT LOADING ......................... BAGGAGE LOADING ....................................... BAGGAGE LOADING TABLE............................... FUEL LOADING .............................................. COMPUTATION OF CG ..................................... SAMPLE LOADING PROBLEM .............................

5-1 5-2 ......... 5-3.......... 5-4......... 5-5.......... 5-5-A . ..... 5-5-B ...... 5-6........... 5-6-A ..... 5-6-B ....... 5-7 .... 5-7-A ...... 5-7-B ........

...

Page Number 5-3 5-3 5-3 5-3 5-3 5-3 5-4 5-4 5-4 5-4 5-4 5-5

LIST OF FIGURES Title

Figure Number

Helicopter station diagram .....................................

5-1...........

Page Number

5-6

LIST OF TABLES Title

Table Number

Door weights and moments .................................... Crew and passenger table of moments ........................

5-1.......... 5-2...........

Internal cargo loading .......................................... Baggage loading ................................................

Fuel loading .................................................... Fuel loading.....................................................

5-3..........

Page Number 5-7 5-8

5-9

5-4

5-12

5-6 ..........

5-15

5-5..........

5-13

5-1/5-2

MANUFACTURER'S DATA

BHT-2121FR-FM-1

Section 5 5-1.

INTRODUCTION

This section provides information

5-4. DOORS OPEN OR REMOVED

center of gravity and

Opening or removing doors results in CG

cockpit and cabin loading. Loading table for pilot and passengers, cargo, and fuel

changes. Door configuration shall be symmetrical for both sides of fuselage.

regarding

helicopter

are provided.

A sample loading problem is

provided to aid in flight planning.

Door weights and moments table (table 5-

1) lists weight and moment adjustments

which should be made in determining

GW

and CG when doors are opened or

5-2. EMPTY WEIGHT CENTER OF GRAVITY

removed.

Weight empty consists of basic helicopter

LOADING

with required equipment, optional with required equipment and KitS, optional equipment kits, transmission gearbox

undrainable engine oil, and fixed ballast. Weigh empty CG shall be adjusted within

limits of applicable Weight empty center of

5-5.

COCKPIT AND CABIN

A minimum crew inweight of (77.1 (77.1 kilograms) kilograms) in cockpit cockpit Except for two aft passenger

170 pounds is required. is required. seats, crew

and passengers may be loaded in any sequence without exceeding GW CG limits

approved for flight.

gravity chart in BHT-212-MM. NOTE

5-3.

GROSS WEIGHT CENTER

OF GRAVITY

Outboard facing seats should not be occupied unless at least four passengers are seated in forward

It shall be pilot responsibility to ensure helicopter Is properly loaded so entire flight is conducted within limits of Gross

and/or aft facing seats.

Weight Center of Gravity Chart in Section

1. GW CG may be calculated

from

helicopter Actual Weight Record (historical records) and loading tables in this section

or in appropriate

Flight

Manual

5-5-A.

CABIN DECK LOADING

Cabin deck cargo loading limit is 100 pounds per square foot (0.048 kilograms per square centimeter).

Supplements to assure safe loading. Locations of crew and passenger seats, baggage compartment, and fuel tanks are

shown in helicopter station diagram (figure 5-1). 5-3

BHT-2121FR-FM-1

MANUFACTURER'S DATA

5-6-B. BAGGAGE LOADING TABLE

WARNING

at various

arms and their

Helicopter CG shall be computed

Weights

configurations before flight.

increments from 20 pounds through 400 pounds and in 10 kilogram increments

for

all

cargo/baggage

Refer to table 5-2 for personnel weights

moments are listed

In 20 pound

from 10 kilograms through 181.4 kilograms

(table 5-4).

and moments in English and Metric units.

5-5-B.

INTERNAL CARGO LOADING

TABLE

5-7.

FUEL LOADING

At beginning of any flight with full fuel on board, helicopter CG will move forward

Weights at various arms and their moments are listed in 50 pound Increments from 50 pounds through 2000 pounds and in 25 kilogram increments from 25 kilograms through 900 kilograms (table 5-3).

due to the fact that the CG of fuel on board

moves forward as it is consumed. This occurs because fuel is consumed from rear (upper) fuel cells first. Maximum forward CG condition of fuel on board occurs when 72.6 U.S. gallons (274.8 liters) remain for helicopter serial numbers prior to 35049 and at 78.5 U.S. gallons

5-6. BAGGAGE COMPARTMENT LOADING Baggage compartment is accessible from

right side of tailboom and contains approximately 28 cubic feet of space. Baggage compartment has a load limit of

400 pounds (181.4 kilograms) not to exceed 100 pounds per square foot (0.048

kilograms per square centimeter). These are structural

limitations

only and do not

infer that CG will remain within approved limits. When weight is loaded into baggage compartment, indiscriminate crew, passenger, and fuel loading can no longer be assumed, and pilot must compute GW CG to ensure loading is within approved limits.

5-6-A.

BAGGAGE LOADING

Loading of baggage compartment should from front front to rear. Load shall be be from secured to tiedown fittings if shifting of load in flight could result in structural damage to baggage compartment or in GW CG limits being exceeded. If baggage Is

not secured, CG shall be computed with load in most adverse position. 5-4

(297.1

liters) for helicopter serial numbers 30549 and subsequent. CG then begins to move rearward as fuel is consumed from forward (lower) fuel cells. With normal crew and passenger loading, GW CG should remain

within limits at any fuel quantity.

Fuel quantities are listed with moments in 10 gallon increments from 10 gallons

through 216.8 gallons and in 40 liter increments

from

40 liters

through

820.7

liters for helicopter serial numbers prior to 35049 (table 5-5).

Fuel quantities are listed with moments in 10 gallon increments from 10 gallons through 218.6 gallons and in 40 liter increments from 40 liters through 827.4 liters for helicopter serial numbers 35049 and subsequent (table 5-6).

5-7-A.

COMPUTATION OF CG

A sample problem Is presented showing calcuiation of takeoff and landing weights calculation of takeoff and landin weights g and CG locations for two typical loading conditions.

_

MANUFACTURER'S DATA

BHT-2121FR-FM-1

5-7-B. SAMPLE LOADING

155 gallons (586.8 liters) of fuel. Pilot, weighing 180 pounds (82 kilograms), will return alone. Determine extreme CG

PROBLEM CG of helicopter will move forward as fuel Is burned off in flight. This occurs because fuel is burned from upper rear fuel cells first. A maximum forward CG condition occurs when 72.6 gallons (274.8

conditions for both trips. From GW CG charts in Section 1, it can be determined that CG is within limits for first leg of flight and that loading of passengers in five man and four man seats will be

liters) of fuel is on board for helicopter serial numbers prior to 35049. CG then

satisfactory for first leg

begins to move rearward as fuel is burned

From

out of lower fuel cells.

determined that CG Is within limits for second leg of flight, thus, entire operation

Helicopter

is chartered

to transport

nine

GW CG charts,

it can

also

be

can be completed.

passengers and 180 pounds of baggage for a trip that will require approximately

5-5/5-6

BHT-2121FR-FM-1

MANUFACTURER'S DATA

FUSELAGE STATIONS 0

243

166

23

BAGGAGE COMPARTMENT 177 155

DATUM

///////// ///////// _ /

Pilot Seat (2) Copilot or PassengerSeat Fuel Cells Seats Lateral Location (Inches From CL) of Helicopter Longitudinal Location (Inches Aft of Ref Datum) of Personnel External Cargo

Figure 5-1.

2121FR-FM-5-1

Helicopter station diagram

5-7

BHT-2121FR-FM-1

MANUFACTURER'S DATA Table 5-1.

Door weights and moments ENGLISH

DOOR CONFIGURATION Both Both Both Both

crew doors removed hinged panels removed sliding doors removed sliding doors full open

WEIGHT CHANGE (POUNDS)

ARM (INCHES)

-39.0 -20.4 -90.4 0

46.2 85.0 130.0 202.0

MOMENT CHANGE (IN-LB) -1802 1734 -11,752 +6509

METRIC

DOOR CONFIGURATION Both Both Both Both

crew doors removed hinged panels removed sliding doors removed sliding doors full open

WEIGHT CHANGE (KILOGRAMS)

ARM (MILLIMETERS)

-17.7 - 9.3 -41.0 0

1173 2159 3302 5131

MOMENT CHANGE (KG * MM/100) -207.6 200.8 -1353.8 +749.9

(TABLE

5-8

I.D. 911208)

MANUFACTURER'S DATA

a,

BHT-2121FR-FM-1

BHT-2121FR-FM-1

5-10

o

MANUFACTURER'S DATA

MANUFACTURER'S DATA

BHT-2121FR-FM-1 Table 5-3.

Internal cargo loading

INTERNAL CARGO LOADING TABLE (ENGLISH) CARGO WEIGHT (POUNDS)

75

90

CARGO CENTER OF GRAVITY (FS) 105 120

135

150

CARGO MOMENT(IN-LB) 50 100 150 200 250

3750 7500 11250 15000 18750

4500 9000 13500 18000 22500

5250 10500 15750 21000 26250

6000 12000 18000 24000 30000

6750 13500 20250 27000 33750

7500 15000 22500 30000 37500

300 350 400 450 500

22500 26250 30000 33750 37500

27000 31500 36000 40500 45000

31500 36750 42000 47250 52500

36000 42000 48000 54000 60000

40500 47250 54000 60750 67500

45000 52500 60000 67500 75000

550 600 650 700 750

41250 45000 48750 52500 56250

49500 54000 58500 63000 67500

57750 63000 68250 73500 78750

66000 72000 78000 84000 90000

74250 81000 87750 94500 101250

82500 90000 97500 105000 112500

800 850 900 950 1000

60000 63750 67500 71250 75000

72000 76500 81000 85500 90000

84000 89250 94500 99750 105000

96000 102000 108000 114000 120000

108000 114750 121500 128250 135000

120000 127500 135000 142500 150000

1050 1100 1150 1200 1250

78750 82500 86250 90000 93750

94500 99000 103500 108000 112500

110250 115500 120750 126000 131250

126000 132000 138000 144000 150000

141750 148500 155250 162000 168750

157500 165000 172500 180000 187500

1300 1350 1400 1450 1500

97500 101250 105000 108750 112500

117000 121500 126000 130500 135000

136500 151750 147000 152250 157500

156000 162000 168000 174000 180000

175500 182250 189000 195750 202500

195000 202500 210000 217500 225000

1550 1600 1650 1700 1750

116250 120000 123750 127500 131250

139500 144000 148500 153000 157500

162750 168000 173250 178500 183750

186000 192000 198000 204000 210000

209250 216000 222750 229500 236250

232500 240000 247500 255000 262500

1800 1850 1900 1950 2000

135000 138750 142500 146250 150000

162000 166500 171000 175500 180000

189000 194250 199500 204750 210000

216000 222000 228000 234000 240000

243000 249750 256500 263250 270000

270000 277500 285000 292500 300000 (TABLE

I.D. 911214)

5-11

MANUFACTURER'S DATA

BHT-2121FR-FM-1 Table 5-3.

Internal cargo loading (Cont)

INTERNAL CARGO LOADING TABLE (METRIC) CARGO WEIGHT (KG)

1905

2286

CARGO CENTER OF GRAVITY (MM) 3048 2667

3429

3810

CARGO MOMENT(KG * MM/100) 25 50 75

476.3 952.5 1428.8

571.5 1143.0 1714.5

666.8 1333.5 2000.3

857.3 1714.5 2571.8

952.5 1905.0 2857.5

2286.0

2667.0

762.0 1524.0 2286.0

3048.0

3429.0

3810.0

125

2381.3

2857.5

3333.8

3810.0

4286.3

4762.5

275 300 325 350 375 400 425 450 475 500 525 550 575 600 625 650 675 700 725 750 775 800 825 850 875 900

5238.8 5715.0 6191.3 6667.5 7143.8 7620.0 8096.3 8572.5 9048.8 9525.0 10001.3 10477.5 10953.8 11430.0 11906.3 12382.5 12858.8 13335.0 13811.3 14287.5 14763.8 15240.0 15716.3 16192.5 16668.8 17145.0

6286.5 6858.0 7429.5 8001.0 8572.5 9144.0 9715.5 10287.0 10858.5 11430.0 12001.5 12573.0 13144.5 13716.0 14287.5 14859.0 15430.5 16002.0 16573.5 17145.0 17716.5 18288.0 18859.5 19431.0 20002.5 20574.0

7334.3 8001.0 8667.8 9334.5 10001.3 10668.0 11334.8 12001.5 12668.3 13335.0 14001.8 14668.5 15335.3 16002.0 16668.8 17335.5 18002.3 18669.0 19335.8 20002.5 20669.3 21336.0 22002.8 22669.5 23336.3 24003.0

8382.0 9144.0 9906.0 10668.0 11430.0 12192.8 12954.0 13716.0 14478.0 15240.0 16002.0 16764.0 17526.0 18288.0 19050.0 19812.0 20574.0 21336.0 22098.0 22860.0 23622.0 24384.0 25146.0 25908.0 26670.0 27432.0

9429.8 10287.0 11144.3 12001.5 12858.8 13716.0 14573.3 15430.5 16287.8 17145.0 18002.3 18859.5 19716.8 20574.0 21431.3 22288.5 23145.8 24003.0 24860.3 25717.5 26574.8 27432.0 28289.3 29146.5 30003.8 30861.0

10477.5 11430.0 12382.5 13335.0 14287.5 15240.0 16192.5 17145.0 18097.5 19050.0 20002.5 20955.0 21907.5 22860.0 23812.5 24765.0 25717.5 26670.0 27622.5 28575.0 29527.5 30480.0 31432.5 32385.0 33337.5 34290.0

100 150 175 200 225 250

1905.0 2857.5 3333.8 3810.0 4286.3 4762.5

3429.0 4000.5 4572.0 5143.5 5715.0

4000.5 4667.3 5334.0 6000.8 6667.5

4572.0 5334.0 6096.0 6858.0 7620.0

5143.5 6000.8 6858.0 7715.3 8572.5

(TABLE

5-12

5715.0 6667.5 7620.0 8572.5 9525.0

I.D. 911215)

MANUFACTURER'S DATA

BHT-2121FR-FM-1 Table 5-4.

Baggage loading

BAGGAGE LOADING TABLE (ENGLISH) LOAD BAGGAGE FROM FORWARD END OF COMPARTMENT 400 POUND MAXIMUM WEIGHT (LB)

APPROX. CG (FS)

MOMENT

WEIGHT (LB)

APPROX. CG (FS)

MOMENT

20 40 60 80 100 120 140 160 180 200

245 247 249 251 253 255 257 259 261 263

4900 9880 14940 20080 25300 30600 35980 41440 46980 52600

220 240 260 280 300 320 340 360 380 400

265 267 269 271 273 275 277 279 281 283

58300 64080 69940 75880 81900 88000 94180 100440 106780 113200

BAGGAGE LOADING TABLE (METRIC) LOAD BAGGAGE FROM FORWARD END OF COMPARTMENT 181.4 KILOGRAMS MAXIMUM WEIGHT (KG)

APPROX. CG (MM)

MOMENT (KG · MM/100)

WEIGHT (KG)

APPROX.CG (MM)

MOMENT (KG MM/100)

10 20 30 40 50 60 70 80 90 100

6228 6284 6340 6396 6452 6507 6563 6619 6675 6734

622.8 1256.8 1902.0 2558.4 3226.0 3904.2 4594.1 5295.2 6007.5 6734.0

110 120 130 140 150 160 170 180 181.4

6789 6845 6901 6957 7013 7069 7125 7181 7188

7467.9 8214.0 8971.3 9739.8 10519.5 11310.4 12112.5 12925.8 13039.0 (TABLE

I.D. 911213)

5-13

MANUFACTURER'S DATA

BHT-2121FR-FM-1 Table 5-5. Fuel loading Helicopterserial numbersprior to 35049 ENGLISH ASTM D-1655 TYPE A, A-1, JP-5, AND JP-8 (6.8 LBS/GAL) QUANTITY (U.S. GAL) 10 20 30 40 50 60 70 *72.6 80 90 100 110 120 130 140 150 160 170 180 190 200 210 **216.8

WEIGHT (LB) 68 136 204 272 340 408 476 494 544 612 680 748 816 884 952 1020 1088 1156 1224 1292 1360 1428 1474

CG (IN) 143.6 143.6 140.2 134.8 131.6 129.4 127.9 127.6 128.3 130.6 134.6 137.8 140.4 142.6 144.6 146.1 147.6 148.8 149.9 150.9 151.9 152.7 153.3

MOMENT (IN-LB) 9765 19530 28601 36666 44744 52795 60880 63034 69795 79927 91528 103074 114566 126058 137659 149022 160589 172013 183478 194963 206584 218056 225964

ASTM D-1655 TYPE B AND JP-4 (6.5 LBS/GAL) QUANTITY (U.S. GAL) 10 20 30 40 50 60 70 '72.6 80 90 100 110 120 130 140 150 160 170 180 190 200 210 **216.8

WEIGHT (LB) 65 130 195 260 325 390 455 472 520 585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365 1409

CG (IN)

MOMENT (IN-LB)

143.6 143.6 140.2 134.8 131.6 129.4 127.9 127.6 128.3 130.6 134.6 137.8 140.4 142.6 144.6 146.1 147.6 148.8 149.9 150.9 151.9 152.7 153.3

9334 18668 27339 35048 42770 50466 58195 60227 66716 76401 87490 98527 109512 120497 131586 142448 153504 164424 175383 186362 197470 208436 216000

* Most critical fuel amount for most forward flight condition. * Most critical fuel amount for most aft flight condition. NOTE:All data aboverepresentsusable fuel basedon nominal densityat 15°C(59°F). (TABLE I.D. 911211)

5-14

MANUFACTURER'S DATA

BHT-2121FR-FM-1 Table 5-5. Fuel loading (Cont) Helicopterserial numbersprior to 35049 METRIC

ASTM D-1655 TYPE A, A-1, JP-5, AND JP-8 (0.815 KG/L)

LITERS 40 80 120 160 200 240 274.8 280 320 360 400 440 480 520 560 600 640 680 720 760 800 **820.7

WEIGHT (KG) 32.6 65.2 97.8 130.4 163.0 195.6 224.0 228.2 260.8 293.4 326.0 358.6 391.2 423.8 456.4 489.0 521.6 554.2 586.8 619.4 652.0 668.9

ASTM D-1655 TYPE B AND JP-4 (.779 KG/L)

CG (MM)

MOMENT KG * MM 100

LITERS

WEIGHT (KG)

3647 3647 3541 3399 3322 3272 3241 3246 3277 3368 3470 3541 3609 3665 3708 3744 3777 3805 3833 3858 3884 3894

1188.9 2377.8 3463.1 4432.3 5414.9 6400.0 7259.8 7407.4 8546.4 9881.7 11312.2 12698.0 14118.4 15532.3 16923.3 18308.2 19700.8 21087.3 22492.0 23896.5 25323.7 26047.0

40 80 120 160 200 240 *274.8 280 320 360 400 440 480 520 560 600 640 680 720 760 800 **820.7

31.2 62.3 93.5 124.6 155.8 187.0 214.1 218.1 249.3 280.4 311.6 342.8 373.9 405.1 436.2 467.4 498.6 529.7 560.9 592.0 623.2 639.3

CG (MM)

MOMENT KG * MM 100

3647 3647 3541 3399 3322 3272 3241 3246 3277 3368 3470 3541 3609 3665 3708 3744 3777 3805 3833 3858 3884 3894

1137.9 2272.1 3310.8 4235.2 5175.7 6118.6 6939.0 7079.5 8169.6 9443.9 10812.5 12138.5 13494.1 14846.9 16174.3 17499.5 18832.1 20155.1 21499.3 22839.4 24205.1 24894.3

* Most critical fuel amount for most forward flight condition. ** Most critical fuel amount for most aft flight condition. NOTE:All data above representsusablefuel basedon nominaldensity at 15°C(59°F). (TABLE

I.D. 911212)

5-15

MANUFACTURER'S DATA

BHT-2121FR-FM-1

Table 5-6. Fuel loading Helicopterserial numbers35049and subsequent ENGLISH ASTM D-1655 TYPE A, A-1, JP-5, AND JP-8 (6.8 LBS/GAL) QUANTITY (U.S. GAL) 10 20 30 40 50 60 70 *78.5 80 90 100 110 120 130 140 150 160 170 180 190 200 210 218.6

WEIGHT (LB) 68 136 204 272 340 408 476 534 544 612 680 748 816 884 952 1020 1088 1156 1224 1292 1360 1428 1486

CG (IN) 143.9 144.0 141.6 135.7 132.2 129.9 128.2 127.3 127.4 129.5 133.4 136.7 139.3 141.7 143.6 145.2 146.8 148.1 149.3 150.3 151.3 152.1 152.6

MOMENT (IN-LB) 9785 19584 28886 36910 44948 52999 61023 67953 69306 79254 90712 102252 113669 125263 136707 148104 159718 171204 182743 194188 205768 217199 226837

ASTM D-1655 TYPE B AND JP-4 (6.5 LBS/GAL) QUANTITY (U.S. GAL) 10 20 30 40 50 60 70 *78.5 80 90 100 110 120 130 140 150 160 170 180 190 200 210 218.6

WEIGHT (LB) 65 130 195 260 325 390 455 510 520 585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365 1421

CG (IN) 143.9 144.0 141.6 135.7 132.2 129.9 128.2 127.3 127.4 129.5 133.4 136.7 139.3 141.7 143.6 145.2 146.8 148.1 149.3 150.3 151.3 152.1 152.6

MOMENT (IN-LB) 9354 18720 27612 35282 42965 50661 58331 64955 66248 75758 86710 97741 108654 119737 130676 141570 152672 163651 174681 185621 196690 207617 216829

* Mostcritical fuel amountfor most forward flight condition. NOTE:All data aboverepresentsusablefuel basedon nominaldensity at 15°C(59°F). (TABLE

5-16

I.D. 911330)

MANUFACTURER'S DATA

BHT-2121FR-FM-1

Table 5-6. Fuel loading (Cont) Helicopterserial numbers35049and subsequent METRIC ASTM D-1655 TYPE A, A-1, JP-5, AND JP-8 (0.815 KG/L)

LITERS

WEIGHT (KG)

40 80 120 160 200 240 280 *297.1 320 360 400 440 480 520 560 600 640 680 720 760 800 827.4

32.6 65.2 97.8 130.4 163.0 195.6 228.2 242.1 260.8 293.4 326.0 358.6 391.2 423.8 456.4 489.0 521.6 554.2 586.8 619.4 652.0 674.3

CG (MM) 3655 3658 3561 3421 3340 3284 3246 3233 3249 3343 3434 3515 3579 3635 3683 3721 3757 3790 3818 3843 3866 3876

MOMENT KG * MM 100 1191.5 2385.0 3482.7 4461.0 5444.2 6423.5 7407.4 7827.1 8473.4 9808.4 11194.8 12604.8 14001.1 15405.1 16809.2 18195.7 19596.5 21004.2 22404.0 23803.5 25206.3 26135.9

ASTM D-1655 TYPE B AND JP-4 (.779 KG/L)

LITERS

WEIGHT (KG)

40 80 120 160 200 240 280 *297.1 320 360 400 440 480 520 560 600 640 680 720 760 800 827.4

31.2 62.3 93.5 124.6 155.8 187.0 218.1 231.4 249.3 280.4 311.6 342.8 373.9 405.1 436.2 467.4 498.6 529.7 560.9 592.0 623.2 644.5

CG (MM) 3655 3658 3561 3421 3340 3284 3246 3233 3249 3343 3434 3515 3579 3635 3683 3721 3757 3790 3818 3843 3866 3876

MOMENT KG * MM 100 1140.4 2278.9 3329.5 4262.6 5203.7 6141.1 7079.5 7481.2 8099.8 9373.8 10700.3 12049.4 13381.9 14725.4 16065.3 17392.0 18732.4 20075.6 21415.2 22750.6 24092.9 24980.8

* Most critical fuel amount for most forward flight condition. NOTE:All data aboverepresentsusable fuel basedon nominaldensity at 15°C(59°F). (TABLE

I.D. 911329)

5-17

MANUFACTURER'S DATA

BHT-2121FR-FM-1

SAMPLE LOADING PROBLEM (ENGLISH UNITS) HELICOPTER SERIAL NUMBERS PRIOR TO 35049 FIRST LEG WEIGHT (LBS)

o

CG (INCHES)

MOMENT (IN-LBS)

Licensed Empty Weight

6529.4

939996

+Oil +Pilot +Passengers (5 man seat) +Passengers (4 man seat) +Baggage

24.5 *170.0 *850.0 '680.0 *180.0

4146 7990 99450 59160 46980

Basic Operating Weight + Payload

8433.9

1157722

Basic Operating Weight + Payload

8433.9

1157722

+Takeoff Fuel (216.8 gallons Type B)

1409.0

Takeoff Weight, CG & Moment

9842.9

Basic Operating Weight + Payload

8433.9

216000 139.6

1373722 1157722

+Critical Fuel (72.6 gallons Type B)

*472.0

Critical Weight, CG & Moment

8905.9

60227

Basic Operating Weight + Payload

8433.9

1157722

+Landing Fuel (60 gallons Type B)

*390.0

50466

Landing Weight, CG & Moment

8823.9

136.8

136.9

1217949

1208188

(* Information obtained from loading charts) (TABLE I.D. 911217)

5-18

MANUFACTURER'S DATA

BHT-2121FR-FM-1

SAMPLE LOADING PROBLEM (ENGLISH UNITS) HELICOPTER SERIAL NUMBERS PRIOR TO 35049 SECOND LEG WEIGHT (LBS)

CG (INCHES)

MOMENT (IN-LBS)

Licensed Empty Weight

6529.4

939996

+Oil +Pilot Basic Operating Weight (No Payload)

24.5 *170.0 6723.9

4146 7990 952132

+Takeoff Fuel (216.8 gallons Type B)

*1409.0

Takeoff Weight, CG & Moment

8132.9

Basic Operating Weight (No Payload)

6723.9

+Critical Fuel (72.6 gallonsType B)

60227

7195.9

Basic Operating Weight (No Payload)

6723.9

Fuel (60 gallons Type B)

Landing Weight, CG & Moment

1168132 952132

*472.0

Critical Weight, CG & Moment

+Landing

216000 143.6

140.7

952132

*390.0 7113.9

1012359

50466 140.9

1002598

(TABLEI.D. 911218)

5-19

MANUFACTURER'S DATA

BHT-2121FR-FM-1

SAMPLE LOADING PROBLEM (METRIC UNITS) HELICOPTER SERIAL NUMBERS PRIOR TO 35049 FIRST LEG WEIGHT (KG)

CG (MM)

MOMENT (KG-MM 100)

2961.7

108298.7

11.1 *90.0

477.7 1074.6

+Passengers (5 man seat) +Passengers (4 man seat) +Baggage

*375.0 *300.0 *80.0

11145.0 6630.0 5295.2

Basic Operating Weight + Payload Basic Operating Weight + Payload

3817.8 3817.8

132921.2 132921.2

+Takeoff Fuel (820.7 liters Type B)

*639.3

24894.3

Takeoff Weight, CG & Moment

4457.1

157815.5

Basic Operating Weight + Payload

3817.8

+Critical Fuel (274.8 liters Type B)

'214.1

Critical Weight, CG & Moment

4031.9

Basic Operating Weight + Payload

3817.8

132921.2

+Landing Fuel (227.1 liters Type B)

*176.9

5814.5

Landing Weight, CG & Moment

3994.7

Licensed Empty Weight +Oil

+Pilot

3541

132921.2 6939.0 3469

139860.2

138735.7

3473

(* Information obtained from loading charts) (TABLE

5-20

I.D. 911219)

MANUFACTURER'S DATA

BHT-2121FR-FM-1

SAMPLE LOADING PROBLEM (METRIC UNITS) HELICOPTER SERIAL NUMBERS PRIOR TO 35049 SECOND LEG

WEIGHT (KG) Licensed Empty Weight

CG (MM)

MOMENT (KG*MM 100)

2961.7

108298.7

11.1

+Oil +Pilot *90.0 Basic Operating Weight (No Payload)

3062.8

477.7 1074.6 109851.0

+Takeoff Fuel (820.7 liters Type B)

*639.3

24894.3

Takeoff Weight, CG & Moment

3702.1

Basic Operating Weight (No Payload) +Critical Fuel (274.8 liters Type B)

3062.8

3276.9

Basic Operating Weight (No Payload)

3062.8

Landing Weight, CG & Moment

6939.0 3564

116790.0 109851.0

*176.9 3239.7

134745.3 109851.0

*214.1

Critical Weight, CG & Moment

+Landing Fuel (227.1 liters Type B)

3640

5814.5 3570

115665.5 (TABLEI.D. 911220)

5-21

MANUFACTURER'S DATA

BHT-212IFR-FM-1

SAMPLE LOADING PROBLEM (METRIC UNITS) HELICOPTER SERIAL NUMBERS PRIOR TO 35049 SECOND LEG

WEIGHT (KG) Licensed Empty Weight +Oil

+Pilot Basic Operating Weight (No Payload)

MOMENT (KG*MM 100)

CG (MM)

2961.7

108298.7

11.1

477.7

'90.0

1074.6

3062.8

109851.0

+Takeoff Fuel (820.7 liters Type B)

*639.3

24894.3

Takeoff Weight, CG & Moment

3702.1

Basic Operating Weight (No Payload) +Critical Fuel (274.8 liters Type B)

3062.8

109851.0

*214.1

6939.0

Critical Weight, CG & Moment

3276.9

Basic Operating Weight (No Payload)

3062.8

+Landing Fuel (227.1 liters Type B)

'176.9

Landing Weight, CG & Moment

3239.7

3640

134745.3

3564

116790.0 109851.0 5814.5

3570

115665.5 (TABLE

I.D. 911220)

5-21

MANUFACTURER'S DATA

BHT-2121FR-FM-1

SAMPLE LOADING PROBLEM (ENGLISH UNITS) HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT FIRST LEG WEIGHT (LBS)

CG (INCHES)

MOMENT (IN-LBS)

+Pilot

6529.4 24.5 *170.0

939996 4146 7990

+Passengers (5 man seat) (4 man seat) +Passengers +Baggage

*850.0 *680.0 *180.0

99450 59160 46980

Basic Operating Weight + Payload

8433.9

1157722

Basic Operating Weight + Payload

8433.9

1157722

*1421.0

216829

Licensed Empty Weight +Oil

+Takeoff Fuel (218.6 gallons Type B)

139.5

1374551

Takeoff Weight, CG & Moment

9854.9

Basic Operating Weight + Payload

8433.9

1157722

+Critical Fuel (78.5 gallons Type B)

*510.0

64955

Critical Weight, CG & Moment

8943.9

Basic Operating Weight + Payload

8433.9

1157722

+Landing Fuel (60 gallons Type B)

*390.0

50661

Landing Weight, CG & Moment

8823.9

136.7

136.9

1222677

1208383

(* Information obtained from loading charts) (TABLE

5-22

I.D. 911328)

MANUFACTURER'S DATA

BHT-2121FR-FM-1

SAMPLE LOADING PROBLEM (ENGLISH UNITS) HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT SECOND LEG WEIGHT (LBS)

CG (INCHES)

MOMENT (IN-LBS)

Licensed Empty Weight

6529.4

939996

+Oil +Pilot Basic Operating Weight (No Payload)

24.5 *170.0 6723.9

4146 7990 952132

+Takeoff Fuel (218.6 gallons Type B)

'1421.0

216829

Takeoff Weight, CG & Moment

8144.9

Basic Operating Weight (No Payload)

6723.9

952132

+Critical Fuel (78.5 gallonsType B)

*510.0

64955

Critical Weight, CG & Moment

7233.9

Basic Operating Weight (No Payload)

6723.9

952132

+Landing Fuel (60 gallons Type B)

*390.0

50661

Landing Weight, CG & Moment

7113.9

143.5

140.6

141.0 (TABLE

1168961

1017087

1002793 I.D. 911327)

5-23

MANUFACTURER'S DATA

BHT-2121FR-FM-1

SAMPLE LOADING PROBLEM (METRIC UNITS) HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT FIRST LEG WEIGHT (KG)

CG (MM)

MOMENT (KG*MM 100)

2961.7

108298.7

11.1 *90.0

477.7 1074.6

+Passengers (5 man seat) +Passengers (4 man seat) +Baggage

*375.0 *300.0 *80.0

11145.0 6630.0 5295.2

Basic Operating Weight + Payload Basic Operating Weight + Payload

3817.8 3817.8

132921.2 132921.2

+Takeoff Fuel (827.4 liters Type B)

*644.5

24980.8

Takeoff Weight, CG & Moment

4462.3

Basic Operating Weight + Payload

3817.8

132921.2

+Critical Fuel (297.1 liters Type B)

*231.4

7481.2

Critical Weight, CG & Moment

4049.2

Basic Operating Weight + Payload

3817.8

+Landing Fuel (227.1 liters Type B)

'176.9

Landing Weight, CG & Moment

3994.7

Licensed Empty Weight +Oil +Pilot

157902.0

3539

3467

140402.4 132921.2 5838.8

3474

138760.0

(* Information obtained from loading charts) (TABLE

5-24

I.D. 911326)

MANUFACTURER'S DATA

BHT-2121FR-FM-1

SAMPLE LOADING PROBLEM (METRIC UNITS) HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT SECOND LEG

WEIGHT (KG)

-

CG (MM)

MOMENT (KG'MM 100)

Licensed Empty Weight

2961.7

108298.7

+Oil +Pilot Basic Operating Weight (No Payload)

11.1 90.0 3062.8

477.7 1074.6 109851.0

+Takeoff Fuel (827.4 liters Type B)

*644.5

Takeoff Weight, CG & Moment

3707.3

Basic Operating Weight (No Payload) +Critical Fuel (297.1 liters Type B)

3062.8

Critical Weight, CG & Moment

3294.2

Basic Operating Weight (No Payload)

3062.8

+Landing Fuel (227.1 liters Type B)

'176.9

Landing Weight, CG & Moment

3239.7

24980.8 3637

134831.8 109851.0

*231.4

7481.2 3562

117332.2 109851.0 5838.8

3571

115689.8 (TABLE I.D. 911325)

5-25/5-26

MANUFACTURER'S DATA

*

BHT-2121FR-FM-1

Appendix A A-1. OPTIONALEQUIPMENT

or install such changes, additions,

Bell Helicopter Textron's

manufactured. previously previously manufactured.

policy is one of

continuous product improvement. Bell reserves the right to incorporate design changes, make additions to, and improve

its product without imposing any obligation

upon the company to furnish for Table A-1.

improvements, etc., on products Flight manual supplement for each kit listed in table A-1 must be carried in helicopter at all times if subject kit is

installed.

FLIGHT MANUAL SUPPLEMENTS

NAME OF EQUIPMENT

KIT NUMBER

FAA APPROVED

REVISION NO.

BHT-212-FMS-1 Litters

205-706-047

01 MAR 72

Reissue 14 AUG 95

BHT-212-FMS-2 Winterization Heater

212-706-008

29 OCT 70

Reissue 14 AUG 95

BHT-212-FMS-3 Cargo Hook

212-706-103

29 OCT 70

Revision 1 12 SEP 97

BHT-212-FMS-4 Auxiliary Fuel Tanks

205-706-044 205-706-045

29 OCT 70

Revision 1 12 SEP 97

BHT-212-FMS-5 Internal Rescue Hoist (Breeze)

205-706-030

01 MAR 71

Reissue 14 AUG 95

BHT-212-FMS-6 Fixed Floats

205-706-050

01 APR 71

Reissue 14 AUG 95

18 AUG 72

Revision 1 12 SEP 97

BHT-212-FMS-7 Category A Operations BHT-212-FMS-8 Emergency Flotation

212-706-021

28 AUG 72

Reissue 14 AUG 95

BHT-212-FMS-9 Emergency Flotation

212-706-042

09 AUG 73

Reissue 14 AUG 95

BHT-212-FMS-10.1

Incorporated into

Battery Temperature Sensor

basic manual.

Rev. 2

A-1

MANUFACTURER'S DATA

BHT-212IFR-FM-1 Table A-1.

FLIGHT MANUAL SUPPLEMENTS

NAME OF EQUIPMENT

KIT NUMBER

BHT-212-FMS-10.2

Incorporated

(Cont)

FAA APPROVED

REVISION NO.

Into

Battery Temperature Sensor

basic manual.

BHT-212-FMS-11 VLF-1000 Navigation System

212-899-118

21 MAY 74

Reissue 14 AUG 95

BHT-212-FMS-12 Heated Windshield

212-899-244

03 JUN 74

Reissue 14 AUG 95

BHT-212-FMS-13 Environmental Control Unit

212-706-025 (30597 and sub)

17 JUN 74

Reissue 14 AUG 95

BHT-212-FMS-14 20/90 Auxiliary Fuel

212-899-243

30 OCT 74

Reissue 14 AUG 95

212-899-131 BHT-212-FMS-15 KNC 610 Area Navigation System

20 NOV 74

Reissue 14 AUG 95

Tanks

BHT-212-FMS-16 Heated Windshield

212-706-053 (30554 and sub)

01 NOV 74

Reissue 14 AUG 95

BHT-212-FMS-17 Internal Rescue Hoist (Western Gear)

214-706-003

20 NOV 75

Reissue 14 AUG 95

BHT-212-FMS-18 AFCS/Autopilot

212-961-620 (30597 thru 30849)

15 DEC 76

Reissue 14 AUG 95

BHT-212-FMS-19 AFCS/Autopilot

212-706-111 (30850 and sub)

14 JUN 77

Reissue 14 AUG 95

BHT-212-FMS-20 Altitude Hold System

212-899-143

12 DEC 77

Reissue 14 AUG 95

BHT-212-FMS-21

212-899-375

29 JAN 80

Reissue 14 AUG 95

Crash Position Indicator (Argentine Air Force) BHT-212-FMS-22 Transmission

212-040-001-131

BHT-212-FMS-23

Incorporated into

PT6T-3B Engine

basic manual

A-2

Rev.2

MANUFACTURER'S DATA

BHT-2121FR-FM-1

Table A-1.

FLIGHT MANUAL SUPPLEMENTS (Cont)

NAME OF EQUIPMENT

KIT NUMBER

BHT-212-FMS-24 Seat Cushion BHT-212-FMS-25 Fixed Step

FAA APPROVED

REVISION NO.

212-706-019

24 JUL 87

Reissue 14 AUG 95

212-706-057

27 SEP 89

Reissue 14 AUG 95

09 NOV 89

Reissue 14 AUG 95

BHT-212-FMS-28 214-706-003 Two-Speed Internal Hoist

07 MAY 92

Reissue 14 AUG 95

BHT-212-FM-29 Increased Takeoff

212-704-153

16 DEC 91

Reissue 14 AUG 95

412-706-028

18 JUN 93

Reissue 14 AUG 95

28 JUL 94

Original

BHT-212-FMS-CAN-26 Internal Rescue Hoist and Cargo Hook

BHT-212-FMS-27 Alternate Static Air Valve

Incorporated into basic manual

Horsepower BHT-212-FMS-30 Airline Passenger

Seating BHT-212-FMS- 31

Reserved

BHT-212-FMS-32 Engine No. 2 Governor

TB 212-93-145

BHT-212-FMS-33 Bendix/King RDS 81 Weather Radar

212-899-234

07 OCT 94

Original 07 OCT 94

BHT-212-FMS-34 212-899-835 TRIMPAC GPS Navigator

07 OCT 94

Reissued 24 FEB 95

BHT-212-FMS-35 Increased Weight

22 MAR 96

Original issue

28 JUL 94

Trim Actuator

Altitude Temperature Limit

212-704-129 212-704-153

Rev. 2

A-3/A-4