BHT214ST Flight Manual

A S ub sid ia ry of Textr on Inc .
POST OFFICE BOX 482 FORT WORTH, TEXAS 76101
Bell HelicopterCOPYRIGHT NOTICE
BHT-214ST-FM
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
PROPRIETARY RIGHTS NOTICE
These data are proprietary to Bell Helicopter Textron Inc. Disclosure, reproduction, or use of these data for any purpose other than helicopter operation and/or maintenance is forbidden without prior written authorization from Bell Helicopter Textron Inc.
NP Rev. 14 15 OCT 2002

NOTE
Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of
superseded pages.
Revision.....................1 .....................15 OCT 82
Revision.....................2 ..................... 09 JUN 83
Revision.....................3 ..................... 13 JUN 84
Revision.....................4 .....................13 DEC 84
Revision.....................5 ..................... 17 SEP 85
Revision.....................6 .....................23 OCT 87
Revision.....................7 .................... 16 MAR 88
15 OCT 2002 Rev. 14 C/D

MANAGER
intended
when application Kn
Compliance
with
Certified
Certified for VFR day or night operation with (4355 kg)
operable
operable SCAS.
Aerobatics
prohibited.
01 cooler/bleed
prohibited.
takeoff.
system
noperative
VNE ailed
FBW elevator
NOTE
Refer
12.000
AIRCRAFT HOVER
13 14 15 16 17 18
OAT -
°C
weight-altitude-temperature
limitations
IGHT
NOTE
LIMIT
MINIMUM
PERATINGEMP
MAX.
OAT
6000
4000
MIN
GROSS
WEIGHT
LIMIT
2000
-60-40-20 0 20 40 60 40 45 50 66 60 65 70 75 80
OAT -
°C
GROSS
WEIGHT-
kg
Height-velocity
limitations
A M B IE N
T A
AT
lapse rate of 2°C (3.6°F)/1000 feet to 20,000
feet.
IFR maximum
- 1500 ft/min.
Vy VFR - 78 KIAS.
to ambient
similar warm environment at a
temperature of -20°C (-4°F) or above
for a minimum of four hours prior to
engine start when ambient
Once the first
to -13
below
helicopter
from
standard helicopter instrument panel
BHT-214ST-FM
internal cargo operations.
operation.
MIL-T-5624, Grade JP-4, may be used at all
ambient temperatures above -40°C (-40°F).
Fuel conforming to ASTM D-1655 JET A, JET
A-1, or MIL-T-5624, Grade JP-5, may be used
at ambient temperatures above -34°C
(-29.4°F).

to -20°C.
During start engine oil pressure may
30 Minute Range 101.2 to 101.7% exceed 180 psi for maximum of two
minutes
range (40 to 100 psi) after
five minutes
TWIN
FLIGHT MANUAL
LIMITS
LIMITATIONS
(Transmission
scale
Continuous Operation 10
to 69.1% HYDRAULIC
TEMPERATURE LIMITS
°
1-18 Rev. 1
80% MIN
1-24
Rev.
5
FLIGHT MANUAL
section
They are approved for use in the operation of
this helicopter.
Publications - Checked.
It may be made as comprehensive as
Performance
Requirements
- Completed.
conditions
Pilots
Upper navigation light - Condition.
Condition and security, including
leaks.
MENTS AND
TAILBOOM, RIGHT
Tailboom - Skin
Tail rotor driveshaft cover - Condition Hydraulic ground power access
and security. panel - Closed and secure.
Aft
ted and condition.
security, secured.
Door
Security.
6. COPILOT
Pilot seat belt and
Condition and security. Condition and security.
Pilot seat
- Condition
Main rotor blades - Condition and Cockpit doors - Secured. All latches
security. seated. Indicator pins out of view.
Nodal beam ram air inlet - Unobstruc- Cabin doors - Secured. Indicator pins out
ted.
Transmission
- Check.
FORCE TRIM
switch - ON.
ENGINE 1
FUEL switch -
OFF.
ENGINE
Fresh
air
vents
- As
desired.
COMM
NAV AUDIO/marker beacon - OFF.
ELEV
switches - OFF.
XPDR - OFF.
momentarily retract from view.
2 for STBY ATT switch
- OFF.
HYD SYS
1 switch
Rev. 9 2-9
FLIGHT MANUAL
HEATER
SEC
CAUTION
lights
illuminate.
PED
ENGINE INST LT rheostat - OFF. to test. Observe lights illuminate.
PILOT
PITOT
VENT BLOWER
switch - OFF.
ON. tanks is unequal,
equalize fuel loading.
CLOSEposition prior to takeoff.
shall be ON for an APU assisted start or
for battery
BATT 2 posi-
tions and check 24 V indications.
2-10
Rev.
6
FUEL
PRIME
ENG
1
- ON.
ENG
Ng indication, refer to FALSE
switch.
ON.
NOTE
for
cross
start.
ENGINE
V I
20 psi or greater after reaching idle Ng,
67 + No. 2 throttle - Advance
to equalize Ng
3%. speeds with rotor rpm at 95% Nr or above.
NOTE
exceed 180 psi
range (40 to 100 psi) after five minutes
of operationat idle.
STOP
MONITOR
ENGINE
PSI.
AND ZERO TORQUE. IF AN ENGINE
ROTOR RPM light-Illuminatesabove80%
DOES NOT ENGAGE
RPM AUDIO switch - OFF.
TWIST GRIP OF THE
GENERATOR
THAT FAILED TO ENGAGE ON
INVERTER
FLIGHT MANUAL
EMERG lights extinguish.
EMERG lights illuminate.
ON. Check GEN caution lights out.
NON ESNTL BUS CONTROL switch — ON.
BATTERY NO. 1 and NO. 2 switches — ON.
BATTERY BUS NO. 1 and NO. 2 switches —
ON.
light illuminates. Check inverter 2 assumes
AC load.
caution lights illuminate. Observe that pilot
and copilot ATT and HSI OFF flags are in
view.
caution lights extinguish.
extinguishes.
after gyros return to speed.
HYDRAULIC CHECKS
determine proper operation of the
hydraulic actuators for each flight
control system. If abnormal forces,
unequal forces, control binding or
motoring are encountered, it may be an
indication of a malfunction of a flight
control actuator.
Rotor rpm (NR) — Set to 100%.
HYD SYS 1 switch — OFF. Check NO. 1 HYD
caution light and MASTER CAUTION light
illuminate and system 1 pressure drops to zero.
Cyclic — Centered, friction removed.
cyclic forward, aft, left and right a slight amount
(approximately one inch). Center cyclic.
Collective — Check for normal operations by
increasing collective control slightly (1 to 2
inches). Repeat 2 to 3 times as required. Return
to full down position.
Note no increase in force required to move
pedals.
NOTE
hydraulic systems from being
both hydraulic switches are in the
OFF position, an interlock causes
both systems to operate at normal
pressure.
remains operational and system 1 becomes
operational.
remains operational. Check NO. 2 HYD
segment illuminates and system 2 pressure
drops to zero.
cyclic forward, aft, left and right approximately
one inch. Center cyclic.
increasing collective control slightly (1 to 2
inches). Repeat 2 to 3 times as required. Return
to full down position.

increase
BLEED AIR override switch
HYDSYS 2 switch-ON.
FORCE TRIM switch - ON. OIL COOLER and UTILITY HYD caution
lights extinguish and BLEED AIR test switch
trips to NORM.
SYSTEM
CHECK
Decrease engine number two to flight idle. CABIN HEATER switch - ON.
Set power
illuminates.
Defrost control
1
OVRD. Observe OIL COOLER caution light DEFOG knob - Pull. Check for ositive
extinguishes.irflow
NUMBER TWO ENGINE DEFOG nob - As desired. (If dual pilot)
Prior
BLOWER switch - ON.
Increase collective until 85% Ng is reached. airflow.
Rev. 9 2-15
Vent outlet - As desired. Collective - Increase till helicopter is light
on landing
As desired.
required.
NOTE
ELT
to
If Air Data Computer displays a
Manual check of heat rise on pitot power assurance indication of less
tubes
and
staticports.
PITOTS PRIOR TO TURN ON TO
PREVENT
BURN.
PITOT STATIC HTR
(FOVERSPEED
ENG 1 switch - ON. No. 1 engine Ng - Note RPM.
ENGINE
NOTE
FLIGHT
MANUAL
BHT-214ST-FM
FBW ELEVATOR CHECK
and Upon completion
extinguishes
a
AFCS CAUTION
Elevator position indicator switch - SYS 1.
A/S 3 test switch - FAIL.
MON TEST switch - SYS 1.
NOTE
NOTE
Elevator
position
indicator
SYS
2.
NOTE
ELEV
SYS
ator
(green
R, and FLT CONTROLS annunciator
panel lights
AARS
CHECK
extinguished.
MONITOR
MONITOR
switch
GRAVITY INTCON switch - Check
CLOSE.
AARS ENGA light - Push. Note ENGA PITOT STATIC HTR switches - As desired.
light illuminates,
ATTD TRIM control (Chinese Hat) - Check
operation.
Rotor
HDG bug
displace
required
to
hover
below).
ICE operation prior to takeoff.
Cyclic control
IGE plus an additional
If AC or DC
-OFF. Install main rotor blade
tiedown socks on blades
ROTOR STOPS, THEN ENSURE Total unusable fuel - 30 pounds.
HANDLE IS RETURNED TO
main cell provides independent
Remainder
lower main cells permits
switches -
BATTERY
- OFF. ON.
RNAV annunciator - Illuminated. If either anti-ice advisory light fails to
illuminate, locate
- As desired.
BRG PTR NO. 1 switch - NAV 1. Green ENGINE INLET ANTI-ICE
pointer
- ON.
NO.
ENG 1 and
switches ON.
6°C (43°F).
ROTOR beep switch - Hold in either UP or (Tests with ambient temperatures
DOWN
until
vibration
level
is
above
flights.
NOTE
ALT
HLD
TRIM button
tions may be observed.
to aircraft heading.
COLD WEATHER OPERATIONS
HDG SEL - ENGA.
of three
When heading
Altitude - Stabilized.
high engine
Engine and engine inlet anti-icing systems
Run engine at idle speed until oil pressure is shall be turned on after reaching idle speed
within limits. Oil pressure should return to 40- when ambient temperature is 4°C (40°F) or
100 psig after operating 5 minutes. However, colder and visible moisture is present.
time
required
will
depend
on
temperature of the engine and oil system prior BLEED AIR HEATER
to start.
and may
exceed 180 psig for maximum of two minutes. The initial vibration at the crew and passenger
The engine should remain at idle speed until oil stations will be abnormally high if the aircraft
pressure
was exposed to ambient temperatures
of
pressure 0°C(32°F) or less for periods
of 6 hours or more
above 120 psig. prior to flight. Time required for vibration to
diminish to normal
occurred,
FLIGHT MANUAL
HydraulicActuator ServoValve
SCAS Failure AARS
AARS
..................................
LAND
Urgency
FLIGHT
MANUAL
SLIDING
DOOR
EMERGENCY
XIT
WINDOW.
Release.
3.
Exit
helicopter.
WARNING AND CAUTION LIGHTS
MASTER CAUTION
DOWN
DETERMINED THAT IT IS
1. Same corrective action as
stated for
Eng 1.
condition for
CARGO HOOK
ARM, CARGO
WARN.
FUEL PRESS Fuel Suction
in appropriate
limitations.
(Green)
89%
2. Check circuit breakers.
situations where full power is required.
Observe placarded Ng limits with the
ANTI-ICE ON.
PANEL WORDING FAULT CONDITION PILOT CORRECTIVE ACTION
ECU LOCKOUT Respective engine 1. Check for overspeed indication and con-
(#1 or #2) in ECU
lockout. trol RPM
prior to next flight.
Oil filter bypass
FUEL VALVE
fuel switch for desired position.
(#1
or
#2)
4.
1. Check TRANS PUMP switch
position.
NO.
3. GRAVITY
INTCON switch
FLIGHT
MANUAL
ENG
engine.
good engine.
3. Shut
down engine
engine gages, noise, etc.
NO. 1 FUEL
FILTER/ Fuel filter
PRACTICAL.
POSSIBLE.
or
switch to SECONDARY.
handle - Detent position.
SOON AS POSSIBLE.
(Red)
2.
in accordance
with manufacturer's
NO. 2 BATT
°
NOTE
Electrical
oads
FIRE ENG 1 Engine compartment 1. Close No. 1 throttle.
(Red)
fire.
3. Execute
single-engine procedures.
(Red)
L BAG FIRE/ Smoke, fumes or 1. LAND AS SOON AS POSSIBLE.
R BAG
panel segment GRBX CHIP
will illuminate along with
MASTER CAUTION light for any segment on the chip indicator panel.
PANEL WORDING FAULT
attempt chip burnoff.
4. If chip light fails to extinguish: Reset
MASTER CAUTION light. LAND AS
SOON AS POSSIBLE.
°
or 90
attempt chip burnoff.
MASTER
in 1. Push CB 1 or CB 2 chip
indicator 3 times
gearbox.
CB 1/CB 2 Imminent
affected engine.
tion.)
SUMP (Accompanied bining gearbox failure.
by CBOX OIL light
detector 3 times to
SOON
AS
POSSIBLE.
controlled by electronic control unit (E.C.U.)
and hydro-mechanical unit (H.M.U.). Direct
INTRODUCTION
and the load demand spindle
designed
FLIGHT
MANUAL
Engine failures or malfunctions can be by providing power from 3 independent
grouped into two major categories, electrical windings, one for each function. The E.C.U.
(normally associatedwiththe E.C.U.) and non- receives following inputs:
electrical
setting 4 Measured gas temperature
(MGT).
minute cooldown. If a
signal from opposite engine for
not possible without overtemping the gearbox(s) load sharing.
oil, the
has provisions for
(PAS) in
engine damage.
generator
to
idle
Ng
power,
there
still
remains
is initiated within 5
potential for actual engine failure.
c. The engine is allowed to cool
for4 Engine control systems
maintain constant Np speed even in event of a
failure of
one engine.
In order
to maintain
constant rotor
engine
and ignition
operation will
cause operating
engine to
engine.
The
(possibly).
affected engine decrease.
OUT-OF-GROUND
EFFECT)
Indications:
4. LAND
AS SOON
5.
Helicopter
- SHUTDOWN.
SINGLE ENGINE
density altitude.
2. Master caution light and appropriate helicopter gross weight, proximity of a
caution
left.
Except
failure is encountered
4. Failed
FLIGHT MANUAL
decrease both
amount that rotor rpm will increase is Rotor RPM Control.
dependent upon gross
weight and rate
that 2. Throttle
2. ROTOR RPM decreases.
4. Both engines instrument readings
CAUTION
decrease.
NP GOVERNING, MGT LIMIT-
airstart.
shut off fuel.
3.
MGT
decrease.
may
increase
3%
or
higher
depending
on
rotor
FLIGHT MANUAL
(affected
overspeed
ENGINE PRIME
engine) -ON
for start.
2,. Throttle (affected engine)
-RETARD 9. Throttle (affected
3. Engine power -
Set and maintain
4. Engine
higher MGTisenginewithfailureand
OPEN (if no
3.
TRANS
PUMP
switch
(both
engines)
sensitivity
and
decrease
stall
margin
are
- Check
ON.
4. Engine oil temperature
(affected ing fuel control
4. Increasing
or erratic
2. Throttle (affected
engine) - 1. Firewarninglightilluminated(Eng
4. Maintain slow cruise flight. 3. Fire.
If compressor stalls persist: Procedures:
1. Throttle
2. Perform single
In event a jam
section is
up" RLSE switch - BTL
engine. The LDS
and electrical switches - OFF.
is reached.
illuminates.
bleed
air
valves,
causing
loss
FLIGHT MANUAL
If fire is no longer
evident or an
5. GENERATOR switches - ON
The key to successful handling of a tail rotor
7. INVERTER
8. Necessary
If fire is evident
COMPLETE LOSS OF
2. Suspect
3. LAND AS SOON
slip) and usually
If
and density altitude.
6. LAND AS SOON AS POSSIBLE.
1. HOVERING.
Chop throttles
autorotation landing.
the higher power
smoke and loss of visibility, etc. shall be required in a climb maneuver, the degree of
immediately
to
NOTE
into
to the
right can be more nearly streamlined by the If altitude permits with airspeed
use
a. If the throttles are
not off at the time
desirable. It is essential
that the of the
failure, roll them off.
LIMITS
loss
off, a slight
maximum effort, since a more
serious
slightly
although
1.
If pedals lock
power
controlled
about
area
2. FORWARD FLIGHT. If control is lost as effective translational lift is lost.
during climb
a. Right Pedal Locked Forward of ment with the throttle.
Neutral:
(1) Power
approach.
(2)
Execute
the
to
After ground contact use collective and follow the turn until the ship has come to a
throttle as necessary to maintain alignment complete stop.
with the landing
strip, and minimize
cyclic as necessary
tail
3-23
SOMEWHAT COMPARABLE TO
executed more IMMEDIATELY.
forward REACT IMMEDIATELY
A LOW
ROTOR RPM
AUDIO SIGNAL,
more positive
and abrupt
APPLICATION OF THROTTLE 4. Possible ncrease in noise due to:
WILL RESULT
IN ROTATION
3-24 Rev. 2
failure at the transmission end. 3. Hydraulic Pressure (Affected System)
Continued
failure
failures). 6. At ambient temperature
of -10°C or less,
NOTE
additional
forces
will
autorotation descent.
landing without hydraulic power,
System
1
powers
one-half
of
directional
unmanageable.
Whenever
possible
landing
control
servo
actuator
and
upper
one-half
of
directional control servo actuator as well as 1. MASTER CAUTION light.
lower half
of right
lights
illuminate.
Indications:
1. MASTER
CAUTION light.
caution light 4. Hydraulic Temperature
(Both Systems)
temps
remain
normal.
5.
LAND
temperatures
- Monitor.
NOTE
system circuitry.
1. Bypass Valve Indicator light
illuminated
pilot control force required to accomplish the without accompanying stiffness in controls
bypass
should
normal but a
system operating in
system (SYS 1 or SYS 2).
In this SINGLE GENERATOR
failures.
turned on for landing,
provided the 3. INV
system
2. Bypass Valve Indicator light (Affected
Servo) illuminated.
2. GENERATOR
switch
- Leave
2. Turn off the affected hydraulic system if in OFF position if switch was tripped OFF.
temperature exceeds imits.
3. LAND AS SOON
See manufacturers data for bus elevator system will reengage after
loading.
1. MASTER CAUTION lights illuminate breakers - Check in.
2.
engaged, wait 30 seconds before
to ground
VAC caution
3.
Indications:
1.
AC power
is interrupted
while SCAS
1. Check caution panel to determine is engaged, wait 30 seconds before
inverter
failed.
reengaging
SCAS.
NOTE
are
inverters fail to reset. not engaged; use ATTD TRIM switch "beep"
to fly
pitch and/or
SYSTEM
FAILURES
(AFCS)
3.
Yaw
oscillations
if
2. Pitch/roll/yaw
HDG
SEL
function
If circuit
breakers are
NOTE
with
dual
will lock in position at time of failure.
A/S
or
lower.
Indications:
Check in.
4. ELEV
minutes elevator 1 remains
3, a
subsequent failure of another
If one or both elevator systems disengage: airspeed system will result in elevator
locking in position. If this occurs,
7.
follow dual FBW system
CRACKED
WINDSHIELD
1. Airspeed -
FLIGHT MANUAL
Performance - IFR -
- IFR -
- VFR -
100% NR 10,000
Lb. G.W. (English)
- VFR -
-
100% NR 10,000
Lb. G.W. (English) ............................
Engineand Engine nlet Anti-Ice On - HeaterOff -
100% NR 10,000 Lb. G.W.
(English) ............................
4A-85
Performance
4A-95
- IFR
Performance
-
On -
Meters Obstacle (Metric)...................
Anti-ce OFF
Procedures:
on
Figure
4-1.
Throttle
(test
engine)
DOWNWARD
ALLOWABLE GT.
FLIGHT MANUAL
EXAMPLE:
GENERAL
ELECTRIC
CT-7-2A
ENGINE
DOWNWARD TO
IN THE OPPOSITE
MARGIN IS
visible moisture may be unreliable.
Procedures:
Computer
HEATER
witches
OIL
Throttle
Determine
maximum

ENGINERPM 100%
HEATER OFF
GENERATOR 400
MAX.EN ALT
10 11 12 13 14 15
16 17 18
214099-3-1A
ENGLISH
Figure
4A-1.
-10
-15
NOTE
MINIMUMPERATINGEMP
MAX.
GROSS
WEIGHTLIMIT
214099-3-2A
ENGLISH
Figure
-35
NOTE
MINIMUM
4A-4
GENERATOR400 AMPS ENGINE AND ENGINE INLET ANTI-ICE OFF
14,000
20
MINIMUMOPERATING
TEMP.
MAX
GROSS
WEIGHTLIMIT
-50 -40-30-20-10 0 10 20 10 11 12 13 14 15 16 17 18
OAT - C
GROSS WEIGHT
TAKE-OFFAND LANDING. THIS HELICOPTER
_ GROSS
TAKE-OFF POWER.
0 10 20 30 40 50 60 10 11 12 13 14 15 16 17 18
OAT - °C GROSS WEIGHT - LBS x 1000
214099-3-6A
ENGLISH
14,000
-50-40-30-20-10
0°TO-35°C
OAT °C GROSS WEIGHT - LBS x1000
214099-3-11A
Figure 4A-2. Hover ceiling out of ground effect (Sheet 2 of 10)
4A-12 Rev. 5
NOTE
MINIMUMOPERATINGEMP
AUTHORIZED
O
15 16 17
FLIGHT
MANUAL
BHT-214ST-FM
ENGINE RPM 100%
15
25
MINIMUM
OPERATING
TEMP
18
OAT
18
-15
AUTHORIZED TO -35°C
Figure 4A-2. Hover ceiling out of ground effect (Sheet 10 of 10)
4A-20 Rev. 5
FLIGHT
MANUAL
BHT-214ST-FM
attitude to avoid either
4. Rotate aft at 37 KIAS but allow
airspeed o
air temperature,
pressure altitude,
and gross
climb,
1.
10% POWER
distance.
OAT
TAKE-OFF
BHT-214ST-FM
HOVER
GENERATOR400
AMPS
OAT -
HOVER POWER+ 10%TORQUE VTOCS= 50 KIAS
ENGINE RPM
(Sheet 2 of 2)
Figure 4A-4. Twin engine take-off (5 Min.) power climbperformance - IFR
engine & engine inlet anti-ice off - 100%
NR
4A-26 Rev. 5
FLIGHT MANUAL
Figure4A-4. Twin engine take-off (5 Min.) power climb performance IFR
engine & engine nlet anti-ice off - 100% NR
14,000 Lb. G.W. (Sheet3 of 7)
Rev. 5 4A- 27
16,000 Lb. G.W. Sheet 5 of 7)
Rev. 5 4A-29
FLIGHT MANUAL

performance
- IFR
engine & engine inlet anti-ice on - heater off or on - 100% NR
14,000
Rev. 5 4A-41
FLIGHT
MANUAL
BHT-214ST-FM
BHT-214ST-FM
FLIGHT
MANUAL
ENGLISH
Figure 4A-6. Twin engine maximum continuous power climb performance - IFR
engine & engine inlet anti-ice off - heater off -
100% NR
FLIGHT
BHT-214ST-FM
11,000 Lb.G.W (Sheet2 of 9)
4A-50 Rev.5
engine& engine nlet anti-ice
16,000 Lb. G.W. (Sheet 7 of 9)
Rev. 5 4A-55
BHT-214ST-FM
engine&engine nlet anti-ice on - heater off - 100% NR
17,000 Lb. G.W. (Sheet8
Rev. 5 4A-57
ev. 5 4A-57

10,000 Lb.G.W. (Sheet 1 of 9)
Rev. 5 4A-67

10,000 Lb .G.W.(Sheet1 of 9)
4A-76 Rev.5
11,000
FLIGHT
MANUAL
BHT-214ST-FM
FLIGHT
MANUAL
BHT-214ST-FM
ENGLISH
4A-80

FLIGHT MANUAL
Figure 4A-10. Twin engine maximum continuous power climb performance- VFR
4A-84 Rev. 5
;: -:- :-' :TT;'' 'CLMS34 FT./MIN.ESS :
4A-88 Rev. 5
. ...ENGINEPM00
ENGLISH
RATE
Rev.
5
4A-91
17,000
Rev. 5 4A-93
AND
DESCENT
These
charts
maximum
continuous
power
4 6 8
214900-214
Rev. 5
FLIGHT MANUAL
performance
- engine
& engine
nlet
anti-ice
off
FLIGHT MANUAL
igure4A-12. Single engine 30 minute (O.E.I.)power climb and descent - IFR
performance - engine & engine inlet anti-ice off - 100% NR
17,000 Lb. G.W. Sheet 8 of 9)
4A-102
Rev.
5
. CHART (FIGURE i :.11~
17,500 Lb. G.W. (Sheet 9 of 9)
Rev. 5 4A-103
ENGLISH
214099-3-122A
ENGLISH
4A-108 Rev. 5
Rev. 5 4A-109
Figure4A-13. Single engine 30 minute power climb and descent - IFR
performance - engine & engine inlet anti-ice on - 100% NR
15,000
climb and descent -IFR-
4A-110
Rev.
5
ENGLISH
Figure 4A-13. Single engine 30 minute power climb and descent - IFR-
performance - engine& engine inlet anti-ice on - 100% NR
17,000 Lb. G.W. (Sheet 8 of 9)
Rev
5
4A-111
ev.
5
- IFR -
4A-112 Rev.5
FLIGHT MANUAL
performance - engine & engine inlet anti-ice off - 100% NR
15,000 Lb. G.W.(Sheet 6 of 9)
4A-118 Rev. 5
14,000
Figure 4A-15. Single enginemaximum-continuous (OEI) ower climb and descent - IFR -
performance
- engine
& engine
BHT-214ST-FM
FLIGHT
MANUAL
ENGLISH
BHT-214ST-FM
performance - engine & engine nlet anti-ice off - 100% NR
11,000 Lb. G.W. (Sheet 2 of 9)
4A-132
Rev.
5
FLIGHT MANUAL
-
4A-136 Rev. 5
FLIGHT MANUAL
FLIGHT MANUAL BHT-214ST-FM
FLIGHT
MANUAL
BHT-214ST-FM
ALTITUDE
ENGINE
RPM100%
performance

performance - engine
Rev.
5
4A-149
and descent - VFR-
000
-16
-2 0 2 4 6
8 10 12
performance
Rev. 5 4A-151
-VFR-
performance
-
4A-158 Rev. 5
performance-engine
& engine
performance- engine&engine nlet anti-ice on - 100%NR

for both ANTI-ICE
- ON and ANTI-ICE
These charts provide required distance for
landing over a 50 foot obstacle in relation to
variances
500ft/min, 45
KIAS at 50 feet AGL and using 2.5 minute OEI
power during the power recovery for landing.
EXAMPLE:
temperature,
read distance.
2.5
INOPERATIVE
ON
Figure 4A-20. Single engine landing distance over 50 foot obstacle
(Sheet 2 of 2)
21900-216
MAX.
OAT
10
MAX.
WEIGHT
LIMIT
0 10 20 30 40 50 60 50 55 60 65 70 75 80
OAT - °C GROSSWEIGHT Kg X 100
214099-11-1A
METRIC
14,000
ENGINE PM100% HEATEROFF
80
214099-11
3A
METRIC
Figure 4B-1. Hover ceiling in ground effect (Sheet 3 of 9)
4B-4
Rev.
5
/-R,{
iSiDENSITY
ALTITUDE
LIMITS
/ _ _
-
OAT -
°C
GROSS
WEIGHT
L ______________________
METRIC
Figure 4B-1. Hover ceiling in ground effect (Sheet 6 of 9)
Rev. 2 4B-7
FLIGHT MANUAL
^-0-
1/^
_MAXRe.
TB-
'0"~'
O 10 20 30 40 50 60 40 45 50 55 60 65 70 75 80
OAT - IC
55 60 65 70 75 80
OAT - °C
METRIC
214099-30-2A
METRIC
Figure 4B-2. Hover ceiling out of ground effect (Sheet 2 of 10)
4B-12
Rev.5
14,000 FT. DEN.ALT.LIMIT
70 75 80
FLIGHT
MANUAL
BHT-214ST-FM
HOVER
CEILING -
OUT
ENGINE PM100%
HEATER N
GENERATOR00 AMPS
60 65 70 75 80
METRIC
214099-30-5A
METRIC
Rev. 5 4B-15
OAT
°C
GROSS
WEIGHT
KgX
100
214099-30-7A
METRIC
Rev. 5 4B-17
FLIGHT MANUAL
20 TO
-35°C
TAKEOFF OWER
MAX. GROSS
50 -40 -30 -20 -10 0 10 20 50 55 60 65 70 75 80
METRIC
Rev.
5
4B-19
ENGINE
PM100%
HEATER
N
GENERATOR
75 80
4B-20 Rev. 5
either
or climbing above 11-foot
clear a
15.2 meter
obstacle at
gross weight,
5. Establish a 50 KIAS climb until obstacle
height
continue climb,
is that
2. Rotate forward establishing a takeoff speed which allows takeoff over a 15.2 meter
attitude,
V restrictions.
52
214099-29-1A
METRIC
2)
4B-22
Rev.
5
5° TO -35°C
ENGINE PM 100%
4500
6500
7000
- - )o,
-50 -40 -30 -20 -10 0 10 16 20 24 28 32 36 40 44 48 52 56 60 64
OAT - °C TAKE-OFFDISTANCEMETERS 10
continuous
power
or
takeoff
and
ON ABOVE10,000 FT., RATE
18,000
4B-28 Rev. 5
Rev.
5
4B-29
- ?:.10,000 FT.___N_
-
FLIGHT MANUAL
IFR- Takeoff power-

Figure 4B-5. Twin engine rate of climb - IFR - Takeoff power -
anti-ice ON
(Sheet 6
of 7)
Rev. 5 4B-37
- IFR - maximum continuous
4B-38 Rev. 5
continuous
FLIGHT MANUAL
W.A.T.CHARTFIG.1-2
4,000
Figure 4B- 7. Twin engine rate of climb - IFR - maximum Continuous
power - anti-ice ON (Sheet 1 of 8)
4B-46 Rev. 5
18,000
NGINE
RPM
100%
· ... _. :. -
climb - IFR - maximum continuous
4B-48 Rev.5
climb - IFR - maximum continuous
FLIGHT MANUAL
4B-56 Rev. 5
FLIGHT
MANUAL
BHT-214ST-FM
78
power
Rev.
5
4B-57
Figure 4B-8. Twin engine rate of climb - VFR - takeoff power
4B-58 Rev.5
FLIGHT
MANUAL
BHT-214ST-FM
METRIC
Figure
VFR - takeoff power -
-
BHT-214ST-FM
4B-66 Rev. 5
I
INLET
ANTI-ICE
ON
- VFR - takeoff power
Rev. 5 4B-69
4B-70 Rev. 5
MAXIMUM
GW
5000
kg

CLIMB
ABOVE

4B-82 Rev.5
FLIGHT
MANUAL
SINGLE
ENGINE
RATE
OF
CLIMB
maximum
continuous
and descent - IFR
Figure 4B-12. Single engine rate of climb and descent - IFR -
30 minute
4B-88
Rev.
5
Figure 4B-12. Single engine rate of climb and descent - IFR
RATE OF CLIMB AND DESCENT FT./MIN. x 100
30
FLIGHT MANUAL
30
Rev. 5 4B-91
IFR -
4B-92
Rev.
5
-
RATE OF CLIMB AND DESCENT- FT./MIN. x 100 | : ,:I 1.=I
Rev. 5 4B-95
30 minute OEI power - anti-ice ON (Sheet 1 of 8)
Rev. 5 4B-95
213A
Figure
4B-98 Rev. 5
·.

descent -IFR
maximum continuous
BHT-214ST-FM
FLIGHT
MANUAL
50'
METRIC
maximum continuous
FT./MIN. x 100
- IFR -
maximum
8)
4B-112
Rev.5
FT./MIN. x 100
-35C
NOTE
6,000R
OPERATION
S
LIMITED
BY
ENROUTE
W.A.T.
CHART
FIG.
1-2
4,000
2,000
-14 -12 -10.-8 -6 .- 4 -2 - 0 2. 4 6 8 10 12 : 14 16
RATE OF CLIMBAND DESCENT-FT./MIN. x
10
. .. 214099-22-6A
METRIC
- IFR -
maximum
continuouspower
BHT-214ST-FM
FLIGHT
MANUAL
x 100
FLIGHT
ANUAL-214ST-FM
BHT-214ST-FM
78
BHT-214ST-FM
FLIGHT
MANUAL
descent - VFR-
descent - VFR -
30 minute
OEI power
descent - VFR-
16.000 _ INLET ANTI-ICE ON
of climb and descent
FLIGHT
MANUAL
BHT-214ST-FM
78
KIAS
(VFR)
MINIMUM
OPERATING
TEMP.
-
Figure 4B-17. Single engine rate of climb and descent - VFR -
30
minute
OEI
power.-.anti-ice
ON
(Sheet
5
GENERATOR
400
AMPS
- VFR-
30
minute
-
Rev.
5
4B-135
Figure 4B-18. Single engine rate of climb and descent - VFR
maximum continuous power - anti-ice OFF (Sheet 5 of 8)
Rev. 5 4B-139
10,000
AUTHORIZED
--: .- M.C.P.:ABSOLUTE--- _._..:__ _ tNLET ANTI-ICE FF
METRIC
Figure
4B-19.
igure 4B-19. Single engine rate of climb and descent - VFR -
maximum continuous power - anti-ice ON (Sheet 3 of 8)
RATEOFCLIMB NDDESCENT- T./MIN.100
'"'
and descent
VFR-
4B-148 Rev. 5
RATE
VFR -
4B-150 Rev.5
FLIGHT MANUAL
landing over a 15.2 meter obstacle in relation
to variances in OAT. altitude, and gross weight
with 100%
45
KIAS
landing.
EXAMPLE:
temperature,
read distance.
RATE OF DESCENT 2.5
BHT-214ST-FMS-9
214-706-601
Tanks)
BHT-214ST-FMS-14
214-706-118
BHT-214ST-FMS-16
214-899-164
Original
Single Air Conditioning System
Gross Weight Center of Gravity
..........................................................
Fuel Loading
6-5
Moments
LIST OF FIGURES
Chart ......................................
.. 6-4
Gross Weight Chart ..............................
6-8
6-3 BaggageCompartment Loading
(English) .......................................
6-15
..............................
(Metric) ...........................................
6-11
6-3M
BaggageCompartment
LoadingTable
6-14
to provide information necessary for Passenger oading in the standard twenty-place
computing weight
WEIGHT
EMPTY
CENTER
OF
gudelines:
GRAVITY
The
aft
seats
(passenger
row
center of Cabin deck cargo loading
limit is 100 pounds
to 6,250 pounds (2835
stations.
COCKPIT
AND
CABIN
LOADING
Fuel
system
has
a
usable
capacity
of
435
COCKPIT
auxiliary fuel tank s installed.
fuel on board when weight
empty is below
gallons (1646.6
liters) when
weight empty
is LOADING
Baggage compartments have
a combined load
limit of 1800 pounds (816.5
kilograms),
fuel
defined above,
indiscriminate crew,
An alternate passenger and fuel
loading can no longer
and pilot must compute gross
18000
13000
MINIMUM
WEIGHT
LONGITUDINAL C. G. STATION-IN.
(Sheet 1 of 2)
JET A. JET A-1 JP-6 (6.8 LBS/GAL)
U.S. WEIGHT
LBS C.G. IN. LB.
30 204
40
'99.7 678 228.2 1546
310 2108 234.0 4934
120 816 231.7
160 1088
190 1292 244.5
3159 410 2788
'218.4 1484 247.3
214100-5-1
6-9
USABLE FUEL LOADING TABLE(METRIC)
210 171 5994
10250 1050 866
280 228
*377 307 5796
17794 1190 970
455 371
525
Weights given are nominal weights at 15°C.
214100-6-1
6-11
214100-6-2
6-12
and their
flight
stations.
Table 6-3 provides arms and moments for Data forweightsfrom25to 1809.8 kilograms
weights from 50 to 740 pounds
in appropriate are given. Moments
have been calculated for
and
kilograms
appropriate
BAGGAGE COMPARTMENT
LBS F.S. 295.2 F.S. 297.0
50
147.6
148.5
100
295.2
297.0
150
442.8
445.5
200
590.4
594.0
INTERNAL CARGO
227.12 STA 163.33
CARGO TO 227.12
LBS MOMENTS MOMENTS MOMENTS
100 IN-LB 100
200
400
500 764.6
600 917.5 1171.4 1900 3709.4 3250 6345.0
650
800
1000 1529.2
1952.3 2300
1200 2342.8 2550 4978.4 3900 7614.0
1250 2440.4 2600 5076.0 3950 7711.6
1300 2538.0 2650 5173.6 3990 7789.7
214100.7
6-15
TO 6482.1 CARGO TO 5768.8 CARGO
TO 5768.8
WEIGHT CG MOMENT
Basic Operating
JP-5 (Full for Takeoff)
MOST
MOST AFT CG
Landing Fuel (40 Gallons) 272.0 242.8 +66000
LANDING CONDITION
*These are sample numbers.
From the Gross Weight Center of Gravity Chart, it can be determined that the CG is within limits
for this
Basic
Operating
Weight
5491.9
5905
324293.7
+ Payload
Landing
the EMERG FLOATS switch shall be OFF and
the FLOAT ARM caution light shall be
or extended over-water operations. the 214-
706-032 Life Raft Kit or equivalent shall be
installed.
the FLOATS caution light shall be extinguished
during flights not over water.
All doors shall remain closed during ditching.
WEIGHT - CG LIMITATIONS
after kit is installed and ballast readjusted if
necessary to obtain empty weight CO within
allowable limits.
ALTITUDE LIMITATIONS
pressure altitude.
PLACARDS AND DECALS
-
IS PROVIDED
FLOATS
FLIGHT
MANUAL
SUPPLEMENT
4 Rev. 1
necessary,
FLIGHT
MANUAL
BHT-214ST-FMS-2
No change rom
basic Flight Manual.
2 Rev. 1
615 U.S. gallons 2327.8 liters)
The auxiliary
fuel tanks
allow gravity flow of
U.S. gallons (2308.9 liters)
aft AUXILIARY FUEL LOADING
Fuel
90
JETB, JP-4 6.5 LBS/GAL)
LBS C.G. IN. LB.
60 390
80 520 230.9
1201 400 2600
*109.2
260 1690 244.5
4132 590 3836
WEIGHTS
BHT-214ST-FMS-2
Table 6-2. Usable fuel loading table (ENGLISH) (Sheet 2 of 4)
USABLE FUEL LOADING TABLE ENGLISH)
ONE LEFT OR RIGHT
GAL
LBS
USABLEFUEL LOADING
TABLE (ENGLISH)
520 3380
242.8 8207
4.69 159
compute
compute
100 UTERS kg mm
Pointof C.G.
direction hange.
1610
1312
6071
79652
Extreme limits of fuel C.G.
· Pointof C.G.direction hange.
ONE LEFT
1890
Extreme limits of fuel C.G.
" Point
Insert latest revision pages; dispose of superseded pages.
A
Check HDG and CPLlightsilluminated,
AFCS/HSI
COMD
- PLT.
the
Pilot flight director SBY button
- Depress occurs when
FLIGHT
CHECKS
automatically
Flight
director
- Select
modes
Flight director
modes may
be utilized
power setting.
HSI - Set heading marker to desired
AARS/SCAS.
flight
path
control.
(Example - HDG
and AIRSPEED.)
operable, automatic level off feature is
provided when coupled. A nominal 50 foot Flight director SBY button - Depress to
radar height is maintained until approach is decouple flight director or depress CPL
terminated.
button
SUPPLEMENT
FLIGHT
MANUAL
BHT-214ST-FMS-3
Section3
Table
ATT
displayed -
Attitude information switch to CPLT position and
unreliable.
I
unreliable.
ADI
cyclic
ATTD
line.
A
SUPPLEMENT
electrically
switch, and the necessary wiring to connect themo the
basic helicopter's
SUPPLEMENT FLIGHT MANUAL
be used in conjunction with the basic
Flight Manual for helicopters
equipped with the Heated
STANDBY
COMPASS
Actual weight change shall be determined U N R E L I A B L E
after kit is installed and ballast added if WINDSHIELDEAT.
necessary to retain empty weight CG within
allowable limits.
COPILOT and
- In. ON; note ammeter
PLT W/S HTR circuit breakers - In. COPILOT HEATED WINDSHIELD - OFF.
1
EQUIPMENT
HEATED WINDSHIELD

red to create maps of weather and surface features. Red
indicates the storm's most severe areas. Weather Radar
also has transponder
i/ii
WEATHER
RDR
AC
IN.
NOTE
The
minimum
slant
Refer to
BENDIX RDR-1400B
preflight and operating instructions
Table 1. Minimum
antenna depression)

conjunction with the Cargo Hook Mirror Kit,
214-706-016,
214-706-123. Any combination of the mirror or loadmeter
may be used with the cargo hook but mirror and loadmeter
is
CG within
allowable limits.
external cargo suspension hook is authorized Maximum gross weight including external
under the standard airworthiness certificate load is 17,500 pounds (7938 kilograms).
under VFR or IFR conditions without removing Loading shall be in accordance with Gross
the unit from the helicopter.
Weight Center of
mirror Maximum allowable load
on cargo hook is
the operators 7900 pounds
VFR
OPERATION
takeoff
external loads under VFRconditions.
whichever is less for all
gross weights with
that the rotorcraft - load combination meets IFR external cargo on suspension unit.
handling requirements and insures that the
Rotorcraft External Load Operator Certificate
reflects same with appropriate restrictions.
RESTRICTIONS CAUTION
is prohibited.
Night operation
Actual weight
Cargo
contact (if installed).
helicopter should
be electrically
until hookup is
complete. Check for proper ring size (table 2-1), Cargo suspension assembly -
configuration (figure 2-1). Condition and security.
WARNING
MAXIMUM
CROSS
PRIMARY
RING
PRIMARY
RING
SECTION
OF
INSIDE
DIAMETER
CROSS
SECTION
SECONDARY
RING
2.88
SUPPLEMENT
BHT-214ST-FMS-6
CARGO
REL
button
- Depress
and
NOTE
hold; pull down on cargo hook; hook The Height-Velocity Diagram is not
should
open.
operating
certificate.
The
electric
release
button
to a minimum to
Push and hold; pull down on cargo hook; prevent oscillation of sling load.
hook should
open. Release
MANUAL
CARGO RELEASE pedal; hook should CARGO HOOK REL switch - As desired.
close and lock.
The manual cargo release will regardless of CARGO HOOK REL
function
FLIGHT MANUAL SUPPLEMENT
Section
6
The External Cargo Loading Table lists the 237.6. The optional metric table provides
moments for
in kilogram millimeters divided
20 to 3583.4 kilograms.
WEIGHT
50 119 1550 3683 3050 7247
100 238 1600 3802 3100 7366
150 356 1650
250
400
550 1307
2050 4871
3550 8435
700
800 1901
2300 5465
3800 9029
900
1100
1300 3089
214100-17-1
13
FLIGHT
MANUAL
SUPPLEMENT
BHT-214ST-FMS-6
Table 6-1. External cargo loading table (ENGLISH) (Sheet 2 of 2)
EXTERNAL CARGO
LOADING TABLE
ENGLISH) - (Cont)
SUPPLEMENT
FLIGHT
MANUAL
BHT-214ST-FMS-6
Table 6-1M. External cargo loading table (METRIC) (Sheet 1 of 2)
EXTERNAL CARGO
LOADING TABLE
WEIGHT
mm 100
2180
like numbered pages in
Supplement, External
line.
A Rev. 1
operation.
For Limitations,
WORTH, TEXAS 76101
NOTE: Revised text is indicated by a black vertical line.
Insert latest revision pages;
the left
LIFE RAFT KIT
shall be used WEIGHT -
DO NOT USE AS HAND HOLD
LOCATION: LIFE RAFT COWLING
BULKHEAD
2. Fuselage, Right
DEPLOYMENT
side air temperature.
6. Copilots
Additional
life
- Main Rotor
The
the cowling is unlocked
on opposite life raft
Rev. 2 3
FLIGHT
MANUAL
SUPPLEMENT
SUPPLEMENT
FLIGHT
MANUAL
BHT-214ST-FMS-8
INTRODUCTION
DEFINITIONS:
fails at any
the takeoff, the helicopter
eturn to and safely stop
on the takeoff
area; or
2. At or after CDP,climb out from point of failure and attain
single engine
fails at any time after
the start of a landing approach
the
helicoptercan -
and safely land and
climb out from point of
failure and attain
at which a rejected takeoff
can
takeoff can be assured.
For this helicopter, CDP
LANDINGDECISIONPOINT
after which the helicopter is
committed to landing.
akeoff
REQUIRED
he takeoff surface
climb are attained following
REJECTED
AKEOFFDISTANCE
is brought to a
TAKEOFF LIGHTPATH
or above 35 feet AGL to 1000 feet AGL.

climb performance
the helicopter s 50
to a safe stop
on the designated surface
of
engine
ailure
LDP - Landing Decision Point
VTOss(V2) Takeoff Safety Speed
WAT -
ALTITUDE LIMITATIONS
Refer to Weight
VY = 75 KIAS emergency loats (floats stowed).
1-1/1-2
GENERATOR400 AMPS
OAT-°C
SUPPLEMENT FLIGHTMANUAL
within approximately two seconds.
landing distance
3.
Nrrpm-100%
MGTor
Nglimits.
4. Instruments - Normal operational range. 3. Accelerate the helicopter to VTOSS, nd
at 35 feet AGL,
and pitch attitude.
To determine CDP
(Critical Decision initiated
Point),
off
35
4-2).
presented
nlet Anti-Ice ON (Sheet
HP
FLIGHT MANUAL
LANDING
DISTANCE
REQUIRED
The takeoff flight path begins at the end of the LANDING DISTANCE REQUIRED
takeoff
distance
and
LandingDistance 475 ft.
FOR
ENGINE RPM 100%
B= 0.7FT.
OAT
(m)
1
-15-10 -5 0 5 10 15 20 25 30 35 40 45 50 55 60
(-4)(-2)
(0)
(2)
(4)
(6)
(8)
(10)
(12)
(14)
(16)
MEAN
HEIGHT
GAINED
IN
100
FEET
OF
HORIZONTAL
DISTANCE
- FT
(m)
214099-45-1A
(Sheet 1 of 2)
GENERATOR400AMPS
OFF OR ON
4-10
Flight
Manual
installed.
Limitations, Procedures, and
Insert
Section
4
SUPPLEMENT
fuel loading data for
Total
6-4 and 6-5 present longitudinal
fuel
installations in metric measure.
installed is 468
11752 iters).
single auxiliary
4
(English) Sheet 1 of 2)
ASTM D-1655
TYPE A,
LB* IN. IN.LB. -
(Sheet 1 of 2)
SUPPLEMENT
BHT-214ST-FMS-9
Table 6-3. Lateral usable fuel loading - single fuel tank (English) (Sheet 2 of 2)
ASTM
GRADE P-4 (6.5
120
150 975 2.00
20 340 2210
180
240 1560 3.23
50 430 2795
280 1820 2.76 50
used and minus figures when left fuel
tank
is
Section
6
214ST
ROTORCRAFT
CAA
APPROVED
FLIGHT
MANUAL
SUPPLEMENT
BHT-214ST-FMS-9
Table 6-4. Longitudinal usable fuel loading - dual fuel tanks (Metric) (Sheet 1 of 2)
ASTM
GRADEJP-5 (0.8149
LITERS kg* mm kg.mm 100 LITERS kg* mm kg.mm + 100
35 29
6205 1799
175 143 6096
630 513 6058
31078 1540 1255
770 627 6152 38573
945 770
GRADE P-5 (0.8149 kg/f)
kg* mm kg-mm -
70 57
6205 3537
245
350
420 342 5809
19867 1295 1055
490
630 513 6086 31221
805
FLIGHT
MANUAL
SUPPLEMENT
BHT-214ST-FMS-9
ASTM D-1655 TYPE A, A-1, and MIL-T-5624 GRADEJP-5 (0.8149 kg/l)
WEIGHT
CG
770 627
**Extreme lateral CG limit.
NOTE: Moments and CGsare plus figures when right fuel tank is used and minus figures when left fuel
tank is used.
Additional copies of this publication may be obtained by contacting:
Commercial Publication
2002
Original ...................... 0.................... 30 JUN 82 Revision .................... 2................. 08 MAR 02
Revision ..................... 1.................... 06 SEP 84
LOG OF PAGES
revision
to raise or lower loads up
to
78 meters) in length. The hoist can be extended 90
degrees outboard
from its
location in the aft
right area of the cabin. Caution lights on each side of
hoist illuminate when hook reaches 20 feet (6 meters)
below skids
during retraction.
An electrically
to sever cable in an emergency.
A manually
cutter fails.
i ii
prohibited.
approved, providing
FLIGHT CREW
safety
is prohibited. Crewmember shall
wear protective gloves for
operator shall be familiar with hoist operating
FLIGHT WITH OPTION L procedures
and limitations.
EQUIPMENT INSTALLED
LIMITATIONS
Retractable
passenger
after hoist is
Emergency float fairing shall
gear is
gross weight and center
of gravity. Refer to
Loading
Schedule.
Interior
permitted if they can
at

Loading
Schedule
load
lateral CG s, assuming
transit is 60 KIAS.
VNE
with
If crewmember
HEIGHT-VELOCITY
LIMITATIONS
allowable
hoist
The Height-Velocity limitations of the basic is located laterally at
B.L. +40.0
hoist operations when

METRIC)
-25.4
50.8
operation
3
BOOM FULLY
hoist position.
CABLE CUT
without hoist
adapters and
locking collars
or stowed.

pedestal and hoist) -
CUT
circuit
secured to
HOIST and
functions for proper operation. Check that PASS STEP switch (if
installed) - STOW.
pilot HOIST
switch overrides
operator pendant
spots, fraying
or broken
HOIST PWR switchON.
motor stops; then
limit. Check that hoist
SECURED TO HELICOPTER
and secured observe

- As required
for adequate
hook nears the up or down limits, When emergency transportation
of
be
helicopter for litter
patient
precludes
contained
FOULING
allowing HOISTING OR LOWERING
adequate hoist load clearance over obstacles EMPTY LITTER IN OPEN
if load is not
EMPTY LITTER SUSPENDED
or lowering
with straps.
in a near-vertical
straps

into
helicopter
PRIOR TO
HOISTING LITTER
TO
GRASP
LITTER
Litter sling straps should be adjusted so that SUNG STRAPS TO
CONTROL
ROTATION AS LITTER
In the
may be resumed
Rev. 1
This document provides information supplementing or superseding that in the
basic document
herein shall be attached
Manual Supplement, Internal
APPROVED:
NOTE: Revised ext is indicated by a black vertical line.
Insert
latest
revision
pages;
dispose
Manual when the 214-899-142 Weather Radar Kit has been
installed.
of the basic Flight Manual. For Limitations, Procedures and
Performance
supplement consult

The primary purpose of the system is to detect storms
along the flight path and give a visual indication of their
intensity so a determination
to avoid the storm
beacons. The system can be operated in one of three
modes: radar, beacon,
detection and beacon location simultaneously.
i/ii
GROUND OPERATION
versus altitude at which
Targets
antenna will not be detected
because of
empty weight CG
figure 1.
vs altitude (maximum antenna
m^~tADAR BEAM
DEGREES EITHER SIDE OFTHE
- SCAN switch
RAD
Mode control selector
switch - RAD. IN
or
INFLIGHT OPERATION
RELIED UPON FOR PROXIMITY
- Rotate clockwise.
1.
WEATHER
RDR
AC/DC
FLIGHT
MANUAL
SUPPLEMENT
WEATHER
RADAR
KIT
PRIMUS-500
No
change
Model 214ST Flight
installed.
of
the basic Flight Manual.
BELL HELICOPTERNC
Observepilot and copilot
stationary.
Pilot
NAV-1
NAV-2
switch
- NAV-1.
AFCS/HSI
X
X
X
1,2,4.6,9.12,15
X
LEFT RIGHT CENTER
BAGGAGE BAGGAGE BAGGAGE
BAGGAGE COMPARTMENT COMPARTMENT COMPARTMENT
WEIGHT STA. 278.0 TO 316.0 STA. 290.0 TO 316.0 STA. 278.0 TO 316.0
LBS F.S. 295.2 F.S. 301.0 F.S. 297.0
50 147.6 150.5 148.5
gationequipments installed
baggage ompartment.
LEFT RIGHT CENTER
BAGGAGE BAGGAGE BAGGAGE
WEIGHT TO 8026 mm. TO 8066 mm. TO 8026 mm.
kg.
gationequipment
Model 214ST
Flight Manual
POST OFFICE BOX
482 * FORT WORTH.
Revision
Revision
Page
Insert latest revision pages;
speed
to
accommodate
existing
colective contro - Appy aft
is
CAUTION
line. To Toe brakes -
29
OCTOBER
1982
REVISION
400
amperes.
CAUTION
Air
after kit
if location-
allowable limits.
Rev.2 1
ENGINE AREA. AFT COMPARTMENTS AND OVERHEAD CONSOLE
TAILBOOM,
AIR CONDITIONING SYSTEM CHECK
Exhaust motors - Condition, obstructions
desired.
security.
both generators
for the system to
operate. In the event
FLIGHT MANUAL
Section6
0
4
Rev.
2
Rotorcraft Flight Manual when the 214-899-164, FMS-90
Flight Management
the basic
SUPPLEMENT
keyboard uning
and a
can be used
to navigate point-to-point
Unit, and DEU-90 Data Entry Unit are located on the
pedestal. The CRU-90 Computer Receiver Unit and
AEU-90
baggage
in
overheating.
warning
of navigation and under
mode,
is
not
.
from or approaches to
FLIGHT
MANUAL
SUPPLEMENT
BHT-214ST-FMS-16
system The data base must be updated
according to
instructions and
navigation and steering parameters recommended time interval by use of Collins
referenced to Magnetic North. Data Entry Unit (DEU-90) and Collins update
tape. Data base update must be done on the
RNAV approaches
only at approved
-
change shall be determined
after kit is installed and ballast
adjusted, if
to obtain empty weight CG within
required. limits.
CAUTION
Receiver
OFF.
Section
5
NOTE: All
6 has been deleted
Insert latest revision
GLOBAL NAV SYSTEM-GNS-500A/S3
VFL/OMEGA radio navigation system that provides
great circle
point-to-point navigation
on a worldwide
basis. It also displays to the flight crew an assessment of
its ability to navigate and will automatically revert to
dead reckoning
(CDU) mounted
receiver
120°E extending across the Asian
The following GNI Operators Manuals must be Continent.
immediately available to the flight crew
whenever navigation
operation of the GNS-
required for the specific type of operation
Operators Manual Report 1080 dated 9-1- must be installed and operable.
80 for the -3A
must be checked for accuracy (reasonable-
81 for the -3B
Program and CRT/CDU. ness)
and
Provided the GNS-500A
VLF/Omega during IFR
navigation system is receiving
and Alaska in accordance
requesting off-airway routing, and
or the criteria at hourly intervals
thereafter during RNAV
update self- During period of Dead
Reckoning, navigation
contained navigation
or Doppler, in accordance
with AC 120- 500A/S3
31 A in the areas between Latitudes 85°N to
55°S,
bounded by Longitudes 30°E aircraft
position should be verified by visually
and 120°E extending across the Asian sighting ground reference points and/or by
Continent. using other navigation equipment such as
VOR,
the areas
between Latitudes
navigation in
departures from, or approaches to,
airports.
1
Rotorcraft Flight Manual when the 214-899-285 Air
Conditioning
the basic Flight Manual. For Limitations, Procedures, and
Performance Data not contained in this supplement, consult the
evaporator,
two
blowers,
Vdc nonessential bus. The
portion of the
Model 214ST Flight
Limitations, Procedures,
and Performance
POST
OFFICE
superseded pages.
the helicopter. The xenon
FLIGHT CREW
50 FT
MUST BE IN HORIZONTAL OR UP STOWED
POSITION.
SEARCHLIGHT.
1-1/1-2
For Limitations,
Procedures, and
Bell Helicopter
POST OFFICE
BOX 82 · FORT WORTH, TEXAS 76101 REVISION 1 -1 1 SEPTEMBER
1987
Insert latest revision
Manual and Maintenance Manual

Manual.
Section
4
S&&ticL
2
FLIGHT MANUAL
40
* Quantity at which
direction.
Quantity resulting in maximum forward CG of helicopter (at any weight).
Quantity resulting in maximum aftCG of helicopter (weight empty 10,500 lb/4763 kg or less).
*Quantity resulting in maximum aft CG of helicopter (weight empty more than 10,500 lb/
4763 kg).
JET
113751
NOTE: All data above represents usable fuel (basic and auxiliary) based on nominal density at
15°C (59°F).
direction.
JET
helicopter (at any weight).
tank (English) (Sheet 1 of
4)
RIGHT
LONGITUDINAL
LATERAL
90
110 748
229.7 1718
0 0
170
200
220 1496
244.6 3659
3.40 51
*249.3
density at
15°C
(59°F).
Quantity
AUX TANK ON LEFT
direction.
Quantity
resulting
tank (English) (Sheet 4 of
4)
SELF-SEALING
CELLS
AUX TANK ON LEFT
LONGITUDINAL
LATERAL
any weight).
1 of 4)
WITH ONE 329 LITER AUX TANK ON LEFT OR RIGHT
JET A, A-1. OR JP-5 (0.815 kg/liter)
LONGITUDINAL
35 29
6204 1799
0 0
700
NOTE:
Quantity resulting
helicopter (at any wieght).
weight).
18
Rev.
1
FLIGHT
MANUAL
SUPPLEMENT
BHT-214ST-FMS-24
LOG
annunciator
of the
pilot and
copilot instrument
switches
to independently select
of VHF-DF or UHF-DF
determines the source of the DF signal that will then be
supplied to the
relative bearing pointer
on the pilot/copilot
is
frequency
If single
Both
1
AN/ARC-186(V)
Check pilot and
- As
desired.
AN/ARC-186(V)
radio
- On.
3
FLIGHTMANUAL
SUPPLEMENT
BHT-214ST-FMS-24
Section
3
Section
4
0
0
0
4
Manual when the
214-705-503 Outboard Facing
the basic Flight Manual. For Limitations, Procedures, and
Performance Data not contained in this supplement, consult the
basic Flight
76101
vertical line.
revised if necessary, o return the extreme center
of gravity conditions
to within the
The weight empty center of gravity charts in the
maintenance
that the entire flight is conducted within limits.
COCKPIT AND CABIN LOADING
SEATS FRONT REAR FRONT REAR FRONT REAR FWD AFT
WEIGHT
218.1 244.8
100 11700 14460 15820 17500 18820 20520 21860 16780 21810 24480
110 12870 15906 17402 19260 20702 22572 24046 17336 23991 26928
120 14040 17352 18984 21000 22684 24624 26232 18912 26172 29376
130 16210 18798 20566 22750 24466 26676 28418 20488 28363 31824
140
34272
150
36720
160 18720 23136 25312 28000 30112 32832 34976 25216 34896 39168
170 19890 24582 26894 29750 31994 34884 37162 26792 37077 41616
180 21060 26028 28476 31500 33876 36936 39348 28388 39268 44064
190 22230 27474 30058 33250 36758 38988 41634 29944 41439 46512
200 23400 28920 31640 35000 37640 41040 43720 31520 43620 48960
210 24570
33222 36750 39622 43092 45906 33096 45801 51408
220 26740 31812 34804 38500 41404 45144 48092 34672 47982 53856
Table6-1M. Crewand PassengerTableof Moments (Metric)
CREWAND PASSENGERABLEOFMOMENTS KG MM. - 100)
OUTBOARD ACINGSEATKIT
WEIGHT CREW
KGS. SEATS FRONT REAR FRONT REAR FRONT REAR FWD AFT
2972mm 3673mm 4018mm 4445mm 4780mm 5212mm 5552mm 4003mm 5540mm 6218mm
45 1337.4 1652.9 1808.1 2000.3 2161.0 2345.4 2498.4 1801.4 2493.0 2798.1
50 1486.0 1836.6 2009.0 2222.5 2390.0 2606.0 2776.0 2001.5 2770.0 3109.0
66 1634.6 2020.2 2209.9
3047.0 3419.9
2410.8 2667.0 2868.0 3127.2
3331.2 2401.8 3324.0 3730.8
65 1931.8 2387.5 2611.7 2889.3 3107.0 3387.8 3608.8 2602.0 3601.0 4041.7
70 2080.4 2571.1 2812.6 3111.5 3348.0 3648.4 3888.4 2802.1 3878.0 4352.6
75 2229.0 2764.8 3013.5 3333.8 3585.0 3909.0 4164.0 3002.3 4155.0 4863.5
80
3202.4 4432.0 4974.4
4430.2 4719.2 3402.6 4709.0 5285.3
90 2674.8 3306.7 3616.2 4000.6 4302.0 4890.8 4996.8 3602.7 4986.0 6696.2
95 2823.4 3489.4 3817.1 4222.8 4541.0 4951.4 5274.4 3802.9 5263.0 5907.1
100 2972.0 3673.0 4018.0 4445.0 4780.0 5212.0 5552.0 4003.0 5540.0 6218.0
4
REAR
+340.0
158.2
+53788
CENTERMODULE
BASICOPERATINGWEIGHT
HAT THE CG IS
5
HAT THE CG S
two-thirds open.The
and associated ardware.
check conditionof hold open hinge
assembly.Check

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