Bell BHT-206L3-FM-1 LongRanger-III Technical specifications
COPYRIGHT NOTICE
COPYRIGHT
2005
BELL
®
HELICOPTER TEXTRON INC.
AND BELL HELICOPTER TEXTRON
CANADA LTD.
ALL RIGHTS RESERVED
BHT-206L3-FM-1
MODEL
206L3
28 OCTOBER 1992
REVISION 6 — 26 APRIL 2005
ROTORCRAFT
FLIGHT MANUAL
THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS
BHT 51001 THROUGH 51612
NOTICE PAGE
Additional copies of this publication may be obtained by contacting:
Commercial Publication Distribution Center
Bell Helicopter Textron Inc.
P. O. Box 482
Fort Worth, Texas 76101-0482
PN
BHT-206L3-FM-1
TC APPROVED BHT-206L3-FM-1
NOTE
Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of
superseded pages.
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
Revision ................ 10....................... 04 DEC 89
Revision ................ 11....................... 25 MAY 90
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
Revision .................. 5....................... 18 DEC 01
Revision .................. 6....................... 26 APR 05
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26 APR 2005 Rev. 6 A/B
BHT-206L3-FM-1
APPROVED: DATE:
CHIEF, FLIGHT TEST
FOR
DIRECTOR — AIRCRAFT CERTIFICATION
TRANSPORT CANADA
LOG OF TC APPROVED 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
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
26 APR 2005 Rev. 6 C/D
BHT-206L3-FM-1
APPROVED: DATE:
CHIEF, FLIGHT TEST
FOR
DIRECTOR — AIRCRAFT CERTIFICATION
TRANSPORT CANADA
LOG OF FAA APPROVED 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
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
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 OFPROCEDURAL 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 ...............
..............................
TOT) . . . . .. . . . . . .. . . . . . . . . . . . .
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).
Vne 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
altitudelimitations.
Figure
1-2.
Placards
and
decals
(Sheet
2
of
3)
TC APPROVED BHT-206L3-FM-1
26 APR 2005 Rev. 6 1-7
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
BHT-206L3-FM-1 TC APPROVED
1-8 Rev. 6 26 APR 2005
1-15. ELECTRICAL
1-16. GENERATOR
1-17. POWERPLANT
Allison model 250-C30P.
1-18. GAS PRODUCER RPM
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.)
NOTE
Refer to Allison Operation and
Maintenance Manual for transient
overspeed limits.
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
0 to 90% DC
LOAD
Maximum 90% DC LOAD
Continuous
operation
63 to 105%
Maximum 105%
Maximum transient
(Do not exceed 10
seconds above
105%)
106%
Avoid continuous
operations
71.8 to 91.5%
Minimum 97%
Continuous
operation
97 to 100%
Maximum continuous 100%
Transient overspeed
range
100 to 103%
Continuous
operation
100 to 716°C
Maximum continuous 716°C
5 minute takeoff
range
716 to 768°C
Maximum for takeoff 768°C
Maximum transient
(Do not exceed 10
seconds above
768°C).
871°C
Maximum for starting
and shutdown (Do
not exceed 10
seconds above
768°C.)
927°C
--
-
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 BHT-
206L3-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
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