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POST OFFICE BOX 482 FORT WORTH, TEXAS 76
BHT-212IFR-FM-
COPYRIGHT NOTICE
COPYRIGHT 2002
BELL HELICOPTER TEXTRON INC.
AND BELL HELICOPTER TEXTRON
CANADA LTD.
ALL R IGHTS RESER VED
THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS
ROTORCRAFTFLIGHT MANUAL
14 AUGUST 199REVISION 4 02 DECEMBER 200
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NOTE
Revised text is indicated by a black vertical line. Insert latest revision pages; dispose ofsuperseded pages.
LOG OF REVISIONS
Original ....................... 0.................... 29 JUN 73
Reissue....................... 0....................14 AUG 95
Revision...................... 1....................29 MAY 96
Revision ......................2 ....................12 SEP 9
Revision ......................3 ................... 01 MAY 9
Revision ......................4 ................... 02 DEC 0
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02 DEC 2002 Rev. 4 A/
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LOG OF FAA APPROVED REVISIONS
Original ....................... 0.................... 29 JUN 73
Reissue....................... 0....................14 AUG 95
Revision ..................... 1....................29 MAY 96
Revision ......................2 ....................12 SEP 9
Revision ......................3 ................... 01 MAY 9
Revision ......................4 ................... 02 DEC 0
02 DEC 2002 Rev. 4 C/
DATE:
MANAGER
ROTORCRAFT CERTIFICATION OFFICEFEDERAL AVIATION ADMINISTRATIONFT. WORTH, TX 76193-0170
APPROVED:
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BHT-2121FR-FM-1
FAA
APPROVED
SHOULD
has been
used
only
when
HD
Density
altitude
application
of
a procedure
is
recommended.
recommended.
HP
Pressure altitude
MAY and NEED NOT
have been used HSI
Horizontal situation
only when application
of a procedureindicator
is optional.
HTR
Heater
WILL has been used only to indicate HV Height-velocity
futurity,
never
to
indicate
a
mandatory
procedure.
HYDRSYS
Hydraulic system
IFR
Instrument
flight
ABBREVIATIONS
AND
ACRONYMS
rules
IGE
In ground
effect
Abbreviations
and
acronyms
used
IMC
Instrument
throughout
this
manual
are defined
as
Meteorological
follows:
Conditions
INCR
Increase
AC
Alternating
current
INTCON
Interconnect
AFCS
Automatic
flight
control system INV Inverter
AGL
Above ground level ITT
Interturbine
temperature
ATTD
Attitude
KCAS
Knots calibrated
BLWR
Blower
airspeed
C
Celsius
KG
Kilogram(s)
CDP
Critical
decision
KIAS
Knots
indicated
point
airspeed
CG
Center
of gravity
LB
Pound(s)
CMD
Command
LDP
Landing
decision
DC Direct current point
DECR
Decrease
M
Meter(s)
DSENGA
Disengage
MCP Maximum
continuous
power
ELT
Emergency
locator
transmitter
MIN
Minimum,
minute(s)
ENG
Engine NAV
Navigation
ENGA
Engage
NON ESS
Non essential
ENG RPM
(N
2
) Engine power
NORMNormal
turbine
rpm
OAT
Outside
air
F Fahrenheit temperature
FT Foot, feet OEI One engine
inoperative
GAS
PROD
(N1)
Gas producer
rpm
Out of
ground
effect
OGE
Out
of ground effect
GEN
Generator
PART
SEP
Particle
separator
GOV
Governor
PLT
Pilot
GW
Gross
weight
PRI
Primary
ii
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FAA
APPROVED
BHT-2121FR-F
REL
Release
VMC
Visual
ROTOR
(N)
Rotor
RPM
Meteorological
Conditions
RPM
Revolutions
per
minute
VMI
N
Minimum
speed fo
instrument
(IFR)
SCAS
Stability
and
control
flight
augmentation
system
VNE Never exceed spee
STA
Station
tation
VTOCS
Takeoff
climbout
TEMP
CONT
Temperature
control
speed
VCAL
Calibrated
airspeed
VTOSS
Takeoff
safety
spe
VFR
Visual
flight
rules
XFEED
Crossfeed
VG
Vertical
gyro
.
VIAS
Indicated airspeed
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FAA
APPROVED
BHT-2121FR-FM-
Section
1
TABLE
OF CONTENTS
Page
Subject
Paragraph
Number
INTRODUCTION
.................................................
1-1
...........
1-3
BASIS
OF CERTIFICATION
1-2 ...........
1-3
TYPES
OF
OPERATION
.........................................
1-3 ...........
1-3
FLIGHT
CREW
..................................................
1-4...........
1-3
IFR
OPERATION
...........................................
1-4-A ........
1-3
IFR
CARGO
OPERATION
...................................
1-4-B
........
1-3
VFR
OPERATION
...........................................
1-4-C ........
1-3
VFR
CARGO
OPERATION
..................................
1-4-D
........
1-4
CONFIGURATION
...............................
.............
1-5 ..........
1-4
REQUIRED
EQUIPMENT
....................................
1-5-A
........
1-4
OPTIONAL
EQUIPMENT
....................................
1-5-B
........
1-4
DOORS
OPEN/REMOVED
(VMC ONLY)
..............................
1-5-C
........
1-4
PASSENGERS
..............................................
.. 1-5-D
.......
1-4
CARGO
..................................................
1-5-E
........
1-4A
WEIGHT
AND
CENTER
OF GRAVITY
...........................
1-6...........
1-5
WEIGHT
....................................................
1-6-A
........
1-5
CENTER OF GRAVITY ...................................... 1-6-B
........
1-5
AIRSPEED
......................................................
1-7...........
1-5
ALTITUDE
.......................................................
1-8...........
1-6
MANEUVERING
.................................................
1-9...........
1-6
PROHIBITED
MANEUVERS
...............................
1-9-A
.......
1-6
CLIMB
AND DESCENT
.....................................
1-9-B
........
1-6
HEIGHT-VELOCITY
.............................................
1-10 .........
1-6
AMBIENT
TEMPERATURES
...................................
1-11 .........
1-6
ELECTRICAL
...................................................
1-12
.........
1-6
BATTERY
...................................................
1-12-A
.......
1-6
GENERATOR
...............................................
1-12-B
....... 1-7
STARTER
..................................................
1-12-C.......
1-7
GROUND
POWER
UNIT
....................................
1-12-D.......
1-7
POWER PLANT
..................................................
1-13 .........
1-7
GAS
PRODUCER
RPM
(N) .................................
1-13-A
.......
1-7
POWER
TURBINE
RPM.....................................
1-13-B
......
1-8
INTERTURBINE
TEMPERATURE
...........................
1-13-C
......
1-8
ENGINE
TORQUE ...........................................
1-13-D
.......
1-8
FUEL
RESSURE.....................................
.....
-13-E
...
1-9
ENGINE
OIL PRESSURE
...................................
1-13-F
...... 1-9
ENGINE
OIL TEMPERATURE
..............................
1-13-G
.......
1-9
COMBINING
GEARBOX
OIL
PRESSURE
..................
1-13-H
.......
1-9
COMBINING
GEARBOX
OIL
TEMPERATURE
..............
1-13-J
....... 1-9
Rev. 2 1
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BHT-2121FR-FM-1
FAA APPROVED
TABLE
OF CONTENTS
(Cont)
Page
Subject
Paragraph
Number
TRANSMISSION ................................................. 1-14 ......... 1-9
TRANSMISSION OIL
PRESSURE...........................
1-14-A ....... 1-9
TRANSMISSION OIL TEMPERATURE ...................... 1-14-B ....... 1-9
TRANSMISSION TORQUE .................................. 1-14-C ....... 1-9
ROTOR ..........................................................
1-15
......... 1-10
ROTOR RPM - POWER ON ................................
1-15-A
....... 1-10
ROTOR RPM - POWER OFF ............................... 1-15-B ....... 1-10
HYDRAULIC ..................................................... 1-16 ......... 1-10
HYDRAULIC PRESSURE ................................... 1-16-A ....... 1-10
HYDRAULIC TEMPERATURE ..............................
1-16-B
....... 1-10
FUEL AND
OIL ..................................................
1-17 ......... 1-10
FUEL ........................................................ 1-17-A ....... 1-10
OIL ENGINE AND COMBINING
GEARBOX................
1-17-B ....... 1-10
OIL TRANSMISSION,
INTERMEDIATE AND
TAIL ROTOR
GEARBOX .................................................. 1-17-C ....... 1-10
ROTOR BRAKE.................................................. 1-18 ......... 1-11
LANDING GEAR ................................................. 1-19 ......... 1-11
INSTRUMENT MARKINGS AND PLACARDS ................... 1-20 ......... 1-11
HEATER .........................................................
1-21
......... 1-11
LIST OF FIGURES
Figure Page
Title Number Number
Instrument
markings ............................................
1-1...........
1-13
Placards and decals ............................................ 1-2........... 1-19
Gross weight center of gravity chart .......................... 1-3........... 1-21
Weight-altitude
temperature limitations
for takeoff, landing
and in ground effect
maneuvers chart.........................
1-4........... 1-22
Single engine height velocity chart............................ 1-5........... 1-23
1-2
Rev.
2
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FAA APPROVED BHT-212IFR-FM
02 DEC 2002 Rev. 4 1
Section 1LIMITATIONS
1-1. INTRODUCTION
NOTE
Compliance with limitations in this
section is required by appropriate
operating rules.
Minimum and maximum limits, and normal and
cautionary operating ranges for helicopter and
subsystems are indicated by instrument
markings and placards. Instrument markings
and placards represent aerodynamic
calculations that are substantiated by flight
test data.
Anytime an operating limit is exceeded, an
appropriate entry shall be made in helicopter
log book. Entry shall state which limit was
exceeded, duration of time, extreme value
attained, and any additional information
essential in determining maintenance actionrequired.
1-2. BASIS OFCERTIFICATION
This helicopter is certified under FAR Part 29,
Category B.
1-3. TYPES OF OPERATIONThis helicopter is certified for VFR and
Category 1 IFR operations under IFR day and
night, non-icing conditions.
1-4. FLIGHT CREW
1-4-A. IFR OPERATION
Minimum flight crew for IFR operation, excep
as noted below, shall consist of two pilot
each of which must hold a helicopte
instrument rating.
1-4-B. IFR CARGO OPERATION
Refer to applicable operating rules
for internal cargo operations.
1-4-C. VFR OPERATION
Minimum cockpit (FS 47.0) weight is 17
pounds (77.1 kilograms). Refer to Section 5.
Minimum flight crew consists of one pilot wh
shall operate helicopter from right crew seat
Left crew seat may be used for an addition
pilot for VFR day and night operations whe
approved dual controls and copilot instrume
kits are installed.
NOTE
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BHT-212IFR-FM-1 FAA APPROVED
1-4 Rev. 4 02 DEC 2002
1-4-D. VFR CARGO OPERATION
Refer to applicable operating rules
for internal cargo operations.
1-5. CONFIGURATION
1-5-A. REQUIRED EQUIPMENT
(*) Designates required equipment for VFR
flight.
(*)Operable force trim system.
(*)Heated pitot-static system.
(*)Pilot windshield wiper.
Operational AFCS.
Two VHF communication radios
Two navigation receivers with auxiliary
equipment appropriate for intended route of
flight.
DME equipment.
ATC transponder.
Marker beacon receiver.
Standby attitude indicator or gyro rate of turn
indicator.
Pilot IVSI.
Roof window blackout curtains
Dual controls.
Copilot instruments.
Copilot clock.
1-5-B. OPTIONAL EQUIPMENT
Refer to appropr ia te F l ight Manual
Supplement(s) for additional limitations,
procedures, and performance data with
optional equipment installed. See Appendix A.
1-5-C. DOORS OPEN/REMOVED(VMC ONLY)
Helicopter may be flown with doors open or
removed only with Bell Standard interior
installed. Flight operation is approved for the
following alternative configurations during
VMC only:
Both crew doors removed.
Both sliding doors locked open or removed
with both hinged panels installed or removed.
NOTE
Opening or removing doors shifts
helicopter center of gravity and
reduces VNE. Refer to Section 5 and
to Airspeed Limitations.
In all cases, door configuration shall be
symmetrical.
1-5-D. PASSENGERS
NOTE
Refer to Section 5 for loading
tables to be used in weight/CG
computations.
With the passenger seat kit installed, the
helicopter is certified for operations as afifteen place aircraft.
The above loading does not apply if cargo
or a combination of cargo and passengers
are being transported. It shall be the
responsibi l i ty of the p i lot to ensure
NOTE
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FAA
APPROVED
BHT-2121FR-FM-1
helicopter
is
properly
loaded
so
entire
1-5-E.
CARGO
flight is conducted within the limits of
gross
weight
center
of gravity
charts
1-5-E-1.
INTERNAL
CARGO
(Figure
1-3).
CONFIGURATION
Allowable
deck loading for
cargo is 100
pounds per square foot (4.9 kilograms/100
square
centimeters).
Deck
mounted
tiedown
fittings
are
provided
and
have an
airframe
structural
capacity
of
1250
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FAA
APPROVED
BHT-2121FR-FM
pounds
(567.0
kilograms)
vertical
and 500
NOTE
pounds
(226.8 kilograms)
horizontal per
fitting. Provisions for installation
of cargo Station 0
(datum) is located 20
tiedown fittings
are incorporated
in aft inches
(508.0 millimeters)
aft of
cabin
bulkhead
and transmission
support
most forward
point of cabin
nose.
structure
and have an airframe
structural
capacity
of 1250
pounds
(567.0
kilograms)
1-6-B-2.
LATERAL
CENTER
OF
at 90 degrees to bulkhead and 500 pounds GRAVITY
(226.8 kilograms)
In any direction
parallel
to bulkhead.
Cargo
shall
be secured
by an
Lateral
CG limits
are 3.5
inches
(88.9
approved
restraint
method
that
will
not
millimeters)
from
fuselage
centerline
fo
impede
access
to
cargo
in
an emergency.
IFR.
All
cargo and equipment
must be securely
tied
down
when operating
with
aft cabin
Lateral
CG
limits
are 4.7 inches
(119.
doors
open or
removed.
millimeters)
left
and 6.5 inches
(165.1
millimeters) right of fuselage centerline fo
I
1-5-E-2. BAGGAGE
VFR.
The
baggage
compartment
maximum
1-7. AIRSPEED
allowable loading is 400 pounds (181.4
kilograms),
not to
exceed 100 pounds
per VMIN
(IFR) - 40
KIAS.
square
foot (4.9
kilograms/100
square
centimeters).
NOTE
Due to
control authorities
1-6.
WEIGHT
AND
CENTER
OF
required
for
flight at
airspeeds
GRAVITY
below
40 KIAS, AFCS
ATTD
mode
should
not
be utilized
except
for
ground
checks.
1-6-A.
WEIGHT
VNE
(IFR or
VFR) - 120 KIAS
from sea
Maximum
GW
is 11,200
pounds
(5080.3
level
up to and
including
3000
feet HD a
kilograms).
8800 pounds (3991.6 kilograms) or less
GW
decreasing
linearly
to
VNE
of
100
KIAS
Refer
to Weight-altitude-temperature
at 11,200
pounds (5080.3
kilograms)
G
CG of 132.0 to
142.5. Refer to
OPERATIN
limitations
for
takeoff,
landing
and
in
LIMITATIONS
decal
figure
1-2 V
ground effect
maneuvers
chart (figure
1-4). decreases
3 KIAS
per 1000
feet above 300
feet
HD.
1-6-B.
CENTER
OF
GRAVITY
VNE
(VFR
only)(CG
142.5
to
144.0)
- 11
KIAS
from
sea level
up to
and Including
1-6-B-1.
LONGITUDINAL
CENTER
3000 feet H
D
at 10,000 pounds
(453
OF GRAVITY
kilograms)
or less GW decreasing linearl
to
VNE
of 100
KIAS at 11,200 pounds
(5080.3 kilograms) GW, CG of 142.5 to
Longitudinal CG operational range Is 144.0. Refer to OPERATING LIMITATIONS
variable
(figure
1-3),
depending
upon
GW,
decal,
igure
1-2.
VNE
decreases
3 KIAS
and shall
be computed
from
weight
and per
1000 feet
above 3000
feet H
balance data.
VNE
(VFR
only) doors
open
or removed
-
Longitudinal
CG
limits
are from
station
100 KIAS
for
any GW.
Refer
to Type
o
132.0
to
142.5
for
IFR.
Operation.
Longitudinal
CG limits
are from
station
Maximum
airspeed
when
above
maximum
132.0 to
144.0 for
VFR.
continuous
torque
(87.5%)
is 80
KIAS.
Rev.2 1-
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BHT-2121FR-FM-1 FAA APPROVED
1-8.
ALTITUDE
which a
safe power
off landing
can be
made.
Maximum
operating-
20,000 feet
Hp.
When
takeoffs
are
made
in
accordance
Refer to applicable
operating rules
for high with
HV charts, proceed
as follows:
altitude
oxygen
requirements.
Determine hover torque at a four foot
skid height.
Perform
takeoff with no more than
15% torque
above hover power while
accelerating to Takeoff Climbout
MONITOR
ITT WHEN STARTING
Speed
(VTOCs).
Refer to Section
4 for
ENGINE
IN MANUAL
FUEL VTOCS.
CONTROL MODE
Above 15,000 feet
Hp, restart shall be
NOTE
accomplished
in manual fuel control mode
Downwind takeoffs are not
only.
(No airspeed restrictions.)
recommended
since published
takeoff
distance performance
will
Below 15,000 Hp, restart may be attempted not be achieved. When near zero
in either manual or automatic fuel control wind conditions prevail, determine
mode.
true
direction
of
wind.
1-9.
MANEUVERING
1-11.
AMBIENT
TEMPERA-
TURES
1-9-A. PROHIBITED MANEUVERS
Maximum sea level ambient air
Aerobatic
maneuvers
are prohibited.
temperature
for operation
is +52
C (+125
F) and decreases with altitude at standard
lapse rate (2 C per 1000 feet Hp).
1-9-B. CLIMBAND DESCENT
Minimum ambient air temperature at all
altitudes is -54
C (-65 F). Refer
to
Refer to
Section
4, PERFORMANCE.
Weight-altitude-temperature
limitations
for
takeoff, landing and in ground effect
maneuvers chart (figure 1-4).
1-10.
HEIGHT-VELOCITY
The height-velocity
limitations
are critical
1-12. ELECTRICAL
in the event of a single engine failure
during takeoff, landing, or other operation
near
the
surface
(figure
1-5).
The
AVOID
1-12-A.
BATTERY
area of the Height-Velocity chart defines
the
combinations of airspeed and heightabove the ground from which safe singleNG
engine
landing on a smooth,
level, firm
surface cannot be assured.
BATTERY SHALL NOT BE USED
The H-V chart
is valid only when the
FOR ENGINE START AFTER
Weight-Altitude-Temperature limitations ILLUMINATION OF BATTERY
are not exceeded (figure 1-4).
The diagram TEMP LIGHT(IF
INSTALLED).
does not define the conditions which BATTERY SHALL BE REMOVED
assure continued flight
following an AND SERVICED
IN ACCORDANCE
engine failure nor
the conditions from WITH
MANUFACTURER
1-6
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FAA APPROVED BHT-2121FR-FM-
INSTRUCTIONS PRIOR TO
RETURNING
BATTERY TO
28 vdc ground power units for
starting
SERVICE.
shall be rated at
a minimum of 400 amps
and limited to a maximum of 1000 amps.
Maximum battery
case
temperature
54.5
C
(130
F)
Maximum battery
1-13. POWER
PLANT
internal
internal 62.7 C (145 F) PRATT AND WHITNEY CANADA PT6T
) 3B and PT6T-3.
1-12-B. GENERATOR
NOTE
Operation in 2 1/2 minute or 30
Maximum
- 150 amps per
ammeter.
minute
OEI range is intended
for
emergency
use only,
when one
NOTE
engine becomes
inoperative
due
to actual malfunction. OEI ranges
To
attain published single engine
shall not be used for
training.
performance, generator loads
should
not
exceed
75 amps
each
during twin engine
operation.
1-13-A. GAS PRODUCER RPM (N1)
Ammeter
needle may deflect full
1-13-A-1. TWIN ENGINE
scale
momentarily
during
OPERATION
generator assisted start of second
engine.
PT6T-3B (Gage P/N 212-075-037-101)
Continuous
operation
61 to 100.8%
1-12-C. STARTER
Maximum
continuous 100.8%
Maximum
for takeoff
100.8%
Limit
starter energizing
time to:
Maximum transient
(not to exceed 30
30 seconds - ON.
seconds)
102.4%
60 seconds - OFF.
30 seconds - ON.
5 minutes
-
OFF.
NOTE
30
seconds
- ON.
Either
gage
shall
be installed
in
15 minutes - OFF. pairs.
Above energizing cycle may then be PT6T-3B (Gage
P/N
212-075-037-113)
repeated.
Continuous
operation
61 to
101.8%
Maximum continuous 101.8%
Above 15,000 Hp, restart shall
be Maximum
101.8%
accomplished in manual fuel control mode Maximum
Maximum transient
(not to exceed 30
Below 15,000 Hp, restart may be attempted seconds) 103.4%
in either manual or automatic fuel control
mode.
PT6T-3
Maximum continuous 100%
Maximum transient
(not to exceed 10
seconds)
101.5%
1-12-D.
GROUND POWER
UNIT
Rev.2 1-
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BHT-2121FR-FM-1
FAA
APPROVED
1-13-A-2.
ONE
ENGINE
PT6T-3B
(SINGLE
ENGINE
OPERATION)
INOPERATIVE
(OEI)
30
Minute
OEI
range
765
to 822
C
2'/2 Minute OEI range 822 to 850 C
PT6T-3B(Gage P/N
212-075-037-101)
Maximum OEI
850 C
21/2
Minute
range
100.8
to 102.4%
Maximum
102.4%
PT6T-3
5 Minute range (twin
PT6T-3B(Gage P/N 212-075-037-113) engine operation) 765 to 810 C
21/2
Minute range
101.8
to 103.4%
30 Minute
range
Maximum
103.4% (OEI)
765 to 810
C
Maximum
continuous
limit (Single
or
twin
1-13-B.
POWER
TURBINE
RPM
engine
operation
765
transient
limit
PT6T-3B
or PT6T-3
(Max
5 second
Takeoff
100%
above
810 C)
850 C
I
Minimum 97% Starting transient limit
Continuous
Operation
97
to 100%
(Not
to
exceed
2
Maximum
continuous
seconds
above
810C).
1090
C.
operation
100%
Transient
(not
to
exceed
10 seconds)
101.5%
1-13-D.
ENGINE
TORQUE
1-13-C.
INTERTURBINE
NOTE
TEMPERATURE
For
normal
twin
engine
operation,
maximum
permissible
torque
needle
split is 4%
total
PT6T-3B (TWIN ENGINE OPERATION) needle split is 4% total
Continuous
operation
300
to
765
C
Maximum
continuous
765
C
1-13-D-1.
ONE
ENGINE
5 Minute
takeoff range
765 to 810
C
INOPERATIVE
(OEI)
Maximum
for takeoff
810
C
(ENGINE
SCALE)
Maximum
transient
(Not
to
exceed
5
seconds)
850
C
PT6T-3B
- TORQUEMETERS
MARKED
Maximum
for
starting
71.8%
(Not
to
exceed
2
Maximum
seconds
above
960
C
1090
C
continuous
63.9%
30
Minute
power
63.9%
to 71.8%
Maximum
71.8%
NOTE
If
ITT
remains
above
810
C
longer
PT6T-3B
- TORQUEMETERS
MARKED
than
15
seconds
or exceeds
other
79.4%
limits,
ITT
and duration
shall
be
Maximum
recorded
in
helicopter
logbook.
continuous
63.9%
Refer
to
Pratt
and
Whitney
30
Minute
power
63.9%
to 79.4%
Maintenance
Manual
for
Maximum
79.4%
inspection
requirements.
1-8
Rev.
2
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BHT-212IFR-FM-1 FAA APPROVED
1-15. ROTOR
1-15-A. ROTOR RPM POWER ON
1-15-B. ROTOR RPM POWEROFF
1-16. HYDRAULIC
NOTE
Refer to BHT-212-MD-1 for approved
fluids and vendors.
Hydraulic fluid type MIL-H-5606 (NATO H-515)
shall be used at all ambient temperatures.
Both hydraulic systems shall be operative
prior to takeoff.
1-16-A. HYDRAULIC PRESSURE
1-16-B. HYDRAULICTEMPERATURE
1-17. FUEL AND OIL
1-17-A. FUEL
NOTE
Refer to BHT-212-MD-1 for approved
fuels list.
Fuel conforming to ASTM D-1655 Type B,
NATO F-40, or MIL-T-5624, Grade JP-4 may be
used at all ambient air temperatures.
Fuel conforming to ASTM D-1655 Type A or
A-1, NATO F-44 MIL-T-5624, Grade JP-5, NATO
F-34, or MIL-T-83133, Grade JP-8 may be used
at ambient air temperatures above -30C
(-22F).
1-17-B. OIL ENGINE ANDCOMBINING GEARBOX
NOTE
Refer to BHT-212-MD-1 for approved
vendors.
Oil conforming to PWA Specification No. 521
Type 1 and MIL-L-7808 (NATO 0-148) may be
used at all ambient air temperatures.
Oil conforming to PWA Specification No. 521
Type 2 and MIL-L-23699 (NATO 0-156) or DOD-
L-85734 may be used at all ambient air
temperatures above -40C (-40F).
1-17-C. OIL TRANSMISSION,INTERMEDIATE AND TAIL ROTORGEARBOXES
Oil conforming to MIL-L-7808 (NATO 0-148)may be used a t a l l approved ambient
temperatures.
Oil conforming to, DOD-L-85734AS (Turbine
Oil 555) and MIL-L-23699 (NATO 0-156), may
be used at all ambient air temperatures above
-40 C (-40 F).
Minimum
Maximum
97%
100%
Minimum
Maximum
91%
104.5%
Minimum
Caution range
Normal Operating
Maximum
600 PSI
600 900 PSI
900 1100 PSI
1100 PSI
Maximum 88C
1-10 Rev. 4 02 DEC 2002
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FAA APPROVED
BHT-2121FR-FM
NOTE
1-20.
INSTRUMENT
DOD-L-85734AS
or MIL-L-23699 is
MARKINGS
AND PLACARDS
recommended.
Refer to Figure 1-1 and 1-2 for Instrume
1-18.
ROTOR
BRAKE
range
markings,
placards,
and
decals.
Engine starts with rotor
brake engaged are
1-21. HEATER
prohibited.
Rotor
brake
application
is
limited
to ground
operation
and shall
not Heater
shall not be
operated when
OAT
be applied until engines have been shut above 21 C.
down and ROTOR
RPM (NR) has
decreased
to 40% or less.
Refer to Appendix
A for listing of Flig
Manual
Supplements (FMS)
coverin
1-19.
LANDING
GEAR
optional
equipment
kits
available.
No Flight Manual
Limitations
1-11/1
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FAA
APPROVED
BHT-2121FR-F
(TYPICAL)
PANEL AFT ENDOF OVERHEADCONSOLE
(if
installed)
2121FR-FM-1-2-1
Figure
1-2.
Placards
and
decals
(Sheet
1 of
2)
Rev.
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BHT-2121FR-FM-1
FAA APPROVED
NOTES:
USED
WITH
GAS
PRODUCER
AGE
P/N
212-075-037-101
USED
WITH GAS
PRODUCER
AGEP/N 212-075-037-113
2121FR-FM-1-2
2
LOCATION: 212-IFR-FM-1-4-2
Figure
1-2.
Placards
and
decals
(Sheet
2 of
2)
1-20 Rev.1
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FAA APPROVED
BHT-2121FR-F
11,000
8.000
6,000
5,000
132
134 136
138 140 142
144
LONGITUDINALCG STATION INCHES
2121FR-FM-1-3
Figure 1-3. Gross weight center of gravity chart
Rev. 1
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BHT-2121FR-FM-1 FAA APPROVED
NOTE: ALLOWABLE GROSS WEIGHTS
OBTAINED FROM THIS CHART
MAY EXCEED
CONTINUOUS HOVER CAPABILITY
UNDER CERTAIN AMBIENT
CONDITIONS.
REFER
TO HOVER CEILING
CHARTS IN SECTION
4
14,000 FT. DEN.
ALT. UNIT
14,000
/
-
6000
2000
-40 -20 0 20
40 60 8 9 10
11 12 LB X 1000
OAT - C
1
38
42 46
50
54 KG
X 100
GROSSWEIGHT
2121FR-FM- -4
Figure
1-4.
Weight-altitude
temperature
limitations
for takeoff,
landing
and
in
ground
effect maneuvers chart
1-22
Rev.
1
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FAA APPROVED BHT-2121FR-
450
NOTE: THEHELICOPTERCONFIGURATION
SHALLCOMPLYWITHTHEWEIGHT-
400
ALTITUDE-TEMPERATURECHART
FOR HEIGHT-VELOCITY DIAGRAM
TO
BE
VALID
350
250
250 1000 LBLESS THAN
0
200
150
50
0 10 20
30 40
50
60
70
INDICATEDAIRSPEED - KNOTS
Figure
1-5. Single engine height velocity chart
Rev. 1 1-23
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FAA
APPROVED
BHT-2121FR-F
Section
2
TABLE
OF CONTENTS
Page
Subject
Paragraph
Numb
INTRODUCTION
..........................
2-1...
.............
2-3
FLIGHT
PLANNING
............................
2-2.....................
2-3
TAKEOFF
AND
LANDING
.........
............
.......
2-2-A
........
2-3
WEIGHT
AND
BALANCE
...................................
2-2-B ........
2-3
PREFLIGHT CHECK ............................ ..................... 2-3
BEFORE
EXTERIOR
CHECK
..............................
2-3-A
.......
2-3
EXTERIOR
CHECK
.........................................
2-3-B
.......
2-4
INTERIOR
AND
PRESTART
CHECK
............................
2-4........
2-6
ENGINE
START
.
.............................................
2-5
2-7
ENGINE
1 START...........................................
2-5-A
......
2-8
ENGINE
2
START...........................................
2-5-B ......
2-9
POST
START
...............................................
2-5-C
......
2-9
ENGINE
FAILS
TO START
.................................
2-5-D
.....
2-10
DRY
MOTORING
RUN
............................
........
2-5-E
.....
2-10
SYSTEMS
CHECK
............................
26...................
..
2-10
FORCE
TRIM
CHECK......................................
2-6-A
. .....
2-10
PRELIMINARY
HYDRAULIC
CHECK
.......................
2-6-B
....
.
2-11
ENGINE FUEL CONTROL CHECK....................... 2...-6-C
......
2-11
GOVERNOR
CHECK
........................................
2-6-D ........
2-11
FUEL
CROSSFEED
VALVE
CHECK........................
2-6-E
.......
2-11
ELECTRICAL
SYSTEMS
CHECK
...........................
2-6-F........
2-11
AFCS
CHECK
............................
2-.......
.......-6-G.......
2-12
CABIN
HEATER
CHECK....................................
2-6-H
.......
2-14
HYDRAULIC
SYSTEM
CHECK..............................
2-6-J.........
2-14
BEFORE
TAKEOFF
.........
...................
.........
.........
-7
2-15
POWER
ASSURANCE
CHECK
.............................
2-7-A
.......
2-16
PROLONGED
GROUND
OPERATION
......................
2-7-B
.......
2-16
TAKEOFF
........................................................
...........
2-16
INFLIGHT
OPERATIONS
.......................................
.
2-16
DESCENT
AND
LANDING
............
........................
.
2-10.........
2-17ENGINE
SHUTDOWN
............................................
2-11
2-17
POSTFLIGHT
CHECK
...........................................
2-12 .........
2-18
LIST
OF
FIGURES
Figure
Page
Title
Number
Numbe
Exterior
check
diagram
............................
........
2-1
...........
2-19
2-1/
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FAA
APPROVED
BHT-2121FR-FM-
Section
2
2-1. INTRODUCTION Consult applicable weight and balanc
instructions
provided
in Section 5.
This
section
contains
instructions
and
This sectionontains instructions
and
Determine weight
of fuel, oil, load, etc.
procedures
for operating
helicopter from
planning
stage, through
actual flight
takeoff
and anticipatatedandin
conditions, to securing
helicopter after GW,
and check helicopterCG locations.
landing.
Ensure
weight
and
balance
limitations
in
Section
1 are not
exceeded.
Normal and
standard conditions
are
assumed in these procedures. Pertinent
data in
other sections
is referenced
when 2-3.
PREFLIGHT
CHECK
applicable.
Pilot
is responsible
for
determining
Instructions and procedures contained
whether helicopter is
in
condition for safe
herein are written for purpose of
flight.
standardization
and are not applicable
to
all situations.
NOTE
2-2. FLIGHT PLANNING Preflight check is not intended to
be
a detailed
mechanical
Planning of mission to be accomplished Inspection, but a guide to check
will provide pilot with data to be used condition of helicopter. This
during flight. Information to be
used can check may
be made as
be compiled
as follows:
comprehensive
as conditions
warrant.
Check type
of mission to be
performed
and destination.
All areas checked
shall
include a
visual
check
for evidence
of
Select appropriate performance charts corrosion, particularly when
to be used from Section 4. helicopter is flown near or over
salt water
or in areas
of high
industrial emissions.
2-2-A.
TAKEOFF
AND LANDING
Refer
to Section 1 for takeoff and
landing 2-3-A. BEFORE EXTERIOR
weight limits and to Section 4 for takeoff
CHECK
and landing data.
Flight
planning -
Completed.
2-2-B.
WEIGHT
AND BALANCE
Publications-
Check.
Determine
proper weight
and balance
of Ensure
helicopter
has been
serviced as
helicopter
as follows:
required.
Rev. 2 2-3
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BHT-2121FR-FM-1
FAA APPROVED
2-3-B.
EXTERIOR
CHECK
Fuel
sump drain
buttons
(left and
right)
- Press.
Fuel filters - Drain before first flight
of day
as follows:
ENGINE
1 BOOST
PUMP
and
IF HELICOPTER HAS BEEN ENGINE2 BOOSTPUMPswitches -
EXPOSED TO SNOW OR ICING ON.
CONDITIONS,
SNOW
AND ICE
SHALL BE REMOVED PRIOR TO
ENGINE 1 FUEL and
ENGINE2 FUEL
FLIGHT. switches - ON.
1.
FUSELAGE-
FRONT
Fuel filters
(left and right)
- Drain
samples.
Rotor blade - Condition and
cleanliness.
ENGINE 1
FUEL and ENGINE
2 FUEL
switches
-
OFF.
Cabin area - Condition, all glass
clean. ENGINE 1 BOOST PUMP and
ENGINE 2 BOOST PUMP switches -
Pitot tubes - Covers removed, OFF.
unobstructed.
BATTERY BUS 1 switch - OFF.
Static ports (left and right) -
Unobstructed.
2. FUSELAGE
- CABIN
LEFT SIDE
Remote
hydraulic
filter
bypass
Copilot
and passenger
doors
-
Indicator
- Check
green.
Condition
and
operation,
glass
clean.
Security of
emergency release
Cabin
nose
ventilators
- handles.
Unobstructed.
Position lights - Condition.
Nose compartment - Condition and
doors
secured.
Landing
gear
-
Condition,
ground
handling
wheels
removed.
Battery vent and drain tubes
-
Battery
vent
and
drain
tubes
Engine
air
intake
- Cover
removed,
Unobstructed.
unobstructed.
Searchlight
and landing light - 3. FUSELAGE AFT LEFT SIDE
Antenna
-
Condition,
security.
Drain
lines
-
Clean,
unobstructed.
Engine compartment - Check.
Fuel sumps - Drain samples as
follows:
Engine
oil level - Verify presence of
oil
in sight
gage
and
proper
oil
level.
ENGINE
1 BOOST
PUMP
and
ENGINE
2
BOOST
PUMPswitches
-
Engine
governor
spring -
Condition.
OFF.
Engine
fire extinguisher
- Bottle
ENGINE 1
FUEL and ENGINE
2 FUEL
pressure
gage
and temperature
range.
switches
- OFF.
BATTERY
BUS 1 switch
- ON.
2-4
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FAA APPROVED
BHT-2121FR-FM
Combining
gearbox
filter
- Bypass
Engine
compartment
-
Check.
indicator retracted.
Engine
oil level
- Verify
presence
o
Access
doors and
engine cowling
-
oil and
proper level
in sight
gage.
Secured.
Access
doors
and engine
cowling
-
Engine exhaust ejector tubes - Secured.
Covers removed, unobstructed.
Fuel
filler
- Check
fuel
quantity
4.
FUSELAGE
-AFT
secure
cap.
Tailboom - Condition.
6. FUSELAGE
- CABIN RIGHT SIDE
Tail rotor driveshaft covers - remov
Secured.
Engine air intake
- Cover removed
*secured.
unobstructed.
Synchronized
elevator
-
Condition,
security
z
Transmission
oil
-
Verify
presence
o
oil and
proper level
in sight gage.
Main
rotor
blade
- Condition,
cleanliness.
Remove
iedown.
Pilot and
passenger
doors-
Condition and operation, glass clean
Tail
rotor
gearbox
-
Verify
presence
Security
of
emergency
release
of
oil and
proper
level
in sight
gage,
handles.
filler
cap
and
chip detector
plug
security.
Position
lights -
Condition.
Tail rotor
- Condition,
free movement
Landing
gear
- Condition,
groun
on flapping
axis.
handling
wheels
removed.
Tail
rotor yoke
- Evidence
of static
7. CABIN
TOP
stop
contact
damage
(deformed
static
stop
yield indicator).
Intermediate gearbox - Verify CAUTION
presence
of
oil
and
proper
level
in
sight gage.
Filler cap and chip
SNOW AND ICE SHALL
BE
detector plug security. REMOVED PRIOR TO FLIGHT
Tail skid
- Condition,
security.
WHEN
HELICOPTER
HAS
BEEN
EXPOSED
TO SNOW OR
ICING
Synchronized
elevator
- Condition,
CONDITIONS.
security.
Main rotor and
controls - Conditio
Tailboom
-
Condition.
fluid levels
in all
reservoirs.
Baggage
compartment
- Check
Transmission
oil filler
cap - Secured
smoke detector - Condition and
security. Cargo
and door secured.
Hydraulic
oil reservoirs
- Check sigh
glasses
for
proper
fluid
levels.
Cap
5. FUSELAGE - AFT RIGHT SIDE secured.
Engine fire extinguisher - Bottle Antenna(s)- Condition and security
pressure gage
and temperature
range.
Combining
gearbox
oil
filler
cap
-
Combining gearbox oil level - Verify Secured
presence
of
oil and
proper
level
In
sight
gage.
Close
access
door.
Rev.
3
2
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BHT-2121FR-FM-1
FAA
APPROVED
Anticolllsion
light -
Condition
and
Shoulder
harness
inertia
reel
and lock-
security.
Check.
Flight controls -
Freedom of movement,
CAUTION
position
for
start.
Cyclic - Centered,.friction
as
desired.
IF ANY TEMP-PLATE IS MISSING
OR HAS
BLACK
DOTS,
Collective
- Full down.
MAINTENANCE
PERSONNEL
SHALL
ASSIST
IN
DETERMINING
Transmission
chip detector
indicators
(if
AIRWORTHINESS.
installed)
- Check.
Main
driveshaft
and
coupling
-
Lower
pedestal
circuit
breakers
- In.
Condition,
security, and
grease
leakage.
Check
Temp-Plates
(four
Collective
control
head switches
- OFF.
places
each
coupling)
for evidence
of
elevated
temperature
indicated
by dot
COMPASS
CONTROL
slaving
swltch(es)
changing
color
to
black.
-
MAG (slave
position).
Engine air intakes - Unobstructed, Radio equipment - OFF.
particle
separator
doors
closed.
Fuel
INTCON switch
- NORM.
Engine
and
transmission
cowling
-
Secured.
ENGINE 1 BOOST PUMP
and ENGINE 2
BOOST
PUMP switches
- OFF.
Fresh
air inlet
screen
- Unobstructed.
FUEL
XFEED switch
- NORM.
2-4.
INTERIOR AND
ENGINE 1 FUEL and ENGINE
2 FUEL
PRESTART
CHECK
switches
- OFF.
Cabin interior - Cleanliness, security of ENGINE NO. 1 PART SEP and ENGINE
equipment.
NO.
2 PART
SEP
switches
- NORM.
Portable
fire
extinguishers
- Proper
ENGINE
NO.
1 GOV
and
ENGINE
NO.
2
charge,
secured.
GOV
switches
- AUTO.
Passenger
seats
- Secured,
each
HYDR SYS
NO. 1
and HYDR
SYS NO.
2
occupied seat
equipped with seat belt.
switches - ON.
Crew and
passenger
doors -
Secured.
STEP
switch
(if Installed)
- As
desired.
Cargo load - Secured.
FORCE TRIM switch -
ON, cover down.
Protective breathing equipment (if Instruments Staticcheck.
required)
-
Condition
and
properly
serviced. STATIC SOURCEswitch (if installed) -
PRI.
Seat and pedals - Adjust.
Altimeter(s)
-
Set.
Seat
belt and
shoulder
harness -
Fasten
and adjust.
Clock - Set and
running.
FIRE EXT switch - OFF.
2-6
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FAA APPROVED BHT-212IFR-FM
FIRE PULL handles In (forward).
AFT DOME LT rheostat and switch OFF.
PITOT STATIC HEATERS switch OFF.
WIPERS switch OFF.
CARGO REL switch (if installed) OFF.
VENT BLWR switch OFF.
HEAT AFT OUTLET switch OFF.
SYSTEM SELECTOR switch OFF.
AIR COND TEMP CONT switch (if installed)
As desired.
NAV AC switch NORM.
Overhead circuit breakers In.
All light rheostats OFF.
EXTERIOR LIGHT POSITION switch OFF.
EXTERIOR LIGHT ANTI COLL switch OFF.
INV 1, INV 2, and INV 3 switches OFF.
NON ESS BUS switch NORMAL.
GEN 1 and GEN 2 switches OFF.
External power Connect (as desired).
Check DC voltmeters for 27 1 volts. Adjust
external power source, if required.
BATTERY BUS 1 and BATTERY BUS 2
switches ON, check BATTERY caution
light illuminates.
NOTETest all lights when night flights are
planned or anticipated. Accomplish
light tests with external power
connected or during engine runup.
MASTER CAUTION switch (overhead)
TEST, check all caution panel lights
ext inguish except CAUTION PANE
segment and MASTER CAUTION light. (Bot
ENG OUT lights and RPM light will di
during test.)
CAUTION
ROTOR BRAKE HANDLE SHALL
BE IN DETENT POSITION (OFF) AT
ALL TIMES WHEN ENGINES ARE
RUNNING.
ROTOR BRAKE lights Test. Pull brak
lever and check that both lights illuminat
return to off and check lights extinguish.
FIRE PRESS TO TEST switch Press an
release. FIRE PULL 1 and FIRE PULL warning lights illuminate when switch
pressed and extinguish when switch
released.
BAGGAGE FIRE warning light TEST butto
Press to test (verify light flashes).
CARGO RELEASE ARMED light (if installe
TEST.
Caution panel lights TEST and RESET.
INV 1 switch ON, check no. 1 AC voltmet
for 104 to 122 volts.
INV 2 switch ON, check no. 2 AC voltmet
for 104 to 122 volts.
FUEL QTY SEL switch LEFT, then RIGH
check fuel quantity gauge indicates lowe
fuel cell quantity of 270 to 300 pound
(each).
2-5. ENGINE START
NOTE
If helicopter has been cold soaked
in ambient temperature of -18 C
....
02 DEC 2002 Rev. 4 2
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FAA APPROVED
BHT-2121FR-FM-1
GAS
PROD RPM (N,) -
Check 61 1%
Engine 2 throttle
- Open to Idle
at 12%
when
throttle
is
on idle
stop.
GAS
PROD
RPM
(N
1
) minimum.
Engine 2 ITT - Monitor. Observe ITT
If battery start: limitations.
GAS
PROD
RPM
(N1)
-
71%.
START
switch
-
Off at
55%
GAS
PROD
RPM
(N1)
GEN 1 switch - ON.
GAS PROD
RPM (N1) - Check
61 + 1%
AMPS
1 - Check
at or below
150 amps.
when
engine 2 throttle
is on
Idle stop.
NOTE
CAUTION
During extremely
cold ambient
temperatures, idle rpm will be
high and
ENGINE
OIL, XMSN
OIL,
ENSURE
SECOND
ENGINE
and
GEAR
BOX OIL
pressures
ENGAGES
AS THROTTLE
IS
may
exceed
maximum
limits
for
INCREASED.
A NON-ENGAGED
up to 2 minutes after starting. ENGINE IS INDICATED BY 10 TO
15% ENG RPM
(N2) HIGHER
THAN
Do
not increase ROTOR RPM (NR)
ENGAGED ENGINE AND
NEAR
above 80% until XMSN OIL ZERO TORQUE. IF A NON-
temperature is above 15
C. ENGAGEMENT
OCCURS, CLOSE
THROTTLE
OF
NON-ENGAGED
ENGINE OIL, XMSN OIL, AND GEAR BOX ENGINE. WHEN NON-ENGAGED
OIL
pressures
- Check.
ENGINE
HAS
STOPPED,
SHUT
DOWN ENGAGED ENGINE.
ENG 1 PART
SEP OFF caution
light -
Extinguished. IF S
U D D E
N (
H A R D)
ENGAGEMENT
OCCURS,
SHUT
Engine 1 throttle
-
Increase to 85% ENG DOWN BOTH ENGINES.
RPM (N2). Friction as desired.
MAINTENANCE
ACTION IS
REQUIRED.
2-5-B.
ENGINE
2 START
Engine
2 throttle -
Increase slowly
to
85% ENG RPM
(N2). Monitor tachometer
ENGINE
2 BOOST
PUMP switch
- ON,
and torquemeter
to
verify engagement
of
check ENG
2 FUEL BOOST
caution light
second
engine.
extinguished
(FUEL XFEEDcaution
light
will illuminate
momentarily).
Engine 2 ENGINE
OIL pressure
- Check.
ENGINE 2 FUEL
switch
-
ON. (ENG 2 ENG
2 PART SEP OFF light -
FUELVALVE caution light will illuminate Extinguished.
momentarily.)
Engine 2 FUEL
PRESS - Check.
2-5-C. POST START
START switch - ENG 2
position. External power - Disconnect
if used,
Observe starter limitations.
GEN 1
switch - ON.
Engine
2 ENGINE
OIL pressure
- GEN 2 switch
- ON (BATTERY
BUS 1
Indicating.
will switch
OFF automatically).
2-9
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39/585
BHT-2121FR-FM-1
FAA
APPROVED
2-5-E. DRY MOTORING RUN
CAUTION
Following
procedure
is
used to
clear an
IF
OPERATING
ON BATTERY
BUS
engine
whenever
it
Is deemed
necessary
to
1,
POSITION
INV
3
SWITCH
TO
ON
remove
internally
trapped
fuel
and
vapor:
DC
BUS
1.
Throttle
- Fully
closed.
ONLY
ONE
BATTERY
SWITCH
SHALL
BE ON
DURING
FLIGHT.
ENGINE
(1
or 2) BOOST
PUMP
switch
-
ON.
Caution
lights -
Check all
extinguished.
ENGINE
(1 or 2)
FUEL switch -
ON.
ENGINE
OIL, XMSN
OIL,
and GEAR
BOX
OIL temperatures
and
pressures
-
ENG
IGN SYS
circuit
breaker-Pull
out.
Within limits.
START
switch
- Engage
for
15 seconds,
AMPS
1
and AMPS
2 -
Within
limits,
then
disengage.
ENGINE (1 or 2) FUEL switch - OFF.
NOTE
AMPS
2 will
indicate
a higher
load
ENGINE
(1
or 2)
BOOST
PUMP
switch
-
than
AMPS
1
until
battery
is
fully
OFF.
charged.
ENG
IGN SYS circuit
breaker - In.
Radios
- ON
as required.
Allow
required
cooling
period
for
starter
ELT
(if installed)
-
Check
for
before
proceeding.
Follow
normal
start
inadvertent
transmission.
sequence
as
described
on
preceding
pages.
Refer to
SECTION
1, STARTER
LIMITATIONS.
2-5-D.
ENGINE
FAILS TO START
When
engine
fails
to
light
off
within
15
2-6.
SYSTEMS
CHECK
seconds
after
throttle
has
been
opened
to
idle,
following
action
is
recommended:
2-6-A.
FORCE
TRIM
CHECK
IDLE
STOP
REL switch
-
Actuate.
Flight
controls
-
Friction
off;
collective
lock removed.
Throttle
- Fully
closed.
Cyclic
and pedals
- Move
slightly
each
START
switch
- OFF.
direction
to
check
force
gradients.
ENGINE
(1
or 2)
BOOST
PUMP
switch
Cyclic FORCE TRIM release button -
-
OFF.
Press;
check
trim releases
with button
pressed,
reengages
with
button
ENGINE
(1 or 2)
FUEL
switch
-
OFF.
released.
After
GAS
PROD
RPM
(N
1
)
has
FORCE
TRIM
switch
- OFF;
check
trim
decreased
to zero,
allow
30 seconds
for
disengages
and
FT
OFF
caution
light
fuel
to
drain
from
engine.
Conduct
a
illuminates.
DRY
MOTORING
RUN
before
attempting
another
start.
FORCE
TRIM switch
-
ON.
2-10 Rev. 2
8/10/2019 Bell Helicopter manual
40/585
FAA
APPROVED
BHT-2121FR-FM
2-6-B. PRELIMINARY HYDRAULIC
RPM INCR DECR switch
-
INCR to 10
CHECK
(N
2
).
Throttles -
Set to idle.
2-6-E.
FUEL
CROSSFEED
VALVE
CHECK
NOTE
NOTE FUEL XFEED test switch - TEST BUS
Uncommanded
control movement
and hold.
or motoring
with either
hydraulic
system
off may indicate
hydraulic
system malfunction. NOTE
If, after turning either boost pump
HYDR
SYS NO. 1
switch -
OFF, then
off,
fuel pressure
remains
4 to 6
psi
below
normal
(10
4
psi),
appropriate
check
valve is
not
HYDR
SYS
NO.
2
switch
- OFF,
then
functioning
properly.
ON.
ENGINE
1 BOOST
PUMP switch -
OF
Check no. 1 FUEL PRESS decrease
2-6-C.
ENGINE
FUEL
CONTROL
then
returns
to
normal.
(This
indicat
CHECK
that crossfeed
valve has opened by b
no. 1 power
and check
valve
Throttles - Idle. functioning properly.) ENGINE 1 BOO
PUMP switch - ON.
NOTE
FUEL XFEED
test switch
- TEST BUS
and hold.
Do
not
allow
GAS
PROD
RPM
(N
1
)
to decrease
below 50%.
ENGINE
2
BOOST
PUMP
switch
- OF
Check no. 2 FUEL
PRESS decrease
Around
8000
feet Hp,
GAS PROD
then
returns
to normal.
ENGINE
RPM (N
1
)
may not change BOOSTPUMPswitch
-
ON.
significantly
when
manual fuel
control
is selected.
FUEL
XFEED
test switch
- NORM.
GOV
switch (ENGINE
NO. 1 or 2)
- FUEL XFEED
switch - OVRD
CLOSE.
MANUAL,
observe
change in
GAS PROD
RPM
(N
1
).
Open respective
throttle
ENGINE
1 (or
ENGINE 2) BOOST
PUM
carefully
to assure
GAS PROD
RPM (N
1
) switch
- OFF.
Check fuel
pressur
responds upward,
then return throttle
to drops
to zero on
selected system
idle.
Return
GOV switch
to AUTO.
ENGINE
1 (or
ENGINE 2) BOOST
PUM
Check for
return to original
GAS
PROD
switch - ON.
RPM (N
1
). Check
other governor
in same
manner.
FUEL XFEED
switch - NORM.
2-6-D. GOVERNOR CHECK
2-6-F. ELECTRICAL
SYSTEMS
CHECK
No. 1 throttle - Full open. Check ENG
RPM (N
2
) stabilizes
at 95 1%.
DC voltmeters - Check 27 1 vdc.
No. 2 throttle
- Full
open. Check
no. 1
AC voltmeters
- Check
104 to 122
vac
engine
ENG RPM (N
2
)
increases 2% and
both engines stabilize
at 97 1%
N
2
. Ammeters
- Check
within limits.
2-
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41/585
BHT-2121FR-FM-1
FAA APPROVED
AC system - Check as follows:
light illuminates,
then extinguishes after
several seconds.
INV 3 switch
-
ON DC
BUS 2,
check
INVERTER
3 caution
light
Cyclic - Move
laterally and hold.
Check
extinguishes. that roll NO GO light Illuminates, then
extinguishes after several seconds.
INV 2 switch - OFF, INVERTER 2 Return to neutral.
caution light illuminates. Check no. 2
AC voltmeter
for indication
that Pedals
- Move and hold.
Check that
inverter no. 3 has assumed load.
INV yaw NO GO light illuminates,
then
2 switch - ON. INVERTER2 caution
extinguishes after several
seconds.
light extinguishes.
Return pedals to neutral.
INV 3 switch - OFF, then ON DC BUS SCAS switch - ENGA, SCAS lights
1, check
INVERTER
3 caution
light
illuminate.
extinguishes.
SCAS switch -
DSENGA, SCAS
lights
INV 1 switch - OFF,
INVERTER 1 extinguish.
caution light illuminates. Check no. 1
AC
voltmeter for indication that
SCAS switch - ENGA, SCAS
lights
inverter no. 3 has assumed load. INV illuminate.
1 switch - ON.
INVERTER 1
caution
light extinguishes.
INV 1 switch - OFF,
SCAS disengages.
INV
3 switch
- OFF,
INVERTER
3 INV
1 switch -
ON, check
no. 1 AC
caution
light
illuminates.
INV
3 switch
voltmeter
for
104 o 122
volts.
- ON DC BUS 2, INVERTER 3 caution
light
extinguishes.
SCAS
switch
- ENGA,
SCAS
lights
illuminate.
2-6-G.
AFCS
CHECK
Pilot
AFCS
RELEASE
-
Press,
SCAS
disengages.
NOTE
NOTE SCAS switch - ENGA, SCAS
lights
AFCS mode
operation is
illuminate.
annunciated
on instrument
panel
by a
three segment light (PITCH,
Copilot AFCS RELEASE - Press,
SCAS
ROLL, YAW). AFCS functions In disengages.
two
modes - automatic with
turn
and trim functions,
and pilot
SCAS
switch - ENGA,
SCAS lights
cyclic steering. AFCS
illuminate.
annunciation is applicable to both
modes.
FORCE TRIM -
ON, cover down.
AFCS power - ON.
ATTD switch
- ENGA, AFCS lights
illuminate, SCAS ights extinguish.
Channel arm switches
- ATTD.
ATTD switch - DSENGA, AFCS lights
SCAS NO GO lights - Illuminated, extinguish, SCAS ights Illuminate.
should extinguish within several
seconds to Indicate system null.
Wait ATTD switch - ENGA,
AFCS lights
for lights to extinguish.
illuminate, SCAS
ights extinguish.
Cyclic - Move forward
and hold, then Pilot AFCS
RELEASE - Press, AFCS
aft
and hold. Check that pitch NO GO
lights extinguish, SCAS disengages.
2-12
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FAA
APPROVED
BHT-2121FR-FM-1
SCAS
switch
- ENGA,
SCAS lights
laterally.
Cyclic
should
follow and
illuminate.
AFCS ROLL
light remain
illuminated.
Center cyclic
using cyclic
FORCE
ATTD switch
- ENGA, AFCS lights
TRIM switch.
illuminate,
SCAS
lights
extinguish.
Turn
- Actuate
turn
knob
through
Copilot
AFCS
RELEASE
-
Press,
AFCS
cycle.
Cyclic
should
follow
and
AFCS
Copilot
AFCS RELEASE
- Press,
AFCS
PITCH
and ROLL
remain
PITCH and
ROLL lights
remain
lights extinguish, SCASdisengages. illuminated, AFCS YAW light
extinguishes.
Center
cyclic using
cyclic FORCE
TRIM switch.
CAUTION
AFCS
pilot
cyclic
steering
mode
-
Check
as follows:
MONITOR
ALL CONTROLS
TO
E
N S U R
E CONTROL
Pitch -
Displace cyclic
slightly
DEFLECTIONS
ARE NOT
forward and release. AFCS
PITCH
EXCESSIVE
DURING AFCS
light extinguishes and SCAS
PITCH
CHECK.
light illuminates.
Displace cyclic
slightly
aft
and release.
AFCS PITCH
SCAS switch - ENGA.
light
extinguishes and SCAS PITCH
CAS
switch- ENGA.
light illuminates.
ATTD
switch
-
ENGA.
Roll -
Displace
cyclic
slightly
left and
release.
AFCS ROLL
light
NOTE
extinguishes
and
SCAS
ROLL
light
illuminates.
Displace
cyclic
slightly
right and
release. AFCS
ROLL ight
Cyclic
friction must be properly
right and release. AFCS ROLL
light
set for
proper AFCS
operation,
extinguishes and
SCAS ROLL
light
Friction adjust ring must neither
be
tightly
compressed
against
Yaw
-
Displace
left
pedal
slightly
minimum
friction
bracket
nor be
forward
and release.
AFCS
YAW light
excessively
tight.
extinguishes
and SCAS
YAW
light
illuminates. Displace right pedal
Cyclic
friction
-
Adjust.
slightly
forward
and release.
AFCS
YAW
light extinguishes
and SCAS
AFCS automatic mode
- Check as YAW light
illuminates.
follows:
Pitch
- Actuate
pitch
trim
wheel
CAUTION
through cycle. Cyclic
should follow
and
AFCS PITCH
light remain
illuminated.
Center
cyclic using cyclic
CYCLIC
CONTROLS MAY
MOTOR
FORCE
TRIM switch.
Actuate AFCS
TO STOP
IF AFCS
IS LEFT
TRIM switch forward
and aft. Cyclic
ENGAGED
AND UNMONITORED
should follow and AFCS PITCH light DURING GROUND OPERATIONS.
remain
illuminated.
Center
cyclic
using cyclic FORCETRIM switch. FOR PROLONGED GROUND
OPERATION,
AFCS
SHALL NOT
Roll - Actuate roll trim wheel through BE OPERATED IN ATTD MODE.
cycle.
Cyclic
should
follow and
AFCS
ROLL
light remain
illuminated.
Center
cyclic
using cyclic
FORCE TRIM
switch. Actuate
AFCS TRIM
switch
2-13
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43/585
BHT-2121FR-FM-1
FAA APPROVED
ATTD
switch - DSENGA
prior to takeoff.
VENT BLOWER
switch -
As desired.
2-6-H. CABIN HEATER CHECK
2-6-J. HYDRAULIC
SYSTEM
CHECK
GAS
PROD RPM
(N,) - Check
75%
minimum
(both
engines).
NOTE
AIR COND TEMP CONT switch - Fully
COOL.
This check
is to determine
proper
operation of hydraulic actuators
for each flight
control system.
If
abnormal
forces,
unequal
forces,
CAUTION
control binding,
or motoring
is
encountered,
it may be an
indication of a malfunction of a
SYSTEM SELECTOR
SWITCH
flight control actuator.
SHALL
BE TURNED
OFF
WHEN
HEATED
AIRFLOW DOES NOT
FORCE TRIM switch
- OFF.
SHUT OFF AFTER
AIR COND
TEMP
CONT
SWITCH
IS
TURNED
Collective
- Down,
friction
removed.
TO FULLY
COLD, HEATER AIR
LINE
CAUTION
LIGHT
ROTOR
RPM
(NR)-
Set to
100%.
ILLUMINATES,
OR
CABIN
HTR
CIRCUIT
BREAKER
TRIPS.
Cyclic
- Centered,
friction
removed.
DO NOT OPERATE HEATER
ABOVE
21
C
OAT.
Hydraulic
system
- Check
as follows:
HYDR SYS NO.
1
switch - OFF.
SYSTEM
SELECTOR switch
- HEATER.
Check
Check MASTER CAUTION and
VENT BLOWER
switch -
ON.
HYDRAULIC
caution lights
Illuminate
and
hydraulic system no. 1 pressure
AIR COND TEMP
CONT switch - Rotate
decreases.
counterclockwise and observe heatedyclic - Check normal operation by
Cyclic - Check normal operation by
airflow.
moving
cyclic
in
an 'X'
pattern
right
forward
to
left aft,
then left
forward
to
DEFOG lever -
ON; check airflow
is right
aft (approximately
1 inch).
diverted from pedestal
outlets to Center
cyclic.
windshield
nozzles.
Return lever
to
OFF.
Collective
-
Check
normal
operation
by Increasing
collective slightly
(1 to 2
AFT
OUTLET switch - ON; check
inches). Return to down
position.
airflow distributed equally between
pedestal
outlets and
aft outlets. Return
switch
to OFF.
NOTE
Boost for tail rotor controls is
NOTE
furnished
by hydraulic
system no.
1 only. When hydraulic system
Heater operation
affects
no.
1 is being checked,
tail rotor
performance.
Refer to Hover
controls will be unboosted.
Ceiling and Rate of Climb charts
for HEATER ON in Section 4.
SYSTEM
SELECTOR
switch -
As
desired.
2-14
Rev. 2
8/10/2019 Bell Helicopter manual
44/585
FAA
APPROVED
BHT-2121FR-FM-
Pedals
- Displace
slightly
left
and
right.
Note
an increase
in
force
WARNING
required
to move
pedals.
BOTH
HYDRAULIC
SYSTEMS
WARNING
SHALL BE OPERATIONAL
PRIOR
TO
TAKEOFF.
DO
NOT
TURN
BOTH
HYDRAULIC
NOTE
SYSTEMS
OFF
AT
SAME
TIME
DUE
TO
EXCESSIVE
FORCE
System
1 will
normally
operate
10
REQUIRED
TO
MOVE
FLIGHT
to 20
C
cooler
than
system
2.
CONTROLS.
HYDR
SYS
NO.
1
switch -
ON.
Check
2-7.
BEFORE
TAKEOFF
MASTER
CAUTION
and
HYDRAULIC
caution
lights
extinguish
and
Engine,
transmission,
gearbox,
hydraulic
system
no.
2
pressure
hydraulic,
and
electrical
Instruments
-
returns
to
normal.
Check
readings
within
operational
HYDR SYS
NO. 2 switch -
OFF. range.
Check
MASTER
CAUTION
and
Flight
instruments
-
Check
operation
HYDRAULIC
caution
lights
illuminate
and set.
and
hydraulic
system
no.
2
pressure
decreases.
Attitude
indicators
-
Erect
and
set.
Cyclic
- Check
normal
operation
by
moving
cyclic
in an
'X' pattern,
right
NOTE
forward
to
left aft,
then left
forward
to
right
aft
(approximately
1 Inch).
If fast
slaving
is desired,set
roll
Center cyclic.
trim to
null, push
and hold
VG
FAST
ERECT
switch
(if installed)
Collective - Check normal operation until attitude indicator displays
by increasing
collective
slightly
(1 to
2
zero
degrees
bank
angle.
inches).
Return
to
down
position.
Turn
and
slip
indicators
- Operative.
Pedals
-
Displace
slightly
left
and
right.
Note
no
increase
in
force
HSls
-
Slaved
and
heading
correct,
required
to
move
pedals.
course
bar
and
bearing
pointers
set
to
proper
navigation
receivers.
HYDR
SYS NO.
2 switch
- ON.
Check
MASTER
CAUTION
and
HYDRAULIC
caution
lights
extinguish
and
hydraulic
system
no.
1 pressure
CAUTION
returns to
normal.
Cyclic
and collective
friction - As
INDICATOR
IS CPLT/PLT
desired. INDICATOR IS
ILLUMINATED,
CHANGING
COURSE
SETTING
ON
HSI
OF
COPILOT/PILOT
IN
ORCE
TRIM
switch-ON.
COMMAND
WILL
CHANGE
COURSE
SETTING
ON
REMAINING HSI (IF INSTALLED).
Magnetic
compasses
- Fluid
level
and
heading.
2-15
8/10/2019 Bell Helicopter manual
45/585
BHT-2121FR-FM-1
FAA
APPROVED
Altimeters
- Set.
2-7-B.
PROLONGED
GROUND
Vertical
speed
indicators
- Zero.
OPERATION
Clocks
-
Set
and running.
NOTE
Communication
and
navigation
For
prolonged
ground
operation,
equipment - Set and functioning. AFCS shall not be operated in
ATTD mode.
Position lights - As required.
Anti-collision
lights
- As required.
2-8.
TAKEOFF
Pitot
heater
-
As
required.
ENG RPM (N2) - 100%.
Cyclic
-
Fiction
as desired.
NOTE
NOTE
No
more
than
15%
torque
above
Moderate friction shall be applied hover power shall be used
to
each
throttle
to
overcome
accelerating
to
Takeoff
Climbout
follow-through
coupling
between
Speed.
twist
grips.
Collective
- Initiate
takeoff
from
a
hover
Throttles -
Full open, friction
adjusted.
height
of 4 feet.
ENG
RPM
(N
2
) -
100%
(both
engines).
FORCE
TRIM
switch
- As
desired.
COCKPIT
VOICE
RECORDER
TEST
switch
(if installed)--
press
and
hold
for
OBSER
VE
VMINITS
IN
3 seconds. Verify meter indicates GOOD. SECTION 1 FOR IFR OPERATION.
Passenger
STEP
switch
(if
installed)-
NOTE
As
desired.
Takeoff
must
be
executed
in
Passenger seat belts - Fastened. accordance with Height-Velocity
limitations
for type
of
operation
All doors
- Secured.
being
conducted.
Refer
to
Section
1.
Caution
and
warning
lights
-
Extinguished.
Refer
to
Section
4
for additional
climb performance
data.
2-7-A. POWER ASSURANCE
CHECK
ATTD
switch
-
ENGA
as
desired
above
40 KIAS.
Perform
power
assurance
check
daily.
Refer
o Section
4.
2-9.
IN-FLIGHT
OPERATIONS
Maneuvering
with
AFCS
on
may
be
accomplished
by
one
of
following
methods:
2-16 Rev. 2
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FAA APPROVED
BHT-2121FR-FM-
NOTE
necessary
to maintain
balanced
flight
Use
PITCH rim
as necessary
to
maintai
If ROLL trim
wheel is
used during
desired
attitude.
turn, helicopter
may
not return to
level flight
(in roll)
when turn
is
Method 2:
terminated.
Move cyclic to desired bank angle an
Method 1: pitch attitude. Apply pedal as necessary
Press
TURN knob
and
select desired
angle of
bank. Apply
pedal as
Rev. 2 2-16A/2-16
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FAA
APPROVED
BHT-2121FR-FM
to
maintain balanced
flight
during
turning
maneuver.
CAUTION
Method
3:
Method 3:
CYCLIC
CONTROLS
MAY MOTOR
Press cyclic FORCE
TRIM switch
and TO
STOP IF AFCS
IF LEFT
maneuver as desired.
Release
switch ENGAGED
AND UNMONITORED
when maneuver is complete and with DURING GROUND OPERATIONS.
helicopter
at level
attitude.
Collective
- Down.
2-10. DESCENT
AND Cyclic
control and
pedals - Centere
2-10LANDIN
and
frictioned.
FORCE
TRIM switch
- ON.
Flight controls
- Adjust
friction
as
desired.
Throttles -
Idle.
Throttles - Full open.
ITT - Stabilize
for one minute at id
prior
to shut
down.
ENG RPM
(N2)
-
100%.
Engine
instruments
-
Within
limits.
FORCE RIM
switch As desired.
ELT (if installed)
- Check
fo
inadvertent transmission.
Passenger
STEP
switch
- As
desired.
Radios - OFF.
WARNING
IDLE
STOP
REL
switch
- ENG
1.
Engine
1 throttle
- Closed.
Check
I
OBSERVE VMIN
LIMITS
IN
and GAS
PROD RPM
(N
1
) decreasing.
SECTION
1 FOR IFR
OPERATION.
BATTERY BUS 1 switch - ON.
Flight path
- Establish
in accordance
with
Height-Velocity diagram. Single
IDLE STOP REL switch
- ENG 2.
engine balked
landings
can be made
from a landing decision
point (LDP) of Engine
2 throttle - Closed. Check I
100 feet altitude, 40 knots airspeed,
and and GAS PROD RPM
(N.) decreasing.
500
feet rate of descent.
Anticipated
single engine landings initiated from GEN 1 and GEN 2 switches - OFF.
these conditions
require reference
to
landing performance data
in Section 4. INV 1, INV 2, and
INV 3 switches - OF
ATTD switch - DSENGA
as desired. ENGINE
1 FUEL switch - OFF.
ENGINE 1 BOOST PUMP switch - OFF
NOTE
ENGINE
2 FUEL
switch - OFF.
ATTD switch
must be disengaged
below
40 knots.
ENGINE
2 BOOST
PUMP
switch
- OFF
2-11.
ENGINE
SHUTDOWN
AFCS power - OFF.
2-
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BHT-2121FR-FM-1 FAA APPROVED
CAUTION
2-12.
POSTFLIGHT
CHECK
Main
rotor and tail
rotor blades
-
AVOIDRAPID
ENGAGEMENT
F Tiedown
when any
of following
ROTOR BRAKE IF HELICOPTER IS conditions exist:
ON ICE OR OTHER SLIPPERY OR
LOOSE SURFACE TO PREVENT Thunderstorms exist in local area or
ROTATION OF HELICOPTER. are forecast.
Rotor
brake - Apply
at or below 40%
Winds in
excess of 20 knots
or a gust
ROTOR
RPM (NR),
return to stowed
spread
of 15 knots exist or
is forecast.
position
after
main
rotor
stops.
Helicopter Is parked within 150 feet of
Pilot
- Remain at flig