Bell Helicopter manual

8/10/2019 Bell Helicopter manual

1/585

POST OFFICE BOX 482 FORT WORTH, TEXAS 76

BHT-212IFR-FM-

COPYRIGHT NOTICE

COPYRIGHT 2002

BELL HELICOPTER TEXTRON INC.

AND BELL HELICOPTER TEXTRON

CANADA LTD.

ALL R IGHTS RESER VED

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

ROTORCRAFTFLIGHT MANUAL

14 AUGUST 199REVISION 4 02 DECEMBER 200


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BHT-212IFR-FM

NOTE

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

LOG OF REVISIONS

Original ....................... 0.................... 29 JUN 73

Reissue....................... 0....................14 AUG 95

Revision...................... 1....................29 MAY 96

Revision ......................2 ....................12 SEP 9

Revision ......................3 ................... 01 MAY 9

Revision ......................4 ................... 02 DEC 0

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02 DEC 2002 Rev. 4 A/


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BHT-212IFR-FM

LOG OF FAA APPROVED REVISIONS

Original ....................... 0.................... 29 JUN 73

Reissue....................... 0....................14 AUG 95

Revision ..................... 1....................29 MAY 96

Revision ......................2 ....................12 SEP 9

Revision ......................3 ................... 01 MAY 9

Revision ......................4 ................... 02 DEC 0

02 DEC 2002 Rev. 4 C/

DATE:

MANAGER

ROTORCRAFT CERTIFICATION OFFICEFEDERAL AVIATION ADMINISTRATIONFT. WORTH, TX 76193-0170

APPROVED:


5/585


6/585

BHT-2121FR-FM-1

FAA

APPROVED

SHOULD

has been

used

only

when

HD

Density

altitude

application

of

a procedure

is

recommended.

recommended.

HP

Pressure altitude

MAY and NEED NOT

have been used HSI

Horizontal situation

only when application

of a procedureindicator

is optional.

HTR

Heater

WILL has been used only to indicate HV Height-velocity

futurity,

never

to

indicate

a

mandatory

procedure.

HYDRSYS

Hydraulic system

IFR

Instrument

flight

ABBREVIATIONS

AND

ACRONYMS

rules

IGE

In ground

effect

Abbreviations

and

acronyms

used

IMC

Instrument

throughout

this

manual

are defined

as

Meteorological

follows:

Conditions

INCR

Increase

AC

Alternating

current

INTCON

Interconnect

AFCS

Automatic

flight

control system INV Inverter

AGL

Above ground level ITT

Interturbine

temperature

ATTD

Attitude

KCAS

Knots calibrated

BLWR

Blower

airspeed

C

Celsius

KG

Kilogram(s)

CDP

Critical

decision

KIAS

Knots

indicated

point

airspeed

CG

Center

of gravity

LB

Pound(s)

CMD

Command

LDP

Landing

decision

DC Direct current point

DECR

Decrease

M

Meter(s)

DSENGA

Disengage

MCP Maximum

continuous

power

ELT

Emergency

locator

transmitter

MIN

Minimum,

minute(s)

ENG

Engine NAV

Navigation

ENGA

Engage

NON ESS

Non essential

ENG RPM

(N

2

) Engine power

NORMNormal

turbine

rpm

OAT

Outside

air

F Fahrenheit temperature

FT Foot, feet OEI One engine

inoperative

GAS

PROD

(N1)

Gas producer

rpm

Out of

ground

effect

OGE

Out

of ground effect

GEN

Generator

PART

SEP

Particle

separator

GOV

Governor

PLT

Pilot

GW

Gross

weight

PRI

Primary

ii


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FAA

APPROVED

BHT-2121FR-F

REL

Release

VMC

Visual

ROTOR

(N)

Rotor

RPM

Meteorological

Conditions

RPM

Revolutions

per

minute

VMI

N

Minimum

speed fo

instrument

(IFR)

SCAS

Stability

and

control

flight

augmentation

system

VNE Never exceed spee

STA

Station

tation

VTOCS

Takeoff

climbout

TEMP

CONT

Temperature

control

speed

VCAL

Calibrated

airspeed

VTOSS

Takeoff

safety

spe

VFR

Visual

flight

rules

XFEED

Crossfeed

VG

Vertical

gyro

.

VIAS

Indicated airspeed


8/585

FAA

APPROVED

BHT-2121FR-FM-

Section

1

TABLE

OF CONTENTS

Page

Subject

Paragraph

Number

INTRODUCTION

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

1-1

...........

1-3

BASIS

OF CERTIFICATION

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

1-3

TYPES

OF

OPERATION

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

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

1-3

FLIGHT

CREW

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

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

1-3

IFR

OPERATION

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

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

1-3

IFR

CARGO

OPERATION

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

1-4-B

........

1-3

VFR

OPERATION

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

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

1-3

VFR

CARGO

OPERATION

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

1-4-D

........

1-4

CONFIGURATION

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

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

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

1-4

REQUIRED

EQUIPMENT

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

1-5-A

........

1-4

OPTIONAL

EQUIPMENT

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

1-5-B

........

1-4

DOORS

OPEN/REMOVED

(VMC ONLY)

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

1-5-C

........

1-4

PASSENGERS

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

.. 1-5-D

.......

1-4

CARGO

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

1-5-E

........

1-4A

WEIGHT

AND

CENTER

OF GRAVITY

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

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

1-5

WEIGHT

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

1-6-A

........

1-5

CENTER OF GRAVITY ...................................... 1-6-B

........

1-5

AIRSPEED

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

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

1-5

ALTITUDE

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

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

1-6

MANEUVERING

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

1-9...........

1-6

PROHIBITED

MANEUVERS

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

1-9-A

.......

1-6

CLIMB

AND DESCENT

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

1-9-B

........

1-6

HEIGHT-VELOCITY

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

1-10 .........

1-6

AMBIENT

TEMPERATURES

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

1-11 .........

1-6

ELECTRICAL

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

1-12

.........

1-6

BATTERY

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

1-12-A

.......

1-6

GENERATOR

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

1-12-B

....... 1-7

STARTER

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

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

1-7

GROUND

POWER

UNIT

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

1-12-D.......

1-7

POWER PLANT

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

1-13 .........

1-7

GAS

PRODUCER

RPM

(N) .................................

1-13-A

.......

1-7

POWER

TURBINE

RPM.....................................

1-13-B

......

1-8

INTERTURBINE

TEMPERATURE

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

1-13-C

......

1-8

ENGINE

TORQUE ...........................................

1-13-D

.......

1-8

FUEL

RESSURE.....................................

.....

-13-E

...

1-9

ENGINE

OIL PRESSURE

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

1-13-F

...... 1-9

ENGINE

OIL TEMPERATURE

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

1-13-G

.......

1-9

COMBINING

GEARBOX

OIL

PRESSURE

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

1-13-H

.......

1-9

COMBINING

GEARBOX

OIL

TEMPERATURE

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

1-13-J

....... 1-9

Rev. 2 1


9/585

BHT-2121FR-FM-1

FAA APPROVED

TABLE

OF CONTENTS

(Cont)

Page

Subject

Paragraph

Number

TRANSMISSION ................................................. 1-14 ......... 1-9

TRANSMISSION OIL

PRESSURE...........................

1-14-A ....... 1-9

TRANSMISSION OIL TEMPERATURE ...................... 1-14-B ....... 1-9

TRANSMISSION TORQUE .................................. 1-14-C ....... 1-9

ROTOR ..........................................................

1-15

......... 1-10

ROTOR RPM - POWER ON ................................

1-15-A

....... 1-10

ROTOR RPM - POWER OFF ............................... 1-15-B ....... 1-10

HYDRAULIC ..................................................... 1-16 ......... 1-10

HYDRAULIC PRESSURE ................................... 1-16-A ....... 1-10

HYDRAULIC TEMPERATURE ..............................

1-16-B

....... 1-10

FUEL AND

OIL ..................................................

1-17 ......... 1-10

FUEL ........................................................ 1-17-A ....... 1-10

OIL ENGINE AND COMBINING

GEARBOX................

1-17-B ....... 1-10

OIL TRANSMISSION,

INTERMEDIATE AND

TAIL ROTOR

GEARBOX .................................................. 1-17-C ....... 1-10

ROTOR BRAKE.................................................. 1-18 ......... 1-11

LANDING GEAR ................................................. 1-19 ......... 1-11

INSTRUMENT MARKINGS AND PLACARDS ................... 1-20 ......... 1-11

HEATER .........................................................

1-21

......... 1-11

LIST OF FIGURES

Figure Page

Title Number Number

Instrument

markings ............................................

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

1-13

Placards and decals ............................................ 1-2........... 1-19

Gross weight center of gravity chart .......................... 1-3........... 1-21

Weight-altitude

temperature limitations

for takeoff, landing

and in ground effect

maneuvers chart.........................

1-4........... 1-22

Single engine height velocity chart............................ 1-5........... 1-23

1-2

Rev.

2


10/585

FAA APPROVED BHT-212IFR-FM

02 DEC 2002 Rev. 4 1

Section 1LIMITATIONS

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 placards represent aerodynamic

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 actionrequired.

1-2. BASIS OFCERTIFICATION

This helicopter is certified under FAR Part 29,

Category B.

1-3. TYPES OF OPERATIONThis helicopter is certified for VFR and

Category 1 IFR operations under IFR day and

night, non-icing conditions.

1-4. FLIGHT CREW

1-4-A. IFR OPERATION

Minimum flight crew for IFR operation, excep

as noted below, shall consist of two pilot

each of which must hold a helicopte

instrument rating.

1-4-B. IFR CARGO OPERATION

Refer to applicable operating rules

for internal cargo operations.

1-4-C. VFR OPERATION

Minimum cockpit (FS 47.0) weight is 17

pounds (77.1 kilograms). Refer to Section 5.

Minimum flight crew consists of one pilot wh

shall operate helicopter from right crew seat

Left crew seat may be used for an addition

pilot for VFR day and night operations whe

approved dual controls and copilot instrume

kits are installed.

NOTE


11/585

BHT-212IFR-FM-1 FAA APPROVED

1-4 Rev. 4 02 DEC 2002

1-4-D. VFR CARGO OPERATION

Refer to applicable operating rules

for internal cargo operations.

1-5. CONFIGURATION

1-5-A. REQUIRED EQUIPMENT

(*) Designates required equipment for VFR

flight.

(*)Operable force trim system.

(*)Heated pitot-static system.

(*)Pilot windshield wiper.

Operational AFCS.

Two VHF communication radios

Two navigation receivers with auxiliary

equipment appropriate for intended route of

flight.

DME equipment.

ATC transponder.

Marker beacon receiver.

Standby attitude indicator or gyro rate of turn

indicator.

Pilot IVSI.

Roof window blackout curtains

Dual controls.

Copilot instruments.

Copilot clock.

1-5-B. OPTIONAL EQUIPMENT

Refer to appropr ia te F l ight 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:

Both crew doors removed.

Both sliding doors locked open or removed

with both hinged panels installed or removed.

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.

1-5-D. PASSENGERS

NOTE

Refer to Section 5 for loading

tables to be used in weight/CG

computations.

With the passenger seat kit installed, the

helicopter is certified for operations as afifteen place aircraft.

The above loading does not apply if cargo

or a combination of cargo and passengers

are being transported. It shall be the

responsibi l i ty of the p i lot to ensure

NOTE


12/585

FAA

APPROVED

BHT-2121FR-FM-1

helicopter

is

properly

loaded

so

entire

1-5-E.

CARGO

flight is conducted within the limits of

gross

weight

center

of gravity

charts

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).

Deck

mounted

tiedown

fittings

are

provided

and

have an

airframe

structural

capacity

of

1250

Rev. 2 1-4A/1-4


13/585

FAA

APPROVED

BHT-2121FR-FM

pounds

(567.0

kilograms)

vertical

and 500

NOTE

pounds

(226.8 kilograms)

horizontal per

fitting. Provisions for installation

of cargo Station 0

(datum) is located 20

tiedown fittings

are incorporated

in aft inches

(508.0 millimeters)

aft of

cabin

bulkhead

and transmission

support

most forward

point of cabin

nose.

structure

and have an airframe

structural

capacity

of 1250

pounds

(567.0

kilograms)

1-6-B-2.

LATERAL

CENTER

OF

at 90 degrees to bulkhead and 500 pounds GRAVITY

(226.8 kilograms)

In any direction

parallel

to bulkhead.

Cargo

shall

be secured

by an

Lateral

CG limits

are 3.5

inches

(88.9

approved

restraint

method

that

will

not

millimeters)

from

fuselage

centerline

fo

impede

access

to

cargo

in

an emergency.

IFR.

All

cargo and equipment

must be securely

tied

down

when operating

with

aft cabin

Lateral

CG

limits

are 4.7 inches

(119.

doors

open or

removed.

millimeters)

left

and 6.5 inches

(165.1

millimeters) right of fuselage centerline fo

I

1-5-E-2. BAGGAGE

VFR.

The

baggage

compartment

maximum

1-7. AIRSPEED

allowable loading is 400 pounds (181.4

kilograms),

not to

exceed 100 pounds

per VMIN

(IFR) - 40

KIAS.

square

foot (4.9

kilograms/100

square

centimeters).

NOTE

Due to

control authorities

1-6.

WEIGHT

AND

CENTER

OF

required

for

flight at

airspeeds

GRAVITY

below

40 KIAS, AFCS

ATTD

mode

should

not

be utilized

except

for

ground

checks.

1-6-A.

WEIGHT

VNE

(IFR or

VFR) - 120 KIAS

from sea

Maximum

GW

is 11,200

pounds

(5080.3

level

up to and

including

3000

feet HD a

kilograms).

8800 pounds (3991.6 kilograms) or less

GW

decreasing

linearly

to

VNE

of

100

KIAS

Refer

to Weight-altitude-temperature

at 11,200

pounds (5080.3

kilograms)

G

CG of 132.0 to

142.5. Refer to

OPERATIN

limitations

for

takeoff,

landing

and

in

LIMITATIONS

decal

figure

1-2 V

ground effect

maneuvers

chart (figure

1-4). decreases

3 KIAS

per 1000

feet above 300

feet

HD.

1-6-B.

CENTER

OF

GRAVITY

VNE

(VFR

only)(CG

142.5

to

144.0)

- 11

KIAS

from

sea level

up to

and Including

1-6-B-1.

LONGITUDINAL

CENTER

3000 feet H

D

at 10,000 pounds

(453

OF GRAVITY

kilograms)

or less GW decreasing linearl

to

VNE

of 100

KIAS at 11,200 pounds

(5080.3 kilograms) GW, CG of 142.5 to

Longitudinal CG operational range Is 144.0. Refer to OPERATING LIMITATIONS

variable

(figure

1-3),

depending

upon

GW,

decal,

igure

1-2.

VNE

decreases

3 KIAS

and shall

be computed

from

weight

and per

1000 feet

above 3000

feet H

balance data.

VNE

(VFR

only) doors

open

or removed

-

Longitudinal

CG

limits

are from

station

100 KIAS

for

any GW.

Refer

to Type

o

132.0

to

142.5

for

IFR.

Operation.

Longitudinal

CG limits

are from

station

Maximum

airspeed

when

above

maximum

132.0 to

144.0 for

VFR.

continuous

torque

(87.5%)

is 80

KIAS.

Rev.2 1-


14/585

BHT-2121FR-FM-1 FAA APPROVED

1-8.

ALTITUDE

which a

safe power

off landing

can be

made.

Maximum

operating-

20,000 feet

Hp.

When

takeoffs

are

made

in

accordance

Refer to applicable

operating rules

for high with

HV charts, proceed

as follows:

altitude

oxygen

requirements.

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

IN MANUAL

FUEL VTOCS.

CONTROL MODE

Above 15,000 feet

Hp, restart shall be

NOTE

accomplished

in manual fuel control mode

Downwind takeoffs are not

only.

(No airspeed restrictions.)

recommended

since published

takeoff

distance performance

will

Below 15,000 Hp, restart may be attempted not be achieved. When near zero

in either manual or automatic fuel control wind conditions prevail, determine

mode.

true

direction

of

wind.

1-9.

MANEUVERING

1-11.

AMBIENT

TEMPERA-

TURES

1-9-A. PROHIBITED MANEUVERS

Maximum sea level ambient air

Aerobatic

maneuvers

are prohibited.

temperature

for operation

is +52

C (+125

F) and decreases with altitude at standard

lapse rate (2 C per 1000 feet Hp).

1-9-B. CLIMBAND DESCENT

Minimum ambient air temperature at all

altitudes is -54

C (-65 F). Refer

to

Refer to

Section

4, PERFORMANCE.

Weight-altitude-temperature

limitations

for

takeoff, landing and in ground effect

maneuvers chart (figure 1-4).

1-10.

HEIGHT-VELOCITY

The height-velocity

limitations

are critical

1-12. ELECTRICAL

in the event of a single engine failure

during takeoff, landing, or other operation

near

the

surface

(figure

1-5).

The

AVOID

1-12-A.

BATTERY

area of the Height-Velocity chart defines

the

combinations of airspeed and heightabove 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

FOR ENGINE START AFTER

Weight-Altitude-Temperature limitations ILLUMINATION OF BATTERY

are not exceeded (figure 1-4).

The diagram TEMP LIGHT(IF

INSTALLED).

does not define the conditions which BATTERY SHALL BE REMOVED

assure continued flight

following an AND SERVICED

IN ACCORDANCE

engine failure nor

the conditions from WITH

MANUFACTURER

1-6


15/585

FAA APPROVED BHT-2121FR-FM-

INSTRUCTIONS PRIOR TO

RETURNING

BATTERY TO

28 vdc ground power units for

starting

SERVICE.

shall be rated at

a minimum of 400 amps

and limited to a maximum of 1000 amps.

Maximum battery

case

temperature

54.5

C

(130

F)

Maximum battery

1-13. POWER

PLANT

internal

internal 62.7 C (145 F) PRATT AND WHITNEY CANADA PT6T

) 3B and PT6T-3.

1-12-B. GENERATOR

NOTE

Operation in 2 1/2 minute or 30

Maximum

- 150 amps per

ammeter.

minute

OEI range is intended

for

emergency

use only,

when one

NOTE

engine becomes

inoperative

due

to actual malfunction. OEI ranges

To

attain published single engine

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. TWIN ENGINE

scale

momentarily

during

OPERATION

generator assisted start of second

engine.

PT6T-3B (Gage P/N 212-075-037-101)

Continuous

operation

61 to 100.8%

1-12-C. STARTER

Maximum

continuous 100.8%

Maximum

for takeoff

100.8%

Limit

starter energizing

time to:

Maximum transient

(not to exceed 30

30 seconds - ON.

seconds)

102.4%

60 seconds - OFF.

30 seconds - ON.

5 minutes

-

OFF.

NOTE

30

seconds

- ON.

Either

gage

shall

be installed

in

15 minutes - OFF. pairs.

Above energizing cycle may then be PT6T-3B (Gage

P/N

212-075-037-113)

repeated.

Continuous

operation

61 to

101.8%

Maximum continuous 101.8%

Above 15,000 Hp, restart shall

be Maximum

101.8%

accomplished in manual fuel control mode Maximum

Maximum transient

(not to exceed 30

Below 15,000 Hp, restart may be attempted seconds) 103.4%

in either manual or automatic fuel control

mode.

PT6T-3

Maximum continuous 100%

Maximum transient

(not to exceed 10

seconds)

101.5%

1-12-D.

GROUND POWER

UNIT

Rev.2 1-


16/585

BHT-2121FR-FM-1

FAA

APPROVED

1-13-A-2.

ONE

ENGINE

PT6T-3B

(SINGLE

ENGINE

OPERATION)

INOPERATIVE

(OEI)

30

Minute

OEI

range

765

to 822

C

2'/2 Minute OEI range 822 to 850 C

PT6T-3B(Gage P/N

212-075-037-101)

Maximum OEI

850 C

21/2

Minute

range

100.8

to 102.4%

Maximum

102.4%

PT6T-3

5 Minute range (twin

PT6T-3B(Gage P/N 212-075-037-113) engine operation) 765 to 810 C

21/2

Minute range

101.8

to 103.4%

30 Minute

range

Maximum

103.4% (OEI)

765 to 810

C

Maximum

continuous

limit (Single

or

twin

1-13-B.

POWER

TURBINE

RPM

engine

operation

765

transient

limit

PT6T-3B

or PT6T-3

(Max

5 second

Takeoff

100%

above

810 C)

850 C

I

Minimum 97% Starting transient limit

Continuous

Operation

97

to 100%

(Not

to

exceed

2

Maximum

continuous

seconds

above

810C).

1090

C.

operation

100%

Transient

(not

to

exceed

10 seconds)

101.5%

1-13-D.

ENGINE

TORQUE

1-13-C.

INTERTURBINE

NOTE

TEMPERATURE

For

normal

twin

engine

operation,

maximum

permissible

torque

needle

split is 4%

total

PT6T-3B (TWIN ENGINE OPERATION) needle split is 4% total

Continuous

operation

300

to

765

C

Maximum

continuous

765

C

1-13-D-1.

ONE

ENGINE

5 Minute

takeoff range

765 to 810

C

INOPERATIVE

(OEI)

Maximum

for takeoff

810

C

(ENGINE

SCALE)

Maximum

transient

(Not

to

exceed

5

seconds)

850

C

PT6T-3B

- TORQUEMETERS

MARKED

Maximum

for

starting

71.8%

(Not

to

exceed

2

Maximum

seconds

above

960

C

1090

C

continuous

63.9%

30

Minute

power

63.9%

to 71.8%

Maximum

71.8%

NOTE

If

ITT

remains

above

810

C

longer

PT6T-3B

- TORQUEMETERS

MARKED

than

15

seconds

or exceeds

other

79.4%

limits,

ITT

and duration

shall

be

Maximum

recorded

in

helicopter

logbook.

continuous

63.9%

Refer

to

Pratt

and

Whitney

30

Minute

power

63.9%

to 79.4%

Maintenance

Manual

for

Maximum

79.4%

inspection

requirements.

1-8

Rev.

2


17/585


18/585

BHT-212IFR-FM-1 FAA APPROVED

1-15. ROTOR

1-15-A. ROTOR RPM POWER ON

1-15-B. ROTOR RPM POWEROFF

1-16. HYDRAULIC

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

1-16-B. HYDRAULICTEMPERATURE

1-17. FUEL AND OIL

1-17-A. FUEL

NOTE


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 -30C

(-22F).

1-17-B. OIL ENGINE ANDCOMBINING GEARBOX

NOTE


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 DOD-

L-85734 may be used at all ambient air

temperatures above -40C (-40F).

1-17-C. OIL TRANSMISSION,INTERMEDIATE AND TAIL ROTORGEARBOXES

Oil conforming to MIL-L-7808 (NATO 0-148)may be used a t a l l approved 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).

Minimum

Maximum

97%

100%

Minimum

Maximum

91%

104.5%

Minimum

Caution range

Normal Operating

Maximum

600 PSI

600 900 PSI

900 1100 PSI

1100 PSI

Maximum 88C

1-10 Rev. 4 02 DEC 2002


19/585

FAA APPROVED

BHT-2121FR-FM

NOTE

1-20.

INSTRUMENT

DOD-L-85734AS

or MIL-L-23699 is

MARKINGS

AND PLACARDS

recommended.

Refer to Figure 1-1 and 1-2 for Instrume

1-18.

ROTOR

BRAKE

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 Heater

shall not be

operated when

OAT

be applied until engines have been shut above 21 C.

down and ROTOR

RPM (NR) has

decreased

to 40% or less.

Refer to Appendix

A for listing of Flig

Manual

Supplements (FMS)

coverin

1-19.

LANDING

GEAR

optional

equipment

kits

available.

No Flight Manual

Limitations

1-11/1


20/585


21/585


22/585


23/585


24/585


25/585


26/585

FAA

APPROVED

BHT-2121FR-F

(TYPICAL)

PANEL AFT ENDOF OVERHEADCONSOLE

(if

installed)

2121FR-FM-1-2-1

Figure

1-2.

Placards

and

decals

(Sheet

1 of

2)

Rev.


27/585

BHT-2121FR-FM-1

FAA APPROVED

NOTES:

USED

WITH

GAS

PRODUCER

AGE

P/N

212-075-037-101

USED

WITH GAS

PRODUCER

AGEP/N 212-075-037-113

2121FR-FM-1-2

2

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

Figure

1-2.

Placards

and

decals

(Sheet

2 of

2)

1-20 Rev.1


28/585

FAA APPROVED

BHT-2121FR-F

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


29/585


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

40 60 8 9 10

11 12 LB X 1000

OAT - C

1

38

42 46

50

54 KG

X 100

GROSSWEIGHT

2121FR-FM- -4

Figure

1-4.

Weight-altitude

temperature

limitations

for takeoff,

landing

and

in

ground

effect maneuvers chart

1-22

Rev.

1


30/585

FAA APPROVED BHT-2121FR-

450

NOTE: THEHELICOPTERCONFIGURATION

SHALLCOMPLYWITHTHEWEIGHT-

400

ALTITUDE-TEMPERATURECHART

FOR HEIGHT-VELOCITY DIAGRAM

TO

BE

VALID

350

250

250 1000 LBLESS THAN

0

200

150

50

0 10 20

30 40

50

60

70

INDICATEDAIRSPEED - KNOTS

Figure

1-5. Single engine height velocity chart

Rev. 1 1-23


31/585

FAA

APPROVED

BHT-2121FR-F

Section

2

TABLE

OF CONTENTS

Page

Subject

Paragraph

Numb

INTRODUCTION

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

2-1...

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

2-3

FLIGHT

PLANNING

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

2-2.....................

2-3

TAKEOFF

AND

LANDING

.........

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

.......

2-2-A

........

2-3

WEIGHT

AND

BALANCE

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

2-2-B ........

2-3

PREFLIGHT CHECK ............................ ..................... 2-3

BEFORE

EXTERIOR

CHECK

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

2-3-A

.......

2-3

EXTERIOR

CHECK

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

2-3-B

.......

2-4

INTERIOR

AND

PRESTART

CHECK

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

2-4........

2-6

ENGINE

START

.

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

2-5

2-7

ENGINE

1 START...........................................

2-5-A

......

2-8

ENGINE

2

START...........................................

2-5-B ......

2-9

POST

START

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

2-5-C

......

2-9

ENGINE

FAILS

TO START

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

2-5-D

.....

2-10

DRY

MOTORING

RUN

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

........

2-5-E

.....

2-10

SYSTEMS

CHECK

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

26...................

..

2-10

FORCE

TRIM

CHECK......................................

2-6-A

. .....

2-10

PRELIMINARY

HYDRAULIC

CHECK

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

2-6-B

....

.

2-11

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

......

2-11

GOVERNOR

CHECK

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

2-6-D ........

2-11

FUEL

CROSSFEED

VALVE

CHECK........................

2-6-E

.......

2-11

ELECTRICAL

SYSTEMS

CHECK

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

2-6-F........

2-11

AFCS

CHECK

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

2-.......

.......-6-G.......

2-12

CABIN

HEATER

CHECK....................................

2-6-H

.......

2-14

HYDRAULIC

SYSTEM

CHECK..............................

2-6-J.........

2-14

BEFORE

TAKEOFF

.........

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

.........

.........

-7

2-15

POWER

ASSURANCE

CHECK

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

2-7-A

.......

2-16

PROLONGED

GROUND

OPERATION

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

2-7-B

.......

2-16

TAKEOFF

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

...........

2-16

INFLIGHT

OPERATIONS

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

.

2-16

DESCENT

AND

LANDING

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

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

.

2-10.........

2-17ENGINE

SHUTDOWN

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

2-11

2-17

POSTFLIGHT

CHECK

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

2-12 .........

2-18

LIST

OF

FIGURES

Figure

Page

Title

Number

Numbe

Exterior

check

diagram

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

........

2-1

...........

2-19

2-1/


32/585

FAA

APPROVED

BHT-2121FR-FM-

Section

2

2-1. INTRODUCTION Consult applicable weight and balanc

instructions

provided

in Section 5.

This

section

contains

instructions

and

This sectionontains instructions

and

Determine weight

of fuel, oil, load, etc.

procedures

for operating

helicopter from

planning

stage, through

actual flight

takeoff

and anticipatatedandin

conditions, to securing

helicopter after GW,

and check helicopterCG locations.

landing.

Ensure

weight

and

balance

limitations

in

Section

1 are not

exceeded.

Normal and

standard conditions

are

assumed in these procedures. Pertinent

data in

other sections

is referenced

when 2-3.

PREFLIGHT

CHECK

applicable.

Pilot

is responsible

for

determining

Instructions and procedures contained

whether helicopter is

in

condition for safe

herein are written for purpose of

flight.

standardization

and are not applicable

to

all situations.

NOTE

2-2. FLIGHT PLANNING Preflight check is not intended to

be

a detailed

mechanical

Planning of mission to be accomplished Inspection, but a guide to check

will provide pilot with data to be used condition of helicopter. This

during flight. Information to be

used can check may

be made as

be compiled

as follows:

comprehensive

as conditions

warrant.

Check type

of mission to be

performed

and destination.

All areas checked

shall

include a

visual

check

for evidence

of

Select appropriate performance charts corrosion, particularly when

to be used from Section 4. helicopter is flown near or over

salt water

or in areas

of high

industrial emissions.

2-2-A.

TAKEOFF

AND LANDING

Refer

to Section 1 for takeoff and

landing 2-3-A. BEFORE EXTERIOR

weight limits and to Section 4 for takeoff

CHECK

and landing data.

Flight

planning -

Completed.

2-2-B.

WEIGHT

AND BALANCE

Publications-

Check.

Determine

proper weight

and balance

of Ensure

helicopter

has been

serviced as

helicopter

as follows:

required.

Rev. 2 2-3


33/585

BHT-2121FR-FM-1

FAA APPROVED

2-3-B.

EXTERIOR

CHECK

Fuel

sump drain

buttons

(left and

right)

- Press.

Fuel filters - Drain before first flight

of day

as follows:

ENGINE

1 BOOST

PUMP

and

IF HELICOPTER HAS BEEN ENGINE2 BOOSTPUMPswitches -

EXPOSED TO SNOW OR ICING ON.

CONDITIONS,

SNOW

AND ICE

SHALL BE REMOVED PRIOR TO

ENGINE 1 FUEL and

ENGINE2 FUEL

FLIGHT. switches - ON.

1.

FUSELAGE-

FRONT

Fuel filters

(left and right)

- Drain

samples.

Rotor blade - Condition and

cleanliness.

ENGINE 1

FUEL and ENGINE

2 FUEL

switches

-

OFF.

Cabin area - Condition, all glass

clean. ENGINE 1 BOOST PUMP and

ENGINE 2 BOOST PUMP switches -

Pitot tubes - Covers removed, OFF.

unobstructed.

BATTERY BUS 1 switch - OFF.

Static ports (left and right) -

Unobstructed.

2. FUSELAGE

- CABIN

LEFT SIDE

Remote

hydraulic

filter

bypass

Copilot

and passenger

doors

-

Indicator

- Check

green.

Condition

and

operation,

glass

clean.

Security of

emergency release

Cabin

nose

ventilators

- handles.

Unobstructed.

Position lights - Condition.

Nose compartment - Condition and

doors

secured.

Landing

gear

-

Condition,

ground

handling

wheels

removed.

Battery vent and drain tubes

-

Battery

vent

and

drain

tubes

Engine

air

intake

- Cover

removed,

Unobstructed.

unobstructed.

Searchlight

and landing light - 3. FUSELAGE AFT LEFT SIDE

Antenna

-

Condition,

security.

Drain

lines

-

Clean,

unobstructed.

Engine compartment - Check.

Fuel sumps - Drain samples as

follows:

Engine

oil level - Verify presence of

oil

in sight

gage

and

proper

oil

level.

ENGINE

1 BOOST

PUMP

and

ENGINE

2

BOOST

PUMPswitches

-

Engine

governor

spring -

Condition.

OFF.

Engine

fire extinguisher

- Bottle

ENGINE 1

FUEL and ENGINE

2 FUEL

pressure

gage

and temperature

range.

switches

- OFF.

BATTERY

BUS 1 switch

- ON.

2-4


34/585

FAA APPROVED

BHT-2121FR-FM

Combining

gearbox

filter

- Bypass

Engine

compartment

-

Check.

indicator retracted.

Engine

oil level

- Verify

presence

o

Access

doors and

engine cowling

-

oil and

proper level

in sight

gage.

Secured.

Access

doors

and engine

cowling

-

Engine exhaust ejector tubes - Secured.

Covers removed, unobstructed.

Fuel

filler

- Check

fuel

quantity

4.

FUSELAGE

-AFT

secure

cap.

Tailboom - Condition.

6. FUSELAGE

- CABIN RIGHT SIDE

Tail rotor driveshaft covers - remov

Secured.

Engine air intake

- Cover removed

*secured.

unobstructed.

Synchronized

elevator

-

Condition,

security

z

Transmission

oil

-

Verify

presence

o

oil and

proper level

in sight gage.

Main

rotor

blade

- Condition,

cleanliness.

Remove

iedown.

Pilot and

passenger

doors-

Condition and operation, glass clean

Tail

rotor

gearbox

-

Verify

presence

Security

of

emergency

release

of

oil and

proper

level

in sight

gage,

handles.

filler

cap

and

chip detector

plug

security.

Position

lights -

Condition.

Tail rotor

- Condition,

free movement

Landing

gear

- Condition,

groun

on flapping

axis.

handling

wheels

removed.

Tail

rotor yoke

- Evidence

of static

7. CABIN

TOP

stop

contact

damage

(deformed

static

stop

yield indicator).

Intermediate gearbox - Verify CAUTION

presence

of

oil

and

proper

level

in

sight gage.

Filler cap and chip

SNOW AND ICE SHALL

BE

detector plug security. REMOVED PRIOR TO FLIGHT

Tail skid

- Condition,

security.

WHEN

HELICOPTER

HAS

BEEN

EXPOSED

TO SNOW OR

ICING

Synchronized

elevator

- Condition,

CONDITIONS.

security.

Main rotor and

controls - Conditio

Tailboom

-

Condition.

fluid levels

in all

reservoirs.

Baggage

compartment

- Check

Transmission

oil filler

cap - Secured

smoke detector - Condition and

security. Cargo

and door secured.

Hydraulic

oil reservoirs

- Check sigh

glasses

for

proper

fluid

levels.

Cap

5. FUSELAGE - AFT RIGHT SIDE secured.

Engine fire extinguisher - Bottle Antenna(s)- Condition and security

pressure gage

and temperature

range.

Combining

gearbox

oil

filler

cap

-

Combining gearbox oil level - Verify Secured

presence

of

oil and

proper

level

In

sight

gage.

Close

access

door.

Rev.

3

2


35/585

BHT-2121FR-FM-1

FAA

APPROVED

Anticolllsion

light -

Condition

and

Shoulder

harness

inertia

reel

and lock-

security.

Check.

Flight controls -

Freedom of movement,

CAUTION

position

for

start.

Cyclic - Centered,.friction

as

desired.

IF ANY TEMP-PLATE IS MISSING

OR HAS

BLACK

DOTS,

Collective

- Full down.

MAINTENANCE

PERSONNEL

SHALL

ASSIST

IN

DETERMINING

Transmission

chip detector

indicators

(if

AIRWORTHINESS.

installed)

- Check.

Main

driveshaft

and

coupling

-

Lower

pedestal

circuit

breakers

- In.

Condition,

security, and

grease

leakage.

Check

Temp-Plates

(four

Collective

control

head switches

- OFF.

places

each

coupling)

for evidence

of

elevated

temperature

indicated

by dot

COMPASS

CONTROL

slaving

swltch(es)

changing

color

to

black.

-

MAG (slave

position).

Engine air intakes - Unobstructed, Radio equipment - OFF.

particle

separator

doors

closed.

Fuel

INTCON switch

- NORM.

Engine

and

transmission

cowling

-

Secured.

ENGINE 1 BOOST PUMP

and ENGINE 2

BOOST

PUMP switches

- OFF.

Fresh

air inlet

screen

- Unobstructed.

FUEL

XFEED switch

- NORM.

2-4.

INTERIOR AND

ENGINE 1 FUEL and ENGINE

2 FUEL

PRESTART

CHECK

switches

- OFF.

Cabin interior - Cleanliness, security of ENGINE NO. 1 PART SEP and ENGINE

equipment.

NO.

2 PART

SEP

switches

- NORM.

Portable

fire

extinguishers

- Proper

ENGINE

NO.

1 GOV

and

ENGINE

NO.

2

charge,

secured.

GOV

switches

- AUTO.

Passenger

seats

- Secured,

each

HYDR SYS

NO. 1

and HYDR

SYS NO.

2

occupied seat

equipped with seat belt.

switches - ON.

Crew and

passenger

doors -

Secured.

STEP

switch

(if Installed)

- As

desired.

Cargo load - Secured.

FORCE TRIM switch -

ON, cover down.

Protective breathing equipment (if Instruments Staticcheck.

required)

-

Condition

and

properly

serviced. STATIC SOURCEswitch (if installed) -

PRI.

Seat and pedals - Adjust.

Altimeter(s)

-

Set.

Seat

belt and

shoulder

harness -

Fasten

and adjust.

Clock - Set and

running.

FIRE EXT switch - OFF.

2-6


36/585

FAA APPROVED BHT-212IFR-FM

FIRE PULL handles In (forward).

AFT DOME LT rheostat and switch OFF.

PITOT STATIC HEATERS switch OFF.

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.

INV 1, INV 2, and INV 3 switches OFF.

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.

NOTETest all lights when night flights are

planned or anticipated. Accomplish

light tests with external power

connected or during engine runup.

MASTER CAUTION switch (overhead)

TEST, check all caution panel lights

ext inguish except CAUTION PANE

segment and MASTER CAUTION light. (Bot

ENG OUT lights and RPM light will di

during test.)

CAUTION

ROTOR BRAKE HANDLE SHALL

BE IN DETENT POSITION (OFF) AT

ALL TIMES WHEN ENGINES ARE

RUNNING.

ROTOR BRAKE lights Test. Pull brak

lever and check that both lights illuminat

return to off and check lights extinguish.

FIRE PRESS TO TEST switch Press an

release. FIRE PULL 1 and FIRE PULL warning lights illuminate when switch

pressed and extinguish when switch

released.

BAGGAGE FIRE warning light TEST butto

Press to test (verify light flashes).

CARGO RELEASE ARMED light (if installe

TEST.

Caution panel lights TEST and RESET.

INV 1 switch ON, check no. 1 AC voltmet

for 104 to 122 volts.

INV 2 switch ON, check no. 2 AC voltmet

for 104 to 122 volts.

FUEL QTY SEL switch LEFT, then RIGH

check fuel quantity gauge indicates lowe

fuel cell quantity of 270 to 300 pound

(each).

2-5. ENGINE START

NOTE

If helicopter has been cold soaked

in ambient temperature of -18 C

....

02 DEC 2002 Rev. 4 2


37/585


38/585

FAA APPROVED

BHT-2121FR-FM-1

GAS

PROD RPM (N,) -

Check 61 1%

Engine 2 throttle

- Open to Idle

at 12%

when

throttle

is

on idle

stop.

GAS

PROD

RPM

(N

1

) minimum.

Engine 2 ITT - Monitor. Observe ITT

If battery start: limitations.

GAS

PROD

RPM

(N1)

-

71%.

START

switch

-

Off at

55%

GAS

PROD

RPM

(N1)

GEN 1 switch - ON.

GAS PROD

RPM (N1) - Check

61 + 1%

AMPS

1 - Check

at or below

150 amps.

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,

ENSURE

SECOND

ENGINE

and

GEAR

BOX OIL

pressures

ENGAGES

AS THROTTLE

IS

may

exceed

maximum

limits

for

INCREASED.

A NON-ENGAGED

up to 2 minutes after starting. ENGINE IS INDICATED BY 10 TO

15% ENG RPM

(N2) HIGHER

THAN

Do

not increase ROTOR RPM (NR)

ENGAGED ENGINE AND

NEAR

above 80% until XMSN OIL ZERO TORQUE. IF A NON-

temperature is above 15

C. ENGAGEMENT

OCCURS, CLOSE

THROTTLE

OF

NON-ENGAGED

ENGINE OIL, XMSN OIL, AND GEAR BOX ENGINE. WHEN NON-ENGAGED

OIL

pressures

- Check.

ENGINE

HAS

STOPPED,

SHUT

DOWN ENGAGED ENGINE.

ENG 1 PART

SEP OFF caution

light -

Extinguished. IF S

U D D E

N (

H A R D)

ENGAGEMENT

OCCURS,

SHUT

Engine 1 throttle

-

Increase to 85% ENG DOWN BOTH ENGINES.

RPM (N2). Friction as desired.

MAINTENANCE

ACTION IS

REQUIRED.

2-5-B.

ENGINE

2 START

Engine

2 throttle -

Increase slowly

to

85% ENG RPM

(N2). Monitor tachometer

ENGINE

2 BOOST

PUMP switch

- ON,

and torquemeter

to

verify engagement

of

check ENG

2 FUEL BOOST

caution light

second

engine.

extinguished

(FUEL XFEEDcaution

light

will illuminate

momentarily).

Engine 2 ENGINE

OIL pressure

- Check.

ENGINE 2 FUEL

switch

-

ON. (ENG 2 ENG

2 PART SEP OFF light -

FUELVALVE caution light will illuminate Extinguished.

momentarily.)

Engine 2 FUEL

PRESS - Check.

2-5-C. POST START

START switch - ENG 2

position. External power - Disconnect

if used,

Observe starter limitations.

GEN 1

switch - ON.

Engine

2 ENGINE

OIL pressure

- GEN 2 switch

- ON (BATTERY

BUS 1

Indicating.

will switch

OFF automatically).

2-9


39/585

BHT-2121FR-FM-1

FAA

APPROVED

2-5-E. DRY MOTORING RUN

CAUTION

Following

procedure

is

used to

clear an

IF

OPERATING

ON BATTERY

BUS

engine

whenever

it

Is deemed

necessary

to

1,

POSITION

INV

3

SWITCH

TO

ON

remove

internally

trapped

fuel

and

vapor:

DC

BUS

1.

Throttle

- Fully

closed.

ONLY

ONE

BATTERY

SWITCH

SHALL

BE ON

DURING

FLIGHT.

ENGINE

(1

or 2) BOOST

PUMP

switch

-

ON.

Caution

lights -

Check all

extinguished.

ENGINE

(1 or 2)

FUEL switch -

ON.

ENGINE

OIL, XMSN

OIL,

and GEAR

BOX

OIL temperatures

and

pressures

-

ENG

IGN SYS

circuit

breaker-Pull

out.

Within limits.

START

switch

- Engage

for

15 seconds,

AMPS

1

and AMPS

2 -

Within

limits,

then

disengage.

ENGINE (1 or 2) FUEL switch - OFF.

NOTE

AMPS

2 will

indicate

a higher

load

ENGINE

(1

or 2)

BOOST

PUMP

switch

-

than

AMPS

1

until

battery

is

fully

OFF.

charged.

ENG

IGN SYS circuit

breaker - In.

Radios

- ON

as required.

Allow

required

cooling

period

for

starter

ELT

(if installed)

-

Check

for

before

proceeding.

Follow

normal

start

inadvertent

transmission.

sequence

as

described

on

preceding

pages.

Refer to

SECTION

1, STARTER

LIMITATIONS.

2-5-D.

ENGINE

FAILS TO START

When

engine

fails

to

light

off

within

15

2-6.

SYSTEMS

CHECK

seconds

after

throttle

has

been

opened

to

idle,

following

action

is

recommended:

2-6-A.

FORCE

TRIM

CHECK

IDLE

STOP

REL switch

-

Actuate.

Flight

controls

-

Friction

off;

collective

lock removed.

Throttle

- Fully

closed.

Cyclic

and pedals

- Move

slightly

each

START

switch

- OFF.

direction

to

check

force

gradients.

ENGINE

(1

or 2)

BOOST

PUMP

switch

Cyclic FORCE TRIM release button -

-

OFF.

Press;

check

trim releases

with button

pressed,

reengages

with

button

ENGINE

(1 or 2)

FUEL

switch

-

OFF.

released.

After

GAS

PROD

RPM

(N

1

)

has

FORCE

TRIM

switch

- OFF;

check

trim

decreased

to zero,

allow

30 seconds

for

disengages

and

FT

OFF

caution

light

fuel

to

drain

from

engine.

Conduct

a

illuminates.

DRY

MOTORING

RUN

before

attempting

another

start.

FORCE

TRIM switch

-

ON.

2-10 Rev. 2


40/585

FAA

APPROVED

BHT-2121FR-FM

2-6-B. PRELIMINARY HYDRAULIC

RPM INCR DECR switch

-

INCR to 10

CHECK

(N

2

).

Throttles -

Set to idle.

2-6-E.

FUEL

CROSSFEED

VALVE

CHECK

NOTE

NOTE FUEL XFEED test switch - TEST BUS

Uncommanded

control movement

and hold.

or motoring

with either

hydraulic

system

off may indicate

hydraulic

system malfunction. NOTE

If, after turning either boost pump

HYDR

SYS NO. 1

switch -

OFF, then

off,

fuel pressure

remains

4 to 6

psi

below

normal

(10

4

psi),

appropriate

check

valve is

not

HYDR

SYS

NO.

2

switch

- OFF,

then

functioning

properly.

ON.

ENGINE

1 BOOST

PUMP switch -

OF

Check no. 1 FUEL PRESS decrease

2-6-C.

ENGINE

FUEL

CONTROL

then

returns

to

normal.

(This

indicat

CHECK

that crossfeed

valve has opened by b

no. 1 power

and check

valve

Throttles - Idle. functioning properly.) ENGINE 1 BOO

PUMP switch - ON.

NOTE

FUEL XFEED

test switch

- TEST BUS

and hold.

Do

not

allow

GAS

PROD

RPM

(N

1

)

to decrease

below 50%.

ENGINE

2

BOOST

PUMP

switch

- OF

Check no. 2 FUEL

PRESS decrease

Around

8000

feet Hp,

GAS PROD

then

returns

to normal.

ENGINE

RPM (N

1

)

may not change BOOSTPUMPswitch

-

ON.

significantly

when

manual fuel

control

is selected.

FUEL

XFEED

test switch

- NORM.

GOV

switch (ENGINE

NO. 1 or 2)

- FUEL XFEED

switch - OVRD

CLOSE.

MANUAL,

observe

change in

GAS PROD

RPM

(N

1

).

Open respective

throttle

ENGINE

1 (or

ENGINE 2) BOOST

PUM

carefully

to assure

GAS PROD

RPM (N

1

) switch

- OFF.

Check fuel

pressur

responds upward,

then return throttle

to drops

to zero on

selected system

idle.

Return

GOV switch

to AUTO.

ENGINE

1 (or

ENGINE 2) BOOST

PUM

Check for

return to original

GAS

PROD

switch - ON.

RPM (N

1

). Check

other governor

in same

manner.

FUEL XFEED

switch - NORM.

2-6-D. GOVERNOR CHECK

2-6-F. ELECTRICAL

SYSTEMS

CHECK

No. 1 throttle - Full open. Check ENG

RPM (N

2

) stabilizes

at 95 1%.

DC voltmeters - Check 27 1 vdc.

No. 2 throttle

- Full

open. Check

no. 1

AC voltmeters

- Check

104 to 122

vac

engine

ENG RPM (N

2

)

increases 2% and

both engines stabilize

at 97 1%

N

2

. Ammeters

- Check

within limits.

2-


41/585

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

3 caution

light

Cyclic - Move

laterally and hold.

Check

extinguishes. that roll NO GO light Illuminates, then

extinguishes after several seconds.

INV 2 switch - OFF, INVERTER 2 Return to neutral.

caution light illuminates. Check no. 2

AC voltmeter

for indication

that Pedals

- Move and hold.

Check that

inverter no. 3 has assumed load.

INV yaw NO GO light illuminates,

then

2 switch - ON. INVERTER2 caution

extinguishes after several

seconds.

light extinguishes.

Return pedals to neutral.

INV 3 switch - OFF, then ON DC BUS SCAS switch - ENGA, SCAS lights

1, check

INVERTER

3 caution

light

illuminate.

extinguishes.

SCAS switch -

DSENGA, SCAS

lights

INV 1 switch - OFF,

INVERTER 1 extinguish.

caution light illuminates. Check no. 1

AC

voltmeter for indication that

SCAS switch - ENGA, SCAS

lights

inverter no. 3 has assumed load. INV illuminate.

1 switch - ON.

INVERTER 1

caution

light extinguishes.

INV 1 switch - OFF,

SCAS disengages.

INV

3 switch

- OFF,

INVERTER

3 INV

1 switch -

ON, check

no. 1 AC

caution

light

illuminates.

INV

3 switch

voltmeter

for

104 o 122

volts.

- ON DC BUS 2, INVERTER 3 caution

light

extinguishes.

SCAS

switch

- ENGA,

SCAS

lights

illuminate.

2-6-G.

AFCS

CHECK

Pilot

AFCS

RELEASE

-

Press,

SCAS

disengages.

NOTE

NOTE SCAS switch - ENGA, SCAS

lights

AFCS mode

operation is

illuminate.

annunciated

on instrument

panel

by a

three segment light (PITCH,

Copilot AFCS RELEASE - Press,

SCAS

ROLL, YAW). AFCS functions In disengages.

two

modes - automatic with

turn

and trim functions,

and pilot

SCAS

switch - ENGA,

SCAS lights

cyclic steering. AFCS

illuminate.

annunciation is applicable to both

modes.

FORCE TRIM -

ON, cover down.

AFCS power - ON.

ATTD switch

- ENGA, AFCS lights

illuminate, SCAS ights extinguish.

Channel arm switches

- ATTD.

ATTD switch - DSENGA, AFCS lights

SCAS NO GO lights - Illuminated, extinguish, SCAS ights Illuminate.

should extinguish within several

seconds to Indicate system null.

Wait ATTD switch - ENGA,

AFCS lights

for lights to extinguish.

illuminate, SCAS

ights extinguish.

Cyclic - Move forward

and hold, then Pilot AFCS

RELEASE - Press, AFCS

aft

and hold. Check that pitch NO GO

lights extinguish, SCAS disengages.

2-12


42/585

FAA

APPROVED

BHT-2121FR-FM-1

SCAS

switch

- ENGA,

SCAS lights

laterally.

Cyclic

should

follow and

illuminate.

AFCS ROLL

light remain

illuminated.

Center cyclic

using cyclic

FORCE

ATTD switch

- ENGA, AFCS lights

TRIM switch.

illuminate,

SCAS

lights

extinguish.

Turn

- Actuate

turn

knob

through

Copilot

AFCS

RELEASE

-

Press,

AFCS

cycle.

Cyclic

should

follow

and

AFCS

Copilot

AFCS RELEASE

- Press,

AFCS

PITCH

and ROLL

remain

PITCH and

ROLL lights

remain

lights extinguish, SCASdisengages. 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

E

N S U R

E CONTROL

Pitch -

Displace cyclic

slightly

DEFLECTIONS

ARE NOT

forward and release. AFCS

PITCH

EXCESSIVE

DURING AFCS

light extinguishes and SCAS

PITCH

CHECK.

light illuminates.

Displace cyclic

slightly

aft

and release.

AFCS PITCH

SCAS switch - ENGA.

light

extinguishes and SCAS PITCH

CAS

switch- ENGA.

light illuminates.

ATTD

switch

-

ENGA.

Roll -

Displace

cyclic

slightly

left and

release.

AFCS ROLL

light

NOTE

extinguishes

and

SCAS

ROLL

light

illuminates.

Displace

cyclic

slightly

right and

release. AFCS

ROLL ight

Cyclic

friction must be properly

right and release. AFCS ROLL

light

set for

proper AFCS

operation,

extinguishes and

SCAS ROLL

light

Friction adjust ring must neither

be

tightly

compressed

against

Yaw

-

Displace

left

pedal

slightly

minimum

friction

bracket

nor be

forward

and release.

AFCS

YAW light

excessively

tight.

extinguishes

and SCAS

YAW

light

illuminates. Displace right pedal

Cyclic

friction

-

Adjust.

slightly

forward

and release.

AFCS

YAW

light extinguishes

and SCAS

AFCS automatic mode

- Check as YAW light

illuminates.

follows:

Pitch

- Actuate

pitch

trim

wheel

CAUTION

through cycle. Cyclic

should follow

and

AFCS PITCH

light remain

illuminated.

Center

cyclic using cyclic

CYCLIC

CONTROLS MAY

MOTOR

FORCE

TRIM switch.

Actuate AFCS

TO STOP

IF AFCS

IS LEFT

TRIM switch forward

and aft. Cyclic

ENGAGED

AND UNMONITORED

should follow and AFCS PITCH light DURING GROUND OPERATIONS.

remain

illuminated.

Center

cyclic

using cyclic FORCETRIM switch. FOR PROLONGED GROUND

OPERATION,

AFCS

SHALL NOT

Roll - Actuate roll trim wheel through BE OPERATED IN ATTD MODE.

cycle.

Cyclic

should

follow and

AFCS

ROLL

light remain

illuminated.

Center

cyclic

using cyclic

FORCE TRIM

switch. Actuate

AFCS TRIM

switch

2-13


43/585

BHT-2121FR-FM-1

FAA APPROVED

ATTD

switch - DSENGA

prior to takeoff.

VENT BLOWER

switch -

As desired.

2-6-H. CABIN HEATER CHECK

2-6-J. HYDRAULIC

SYSTEM

CHECK

GAS

PROD RPM

(N,) - Check

75%

minimum

(both

engines).

NOTE

AIR COND TEMP CONT switch - Fully

COOL.

This check

is to determine

proper

operation of hydraulic actuators

for each flight

control system.

If

abnormal

forces,

unequal

forces,

CAUTION

control binding,

or motoring

is

encountered,

it may be an

indication of a malfunction of a

SYSTEM SELECTOR

SWITCH

flight control actuator.

SHALL

BE TURNED

OFF

WHEN

HEATED

AIRFLOW DOES NOT

FORCE TRIM switch

- OFF.

SHUT OFF AFTER

AIR COND

TEMP

CONT

SWITCH

IS

TURNED

Collective

- Down,

friction

removed.

TO FULLY

COLD, HEATER AIR

LINE

CAUTION

LIGHT

ROTOR

RPM

(NR)-

Set to

100%.

ILLUMINATES,

OR

CABIN

HTR

CIRCUIT

BREAKER

TRIPS.

Cyclic

- Centered,

friction

removed.

DO NOT OPERATE HEATER

ABOVE

21

C

OAT.

Hydraulic

system

- Check

as follows:

HYDR SYS NO.

1

switch - OFF.

SYSTEM

SELECTOR switch

- HEATER.

Check

Check MASTER CAUTION and

VENT BLOWER

switch -

ON.

HYDRAULIC

caution lights

Illuminate

and

hydraulic system no. 1 pressure

AIR COND TEMP

CONT switch - Rotate

decreases.

counterclockwise and observe heatedyclic - Check normal operation by

Cyclic - Check normal operation by

airflow.

moving

cyclic

in

an 'X'

pattern

right

forward

to

left aft,

then left

forward

to

DEFOG lever -

ON; check airflow

is right

aft (approximately

1 inch).

diverted from pedestal

outlets to Center

cyclic.

windshield

nozzles.

Return lever

to

OFF.

Collective

-

Check

normal

operation

by Increasing

collective slightly

(1 to 2

AFT

OUTLET switch - ON; check

inches). Return to down

position.

airflow distributed equally between

pedestal

outlets and

aft outlets. Return

switch

to OFF.

NOTE

Boost for tail rotor controls is

NOTE

furnished

by hydraulic

system no.

1 only. When hydraulic system

Heater operation

affects

no.

1 is being checked,

tail rotor

performance.

Refer to Hover

controls will be unboosted.

Ceiling and Rate of Climb charts

for HEATER ON in Section 4.

SYSTEM

SELECTOR

switch -

As

desired.

2-14

Rev. 2


44/585

FAA

APPROVED

BHT-2121FR-FM-

Pedals

- Displace

slightly

left

and

right.

Note

an increase

in

force

WARNING

required

to move

pedals.

BOTH

HYDRAULIC

SYSTEMS

WARNING

SHALL BE OPERATIONAL

PRIOR

TO

TAKEOFF.

DO

NOT

TURN

BOTH

HYDRAULIC

NOTE

SYSTEMS

OFF

AT

SAME

TIME

DUE

TO

EXCESSIVE

FORCE

System

1 will

normally

operate

10

REQUIRED

TO

MOVE

FLIGHT

to 20

C

cooler

than

system

2.

CONTROLS.

HYDR

SYS

NO.

1

switch -

ON.

Check

2-7.

BEFORE

TAKEOFF

MASTER

CAUTION

and

HYDRAULIC

caution

lights

extinguish

and

Engine,

transmission,

gearbox,

hydraulic

system

no.

2

pressure

hydraulic,

and

electrical

Instruments

-

returns

to

normal.

Check

readings

within

operational

HYDR SYS

NO. 2 switch -

OFF. range.

Check

MASTER

CAUTION

and

Flight

instruments

-

Check

operation

HYDRAULIC

caution

lights

illuminate

and set.

and

hydraulic

system

no.

2

pressure

decreases.

Attitude

indicators

-

Erect

and

set.

Cyclic

- Check

normal

operation

by

moving

cyclic

in an

'X' pattern,

right

NOTE

forward

to

left aft,

then left

forward

to

right

aft

(approximately

1 Inch).

If fast

slaving

is desired,set

roll

Center cyclic.

trim to

null, push

and hold

VG

FAST

ERECT

switch

(if installed)

Collective - Check normal operation until attitude indicator displays

by increasing

collective

slightly

(1 to

2

zero

degrees

bank

angle.

inches).

Return

to

down

position.

Turn

and

slip

indicators

- Operative.

Pedals

-

Displace

slightly

left

and

right.

Note

no

increase

in

force

HSls

-

Slaved

and

heading

correct,

required

to

move

pedals.

course

bar

and

bearing

pointers

set

to

proper

navigation

receivers.

HYDR

SYS NO.

2 switch

- ON.

Check

MASTER

CAUTION

and

HYDRAULIC

caution

lights

extinguish

and

hydraulic

system

no.

1 pressure

CAUTION

returns to

normal.

Cyclic

and collective

friction - As

INDICATOR

IS CPLT/PLT

desired. INDICATOR IS

ILLUMINATED,

CHANGING

COURSE

SETTING

ON

HSI

OF

COPILOT/PILOT

IN

ORCE

TRIM

switch-ON.

COMMAND

WILL

CHANGE

COURSE

SETTING

ON

REMAINING HSI (IF INSTALLED).

Magnetic

compasses

- Fluid

level

and

heading.

2-15


45/585

BHT-2121FR-FM-1

FAA

APPROVED

Altimeters

- Set.

2-7-B.

PROLONGED

GROUND

Vertical

speed

indicators

- Zero.

OPERATION

Clocks

-

Set

and running.

NOTE

Communication

and

navigation

For

prolonged

ground

operation,

equipment - Set and functioning. AFCS shall not be operated in

ATTD mode.

Position lights - As required.

Anti-collision

lights

- As required.

2-8.

TAKEOFF

Pitot

heater

-

As

required.

ENG RPM (N2) - 100%.

Cyclic

-

Fiction

as desired.

NOTE

NOTE

No

more

than

15%

torque

above

Moderate friction shall be applied hover power shall be used

to

each

throttle

to

overcome

accelerating

to

Takeoff

Climbout

follow-through

coupling

between

Speed.

twist

grips.

Collective

- Initiate

takeoff

from

a

hover

Throttles -

Full open, friction

adjusted.

height

of 4 feet.

ENG

RPM

(N

2

) -

100%

(both

engines).

FORCE

TRIM

switch

- As

desired.

COCKPIT

VOICE

RECORDER

TEST

switch

(if installed)--

press

and

hold

for

OBSER

VE

VMINITS

IN

3 seconds. Verify meter indicates GOOD. SECTION 1 FOR IFR OPERATION.

Passenger

STEP

switch

(if

installed)-

NOTE

As

desired.

Takeoff

must

be

executed

in

Passenger seat belts - Fastened. accordance with Height-Velocity

limitations

for type

of

operation

All doors

- Secured.

being

conducted.

Refer

to

Section

1.

Caution

and

warning

lights

-

Extinguished.

Refer

to

Section

4

for additional

climb performance

data.

2-7-A. POWER ASSURANCE

CHECK

ATTD

switch

-

ENGA

as

desired

above

40 KIAS.

Perform

power

assurance

check

daily.

Refer

o Section

4.

2-9.

IN-FLIGHT

OPERATIONS

Maneuvering

with

AFCS

on

may

be

accomplished

by

one

of

following

methods:

2-16 Rev. 2


46/585

FAA APPROVED

BHT-2121FR-FM-

NOTE

necessary

to maintain

balanced

flight

Use

PITCH rim

as necessary

to

maintai

If ROLL trim

wheel is

used during

desired

attitude.

turn, helicopter

may

not return to

level flight

(in roll)

when turn

is

Method 2:

terminated.

Move cyclic to desired bank angle an

Method 1: pitch attitude. Apply pedal as necessary

Press

TURN knob

and

select desired

angle of

bank. Apply

pedal as

Rev. 2 2-16A/2-16


47/585

FAA

APPROVED

BHT-2121FR-FM

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 ENGAGED

AND UNMONITORED

when maneuver is complete and with DURING GROUND OPERATIONS.

helicopter

at level

attitude.

Collective

- Down.

2-10. DESCENT

AND Cyclic

control and

pedals - Centere

2-10LANDIN

and

frictioned.

FORCE

TRIM switch

- ON.

Flight controls

- Adjust

friction

as

desired.

Throttles -

Idle.

Throttles - Full open.

ITT - Stabilize

for one minute at id

prior

to shut

down.

ENG RPM

(N2)

-

100%.

Engine

instruments

-

Within

limits.

FORCE RIM

switch As desired.

ELT (if installed)

- Check

fo

inadvertent transmission.

Passenger

STEP

switch

- As

desired.

Radios - OFF.

WARNING

IDLE

STOP

REL

switch

- ENG

1.

Engine

1 throttle

- Closed.

Check

I

OBSERVE VMIN

LIMITS

IN

and GAS

PROD RPM

(N

1

) decreasing.

SECTION

1 FOR IFR

OPERATION.

BATTERY BUS 1 switch - ON.

Flight path

- Establish

in accordance

with

Height-Velocity diagram. Single

IDLE STOP REL switch

- ENG 2.

engine balked

landings

can be made

from a landing decision

point (LDP) of Engine

2 throttle - Closed. Check I

100 feet altitude, 40 knots airspeed,

and and GAS PROD RPM

(N.) decreasing.

500

feet rate of descent.

Anticipated

single engine landings initiated from GEN 1 and GEN 2 switches - OFF.

these conditions

require reference

to

landing performance data

in Section 4. INV 1, INV 2, and

INV 3 switches - OF

ATTD switch - DSENGA

as desired. ENGINE

1 FUEL switch - OFF.

ENGINE 1 BOOST PUMP switch - OFF

NOTE

ENGINE

2 FUEL

switch - OFF.

ATTD switch

must be disengaged

below

40 knots.

ENGINE

2 BOOST

PUMP

switch

- OFF

2-11.

ENGINE

SHUTDOWN

AFCS power - OFF.

2-


48/585


CAUTION

2-12.

POSTFLIGHT

CHECK

Main

rotor and tail

rotor blades

-

AVOIDRAPID

ENGAGEMENT

F Tiedown

when any

of following

ROTOR BRAKE IF HELICOPTER IS conditions exist:

ON ICE OR OTHER SLIPPERY OR

LOOSE SURFACE TO PREVENT Thunderstorms exist in local area or

ROTATION OF HELICOPTER. are forecast.

Rotor

brake - Apply

at or below 40%

Winds in

excess of 20 knots

or a gust

ROTOR

RPM (NR),

return to stowed

spread

of 15 knots exist or

is forecast.

position

after

main

rotor

stops.

Helicopter Is parked within 150 feet of

Pilot

- Remain at flig

Documents

Bell Helicopter manual