Bell BHT-206L3-FM-1 LongRanger-III Flight Manual

MODEL

206L3

ROTORCRAFT

FLIGHT MANUAL

BHT-206L3-FM-1

BHT 51001 THROUGH 51612

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

COPYRIGHT NOTICE

COPYRIGHT

®

HELICOPTER TEXTRON INC.

BELL
AND BELL HELICOPTER TEXTRON
CANADA LTD.

ALL RIGHTS RESERVED

2005

28 OCTOBER 1992

REVISION 6 — 26 APRIL 2005

BHT-206L3-FM-1

NOTICE PAGE

Additional copies of this publication may be obtained by contacting:

Commercial Publication Distribution Center

PN

Bell Helicopter Textron Inc.

P. O. Box 482

Fort Worth, Texas 76101-0482

TC APPROVED BHT-206L3-FM-1

LOG OF REVISIONS

Original ....................0 ....................... 09 DEC 81

Revision...................1 .......................29 NOV 82

Revision...................2 ....................... 12 DEC 83

Revision...................3 ....................... 26 OCT 84

Revision...................4 ...................... 14 MAR 85

Revision...................5 ....................... 21 OCT 86

Revision...................6 ........................24 JUL 87

Revision...................7 .......................09 MAY 88

Revision...................8 ....................... 14 OCT 88

Revision ...................9 ....................... 12 SEP 89

LOG OF PAGES

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Reissued ................. 0 ....................... 28 OCT 92

Revision .................. 1 ....................... 09 AUG 93

Revision .................. 2 ........................ 14 SEP 95

Revision .................. 3 ........................ 04 JUN 97

Revision .................. 4 ....................... 03 MAR 99

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Revision .................. 6 ....................... 26 APR 05

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NO.

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

NOTE

superseded pages.

26 APR 2005 Rev. 6 A/B

LOG OF TC APPROVED REVISIONS

BHT-206L3-FM-1

Original ....................0 ....................... 09 DEC 81

Revision...................1 .......................29 NOV 82

Revision...................2 ....................... 12 DEC 83

Revision...................3 ....................... 26 OCT 84

Revision...................4 ...................... 14 MAR 85

Revision...................5 ....................... 21 OCT 86

Revision...................6 ........................24 JUL 87

Revision...................7 .......................09 MAY 88

Revision...................8 ....................... 14 OCT 88

Revision ...................9 ....................... 12 SEP 89

Revision ................ 10 ....................... 04 DEC 89

Revision ................ 11 ....................... 25 MAY 90

Reissue.................... 0 ....................... 28 OCT 92

Revision .................. 1 ....................... 09 AUG 93

Revision .................. 2 ........................ 14 SEP 95

Revision .................. 3 ........................ 04 JUN 97

Revision .................. 4 ....................... 03 MAR 99

Revision .................. 5 ....................... 18 DEC 01

Revision .................. 6 ....................... 26 APR 05

APPROVED: DATE:

CHIEF, FLIGHT TEST
FOR
DIRECTOR — AIRCRAFT CERTIFICATION
TRANSPORT CANADA

26 APR 2005 Rev. 6 C/D

LOG OF FAA APPROVED REVISIONS

BHT-206L3-FM-1

Original ....................0 ....................... 09 DEC 81

Revision...................1 .......................29 NOV 82

Revision...................2 ....................... 12 DEC 83

Revision...................3 ....................... 26 OCT 84

Revision...................4 ...................... 14 MAR 85

Revision...................5 ....................... 21 OCT 86

Revision...................6 ........................24 JUL 87

Revision...................7 .......................09 MAY 88

Revision...................8 ....................... 14 OCT 88

Revision ...................9 ....................... 12 SEP 89

Revision ................ 10 ....................... 04 DEC 89

Revision ................ 11 ....................... 25 MAY 90

Reissue.................... 0 ....................... 28 OCT 92

Revision .................. 1 ....................... 09 AUG 93

Revision .................. 2 ........................ 14 SEP 95

Revision .................. 3 ........................ 04 JUN 97

Revision .................. 4 ....................... 15 MAR 99

Revision .................. 5 ........................ 15 JAN 02

Revision .................. 6 ....................... 04 MAY 05

APPROVED: DATE:

CHIEF, FLIGHT TEST
FOR
DIRECTOR — AIRCRAFT CERTIFICATION
TRANSPORT CANADA

26 APR 2005 Rev. 6 E/F

DOT APPROVED

BHT-206L3-FM-1

GENERALINFORMATION

ORGANIZATION

This Rotorcraft Flight Manual is divided

into four sections and an appendix as

follows:

Section 1 - LIMITATIONS
Section 2 - NORMAL PROCEDURES
Section 3 - EMERGENCY AND

MALFUNCTION
PROCEDURES

Section 4 - PERFORMANCE

Appendix - OPTIONAL EQUIPMENT

A

SUPPLEMENTS

Sections 1 through 4 contain the DOT
approved data necessary to operate the
basic helicopter in a safe and efficient
manner.

Appendix A contains the approved
supplements for optional equipment,
which shall be used in conjunction with

the basic Flight Manual when the

respective optional equipment kits are
installed.

The Manufacturer’s Data (BHT-206L3-MD-1)

manual, contains information to be used in
conjunction with the Flight Manual. The
manual is divided into four sections:

Section 1 - WEIGHT AND BALANCE
Section 2 - SYSTEMS DESCRIPTION

Section 3

- OPERATIONAL
INFORMATION

Section 4 - HANDLING/SERVICING/

MAINTENANCE

TERMINOLOGY

WARNINGS, CAUTIONS, AND

NOTES

Warnings, cautions, and notes are used
throughout this manual to emphasize

important and critical instructions as

follows:

AN OPERATING PROCEDURE,
PRACTICE, ETC., WHICH, IF NOT
CORRECTLY FOLLOWED, COULD
RESULT IN PERSONAL INJURY
OR LOSS OF LIFE.

AN OPERATING PROCEDURE,

PRACTICE, ETC., WHICH IF NOT

STRICTLY OBSERVED, COULD

RESULT IN DAMAGE TO OR
DESTRUCTION OF EQUIPMENT.

NOTE

An operating procedure,
condition, etc., which is essential

to highlight.

USE OF PROCEDURAL WORDS

The concept of 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 of a procedure is mandatory.

Rev. 2 i

BHT-206L3-FM-1

“Should” has been used only when
application of a procedure is
recommended.

“May” and “need not” have been used only
when application of a procedure is
optional.

“Will” has been used only to indicate
futurity, never to indicate a mandatory

procedure.

ABBREVIATIONS AND ACRONYMS

Abbreviations and acronyms used

throughout this manual are defined as

follows:

AC

- Alternating Current

A/F

- Airframe

ANTI
COLL LT -

Anticollision Light

APU

BAT
C
CG

DC

DECR

ECS

ELT

ENG
F
ft
GEN
GOV

- Alternate Power Unit

- Battery

- Celsius

-

Center of Gravity

- Direct Current

- Decrease

- Environmental Control
System

- Emergency Locater
Transmitter

- Engine

- Fahrenheit

- Foot, Feet

- Generator

- Governor

Hd

-

Hg -

HP -

HYDR ­IDLE REL ­IFR ­IGE -

IN

-

INCR ­INST LT ­KCAS -

kg -

LBS ­KIAS ­KTAS ­LDG LTS ­LT ­MCP -

mm

-

MPH
OAT ­OGE ­POS LT -

PSI ­QTY ­RLY ­RPM

DOT APPROVED

Density Altitude
Mercury
Pressure Altitude
Hydraulic
Idle Release

Instrument Flight Rules
In Ground Effect
Inch(es)
Increase

Instrument Light
Knots Calibrated Airspeed

Kilograms
Pounds
Knots Indicated Airspeed
Knots True Airspeed
Landing Lights

Light
Maximum Continuous

Power
millimeter
Miles Per Hour (Statute)
Outside Air Temperature
Out of Ground Effect

Position Light
Pounds per Square Inch
Quantity
Relay

Revolutions Per Minute

ii

Rev. 2

FAA APPROVED

BHT-206L3-FM-1

SL - Sea Level

TOT or

- Turbine Outlet Temperature
TURB OUT
TEMP

T/R - Tail Rotor
TRANS - Transmission

VFR

- Visual Flight Rules
Vne - Never Exceed Velocity
WRN

- Warning
XMSN

- Transmission

FAA APPROVED

BHT-206L3-FM-1

Paragraph

TABLE OF CONTENTS

1-1
1-2

-

1-3
1-4
1-5
1-6
1-7
1-8

1-9
1-10
1-11
1-12
1-13
1-14
1-15
1-16
1-17
1-18
1-19
1-20
1-21
1-22
1-23
1-24
1-25
1-26
1-27
1-28
1-29
1-30
1-31
1-32
1-33
1-34
1-35
1-36
1-37

GENERAL

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

BASIS OF CERTIFICATION

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

TYPE OF OPERATION

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

OPTIONAL EQUIPMENT..

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

FLIGHT CREW

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

WElGHT/CG

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

WEIGHT

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

CENTER OF GRAVITY - LONGITUDINAL

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

CENTER OF GRAVITY - LATERAL

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

DOOR(S) OFF

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

AIRSPEED

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

ALTITUDE

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

AMBIENT AIR TEMPERATURE.. ........................................

MANEUVERING

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

ELECTRICAL

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

GENERATOR

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

POWERPLANT

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

GAS PRODUCER RPM..

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

POWER TURBINE RPM ...............

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

T OT) . . . . . . . . . . . . . . . . . . . . . . . . .

TURBINE OUTLET TEMPERATURE (

ENGINE TORQUE ....................

FUEL PRESSURE ....................

ENGINE OIL PRESSURE.. ...........

ENGINE OIL TEMPERATURE.. ......

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

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

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

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

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

ANTIICE ...............................

STARTER

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

TRANSMISSION

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

TRANSMISSION OIL PRESSURE..

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

TRANSMISSION OIL TEMPERATURE

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

ROTOR

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

ROTOR RPM - POWER ON..

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

ROTOR RPM - POWER OFF

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

FUEL AND OIL.. .........................................................

FUEL

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

ENGINE OIL.. .......................................................

TRANSMISSION AND TAIL ROTOR GEARBOX OIL

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

HYDRAULIC

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

Page

Number

1-3
1-3
1-3
1-3
1-3
1-3
1-3
1-4
1-4
1-4
1-4
1-4
1-4
1-4
1-8
1-8
1-8
1-8
1-8
1-8
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
1-10
1-11
1-11
1-11

l-1

BHT-206L3-FM-1 FAA APPROVED

Figure
Number

LIST OF FIGURES

Title

Page

Number

1-1

Gross weight center of gravity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1-5

1-2

Placards and decals....................................................... 1-6

1-3

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

1-12

1-2

TC

APPROVED

BHT-206L3-FM-1

Section

1

.

1-1.

GENERAL

Flight

with

any

combination

of

doors

off

is

approved.

Refer

to

AIRSPEED

limitations.

Compliance

with

limitations

section

is

required

by

appropriate

operating

rules.

1-4.

OPTIONAL

EQUIPMENT

Anytime

an

operating

limitation

is

exceeded,

an

appropriate

entry

shall

be

made

in

The

following

equipment

shall

be

installed

helicopter

logbook.

Entry

shall

state

which

when

conducting

flight

operations

in

falling

limit

was

exceeded,

the

duration

of

time,

the

and/or

blowing

snow

to

reduce

possibility

of

extreme

value

attained,

and

any

additional

engine

flameout:

information

essential

in

determining

maintenance

action

required.

The

Snow

Deflector

Kit

or

the

Particle

Separator

Engine

Air

Induction

System

Intentional

use

of

transient

limits

is

Kit

and

the

Snow

Deflector

Kit.

(See

BHT-

prohibited.

206L3-FMS-3

and

BHT-206L3-FMS-7.)

Torque

events

shall

be

recorded.

A

torque

Refer

to

appropriate

Flight

Manual

event is

defined

as

a

takeoff

or a load

lift

Supplement(s)

for

additional

limitations,

(internal

or

external),

procedures,

and

performance

data.

1-2.

BASIS

OF

1-5.

FLIGHT

CREW

CERTIFICATION

The

minimum

flight

crew

consists of

one

pilot

This

helicopter

is

certified

under

Civil Air

who

shall

operate

the

helicopter

from

the

Regulation,

Parts

6,

Rotorcraft

Airworthiness,

right

crew

seat

Normal

Category.

The

left

crew

seat

may

be

used

for

an

1-3.

TYPE

OF

OPERATION

additional

pilot

when

the approved

dual

controls

are

installed.

seven-place

seating

and

is

certified

for

land

*

H

operation

under

day

or

night

VFR

nonicing

conditions.

1-7. WEIGHT

Flight

operations

are

approved

with

the

..

....

landing

gear

crosstube

fairings

installed

or

CAUTION

removed.

LOADS

THAT

RESULT

IN

GROSS

NOTE

WEIGHTS

ABOVE

4,150

POUNDS

(1882.4

KG)

SHALL

BE

CARRIED

ON

All

unsecured

items

shall

be

removed

AN

APPROVED

EXTERNAL

LOAD

KIT

from

cabin

when

any

door

is

removed.

AND

SHALL

NOT

BE

IMPOSED

ON

LANDING

GEAR.

18

DEC

2001

Rev.

5

1-3

BHT-206L3-FM-1

DOTAPPROVED

Maximum internal approved gross weight
for takeoff and landing is 4,150 pounds
(1882.4 kilograms).

Minimum combined crew weight at
fuselage station 65.0 is 170 pounds (77.1
kilograms) when operating in accordance
with the SELECTIVE PASSENGER
LOADING placard.

1-8. CENTER OF GRAVITY ­LONGITUDINAL

For gross weight longitudinal center of
gravity limits, refer to figure l-l.

The standard helicopter [standard seating
and fuel system) is ballasted in
accordance with the Weight Empty Center
of Gravity chart in the maintenance
manual. The SELECTIVE PASSENGER
LOADING placard shall be installed and
may be used for loading passengers only
within appropriate weight limitations
without computing center of gravity. When
passengers are seated other than in
accordance with the selective loading
placard or the baggage compartment is
utilized, the pilot is responsible for
determining weight and balance to ensure
gross weight and center of gravity will
remain within limits throughout each flight.

The helicopter with nonstandard fuel
system or seating arrangement is not

ballasted in accordance with the Weight
Empty Center of Gravity chart in the
maintenance manual. Selective passenger
loading does not apply and the

ALTERNATE placard shall be installed. The

pilot is responsible for determining weight
and balance to ensure gross weight and
center of gravity will remain within limits
throughout each flight.

Refer to BHT-206L3-MD-1 for loading
tables and instructions.

1-9. CENTER OF GRAVITY -

LATERAL

Lateral center of gravity limits are 4.0

inches (102 mm) left of and 3.5 inches (89

mm) right of fuselage centerline.

1-4 Rev. 4

1-10. DOOR(S) OFF

Determine weight change after doors have
been removed and adjust ballast if
necessary. Refer to BHT-206L3-MD-1.

1-11. AIRSPEED

Basic V,, is 130 KIAS (150 MPH) sea level

to 3,000 feet density altitude. Decrease V,,

for ambient conditions in accordance with
AIRSPEED LIMITATIONS placard (figure 1-

2).

V ne is 84 KIAS (96 MPH) at 85 to 100%
TORQUE takeoff power.

Vne, is 90 KIAS (104 MPH) with any door(s)
off, not to exceed placarded Vne.

1-12. ALTITUDE

Maximum operating pressure altitude is

20,000 feet.

NOTE

For high altitude pressure
operation, refer to appropriate
rules for oxygen requirements.

1-13.

AMBIENT AIR

TEMPERATURE

The maximum sea level ambient air
temperature for operation is +51.7°C

(+125°F) and decreases with pressure
altitude at the standard lapse rate of 2°C
(3.6°F)/1000 feet to 20,000 feet.

1-14. MANEUVERING

Aerobatic maneuvers are prohibited.

FAA APPROVED

BHT-206L3-FM-1

-119.2
(3026)

Figure 1-1. Gross weight center of gravity

1-5

BHT-206L3-FM-1

TC

APPROVED

|IU~~~

P/N

206-075-770-101

i" e

*0

S

a

Z

s

NOTE

Airspeed

limitations

panel

206-075-770-101

Is

applicable

if

Technical

Bulletin

206L-01-209

has

not

been

accomplished.

Airspeed

limits

shown

are

valid only

for

the

corresponding

altitudes

and

temperatures.

Dashes

indicate

conditions

which

exceed

approved

temperature

or

density

altitude

limitations.

206L3FM_121

Figure

1-2.

Placards

and

decals

(Sheet I of

3)

4

1-6

Rev. 5 18

DEC

2001

TC

APPROVED

BHT-206L3-FM-1

P/N

206-075-770-107

NOTE

Airspeed

limitations

panel

206-075-770-107

is

applicable

when

Technical

Bulletin

206L-01-209

has

been

accomplished.

Airspeed

limits

shown

are

valid

only for

the

corresponding

altitudes

and

temperatures.

Dashes

indicate

conditions

which

exceed approved temperature

or

density

altitude

limitations.

Figure

1-2.

Placards

and

decals

(Sheet 2 of

3)

TC APPROVED BHT-206L3-FM-1

Figure 1-2. Placards and Decals (Sheet 3 of 3)

AVOID CONT OPS 71.8% TO 91.5% N2

Location: Instrument panel.

206L3FM_1_0001

26 APR 2005 Rev. 6 1-7

BHT-206L3-FM-1 TC APPROVED

1-15. ELECTRICAL

1-16. GENERATOR

Continuous
operation

Maximum 90% DC LOAD

0 to 90% DC
LOAD

1-17. POWERPLANT

Allison model 250-C30P.

1-18. GAS PRODUCER RPM

Continuous
operation

Maximum 105%

Maximum transient
(Do not exceed 10
seconds above
105%)

63 to 105%

106%

Maximum continuous 100%

Transient overspeed
range

NOTE

Refer to Allison Operation and
Maintenance Manual for transient
overspeed limits.

100 to 103%

1-20. TURBINE OUTLET

TEMPERATURE (TOT)

WARNING

EXCEEDING 768°C TURB OUT TEMP
OR 100% TORQUE CAN CAUSE GAS
PRODUCER TOPPING WITH
RESULTANT ROTOR RPM DROOP.

Continuous
operation

100 to 716°C

1-19. POWER TURBINE RPM

WARNING

USE OF THE THROTTLE TO CONTROL
RPM IS NOT AUTHORIZED.

(REFER TO SECTION 3, EMERGENCY
PROCEDURES — ENGINE
OVERSPEED FOR EXCEPTION.)

Avoid continuous
operations

Minimum 97%

Continuous
operation

71.8 to 91.5%

97 to 100%

Maximum continuous 716°C

5 minute takeoff
range

Maximum for takeoff 768°C

Maximum transient
(Do not exceed 10
seconds above
768°C).

Maximum for starting
and shutdown (Do
not exceed 10
seconds above
768°C.)

716 to 768°C

871°C

927°C

1-8 Rev. 6 26 APR 2005

--

-

DOTAPPROVED

NOTE

Intentional use of power transient
area (768 to 871°C) is prohibited.
The TURB OUT TEMP gage is
equipped with a red warning light
that will illuminate when either of
the following conditions occur:

770 to 927°C more than 10

seconds or above 927°C.

1-21. ENGINE TORQUE

Continuous
operation

0 to 85%

Maximum continuous

85%

5 minute takeoff
range

85 to 100%

Maximum for takeoff

Maximum transient
(Do not exceed 5
seconds above
100%. Intentional use
prohibited.)

100%

105%

1-22. FUEL PRESSURE

Minimum

Continuous
operation

4 PSI

4 to 25 PSI

Maximum

25 PSI

BHT-206L3-FM-1

Minimum
Continuous

operation

4 PSI
4 to 25 PSI

Maximum
Minimum for use of

type A, A-l, or JP-5
fuel, or any mixture
of these, at ambient
temperature below ­18°C (0°F)

25 PSI
8 PSI

1-23. ENGINE OIL PRESSURE

Minimum below 79%

50 PSI
GAS PRODUCER (N,)
RPM

Minimum from 79 to

90 PSI
94% GAS
PRODUCER (N,) RPM

Minimum above 94%

115 PSI
GAS PRODUCER
RPM (N1) RPM

Maximum

130 PSI

1-24. ENGINE OIL TEMPERATURE

Continuous
operation

0 to 107°C

Maximum

107°C

I

l

Gage with red triangle at 8 psi.

Rev. 4

1-9

BHT-206L3-FM-1

DOT APPROVED

1-25. ANTI-ICE

The maximum ambient temperature for use

I

of engine anti-ice is

4.4°C (40°F).
ENGINE ANTI-ICING shall be ON for flight

I

in visible moisture in temperature below

4.4°C (40°F).

1-26. STARTER

Limit starter energize time to the following:

External Power Start Battery Start

40 Seconds ON

60

Seconds ON

30 Seconds OFF

60

Seconds OFF

40 Seconds ON

60

Seconds ON

30 Seconds OFF

60

Seconds OFF

40 Seconds ON

60

Seconds ON

30 Minutes OFF

30

Minutes OFF

1-27. TRANSMISSION

1-26.

TRANSMISSION OIL

PRESSURE

Minimum
Continuous

operation

Maximum

30 PSI
40 to 70 PSI

70 PSI

1-29. TRANSMISSION OIL

TEMPERATURE

Continuous
operation

15 to 110°C

Maximum

110°C

1-30. ROTOR

1-31. ROTOR RPM - POWER ON

Minimum transient
(Do not exceed 5
seconds)

-

95%

Minimum

Continuous
operation

Maximum continuous

Maximum transient

during low power

descent. (Do not

exceed 6 minutes

above 100%.)

97%
97 to 100%

100%
103%

1-32. ROTOR RPM - POWER

OFF

Minimum

90%

Maximum

107%

1-33. FUEL AND OIL

1-34. FUEL

Turbine fuel ASTM-D-1655, Type B, or MIL-

T-5624, Grade JP-4, may be used at all
ambient temperatures.

1-10

DOT APPROVED BHT-206L3-FM-1
Turbine fuel ASTM-D-1655, Type A or A-l,

or MIL-T-5624, Grade JP-5, (NATO F-44), or
MIL-T-83133, Grade JP-8, (NATO F-34),

limited to ambient temperatures above .

- -17.8% (0°F).
Turbine fuel ASTM-D-1655, Type A or A-l,

or MIL-T-5624, Grade JP-5, (NATO F-44), or
MIL-T-83133, Grade JP-8, (NATO F-34),
limited to ambient temperatures -32°C

(-25°F) and above when equipped with fuel

pressure gage with red triangle at 6 psi.

NOTE

Anti-icing fuel additives are not
required for any ambient

temperature.

fer to Allison Operation and

intenance Manual for cold weather fuel

and blending instructions.

Re

Ma

1-35. ENGINE OIL

Turbine oil MIL-L-7808 may be used at all
ambient temperatures.

DOD-L-85734(AS) or MIL-L-23699 limited to
ambient temperatures above -40°C (-40°F).

NOTE

Refer to Allison Operation and
Maintenance Manual and BHT­206L3-MD-1 manual for approved
oils and mixing of oils of different
brands, types, and manufacturers.

1-36. TRANSMISSION AND TAIL
ROTOR GEARBOX OIL

Turbine oil MIL-L-7808 may be used at all
ambient temperatures.

DOD-L-85734(AS) or MIL-L-23699 limited to
ambient temperatures above -40°C (-40°F).

1-37. HYDRAULIC

Hydraulic fluid MIL-H-5606 may be used at
all ambient temperatures.

Rev. 4

1-11

BHT-206L3-FM-1

DOT APPROVED

ENGINE OIL PRESSURE

50 PSI

Mhmum

50 to so PSI

Operation below
79% Nl RPM

so to 115 PSI

Continuous operatmn
below 94% Nl RPM

115 to 130 PSI

Contmuous operation

130 PSI

Maximum

ENGINE OIL TEMPERATURE

m 0 to 107oc

Continuous operation

­Maximum

TRANSMISSION OIL PRESSURE
30 PSI

Mmlmum

40 to 70 PSI

Continuous operatlo”

70 PSI

Maximum

TRANSMISSION OIL TEMPERATURE
15 to 110°C

Continuous operatmn

110°C

Maxmum

GAS PRODUCER RPM (Nl,

Continuous operation
Maximum

L206075-205-l

Figure 1-3. instrument markings (Sheet 1 of 3)

1-12

Rev. 4

.

DOT APPROVED

BHT-206L3-FM-1

TORQUE

0 to 85%
85 to 100%
100%

TURBINE OUTLET

m

100 to716 C

r”

716fo768 C
768 C

@

927 C

a

Warn1nq lqht

Continuous operatmn
5 Mmute takeoff range
Maximum

TEMPERATURE

Continuous operatmn
5 Minute takeoff range
Manmum for takeoff

MaxImum for start and
shutdown (1 second max )

TOT between 770 and 927 C
longer than 10 seconds.
or TOT above 927 C

NOTE

Range Mark at 999 “C
Any one of the two turbme

outlet temperature gages
may be mstalled I” hellcopter

POWER TURBINE RPM (N2)

97%
97% to 100%
100%
100 to 103%

Minimum
Continuous operation
Maximum continuous

Transient overspeed
range f 5 minutes rmx.)

Mnmum (power off)
Continuous operat,on (power off)
Mawmum (power off)

Fiaure 1-3.

Instrument markings (Sheet 2 of 3)

BHT-206L3-FM-1

DOT APPROVED

AIRSPEED

:o 130 Knots
IO Knots

130 Knots

Continuous operation
Maximum for autorotation
Maximum

FUEL QUANTITY
0

Empty (zero usable)

“L LUAU

I 90%

Maximum

FUEL PRESSURE

4 PSI

Minimum

4 to 25 PSI

Continuous operatio

I 25 PSI

Maximum

I

NOTE: Either indicator may

be

installed.

m

DC LOAD

n

Maximum

FUEL PRESSURE

m 4PSI

Minimum

0 25 PSI

Continuous operation

PSI Maximum

A

8 PSI Minimum Type A, A-l, or JP-5

fuel below 18°C (O°Fj

Figure 1-3.

Instrument markings (Sheet 3 of 3)

1-14 Rev.

4

FAA APPROVED

BHT-206L3-FM-1

Paragraph

TABLE OF CONTENTS

2-1
2-2
2-3
2-4
2-6
2-6
2-7
2-6
2-9
2-10
2-11
2-12
2-13
2-14
2-15

2-16
2-17
2-l 6
2-19
2-20
2-21
2-22
2-23
2-24
2-25
2-26

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

OPERATING LIMITATIONS ..............................................

FLIGHT PLANNING ......................................................

TAKEOFF AND LANDING DATA

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

WEIGHT AND BALANCE

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

PREFLIGHT CHECK .....................................................

BEFORE EXTERIOR CHECK

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

EXTERIOR CHECK..

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

FUSELAGE - CABIN RIGHT SIDE..

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

FUSELAGE - CENTER RIGHT SIDE..

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

FUSELAGE - AFT RIGHT SIDE

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

FUSELAGE - FULL AFT..

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

FUSELAGE - AFT LEFT SIDE

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

FUSELAGE - CABIN LEFT SIDE

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

FUSELAGE - FRONT ..............................................

INTERIOR AND PRESTART CHECK.. ...................................

ENGINE STARTING.. ....................................................

PRELIMINARY HYDRAULIC SYSTEMS CHECK..

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

ENGINE RUNUP .........................................................

HYDRAULIC SYSTEMS CHECK

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

BEFORE TAKEOFF ......................................................

TAKEOFF ................................................................

INFLIGHT OPERATIONS.. ...............................................

DESCENT AND LANDING ...............................................

ENGINE SHUTDOWN ....................................................

AFTER EXITING HELICOPTER

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

LIST OF FIGURES

Figure
Number Title

Page

Number

2-3
2-3
2-3
2-3
2-3
2-3
2-5
2-5
2-5
2-5

2-6

2-6

2-7

2-8
2-8

2-9
2-10
2-11
2-11
2-l 1
2-11
2-12
2-12
2-12
2-13
2-13

Page

Number

2-l

Preflight check sequence . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4

2-112-2

FAA APPROVED

BHT-206L3-FM-1

2-1. INTRODUCTION

This section contains instructions and

procedures for operating the helicopter
from the planning stage, through actual
flight conditions, to securing the

helicopter after landing.

Normal and standard conditions are

assumed in these procedures. Pertinent

data in other sections is referenced when

applicable.

The instructions and procedures contained

herein are written for the purpose of

standardization and are not applicable to

all situations.

2-2. OPERATING

LIMITATIONS

The minimum and maximum limits, and the

normal and cautionary operating ranges

for the helicopter and its subsystems are

indicated by instrument markings and

placards. The instrument markings and

placards represent careful aerodynamic

calculations that are substantiated by

flight test data. Refer to Section 1,

--

LIMITATIONS, for a detailed explanation of

each operating limitation.

2-3. FLIGHT PLANNING

Each flight should be planned adequately
to ensure safe operations and to provide
the pilot with the data to be used during
flight.

Check type of mission to be performed

and destination.

Select appropriate performance charts to

be used from Section 4, PERFORMANCE.

2-4. TAKEOFF AND LANDING

DATA

Refer to Section 1 for takeoff and landing

weight limits and to Section 4 for

performance information.

2-5. WEIGHT AND BALANCE

Determine proper weight and balance of

the helicopter as follows:

1.

Consult BHT-206L3-MD-1 for
instructions.

2. Compute takeoff and anticipated
landing gross weight, check
helicopter center of gravity (CG)
locations, and determine weight of

fuel, oil, payload, etc.

3. Ensure weight/CG limits listed in
Section 1 have not been exceeded.

2-6. PREFLIGHT CHECK

The pilot is responsible for determining
whether the helicopter is in condition for
safe flight. Refer to figure 2-l for preflight
check sequence.

NOTE

The preflight check is not
intended to be a detailed
mechanical inspection, but simply
a guide to help the pilot check the
condition of the helicopter. It may

be as comprehensive as
conditions warrant at the
discretion of the pilot.

Rev. 1

2-31

BHT-206L3-FM-1

FAAAPPROVED

Figure 2-1. Preflight check sequence

2-4

DOT APPROVED

BHT-206L3-FM-1

All areas checked shall include a
visual check for evidence of
corrosion, particularly when
helicopter is flown near or over
salt water or in areas of high
industrial emissions.

3.

Hydraulic system filters ­Bypass indicator retracted.

4.

Hydraulic actuators and lines ­Condition, security, interference,
leakage.

2-7. BEFORE EXTERIOR
CHECK

5.

6.

Forward fairing - Secured.

--

1. Flight planning - Completed.

2. Publications - Checked.

3.

Gross weight and CG ­Computed.

4.

Helicopter servicing -

Completed.

5. Battery - Connected.

Transmission

- Check oil level.
Verify actual presence of oil in
sight gage.

7. Transmission oil cooler lines ­Condition and security.

6.

Nodal beam - Check condition
and security of elastomeric
bearings, elastomeric straps, and

fore and aft restraint damper.

9.

2-8. EXTERIOR CHECK

2-9. FUSELAGE

- CABIN RIGHT

Main driveshaft forward coupling

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

temperature indicated by dot

changing color to black.

SIDE

1.

2.

3.

4.

5.

2-10.

Right static port - Condition.
Cabin doors - Condition and

security.

Windows

- Condition and

security.

Landing gear - Condition and

ground handling wheel removed.

Forward and aft crosstube
fairings - Secured, condition,
and aligned.

FUSELAGE

- CENTER

RIGHT SIDE

1. Engine inlet - Condition; remove
inlet covers.

2. Cabin roof, transmission cowling,
and engine air inlet area ­Cleaned of all debris and
accumulated snow and ice;
cowling secured.

IF ANY TEMP-PLATE IS MISSING
OR HAS BLACK DOTS
MAINTENANCE PERSONNEL
SHALL ASSIST IN DETERMINING
AIRWORTHINESS.

10. Access door - Secured.

11. Rotor head - Condition.

12. Fuel filler cap - Visually check
fuel level and cap secured.

13. Fuel sump - Drain fuel sample
as follows:

a. FUEL BOOST circuit breakers

- out.

b. BAT switch - On.
c. FUEL VALVE switch - OFF.
d. PUSH FOR FUEL SUMP DRAIN

button -

Press, drain sample,

then release.

Rev. 3 2-5

BHT-206L3-FM-1

DOTAPPROVED

NOTE

Forward fuel cells can be drained
manually as desired.

14. A/F fuel filter - Drain and check
before first flight of the day as
follows:

a. FUEL VALVE switch - ON.
b. FUEL BOOST circuit breakers

- In.

c. Fuel filter drain valve - Open,

drain sample, then close.

NOTE

Filter test button is located on top

of fuel filter.

15. Fuel filter test button - Press

and check FUEL FILTER caution
light illuminated. Release switch
and check light extinguished.

16. FUEL VALVE switch - OFF.

17. BAT switch - OFF.

16. Powerplant Area

a. Main driveshaft aft coupling -

Condition, security, and grease

leakage. Check Temp-Plates
(four places) for evidence of
elevated temperature indicated

by dot changing color to black.

IF ANY TEMP-PLATE IS MISSING

OR HAS BLACK DOTS,

MAINTENANCE PERSONNEL
SHALL ASSIST IN DETERMINING
AIRWORTHINESS.

b. Engine - Condition; security

of attachments. Evidence of oil
leakage.

c. Engine mounts - Condition

and security.

d. Throttle linkage - Condition,

security,

and freedom of

operation.

e. Fuel control and mechanical

fuel pump - Security and
condition; evidence of leakage,
governor air lines.

f. Hoses and tubing - Chafing,

security, and condition.

19. Engine cowl - Secured.

20. Generator cooling scoop ­Clear of debris.

21.

Oil tank - Oil level, leaks,
security, and cap secured.

22. Access door - Secured.

23. Aft fairing - Secured.

2-11. FUSELAGE - AFT RIGHT
SIDE

1. Fuselage - Condition.

2. Tail. rotor driveshaft cover -

Condition and security.

3. Tailboom - Condition.

4. Horizontal stabilizer and position

light - Condition and security.

5. Sync elevator - Check lateral
freedom, bearing play, and clear
of obstructions.

6. Main rotor blade - Condition.

2-12. FUSELAGE - FULL AFT

1. Vertical fin - Condition.

2. Tail rotor guard - Condition and

security.

3. Anticollision light - Condition
and security of lens.

4. Aft position light - Condition.

5. Tail rotor gearbox - Oil level,
leaks and security.

2-6

Rev. 3

DOT APPROVED

6. Tail rotor - Tiedown removed,
condition and free movement.

7. Tail rotor controls - Condition and

security.

6. Tail rotor blades - Condition; tip
block security, evidence of

corrosion, and seal condition.

2-13. FUSELAGE - AFT LEFT
SIDE

FAILURE TO REMOVE ROTOR

TIEDOWNS BEFORE ENGINE

STARTING MAY RESULT IN
SEVERE DAMAGE AND POSSIBLE
INJURY.

1.

Main rotor blade - Tiedown
removed; condition.

2. Tailboom - Condition.

3. Tail rotor driveshaft cover ­Condition and security.

4. Horizontal stabilizer and position

light - Condition and security.

6. Sync elevator - Check lateral
freedom, bearing play, and clear of
obstructions.

6. Fuselage - Condition.

7.

Forward tail rotor driveshaft
coupling - Condition of splined
adapter.

6. Oil cooler blower shaft hanger
bearings - Evidence of grease
leakage and overheating.

9. Oil cooler blower - Clear of
obstruction and condition.

10. Oil cooler - Condition and leaks.

BHT-206L3-FM-1

11. Oil cooler access door - Secured.

12. Aft fairing - Secured.

13. Baggage compartment - Cargo
tied down, door secured.

14. Exhaust cover - Removed.

15. Powerplant Area
a. Engine - Condition; security of

attachments.

b. Engine mounts - Condition and

security.

c. Exhaust stack - Condition and

security.
d. Evidence of fuel and oil leaks.
e. Hoses and tubing for chafing

and condition.

f. Pneumatic lines - Condition and

security.

g.

Linear actuator and governor
control linkage - Condition and
security.

h.

Tail rotor driveshaft - Condition

of splines, couplings, and
freedom of movement.

i. Air induction diffuser hose -

Condition and security.

j. Engine cowling - Secured.

k. Air Induction cowling -

Secured.

I.

Cabin roof, transmission

cowling, engine air inlet area,

and plenum - Clear of all debris
and accumulated snow and ice;
cowling secured.

16. Transmission Area

2-7

BHT-206L3-FM-1

DOT APPROVED

a. Nodal beam - Condition and

security of elastomeric
bearings, elastomeric strap,
and fore and aft restraint
damper.

I

b. Transmission oil filter bypass

button - Ensure not extended.

c. Main driveshaft forward

coupling - Condition and
evidence of grease leakage.
Check paint strip for evidence
of overheat indicated by brown
color.

d. Cockpit indicator pressure

lines - Condition and security.

e. Access door - Secured.

2-14. FUSELAGE - CABIN LEFT
SIDE

1. Main rotor hub and yoke ­Condition.

2. Main rotor blade doublers and

skin - Condition.

3. Pitch horn trunnion bearing -

Wear and security.

4.

Main rotor pitch links ­Condition and security of
attachment bolts and locking

hardware.

6. Swashplate assembly ­Condition, security of attached
controls, and boot condition.

6. Control linkages to swashplate -

Condition, security of attachment
bolts and locking hardware.

7. Forward fairing and access door

- Secured.

6. Cabin doors and hinge pins ­Condition and security.

9. Windows - Condition and

security.

2-8 Rev. 4

10. Hydraulic reservoir - Check
fluid level.

11. Landing gear - Condition and

ground handling wheel

removed.

12.

Forward and aft crosstube
fairings - Secured, condition
and aligned.

13. Left static port - Condition.

2-15. FUSELAGE - FRONT

1. Exterior surfaces - Condition.

2. Windshield - Condition and

cleanliness.

3.

Battery and vent lines ­Condition and security.

4. HOUR METER circuit breaker ­In.

5.

FUEL BOOST LEFT circuit
breaker - In.

6. Battery access door - Secured.

7. Pitot tube - Cover removed,

clear of obstruction.

6. External power door - Condition

and security.

NOTE

APU should be 500 amperes or
less to reduce risk of starter
damage from overheating.

9. Landing light glass - Condition.

10. Antennas - Condition and
security.

11. Main rotor blade - Condition.

12. External power - Check BAT
switch OFF and APU connected
as desired.