Bell 212 Flight manual

(1)

BHT-212VFR-FM-1

POST OFFICE BOX 482 FORT WORTH, TEXAS 76101

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

ROTORCRAFT

FLIGHT MANUAL

14 AUGUST 1995

REVISION 4 — 02 DECEMBER 2002

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BHT-212VFR-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.

(3)

BHT-212VFR-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superseded pages.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 OCT 70

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-212VFR-FM-1

LOG OF FAA APPROVED REVISIONS

Original ... 0... 29 OCT 70

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

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BHT-212VFR-FM-1

GENERAL INFORMATION

This flight manual is divided into five

TERMINOLOGY

sections and an appendix as follows:

Section 1 LIMITATIONS

Section 2 NORMAL PROCEDURES WARNINGS, CAUTIONS, AND NOTES ARE Section 3 EMERGENCY AND USED THROUGHOUT THIS MANUAL TO MALFUNCTION EMPHASIZE IMPORTANT AND CRITICAL PROCEDURES INSTRUCTIONS AND ARE USED AS Section 4 PERFORMANCE DATA FOLLOWS:

Section 5 WEIGHT AND BALANCE DATA

Appendix A OPTIONAL EQUIPMENT WARNING SUPPLEMENTS

AN OPERATING PROCEDURE

Sections 1 through

approved data necessary to operate

helicopter in a safe and efficient manner.

RESULT IN PERSONAL INJURY

Section 5 provides weight and balance OR LOSS OF LIFE.

data essential for safe operation of the

helicopter. .

CAUTION

Appendix A contains a list of FAA

approved supplements for optional

equipment, which shall be used in AN OPERATING PROCEDURE,

conjunction with basic flight manual when PRACTICE, ETC., WHICH, IF NOT

respective optional equipment kits are STRICTLY OBSERVED, COULD

installed. RESULT IN DAMAGE TO OR

DESTRUCTION OF EQUIPMENT Manufacturer's data manual

(BHT-212-MD-1) contains additional information to be

used in conjunction with flight manual and NOTE

optional equipment supplements, as AN OPERATING PROCEDURE

applicable. Manufacturer's data manual is CONDITION ETC. WHICH IS

divided into four sections as follows: ESSENTIAL TO HIGHLIGHT.

Section 1 SYSTEMS DESCRIPTION

Section 2 HANDLING AND USE OF PROCEDURAL WORDS SERVICING

Section 3 CONVERSION CHARTS

AND TABLES Procedural word usage and intended

Section 4 EXPANDED meaning which has been adhered to in PERFORMANCE preparing this manual is as follows:

SHALL has been used only when

application

of a procedure is

mandatory.

SHOULD has been used only when

application

of a procedure is

recommended.

(6)

BHT-212VFR-FM-1 FAA APPROVED

MAY and NEED NOT have been used HV HEIGHT-VELOCITY only when application of a procedure

Is optional. HYDR SYS HYDRAULIC SYSTEM

WILL has been used only to indicate IGE IN GROUND EFFECT futurity, never to indicate a mandatory IMC INSTRUMENT

procedure. METEOROLOGICAL

CONDITIONS INCR INCREASE ABBREVIATIONS AND ACRONYMS USED

THROUGHOUT THIS MANUAL ARE INTCON INTERCONNECT

DEFINED AS FOLLOWS: INV INVERTER

ITT INTERTURBINE

AC ALTERNATING CURRENT TEMPERATURE

AGL ABOVE GROUND LEVEL KCAS KNOTS CALIBRATED

ATTD ATTITUDE AIRSPEED

BLWR BLOWER KG KILOGRAM(S)

C CELSIUS KIAS KNOTS INDICATED

AIRSPEED CDP CRITICAL DECISION AIRSPEED

POINT LB POUND(S)

CG CENTER OF GRAVIT Y LDP LANDING DECISION

CMD

COMMANDPOINT

DC DIRECT CURRENT METER(S)

DECR DECREASE

POWER

DSENGA DISENGAGE MIN MINIMUM, MINUTE(S) ELT EMERGENCY LOCATOR

TRANSMITTER

NAVIGATION

ENG ENGINE NON ESS NON ESSENTIAL

ENGA ENGAGE NORM NORMAL

ENG RPM ENGINE POWER TURBINE OAT OUTSIDE AIR

(N2) RPM TEMPERATURE

F FAHRENHEIT OEI ONE ENGINE

INOPERATIVE FT FOOT, FEET

OGE OUT OF GROUND EFFECT GAS PROD GAS PRODUCER RPM

(NI) PART SEP PARTICLE SEPARATOR

GEN GENERATOR PLT PILOT

GOV GOVERNOR PRI PRIMARY

GW GROSS WEIGHT REL RELEASE

HD DENSITY ALTITUDE ROTOR (NR) ROTOR RPM Hp PRESSURE ALTITUDE RPM REVOLUTIONS PER HSI HORIZONTAL SITUATIONMINUTE

INDICATOR STA STATION

HTR HEATER TEMP CONT TEMPERATURE CONTROL ii

(7)

FAA APPROVED

VCAL CALIBRATED AIRSPEED VNE NEVER EXCEED SPEED

VFR VISUAL FLIGHT RULES VTOCS TAKEOFF CLIMBOUT

VG VERTICAL GYRO SPEED

VIAS INDICATED AIRSPEED VTOSS TAKEOFF SAFETY SPEED

VISUAL XFEED CROSSFEED

METEOROLOGICAL CONDITIONS

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FAA APPROVED BHT-212VFR-FM-1

Section

1

TABLE OF CONTENTS

Page

Subject Paragraph Number

TRANSMISSION

... ... ...

-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 ... 1-9

(9)

TABLE OF CONTENTS (Cont)

Page

ROTOR RPM - POWER ON ... ... 1-15-A ... 1-9 ROTOR RPM - POWER OFF ... 1-15-B ... 1-9 HYDRAULIC ... 1-16 ... 1-9 HYDRAULIC PRESSURE ... 1-16-A ... 1-9 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

GEARBOXES ... 1-17-C ... 1-10 ROTOR BRAKE... 1-18 ... 1-10 LANDING GEAR ... 1-19 ... 1-10 INSTRUMENT MARKINGS AND PLACARDS ... 1-20 ... 1-10 HEATER ... 1-21 ... 1-10

LIST OF FIGURES

Figure Page

Title Number Number

Weight-altitude-temperature limitations for takeoff, landing

and in ground effect maneuvers chart ... 1-1... 1-11

Gross weight center of gravity chart ... 1-2... 1-12

Placards and decals ... 1-3... 1-13 Single engine height-velocity chart ... 1-4... 1-15

Instrument markings ... 1-5... 1-16

(10)

FAA APPROVED

BHT-212VFR-FM-1

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

The basic configured helicopter is approved

as a fifteen-place helicopter and is certified for

operation in day or night VFR non-icing

conditions.

1-4.

FLIGHT CREW

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.

Refer to applicable operating rules

for internal cargo operations.

1-5.

CONFIGURATION

1-5-A.

REQUIRED EQUIPMENT

Heated pitot-static system

Pilot windshield wiper

Force trim system

NOTE

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(12)

Longitudinal CG limits are from station NOTE

130.0 to

144.0. Station 0 (datum) is located 20

inches (508 millimeters) aft of Longitudinal CG operational range is most forward point of cabin nose.

variable (figure 1-2), depending upon GW,

and shall be computed from weight and

balance data.

(13)

BHT-212VFR-FM-1

1-6-B-2. LATERAL CENTER OF 1-9. MANEUVERING

GRAVITY

Lateral CG limits are 4.7 inches (119.4 1-9-A. PROHIBITED MANEUVERS millimeters) left and 6.5 inches (165.1

millimeters) right of fuselage centerline. Aerobatic maneuvers are prohibited.

1-7. AIRSPEED _{1-9-B. CLIMB AND DESCENT}

7500 pounds (3402 kilograms) GW - VNE _{Refer to Section 4, PERFORMANCE.}

130 KIAS.

11,200 pounds (5080.3 kilograms) GW

-

1-10.

HEIGHT-VELOCITY

VNE 100 KIAS.

The height-velocity limitations are critical Doors open/off operation - VNE 100 KIAS in the event of a single engine failure

(any GW).

during takeoff, landing, and other

operation near the surface (figure 1-4).

VNE decreases linearly from 130 knots to The AVOID area of the Height-Velocity 100 knots with GW (Refer to Placards And chart defines the combinations of airspeed Decals, Figure 1-3). and height above ground from which a

safe single engine landing on a smooth, VNE decreases 3 knots per 1000 feet above level, firm surface cannot be assured.

3000 feet H .

The H-V chart is valid only when the

Maximum airspeed when operating above Weight-Altitude-Temperature limitations/ maximum continuous torque (87.5%) is 80 are not exceeded (figure 1-1). The diagram

KIAS. does not define the conditions which

assure continued flight following an

engine failure nor the conditions from

1-8. ALTITUDE

which a safe power off landing can be

made.

Maximum operating- _Maximum_{operating -} 20,000 feet Hp._{20,000 feet Hp.} _{When takeoffs}

are made in accordance with HV charts, proceed as follows:

Refer to applicable operating rules for high altitude oxygen requirements.

altitude requiremrnt. oxygen Determine hover torque at a four foot skid height.

CAUTION 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

15,000 feet takeoff distance performance will

Below 15,000 feet Hp, restart may be not be achieved. When near zero

attempted in either manual or automatic wind conditions prevail, determine

fuel control mode. true direction of wind.

(14)

1-11. AMBIENT TEMPERA-

1-12-C. STARTER

TURES

Limit starter energizing time to:

Maximum sea level ambient air

30 seconds - ON.

temperature for operation is +52 °C (+125 60 seconds - OFF. °F) and decreases with altitude at standard

lapse rate (2 °C per 1000 feet H ). 30 seconds - ON. Minimum ambient air temperature at all 5 minutes - OFF. altitudes is -54 °C (-65 °F). Refer to 30 seconds - ON. Weight-altitude-temperature limitations for 15 minutes -OFF.

takeoff, landing and in ground effect

maneuvers chart (figure 1-1). Above energizing cycle may then be

repeated.

1-12. ELECTRICAL

1-12-A. BATTERY

28 VDC ground power units for starting

shall be rated at a minimum of 400 amps and a maximum of 1000 amps.

WA R NIN G

1-13. POWER PLANT

BATTERY SHALL NOT BE USED PRATT AND WHITNEY CANADA PT6T-FOR ENGINE START AFTER 3B and PT6T-3.

ILLUMINATION OF BATTERY

TEMP LIGHT (IF INSTALLED).

BATTERY SHALL BE REMOVED NOTE

AND SERVICED IN ACCORDANCE Operation in 2 1/2 minute or 30 WITH MAN U FACTU R E R minute OEI range is intended for

INSTRUCTIONS PRIOR TO emergency use only, when one

RETURNING BATTERY TO engine becomes inoperative due

SERVICE. to actual malfunction. OEI ranges

shall not be used for training.

Maximum battery case temperature - 54.5

°° (130 °F). _{1-13-A. GAS PRODUCER RPM}

Maximum battery internal temperature

-62.7 °C (145 °F). 1-13-A-1. TWIN ENGINE OPERATION 1-12-B. GENERATOR

Maximum - 150 amps per ammeter. GAS PROD RPM (N1) - PT6T-3B

(Gage P/N 212-075-037-101)

Continuous

operation 61 to 100.8%

To attain published single engine Maximum

performance, generator loads

continuous

100.8%

should not exceed 75 amps each

during twin engine operation. Maximum for

takeoff 100.8% Ammeter needle may deflect full Maximum Transient

scale momentarily during (not to exceed 30

generator assisted start of second seconds) 102.6%

engine.

(15)

GAS PROD RPM (N|) - PT6T-3B 1-13-C. INTERTURBINE

(Gage P/N 212-075-037-113) TEMPERATURE

Continuous

operation 61 to 101.8%

Maximum PT6T-3B (TWIN ENGINE

continuous 101.8% OPERATION)

Maximum for Continuous

takeoff 101.8% operation 300 to 765 °C Maximum Transient (not to exceed 30 seconds) 102.6% continuous 765 5 Minute takeoff range 765 to 810 °C

GAS PROD RPM (N) - PT6T-3 Maximum

Maximum for

Maximum continuous operation takeoff 810 °C

Maximum transient

Transient (not to exceed 10 seconds) (Not to exceed 5

101.5% seconds) 850 °C

Maximum for

1-13-A-2. ONE ENGINE starting (Not to

INOPERATIVE (OEI) exceed 2 seconds

above 960 °C) 1090 °C

GAS PRODUCER RPM (N|) -PT6T-3B(Gage P/N

212-075-037-101) NOTE

21/2 minute range 100.8 to 102.4% If ITT remains above 810 °C longer Maximum 102.4% than 15 seconds or exceeds other

limits, ITT and duration shall be recorded in helicopter logbook.

GAS PRODUCER RPM (N|) -

Refer to Pratt and Whitney

PT6T-3B (Gage P/N 212-075-037- Maintenance Manual for

113) inspection requirements.

21/2 minute range 101.8 to 103.4%

Maximum 103.4% PT6T-3B (SINGLE ENGINE

OPERATION)(OEI)

1-13-B. POWER TURBINE RPM 30 Minute OEI range 765 to 822 °C

(N₂) 2/2 Minute

OEI range 822 to 850 °C PT6T-3B and PT6T-3 Maximum OEI 850 °C Takeoff 100%

Minimum 97%

Continuous

operation 97 to 100%

Maximum continuous 5 Minute range (twin

operation 100% engine operation) 765 to 810 °C Transient (not to 30 Minute range (single

exceed 10 seconds) 101.5% engine operation) 765 to 810 °C

(16)

PT6T-3 1-13-F. ENGINE OIL PRESSURE

Maximum continuous

limit (single or twin PT6T-3B or PT6T-3

engine operation) 765 °C Mnimum (Below

Power change transient 79% N,) 40 PSI limit (5 seconds above

810 °C not to exceed 850 79 to 100% N

°C) 850 °C Maximum 115 PSI

Starting transient limit

(Not to exceed 2 seconds

above 810 °C) 1090 C 1-13-G. ENGINE OIL TEMPERATURE 1-13-D. ENGINE TORQUE

NOTE

NOTE _{Helicopters with PT6T-3B engine}

For normal twin engine operation, shall use only gages marked 0 -maximum permissible torque 115°C. Helicopters with PT6T-3

needle split is 4% total. engine may use either gage.

ONE ENGINE INOPERATIVE PT6T-3B or PT6T-3

(ENGINE SCALE) - PT6T-3 (AND PT6T-3B WITH TORQUEMETER

MARKED FOR 71.8% MAX OEI) Continuous

Maximum operation 0 to 115 °C continuous 63.9% Maximum 115 °C 30 Minute power range 63.9 to 71.8% Maximum 71.8% PT6T-3 ONLY Minimum 5 °C ONE ENGINE INOPERATIVE Maximum 107 °C

(ENGINE SCALE) - PT6T-3B WITH TORQUEMETER MARKED

FOR 79.4% MAX OEI 1-13-H. COMBINING GEARBOX OIL

Maximum PRESSURE

continuous 63.9% 30 Minute power

range 63.9 to 79.4% PT6T-3B or PT6T-3

Maximum 79.4% Minimum for idle 40 PSI Operation below

1-13-E. FUEL PRESSURE _Continuous94% N2 40 to 60 PSI

Minimum 4 PSI operation 60 to 80 PSI Continuous 4 - 35 PSI Maximum 80 % 80 PSI Maximum 35 PSI

(17)

(18)

BHT-212VFR-FM-1

FAA APPROVED

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;

MIL-T-5624, Grade JP-4; or NATO F-40 may be

used at all ambient air temperatures.

Fuel conforming to ASTM D-1655, Type A or

A-1; MIL-T-5624, Grade JP-5; or NATO F-44

and MIL-T-83133, Grade JP-8, or NATO F-34

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 5 7 3 4 m ay b e u s e d a t a l l a m b i e nt 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)

may be used at all 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).

NOTE

DOD-L-85734AS or MIL-L-23699 is

recommended.

1-18. ROTOR BRAKE

Engine starts with rotor brake engaged are

prohibited. Rotor brake application is limited

to ground operations and shall not be applied

unti l engi nes have been shut down and

ROTOR RPM has decreased to 40% or less.

1-19. LANDING GEAR

Refer to BHT-212-MD-1.

1-20. INSTRUMENT

MARKINGS AND PLACARDS

Refer to Figure 1-3 for Placards and Decals.

Refer to Figure 1-5 for Instrument range

markings.

1-21. HEATER

Heater shall not be operated when OAT is

above 21 °C (69.8 °F).

Refer to Appendix A for a listing of Flight

Ma nual Supp le me nts covering optional

equipment kits available.

Maximum

88 °C

(19)

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. LIMIT

6000

GROSS WEIGHT

212VFR-FM-1-1

Figure 1-1. Weight-altitude-temperature limitations for takeoff, landing and in ground effect maneuvers chart

(20)

BHT-212VFR-FM-1 FAA APPROVED

11,000

10,000

130 132 134 13B 138 140 142 144

LONGITUDINAL C.G. STATION INCHES

212VFR-FM-1-2

Figure 1-2. Gross weight center of gravity chart

(21)

FAA APPROVED

(if installed)

(TYPICAL)

PANEL AFT END OF OVERHEAD CONSOLE

212VFR-FM-1-3-1

Figure 1-3. Placards and decals

PANEL AFT END OF OVERHEAD CONSOLE _{212VFR-FM-1-3-1}

Figure 1-3. Placards and decals

(22)

NOTES:

A

USED WITH GAS PRODUCER GAGE P/N 212-075-037-101

A2

USED WITH GAS PRODUCER GAGE P/N 212-075-037-113

212VFR-FM-1-3-2

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

(23)

FAA APPROVED

NOTE: THEHELICOPTERCONFIGURATION SHALL COMPLY WITH THE

WEIGHT-400 ALTITUDE-TEMPERATURECHART

FOR HEIGHT-VELOCITY DIAGRAM TO BE VALID 350 IATL

3LIMIlT

1000 LB LESS THAN WAT LIMIT

200

100 IN SHADED AREAS 50 00 10 20 30 40 50 60 70

INDICATED AIRSPEED - KNOTS

Figure 1-4. Single engine height-velocity chart

(24)

INSTRUMENT

MARKINGS

-

PT6T-3B

(25)

FAA APPROVED

(26)

FAA APPROVED

INSTRUMENT

MARKINGS

-

PT6T-3

Figure 1-5. Instrument markings (Sheet 3 of 6)

(27)

INSTRUMENT

MARKINGS

-

PT6T-3

(28)

BHT-212VFR-FM-1

FAA APPROVED

(29)

FAA APPROVED

(30)

Section 2

TABLE OF CONTENTS

Page

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... 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 ... 2-6... 2-10 FORCE TRIM CHECK... 2-6-A ... 2-10 PRELIMINARY HYDRAULIC CHECK ... 2-6-B ... 2-10 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... 2-12 CABIN HEATER CHECK ... 2-6-G ... 2-12 HYDRAULIC SYSTEMS CHECK ... 2-6-H ... 2-13

BEFORE TAKEOFF... 2-7... 2-14

POWER ASSURANCE CHECK ... 2-7-A ... 2-14

TAKEOFF ... 2-8... 2-14

INFLIGHT OPERATIONS ... 2-9 ... 2-15 DESCENT AND LANDING ... 2-10 ... 2-15 ENGINE SHUTDOWN ... ... 2-11 ... 2-15 POSTFLIGHT CHECK ... 2-12 ... 2-16

LIST OF FIGURES

Figure Page

Title Number Number

Exterior check diagram ... 2-1... 2-17

(31)

Section 2 2-1. INTRODUCTION

Consult applicable weight and balance instructions provided in Section 5.

This section contains instructions and

procedures for operataing helicopter from Determine weight of fuel, oil, load, etc., compute takeoff and anticipated landing

planning stage, through actual flight

GW, and check helicopter CG locations.

conditions, to securing helicopter after

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.

(32)

2-3-B. EXTERIOR CHECK ENGINE 1 BOOST PUMP and ENGINE

2 BOOST PUMP switches - ON.

switches - ON.

IF HELICOPTER HAS BEEN Fuel filters (left and right) - Drain

EXPOSED TO SNOW OR ICING CONDITIONS, SNOW AND ICE

CONDITIONS, SNOW AND ICE ENGINE 1 FUEL and ENGINE 2 FUEL SHALL BE REMOVED PRIOR TO

_switches

_-

_OFF.

FLIGHT

ENGINE 1 BOOST PUMP and ENGINE 1. FUSELAGE -FRONT _{2 BOOST PUMP switches -} _OFF.

Rotor blade -

Condition

and

BATTERY

BUS 1 switch - OFF.

cleanliness.

2. FUSELAGE- CABIN LEFT SIDE Cabin area - Condition, all glass clean.

Copilot and passenger doors

-Pitot tube(s) - Cover(s) removed, Condition and operation, glass clean.

unobstructed. _{Security of emergency release handles.}

Static ports (left and right) -

Position

lights - Condition.

Unobstructed.

Landing gear -

Condition, ground

Remote hydraulic filter bypass indicator handling wheels removed.

- Check green.

Engine air intake - Cover removed, Cabin nose ventilators - Unobstructed. unobstructed.

Nose compartment - Condition and 3. FUSELAGE - AFT LEFT SIDE doors secured.

Drain lines - Clean, unobstructed.

Battery vent and drain tubes

-Unobstructed. Engine compartment - Check.

Searchlight and landing light - Stowed. Engine oil level - Verify presence of oil in sight gage and proper oil level. Antenna - Condition, security.

Engine governor spring - Condition.

Fuel sumps - Drain samples as follows:

Engine fire extinguisher - Bottle

ENGINE 1 BOOST PUMP and ENGINE pressure gage and temperature range. 2 BOOST PUMP switches - OFF.

Combining gearbox filter - Bypass

ENGINE 1 FUEL and ENGINE 2 FUEL indicator retracted.

switches - OFF.

Access doors and engine cowling

-BATTERY BUS 1 switch - ON. Secured.

Fuel sump drain buttons (left and right) - Press.

Fuel filters - Drain before first flight of

day as follows:

(33)

FAA APPROVED

Engine exhaust ejector tubes - Covers Fuel filler - Check fuel quantity, secure

removed, unobstructed. cap.

4. FUSELAGE - AFT 6. FUSELAGE - CABIN RIGHT SIDE

Tailboom - Condition. Engine air intake - Cover removed,

unobstructed.

Tail rotor driveshaft covers - Secured. Transmission oil - Verify presence of

oil and proper level in sight gage

Synchronized elevator -

Condition,

security. Pilot and passenger doors - Condition

and operation, glass clean. Security of

Main rotor blade -

Condition,

emergency

release handles.

cleanliness. Remove tiedown.

Position lights - Condition. Tail rotor gearbox - Verify presence of

oil and proper level in sight gage, filler Landing gear - Condition, ground cap and chip detector plug security, handling wheels removed.

Tail rotor - Condition, free movement 7. CABIN TOP

on flapping axis.

Intermediate gearbox - Verify presence CAUTION

of oil and proper level in sight gage,

filler cap and chip detector plug SNOW AND ICE SHALL BE

security. REMOVED PRIOR TO FLIGHT

WHEN HELICOPTER HAS BEEN Tail skid - Condition, security. EXPOSED TO SNOW OR ICING

CONDITIONS.

Synchronized elevator - Condition, CONDITIONS.

security. Main rotor and controls - Condition,

fluid levels in all reservoirs. Tailboom - Condition.

Transmission oil filler cap - Secured.

Baggage compartment - Check smoke

detector - Condition and security. Hydraulic oil reservoirs - Check sight Cargo and door secured. glasses for proper fluid levels. Caps

secured. 5. FUSELAGE AFT RIGHT SIDE

Antenna(s) - Condition and security.

Engine fire extinguisher -

Bottle

Combining gearbox oil filler cap

pressure gage and temperature range. Secured.

Combining gearbox oil -

Verify

Anticollision light -

Condition and

presence of oil and proper level in sight security.

gage. Close access door.

Engine compartment - Check. CAUTION

Engine oil level - Verify presence of oil

and proper level in sight gage. IF ANY TEMP-PLATE IS MISSING

OR HAS BLACK

DOTS,

Access doors and engine cowling - MAINTENANCE PERSONNEL

Secured. SHALL ASSIST IN DETERMINING

AIRWORTHINESS AS STATED IN BHT-212-MM.

(34)

Main driveshaft and coupling - Lower pedestal circuit breakers -In.

Condition, security, and grease leakage.

Check Temp-Plates (four places each Collective control head switches - OFF.

coupling) for evidence of elevated

temperature indicated by dot changing COMPASS CONTROL slaving switch(es)

color to black. - MAG (slave position).

Engine air intakes - Unobstructed, Radio equipment - OFF. particle separator doors closed.

Fuel INTCON switch - Normal.

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

switches - OFF.

PRESTART CHECK

switches OFF.

ENGINE NO. 1 PART SEP and ENGINE

Cabin Interior - Cleanliness, security of NO. 2 PART SEP switches - NORM (if

equipment. installed).

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.

FORCE TRIM switch - ON, cover down. Cargo load - Secured.

Instruments - Static check.

Protective breathing equipment (if

required) - Condition and properly STATIC SOURCE switch (if installed)

-serviced. PRI.

Seat and pedals - Adjust. Altimeter(s) - Set.

Seat belt and shoulder harness - Clock - Set and running.

Fasten and adjust.

FIRE EXT switch - OFF.

Shoulder harness inertia reel and lock

-Check. FIRE PULL handles - In (forward).

AFT DOME LT rheostat and switch

-Flight controls - Freedom of movement, AFT DOME LT rheostat and

switch-position for start. OFF.

Cyclic - Centered, friction as desired. PITOT STATIC HEATERS switch - OFF

Collective - Full down.

Transmission chip detector indicators (if installed) - Check.

(35)

FAA APPROVED

BHT-212VFR-FM-1

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 (if installed) — NORM.

Overhead circiut breakers — In.

All light rheostats — OFF.

EXTERIOR LIGHT POSITION switch —

OFF.

EXTERIOR LIGHT ANTI COLL switch — OFF.

All invertor 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

l i g h t i l l u m i n a t e s ( S N 3 0 5 5 4 a n d

subsequent).

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.) (SN 30597 and subsequent).

CAUTION

ROTOR BRAKE HANDLE SHALL

BE IN DETENT POSITION (OFF) AT

ALL TIMES WHEN ENGINES ARE

RUNNING.

ROTOR BRAKE lights (if installed) — 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 light test switch — TEST and

RESET.

INV 1 switch — ON, check no. 1 AC voltmeter

f o r 1 0 4 t o 1 2 2 vo l t s ( S N 3 0 5 5 4 a n d

subsequent).

INV 2 switch — ON, check no. 2 AC voltmeter

f o r 1 0 4 t o 1 2 2 vo l t s ( S N 3 0 5 5 4 a n d

subsequent).

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 temperatures of -18 °C (0 °F)

or less, both throttles will be difficult

to move and follow-through coupling

may be increased.

Throttles — Rotate engine 1 throttle full

o p e n , t h e n b a c k a g a i n s t i d l e s t o p .

A c t u a t e E N G 1 I D L E S TO P R E L , r o l l

(36)

(37)

FAA APPROVED

AMPS 1 - Check at or below 150 GAS PROD RPM (N|) - Check 61 ± 1% 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% HIGHER ENG RPM (N2) THAN

Do not increase ROTOR above ENGAGED ENGINE AND NEAR

80% RPM 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 SN 30597 Engine 2 ENGINE OIL pressure - Check. and subsequent.)

ENG 2 PART SEP OFF light

-ENGINE 2 FUEL switch - ON. (ENG 2 Extinguished.

FUEL VALVE caution light will Illuminate

momentarily SN 30597 and subsequent.)

2-5-C. POST START

Engine 2 FUEL PRESS - Check.

External power - Disconnect if used, START switch - ENG 2 position. GEN 1 switch - ON.

Observe starter limitations.

GEN 2 switch - ON (BATTERY BUS 1

Engine 2 ENGINE OIL pressure - will switch OFF automatically SN 30554

Indicating. and subsequent).

Engine 2 throttle - Open to idle at 12% GAS PROD RPM (Nl) minimum.

Engine 2 ITT - Monitor. Observe ITT

limitations. IF OPERATING ON BATTERY BUS POSITION INV 3 SWITCH TO ON

START switch - Off at 55% GAS PROD

(38)

ONLY ONE BATTERY SWITCH Throttle - Fully closed.

SHALL BE ON DURING FLIGHT

(SN 30554 AND SUBSEQUENT). 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.

NOTE ENGINE (1 or 2) FUEL switch - OFF. 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

2-5-D.

ENGINE FAILS TO START LIMITATIONS.

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._{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

-Press; check trim releases with button

pressed, reengages with button

ENGINE (1 or 2) FUEL switch - OFF. released.

After GAS PROD RPM (No) has decreased FORCE TRIM switch - OFF; check trim

to zero, allow 30 seconds for fuel to disengages and FT OFF caution light drain from engine. Conduct a DRY disengages

MOTORING RUN before attempting

another start.

another start. FORCE TRIM switch - ON.

2-5-E. DRY MOTORING RUN 2-6-B. PRELIMINARY HYDRAULIC

Following procedure is used to clear an

CHECK

engine whenever it is deemed necessary to

remove internally trapped fuel and vapor: Throttles - Set to idle.

(39)

FAA APPROVED

NOTE 2-6-E. FUEL CROSSFEED VALVE

Uncommanded control movement CHECK

or motoring with either hydraulic

system off may Indicate hydraulic 2-6-E-1. SN PRIOR TO 30554 system malfunction.

FUEL PUMP CROSSFEED switch -HYDR SYS NO. 1 switch - OFF, then NORMAL. Position ENGINE 1 BOOST

ON. PUMP switch to OFF. Note pressure

HYDR SYS NO. 2 switch - OFF, then drop on No. 1 FUEL PRESS gage,

ON.

followed by

_{Indication, showing crossfeed valve has}

a

return to normal

opened and check valve is functioning

2-6-C. ENGINE FUEL CONTROL properly.

CHECK Position ENGINE 1 BOOST PUMP switch to ON and position ENGINE 2 BOOST

Throttles - Idle. PUMP switch to OFF. Note pressure

drop on No. 2 FUEL PRESS gage,

followed by a return to normal

Indication, showing crossfeed valve has

Do not allow GAS PROD (N,) RPM opened and check valve is functioning to decrease below 50%. properly.

At approximately 8000 feet Hp,

GAS PROD RPM (N,) may not NOTE

change significantly when manual If in either of the above checks; fuel control Is selected. fuel pressure is 4 to 6 psi below

normal (10 ± 4 psi), appropriate

GOV switch (ENGINE NO. 1 or 2) - check valve Is not functioning MANUAL, observe change in GAS PROD properly.

RPM (N,). Open respective throttle

carefully to assure GAS PROD RPM (N|) ENGINE 2 BOOST PUMP switch - ON.

responds upward, then return throttle to

idle. Return GOV switch to AUTO. FUEL PUMP CROSSFEED switch -Check for return to original GAS PROD OVERRIDE CLOSE. Position either

RPM (N|). Check other governor in same BOOST PUMP switch to OFF. Note fuel

manner. pressure drops to zero. Position BOOST

PUMP switch to ON and FUEL PUMP

2-6-D. GOVERNOR CHECK CROSSFEED switch to NORMAL.

2-6-E-2. SN 30554 AND

No. 1 throttle - Full open. Check ENG SUBSEQUENT RPM (N2) stabilizes at 95 ± 1%.

FUEL XFEED test switch - TEST BUS 1 No. 2 throttle - Full open. Check ENG and hold.

RPM (N2) increases 2% and both engines

stabilize at 97 ± 1% .

NOTE RPM INCR DECR switch - INCR to 100%

If, after turning either boost pump

(N2) off, fuel pressure remains 4 to 6 psi below normal (10 ± 4 psi), appropriate check valve is not functioning properly.

(40)

ENGINE 1 BOOST PUMP switch - OFF. INV 3 switch (if installed) - OFF, then Check no. 1 FUEL PRESS decreases, ON DC BUS 1, check INVERTER 3

then returns to normal. (This indicates caution light extinguishes.

that crossfeed valve has opened by bus

no. 1 power and check valve is INV 1 switch - OFF, INVERTER 1 functioning properly.) ENGINE 1 BOOST caution light illuminates. check no. 1

PUMP

switch - ON.

AC voltmeter for Indication that

inverter no. 3 has assumed load (SN FUEL XFEED test switch - TEST BUS 2 30554 and sub). INV 1 switch - ON,

and hold.

INVERTER

1 caution

light

extinguishes.

ENGINE 2 BOOST PUMP switch - OFF.

Check no. 2 FUEL PRESS decreases, NOTE

then returns to normal. ENGINE 2

BOOST PUMP switch - ON. INV 3 Switch must be ON for

avionics cooling fan to operate.

FUEL XFEED test switch - NORM.

INV 3 switch (if installed) - OFF, then

ON DC BUS 2. FUEL XFEED switch - OVRD CLOSE.

ENGINE 1 (or ENGINE 2) BOOST PUMP 2-6-G. CABIN HEATER CHECK switch - OFF. Check fuel pressure

drops to zero on selected system. GAS PROD - Check 75%(Nl) minimum

ENGINE 1 (or ENGINE 2) BOOST PUMP (both engines).

switch - ON.

AIR COND TEMP CONT switch - Fully FUEL XFEED switch - NORM. COOL.

2-6-F. ELECTRICAL SYSTEMS CAUTION

CHECK

SYSTEM SELECTOR SWITCH

DC voltmeters - Check 27 ± 1 vdc. SHALL BE TURNED OFF WHEN HEATED AIRFLOW DOES NOT AC voltmeters - Check 104 to 122 vac. SHUT OFF AFTER AIR COND TEMP CONT SWITCH IS TURNED

Ammeters - Check within limits. TO FULLY COLD, HEATER AIR

LINE CAUTION LIGHT

ILLUMINATES, OR CABIN HTR AC system - Check as follows (SN CIRCUIT BREAKER TRIPS. 30554 and subsequent):

DO NOT OPERATE HEATER

INV 3 switch (if installed) - ON DC ABOVE 21°C OAT. BUS 2, check INVERTER 3 caution

light extinguishes.

light extinguishes. SYSTEM SELECTOR switch - HEATER.

VENT BLOWER switch - ON. INV 2 switch - OFF, INVERTER 2

caution light illuminates. Check no. 2

AC voltmeter for indication that

inverter no. 3 (if installed) has

assumed load. INV 2 switch - ON,

INVERTER 2 caution light

extinguishes.

(41)

AIR COND TEMP CONT switch - Rotate illuminates and HYDRAULIC caution

counterclockwise and observe heated light illuminates. Hydraulic system

airflow. no. 1 pressure decreases..

DEFOG lever - ON; check airflow is Cyclic - Check normal operation by diverted from pedestal outlets to moving cyclic in an 'X' pattern, right windshield nozzles. Return lever to forward to left aft, then left forward to

OFF.

right aft (approximately 1 inch).

Center cyclic. AFT OUTLET switch - ON; check

airflow distributed equally between Collective - Check normal operation

pedestal outlets and aft outlets. Return by increasing collective slightly (1 to 2

switch to OFF. inches). Return to down position.

NOTE NOTE

Heater operation

affects

Boost for tail rotor controls is

performance. Refer to Hover furnished by hydraulic system no.

Ceiling and Rate of Climb charts 1 only. When hydraulic system for HEATER ON in Section 4. no. 1 is being checked, tail rotor

controls will be unboosted. SYSTEM SELECTOR (heater) switch

-SYSTEM SELECTOR (heater) switch Pedals - Displace slightly left and right. Note an increase in force VENT BLOWER switch - As desired. required to move pedals.

2-6-H. HYDRAULIC SYSTEMS CHECK

DO NOT TURN BOTH HYDRAULIC NOTE SYSTEMS OFF AT SAME TIME

DUE TO EXCESSIVE FORCE

This check is to determine proper REQUIRED TO MOVE FLIGHT

operation of hydraulic actuators CONTROLS.

for each flight control system. If

abnormal forces, unequal forces, HYDR SYS NO. 1 switch - ON. Check

control binding, or motoring is MASTER CAUTION light extinguishes encountered, it may be an and hydraulic system no. 1 pressure indication of a malfunction of a returns to normal. HYDRAULIC flight control actuator. caution light extinguishes.

FORCE TRIM switch - OFF. HYDR SYS NO. 2 switch - OFF.

Check MASTER CAUTION light

Collective - Down, friction removed. illuminates and hydraulic system no. 2 pressure decreases. HYDRAULIC

ROTOR RPM (NR) - Set to 100%. caution ght illuminates.

Cyclic - Check normal operation of Cyclic - Centered, friction removed. cyclic controls by moving cyclic in an

0

Hydraulic system - Check as follows:

HYDR SYS NO. 1 switch - OFF.

Check MASTER CAUTION light

(42)

then left forward to right aft

Radlo(s)

-

Check operation and set.

(approximately 1 inch). Center cyclic.

Cyclic - Friction as desired. Collective - Check normal operation

by increasing collective slightly (1 to 2

inches). Return to down position. NOTE

Moderate friction shall be applied Pedals - Displace slightly left and to each throttle to overcome right. Note no increase in force follow-through coupling between

required to move pedals. _{twist grips.}

HYDR SYS NO. 2 switch - ON. Check Throttles - Full open, Adjust friction. MASTER CAUTION light extinguishes

and hydraulic system no. 2 pressure ENG RPM (N) - 100% (both engines).

returns to normal. HYDRAULIC

caution light extinguishes. FORCE TRIM switch - As desired.

Cyclic and collective friction - As COCKPIT VOICE RECORDER TEST

desired. switch (If Installed) - Press and hold for

3 seconds. Verify meter indicates

FORCE TRIM switch - ON. GOOD.

Passenger step switch (if installed)

-As desired.

Passenger seat belts - Fastened.

BOTH HYDRAULIC SYSTEMS

SHALL BE OPERATIONAL PRIOR All doors - Secured. TO TAKEOFF.

Caution and warning lights

-Extinguished.

NOTE

System 1 will normally operate 10 2-7-A. POWER ASSURANCE

to 20 °C cooler than system 2.

CHECK

2-7. BEFORE

TAKEOFF Perform power assurance check daily.

2-7. BEFORE TAKEOFF

Refer to Section 4.

Engine, transmission, gearbox,

hydraulic, and electrical instruments -

2-8. TAKEOFF

Check readings within operational

range. ENG RPM (N2) - 100%.

Flight instruments - Check operation

and set. NOTE

No more than 15% torque above

Position lights - As required.

hover power shall be used

accelerating to Takeoff Climbout Magnetic compass - Fluid level and Speed.

heading.

Collective - Initiate takeoff from a hover Anti-collision lights - As required. height of 4 feet.

Pitot heater - As required.

(43)

NOTE Cyclic control and pedals - Centered and frictioned.

Takeoff must be executed in

accordance with Height-Velocity FORCE TRIM switch - ON. limitations for type of operation

being conducted.

Refer to

Throttles

- Idle.

Section 1.

ITT - Stabilize for one minute at idle Refer to Section 4 for additional prior to shut down

climb performance data.

Engine instruments - Within limits.

2-9. IN-FLIGHT OPERATIONS

ELT (if installed)

-

Check for

ENG RPM (N2) - Adjust INCR DECR inadvertent transmission.

switch to select desired RPM between 97 Radios OFF and 100%. (100% is normal RPM).

IDLE STOP REL switch - ENG 1. Airspeed - Within limits for GW and IDLE STOP REL switch ENG 1. flight altitude. Engine 1 throttle - Closed. Check ITT

and GAS PROD RPM (N.) decreasing.

Engine, gearbox, and transmission

Instruments - Within limits. BATTERY BUS 1 switch - ON (SN 30554 and subsequent).

NOTE _{IDLE STOP REL switch -} _{ENG 2.}

Refer to applicable operating

rules for high altitude operations. Engine 2 throttle - Closed. Check ITT

and GAS PROD RPM (N1) decreasing.

2-10.

DESCENT AND

GEN 1 and 2 switches - OFF.

LANDING

All invertors - OFF.

Flight controls -

Adjust friction as

desired. ENGINE 1 FUEL switch - OFF.

Throttles - Full open. ENGINE 1 BOOST PUMP switch - OFF. ENG RPM (N) - 100%. ENGINE 2 FUEL switch - OFF.

FORCE TRIM switch - As desired. ENGINE 2 BOOST PUMP switch - OFF. Passenger STEP switch - As desired.

CAUTION

Flight path - Avoid critical areas of HV

diagram from which a safe landing may

not be made In case of single engine AVOID RAPID ENGAGEMENT OF failure. For landing distance information ROTOR BRAKE IF HELICOPTER IS

in event of engine failure during ON ICE OR OTHER SLIPPERY OR

approach, refer to Section 4.. LOOSE SURFACE TO PREVENT ROTATION OF HELICOPTER.

2-11. ENGINE SHUTDOWN

Rotor brake

- Apply

at or below 40% ROTOR RPM (NR), return to stowed

Collective - Down. position after main rotor stops.

(44)

Pilot - Remain at flight controls until Winds in excess of 20 knots or a gust

rotor has come to a complete stop. spread of 15 knots exist or is forecast.

Lighting and miscellaneous switches - Helicopter is parked within 150 feet of

OFF. hovering or taxiing aircraft that are in

excess of basic helicopter GW.

BATTERY switch(es) - OFF.

Helicopter is to be left unattended.

2-12. POSTFLIGHT CHECK

Protective covers (engine exhaust and

pitot tube) - Install.

Main rotor and tail rotor blades

-Tiedown when any of following

conditions exist:

Thunderstorms exist in local area or are forecast.

(45)

BHT-212VFR-FM-1

212VFR-FM-2-1

Figure 2-1. Exterior check diagram

(46)

*

Section 3

TABLE OF CONTENTS

Page

INTRODUCTION ... 3-1 ... 3-3

DEFINITIONS ... 3-2... 3-3

ENGINE

...

3-3...3-3

SINGLE ENGINE FAILURE ... 3-3-A ... 3-3

ENGINE RESTART IN FLIGHT ... 3-3-B ... 3-4 DUAL ENGINE FAILURE ... 3-3-C ... 3-5 ENGINE UNDERSPEED ... 3-3-D ... 3-6 ENGINE OVERSPEED - FUEL CONTROLGOVERNOR

FAILURE ... 3-3-E ... 3-7 ENGINE OVERSPEED - DRIVESHAFT FAILURE ... 3-3-F ... 3-8 ENGINE COMPRESSOR STALL ... 3-3-G ... 3-9 ENGINE HOT START/SHUTDOWN ... ... 3-3-H ... 3-9 FIRE ... 3-4 ... 3-9 ENGINE FIRE ... 3-4-A ... 3-9 CABIN SMOKE OR FUMES... ... 3-4-B ... 3-11

BAGGAGE COMPARTMENT FIRE... 3-4-C ... 3-11 TAIL ROTOR... 3-5 ... 3-11 COMPLETE LOSS OF TAIL ROTOR THRUST ... 3-5-A ... 3-11 LOSS OF TAIL ROTOR THRUST AT HOVER ... 3-5-B ... 3-11 LOSS OF TAIL ROTOR THRUST IN CLIMB... 3-5-C ... 3-11 LOSS OF TAIL ROTOR THRUST IN LEVEL FLIGHT OR

DESCENT ... 3-5-D ... 3-12 LOSS OF TAIL ROTOR COMPONENTS ... 3-5-E ... 3-12 TAIL ROTOR FIXED PITCH FAILURES ... 3-5-F... 3-12 FIXED PITCH FAILURE AT A HOVER... 3-5-G ... 3-13 FIXED PITCH FAILURE IN FLIGHT ... 3-5-H ... 3-13 LOSS OF PITCH CHANGE CONTROL LINKAGE ... 3-5-J... 3-14 HYDRAULIC SYSTEM ... 3-6... 3-14 ELECTRICAL SYSTEM ... 3-7... 3-14 DC FAILURE TO PRODUCE POWER... 3-7-A ... 3-14 AC FAILURE TO PRODUCE POWER...3... 3-7- .... 3-14 FUEL SYSTEM ... 3-8 ... 3-14 FUEL BOOST PUMP FAILURE ... 3-8-A ... 3-14 FUEL FILTER PARTIALLY BLOCKED... 3-8-B ... 3-15 FUEL QUANTITY INDICATION MALFUNCTIONS ... 3-8-C ... 3-15 AUTOMATIC FLIGHT CONTROLS SYSTEM ... 3-9... 3-15 COMMUNICATION SYSTEM ... 3-10 ... 3-15 NAVIGATION RADIO FAILURE ... 3-10-A ... 3-15 INTERCOM FAILURE ... 3-10-B ... 3-15 CABIN HEATER ... 3-11 ... 3-15

(47)

FAA APPROVED

TABLE OF CONTENTS (Cont)

Page

LANDING GEAR ... 3-12 ... 3-16 STATIC PORT OBSTRUCTION ... 3-13 ... 3-16

LIST OF TABLES

Table Page

Title Number Number

WARNING LIGHTS ... 3-1 ... 3-17 CAUTION LIGHTS ... 3-2... 3-19

(48)

FAA APPROVED

BHT-212VFR-FM-1

Section 3 EMERGENCY/MALFUNCTION PROCEDURES

/secttitle>

3-1.

INTRODUCTION

Following procedures contain indications of

equipment or system failure or malfunction,

use of emergency features of primary and

backup systems, and appropriate warnings,

cautions, and explanatory notes. Table 3-1

lists fault conditions and corrective actions

required for illumination of red warning lights.

Table 3-2 addresses malfunction procedures

associated with yellow caution lights.

Corrective action procedures listed herein

assume pilot gives first priority to helicopter

control and a safe flight path.

Helicopter should not be operated following

any precautionary landing until cause of

m a l f u n c t i o n h a s b e e n d e t e r m i n e d a n d

corrective maintenance action taken.

3-2.

DEFINITIONS

Following terms indicate degree of urgency in

landing helicopter.

LAND AS SOON AS POSSIBLE — Land

without delay at nearest suitable area (i.e.,

open field) at which a safe approach and

landing is reasonably assured.

LAND AS SOON AS PRACTICAL — Duration of

flight and landing site are at discretion of pilot.

Extended flight beyond nearest approved

landing area is not recommended.

F o l l ow i n g t e r m s a r e u s e d t o d e s c r i b e

operating condition of a system, subsystem,

assembly, or component:

AFFECTED — Fails to operate in intended or

usual manner.

NORMAL — Operates in intended or usual

manner.

3-3.

ENGINE

3-3-A.

SINGLE ENGINE FAILURE

ENG RPM (N

₂

) of operating engine is allowed

to droop to 97% during transition from twin

engine operation to single engine operation.

When best rate of climb airspeed (58 KIAS) is

attained, N

₂

RPM should be increased to 100%

if possible.

Flight can be continued on remaining engine

until a desirable landing site is available. There

are certain combinations of GW, altitude, and

ambient air temperatures that will result in OEI

torque limit being exceeded. A run-on landing

at 20 to 30 knots is recommended.

Loss of an engine while hovering at high GW

and extremely cold conditions is likely to

result in exceeding OEI torque limit. If an

overtorque is observed or suspected, an entry

s h a l l b e m a d e i n l o g b o o k . R e f e r t o

performance charts in Section 4.

NOTE

Refer to ENGINE RESTART if an

engine restart is to be attempted.

INDICATIONS:

ENG 1 OUT or ENG 2 OUT warning light

illuminated.

(49)

BHT-212VFR-FM-1

FAA APPROVED

GAS PROD RPM (N

_I

) below 61 ± 1% and

decreasing.

ENG RPM (N

₂

) below 85% and decreasing.

ITT below 400 °C and decreasing.

ENG 1 or ENG 2 OIL PRESSURE, DC

GENERATOR, and PART SEP OFF caution

lights illuminated.

PROCEDURES:

WARNING

DO NOT ALLOW ROTOR RPM (N

_R

)

TO DECAY BELOW MINIMUM LIMITS.

CAUTION

D U R I N G C O L D W E A T H E R

OPERATIONS, MONITOR TORQUE

OF OPERATING ENGINE WHEN

ONE ENGINE FAILS OR IS SHUT

DOWN IN FLIGHT.

Shut down affected engine as follows:

Collective — Reduce as required to maintain

ROTOR RPM (N

_R

) within limits and power

within OEI limits.

NOTE

A i r s p e e d — 5 5 t o 6 5 K I A S f o r

Minimum Power for level flight.

RPM INCR DECR switch — INCR, set

remaining ENG RPM (N

₂

) at 100% if possible.

Throttle — Closed.

Fuel Crossfeed switch — Override Close.

Fuel Interconnect switch — OPEN.

ENGINE (1 or 2) BOOST PUMP switch — OFF.

Verify FUEL BOOST caution light and FUEL

switch to be turned off are all for affected

engine.

ENGINE (1 or 2) FUEL switch — OFF.

GEN (1 or 2) switch — OFF.

MASTER CAUTION light — Reset.

Land as soon as practical.

If no. 2 engine failed:

INV 3 to DC BUS 1 (if installed).

BATTERY BUS 2 switch — OFF.

BATTERY BUS 1 switch — ON.

MASTER CAUTION light — Reset.

Land as soon as practical.

3-3-B.

ENGINE RESTART IN

FLIGHT

Conditions which would warrant an attempt to

restar t an engine woul d probably be a

f l a m e o u t , c a u s e d by a m a l f u n c t i o n o f

automatic mode of fuel control unit. Decision

to attempt an engine restart during flight is

pilot responsibility. If an engine restart is to be

made, proceed as follows:

CAUTION

MONITOR ITT WHEN RESTARTING

E N G I N E I N M A N U A L F U E L

CONTROL MODE.

ENGINE RESTART:

ENGINE RESTART NO. 1:

Engine 1 throttle — Closed.

ENGINE 1 BOOST PUMP switch — ON.

Fuel Crossfeed switch — Normal.

ENGINE 1 FUEL switch — ON.

ENGINE NO. 1 GOV switch — MANUAL.

BATTERY BUS 2 switch — OFF.

BATTERY BUS 1 switch — ON.

INV 1 and INV 2 switches — ON.

INV 3 switch (if equipped) — ON DC BUS 1.

START switch — ENG 1.

A f t e r 1 2 % G A S P RO D R P M ( N

_I

) i s

attained and oil pressure is indicating,

slowly open throttle until a rise is seen

in ITT which indicates engine is

self-s u self-s t a i n i n g . D o n o t o p e n t h ro t t l e

farther until GAS PROD RPM (N

_I