POST OFFICE BOX 482 FORT WORTH, TEXAS 76101
BHT-212IFR-FM-1
COPYRIGHT NOTICE COPYRIGHT 2002 BELL ® HELICOPTER TEXTRON INC. AND BELL HELICOPTER TEXTRON CANADA LTD.
ALL RIGHTS RESERVED
THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS
ROTORCRAFT
FLIGHT MANUAL
14 AUGUST 1995
REVISION 4 — 02 DECEMBER 2002
BHT-212IFR-FM-1
NP
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
Manufacturer’s Data portion of this manual is proprietary to Bell Helicopter
Textron Inc. Disclosure, reproduction, or use of these data for any purpose other
than helicopter operation is forbidden without prior written authorization from Bell
Helicopter Textron Inc.
BHT-212IFR-FM-1
NOTE
Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of
superseded pages.
LOG OF REVISIONS
Original ... 0... 29 JUN 73
Reissue ... 0...14 AUG 95
Revision ... 1...29 MAY 96
Revision ... 2 ... 12 SEP 97
Revision ... 3 ... 01 MAY 98
Revision ... 4 ... 02 DEC 02
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BHT-212IFR-FM-1
LOG OF FAA APPROVED REVISIONS
Original ... 0... 29 JUN 73
Reissue ... 0...14 AUG 95
Revision ... 1...29 MAY 96
Revision ... 2 ... 12 SEP 97
Revision ... 3 ... 01 MAY 98
Revision ... 4 ... 02 DEC 02
02 DEC 2002
Rev. 4
C/D
DATE:
MANAGER
ROTORCRAFT CERTIFICATION OFFICE
FEDERAL AVIATION ADMINISTRATION
FT. WORTH, TX 76193-0170
FAA APPROVED BHT-2121FR-FM-1 GENERAL INFORMATION
ORGANIZATION
TERMINOLOGY
This flight manual is divided into five
sections and an appendix as follows: WARNINGS,
CAUTIONS,
AND
Section 1 LIMITATIONS
NOTES
Section 2 NORMAL PROCEDURES
Section 3 EMERGENCY AND MAL- Warnings, cautions, and notes are used FUNCTION PROCEDURES throughout this manual to emphasize Section 4 PERFORMANCE DATA important and critical instructions and are Section 5 WEIGHT AND BALANCE used as follows:
Appendix A OPTIONAL EQUIPMENT SUPPLEMENTS
WARNING
Sections 1 through 4 contain FAA
approved data necessary to operate AN OPERATING PROCEDURE helicopter in a safe and efficient manner. PRACTICE, ETC., WHICH, IF NOT Sections 5 contains Weight and Balance CORRECTLY FOLLOWED, COULD
data. RESULT IN PERSONAL INJURY
Appendix A contains a list of approved OR LOSS OF LIFE.
supplements for optional equipment,
which shall be used in conjunction with
basic flight manual when respective CAUTION optional equipment kits are installed.
Manufacturer's data manual (BHT-212-MD- AN OPERATING PROCEDURE, 1) contains additional information to be PRACTICE, ETC., WHICH, IF NOT used in conjunction with flight manual and STRICTLY OBSERVED, COULD optional equipment supplements, as RESULT IN DAMAGE TO OR
applicable. Manufacturer's data manual is DESTRUCTION OF EQUIPMENT divided into four sections as follows:
Section 1 SYSTEMS NOTE
DESCRIPTION
Section 2 HANDLING AND An operating procedure, SERVICING condition, etc., which is essential Section 3 CONVERSION to highlight.
CHARTS AND TABLES
Section 4 EXPANDED
USE OF PROCEDURAL WORDS
PERFORMANCE
Procedural word usage and intended meaning which has been adhered to in preparing this manual is as follows:
SHALL has been used only when
application
of a procedure is
mandatory.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. HYDR SYS 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 (N2) 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
FAA APPROVED BHT-2121FR-FM-1
REL Release VMC Visual
ROTOR (N) Rotor RPM Meteorological
Conditions
RPM Revolutions per
minute VMIN Minimum speed for
instrument (IFR)
SCAS Stability and control flight
augmentation system VNE Never exceed speed STA StationStation VTOCS Takeoff climbout
TEMP CONT Temperature control speed
VCAL Calibrated airspeed VTOSS Takeoff safety speed
VFR Visual flight rules XFEED Crossfeed
VG Vertical gyro
FAA APPROVED BHT-2121FR-FM-1
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
PRESSURE...
...
1-13-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
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
FAA APPROVED
BHT-212IFR-FM-1
02 DEC 2002
Rev. 4
1-3
Section 1
LIMITATIONS
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
a n d p l a c a r d s r e p r e s e n t a e r o d y n a m i c
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 action
required.
1-2.
BASIS OF
CERTIFICATION
This helicopter is certified under FAR Part 29,
Category B.
1-3.
TYPES OF OPERATION
This helicopter is cer tified 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, except
as noted below, shall consist of two pilots,
e a ch o f w h i c h mu s t h o l d a h e l i c o p t e r
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 170
pounds (77.1 kilograms). Refer to Section 5.
Minimum flight crew consists of one pilot who
shall operate helicopter from right crew seat.
Left crew seat may be used for an additional
pilot for VFR day and night operations when
approved dual controls and copilot instrument
kits are installed.
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
R e f e r t o a p p r o p r i a t e F l i g h t M a n u a l
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 V
NE. Refer to Section 5 and
to Airspeed Limitations.
In all cases, door configuration shall be
symmetrical.
1-5-D.
PASSENGERS
NOTE
R ef e r t o S ec t i o n 5 f o r l o a d i n g
tables to be used in weight/CG
computations.
With the passenger seat kit installed, the
helicopter is certified for operations as a
fifteen place aircraft.
The above loading does not apply if cargo
or a combination of cargo and passengers
a r e b e i n g t r a n s p o r t ed . I t s h a l l b e t h e
r e s p o n s i b i l i t y o f t h e p i l o t t o e n s u r e
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
FAA APPROVED BHT-2121FR-FM-1 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 for 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 (119.4 doors open or removed. millimeters) left and 6.5 inches (165.1
millimeters) right of fuselage centerline for
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 airspeedsGRAVITY
below 40 KIAS, AFCS ATTD modeshould 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 at 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) GW,CG of 132.0 to 142.5. Refer to OPERATING 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 3000
feet HD.
1-6-B. CENTER OF GRAVITY VNE (VFR only)(CG 142.5 to 144.0) - 110 KIAS from sea level up to and Including 1-6-B-1. LONGITUDINAL CENTER 3000 feet HD at 10,000 pounds (4536 OF GRAVITY kilograms) or less GW decreasing linearly 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 of 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.
BHT-2121FR-FM-1 FAA APPROVED
1-8. ALTITUDE
which a safe power off landing can bemade.
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. CLIMB AND DESCENT
Minimum ambient air temperature at all altitudes is -54 °C (-65 °F). Refer to Refer to Section 4, PERFORMANCE. Weight-altitude-temperature limitations fortakeoff, 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 failureduring takeoff, landing, or other operation
near the surface (figure 1-5). The AVOID
1-12-A.
BATTERY area of the Height-Velocity chart definesthe combinations of airspeed and height above 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
FAA APPROVED BHT-2121FR-FM-1
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 ENGINEscale 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
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 810°C). 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
BHT-212IFR-FM-1
FAA APPROVED
1-15. ROTOR
1-15-A.
ROTOR RPM – POWER ON
1-15-B.
ROTOR RPM – POWER
OFF
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.
HYDRAULIC
TEMPERATURE
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 -30°C
(-22°F).
1-17-B.
OIL – ENGINE AND
COMBINING 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 - 8 57 3 4 m ay b e u s e d a t a l l a m b i e n t a i r
temperatures above -40
°C (-40°F).
1-17-C.
OIL – TRANSMISSION,
INTERMEDIATE AND TAIL ROTOR
GEARBOXES
Oil conforming to MIL-L-7808 (NATO 0-148)
m a y b e u s e d a t a l l a p p r o v e d a m b i e n t
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
88°C
1-10
Rev. 4
02 DEC 2002
FAA APPROVED BHT-2121FR-FM-1
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 Instrument
1-18. ROTOR BRAKE
range markings, placards, and decals. Engine starts with rotor brake engaged are1-21. HEATER
prohibited. Rotor brake application is
limited to ground operation and shall not Heater shall not be operated when OAT is 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 Flight Manual Supplements (FMS) covering
1-19. LANDING GEAR
optional equipment kits available. No Flight Manual LimitationsFAA APPROVED BHT-2121FR-FM-1
(TYPICAL)
PANEL AFT END OF OVERHEAD CONSOLE
(if installed) 2121FR-FM-1-2-1
Figure 1-2. Placards and decals (Sheet 1 of 2)
BHT-2121FR-FM-1 FAA APPROVED
NOTES:
USED WITH GAS PRODUCER GAGE P/N 212-075-037-101 USED WITH GAS PRODUCER GAGE P/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)
FAA APPROVED BHT-2121FR-FM-1 11,000 8.000 6,000 5,000 132 134 136 138 140 142 144
LONGITUDINAL CG STATION - INCHES
2121FR-FM-1-3
Figure 1-3. Gross weight center of gravity chart
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 -38 42 46 50 54 KG X 1 1 00 GROSS WEIGHT 2121FR-FM- 1-4Figure 1-4. Weight-altitude temperature limitations for takeoff, landing and in ground effect maneuvers chart
FAA APPROVED BHT-2121FR-FM-1
450
NOTE: THEHELICOPTERCONFIGURATION SHALL COMPLY WITH THE
WEIGHT-400 ALTITUDE-TEMPERATURECHART
FOR HEIGHT-VELOCITY DIAGRAM TO BE VALID 350 250 250 1000 LB LESS THAN
0
200 150 50 0 10 20 30 40 50 60 70INDICATED AIRSPEED - KNOTS
Figure 1-5. Single engine height velocity chart
FAA APPROVED BHT-2121FR-FM-1
Section 2
TABLE OF CONTENTS
Page
Subject Paragraph Number
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... 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-... 2-6-G... 2-12 CABIN HEATER CHECK... 2-6-H ... 2-14 HYDRAULIC SYSTEM CHECK... 2-6-J... 2-14 BEFORE TAKEOFF ... ... ... ... 2-7 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... 2-17 ENGINE SHUTDOWN ... 2-11 2-17 POSTFLIGHT CHECK ... 2-12 ... 2-18
LIST OF FIGURES
Figure Page
Title Number Number
Exterior check diagram ... ... 2-1 ... 2-19
FAA APPROVED BHT-2121FR-FM-1
Section 2
2-1.
INTRODUCTION
Consult applicable weight and balance instructions provided in Section 5.This section contains instructions and
This section contains instructions and Determine weight of fuel, oil, load, etc.,procedures for operating helicopter from
planning stage, through actual flight
takeoff and anticipatated
landing
conditions, to securing helicopter after GW, and check helicopter CG 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 tobe 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.
BHT-2121FR-FM-1 FAA APPROVED
2-3-B. EXTERIOR CHECK
Fuel sump drain buttons (left andright) - Press.
Fuel filters - Drain before first flight of day as follows:
ENGINE 1 BOOST PUMP and IF HELICOPTER HAS BEEN ENGINE 2 BOOST PUMP switches
-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 PUMP switches - 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
FAA APPROVED BHT-2121FR-FM-1 Combining gearbox filter - Bypass Engine compartment - Check. indicator retracted.
Engine oil level - Verify presence of 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 -
removed,
Secured.
Engine air intake - Cover removed,
*secured. unobstructed.
Synchronized elevator - Condition,
security z Transmission oil - Verify presence of oil and proper level in sight gage.
Main rotor blade -
Condition,
cleanliness. Remove
tiedown.
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, ground 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 - Condition, 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 sight glasses for proper fluid levels. Caps 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.
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 FUELPRESTART 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
- Static check.
required) -
Condition and properly
serviced. STATIC SOURCE switch (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
FAA APPROVED
BHT-212IFR-FM-1
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.
NOTE
Test all lights when night flights are
planned or anticipated. Accomplish
light test s with external power
connected or during engine runup.
MASTER CAUTION switch (overhead) —
T E S T, che ck a ll c au t io n p an e l l i g h t s
e x t i n g u i s h e x c e p t C AU T I O N PA N E L
segment and MASTER CAUTION light. (Both
ENG OUT lights and RPM light will dim
during test.)
CAUTION
ROTOR BRAKE HANDLE SHALL
BE IN DETENT POSITION (OFF) AT
ALL TIMES WHEN ENGINES ARE
RUNNING.
ROTOR BRAKE lights — Test. Pull brake
lever and check that both lights illuminate;
return to off and check lights extinguish.
FIRE PRESS TO TEST switch — Press and
release. FIRE PULL 1 and FIRE PULL 2
warning lights illuminate when switch is
pressed and extinguish when switch is
released.
BAGGAGE FIRE warning light TEST button
— Press to test (verify light flashes).
CARGO RELEASE ARMED light (if installed)
— TEST.
Caution panel lights — TEST and RESET.
INV 1 switch — ON, check no. 1 AC voltmeter
for 104 to 122 volts.
INV 2 switch — ON, check no. 2 AC voltmeter
for 104 to 122 volts.
FUEL QTY SEL switch — LEFT, then RIGHT;
check fuel quantity gauge indicates lower
fuel cell quantity of 270 to 300 pounds
(each).
2-5.
ENGINE START
NOTE
If helicopter has been cold soaked
in ambient temperature of -18 °C
....
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 (N1) 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 XFEED caution light
will illuminate momentarily). Engine 2 ENGINE OIL pressure - Check. ENGINE 2 FUEL switch - ON. (ENG 2 ENG 2 PART SEP OFF light -FUEL VALVE 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).
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 openedto 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 (N1) 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.
FAA APPROVED BHT-2121FR-FM-1 2-6-B. PRELIMINARY HYDRAULIC RPM INCR DECR switch - INCR to 100%
CHECK (N2).
Throttles - Set to idle. 2-6-E. FUEL CROSSFEED VALVE CHECK
NOTE NOTE FUEL XFEED test switch - TEST BUS 1
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 - OFF. Check no. 1 FUEL PRESS decreases, 2-6-C. ENGINE FUEL CONTROL then returns to normal. (This indicates CHECK that crossfeed valve has opened by bus
no. 1 power and check valve is
Throttles - Idle. functioning properly.) ENGINE 1 BOOSTPUMP switch - ON.
NOTE FUEL XFEED test switch - TEST BUS 2 and hold.
Do not allow GAS PROD RPM (N1)
to decrease below 50%. ENGINE 2 BOOST PUMP switch - OFF. Check no. 2 FUEL PRESS decreases, Around 8000 feet Hp, GAS PROD then returns to normal. ENGINE 2 RPM (N1) may not change BOOST PUMP switch - 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 (N1). Open respective throttle ENGINE 1 (or ENGINE 2) BOOST PUMP carefully to assure GAS PROD RPM (N1) switch - OFF. Check fuel pressure
responds upward, then return throttle to drops to zero on selected system. idle. Return GOV switch to AUTO. ENGINE 1 (or ENGINE 2) BOOST PUMP Check for return to original GAS PROD switch - ON.
RPM (N1). 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 (N2) 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 (N2) increases 2% and
both engines stabilize at 97 ± 1% N2. Ammeters - Check within limits.
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. INVERTER 2 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 to 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 panelby 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 lights extinguish. Channel arm switches - ATTD.
ATTD switch - DSENGA, AFCS lights SCAS NO GO lights - Illuminated, extinguish, SCAS lights Illuminate.
should extinguish within several
seconds to Indicate system null. Wait ATTD switch - ENGA, AFCS lights for lights to extinguish. illuminate, SCAS lights 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
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
PITCH and ROLL lights remain
and ROLL remain lights extinguish, SCAS disengages. illuminated, AFCS YAW lightextinguishes. 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
SCAS 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 light
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 FORCE TRIM 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
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
Cyclic - Check normal operation by
- Check normal operation by airflow. moving cyclic in an 'X' pattern rightforward 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. Returnswitch 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 chartsfor HEATER ON in Section 4.
SYSTEM SELECTOR switch - As desired.
FAA APPROVED BHT-2121FR-FM-1 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 FORCE TRIM switch-ON.
COMMAND WILL CHANGE
COURSE SETTING
ON
REMAINING HSI (IF INSTALLED). Magnetic compasses - Fluid level and heading.
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 (N2) - 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 above40 KIAS. Perform power assurance check daily.
Refer to Section 4.
2-9.
IN-FLIGHT OPERATIONS
Maneuvering with AFCS on may be accomplished by one of following methods:
FAA APPROVED BHT-2121FR-FM-1 NOTE necessary to maintain balanced flight.
Use PITCH trim as necessary to maintain 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 and Method 1: pitch attitude. Apply pedal as necessary
Press TURN knob and select desired
angle of bank.
Apply pedal as
FAA APPROVED BHT-2121FR-FM-1
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 - Centered2-10
.LANDIN
and frictioned.FORCE TRIM switch - ON.
Flight controls -
Adjust friction as
desired. Throttles - Idle.
Throttles - Full open. ITT - Stabilize for one minute at idle prior to shut down.
ENG RPM (N2) - 100%.
Engine instruments - Within limits.
FORCE
TRIM switch - As desired.
ELT (if installed)
-
Check for
inadvertent transmission. Passenger STEP switch - As desired.
Radios - OFF.
WARNING IDLE STOP REL switch - ENG 1. Engine 1 throttle - Closed. Check ITT OBSERVE VMIN LIMITS IN and GAS PROD RPM (N1) 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 ITT 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 - OFF. 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.
