Bell 212 Flight manual

BHT-212VFR-FM-1

ROTORCRAFT FLIGHT MANUAL

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

COPYRIGHT NOTICE COPYRIGHT 2002 BELL ® HELICOPTER TEXTRON INC. AND BELL HELICOPTER TEXTRON CANADA LTD. ALL RIGHTS RESERVED

POST OFFICE BOX 482

FORT WORTH, TEXAS 76101

14 AUGUST 1995 REVISION 4 — 02 DECEMBER 2002

BHT-212VFR-FM-1

NOTICE PAGE

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.

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 NP

BHT-212VFR-FM-1

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

LOG OF PAGES PAGE

REVISION NO.

Cover......................................................... 0 Title............................................................ 4 NP .............................................................. 0 A/B............................................................. 4 C/D............................................................. 4 i/ii ............................................................... 0 iii/iv ............................................................ 0 1-1 — 1-2 ................................................... 1 1-3.............................................................. 4 1-4.............................................................. 2 1-4A/1-4B .................................................. 2 1-5.............................................................. 1 1-6 — 1-7 ................................................... 2 1-8 — 1-9 ................................................... 1 1-10............................................................ 4 1-11 — 1-12 ............................................... 0 1-13 — 1-20 ............................................... 1 1-21/1-22.................................................... 1 2-1/2-2........................................................ 2 2-3.............................................................. 1 2-4.............................................................. 2 2-5.............................................................. 3 2-6.............................................................. 2 2-7.............................................................. 4 2-8.............................................................. 2 2-9.............................................................. 0 2-10............................................................ 2

REVISION NO.

PAGE

2-11 ........................................................... 1 2-12 — 2-14 .............................................. 2 2-15 ........................................................... 0 2-16 ........................................................... 2 2-17/2-18 ................................................... 0 3-1 — 3-2 .................................................. 0 3-3 — 3-4 .................................................. 4 3-5 — 3-9 .................................................. 2 3-10 ........................................................... 4 3-11 — 3-15 .............................................. 2 3-16 — 3-19 .............................................. 0 3-20 ........................................................... 2 3-21 — 3-22 .............................................. 0 4-1 — 4-4 .................................................. 0 4-5/4-6 ....................................................... 0 4-7 — 4-10 ................................................ 1 4-11 — 4-26 .............................................. 0 4-27 — 4-78 .............................................. 2 4-79/4-80 ................................................... 2 5-1/5-2 ....................................................... 0 5-3 — 5-4 .................................................. 0 5-5/5-6 ....................................................... 0 5-7 — 5-24 ................................................ 0 5-25/5-26 ................................................... 0 A-1 — A-2 ................................................. 2 A-3/A-4 ...................................................... 2

NOTE Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. 02 DEC 2002

Rev. 4

A/B

BHT-212VFR-FM-1

LOG OF FAA APPROVED REVISIONS Original ....................... 0.................... 29 OCT 70 Reissue ....................... 0....................14 AUG 95 Revision ..................... 1....................29 MAY 96

APPROVED:

Revision ......................2 .................... 12 SEP 97 Revision ......................3 ................... 01 MAY 98 Revision ......................4 ................... 02 DEC 02

DATE:

MANAGER

ROTORCRAFT CERTIFICATION OFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170 02 DEC 2002

Rev. 4

C/D

FAA APPROVED

BHT-212VFR-FM-1 GENERAL INFORMATION

This flight manual is divided into five sections and an appendix as follows: Section 1 Section 2 Section 3

LIMITATIONS NORMAL PROCEDURES EMERGENCY AND MALFUNCTION PROCEDURES PERFORMANCE DATA WEIGHT AND BALANCE DATA OPTIONAL EQUIPMENT SUPPLEMENTS

Section 4 Section 5 Appendix A

helicopter Section

WARNINGS, CAUTIONS, AND NOTES ARE USED THROUGHOUT THIS MANUAL TO EMPHASIZE IMPORTANT AND CRITICAL INSTRUCTIONS AND ARE USED AS FOLLOWS: WARNING

AN OPERATING

Sections 1 through approved

data necessary weight

and balance

data essential for safe operation of the helicopter. Appendix

A contains

a list

conjunction

which

shall

RESULT IN PERSONAL INJURY OR LOSS OF LIFE.

. CAUTION

of FAA

approved supplements for optional equipment,

PROCEDURE

to operate

in a safe and efficient manner. 5 provides

TERMINOLOGY

be used in

with basic flight manual when

respective optional equipment kits are installed.

AN OPERATING PROCEDURE, PRACTICE, ETC., WHICH, IF NOT

STRICTLY OBSERVED, COULD RESULT IN DAMAGE TO OR DESTRUCTION OF EQUIPMENT

Manufacturer's

data manual (BHT-212-MD-

1) contains additional information to be used in conjunction

optional applicable.

with flight manual and

equipment

supplements,

Manufacturer's

as

data manual is

divided into four sections as follows: Section 1 Section 2 Section 3 Section 4

NOTE

AN OPERATING PROCEDURE CONDITION

ETC.

WHICH

ESSENTIALTO HIGHLIGHT.

IS

SYSTEMS DESCRIPTION HANDLING AND SERVICING CONVERSION CHARTS

USE OF PROCEDURAL

AND TABLES

Procedural word usage and intended

EXPANDED PERFORMANCE

meaning which has been adhered preparing this manual is as follows:

WORDS

to in

SHALL has been used only when

application

of a procedure

is

mandatory.

SHOULD has been used only when

application

recommended.

of a procedure

is

FAA APPROVED

BHT-212VFR-FM-1 MAY and NEED NOT have been used only when application of a procedure

HV

HEIGHT-VELOCITY

HYDR SYS

HYDRAULIC SYSTEM

WILL has been used only to indicate futurity, never to indicate a mandatory procedure.

IGE IMC

IN GROUND EFFECT INSTRUMENT METEOROLOGICAL CONDITIONS

INCR

INCREASE

INTCON

INTERCONNECT

INV

INVERTER

ITT

INTERTURBINE TEMPERATURE

Is optional.

ABBREVIATIONS AND ACRONYMS USED

THROUGHOUT

THIS

MANUAL

ARE

DEFINED AS FOLLOWS: AC

ALTERNATING CURRENT

AGL

ABOVE GROUND LEVEL ATTITUDE

KCAS

KNOTS CALIBRATED AIRSPEED

ATTD BLWR

BLOWER

KG

KILOGRAM(S)

C

CELSIUS

KIAS

CDP

CRITICAL DECISION AIRSPEED LB POINT

KNOTS INDICATED AIRSPEED

CG

CENTER OF GRAVIT Y

CMD

COMMANDPOINT

DC

DIRECT CURRENT

DECR

DECREASE

DSENGA ELT

DISENGAGE EMERGENCY LOCATOR

MIN

TRANSMITTER

NAVIGATION

ENG

ENGINE

NON ESS

NON ESSENTIAL

ENGA

ENGAGE

NORM

NORMAL

ENG RPM (N2 ) F

ENGINE POWER TURBINE RPM FAHRENHEIT

OAT

FT GAS PROD (NI)

FOOT, FEET GAS PRODUCER RPM

OUTSIDE AIR TEMPERATURE ONE ENGINE INOPERATIVE

GEN

LDP

POUND(S) LANDING DECISION METER(S) POWER

OEI

MINIMUM, MINUTE(S)

OGE

OUT OF GROUND EFFECT

PART SEP

PARTICLE SEPARATOR

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 STA INDICATOR

HTR

HEATER

ii

TEMP CONT

STATION TEMPERATURE CONTROL

BHT-212VFR-FM-1

FAA APPROVED VCAL

VFR VG VIAS

CALIBRATED AIRSPEED VISUAL FLIGHT RULES VERTICAL GYRO INDICATED AIRSPEED VISUAL METEOROLOGICAL CONDITIONS

VTOCS

NEVER EXCEED SPEED TAKEOFF CLIMBOUT

VTOSS XFEED

SPEED TAKEOFF SAFETY SPEED CROSSFEED

VNE

ill/iv

FAA APPROVED

Section

BHT-212VFR-FM-1

1 TABLE OF CONTENTS

Subject

TRANSMISSION ............... ................................ TRANSMISSION OIL PRESSURE........................... TRANSMISSION OIL TEMPERATURE ......................

TRANSMISSIONTORQUE.................................. ROTOR ..........................................................

Page Number

Paragraph

-14........ 1-14-A...... 1-14-B.......

1-9 1-9 1-9

1-14-C.......

1-9

1-15 ........

1-9 Rev. 1

1-1

BHT-212VFR-FM-1

FAA APPROVED TABLE OF CONTENTS (Cont) Page Number

Subject

Paragraph

ROTOR RPM - POWER ON .................. ............. ROTOR RPM - POWER OFF ............................... HYDRAULIC ..................................................... HYDRAULIC PRESSURE ................................... HYDRAULIC TEMPERATURE .............................. FUEL AND OIL .................................................. FUEL ........................................................ OIL ENGINE AND COMBINING GEARBOX................ OIL TRANSMISSION, INTERMEDIATE AND TAIL ROTOR GEARBOXES ............................................... ROTOR BRAKE.................................................. LANDING GEAR ................................................. INSTRUMENT MARKINGS AND PLACARDS ................... HEATER .........................................................

1-15-A ....... 1-15-B ..... 1-16 ......... 1-16-A ....... 1-16-B ....... 1-17 ......... 1-17-A ....... 1-17-B .......

1-9 1-9 1-9 1-9 1-10 1-10 1-10 1-10

1-17-C ....... 1-18 ......... 1-19 ......... 1-20 ......... 1-21 .........

1-10 1-10 1-10 1-10 1-10

LIST OF FIGURES Figure Number

Title

Page 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 ............................................ Single engine height-velocity chart ............................

1-3........... 1-4..........

1-13 1-15

Instrument markings ............................................

1-2

Rev. 1

1-5...........

1-16

FAA APPROVED

BHT-212VFR-FM-1

Section 1 LIMITATIONS

1-1.

INTRODUCTION

1-4.

FLIGHT CREW

NOTE

NOTE

Compliance with limitations in this section is required by appropriate operating rules.

Minimum cockpit (FS 47.0) weight is 170 pounds (77.1 kilograms). Refer to Section 5.

Minimum and maximum limits, and normal and cautionary operating ranges for helicopter and subsystems are indicated by instrument markings and placards. Instrument markings and p laca rds represent ae rody namic calculations that are substantiated by flight test data.

Minimum flight crew consists of one pilot who shall operate helicopter from right crew seat.

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.

NOTE

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. 1-5-A.

1-2.

BASIS OF CERTIFICATION

This helicopter is certified under FAR Part 29, Category B.

CONFIGURATION REQUIRED EQUIPMENT

Heated pitot-static system Pilot windshield wiper Force trim system

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.

02 DEC 2002

Rev. 4

1-3

FAA APPROVED

BHT-212VFR-FM-1

Longitudinal CG limits are from station 144.0. 130.0 to Longitudinal

CG operational

range is

NOTE Station 0 (datum) is located 20 inches (508 millimeters) aft of most forward point of cabin nose.

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

and shall be computed from weight and balance data.

Rev. 2

1-4A/1-4B

FAA APPROVED

1-6-B-2.

BHT-212VFR-FM-1

LATERAL CENTER OF GRAVITY

1-9.

MANEUVERING

Lateral CG limits are 4.7 inches (119.4 millimeters) left and 6.5 inches (165.1 millimeters) right of fuselage centerline.

1-9-A.

1-7.

1-9-B.

AIRSPEED

7500 pounds (3402 kilograms) 130 KIAS.

GW -

VNE

11,200 pounds (5080.3 kilograms) GW VNE

PROHIBITED MANEUVERS

Aerobatic maneuvers are prohibited. CLIMB AND DESCENT

Refer to Section 4, PERFORMANCE.

1-10.

HEIGHT-VELOCITY

100 KIAS.

Doors open/off operation -

(any GW).

VNE100 KIAS

The height-velocity limitations are critical in the event of a single engine failure

during takeoff,

landing, and other

operation near the surface (figure 1-4). VNE decreases

linearly from 130 knots to 100 knots with GW (Refer to Placards And Decals, Figure 1-3).

The AVOID area of the Height-Velocity chart defines the combinations of airspeed and height above ground from which a

safe single engine landing on a smooth, decreases 3 knots per 1000 feet above 3000 feet H . VNE

Maximum airspeed when operating above maximum continuous torque (87.5%) is 80

KIAS.

level, firm surface cannot be assured.

The H-V chart is valid only when the Weight-Altitude-Temperature limitations/ are not exceeded (figure 1-1). The diagram

does not define the conditions

which

assure continued flight following an engine failure nor the conditions from which a safe power off landing can be

1-8. ALTITUDE

made.

Maximum Maximum operatingoperating - 20,000 20,000 feet feet Hp. Hp.

Refer to applicable operating rules for high altitude oxygen requirements. altitude requiremrnt. oxygen CAUTION

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

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

ENGINE

IN MANUAL

FUEL

Speed (VTOCS). Refer to Section 4 for

VTOCS'

CONTROL MODE.

Above 15,000 feet Hp, restart shall be accomplished in manual fuel control mode only. (No airspeed restrictions.) 15,000 feet Below

15,000 feet

Hp, restart

may be

attempted in either manual or automatic fuel control mode.

NOTE Downwind takeoffs are not recommended since published takeoff distance performance will not be achieved.

When near zero

wind conditions prevail, determine true direction of wind. 1-5

FAA APPROVED

BHT-212VFR-FM-1

1-11.

1-12-C. STARTER

AMBIENT TEMPERA-

TURES Maximum

Limit starter energizing time to:

sea level

ambient

air

temperature for operation is +52 °C (+125 °F) and decreases with altitude at standard

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

takeoff, landing and in ground effect maneuvers chart (figure 1-1).

30 seconds- ON. 60 seconds -

OFF.

30 seconds - ON. 5 minutes - OFF. 30 seconds - ON. 15 minutes -OFF. 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 N IN G

1-13.

POWER PLANT

BATTERY SHALL NOT BE USED FOR ENGINE START AFTER

PRATT AND WHITNEY CANADA PT6T3B and PT6T-3.

TEMP LIGHT (IF INSTALLED). BATTERY SHALL BE REMOVED AND SERVICED IN ACCORDANCE WITH MAN U FACTU RER

NOTE Operation in 2 1/2 minute or 30 minute OEI range is intended for

ILLUMINATION

OF BATTERY

INSTRUCTIONS PRIOR RETURNING BATTERY

TO TO

emergency use only, when one engine becomes inoperative due

SERVICE. Maximum battery case temperature °° (130 °F).

to actual malfunction. 54.5

Maximum battery internal temperature 62.7 °C (145 °F). 1-12-B.

1-13-A. 1-13-A-1.

GAS PRODUCER RPM TWIN ENGINE OPERATION

GENERATOR

Maximum -

150 amps per ammeter.

GAS PROD RPM (N1) - PT6T-3B (Gage P/N 212-075-037-101) Continuous operation

To attain published single engine

performance, generator loads should not exceed 75 amps each

during twin engine operation.

Ammeter needle may deflect full

scale momentarily during generator assisted start of second engine. 1-6

OEI ranges

shall not be used for training.

Rev. 1

61 to 100.8%

Maximum

continuous Maximum for

takeoff Maximum Transient

(not to exceed 30 seconds)

100.8% 100.8%

102.6%

FAA APPROVED

BHT-212VFR-FM-1

GAS PROD RPM (N|) - PT6T-3B (Gage P/N 212-075-037-113) Continuous

1-13-C. INTERTURBINE TEMPERATURE

operation

61 to 101.8%

Maximum continuous Maximum for

101.8%

PT6T-3B (TWIN ENGINE OPERATION) Continuous

101.8%

operation

300 to 765 °C

102.6%

765

Maximum continuous operation

continuous 5 Minute takeoff range Maximum Maximum for takeoff

Transient (not to exceed 10 seconds) 101.5%

(Not to exceed 5 seconds)

takeoff Maximum Transient (not to exceed 30 seconds)

GAS PROD RPM (N) -

PT6T-3

ONE ENGINE INOPERATIVE (OEI)

1-13-A-2.

765 to 810 °C 810 °C

Maximum transient

Maximum for starting (Not to exceed 2 seconds above 960 °C)

850 °C

1090 °C

GAS PRODUCER RPM (N|) PT6T-3B(Gage P/N 212-075-037101) 21/2 minute range Maximum

100.8 to 102.4% 102.4%

NOTE If ITT remains above 810 °C longer than 15 seconds or exceeds other

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

GAS PRODUCERRPM (N|) -

Refer to Pratt and Whitney

PT6T-3B (Gage P/N 212-075-037113)

Manual Maintenance inspection requirements.

21/2 minute range

101.8 to 103.4%

Maximum

103.4%

1-13-B.

POWER TURBINE

PT6T-3B (SINGLE ENGINE OPERATION)(OEI) RPM

(N 2 ) PT6T-3B Takeoff Minimum

for

and PT6T-3 100% 97%

30 Minute OEI range

765 to 822 °C

2/2 Minute OEI range Maximum OEI

822 to 850 °C 850 °C

Continuous 97 to 100% operation Maximum continuous 100% operation Transient (not to exceed 10 seconds) 101.5%

5 Minute range (twin engine operation) 30 Minute range (single engine operation)

765 to 810 °C 765 to 810 °C Rev.1

1-7

FAA APPROVED

BHT-212VFR-FM-1

PT6T-3

1-13-F.

ENGINE OIL PRESSURE

Maximum continuous

PT6T-3B or PT6T-3

limit (single or twin 765 °C engine operation) Power change transient limit (5 seconds above 810 °C not to exceed 850 850 °C °C)

Mnimum (Below 79% N,)

40 PSI

79 to 100% N Maximum

115 PSI

Starting transient limit (Not to exceed 2 seconds above 810 °C) 1090 C

1-13-G.

ENGINE OIL

TEMPERATURE ENGINE TORQUE

1-13-D.

NOTE

NOTE For normal twin engine operation, maximum permissible torque

Helicopters with PT6T-3B engine shall use only gages marked 0 115°C. Helicopters with PT6T-3

needle split is 4% total.

engine may use either gage.

ONE ENGINE INOPERATIVE (ENGINE SCALE) - PT6T-3 (AND PT6T-3B WITH TORQUEMETER MARKED FOR 71.8% MAX OEI) Maximum continuous 30 Minute power range

Maximum

63.9%

Continuous operation Maximum

0 to 115 °C 115 °C

63.9 to 71.8%

71.8%

ONE ENGINE

PT6T-3B or PT6T-3

INOPERATIVE

(ENGINE SCALE) - PT6T-3B WITH TORQUEMETER MARKED FOR 79.4% MAX OEI Maximum continuous 30 Minute power

63.9%

range

63.9 to 79.4%

Maximum

79.4%

PT6T-3 ONLY Minimum

5 °C

Maximum

107 °C

1-13-H. COMBINING GEARBOX OIL PRESSURE PT6T-3B or PT6T-3 Minimum for idle

40 PSI

Operation below 1-13-E.

FUEL PRESSURE

Minimum Continuous Maximum 1-8

Rev. 1

4 PSI 4 - 35 PSI 35 PSI

94% N

40 to 60 PSI

operation Maximum 80 %

60 to 80 PSI 80 PSI

2 Continuous

BHT-212VFR-FM-1

FAA APPROVED

1-16-B. HYDRAULIC TEMPERATURE Maximum

88 °C

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

1-17. FUEL AND OIL DOD-L-85734AS recommended.

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 DODL-8 573 4 m ay b e us ed at all am bie nt air 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.

1-10

Rev. 4

02 DEC 2002

or

MIL-L-23699

is

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 until engines 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.

FAA APPROVED

BHT-212VFR-FM-1

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

1-11

FAA APPROVED

BHT-212VFR-FM-1

11,000

10,000

130

132

134

13B

LONGITUDINAL

138 C.G. STATION

140

142

144

INCHES

212VFR-FM-1-2

Figure 1-2. Gross weight center of gravity chart

1-12

BHT-212VFR-FM-1

FAA APPROVED

(if installed)

(TYPICAL)

PANEL AFT END OF OVERHEAD CONSOLE

Figure Placards and decals PANEL AFT 1-3. END OF OVERHEAD CONSOLE Figure 1-3.

212VFR-FM-1-3-1 212VFR-FM-1-3-1

Placards and decals

Rev.1

1-131

BHT-212VFR-FM-1

FAA APPROVED

NOTES:

A

USEDWITH GASPRODUCER GAGEP/N 212-075-037-101

A2

USEDWITHGAS PRODUCER GAGEP/N 212-075-037-113 212VFR-FM-1-3-2

Figure 1-3.

1-14

Rev. 1

Placards and decals (Sheet 2 of 2)

BHT-212VFR-FM-1

FAA APPROVED

NOTE: THEHELICOPTERCONFIGURATION SHALLCOMPLYWITHTHEWEIGHTALTITUDE-TEMPERATURECHART DIAGRAM FORHEIGHT-VELOCITY TO BE VALID

400

350

IATL

3LIMIlT

1000 LBLESS THAN WATLIMIT

200

IN SHADEDAREAS

100

50

00

10

Figure 1-4.

40 30 20 INDICATEDAIRSPEED -

50 KNOTS

60

70

Single engine height-velocity chart

Rev. 1

1-15

FAA APPROVED

BHT-212VFR-FM-1

INSTRUMENT

MARKINGS - PT6T-3B GASPRODUCER RPM(N1,P/N212-075-037-101

BHT-212VFR-FM-1

FAA APPROVED

INSTRUMENT

MARKINGS

-

PT6T-3B

FAA APPROVED

INSTRUMENT

Figure

1-1B

Rev. 1

1-5.

MARKINGS

Instrument

markings

-

PT6T-3

(Sheet 3 of 6)

FAA APPROVED

BHT-212VFR-FM-1

INSTRUMENT

MARKINGS

INSTRUMENT

-

MARKINGS

PT6T-3

BHT-212VFR-FM-1

FAA APPROVED

INSTRUMENT

MARKINGS

BHT-212VFR-FM-1

FAA APPROVED

INSTRUMENT

MARKINGS

BHT-212VFR-FM-1

FAA APPROVED

Section 2 TABLE OF CONTENTS Paragraph

Subject INTRODUCTION ................................................. FLIGHT PLANNING .............................................. TAKEOFF AND LANDING .................................. WEIGHT AND BALANCE ................................... PREFLIGHT CHECK ............................................. BEFORE EXTERIOR CHECK ............................... EXTERIOR CHECK ......................................... INTERIOR AND PRESTART CHECK ............................ ENGINE START .................................................. ENGINE 1 START........................................... ENGINE 2 START ........................................... POST START ............................................... ENGINE FAILS TO START ................................. DRY MOTORING RUN ...................................... SYSTEMS CHECK ............................................... FORCE TRIM CHECK....................................... PRELIMINARY HYDRAULIC CHECK ....................... ENGINE FUEL CONTROL CHECK.......................... GOVERNOR CHECK .................................... FUEL CROSSFEED VALVE CHECK ........................ ELECTRICAL SYSTEMS CHECK ........................... CABIN HEATER CHECK ................................... HYDRAULIC SYSTEMS CHECK ............................

BEFORETAKEOFF.............................................. POWER ASSURANCE CHECK .............................

2-1 ........... 2-2........... 2-2-A ........ 2-2-B ........ 2-3........... 2-3-A ........ 2-3-B ........ 2-4........... 2-5........... 2-5-A ........ 2-5-B ........ 2-5-C ........ 2-5-D ....... 2-5-E ....... 2-6.......... 2-6-A ....... 2-6-B ....... 2-6-C ....... .... 2-6-D ....... 2-6-E ....... 2-6-F........ 2-6-G ........ 2-6-H .......

Page Number 2-3 2-3 2-3 2-3 2-3 2-3 2-4 2-6 2-7 2-8 2-9 2-9 2-10 2-10 2-10 2-10 2-10 2-11 2-11 2-11 2-12 2-12 2-13

2-7..........

2-14

2-7-A

2-14

.......

2-8..........

2-14

2-9 .......... 2-10 ......... .....2-11 ........ 2-12 .........

2-15 2-15 2-15 2-16

Title

Figure Number

Page Number

Exterior check diagram .........................................

2-1...........

TAKEOFF........................................................ INFLIGHT OPERATIONS ........................................ DESCENT AND LANDING ....................................... ENGINE SHUTDOWN ....................................... POSTFLIGHT CHECK ........................................... LIST OF FIGURES

Rev. 2

2-17

2-1/2-2

BHT-212VFR-FM-1

FAA APPROVED

Section 2 2-1. INTRODUCTION This section contains instructions and procedures for operataing helicopter from

planning stage, through actual flight conditions,

to securing helicopter after

landing.

Normal and standard conditions are assumed in these procedures. Pertinent

Consult applicable weight and balance instructions provided in Section 5. Determine weight of fuel, oil, load, etc., and anticipated landing compute GW,and takeoff check helicopter CG locations. Ensure weight and balance limitations Section 1 are not exceeded.

in

data in other sections is referenced when

2-3.

Instructions

whether helicopter is in condition for safe

applicable.

and procedures contained

herein are written

for purpose of

standardization and are not applicable to all situations.

PREFLIGHT CHECK

Pilot is responsible for determining flight 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

during flight. Information to be used can be compiled as follows:

as may be made check comprehensive as conditions

Check type of mission to be performed and destination.

All areas checked shall include a

will provide pilot with data to be used

Select appropriate performance charts to be used from Section 4. 2-2-A.

warrant.

visual check for evidence of when corrosion, particularly helicopter is flown near or over salt water or in areas of high industrial emissions.

TAKEOFF AND LANDING

Refer to Section 1 for takeoff and landing

weight limits and to Section 4 for takeoff and landing data.

2-2-B.

condition of helicopter. This

WEIGHT AND BALANCE

Determine proper weight and balance of helicopter as follows:

2-3-A.BEFORE EXTERIOR

CHECK

Flight planning - Completed. Publications

-

Check.

Ensure helicopter has been serviced as required. 2-3

BHT-212VFR-FM-1

2-3-B.

FAA APPROVED

EXTERIOR CHECK

ENGINE 1 BOOST PUMP and ENGINE 2 BOOST PUMP switches - ON.

switches -

Fuel filters (left and right) -

HAS BEEN

IF HELICOPTER

EXPOSED TO SNOW OR ICING CONDITIONS, SNOW AND ICE SHALL BE REMOVED PRIOR TO FLIGHT

Rotor

blade -

Cabin area -

Condition

and

Condition, all glass clean.

Pitot tube(s) -

Cover(s)

removed,

unobstructed.

Unobstructed.

Remote hydraulic filter bypass indicator Check green.

Cabin nose ventilators -

Unobstructed.

Nose compartment doors secured.

Condition and

Battery vent and drain tubes Unobstructed.

Stowed.

Antenna - Condition, security. Drain samples as follows:

ENGINE 1 BOOST PUMP and ENGINE 2 BOOST PUMP switches - OFF. ENGINE 1 FUEL and ENGINE 2 FUEL

switches -

OFF.

BATTERY BUS 1 switch -

ON.

Fuel sump drain buttons (left and right) - Press. Fuel filters day as follows: 2-4

Rev. 2

switches - OFF.

BATTERYBUS1 switch- OFF. 2. FUSELAGE-

CABIN LEFT SIDE

Copilot and passenger doors -

Condition and operation, glass clean.

Positionlights- Condition. Landing gear -

Condition, ground

handling wheels removed. Engine air intake unobstructed. 3. FUSELAGEDrain lines -

Drain before first flight of

Cover removed,

AFT LEFT SIDE Clean, unobstructed.

Engine compartment -

Searchlight and landing light -

Fuel sumps -

ENGINE 1 FUEL and ENGINE 2 FUEL

Security of emergency release handles.

Static ports (left and right) -

Drain

ENGINE 1 BOOST PUMP and ENGINE 2 BOOST PUMP switches - OFF.

1. -FRONT FUSELAGE

cleanliness.

ON.

Check.

Engine oil level - Verify presence of oil in sight gage and proper oil level. Engine governor spring -

Condition.

Engine fire extinguisher - Bottle pressure gage and temperature

Combining gearbox filter indicator retracted.

range.

Bypass

Access doors and engine cowling Secured.

BHT-212VFR-FM-1

FAA APPROVED

Engine exhaust ejector tubes -

Covers

4. FUSELAGE -

Tail rotor driveshaft covers - Secured.

Synchronized elevator -

Condition,

security.

Main rotor

blade -

Condition,

cleanliness. Remove tiedown.

free movement

Condition,

CABIN RIGHT SIDE

Engine air intake - Cover removed, unobstructed. Transmission oil - Verify presence of oil and proper level in sight gage

Pilot and passenger doors - Condition and operation, glass clean. Security of

emergencyreleasehandles. Position lights - Condition.

Tail rotor gearbox - Verify presence of oil and proper level in sight gage, filler cap and chip detector plug security, Tail rotor -

Check fuel quantity, secure

6. FUSELAGE -

AFT

Condition.

Tailboom -

Fuel filler cap.

removed, unobstructed.

Landing gear - Condition, handling wheels removed.

ground

7. CABIN TOP

on flapping axis. Intermediate

Tail skid -

Condition, security.

Synchronized security. Tailboom -

elevator -

Condition,

Condition.

Baggage compartment

Check smoke

AFT RIGHT SIDE

Engine fire extinguisher gearbox oil -

Verify

presence of oil and proper level in sight gage. Close access door. Engine compartment -

Engine oil level -

WHEN HELICOPTER HAS BEEN EXPOSED TO SNOW OR ICING CONDITIONS.

CONDITIONS. Main rotor and controls - Condition, fluid levels in all reservoirs. Secured.

Hydraulic oil reservoirs - Check sight glasses for proper fluid levels. Caps secured.

Antenna(s) -

Bottle

pressure gage and temperature range.

Combining

SNOW AND ICE SHALL BE REMOVED PRIOR TO FLIGHT

Transmission oil filler cap -

detector - Condition and security. Cargo and door secured. 5. FUSELAGE

CAUTION

Verify presence

gearbox -

of oil and proper level in sight gage, filler cap and chip detector plug security.

Condition and security.

Combining gearbox oil filler cap Secured.

Anticollision light -

Condition and

security.

Check.

CAUTION

Verify presence of oil

and proper level in sight gage.

IF ANY TEMP-PLATE IS MISSING

Access doors and engine cowling -

MAINTENANCE

Secured.

OR HAS

BLACK

DOTS,

PERSONNEL

SHALL ASSIST IN DETERMINING AIRWORTHINESS AS STATED IN BHT-212-MM. Rev. 2

2-5

BHT-212VFR-FM-1

FAA APPROVED

Main driveshaft

and coupling

Condition, security,

and grease leakage.

-

Lower pedestal circuit breakers -In.

Check Temp-Plates (four places each

Collective control head switches -

temperature indicated by dot changing color to black.

COMPASSCONTROL slaving switch(es) - MAG (slave position).

Engine air intakes - Unobstructed, particle separator doors closed.

Radio equipment -

coupling) for evidence of elevated

Engine and transmission cowling Secured.

Fresh air inlet screen -

Unobstructed.

2-4. INTERIOR AND PRESTART CHECK Cabin Interior equipment.

-

Fuel INTCON switch -

Normal.

ENGINE 1 BOOST PUMP and ENGINE 2 BOOST PUMP switches - OFF. Fuel XFEED switch -

NORM.

switches - OFF. switches

Cleanliness, security of

seats

OFF.

ENGINE 1 FUEL and ENGINE 2 FUEL

Portable fire extinguishers charge, secured. Passenger

OFF.

-

Secured,

OFF.

ENGINE NO. 1 PART SEP and ENGINE

NO. 2 PART SEP switches installed).

NORM (if

Proper

ENGINE NO. 1 GOV and ENGINE NO. 2 GOV switches - AUTO.

each

HYDR SYS NO. 1 and HYDR SYS NO. 2

occupied seat equipped with seat belt.

switches -

Crew and passenger doors - Secured.

STEP switch (if installed) - As desired.

Cargo load -

FORCE TRIM switch -

Secured.

Protective breathing equipment (if required) -

Condition

serviced.

ON.

and properly

Instruments -

ON, cover down.

Static check.

STATIC SOURCE switch (if installed) PRI.

Seat and pedals -

Adjust.

Seat belt and shoulder

Altimeter(s) - Set. harness -

Clock -

Set and running.

Fasten and adjust. FIRE EXT switch -

OFF.

Shoulder harness inertia reel and lock Check.

FIRE PULL handles -

Flight controls - Freedom of movement, OFF. position for start.

AFT LT rheostat AFT DOME DOME LT rheostat and and switch switch- -

Cyclic -

PITOT STATIC HEATERS switch -

Centered, friction

Collective -

as desired.

Full down.

Transmission chip detector indicators (if installed) - Check. 2-6

Rev. 2

In (forward).

OFF

FAA APPROVED

BHT-212VFR-FM-1

WIPERS switch — OFF.

CAUTION

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.

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.

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 (SN 30554 and subsequent).

NOTE Test all lights when night flights are planned or anticipated. Accomplish light tests with external power connected or during engine runup. MASTER CAUTION switch (overhead) — TES T, check a ll c autio n p anel lights 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).

INV 1 switch — ON, check no. 1 AC voltmeter fo 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 fo 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 open, then back against idle stop. 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

02 DEC 2002

Rev. 4

2-7

BHT-212VFR-FM-1

FAA APPROVED AMPS amps.

at or below

Check

1 -

150

GAS PROD RPM (N|) - Check 61 ± 1% when engine 2 throttle is on idle stop.

NOTE

CAUTION

During extremely cold ambient temperatures, idle rpm will be

ENGINE SECOND ENSURE IS AS THROTTLE ENGAGES A NON-ENGAGED INCREASED. ENGINE IS INDICATED BY 10 TO 15% HIGHER ENG RPM (N2 ) THAN ENGAGED ENGINE AND NEAR

high and ENGINE OIL, XMSN OIL, and GEAR BOX OIL pressures may exceed maximum limits for up to 2 minutes after starting. Do not increase

ROTOR above

80% RPM until

ZERO TORQUE.

XMSN OIL

temperature is above 15 °C. ENGINE OIL, XMSN OIL, AND GEAR BOX OIL pressures - Check. ENG 1 PART SEP OFF caution Extinguished.

light ( H A R D) S U D D E N IF ENGAGEMENT OCCURS, SHUT

Engine 1 throttle - Increase to 85% ENG RPM (N2). Friction as desired. 2-5-B.

IF A NON-

ENGAGEMENT OCCURS, CLOSE THROTTLE OF NON-ENGAGED ENGINE. WHEN NON-ENGAGED ENGINE HAS STOPPED, SHUT DOWN ENGAGED ENGINE.

ENGINE 2 START

ENGINE 2 BOOST PUMP switch - ON, check ENG 2 FUEL BOOST caution light

BOTH DOWN MAINTENANCE

ENGINES. ACTION IS

REQUIRED.

Engine 2 throttle - Increase slowly to 85% ENG RPM (N2). Monitor tachometer and torquemeter to verify engagement of second engine.

extinguished (FUEL XFEEDcaution light will illuminate momentarily and subsequent.) ENGINE 2 FUEL switch

-

SN 30597 ON. (ENG 2

FUEL VALVE caution light will Illuminate momentarily

Engine 2 ENGINE OIL pressure -

Check.

ENG 2 PART SEP OFF light

-

Extinguished.

SN 30597 and subsequent.)

2-5-C. Engine 2 FUEL PRESS -

POST START

Check.

START switch - ENG 2 position. Observe starter limitations. Engine 2 ENGINE OIL pressure Indicating.

-

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

ON (BATTERY BUS 1

will switch OFF automatically SN 30554 and subsequent).

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

Monitor. Observe ITT

Engine 2 ITT limitations. START switch

-

Off at 55% GAS PROD

IF OPERATING ON BATTERY BUS POSITION INV 3 SWITCH TO ON

2-9

BHT-212VFR-FM-1

FAA APPROVED

ONLY ONE BATTERY SWITCH

Throttle -

SHALL BE ON DURING FLIGHT (SN 30554 AND SUBSEQUENT).

Caution lights - Check all extinguished.

Fully closed.

ENGINE (1 or 2) BOOST PUMP switch ON. ENGINE (1 or 2) FUEL switch -

ON.

ENGINE OIL, XMSN OIL, and GEAR BOX

OIL temperatures Within limits.

and pressures

AMPS 1 and AMPS 2 -

-

ENG IGN SYScircuit breaker - Pull out. START switch - Engage for 15 seconds,

Within limits.

then disengage.

ENGINE (1 or 2) FUEL switch -

NOTE AMPS 2 will indicate a higher load than AMPS 1 until battery Is fully charged.

ENGINE (1 or 2) BOOST PUMP switch OFF. ENG IGN SYS circuit

Radios -

ON as required.

ELT (If Installed) inadvertent transmission.

Check

OFF.

for

breaker -

In.

Allow required cooling period for starter before proceeding. Follow normal start sequence as described on preceding pages. Refer to SECTION 1, STARTER

2-5-D. ENGINE FAILS TO START When engine fails to light off within 15

seconds after throttle has been opened

LIMITATIONS.

2-6. SYSTEMS CHECK

to idle, following action is recommended:

2-6-A.

IDLE STOP IDLE REL switch RELSTOP switch -- Actuate. Actuate. Throttle -

Fully closed.

FORCE TRIM CHECK

Flight controls lock removed.

Friction off; collective

START switch - OFF.

Cyclic and pedals - Move slightly each direction to check force gradients.

ENGINE (1 or 2) BOOST PUMP switch

Cyclic

FORCE TRIM release button

-

Press; check trim releases with button ENGINE (1 or 2) FUEL switch -

OFF.

pressed, reengages with button released.

After GAS PROD RPM (No) has decreased

FORCE TRIM switch -

another start. start. another

FORCE TRIM switch -

to zero, allow 30 seconds for fuel to drain from engine. Conduct a DRY MOTORING RUN before attempting

2-5-E.

DRY MOTORING RUN

Following procedure is used to clear an

2-6-B.

2-10

Rev. 2

ON.

PRELIMINARY HYDRAULIC

CHECK

engine whenever it is deemed necessary to

remove internally trapped fuel and vapor:

OFF; check trim

disengages and FT OFF caution light disengages

Throttles -

Set to idle.

BHT-212VFR-FM-1

FAA APPROVED

HYDR SYS NO. 1 switch ON.

OFF, then

HYDR SYS NO. 2 switch -

OFF, then

ON.

2-6-C.

FUEL CROSSFEED VALVE

2-6-E.

NOTE Uncommanded control movement or motoring with either hydraulic system off may Indicate hydraulic system malfunction.

ENGINE FUEL CONTROL

CHECK

CHECK 2-6-E-1.

SN PRIOR TO 30554

FUEL PUMP CROSSFEED switch NORMAL. Position ENGINE 1 BOOST PUMP switch to OFF. Note pressure

drop on No. 1 FUEL PRESS gage,

by a return to normal followed Indication, showing crossfeed valve has opened and check valve is functioning properly. 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 to decrease below 50%.

opened and check valve is functioning properly.

At approximately 8000 feet Hp, GAS PROD RPM (N,) may not change significantly when manual fuel control Is selected.

NOTE If in either of the above checks; fuel pressure is 4 to 6 psi below

GOV switch (ENGINE NO. 1 or 2) MANUAL, observe change in GAS PROD throttle Open respective RPM (N,). carefully to assure GAS PROD RPM (N|)

responds upward, then return throttle to idle. Return GOV switch to AUTO. Check for return to original GAS PROD

normal (10 ± 4 psi), appropriate

check valve Is not functioning properly. ENGINE 2 BOOST PUMP switch -

ON.

FUEL PUMP CROSSFEED switch 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

2-6-D.

GOVERNOR CHECK

2-6-E-2. No. 1 throttle - Full open. Check ENG RPM (N2) stabilizes at 95 ± 1%. No. 2 throttle - Full open. Check ENG RPM (N 2) increases 2% and both engines stabilize at 97 ± 1% .

to ON and FUEL PUMP

CROSSFEEDswitch to NORMAL. SN 30554 AND SUBSEQUENT FUEL XFEED test switch and hold.

TEST BUS 1

NOTE RPM INCR DECR switch -

(N2)

INCR to 100%

If, after turning either boost pump off, fuel pressure remains 4 to 6 psi below normal (10 ± 4 psi), appropriate check valve is not functioning properly. Rev. 1

2-11

BHT-212VFR-FM-1

FAA APPROVED

ENGINE 1 BOOST PUMP switch - OFF. Check no. 1 FUEL PRESS decreases,

then returns to normal. (This indicates that crossfeed valve has opened by bus

INV 3 switch (if installed) - OFF, then ON DC BUS 1, check INVERTER 3

caution light extinguishes.

no. 1 power and check valve is functioning properly.) ENGINE1 BOOST

INV 1 switch - OFF, INVERTER 1 caution light illuminates. check no. 1

FUEL XFEED test switch -

inverter no. 3 has assumed load (SN 30554 and sub). INV 1 switch - ON,

PUMPswitch- ON.

TEST BUS 2

and hold.

AC voltmeter for Indication that INVERTER

1 caution

extinguishes.

ENGINE 2 BOOST PUMP switch - OFF. Check no. 2 FUEL PRESS decreases,

then returns to normal. BOOST PUMP switch -

FUEL XFEED test switch FUEL XFEED switch -

NOTE

ENGINE 2

ON.

INV 3 Switch

NORM.

OVRD CLOSE.

2-6-G.

CABIN HEATER CHECK

GAS PROD (both engines).

ON.

2-6-F. ELECTRICAL SYSTEMS CHECK

SYSTEM SELECTOR SWITCH

Check 27 ± 1 vdc.

AC voltmeters -

Check 104 to 122 vac.

Check within limits. (SN

OR CABIN ILLUMINATES, CIRCUIT BREAKER TRIPS.

DO NOT OPERATE

INV 3 switch (if installed) - ON DC BUS 2, check INVERTER 3 caution

light light extinguishes. extinguishes.

AC voltmeter for indication that inverter no. 3 (if installed) has assumed load. INV 2 switch -

ON,

light

HTR

HEATER

ABOVE 21°C OAT.

SYSTEMSELECTORswitch -

INV 2 switch - OFF, INVERTER 2 caution light illuminates. Check no. 2

Rev. 2

SHALL BE TURNED OFF WHEN HEATED AIRFLOW DOES NOT SHUT OFF AFTER AIR COND TEMP CONT SWITCH IS TURNED TO FULLY COLD, HEATER AIR

LINE CAUTION LIGHT

AC system - Check as follows 30554 and subsequent):

2-12

Fully

CAUTION

DC voltmeters -

extinguishes.

Check 75%(Nl) minimum

AIR COND TEMP CONT switch COOL.

NORM.

INVERTER 2 caution

OFF, then

ON DC BUS 2.

ENGINE 1 (or ENGINE 2) BOOST PUMP

Ammeters -

be ON for

INV 3 switch (if installed) -

ENGINE 1 (or ENGINE 2) BOOST PUMP

FUEL XFEED switch -

must

avionics cooling fan to operate.

switch - OFF. Check fuel pressure drops to zero on selected system. switch -

light

VENT BLOWER switch -

ON.

HEATER.

FAA APPROVED

BHT-212VFR-FM-1

AIR COND TEMP CONT switch -

Rotate

illuminates

and HYDRAULIC caution

counterclockwise and observe heated

light illuminates.

airflow.

no. 1 pressure decreases..

DEFOG lever - ON; check airflow is diverted from pedestal outlets to windshield nozzles. Return lever to

Cyclic - Check normal operation by moving cyclic in an 'X' pattern, right forward to left aft, then left forward to

OFF.

Hydraulic system

right aft (approximately 1 inch). Center cyclic.

AFT OUTLET switch - ON; check airflow distributed equally between Return

pedestal outlets and aft outlets.

switch to OFF.

Collective -

NOTE

operation

affects

Boost for tail rotor controls is

Refer to Hover

performance.

slightly (1 to 2

inches). Return to down position.

NOTE

Heater

Check normal operation

by increasing collective

Ceiling and Rate of Climb charts for HEATER ON in Section 4.

SYSTEM SYSTEM SELECTOR SELECTOR (heater) (heater) switch switch VENT BLOWERswitch -

As desired.

furnished by hydraulic system no. 1 only. When hydraulic system no. 1 is being checked, tail rotor

controls will be unboosted.

Pedals - Displace slightly left and right. Note an increase in force required to move pedals.

2-6-H. HYDRAULIC SYSTEMS CHECK DO NOT TURN BOTH HYDRAULIC SYSTEMS OFF AT SAME TIME

NOTE

DUE TO EXCESSIVE

FORCE

This check is to determine proper

REQUIRED

FLIGHT

operation of hydraulic actuators for each flight control system. If

CONTROLS.

forces, unequal forces,

abnormal

control binding, or motoring is it may be an encountered, indication of a malfunction of a flight control actuator. FORCE TRIM switch -

Collective -

0

MASTER

-

OFF.

ght illuminates.

Cyclic - Check normal operation of cyclic controls by moving cyclic in an

Check as follows:

HYDR SYS NO. 1 switch

Check

SYS NO. 2 switch

illuminates and hydraulic system no. 2 pressure decreases. HYDRAULIC caution

Set to 100%.

Cyclic - Centered, friction removed. Hydraulic system -

ON. Check

MASTER CAUTION light extinguishes and hydraulic system no. 1 pressure returns to normal. HYDRAULIC caution light extinguishes.

Check MASTER CAUTION light

Down, friction removed.

ROTOR RPM (NR) -

HYDR SYS NO. 1 switch -

HYDR

OFF.

TO MOVE

-

CAUTION

OFF.

light Rev. 2

2-13

BHT-212VFR-FM-1

FAA APPROVED

then left forward to right aft

(approximately 1 inch). Center cyclic.

Radlo(s)- Checkoperationand set. Cyclic -

Friction as desired.

Collective - Check normal operation by increasing collective slightly (1 to 2 inches).

NOTE

Return to down position.

Pedals - Displace slightly left and right. Note no increase in force required to move pedals.

Moderate friction shall be applied to each throttle to overcome follow-through coupling between twist grips.

HYDR SYS NO. 2 switch - ON. Check MASTER CAUTION light extinguishes and hydraulic system no. 2 pressure

Throttles -

caution light extinguishes.

FORCETRIM switch -

returns to normal. Cyclic and collective desired. FORCE TRIM switch -

HYDRAULIC

friction

-

As

ON.

Full open, Adjust friction.

ENG RPM (N) -

100% (both engines).

As desired.

COCKPIT VOICE RECORDER TEST switch (If Installed) - Press and hold for

3 seconds. Verify meter indicates GOOD.

Passenger step switch (if installed) As desired. Passenger seat belts -

Fastened.

BOTH HYDRAULIC SYSTEMS SHALL BE OPERATIONAL PRIOR TO TAKEOFF.

All doors -

Secured.

Caution and warning lights Extinguished.

NOTE System 1 will normally operate 10 to 20 °C cooler than system 2.

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

Engine, transmission, gearbox, hydraulic, and electrical instruments -

Check readings within operational range.

2-7-A.

POWER ASSURANCE

CHECK

Perform power assurance check daily. Refer to Section 4.

2-8. TAKEOFF ENG RPM (N 2) -

Flight instruments -

100%.

Check operation

and set.

NOTE

No more than 15% torque above

Positionlights - As required.

hover power shall be used

Magnetic compass -

accelerating to Takeoff Climbout Speed.

Fluid level and

heading.

Anti-collision lights - As required. Pitot heater 2-14

Rev. 2

As required.

Collective - Initiate takeoff from a hover height of 4 feet.

FAA APPROVED

BHT-212VFR-FM-1

NOTE Takeoff must be executed in accordance with Height-Velocity limitations for type of operation

being conducted.

Refer to

Cyclic control and pedals and frictioned.

Centered

FORCETRIM switch - ON.

Throttles- Idle.

Section 1.

Refer to Section 4 for additional

ITT - Stabilize for one minute at idle prior to shut down

climb performance data.

Engine instruments - Within limits.

2-9. IN-FLIGHTOPERATIONS ENG RPM (N 2 ) - Adjust INCR DECR switch to select desired RPM between 97 and 100%. (100% is normal RPM). Airspeed - Within flight altitude.

for GW and

limits

Engine, gearbox, and transmission Instruments

-

Within limits.

NOTE

Refer to applicable operating rules for high altitude operations.

ELT (if installed)

-

Check for

inadvertent transmission. Radios OFF switch - ENG 1. IDLE STOP REL switch ENG 1. IDLE STOP REL Engine 1 throttle - Closed. Check ITT and GAS PROD RPM (N.) decreasing. BATTERY BUS 1 switch and subsequent).

ON (SN 30554

IDLE STOP REL switch -

ENG 2.

Engine 2 throttle -

Closed. Check ITT

and GAS PROD RPM (N1) decreasing.

2-10.

DESCENT AND

GEN 1 and 2 switches -

LANDING

All invertors - OFF.

Flight controls desired.

Throttles -

Adjust friction as

ENGINE 2 FUEL switch -

100%.

FORCE TRIM switch -

As desired.

Passenger STEP switch -

diagram from which a safe landing may not be made In case of single engine failure. For landing distance information

failure

during

approach, refer to Section 4..

2-11. ENGINE SHUTDOWN Collective - Down.

OFF. OFF.

OFF.

ENGINE 2 BOOST PUMP switch -

OFF.

As desired.

Avoid critical areas of HV

in event of engine

ENGINE 1 FUEL switch -

ENGINE 1 BOOST PUMP switch -

Full open.

ENG RPM (N) -

Flight path -

OFF.

CAUTION AVOID RAPID ENGAGEMENT OF ROTOR BRAKE IF HELICOPTER IS

ON ICE OR OTHER SLIPPERYOR LOOSE SURFACE TO PREVENT ROTATION OF HELICOPTER.

Rotor brake - Apply at or below 40% ROTOR RPM (NR), return to stowed position after main rotor stops. 2-15

BHT-212VFR-FM-1

Pilot -

FAA APPROVED

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 OFF.

Helicopter is parked within 150 feet of 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 Main rotor and tail rotor blades Tiedown when any of following conditions exist: Thunderstorms are forecast.

2-16

Rev. 2

exist in local area or

Protective

covers

(engine exhaust

pitot tube) - Install.

and

FAA APPROVED

BHT-212VFR-FM-1

212VFR-FM-2-1

Figure 2-1.

Exterior check diagram

2-17/2-18

FAA APPROVED

*

BHT-212VFR-FM-1

Section 3 TABLE OF CONTENTS Subject

Paragraph

Page Number

INTRODUCTION .................................................

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

3-3

DEFINITIONS....................................................

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

3-3

SINGLE ENGINE FAILURE ................................. ENGINE RESTART IN FLIGHT ............................. DUAL ENGINE FAILURE ................................... ENGINE UNDERSPEED ................................... ENGINE OVERSPEED - FUEL CONTROLGOVERNOR FAILURE .................................................... ENGINE OVERSPEED - DRIVESHAFT FAILURE .......... ENGINE COMPRESSOR STALL ............................ ENGINE HOT START/SHUTDOWN ............... ...... FIRE ............................................................. ENGINE FIRE .............................................. CABIN SMOKE OR FUMES.............................. BAGGAGE COMPARTMENT FIRE.......................... TAIL ROTOR................................... COMPLETE LOSS OF TAIL ROTOR THRUST ............. LOSS OF TAIL ROTOR THRUST AT HOVER .............. LOSS OF TAIL ROTOR THRUST IN CLIMB.............. LOSS OF TAIL ROTOR THRUST IN LEVEL FLIGHT OR DESCENT ................................................... LOSS OF TAIL ROTOR COMPONENTS .................... TAIL ROTOR FIXED PITCH FAILURES .................... FIXED PITCH FAILURE AT A HOVER...................... FIXED PITCH FAILURE IN FLIGHT ......................... LOSS OF PITCH CHANGE CONTROL LINKAGE .......... HYDRAULIC SYSTEM ........................................... ELECTRICAL SYSTEM .......................................... DC FAILURE TO PRODUCE POWER...................... AC FAILURE TO PRODUCE POWER.............3......... FUEL SYSTEM...................................... FUEL BOOST PUMP FAILURE ............................. FUEL FILTER PARTIALLY BLOCKED..................... FUEL QUANTITY INDICATION MALFUNCTIONS .......... AUTOMATIC FLIGHT CONTROLS SYSTEM .................... COMMUNICATION SYSTEM ..................................... NAVIGATION RADIO FAILURE ............................. INTERCOM FAILURE ....................................... CABIN HEATER .................................................

3-3-A 3-3-B 3-3-C 3-3-D

3-3 3-4 3-5 3-6

ENGINE ..........................................................

3-3.........3-3 ........ ........ ........ ........

3-3-E ....... 3-3-F ........ 3-3-G ....... 3-3-H ....... 3-4 .......... 3-4-A ....... ... 3-4-B ..... 3-4-C ....... 3-5 .......... 3-5-A ....... 3-5-B ....... 3-5-C ....... 3-5-D ....... 3-5-E ........ 3-5-F......... 3-5-G ........ 3-5-H ........ 3-5-J......... 3-6........... 3-7........... 3-7-A ........ 3-7.... 3-8 ........... 3-8-A ........ 3-8-B ........ 3-8-C ........ 3-9........... 3-10 ......... 3-10-A ....... 3-10-B ..... 3-11 .........

3-7 3-8 3-9 3-9 3-9 3-9 3-11 3-11 3-11 3-11 3-11 3-11 3-12 3-12 3-12 3-13 3-13 3-14 3-14 3-14 3-14 3-14 3-14 3-14 3-15 3-15 3-15 3-15 3-15 3-15 3-15 3-1

BHT-212VFR-FM-1

FAA APPROVED TABLE OF CONTENTS (Cont)

Subject

Paragraph

Page Number

LANDING GEAR ................................................. STATIC PORT OBSTRUCTION ..................................

3-12 ......... 3-13 .........

3-16 3-16

LIST OF TABLES Title

Table Number

WARNING LIGHTS .............................................. CAUTION LIGHTS ...............................................

3-1 ........... 3-2...........

3-2

Page Number 3-17 3-19

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 lfu n c tio n h a s b e e n d e te rm in 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 low i n g t e r m s a re u s e d t o d e s c ri 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. 3-3-A.

ENGINE SINGLE ENGINE FAILURE

ENG RPM (N2) 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, N2 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 shall be made in log book. Refer to 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.

02 DEC 2002

Rev. 4

3-3

BHT-212VFR-FM-1

FAA APPROVED

GAS PROD RPM (NI) below 61 ± 1% and decreasing. ENG RPM (N2) below 85% and decreasing.

Land as soon as practical. If no. 2 engine failed:

ITT below 400 °C and decreasing.

INV 3 to DC BUS 1 (if installed).

ENG 1 or ENG 2 OIL PRESSURE, DC GENERATOR, and PART SEP OFF caution lights illuminated.

BATTERY BUS 2 switch — OFF. BATTERY BUS 1 switch — ON. MASTER CAUTION light — Reset.

PROCEDURES:

Land as soon as practical. WARNING

DO NOT ALLOW ROTOR RPM (NR) TO DECAY BELOW MINIMUM LIMITS.

CAUTION DURING COLD WEATHER 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 (NR) within limits and power within OEI limits. NOTE Airspeed — 55 to 65 KIAS for Minimum Power for level flight. RPM INCR DECR switch — INCR, set remaining ENG RPM (N2) at 100% if possible.

3-3-B. ENGINE RESTART IN FLIGHT Conditions which would warrant an attempt to restar t an engine would probably be a f la m e o u t , c a u s e d by a m a l f u n c ti 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 ENGINE IN MANUAL FUEL 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.

Throttle — Closed.

BATTERY BUS 2 switch — OFF.

Fuel Crossfeed switch — Override Close.

BATTERY BUS 1 switch — ON.

Fuel Interconnect switch — OPEN.

INV 1 and INV 2 switches — ON.

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

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

Verify FUEL BOOST caution light and FUEL switch to be turned off are all for affected engine.

START switch — ENG 1.

ENGINE (1 or 2) FUEL switch — OFF. GEN (1 or 2) switch — OFF. MASTER CAUTION light — Reset.

3-4

Rev. 4

02 DEC 2002

A f te r 1 2 % G A S P RO D R P M (N I ) is attained and oil pressure is indicating, slowly open throttle until a rise is seen in ITT which indicates engine is selfs u 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) and

BHT-212VFR-FM-1

FAA APPROVED ITT are stabilized.

Continue to open

throttle slowly to complete start. Center START switch after 55% GAS Adjust PROD RPM (N1) is attained. engine to desired power level. Care

3-3-C. DUAL ENGINE FAILURE INDICATIONS: ENG 1 OUT and ENG 2 OUT warning

must be taken to make small

lights illuminated.

compressor stall may result.

RPMcaution light illuminated.

GEN 1 switch -

ROTOR RPM audio on.

adjustments with throttle as ON.

BATTERY BUS 1 switch -

OFF.

BATTERY BUS 2 switch -

ON.

GAS PROD RPM (N1) below 61 ± 1% RPM

and decreasing (both engines).

Engine 2 throttle -

engines).

ENGINE 2 BOOST PUMP switch -

ON.

(both

PRESSURE, DC

GENERATOR, and PART SEP OFF caution lights Illuminated.

Normal.

ENGINE 2 FUEL switch -

ENGINE

85% and

ITT below 400 °C and decreasing

Closed.

Fuel Crossfeed switch -

(N 2 ) below

ENG RPM

decreasing (both engines).

ENGINE RESTART (NO. 2):

ON.

PROCEDURES:

NO. 2 GOV switch

-

MANUAL. BATTERY BUS 1 switch -

OFF. DECAY BELOW MINIMUM LIMITS.

INV 1 and 2 switches - ON. INV 3 switch BUS 2.

(if equipped)

START switch After

-

ON DC

ENG 2.

12% GAS PROD RPM (N,) is

attained and oil pressure is Indicating, slowly open throttle until a rise is seen In ITT which indicates engine is self sustaining. Do not open throttle farther until GAS PROD RPM (N1) and ITT are stabilized. Continue to open

throttle

)

slowly to complete start.

Center START switch after 55% GAS Adjust PROD RPM (N1) is attained. engine to desired power level. Care

Collective - Reduce, establish autorotative glide. Minimum rate of

descent (65 KIAS) or maximum glide (90 KIAS).

Autorotative landing -

If time permits before landing and a restart will not be attempted, proceed as follows: Throttles -

Closed.

ENGINE1 and ENGINE 2 FUEL switches -

OFF.

ENGINE 1 and ENGINE 2 BOOST PUMP

must be taken to make small

switches-OFF.

compressor stall may result.

After landing:

adjustments with throttle as GEN 2 switch -

ON.

Accomplish.

Engine shutdown -

Complete. Rev. 2

3-5

BHT-212VFR-FM-1

Helicopter -

FAA APPROVED

Exit.

Low GAS PROD RPM (N), ITT, and TORQUE on affected engine.

3-3-D.

ENGINE UNDERSPEED

PROCEDURES:

NOTE Normal deviations

WARNING

of ROTOR RPM

(NR) from the governed setting may occur when large collective

ROTOR

changes are made but should not

EXCESSIVELY

failure, unless a large steady-state TORQUE split occurs.

ACTION

RPM

CAN

DECAY

IF CORRECTIVE

IS NOT IMMEDIATELY

INITIATED.

If there is a low power demand (less than single engine power available) at time of low side failure, ROTOR RPM (NR) and ENG RPM (N2 ) of affected engine will decrease and stabilize, at or slightly below governed value. TORQUE, ITT, and GAS PROD RPM

Collective - Adjust as necessary maintain ROTOR RPM (NR).

(N) of affected engine will also decrease.

Affected engine -

As ROTOR RPM (NR) decreases,

to

Airspeed - 55 to 65 KIAS for Minimum Power for level flight.

Identify.

normal

engine will increase TORQUE output to assume load. If power demand is near zero, there might not be a significant TORQUE split.

Throttle friction - Tighten on normal engine, reduce on affected engine. Throttle (affected engine) -

If there is a high power demand (greater

idle.

than single engine power available) at time of low side failure, ROTOR RPM (NR) will

GOV switch

decrease along with ENG RPM (N 2 ), TORQUE, ITT, and GAS PROD RPM (N) of affected engine. As ROTOR RPM (N)

(affected

Reduce to engine)

-

MANUAL.

decreases, normal engine will increase to maximum power to assume load, causing significant increases in TORQUE, ITT, and GAS PROD RPM (N) while ENG RPM (N2 ) will remain below governed value.

INDICATIONS:

CAUTION WHEN OPERATING IN MANUAL FUEL CONTROL MODE, MAKE

SLOW, SMOOTH THROTTLE

MOVEMENTS

TO AVOID STALL,

Low ENG RPM (N) and ROTOR RPM (NR)

COMPRESSOR

(possibly with RPM caution light and audio if power demand is in excess of single engine power available).

OVERTEMPERATURE, OVERSPEED, AND POSSIBLE DRIVETRAINDAMAGE.

TORQUE split (proportional demand).

COORDINATE THROTTLE AND COLLECTIVE CHANGES TO

to power

AVOID OVERLOADING ENGINE.

NORMAL

Throttle (affected engine) - Increase slowly. Adjust throttle and collective as required to maintain TORQUEof affected 3-6

Rev. 2

FAA APPROVED

BHT-212VFR-FM-1

engine slightly below TORQUEof normal engine.

value as normal engine adjusts power output to share load.

MASTER CAUTION light -

Reset.

Land as soon as practical.

INDICATIONS: High ENG RPM (N2 ) and ROTOR RPM

(NR) possibly with RPMcaution light.

3-3-E. ENGINE OVERSPEED FUEL CONTROL/GOVERNOR FAILURE NOTE Normal deviations of ROTORRPM (NR) from the governed setting may occur when large collective changes are made but should not

be confused with fuel control

Definite TORQUE split (proportional power demand).

to

High GAS PROD RPM (N.), ITT, and TORQUE on affected engine. Return of ENG RPM (N 2 ) and ROTOR

RPM (NR) to governed value (if power demand is very high). PROCEDURES:

failure, unless a large steady-state TORQUEsplit occurs. If there is a low power demand (less than single engine power available) at time of high side failure, ROTOR RPM (NR) and ENG RPM (N 2) of affected engine will

increase considerably value.

above governed

ROTOR RPM CAN OVERSPEED EXCESSIVELY IF CORRECTIVE ACTION IS NOT IMMEDIATELY

INITIATED.

TORQUE, ITT, and GAS PROD RPM

(N,) of affected engine will also increase. As ENG RPM (N2 ) and ROTOR RPM (NR)

increase above governed value, normal engine will reduce power to keep itself from overspeeding and will indicate significantly lower TORQUE, ITT, and GAS PROD RPM (N,) than affected engine.

maintain ROTOR RPM (N).

Affected engine Throttle

Identify.

(affected engine) -

If there is a high power demand (greater than single engine power available) at time of high side failure, ROTOR RPM (NR) and ENG RPM (N 2 ) (of affected engine will

TORQUE of normal engine.

and GAS PROD RPM (N|). As ENG RPM (N 2 ) and ROTOR RPM (NR) increase,

Throttle (affected engine) idle.

surge initially along with TORQUE, ITT, normal engine will reduce power to keep itself from overspeeding. Affected engine then tries to assume all of load, which is

Reduce to

maintain TORQUE at or slightly below

Throtte friction -Tighten on normal engine, reduce on afected engine.

GOV switch

(affected

Reduce to

engine)

-

MANUAL.

beyond its capability due to high power demand. ENG RPM (N2 ) of affected engine and ROTOR RPM (NR) will then decrease and rejoin ENG RPM (N2 ) of normal engine, stabilizing at or slightly above governed

CAUTION

................ WHEN OPERATING IN MANUAL FUEL CONTROL MODE, MAKE

SLOW, SMOOTH THROTTLE

MOVEMENTS TO AVOID Rev. 2

3-7

FAA APPROVED

BHT-212VFR-FM-1 COMPRESSOR OVERTEMPERATURE,

STALL, OVER-

SPEED, AND POSSIBLE DRIVETRAINDAMAGE. COORDINATE THROTTLE AND

COLLECTIVE CHANGES TO AVOID

OVERLOADING

NORMAL

IN COMPLETE LOSS OF POWER TO MAIN ROTOR. ALTHOUGH

COCKPIT INDICATIONS FOR A DRIVESHAFT FAILURE ARE SOMEWHAT COMPARABLE TO A

DUAL ENGINE FAILURE, IT IS

AUTOROTATIVE

FLIGHT

PROCEDURES BE ESTABLISHED

Throttle (affected engine) slowly.

Increase

Adjust throttle and collective, as

IMMEDIATELY.

FAILURE TO

REACT IMMEDIATELY

TO LOW

required, to maintain TORQUE of affected engine slightly below TORQUE

ROTOR RPM AUDIO SIGNAL, CAUTION LIGHT, AND

of normal engine.

TACHOMETER

MASTER CAUTION light -

Reset.

LOSS OF CONTROL. This Is a situation

NOTE

If values of the overspeed

parameters are unknown or if NR exceeds 110%, or if engine torque exceeds 104%, land as soon as possible.

WILL RESULT IN involving

a break In

drive system, such as a severed main

driveshaft to transmission. A failure of this type In powered flight will result in nose of helicopter swinging to left (rightt side slip) and usually a roll of fuselage. Nose down attitude may also be present.

Severity of Initial reaction will be affected

Land as soon as practical. * ENGINE OVERSPEED ACTUATOR FAILURE

by airspeed, HD, GW, CG, and power being GOVERNOR

used. INDICATIONS:

INDICATIONS: ENG (N 2 ) RPM and ROTOR RPM (NR) increase to approximately 101%. RPM INCR DECR switch Inoperative. PROCEDURES:

Left yaw. Rapid decrease in ROTOR RPM (NR). Rapid increase in ENG RPM (N 2 ).

If this failure occurs during takeoff or landing, no immediate corrective action

Illumination of ROTOR RPM caution light with audio.

maneuver.

Possible increase in noise due to:

is necessary to complete either

As soon as practical, roll back both throttles to maintain 97 to 100% ENG RPM (N2 ). Further adjustments of collective and throttles simultaneously will allow full power at pilot discretion.

Overspeeding engine turbines. Overspeeding combining gearbox. Driveshaft breakage.

Land as soon as practical.

3-3-F. ENGINE OVERSPEED DRIVESHAFT FAILURE WARNING FAILURE OF MAIN DRIVESHAFT TO TRANSMISSION WILL RESULT 3-8

Rev. 2

Collective -

As required to establish

autorotative descent. Airspeed -

Establish for minimum rate

of descent (90 KIAS).

(65 KIAS) or maximum glide

Throttles -

Close, if time permits.

BHT-212VFR-FM-1

FAA APPROVED

3-4-A-2. ENGINE FIRE DURING TAKEOFF OR APPROACH INDICATIONS:

Shut down affected engine (1 or 2) as follows: FIRE PULL handle — Pull. FIRE EXT switch — Main.

FIRE 1 PULL and/or FIRE 2 PULL handle illuminated.

Throttle — Closed. Fuel Crossfeed switch — Override Close.

PROCEDURES: Fuel interconnect switch — OPEN. If a landing site is available, begin descent and approach. If landing sight is not available , continue takeoff/approach. Proceed as follows:

Engine BOOST PUMP — OFF.

Airspeed — 45 KIAS minimum.

Verify FIRE handle light, FUEL BOOST caution light, and FUEL switch to be turned off are all for affected engine.

Collective — Reduce, if possible.

ENGINE FUEL switch — OFF.

Appropriate FIRE PULL handle — Pull. FIRE EXT switch — MAIN. If FIRE warning light remains illuminated for more than 10 seconds: FIRE EXT switch — RESERVE. ENG RPM (N2) (remaining engine) — Set at 100%.

If FIRE warning light remains illuminated: FIRE EXT switch — RESERVE. ENG RPM (N2) (remaining engine) — Set at 100%. Land as soon as possible. If a landing site is not readily available, proceed as follows:

Land as soon as possible.

FIRE PULL handle — In.

Engine shutdown — Complete.

GEN (1 or 2) switch — OFF.

Helicopter — Exit. If no. 2 engine was shut down:

3-4-A-3. ENGINE FIRE IN FLIGHT INDICATIONS:

BATTERY BUS 2 switch — OFF.

FIRE 1 and/or FIRE 2 PULL handle illuminated.

Immediately initiate emergency descent, if possible.

Rev. 4

BATTERY BUS 1 switch — ON. After landing:

PROCEDURES:

3-10

INV 3 to DC BUS 1 (if installed).

02 DEC 2002

Engine shutdown — Complete. Helicopter — Exit.

FAA APPROVED

3-4-B.

BHT-212VFR-FM-1

CABIN SMOKE OR FUMES

INDICATIONS:

emergency

procedure.

Following

is a discussion of some types of tail rotor malfunctions and their probable effects.

Smoke, toxic fumes, etc. in cabin.

3-5-A. COMPLETE LOSS OF TAIL ROTOR THRUST

PROCEDURES: VENT BLOWER switch -

ON.

Vents and accessible windows -

Open.

If additional ventilation is required: Airspeed -

Reduce to 60 KIAS or less.

Passenger doors, windows, vents Open.

INDICATION:

This is a situation involving a break in

drive system,

such as a severed

driveshaft, wherein tail rotor stops turning and delivers no thrust. A failure of this type in powered flight will result in nose of helicopter swinging to right (left side slip) and usually a roll of fuselage. Nose down attitude may also be present. Severity of

If time and altitude permit and source is suspected to be electrical: Affected system -

Attempt to identify

initial reaction will be affected by airspeed, HD,GW, CG, and power being used.

3-5-B. LOSSOF TAIL ROTOR

and isolate.

THRUST AT HOVER

Land as soon as possible.

PROCEDURES:

3-4-C.

BAGGAGE COMPARTMENT

BAGGAGE COMPANY

FIRE INDICATIONS:

hovering autorotation landing. be expected on touchdown.

3-5-C.

BAGGAGE FIRE warning illuminated.

light

Yawing can

LOSS OF TAIL ROTOR

THRUSTIN CLIMB

Degree of right yaw upon failure will be

PROCEDURES:

greater than that expected

Reduce power to minimum required. Land as soon as possible.

Inspect tailboom area for damage.

3-5.

Close throttles immediately and make a

.TAILROTOR

TAIL ROTOR

NOTE The key to successful handling of a tail rotor emergency lies in pilot ability to quickly recognize type of malfunction and to select proper

due to higher settings.

in level flight

power and antitorque

PROCEDURES:

Close throttles and lower collective immediately. Establish a glide speed

slightly above normal autorotation approach speed.

If a turn is required to reach a more desirable place to land or to align into wind, make it to right if possible. A turn to right can be more nearly streamlined by use of a little power. Rev. 2

3-11

FAA APPROVED

BHT-212VFR-FM-1 Once aligned for landing, yaw can be controlled in following manner:

USE OF COLLECTIVE MAY CAUSE NOSE TO YAW LEFT. DO NOT

pulse of up collective will produce

CORRECT WITH THROTTLE. ALTHOUGH APPLICATION OF IN THROTTLE WILL RESULT OF YAWING TO RIGHT, ADDITION POWER IS A VERY STRONG

bearings, creating a left moment. The greater the input of pulse, the

TOO SENSITIVE FOR PILOT TO DO NOT MANAGE PROPERLY.

Right Yaw If nose yaws right with power off, a

more friction

In mast thrust

more the response will be.

RESPONSEMEASUREAND IS ADD POWER AT THIS TIME.

YAWING UPON

SLIGHT

TOUCHDOWN AT ZERO GROUND SPEED MAY BE EXPECTED. DO NOT ALLOW ROTOR RPM TO DECAY BELOW MINIMUM LIMITS.

Moving collective upward abruptly increases rotor loading. Do not

hold collective up as rotor rpm will decrease lower than desirable. It is

DESCENT PROCEDURES:

essential that collective be returned to down position for autorotation. This cycle is one pulse. Pulse

Close throttles and reduce collective immediately. Attain an airspeed slightly above normal autorotative glide speed.

should be rapid (up and down) but should not be used at low altitudes.

If altitude permits with AIRSPEED above 60 KIAS, throttle and collective may be

Left Yaw If nose yaws left with power off, a

slight addition of power should arrest it. Further increase in power results in more right yaw increase.

gently applied to determine if some

degree of powered flight can be resumed.

If unacceptable

yawing

is

experienced, re-enter autorotation and continue descent to a landing.

Landing technique is same as

prescribed for climb condition above.

Landing During final stages of approach, a mild flare should be executed and

3-5-E. LOSS OF TAIL ROTOR

Maintain helicopter in a slight flare

Loss of any tail rotor component will result

execute a soft, slightly nose high landing. Landing on aft portion of skids will tend to correct side drift. If helicopter starts to turn, move cyclic as necessary to follow turn

additional nose down pitching, this situation would be quite similar to complete loss of tail rotor thrust as discussed above.

all power to rotor should be off.

and use collective smoothly to

COMPONENTS

in a forward CG shift.

Other than

stop. This technique will, in most cases, result in a run on type

until helicopter comes to a complete

3-5-F. TAIL ROTOR FIXED PITCH FAILURES

landing.

INDICATIONS:

CAUTION FOR ZERO GROUND SPEED LANDING, FLARE AND ABRUPT 3-12

3-5-D. LOSS OF TAIL ROTOR THRUST IN LEVEL FLIGHT OR

Rev. 2

Tail rotor pitch change control failures are either by a lack of characterized directional response when a pedal is pushed or by locked pedals. if pedals can not be moved with a moderate amount of force, do not attempt to apply a maximum

FAA APPROVED

BHT-212VFR-FM-1

effort since a more serious malfunction could result. FIXED PITCH FAILURE AT A

3-5-G.

AIRSPEED of 60 KIAS during initial part of approach.

HOVER

area can be made, start a slow deceleration to arrive at intended landing point with AIRSPEED at about

PROCEDURES:

25 KIAS.

Do not close throttles unless a severe right yaw occurs. If pedals lock in any position at a hover, landing from a hover can be accomplished with greater safety under power controlled flight rather than

At 2 to 5 feet AGL, slowly reduce throttle to overcome yaw effect and When allow helicopter to settle. aligned with landing area, allow helicopter to touch down.

autorotation.

After ground contact, use collective and throttle as necessary to maintain alignment with landing strip, and to

by closing throttles and entering 3-5-H. FIXED PITCH FAILURE IN

minimize forward speed.

If helicopter

FLIGHT

starts to turn, move cyclic

If tail rotor fixed pitch failure occurs during climb (left pedal applied), cruise

helicopter comes to a complete stop.

as

necessary to follow turn until

(approximately neutral pedals), and descent (right pedal applied), a descent

and landing can be effected safely by use of power and throttle changes.

PROCEDURES: If helicopter is In a trimmed condition when malfunction is discovered, engine power and airspeed

should be noted and

helicopter flown to a suitable landing area. Combinations of ENG TORQUE, ROTOR RPM (NR), and AIRSPEED will correct or aggravate yaw attitude and these should be adjusted as required to control yaw during landing. Right Pedal Locked Forward of

Neutral

Left Pedal Locked Forward of

Neutral

Reduce power and maintain ENG RPM

(N2) within green arc. Normal turns can be safely made under these conditions, although helicopter nose may be displaced to left. On final

approach,

begin

a slow

deceleration so as to arrive at a point about four to five feet above intended touchdown area as effective translational lift is lost. Apply collective to stop rate of descent and forward speed, and to align helicopter with intended landing path. Allow helicopter to touch down

at near zero ground speed, maintaining alignment with throttle.

Power should be reduced and ENG RPM (N2 ) maintained within green arc.

Pedals Locked in Neutral

This will help streamline helicopter in flight.

Right turns are easier than left

turns. AIRSPEED should maintained at or above 60 KIAS. Execute a adjusting minimize Maintain

be

normal to steep approach power as necessary to or prevent right yaw. ENG RPM (N2 ) and an

Reduce power and maintain ENG RPM

(N2) within green arc. Normal turns can be safely made under these conditions. Execute a normal to shallow approach, holding AIRSPEED at 60 KIAS during initial part of approach. Adjust power Rev. 2

3-13

FAA APPROVED

BHT-212VFR-FM-1

as necessary to minimize or prevent right yaw. At 50 to 75 feet AGL and when landing area can be made, start a deceleration

to arrive at intended landing point with

turned off, tail rotor control forces will increase but no change In limitations result.

3-7.

SYSTEM

ELECTRICAL

AIRSPEED at 25 KIAS. At 2 to 5 feet AGL, use throttle

slowly

3-7-A.

DC FAILURE TO PRODUCE

as necessary to maintain alignment with landing area and to control yaw; do not allow helicopter to settle until

POWER

down.

generator switch to RESET, then ON.

alignment is assured, then touch

If either generator has not failed but circuit

is open, reset generator by moving

After ground contact, use collective

For single

and throttle

as necessary to minimize

nonessential

alignment.

Move cyclic as necessary

NORMAL to MANUAL.

forward speed and to maintain to follow turn until helicopter come to a complete stop.

has

moving NON ESS BUS switch from Monitor to ensure

loads are within limits.

If any Inverter fails to produce power,

INDICATIONS:

check appropriate AC circuit breakers in.

In this type of failure, pitch change is broken at some point

tail rotor will

and

assume a blade angle

determined

by aerodynamic

counterbalance

forces.

and

3-8.

FUEL SYSTEM

3-8-A. FUEL BOOST PUMP

PROCEDURES:

FAILURE

Corrective action procedures are

INDICATION:

described

operation,

3-7-B. AC - FAILURE TO PRODUCE POWER

3-5-J. LOSS OF PITCH CHANGE CONTROL LINKAGE

mechanism

generator

busses may be restored by

in FIXED PITCH FAILURES

above. Specific procedure to be used

NO. 1 or NO2

FUEL BOOST aution

Light illuminates.

depends on yaw change experienced.

PROCEDURE:

3-6.

HYDRAULIC

The helicopter

SYSTEM

has two hydraulic powered

CAUTION

flight control systems (1 and 2). Both.... systems supply power to collective and cyclic

but tail rotor

is powered

only

by

.. IF EITHER BOOST PUMP FAILS,

system 1.

FUEL EXHAUSTION

If system pressure or temperature exceeds

INDICATED ON FUEL QUANTITY

OCCUR

limits, affected system should be turned

off.

Continued

maneuvers

remaining practical. 3-14

can

flight

and normal

GAGE.

on

If practical, descend below 5000 feet Hp

system. Land as soon as If system no. 1 fails and is

to prevent possible fuel starvation in the event remaining boost pump fails.

Rev. 2

be accomplished

COULD

AT 60 POUNDS

BHT-212VFR-FM-1

FAA APPROVED Fuel interconnect

switch -

OPEN.

3-10. COMMUNICATION SYSTEM

NOTE

NAVIGATION RADIO

If fuel crossfeed switch is in NORM position, crossfeed valve

3-10-A.

allowing remaining pump to supply fuel to both engines.

NAV AC switch -

will be automatically opened

FAILURE

3-10-B.

Land as soon as practical.

BUS NO. 2.

INTERCOM FAILURE

INDICATION:

3-8-B. FUEL FILTER PARTIALLY BLOCKED

Weak or no reception in headsets. PROCEDURE:

Land as soon as practical.

Check headset connection.

3-8-C. FUELQUANTITY

Verify

INDICATION MALFUNCTIONS

properly.

volume and ICS controls

set

Cycle ICS circuit breaker out and in. INDICATION: Fuel quantity

indication

freezes in place.

3-11.

CABIN HEATER

(Possible power failure to the fuel quantity indicator system.)

NOTE

A malfunction in the bleed air heater controls may or may not

PROCEDURE: FUEL QTY circuit breaker Fuel interconnect

switch -

Recycle. OPEN.

cause heater to become inoperative. INDICATION:

HEATER AIR LINE caution NOTE

A failure in the fuel quantity indicating system will have no effect on fuel low caution light, fuel interconect, fuel crossfeed,

fuel boost, or fuel valve and indications.

light

illuminates.

Heated airflow does not shut off when thermostat knob is turned to full cold position.

PROCEDURE: HEATERswitch - OFF immediately.

3-9. AUTOMATIC FLIGHT CONTROLS

SYSTEM

Not applicable to VFR helicopter. Rev. 2

3-15

BHT-212VFR-FM-1 CABIN HTR circuit out, do not reset.

FAA APPROVED breaker -

Check; If

If this occurs, proceed as follows: Windows and vents -

Check prior to next flight.

3-12. LANDING GEAR Not applicable to skid gear helicopters.

3-13. STATIC PORT PORT 3-13. STATIC OBSTRUCTION Erratic readings from airspeed indicator, vertical speed indicator, and altimeter may occur when operating in rain with STATIC SOURCE switch (If installed) in PRI.

3-16

Close.

Heater SYSTEM SELECTOR switch (if installed) - OFF. STATIC SOURCE switch (if installed) ALTN.

NOTE

This procedure

selects

an

alternate static source (cabin air) for pilot instruments only.

FAA APPROVED

BHT-212VFR-FM-1

Table 3-1. PANEL WORDING

WARNING LIGHTS

FAULT CONDITION

FIRE 1 PULL/ FIRE 2 Fire PULL

in engine

CORRECTIVE ACTION

com-

partment.

Pull FIRE PULL handle, position FIRE EXT switch

to MAIN, close

throttle, position FIRE EXT switch to RESERVE, if necessary. Land as soon as possible. ENG 1 OUT/ENG OUT

2

Engine GAS PROD RPM (Ni) below 53 ± 2%.

Check engine torque, GAS PROD (N.) RPM, ENG (N2 ) RPM, and ITT. Adjust power and airspeed. Reset remaining ENG (N2 ) RPM to 100% if

possible. Close throttle of affected engine. Refer to ENGINE FAILURE and ENGINE RESTART. Land as soon as practical. BAGGAGE FIRE

Smoke in compartment.

XMSN OIL PRESS

Transmission

baggage

Reduce power to minimum required. Land as soon as possible. Inspect tailboom area for damage.

oil pressure

below limit, XMSN OIL TEMP

Reduce power.

Land as soon as

possible.

T ra n s m i s s io n

oil

temperature above limit.

Reduce power.

temperature.

Check XMSN OIL

If not within limits,

land as soon as possible. C BOX OIL PRESS

Combining

gearbox

oil

pressure below limit, C BOX OIL TEMP

Combining

Reduce power.

Land as soon as

possible.

gearbox

oil

temperature above limit.

Reduce power.

temperature.

Check GEAR BOX

If not within limits,

land as soon as possible. BATTERY

installed)

TEMP (If

Battery temperature

limit.

above

Position BATTERY switches to OFF.

Land as soon as practical.

If

BATTERY caution segment does not illumninate, turn GEN 2 OFF. Land as soon as possible.

3-17

BHT-212VFR-FM-1

FAA APPROVED Table 3-1.

WARNING LIGHTS (Cont)

PANEL WORDING

FAULT CONDITION

CORRECTIVE

BATTERY

ACTION

SHALL

FOR ENGINE

NOT BE USED

START

AFTER

ILLUMINATION OF BATTERY TEMP

LIGHT. BATTERY SHALL BE REMOVED AND SERVICED IN WITH MANUACCORDANCE FACTURER'S INSTRUCTIONS PRIOR TO RETURN TO SERVICE. R OT OR installed)

3-18

B K (i f

Rotor brake retracted.

linings

not

Check rotor brake handle in detent. If light remains illuminated, land as soon as possible.

FAA APPROVED

BHT-212VFR-FM-1

Table 3-2.

CAUTION

LIGHTS

PANEL WORDING

FAULT CONDITION

CORRECTIVE ACTION

ENG 1 OIL SURE

PRES-

Engine oil pressure limit.

below

Shut down no. 1 engine. SN 30554 and sub.,- Position INV 3 switch to ON DC BUS 2.

ENG 2 OIL

PRES-

Engine

below

Shut down no. 2 engine. SN 30554

SURE

oil pressure

limit.

and sub. -, Position INV 3 switch to ON DC BUS 1 and BATTERY BUS 2 switch to OFF. Position BATTERY BUS 1 switch to ON.

ENG

1 DC

GEN-

ERATOR

Failure of DC generator.

Position

GEN 1 switch

to RESET

then ON. Position to OFF if reset not possible. SN 30554 and sub.position INV 3 switch to ON DC BUS 2.

ENG

2

DC

GEN-

Failureof

ERATOR

DC generator.

Position

GEN 2 switch

to RESET

then ON. Position to OFF if reset not possible.

SN 30554 and subsequentPosition INV 3 switch to ON DC BUS 1 and BATTERY BUS 2 switch to OFF. Position BATTERY BUS 1

switch to ON. ENG 1 PART

OFF/ENG

SEP

2 PART

SEP OFF

Separator

closed. protection Inoperative.

bypass

door

Ice and dust system

Check RPM WARN and PART SEP

circuit breakers in.

Position PART

SEP switch to OVRD ON. If PART SEP OFF light remains Illuminated,

correct malfunction prior to next flight. ENG 1 FUEL BOOST/ ENG 2 FUEL BOOST

Applicable pump pressure is low or pump has failed.

If practical, descend to 5000 feet Hp or below for remainder of flight due

to possible fuel starvation of engine if remaining boost pump fails. If

either fuel boost pump fails,

crossfeed valve is opened by a flow switch, allowing remaining pump to furnish pressure to both engine fuel systems. Above sequence Is possible with

fuel pump crossfeed switch In normal position.

3-19

FAA APPROVED

BHT-212VFR-FM-1

Table 3-2.

CAUTION LIGHTS (Cont)

PANEL CORRECTIVE

FAULT CONDITION

WORDING

ACTION

If this automatic function is not desired, fuel pump crossfeed switch should be positioned to override

close position and interconnect switch to open. and/or

heater

is

Correct

Land as soon as practical.

ENG 1 FUEL FILTER/

Filter

ENG 2 FUEL FILTER

partially clogged.

malfunction prior to next flight

ENG 1 FUEL LOW/ ENG 2 FUEL LOW

Fuel remaining is approximately 140 pounds.

Fuel interconnect switch in normal separates two (closed) position

lower fuel cells. When either FUEL LOW light illuminates, interconnect

switch should be positioned to

OPEN. This will allow fuel quantity in lower tanks to equalize. In event a fuel boost failure has

occurred, or occurs after

interconnect switch is positioned to OPEN, fuel in lower tanks will be available to both engines, through either boost pump. 1 G O V E N G MANUAL/ENG 2 GOV MANUAL

GOV switch in MANUAL.

ENG 1 CHIP/ENG 2 Metal particles oil. CHIP

in engine

ENG RPM, TORQUE, and ITT must manually by throttle be controlled and collective.

Reduce power and shut down engine as soon as practical to preclude

engine damage.

Land as

soon as practical. ENG 1 FUEL VALVE/ ENG 2 FUEL VALVE

Fuel valve not properly breaker seated or circuit

Check FUEL VALVE circuit breakers in. Land as soon as practical. If on

(SN

open.

ground, position FUEL switch to

30597

and

OFF then ON.

subsequent) ENG 1 GEN OVHT/

Generator overheating.

(SN 30597

Position

GEN

switch

to

OFF.

Correct malfunction prior to next

ENG 2 GEN OVHT

flight.

and

subsequent) Caution panel inoperative.

CAUTION PANEL

(SN

30597

MASTER CAUTION

circuit

Monitor instruments.

Land as soon as practical.

subsequent) INVERTER #1

Check

breaker in.

and Failure of no. 1 inverter.

SN 30504 through 30553 - Check INV 1 PWR and INV 1 CONT circuit

breakers in. Position INV 1 switch to OFF.

3-20

Rev. 2

BHT-212VFR-FM-1

FAA APPROVED

Table 3-2. CAUTION LIGHTS (Cont) PANEL WORDING

FAULT CONDITION

CORRECTIVE ACTION SN 30554 and subsequent - Check no. 1 AC voltmeter to determine that

no. 3 inverter has automatically assumed no. 1 inverter load. INVERTER #2

Failure of no. 2 inverter.

SN prior

to 30554 - Check

INV 2

PWR and INV 2 CONT circuit breakers in. to OFF.

Position INV 2 switch

SN 30554 and subsequent - Check no. 2 AC voltmeter to determine that

no. 3 inverter has automatically assumed no. 2 inverter load. INVERTER #3

(SN 30554

and

Failure of no. 3 inverter.

Position

position INV 3 switch to OFF.

subsequent)

EXTERNALPOWER

External power connected to helicopter or external

power door not closed properly.

DOORLOCK

INV 3 switch to other DC

BUS. If light stays illuminated,

Cabin

aft

door(s)

or

Disconnect external power if still applied, close and latch external

powerdoor.

Check doors closed and latched.

baggage compartment door not locked. BATTERY

Battery relay open or both

Position both BATTERY switches to

battery switches in same OFF. Position BATTERY switch to ON DC BUS 1. If light does not position. extinguish, position switch to OFF, and position other switch to ON DC BUS 2. If light does not extinguish,

position switch to OFF. CHIP C BOX CHIP XMSN

Metal

particles

in com-

practical.

Metal

Reduce power.

particles

in trans-

(SN 30504 through

Metal

Land as soon as Land as soon as

practical.

mission oil. ° CHIP 42 BOX

Reduce power.

bining gearbox oil.

in

Land as soon as practical.

in tail rotor

Land as soon as practical.

particles

intermediate gearbox oil.

30596) CHIP 90° BOX

Metal particles

(SN 30504 through

gearbox.

30596)

3-21

BHT-212VFR-FM-1

FAA APPROVED

Table 3-2. CAUTION LIGHTS (Cont) PANEL WORDING

FAULT CONDITION

CORRECTIVE ACTION

CHIP 42°/90 BOX

Metal

Land as soon as practical

subsequent)

gearbox.

°

(SN 30597

and

HYDRAULIC

(SN

30554

particles

in inter-

mediate and/or tail rotor Hydraulic

pressure

low or

a n d temperature above limit,

high, turn affected system off. Land as soon as practical.

FUEL XFEED

30597

If

pressure is low or temperature is

subsequent)

(SN

Verify fault from gage readings.

Fuel crossfeed

and

valve

not

Check FUEL XFEED circuit breakers

fully open or closed, or in. Cycle FUEL XFEEDswitch.

subsequent)

FUEL XFEED circuit breaker open.

HEATER AIR LINE

Heater

mixing

valve

Turn heater off immediately.

malfunction. RPM

ROTOR (NR) RPM above or below operating limits.

Adjust collective and/or RPM INCR DECR switch as required.

FDR SYS FAIL (if installed)

Flight data inoperative.

Refer to applicable regulations for operation with flight data recorder inoperative.

3-22

recorder

FAA APPROVED

BHT-212VFR-FM-1

Section 4 TABLE OF CONTENTS Subject

Paragraph

Page Number

INTRODUCTION .................. ......................... POWER ASSURANCE CHECK .................................. POWER ASSURANCE CHECKS PT6T3B .................. POWER ASSURANCE CHECK PT6T3 .....................

4-1 ........... 4-2........... 4-2-A ........ 4-2-B ........

4-3 4-3 4-3 4-3

DENSITYALTITUDE.............................................

4-3...........

4-3

HEIGHT VELOCITY ENVELOPE ................................ HOVER CEILING ................................................ TAKEOFF DISTANCE ........................................... CLIMB AND DESCENT .......................................... TWIN ENGINE TAKEOFF CLIMBOUT SPEED.............. TWIN ENGINE RATE OF CLIMB............................ SINGLE ENGINE RATE OF CLIMB PT6T3B ............... SINGLE ENGINE RATE OF CLIMB PT6T3 ................

4-4........... 4-5........... 4-6........... 4-7........... 4-7-A ........ 4-7-B ........ 4-7-C ........ 4-7-D ........

4-4 4-4 4-4 4-4 4-4 4-4 4-4 4-4

AIRSPEEDCALIBRATION.......................................

4-8...........

4-4

LANDING DISTANCE ............................................ SINGLE ENGINE LANDING DISTANCE OVER A 50 FOOT (15.2 METER) OBSTACLE ..................................

4-9...........

4-5

.............................................................. NOISE LEVELS .................................................. SAMPLE PERFORMANCE PROBLEM........................... SOLUTION ......................................................

4-9-A ........

4-5

4-9-B ........

4-5

4-10 ......... 4-11 ......... 4-12 .........

4-5 4-5 4-5

LIST OF FIGURES Title

Figure Number

Power assurance check chart - PT6T-3B ...................... Power assurance check chart - PT6T-3 ........................ Density altitude chart ...........................................

4-1 .......... 4-2........... 4-3 ..........

Hover ceiling in ground effect .................................

4-4...........

Page Number 4-7 4-11 4-12

4-13

Hover ceiling out of ground effect .............................

4-5...........

4-16

Critical relative wind azimuths for hover flight ................

4-6 ..........

4-24

Takeoff distance over a 50 foot (15.2 meter) obstacle ........

4-7...........

4-25

4-8...........

4-26

4-9........... 4-10 ........ 4-11 ........

4-27 4-57 4-67

4-12 ......... 4-13 .........

4-77 4-78

Twin engine takeoff climbout speed ...........................

Twin engine rate of climb ............................. ......... Single engine rate of climb - PT6T-3B ......................... Single engine rate of climb - PT6T-3 ...........................

Pilot airspeed system calibration .............................. Copilot airspeed system calibration ...........................

4-1

BHT-212VFR-FM-1

FAA APPROVED LIST OF FIGURES (Cont)

Title

Figure Number

Page Number

Single engine landing distance over a 50 foot (15.2 meter)

obstacle .........................................................

4-2

4-14 .........

4-79

FAA APPROVED

BHT-212VFR-FM-1

Section 4 4-1.

INTRODUCTION

Performance data presented herein are derived from engine manufacturer's specification power for engine less installation losses. These data are applicable to basic helicopter without any optional equipment that would appreciably affect lift, drag, or power available.

4-2-B. POWER ASSURANCE CHECK- PT6T-3 Power assurance check chart (figure 4-2) is provided to determine if engines can produce installed specification power. A power assurance check should be performed daily. Additional checks should be made if unusual operating conditions or

4-2.

POWER

indications arise.

ASSURANCE

CHECK

If either

4-2-A. POWER ASSURANCE CHECKS - PT6T-3B Power assurance check charts (figure 4-1) are provided to determine if engines can produce installed specification

.

Ground check is

performed prior to takeoff.

power.

engine does not meet

requirements of ground power assurance check, published performance may not be achievable. Cause of engine power loss, or excessive ITT or GAS PROD RPM (N), should be determined as soon as practical.

4-3.

DENSITY ALTITUDE

A power assurance check should be performed daily. Additional checks should be made if unusual operating conditions or arise. Hover check is indications

A Density Altitude Chart (figure 4-3) is provided to aid in calculation of performance and limitations. Density altitude is an expression of the density of

monitoring of engine performance. Either

the density

performed prior to takeoff and in-flight check is provided for periodic in-flight

power assurance check may be selected at

discretion of pilot. It is pilot responsibility to accomplish procedure safely, considering passenger load, terrain being overflown, and qualifications of persons on board to assist in watching for other air traffic and to record power check data.

If either engine does not meet requirements

of hover or in-flight

power

assurance check, published performance may not be achievable. Cause of engine power loss, or excessive ITT or GAS PROD RPM (N) should be determined as soon as

the air in terms of height above sea level; hence, the less dense the air, the higher conditions

altitude.

For standard

of temperature

and pressure,

density altitude is the same as pressure altitude. As temperature increases above standard for any altitude, the density altitude will also increase to values higher than pressure altitude. The chart expresses density altitude as a function of pressure altitude and temperature. The chart also includes the inverse of the

square root of the density ratio (1/),

practical. 4-3

BHT-212VFR-FM-1

FAA APPROVED

which is used to calculate KTAS by the relation: KTAS = KCAS x 1/o

4-7.

CLIMB AND DESCENT

4-7-A.

EXAMPLE If ambient temperature

is -15 °C and the

TWIN ENGINE TAKEOFF

CLIMBOUT SPEED

pressure altitude is 6000 feet, find the density altitude, 1/,

100 KCAS.

and true airspeed for

Twin engine takeoff climbout speed (VTOcs)

is that indicated airspeed which will allow takeoff distance over a 50 foot (15.2 meter)

SOLUTION

obstacle to be realized and will comply with HV restrictions to allow a safe landing

Enter the bottom of the chart at -15 °C.

in case of an engine failure (figure 4-8.)

Move vertically to the 6000 foot pressure altitude line.

4-7-B. TWINENGINERATEOF

From this point, move horizontally to the left and read a density altitude of 4000 feet

and move horizontally to the right and read 1/o = 100 x 1.06 = 106 KTAS.

CLIMB Twin engine rate of climb charts are provided for takeoff power and maximum

continuous power for GW ranging from 7000 to 11,200 pounds (figure 4-9).

4-4. HEIGHT - VELOCITY ENVELOPE

4-7-C. SINGLE ENGINE RATE OF CLIMB - PT6T-3B

Refer to SECTION 1.

Single engine rate of climb charts are

4-5.

HOVER CEILING

provided for 2/2 minute OEI power and 30

minute OEI power for GW ranging from

IGE and OGE hover ceiling charts (figures 4-4 and 4-5) present hover performance as allowable GW for conditions of Hp and OAT. Published

IGE hover performance

7000 to 11200 pounds (figure 4-10)

4-7-D. SINGLE ENGINE RATE OF CLIMB - PT6T-3

can be

achieved with adequate tail rotor control margins in relative winds up to 20 knots from any direction. More favorable tail rotor control margins will be realized when winds are outside critical relative wind

Single engine rate of climb charts are provided for 30 minute power and maximum continuous power for GW ranging from 7000to 11,200 pounds (figure 4-11).

azimuth area (figure 4-6).

Downwind takeoffs and landings are not recommended.

4-6.

TAKEOFF DISTANCE

Takeoff distance required to clear a 50 foot (15.2 meter) obstacle is presented in figure 4-7 as a function of OAT, Hp, and GW. 4-4

4-8. AIRSPEED CALIBRATION

Indicated airspeed (IAS) corrected for

position and instrument error equals calibrated airspeed (CAS). corrected 4-13.

Determine

airspeed from figures 4-12 and

W

FAA APPROVED

4-9.

BHT-212VFR-FM-1

ground effect maneuvers chart (Section 1),

LANDING DISTANCE

maximum allowable GW for existing ambient conditions are as follows:

4-9-A.

SINGLE ENGINE LANDING DISTANCE OVER A 50 FOOT (15.2 METER) OBSTACLE Single engine landing distance

over a 50

foot (15.2 meter) obstacle is shown in figure 4-14 as a function of OAT, Hp, and GW.

Maximum takeoff GWallowable at airport A (5676 feet HD) Maximum allowable landing GW at airport B

11,000 pounds 9250 pounds

(10,861feet HD) Estimated fuel burnoff during flight (30 minutes at 545 pounds per hour)

272 pounds

4-9-B.

4-10.

NOISE LEVELS

4-11.

SAMPLE

If pilot takes off at 11,000 pounds, he will arrive at destination 10,728 pounds (11,000

PERFORMANCE

PROBLEM Helicopter is chartered to transport cargo from airport A (elevation 3000 feet, temperature 30 °C) to airport B (elevation 8500 feet, temperature 19 °C). Duration of flight will be 30 minutes and a 30 minute

- 272 pounds). This exceeds maximum allowable landing weight by 1478 pounds (10,728 pounds - 9250 pounds); therefore, maximum allowable payload must be based on allowable landing weight for this particular flight. Maximum allowable landing GW GW at landing: Empty weight

fuel reserve at cruise power is required. Average fuel consumption

is determined

6482 pounds (5942

pounds) Oil

from helicopter historical records to be 545 pounds per hour at 8000 feet Hp, 20 °C OAT, and cruise power (approximately 55% torque). Crew consists of one 190 pound pilot. Determine maximum allowable cargo payload for flight.

9250 pounds

( 22

pounds) Pilot Fuel (600 - 272) Maximum allowable cargo payload

(190 pounds) ( 328 pounds) 2768 pounds

4-12. SOLUTION Fuel required for 30 minute flight

plus 30

minute reserve is 545 pounds. Considering fuel needed for start, runup, taxi, and takeoff, pilot elects to refuel to

Although it is permissible to take off from airport A at 11,000 pounds GW, upon

landing at airport B helicopter would have exceeded allowable landing GW by 1478 pounds due to higher HDat destination.

600 pounds.

According to Weight-altitude-temperature

limitations for takeoff, landing, and in

4-5/4-6

FAA APPROVED

BHT-212VFR-FM-1

PT6T-3B POWERASSURANCE CHECK(HOVER) (WITHGAS PRODUCERGAGEP/N212-075-037-101) HEATER/ECU - OFF. THROTTLES: TEST ENGINE - FULL OPEN, FRICTIONED. OTHER ENGINE - IDLE. ENG RPM (N2) - 97%. COLLECTIVE - INCREASE UNTIL LIGHT ON SKIDS OR HOVERING. DO NOT EXCEED 810 ITT OR 100.8% GAS PROD (N1) RPM.

STABILIZE POWER ONE MINUTE, THEN RECORD Hp, OAT, ENGINE TORQUE, ITT, AND GAS PROD (N 1) RPM.

IF INDICATED ITT OR GAS PROD (N1) RPM EXCEEDS MAXIMUM ALLOWABLE, REPEAT CHECK, STABILIZINGPOWER FOUR MINUTES.

ENTER CHART AT INDICATED ENGINE TORQUE, MOVE UP TO INTERSECT Hp, PROCEED TO RIGHT TO INTERSECT OAT, THEN MOVE UP TO READ VALUES FOR MAXIMUM ALLOWABLE ITT AND GAS PROD (N1) RPM.

REPEATCHECK USING OTHER ENGINE.

MAXIMUM ALLOWABLE ITT -

500

N I N-s-s^^

550

600

650

°C

700

IF EITHER ENGINE EXCEEDS ALLOWABLE ITT OR GAS PROD (N1) RPM AFTER STABILIZING FOUR MINUTES, PUBLISHED PERFORMANCE MAY NOT BE ACHIEVABLE. CAUSE SHOULD BE DETERMINED AND CORRECTED AS SOON AS PRACTICAL.

MAXIMUM ALLOWABLE GAS PROD (N1) RPM - PERCENT

750

800

85

90

95

100

105

.^-^j~si:^-^

ENGINE TORQUE - PERCENT (INDICATED) 212VFR-FM-4-1-1

Figure 4-1. Power assurance

check chart - PT6T-3B (Sheet 1 of 4)

Rev. 1

4-7

BHT-212VFR-FM-1

FAA APPROVED

PT6T-3B POWERASSURANCECHECK(IN-FUGHT) (WITHGASPRODUCERGAGEP/N 212-075-037-101) ESTABLISH LEVELFLIGHTABOVE1000FEET AGL.

ENGRPM(N2)- 97%.

AIRSPEED- 100 KIAS(OR VNE,IF LESS). HEATER/ECU - OFF.

STABILIZEPOWERONE MINUTEIN LEVELFLIGHT, THENRECORDHp, OAT,ENGINETORQUE,ITT,AND GASPROD(N1)RPM.

THROTTLES: TESTENGINE- FULLOPEN,FRICTIONED. OTHER ENGINE - DECREASESLOWLYUNTIL TEST ENGINE TORQUE IS WITHIN TEST RANGE. DO NOT EXCEED810°C ITTOR 100.8%GASPROD(N1)RPM.

ENTER CHART AT INDICATEDENGINE TORQUE, MOVEUPTOINTERSECTHp PROCEEDTORIGHTTO INTERSECTOAT,THENMOVEUPTO READVALUES FORMAXIMUMALLOWABLEITTANDGASPROD(N1) RPM.

550

600

40 50 60 70 80 ENGINE TORQUE - PERCENT (INDICATED)

650

700

750

800

MAXIMUM FORTAKEOFF

4-8

REPEATCHECKUSINGOTHERENGINE. IF EITHERENGINEEXCEEDSALLOWABLEITTOR GAS PROD(N1) RPM AFTERSTABILIZINGFOUR MINUTES, PUBLISHED PERFORMANCE MAYNOTBE ACHIEVABLE. CAUSESHOULDBEDETERMINED ANDCORRECTED AS SOONAS PRACTICAL.

MAXIMUM ALLOWABLE GAS PROD (N1) RPM - PERCENT

MAXIMUM ALLOWABLE ITT - °C

500

IF INDICATED ITTOR GASPROD(N1) RPMEXCEEDS MAXIMUMALLOWABLE,REPEATCHECK,STABILIZING POWERFOURMINUTES.

Rev. 1

85

90

95

100

MAXIMUMCONTINUOUS

105

FAA APPROVED

BHT-212VFR-FM-1

PT6T-3B POWERASSURANCE CHECK(HOVER) (WITHGAS PRODUCERGAGEP/N212-075-037-113) HEATER/ECU - OFF. THROTTLES: TEST ENGINE - FULL OPEN, FRICTIONED. OTHER ENGINE - IDLE. ENG RPM (N2)-

97%.

COLLECTIVE - INCREASE UNTIL LIGHT ON SKIDS OR HOVERING. DO NOT EXCEED 810 ° ITT OR 101.8% GAS PROD (N1) RPM.

STABILIZE POWER ONE MINUTE, THEN RECORD Hp, OAT, ENGINE TORQUE, ITT, AND GAS PROD (N 1) RPM.

IF INDICATED ITT OR GAS PROD (N1) RPM EXCEEDS MAXIMUM ALLOWABLE, REPEAT CHECK, STABILIZING POWER FOUR MINUTES.

ENTER CHART AT INDICATED ENGINE TORQUE, MOVE UP TO INTERSECT Hp, PROCEED TO RIGHTTO INTERSECT OAT, THEN MOVE UPTO READ VALUES FOR MAXIMUM ALLOWABLE ITT AND GAS PROD (N1) RPM.

REPEATCHECK USING OTHER ENGINE.

MAXIMUM ALLOWABLE ITT -

40

50

ENGINE TORQUE -

500

550

600

60

70

80

650

700

C

IF EITHER ENGINE EXCEEDS ALLOWABLE ITT OR GAS PROD (N1) RPM AFTER STABILIZING FOUR MINUTES, PUBLISHED PERFORMANCE MAY NOT BE ACHIEVABLE. CAUSE SHOULD BE DETERMINED AND CORRECTED AS SOON AS PRACTICAL.

MAXIMUM ALLOWABLE GAS PROD (N 1) RPM - PERCENT

750

800

MAXIMUM FORTAKEOFF

86

91

96

101

106

MAXIMUM CONTINUOUS

PERCENT (INDICATED) 212VFR-FM4-1-3

Figure 4-1.

Power assurance check chart - PT6T-3B (Sheet 3 of 4)

Rev. 1

4-9

BHT-212VFR-FM-1

FAA APPROVED

PT6T-3B POWERASSURANCECHECK(IN-FLIGHT) (WITHGASPRODUCERGAGEP/N 212-075-037-113) ESTABLISH LEVELFLIGHTABOVE1000FEET AGL. KIAS (ORVNE,IF LESS). AIRSPEED- 100AIRSPEED-100 KIAS(OR VNE,IF LESS). HEATER/ECU- OFF.

ENGRPM(N2) - 97%.

THROTTLES: TEST ENGINE- FULLOPEN,FRICTIONED.

ENTER.CHART AT INDICATEDENGINE TORQUE, MOVEUPTOINTERSECTH ,PROCEEDTORIGHTTO INTERSECT OAT,THENMOVEUP TO READVALUES FORMAXIMUMALLOWABLEITTANDGASPROD(N1) RPM.

STABILIZEPOWERONE MINUTE IN LEVEL FLIGHT, THENRECORDH OAT,ENGINETORQUE,ITT,AND GASPROD(N1)RPM.

OTHER ENGINE - DECREASESLOWLY UNTIL TEST ENGINE TORQUE IS WITHIN TEST RANGE. DO NOT EXCEED810-C ITTOR 101.8%GASPROD(N1) RPM.

MAXIMUM ALLOWABLE ITT -

500 PENS

BI

_

I

550

600

650

C

700

IF INDICATED ITTOR GASPROD(N1) RPMEXCEEDS MAXIMUMALLOWABLE,REPEATCHECK,STABILIZING POWERFOURMINUTES. REPEATCHECKUSINGOTHERENGINE. IF EITHERENGINEEXCEEDSALLOWABLEITTOR GAS PROD(NI) RPM AFTER STABILIZINGFOUR MINUTES, PUBLISHEDPERFORMANCE MAYNOTBE ACHIEVABLE. CAUSESHOULDBE DETERMINED ANDCORRECTEDAS SOONAS PRACTICAL.

MAXIMUM ALLOWABLE GAS PROD (N1) RPM - PERCENT

750

800

86

91

96

101

106

I I

ENGINE TORQUE - PERCENT (INDICATED) 212VFR-FM-1-4

Figure 4-1.

4-10

Rev. 1

Power assurance check chart - PT6T-3B (Sheet 4 of 4)

FAA APPROVED

BHT-212VFR-FM-1 CHART A

Hp

-500 -1000 -1500

% TORQUE 50.5 Hp

0

% TORQUE 49.5 H

6000

% TORQUE 39.5

51.5

52.5

500

1000

1500

2000 2500

3000 3500 4000

4500

5000

5500

48 5

48.0

470

46.0

44.0

420

41.0

40.5

6500 7000

7500

8000 8500 9000

9500

38.5

37.5

36.5

34.5

38.0

45.0

36.0

35.0

435

42.5

10,000 10,500 11,000 34.0

33.0

32.5

EXAMPLE ALTIMETER ............................................. 29.92 IN HG OBSERVEDH .............................................. 1500 FT OBSERVEDCHART A TORQUE............................. . 47.0% STARTBOTH ENGINES TURN HEATEROFF ON GROUND,ENGINENO. 2 TO IDLE STABILIZENO. 1 ENGINE,4 MINUTES MINIMUM, AT 97% (N2) ENGRPMAND CHART A TORQUEAND OBSERVE GAS PROD(N1) 95.2% RPM ITT 710°C OAT 20C OBSERVEDGAS PROD(N 1) RPMAND ITT MUST BE LESSTHAN CHARTGAS PROD(N 1) RPMAND ITT FOROBSERVEDOAT. REPEATCHECKON NO. 2 ENGINEWITH NO. 1 ENGINEAT IDLE. If OBSERVEDGAS PROD (N1) RPM AND/OR ITT ARE GREATERTHAN CHART B GAS PROD(N1 RPMAND/OR ITT FOROBSERVEDOAT. HOVERIGEAND CHECKNO. 1 AND NO. 2 ENGINETORQUENEEDLESPLITNO GREATER THAN 4%.

1. 2. 3. 4. 5. 6. 7.

8. 9. 10. 11.

CHART B

OAT -

°C

52

GAS PROD

{N1)

%RPM 100

ITT -

°C

810

50

45

40

35

30

25

20

15

10

5

0

100

99.8

99.1

98.4

97.7

97.0

96.3

95.6

94.8

94.1

93.4

810

805

795

780

765

750

735

720

705

690

675

OAT - °C GASPROD (N1- %RPM

-5

-10

-15

-20

-25

-30

-35

-40

-45

-50

-54

92.7

92.0

91.3

90.6

89.9

89.2

88.5

87.8

87.1

86.4

85.8

ITT -

660

645

630

615

605

590

575

560

545

530

C

520 212VFR-FM-4-2

Figure 4-2.

Power assurance check chart - PT6T-3

4-11

BHT-212VFR-FM-1

FAA APPROVED

EXAMPLE: IF AMBIENT TEMP IS -15 C 1.78 AND PRESSURE ALT IS 6.000 FEET.THE 1.76 DENSITY ALT IS 4.000 FEETAND IS 1 06

(11.0) (11.0)36

1

1.78

34 1.72

(10.0)

;-7

(9.0) 27

o36

1. 60

1.62

(5.0)

(4.0)

(1.0)

-70

-60

-50 -40

-30

-20 -10

0

10

20

TEMPERATURE - °C Figure 4-3.

4-12

Density altitude chart

30

40

50

60 212VFR-FM-4-3

FAA APPROVED

BHT-212VFR-FM-1 HOVER CEILING IN GROUND EFFECT SKID HEIGHT 4 FT HEATERON OR OFF WINTERIZATIONKIT HTR ON OR OFF

POWER: SEENOTE BELOW ENG RPM 100% (N2) GENERATOR150 AMPS EACH

0 ° TO 52°C

14,000 FT HD LIMIT

HOT DAY LIMIT

NOTE:THESEIGE HOVERCEIUNGS ARE BASED ON DENSITY ALTITUDE LIMITS FOR TAKEOFF AND LANDING. THIS HELICOPTERCAN BE OVERED IGE AT THE INDICATEDGROSSWEIGHTS WITH LESS THAN TAKEOFF POWER.

MAXIMUM GW LIMIT

MAXIMUM OAT HEATERON (21 °C)

__ 0

_

10 20 30 40 50 OAT - °C

__ 8000 (3629)

11, 200

(5080)

9000 10.000 11.000 12,000 (4082) (4536) (4989) 54431 GW - LB (KG) 212VFR-FM-4-4-1

Figure 4-4.

Hover ceiling in ground effect (Sheet 1 of 3)

4-13

BHT-212VFR-FM-1

FAA APPROVED HOVER CEILING IN GROUNDEFFECT

POWER:SEENOTEBELOW ENGRPM100% (N2) GENERATOR 150 AMPSEACH 0 ° TO-54°C

SKIDHEIGHT4 FT HEATER ON OROFF WINTERIZATION KITHTRON OROFF 14,000 FT HD LIMIT NOTE:THESEIGE HOVERCEILNGS ARE BASED ON DENSITY

WITH LESS THAN TAKEOFF

MAXIMUM GW LIMIT

,-_

Figure 4-4.

4-14

-____X

…/_______(5080)

Hover ceiling in ground effect (Sheet 2 of 3)

FAA APPROVED

BHT-212VFR-FM-1 HOVER CEILING INGROUNDEFFECT

MAXIMUM CONTINUOUS POWER ENG RPM 100% (N2) GENERATOR150 AMPS EACH

0° TO 52°C

SKID HEIGHT 4 FT HEATERON OR OFF WINTERIZATION KIT HTR ON OR OFF

14,000 FT HD LIMIT

MAXIMUM GW LIMIT

GW

LB (KG)

212VFRFM-4-4-3

Figure 4-4. Hover ceiling in ground effect (Sheet 3 of 3)

4-15

FAA APPROVED

BHT-212VFR-FM-1 HOVER CEILING OUTOFGROUNDEFFECT

SKIDHEIGHT60 FT OFF HEATER ° 0 TO52°C

POWER TAKEOFF ENGRPM100% (N2) 150 AMPSEACH GENERATOR

14,000 FTHD LIMIT MAXIMUM GW LIMIT

Figure 4-5.

4-16

Hover ceiling out of ground effect (Sheet 1 of 8)

FAA APPROVED

BHT-212VFR-FM-1 HOVER CEILING OUTOFGROUNDEFFECT

TAKEOFF POWER ENGRPM100% (N2) GENERATOR 150 AMPSEACH 414,000

SKIDHEIGHT60 FT HEATER OFF 0 ° TO-54'C FT HD LIMIT MAXIMUM

GW LIMIT

/

Figure 4-5.

Hover ceiling out of ground effect (Sheet 2 of 8)

-60-50-40-30-20-10 -60-50-40-30-20-10 OAT-C OAT-(3629) - °C

(5080)

4-17

08000 9000 10,000 10.000 11,000 11.000 12,000 (4536) (3629) (4082) (4082) (4536) (4989) (4989) (5443) (5443) GW -- LB (KG) (KG) 21 212VFR-FM-4-5-2 2VFR-FM-4-5-2

Figure 4-5. Hover ceiling out of ground effect (Sheet 2 of 8)

4-17

BHT-212VFR-FM-1

FAA APPROVED HOVER CEILING OUT OF GROUND EFFECT

TAKEOFF POWER ENGRPM100% (N2) GENERATOR 150 AMPS EACH

SKIDHEIGHT60 FT HEATER ON 0° TO20°C

14,000 FT HD LIMIT MAXIMUM GW LIMIT

4-18

Figure 4-5. Hover ceiling out of ground effect (Sheet 3 of 8)

FAA APPROVED

BHT-212VFR-FM-1 HOVER CEILING OUTOFGROUNDEFFECT

TAKEOFF POWER ENGRPM100% (N2) GENERATOR 150 AMPSEACH

SKIDHEIGHT60 FT HEATER ON 0 ° TO-54°C

14,000 FT HD LIMIT

Figure 4-5.

Hover ceiling out of ground effect (Sheet 4 of 8)

-60-50-40-30-20-10 OAT - °C °C

08000 (3629) (3629)

4-19

9000 10,000 11,000 12,000 (4082) (4536) (4989) (5443) (5443) (4082) (4536) (4989) GW - LB KG) LB(KG) 212VFR-FM-4-5-4 212VFR-FM-4-5-4

Figure 4-5.

Hover ceiling out of ground effect (Sheet 4 of 8)

4-19

BHT-212VFR-FM-1

FAA APPROVED HOVER CEILING OUTOFGROUND EFFECT

MAXIMUMCONTINUOUS POWER ENGRPM100% (N2) GENERATOR 150 AMPS EACH

SKIDHEIGHT60 FT HEATER OFF 0 ° TO 52°C

14,000 FT HD LIMIT

212VFR-FM-4-5-5

Figure 4-5.

4-20

Hover ceiling out of ground effect (Sheet 5 of 8)

FAA APPROVED

BHT-212VFR-FM-1 HOVER CEILING OUT OF GROUND EFFECT

SKIDHEIGHT60 FT HEATER OFF 0° TO-54°C

POWER MAXIMUMCONTINUOUS ENGRPM100% (N2) GENERATOR 150 AMPSEACH 14,000 FTHD LIMIT

MAXIMUM LIMIT

-60 -50 -40 -30 -20-10 0 8000 OAT - °C

9000 10,00 11,000 12,000

(3629) (4082) (4536) (4989) (5443)

GW-LB (KG) Figure 4-5.

212VFR-FM-45-6

Hover ceiling out of ground effect (Sheet 6 of 8)

4-21

BHT-212VFR-FM-1

FAA APPROVED HOVER CEILING OUT OF GROUNDEFFECT

MAXIMUM CONTINUOUS POWER ENG RPM 100% (N2)

SKID HEIGHT 60 FT HEATERON

0° TO20°C

GENERATOR 150 AMPS EACH 14,000 FT HD LIMIT

N0;

-

-

-

-

--

-20

C

GW - LB (KG)

212VFR-FM-4-5-7

Figure 4-5. Hover ceiling out of ground effect (Sheet 7 of 8)

4-22

FAA APPROVED

BHT-212VFR-FM-1 HOVER CEILING OUTOFGROUNDEFFECT

MAXIMUMCONTINUOUS POWER

SKIDHEIGHT60 FT

ENG RPM 100% (N2)

HEATERON

GENERATOR 150 AMPSEACH

0 TO-54°C

GW effect - LB(KG) 212VFR-FM-4-5-8 Figure 4-5. Hover ceiling out of ground (Sheet 8 of212VFR-FM-4-5-8 8) GW - LB (KG) Figure 4-5.

Hover ceiling out of ground effect (Sheet 8 of 8)

4-23

BHT-212VFR-FM-1

FAA APPROVED

40

270

'90

°

CRITICAL RELATIVE

WIND AZIMUTHS 40 TO 135

180 ° 212VFR.FM-4-6

Figure 4-6.

4-24

Critical relative wind azimuths for hover flight

FAA APPROVED

BHT-212VFR-FM-1

TAKEOFF DISTANCE OVER 50 FT (15.2m) OBSTACLE HOVER POWER + 15% TORQUE

INITIATED FROM 4 FT SKID HEIGHT

ENGRPM 100% (N2)

HEATER ON OROFF

GENERATOR 150 AMPS

WINTERIZATION KIT HTR ON OR OFF REFERTO VTOCS CHART FOR TAKEOFF SPEED

14,000

FT HD LIMIT

MAXIMUM HOT DAY TEMPERATURE

-60-40-20

0

OAT -

HD FOR TAKEOFF

LIMIT

20 40 60

200

400

600

800

1000

1200

°C

(61)

(122)

(183)

(244)

(305)

(366)

TAKEOFF DISTANCE -

FT (M) 212VFR-FM-4-7

Figure 4-7.

Takeoff distance over a 50 foot (15.2 meter) obstacle

4-25

BHT-212VFR-FM-1

FAA APPROVED

TWIN ENGINE TAKEOFF CLIMBOUT SPEED- KIAS GW -LB (KG)

4000

30

30

32

36

40

42

42

5000

30

30

32

38

40

42

-

6000

30

30

34

38

42

-

212VFR-FM-48

Figure 4-8.

4-26

Twin engine takeoff climbout speed

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 7000 LB (3175 KG)

TAKEOFFPOWER ENG RPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATEROFF WITH ALL DOORSOPENOR REMOVED, RATEOF 200 FT/MIN CLIMB WILL DECREASE

20,0001

111111

I

18,000

14,000 OAT

RATE OF CLIMB- FT/MIN

Figure 4-9.

212VR-FM-4-9-1

Twin engine rate of climb (Sheet 1 of 30) Rev. 2

4-27

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 7000 LB (3175 KG)

TAKEOFFPOWER ENGRPM100% (N2) GENERATOR 150 AMPS

58 KIAS HEATERON WITHALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

-40'C

16,000

14,000

12,000

I

10,000

8,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2.400

2,800

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-28

Rev. 2

Twin engine rate of climb (Sheet 2 of 30)

3,200 212VFRFM-4-9-2

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 8000 LB (3629 KG)

TAKEOFFPOWER ENGRPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATEROFF WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

20,000

18,000

14,000 12,000

10000

6,000

4,000

-

2,000

0 0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB - FT/MIN

Figure 4-9.

3,200 212VFR-FM-4-9-3

Twin engine rate of climb (Sheet 3 of 30)

Rev. 2

4-29

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW8000 LB (3629 KG)

TAKEOFFPOWER ENG RPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATERON WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

18,000

OAT

16,000

14,000

12,000 10,000

84,000

2,000

Figure 4-9.

4-30

Rev. 2

Twin engine rate of climb (Sheet 4 of 30)

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB TAKEOFFPOWER ENG RPM100%{N2} 150 AMPS GENERATOR

58 KIAS HEATEROFF RATE OF WITH ALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMBWILL DECREASE

20,000

18,000

16,000

°

-40 C

C

-30 -20C °

12,000

10,000 OAT LIMIT

8,000

6,000

4,000 2,000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB- FT/MIN

3,200 212VFR-FM-4--5

Figure 4-9. Twin engine rate of climb (Sheet 5 of 30) Rev. 2

4-31

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 9000 LB (4082 KG)

TAKEOFFPOWER ENGRPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATERON WITH ALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

20,000

18.000

-

16,000

14,000

12,000

10,000

_

8,000

6,000

4,000

2,000

0 0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-32

Rev. 2

Twin engine rate of climb (Sheet 6 of 30)

212VFR-FM4-9-6

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG) TAKEOFFPOWER ENGRPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATEROFF WITHALL DOORSOPENOR REMOVED, RATE OF 200 FT/MIN CLIMBWILL DECREASE

Rev. 2

4-33

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG)

TAKEOFFPOWER ENG RPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATERON WITHALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-34

Rev. 2

Twin engine rate of climb (Sheet 8 of 30)

212VFR-FM-4-9-8

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 11,200LB (5080 KG)

TAKEOFFPOWER ENG RPM100%(N21 150 AMPS GENERATOR

58 KIAS HEATEROFF WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

18,000

212VFR-FM-4-9-9

Figure 4-9.

Twin engine rate of climb (Sheet 9 of 30)

Rev.2

4-35

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 11,200LB (5080 KG)

TAKEOFFPOWER ENG RPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATERON WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMB WILL DECREASE 200 FT/MIN

18,000

16,000

14,000

'_

12,000

10,000

8,000

_

_

_

_

6,000

4,000

2,000

0

200

400

600

800

1,000

1,200

1,400

RATE OF CLIMB- FT/MIN 212VFR-FM-4-9-10

Figure 4-9.

4-36

Rev. 2

Twin engine rate of climb (Sheet 10 of 30)

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 7000 LB 13175KG)

58 KIAS HEATEROFF

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS WITH ALL DOORSOPENOR REMOVED, RATEOF CLIMB WILL DECREASE 200 FT/MIN

18,000

14,000

12,000

10.000 8,000 6,000

2,000

0

400

Figure 4-9.

2,000 800 RATE 1,200 1,600 - FT/MIN OF CLIMB

2,400

2,800 212VFR-FM-4-9-11

Twin engine rate of climb (Sheet 11 of 30)

Rev. 2

4-37

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 7000 LB (3175 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS

83 KIAS HEATEROFF

WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMB WILL DECREASE200 FT/MIN

18,000

16,000

14,000 12,000

8,000

OAT

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

2,800

RATE OF CLIMB - FT/MIN

Figure 4-9.

4-38

Rev. 2

Twin engine rate of climb (Sheet 12 of 30)

212VFR-FM4-9-12

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 7000 LB (3175 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS

58 KIAS HEATERON

WITHALL DOORSOPENOR REMOVED, RATE OF

RATEOF CLIMB- FT/MIN

Figure 4-9.

212VFR-FM-4-9-13

Twin engine rate of climb (Sheet 13 of 30)

Rev. 2

4-39

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 7000 LB 13175KG) MAXIMUMCONTINUOUS POWER

83 KIAS

GENERATOR150 AMPS RATE OF WITH ALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMBWILL DECREASE 20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

0 0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-40

Rev. 2

Twin engine rate of climb (Sheet 14 of 30)

2,800 212VFR-FM-4-9-14

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 8000 LB (3629 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%IN2) GENERATOR 150 AMPS

58 KIAS

HEATEROFF

WITHALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

16,000

RATEOF CLIMB- FT/MIN

Figure 4-9.

212VFR-FM-4-9-15

Twin engine rate of climb (Sheet 15 of 30)

Rev. 2

4-41

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 8000 LB (3629 KG) MAXIMUMCONTINUOUS POWER ENG RPM100%(N21) 150 AMPS GENERATOR

83 KIAS HEATEROFF

RATE OF WITH ALL DOORSOPENOR REMOVED, CLIMB WILL DECREASE 200 FT/MIN 20,000

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-42

Rev. 2

Twin engine rate of climb (Sheet 16 of 30)

212VFR-FM-4-9-16

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 8000 LB (3629 KG)

MAXIMUMCONTINUOUS POWER ENG RPM 100% (N2)

58 KIAS

GENERATOR 150 AMPS

HEATERON WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMB WILL DECREASE200 FT/MIN

20,000

18,000

16.000 OAT LIMIT

14,000 _ _

12,000

_

4,000

2,000

0

400

800

1,200

1,600

2.000

2,400

RATE OF CLIMB - FT/MIN

Figure 4-9.

212VFR-FM-4-9-17

Twin engine rate of climb (Sheet 17 of 30)

Rev. 2

4-43

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 8000 LB (3629 KG)

83 KIAS HEATEROR WINTERIZATION KIT ON

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS EACH RATEOF WITHALL DOORSOPENOR REMOVED, CLIMBWILL DECREASE 200 FT/MIN 20,000

18,000 16000

4,000 10,000

8,000

6,000

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-44

Rev. 2

Twin engine rate of climb (Sheet 18 of 30)

212VFR-FM-4-9-18

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 9000 LB (4082 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPSEACH

58 KIAS HATER OFF

WITH ALL DOORSOPENOR REMOVED. RATE OF

RATEOF CLIMB- FT/MIN

Figure 4-9.

212VFR-FM-4-9-19

Twin engine rate of climb (Sheet 19 of 30)

Rev. 2

4-45

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 9000 LB (4082 KG) POWER MAXIMUMCONTINUOUS ENG RPM100%(N2) 150 AMPS EACH GENERATOR RATEOF WITH ALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMB WILL DECREASE 20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000 OAT LIMIT

2,000

0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB- FT/MIN

Figure 4-9.

4-46

Rev. 2

Twin engine rate of climb (Sheet 20 of 30)

212VFR-FM-4--20

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 9000 LB (4082 KG)

58 KIAS HEATERON

POWER MAXIMUMCONTINUOUS ENG RPM100% IN2) 150 AMPSEACH GENERATOR RATE OF WITHALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMBWILL DECREASE

18.000

16,000

14,000

12,000 -

____ _ AX 10,000 8,000

6,000

_

4,000

2,000

0

400

800

1,200

1,600

2,000

2,400

RATE OF CLIMB - FT/MIN

Figure 4-9.

212VFR-FM-4-9-21

Twin engine rate of climb (Sheet 21 of 30)

Rev. 2

4-47

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 9000 LB (4082 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) 150 AMPSEACH GENERATOR

83 KIAS HEATEROR KIT ON WINTERIZATION

WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMB WILL DECREASE 200 FT/MIN

RATEOF CLIMB- FT/MIN

Figure 4-9.

4-48

Rev. 2

Twin engine rate of climb (Sheet 22 of 30)

212VFR-FM-4-9-22

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG)

MAXIMUMCONTINUOUS POWER ENGRPM100%(N2) GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF

WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN 20,000

18,000

16,000

14,000

12,000

10,000

0

200

400

600

800

1,000

1,200

1,400 1,600

RATEOF CLIMB- FT/MIN

Figure 4-9.

212VFR-FM-4-9-23

Twin engine rate of climb (Sheet 23 of 30)

Rev. 2

4-49

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS EACH

83 KIAS HEATEROFF

WITH ALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN 20,000

RATE OF CLIMB - FT/MIN

Figure 4-9.

4-50

Rev. 2

Twin engine rate of climb (Sheet 24 of 30)

212VFR-FM-4-9-24

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 10,000 LB (4536 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS EACH

58 KIAS HEATERON

WITH ALL DOORSOPENOR REMOVED, RATE OF

RATE OF CLIMB - FT/MIN

Figure 4-9.

212VFR-FM-4-9-25

Twin engine rate of climb (Sheet 25 of 30)

Rev. 2

4-51

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 10,000 LB(4536 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPSEACH

83 KIAS HEATEROR WINTERIZATION KIT ON

WITHALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN 20,000

18,000

16,000 14,000

12,000

10,000

8,000

6,000

4,000

2,000

0

200

400

600

800

1,000

1,200

1,400

RATE OF CLIMB- FT/MIN

Figure 4-9. Twin engine rate of climb (Sheet 26 of 30) 4-52

Rev. 2

212VFR-FM-4-9-26

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 11,200LB (5080 KG)

MAXIMUMCONTINUOUS POWER ENGRPM100%(N2) GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF

WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

212VFR-FM-4-9-27

Figure 4-9.

Twin engine rate of climb (Sheet 27 of 30)

Rev. 2

4-53

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 11,200LB (5080 KG) MAXIMUMCONTINUOUS POWER ENGRPM100% (N2) 150 AMPS EACH GENERATOR

83 KIAS HEATEROFF

WITHALL DOORSOPENOR REMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

4,000 RATE OF CLIMB- FT/MIN 212VFR-FM-4-9-28

Figure 4-9.

4-54

Rev.2

Twin engine rate of climb (Sheet 28 of 30)

FAA APPROVED

BHT-212VFR-FM-1 TWIN ENGINE RATE OF CLIMB GW 11,200LB (5080 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPSEACH

58 KIAS HEATERON

WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMB WILL DECREASE 200 FT/MIN

18,000

16,000

14000

12,000

10,000

8,000

6,000

4,000

2,000

0

200

400

600

800

1,000

1,200

1,400

RATE OF CLIMB- FT/MIN 212VFR-FM-4-9-29

Figure 4-9.

Twin engine rate of climb (Sheet 29 of 30)

Rev. 2

4-55

BHT-212VFR-FM-1

FAA APPROVED TWIN ENGINE RATE OF CLIMB GW 11,200LB(5080 KG)

MAXIMUMCONTINUOUS POWER ENG RPM100%(N2) GENERATOR 150 AMPS EACH

83 KIAS HEATEROR WINTERIZATION KIT ON

WITH ALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

18,000

16,000

14,000

12,000

10,000

8,000

4,000

2,000

0

200

400

600 800

1,000

1,200

RATEOF CLIMB- FT/MIN 212VFR-FM-4-9-30

Figure 4-9.

4-56

Rev.2

Twin engine rate of climb (Sheet 30 of 30)

FAA APPROVED

BHT-212VFR-FM-1 SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 7000 LB(3175 KG)

2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITHALL DOORSOPENORREMOVED. RATE OFCLIMBWILLDECREASE 200 FT/MIN

20.000

14,000

12-000

TORQUE

00

8

6000 4000

RATE OF CLIMB - FT/MIN Figure 4-10.

212VFR-FM-4-10-1

Single engine rate of climb - PT6T-3B (Sheet 1 of 10)

Rev. 2

4-57

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 8000 LB(3629 KG)

2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITHALL DOORSOPENORREMOVED. RATE OFCLIMBWILLDECREASE 200 FT/MIN

RATE OF CLIMB - FT/MIN Figure 4-10.

4-58

Rev. 2

212VFR-FM-4-10-2

Single engine rate of climb - PT6T-3B (Sheet 2 of 10)

FAA APPROVED

BHT-212VFR-FM-1 SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW9000 LB(4082 KGI

2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITH ALLDOORSOPENORREMOVED. RATE OFCLIMBWILL DECREASE 200 FT/MIN

RATE OF CLIMB - FT/MIN Figure 4-10.

212VFR-FM-4-10-3

Single engine rate of climb - PT6T-3B (Sheet 3 of 10)

Rev. 2

4-59

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 10,000 LB (4536 KG) 58 KIAS HEATEROFF ENGINESECURED INOPERATIVE

2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS

WITH ALLDOORSOPENORREMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

20,000

NOTE

OAT

18,000

-50C

OPERATIONABOVE 71 8% TORQUE REQUIRES THE

212-070-160-101 TORQUEMETER.OR -103

16,000

14,000

TORQUE

12,000

71.8%

10,000 79.4%

2000

4000

-1200

-800

-400

0

400

RATE OF CLIMB - FT/MIN

Figure 4-10.

4-60

Rev. 2

800

1200 212VFR FM-4-10-4

Single engine rate of climb - PT6T-3B (Sheet 4 of 10)

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 11,200 LB(5080 KG)

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

2 1/2 MINUTEOEIPOWER ENGRPM97% (N2) 150 AMPS GENERATOR

RATEOF WITH ALL DOORSOPENORREMOVED, 200 FT/MIN CLIMBWILL DECREASE

20,000

18.000

NOTE OPERATIONABOVE 71 8% TORQUE REQUIRES THE OR -103

-212-070-160-101

OAT

TORQUEMETER

16.00

6000 -------

-

TORQUE

Figure 4-10. Single engine rate of climb - PT6T-3B (Sheet 5 of 10)

Rev. 2

4-61

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 7000 LB(3175 KG)

30 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS

58 KIAS HEATEROFF INOPERATIVEENGINESECURED WITH ALLDOORSOPENORREMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

4-62

Figure 4-10. Rev. 2

4-62

Rev. 2

Single engine rate of climb - PT6T-3B (Sheet 6 of 10)

RATE OF - FT/MIN Figure 4-10. Single engine rateCLIMB of climb - PT6T-3B (Sheet212VFR-FM-4-10-6 6 of 10)

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW8000 LB(3629 KG)

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

30 MINUTEOEIPOWER ENGRPM97% (N2) 150 AMPS GENERATOR

RATEOF WITH ALLDOORSOPENORREMOVED, 200 FT/MIN CLIMBWILL DECREASE

OAT

Figure 4-10.

Single engine rate of climb - PT6T-3B (Sheet 7 of 10)

Rev. 2 Rev.

4-63 4-63

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 9000 LB(4082 KG)

30 MINUTEOEIPOWER ENGRPM97% (N2) 150 AMPS GENERATOR

58 KIAS HEATEROFF INOPERATIVEENGINESECURED WITH ALLDOORSOPENORREMOVED, RATEOF CLIMBWILL DECREASE 200 FT/MIN

4-64

Rev. 2

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 10.000 LB(4536 KG)

58 KIAS HEATEROFF ENGINESECURED INOPERATIVE

30 MINUTEOEIPOWER ENGRPM97% (N2) 150 AMPS GENERATOR

RATEOF WITH ALLDOORSOPENORREMOVED, 200 FT/MIN CLIMBWILL DECREASE

~,oOo

Rev. 2

4-65

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3B GW 11,200 LB(5080 KG)

30 MINUTEOEIPOWER ENGRPM97% (N2) GENERATOR 150 AMPS

58 KIAS HEATEROFF INOPERATIVE ENGINESECURED WITH ALL DOORS OPEN OR REMOVED, RATE OF

CLIMBWILL DECREASE 200 FT/MIN

20,000 NOTE OPERATIONABOVE 71.8% TORQUE REQUIRES THE 212-070-160-101 OR -103

18,000

OAT

TORQUEMETER.

° -50 C -30C

16,000 16,000

14,000 12,000 TORQUE LIMITS

79.4%

6000

OAT LIMIT

2000

-1200

-800

-400

0

400

RATE OF CLIMB - FT/MIN Figure 4-10.

4-66

Rev. 2

800 212VFR-FM-4-10-10

Single engine rate of climb - PT6T-3B (Sheet 10 of 10)

FAA APPROVED

BHT-212VFR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW 7000 LB(3175 KG) 30 MINUTEPOWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITHALL DOORSOPENORREMOVED,RATE 'OFCLIMBWILLDECREASE 200 FT/MIN

Rev. 2 Rev.

4-67 4-67

BHT-212VFR-FM-1

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW8000 LB(3629 KG) 30 MINUTEPOWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITH ALLDOORSOPENORREMOVED. RATE OFCLIMBWILL DECREASE 200 FT/MIN

20,000

4-68

-1000 -800 14,000 12,000 8000 Rev.2

-600 -400 -200 0 200 OAT LIMIT

400

600

800

100

400

600

800

1000 1200 1400 1600

1200 1400 1600

4000

-1000 -800 -600 -400

-200

0

200

RATE OF CLIMB - FT/MIN

212VFR-FM-4-11-2

Figure 4-11. Single engine rate of climb - PT6T-3 (Sheet 2 of 10)

4-68

Rev. 2

BHT-212VFR-FM-1

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW9000 LB(4082 KG) 30 MINUTEPOWER ENGRPM97% (N2) 150 AMPSEACH GENERATOR

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITHALLDOORSOPENORREMOVED.RATE OFCLIMBWILLDECREASE 200 FT/MIN

20.000 18.000 16.000

12.000

TWINENGINE

10,000

MAXIMUM CONTINUOUS POWER ABSOLUTE CEILING

8000

OAT LIMIT

-1200-1000

-800

Figure 4-11.

-600

-400 0 - 200 400 RATE-200 OF CLIMB FT/MIN

600

800 212VFR-FM-4-11-3 1000 1200 212VFR-FM-4-11-3

Single engine rate of climb - PT6T-3 (Sheet 3 of 10)

Rev.2

4-69

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW10,000 LB(4636 KG)

30 MINUTEPOWER ENGRPM97% IN2 GENERATOR 150 AMPSEACH

KIAS HEATEROFF INOPERATIVE ENGINESECURED

WITH ALL DOORS OPENOR REMOVED, RATE

OFCLIMBWILL DECREASE 200 FT/MIN

20,000

18,000

16,000 OAT

-30c 12,000

8000

6000

TWINENGINE MAXIMUMCONTINUOUS POWERABSOLUTECEILING

4000

2000

-1000

-800

-600

-400

-200

0

RATE OF CLIMB Figure 4-11.

4-70

Rev.2

200 FT/MIN

400

600

800

1000

212VFR-FM-4-11-4

Single engine rate of climb - PT6T-3 (Sheet 4 of 10)

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB-PT6T-3 GW 11,200LB (5080 KG)

58 KIAS HEATEROFF ENGINESECURED INOPERATIVE

30 MINUTEPOWER ENG RPM97%(N2) 150 AMPS EACH GENERATOR

RATEOF WITH ALL DOORSOPENOR REMOVED, 200 FT/MIN CLIMB WILL DECREASE

18,000

TWINENGINE

MAXIMUM CONTINUOUS POWER ABSOLUTECEILING

16,000

14,000

12,000

10,000 8,000

6,000

OAT

LIMIT

2,000

-1,000

-800

-600

-400

-200

0

200

400

RATE OF CLIMB- FT/MIN

212VFR-FM-4-11-5

Figure 4-11. Single engine rate of climb - PT6T-3(Sheet 5 of 10) Rev. 2

4-71

BHT-212VFR-FM-1

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW 7000 LB (3175 KG) MAXIMUM CONTINUOUS POWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITH ALLDOORSOPENORREMOVED, RATE OFCLIMBWILL DECREASE 200 FT/MIN

20000 OAT

16000

OAT

6000

-1000-800

-600 -400 -2.00

0

200

400

600 800 1000 1200 1400 1600

RATE OF CLIMB - FT/MIN

Figure 4-11.

4-72

Rev. 2

212VFR-FM-4-11-6

Single engine rate of climb - PT6T-3 (Sheet 6 of 10)

BHT-212VFR-FM-1

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW 8000 LB(3629 KG) 58 KIAS HEATEROFF INOPERATIVEENGINESECURED

MAXIMUM CONTINUOUS POWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

WITHALL DOORSOPENORREMOVED,RATE 200 FT/MIN OFCLIMBWILL DECREASE

20.000

-1400-1200-1000-800

-600 -400 -200

0

200

400

RATE OF CLIMB - FT/MIN

Figure 4-11.

600

800 1000 1200 212VFR-FM-4-1-7

Single engine rate of climb - PT6T-3 (Sheet 7 of 10)

Rev.2

4-73

BHT-212VFR-FM-1

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW9000 LB(4082 KG) MAXIMUMCONTINUOUS POWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

58 KIAS HEATEROFF INOPERATIVEENGINESECURED

WITH ALLDOORSOPENORREMOVED,RATE OFCLIMBWILL DECREASE 200 FT/MIN

12.000 14,000

6000

OAT LIMIT

-1800-1600-1400-1200-1000-800

-600 -400 -200

0

200 400 600 800 1000

RATE OF CLIMB - FT/MIN

Figure 4-11.

4-74

Rev. 2

Single engine rate of climb - PT6T-3 (Sheet 8 of 10)

FAA APPROVED

BHT-212VFR-FM-1 SINGLE ENGINE RATE OF CLIMB-PT6T-3 GW 10,000 LB (4536KG)

MAXIMUMCONTINUOUS POWER ENGRPM97% (N2) GENERATOR 150 AMPSEACH

58 KIAS HEATEROFF INOPERATIVE ENGINESECURED

WITH ALLDOORSOPENORREMOVED, RATE OFCLIMBWILLDECREASE 200 FT/MIN

20000 18000

OAT

16000

14000

12000

10000

8000

TWINENGINE MAXIMUM CONTINUOUS POWER ABSOLUTE CEILING

6000 OAT LIMIT 4000

2000

-1200

-1000

-800

-600 -400 -200 0 RATE OF CLIMB - FT/MIN

200

400 600 212VFR-FM-4-11-9

Figure 4-11. Single engine rate of climb - PT6T-3 (Sheet 9 of 10)

Rev.2

4-75

BHT-212VFR-FM-1

FAA APPROVED SINGLE ENGINE RATE OF CLIMB - PT6T-3 GW 11,200LB (5080 KG)

MAXIMUMCONTINUOUS POWER ENGRPM97% (N2) GENERATOR 150 AMPS EACH

58 KIAS HEATEROFF INOPERATIVE ENGINESECURED WITHALL DOORSOPENOR REMOVED, RATE OF CLIMBWILL DECREASE 200 FT/MIN

TWIN ENGINE

CEILING MC.P.ABSOLUTE

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000 OAT LIMIT

2,000

0 -1,000

-800

-600

-400

-200

0

200

400

RATE OF CLIMB- FT/MIN 212VFR-FM-4-11-10

Figure 4-11.

4-76

Rev. 2

Single engine rate of climb - PT6T-3 (Sheet 10 of 10)

BHT-212VFR-FM-1

FAA APPROVED PILOT AIRSPEED SYSTEM CALIBRATION

CLIMB LEVELFLIGHT AUTOROTATION SKIDGEAR IAS- ERROR VCAL

140

120 LEVEL FLIGHT

--

AUTO

60 CLIMB

40

20

0

20

40

60

80

100

120

140

INDICATED AIRSPEED - KNOTS 212VFR-FM-4-12

Figure 4-12.

Pilot airspeed system calibration Rev. 2

4-77

BHT-212VFR-FM-1

FAA APPROVED COPILOT AIRSPEED SYSTEM CALIBRATION

CLIMB LEVELFLIGHT AUTOROTATION SKID GEAR IAS - ERROR: VC A L

140

120 AUTO 100

80

60 CLIMB 40

20 0 0

20

40

60

80

100

120

INDICATEDAIRSPEED- KNOTS

Figure 4-13. Copilot airspeed system calibration 4-78

Rev. 2

140 212VFR.FM-4-13

FAA APPROVED

BHT-212VFR-FM-1

SINGLE ENGINE LANDING DISTANCE OVER50 FT(15.2 M) OBSTACLE 40 KIAS RATEOF DESCENT500 FPM HARDSURFACEDRUNWAY

POWERAS REQUIRED ENGRPM97% (N2) 150 AMPS GENERATOR INOPERATIVE ENGINESECURED

14,000 FT H D LIMIT

OAT - °C

(61)

(122)

(183)

(244)

LANDING DISTANCE -

(305)

FT (M)

212VFR-FM-4-14

Figure 4-14. Single engine landing distance over a 50 foot (15.2 meter) obstacle

Rev. 2

4-79/4-80

MANUFACTURER'S DATA

BHT-212VFR-FM-1

Section 5 TABLE OF CONTENTS Subject

Paragraph

INTRODUCTION ......... ..... ..................

5-1..........

EMPTY WEIGHT CENTER OF GRAVITY ........................ GROSS WEIGHT CENTER OF GRAVITY........................ DOORS OPEN OR REMOVED .................................. COCKPIT AND CABIN LOADING ........................... CABIN DECK LOADING .................................... INTERNAL CARGO LOADING TABLE...................... BAGGAGE COMPARTMENT LOADING ......................... BAGGAGE LOADING ....................................... BAGGAGE LOADING TABLE............................... FUEL LOADING ................................................. COMPUTATION OF CG ..................................... SAMPLE LOADING PROBLEM .............................

....

5-2........... 5-3........... 5-4.......... 5-5........... 5-5-A ....... 5-5-B ....... 5-6......... 5-6-A ....... 5-6-B ........ 5-7.......... 5-7-A ........ 5-7-B ........

Page Number

5-3 5-3 5-3 5-3 5-3 5-3 5-3 5-4 5-4 5-4 5-4 5-4 5-4

LIST OF FIGURES Title

Figure Number

Helicopter station diagram .....................................

5-1...........

Page Number

5-7

LIST OF TABLES Title

Title

Door weights and moments .................................... Crew and passenger table of moments ........................

Internal cargo loading .......................................... Baggage loading ..............................................

Table Number 5-1........... 5-2...........

5-3.......... 5-4...........

Fuel loading...................................5-5...........

Fuel loading.....................................................

5-6...........

Page Number 5-8 5-9

5-11 5-13 5-14

5-16

5-1/5-2

MANUFACTURER'S DATA

BHT-212VFR-FM-1

Section 5 5-1. INTRODUCTION This section provides regarding

helicopter

information

center of gravity and

cockpit and cabin loading.

Loading table

for pilot and passengers, cargo, and fuel are provided. A sample loading problem is provided to aid in flight planning.

5-2. EMPTYWEIGHTCENTER OF GRAVITY Weight empty consists of basic helicopter with required equipment, optional equipment kits, transmission and gearbox

oils, hydraulic fluid, unusable fuel,

Door weights and moments table (table 5-

1) lists weight and moment adjustments which should be made in determining GW which be should made in are determining and CG when doors opened GW or removed

5-5. COCKPIT AND CABIN LOADING A minimum crew weight of 170 pounds (77.1 kilograms) in cockpit is required. Except for two aft passenger seats, crew and passengers may be loaded in any sequence without exceeding GW CG limits approved for flight.

undrainable engine oil, and fixed ballast. Weigh empty CG shall be adjusted within limits of applicable Weight empty center of gravity chart in BHT-212-MM.

5-3. GROSSWEIGHTCENTER

NOTE Outboard facing seats should not be occupied unless at least four passengers are seated in forward and/or aft facing seats.

OF GRAVITY It shall be pilot responsibility to ensure helicopter is properly loaded so entire flight is conducted within limits of Gross

5-5-A. CABIN DECK LOADING Cabin deck cargo loading limit is 100 pounds per square foot (0.048 kilograms

Weight Center of Gravity Chart in Section

per square centimeter).

1. GW CG may be calculated

from

helicopter Actual Weight Record (historical

records) and loading tables in this section

or in appropriate

Flight

WARNING

Manual

Supplements to assure safe loading. Locations of crew and passenger seats, baggage compartment, and fuel tanks are shown in helicopter station diagram (figure 5-1).

Helicopter CG shall be computed for all cargo/baggage configurations before flight. Refer to table 5-2 for personnel weights and moments in English and Metric units.

5-4.

DOORS OPEN OR

REMOVED

5-5-B.

Opening or removing doors results in CG

TABLE

changes. Door configuration shall be symmetrical for both sides of fuselage.

INTERNAL CARGO LOADING

Weights at various arms and their moments are listed in 50 pound 5-3

BHT-212VFR-FM-1

MANUFACTURER'S DATA

increments from 50 pounds through 2000 pounds and in 25 kilogram Increments from 25 kilograms through 900 kilograms

remain for helicopter serial numbers prior to 35049 and at 78.5 U.S. gallons (297.1 liters) for helicopter serial numbers 30549

(table 5-3).

and subsequent. CG then begins to move rearward as fuel is consumed from forward (lower) fuel cells. With normal crew and passenger loading, GW CG should remain within limits at any fuel quantity.

5-6. BAGGAGE COMPARTMENT LOADING Baggage compartment

is accessible

from

Fuel quantities are listed with moments in

right side of tallboom and contains approximately 28 cubic feet of space. Baggage compartment has a load limit of

10 gallon 216.8 increments gallons through gallons from and 10 in 40 liter

400 pounds (181.4 kilograms) not to

35049(table5-5

exceed 100 pounds per square foot (0.048 kilograms per square centimeter). These

Fuel quantities are listed with moments in 10 gallon increments from 10 gallons

are structural limitations only and do not Infer that CG will remain within approved limits. When weight is loaded baggage comparment,

indiscriminate

crew, passenger, and fuel loading can no

longer be assumed, and pilot must compute

GW CG to ensure

loading

is

within approved limits. BAGGAGE LOADING

5-6-A.

Loading of baggage compartment

should

increments

from 40 liters through

820.7

through 218.6 gallons and in 40 liter through 218.6 gallons and in 40 liter increments from 40 liters through 827.4

liters for helicopter serial numbers 35049 and subsequent (table 5-6).

5-7-A. COMPUTATION OF CG A sample problem Is presented showing calculation of takeoff and landing weights and CG locations for two typical loading conditions.

be from front to rear. Load shall be secured to tiedown fittings if shifting of load in flight could result in structural

5-7-B. SAMPLELOADING PROBLEM

damage to baggage compartment

CG of helicopter will move forward as fuel

or in GW

CG limits being exceeded. If baggage is not secured, CG shall be computed with

is burned off in flight.

This occurs

because fuel is burned from upper rear

load in most adverse position.

fuel cells first. A maximum forward CG condition occurs when 72.6 gallons (274.8

5-6-B. BAGGAGELOADING

liters) of fuel is on board for helicopter serial numbers prior to 35049. CG then

TABLE Weights at various arms and their moments are listed in 20 pound Increments from 20 pounds through 400 pounds and in 10 kilogram increments from 10 kilograms through 181.4 kilograms (table 5-4).

5-7.

FUEL LOADING

begins to move rearward as fuel is burned

out of lower fuel cells. Helicopter Is chartered to transport nine passengers and 180 pounds of baggage for a trip that will require approximately 155 gallons (586.8 liters) of fuel. Pilot, weighing

180 pounds (82 kilograms),

will

return alone. Determine extreme CG conditions for both trips. From GW CG charts in Section 1, it can be

At beginning of any flight with full fuel on board, helicopter CG will move forward

determined that CG Is within limits for first leg of flight and that loading of passengers

due to the fact that the CG of fuel on board

in five man and four

moves forward as It Is consumed. This occurs because fuel Is consumed from rear (upper) fuel cells first. Maximum forward CG condition of fuel on board occurs when 72.6 U.S. gallons (274.8 liters) 5-4

man seats will be

satisfactory for first leg. From GW CG charts, it can also be determined that CG Is within limits for

MANUFACTURER'S DATA

BHT-212VFR-FM-1

second leg of flight, thus, entire operation can be completed.

5-5/5-6

MANUFACTURER'S DATA

BHT-212VFR-FM-1

FUSELAGE STATIONS 23

166

243

SeatCOMPARTMENT FUSELAGE STATIONS 102

Copilotor

166

diagram

5-7 5-7

MANUFACTURER'S DATA

BHT-212VFR-FM-1 Table 5-1.

Door weights and moments ENGLISH

DOOR CONFIGURATION Both Both Both Both

crew doors removed hinged panels removed sliding doors removed sliding doors full open

WEIGHT CHANGE (POUNDS)

ARM (INCHES)

-39.0 -20.4 -90.4 0

46.2 85.0 130.0 202.0

MOMENT CHANGE (IN-LB) -1802 1734 -11,752 +6509

METRIC

DOOR CONFIGURATION Both Both Both Both

crew doors removed hinged panels removed sliding doors removed sliding doors full open

WEIGHT CHANGE (KILOGRAMS)

ARM (MILLIMETERS)

-17.7 - 9.3 -41.0 0

1173 2159 3302 5131

MOMENT CHANGE (KG * MM/100) -207.6 200.8 -1353.8 +749.9

(TABLE

5-8

I.D.

911208)

Table 5-2.

Crew and passenger table of moments

CREW AND PASSENGER TABLE OF MOMENTS (ENGLISH)

Weight (Pounds)

Pilot and Copilot* FS 47

Passenger (4 - Man Seat Facing Aft) FS 87

Passenger (5 - Man Seat Facing Fwd) FS 117

100 110 120 130 140 150 160 170 180 190 200 210 220

4700 5170 5640 6110 6580 7050 7520 7990 8460 8930 9400 9870 10340

8700 9570 10440 11310 12180 13050 13920 14790 15660 16530 17400 18270 19140

11700 12870 14040 15210 16380 17550 18720 19890 21060 22230 23400 24570 25740

Passenger Facing Outboard Fwd Seat Aft Seat FS 139 FS 156 13900 15290 16680 18070 19460 20850 22240 23630 25020 26410 27800 29190 30580

15600 17160 18720 20280 21840 23400 24960 26520 28080 29640 31200 32760 34320

Litter Patient Lateral Longitudinal Loaded Loaded FS 117 FS 120 11700 12870 14040 15210 16380 17550 18720 19890 21060 22230 23400 24570 25740

12000 13200 14400 15600 16800 18000 19200 20400 21600 22800 24000 25200 26400

*Left Forward Seat

(TABLE I.D. 911209) '1

Table 5-2.

Crew and passenger table of moments (Cont)

CREW AND PASSENGER TABLE OF MOMENTS (METRIC) (KG * MM/100)

Weight (Kilograms)

Pilot and Copilot 1194 MM

Passenger (4 - Man Seat Facing Aft) 2210 MM

Passenger (5 - Man Seat Facing Fwd) 2972 MM

45 50 55 60 65 70 75 80 85 90 95

537.3 597.0 656.7 716.4 776.1 835.8 895.5 955.2 1014.9 1074.6 1134.3

994.5 1105.0 1215.5 1326.0 1436.5 1547.0 1657.5 1768.0 1878.5 1989.0 2099.5

1337.4 1486.0 1634.6 1783.2 1931.8 2080.4 2229.0 2377.6 2526.2 2674.8 2823.4

Passenger Facing Outboard Fwd Seat Aft Seat 3531 MM 3962 MM 1589.0 1765.5 1942.1 2118.6 2295.2 2471.7 2648.3 2824.8 3001.4 3177.9 3354.5

1782.9 1981.0 2179.1 2377.2 2575.3 2773.4 2971.5 3169.6 3367.7 3565.8 3763.9

Litter Patient Lateral Longitudinal Loaded Loaded 2972 MM 3048 MM 1337.4 1486.0 1634.6 1783.2 1931.8 2080.4 2229.0 2377.6 2526.2 2674.8 2823.4

1371.6 1524.0 1676.4 1828.8 1981.2 2133.6 2286.0 2438.4 2590.8 2743.2 2895.6

*Left Forward Seat

> (TABLE

I.D.

911210)

MANUFACTURER'S DATA

BHT-212VFR-FM-1 Table 5-3.

Internal cargo loading

INTERNAL CARGO LOADING TABLE (ENGLISH) CARGO WEIGHT (POUNDS)

75

90

CARGO CENTER OF GRAVITY (FS) 105 120

135

150

CARGO MOMENT (IN-LB) 50 100 150 200 250

3750 7500 11250 15000 18750

4500 9000 13500 18000 22500

5250 10500 15750 21000 26250

6000 12000 18000 24000 30000

6750 13500 20250 27000 33750

7500 15000 22500 30000 37500

300 350 400 450 500

22500 26250 30000 33750 37500

27000 31500 36000 40500 45000

31500 36750 42000 47250 52500

36000 42000 48000 54000 60000

40500 47250 54000 60750 67500

45000 52500 60000 67500 75000

550 600 650 700 750

41250 45000 48750 52500 56250

49500 54000 58500 63000 67500

57750 63000 68250 73500 78750

66000 72000 78000 84000 90000

74250 81000 87750 94500 101250

82500 90000 97500 105000 112500

800 850 900 950 1000

60000 63750 67500 71250 75000

72000 76500 81000 85500 90000

84000 89250 94500 99750 105000

96000 102000 108000 114000 120000

108000 114750 121500 128250 135000

120000 127500 135000 142500 150000

1050 1100 1150 1200 1250

78750 82500 86250 90000 93750

94500 99000 103500 108000 112500

110250 115500 120750 126000 131250

126000 132000 138000 144000 150000

141750 148500 155250 162000 168750

157500 165000 172500 180000 187500

1300 1350 1400 1450 1500

97500 101250 105000 108750 112500

117000 121500 126000 130500 135000

136500 151750 147000 152250 157500

156000 162000 168000 174000 180000

175500 182250 189000 195750 202500

195000 202500 210000 217500 225000

1550 1600 1650 1700 1750

116250 120000 123750 127500 131250

139500 144000 148500 153000 157500

162750 168000 173250 178500 183750

186000 192000 198000 204000 210000

209250 216000 222750 229500 236250

232500 240000 247500 255000 262500

1800 1850 1900 1950 2000

135000 138750 142500 146250 150000

162000 166500 171000 175500 180000

189000 194250 199500 204750 210000

216000 222000 228000 234000 240000

243000 249750 256500 263250 270000

270000 277500 285000 292500 300000 (TABLE I.D. 911214)

5-11

MANUFACTURER'S DATA

BHT-212VFR-FM-1 Table 5-3.

Internal cargo loading (Cont)

INTERNAL CARGO LOADING TABLE (METRIC) CARGO WEIGHT (KG)

1905

2286

CARGO CENTER OF GRAVITY (MM) 3048 2667

3429

3810 952.5 1905.0 2857.5 3810.0 4762.5 5715.0 6667.5

CARGO MOMENT (KG · MM/100) 25 50 75 100 125 150 175

476.3 952.5 1428.8 1905.0 2381.3 2857.5 3333.8

571.5 1143.0 1714.5 2286.0 2857.5 3429.0 4000.5

666.8 1333.5 2000.3 2667.0 3333.8 4000.5 4667.3

762.0 1524.0 2286.0 3048.0 3810.0 4572.0 5334.0

857.3 1714.5 2571.8 3429.0 4286.3 5143.5 6000.8

200 225 250

3810.0 4286.3 4762.5

4572.0 5143.5 5715.0

5334.0 6000.8 6667.5

6096.0 6858.0 7620.0

6858.0 7715.3 8572.5

275 300 325 350 375 400 425 450 475 500 525 550 575 600 625 650 675 700 725 750 775 800 825 850 875 900

5238.8 5715.0 6191.3 6667.5 7143.8 7620.0 8096.3 8572.5 9048.8 9525.0 10001.3 10477.5 10953.8 11430.0 11906.3 12382.5 12858.8 13335.0 13811.3 14287.5 14763.8 15240.0 15716.3 16192.5 16668.8 17145.0

6286.5 6858.0 7429.5 8001.0 8572.5 9144.0 9715.5 10287.0 10858.5 11430.0 12001.5 12573.0 13144.5 13716.0 14287.5 14859.0 15430.5 16002.0 16573.5 17145.0 17716.5 18288.0 18859.5 19431.0 20002.5 20574.0

7334.3 8001.0 8667.8 9334.5 10001.3 10668.0 11334.8 12001.5 12668.3 13335.0 14001.8 14668.5 15335.3 16002.0 16668.8 17335.5 18002.3 18669.0 19335.8 20002.5 20669.3 21336.0 22002.8 22669.5 23336.3 24003.0

8382.0 9144.0 9906.0 10668.0 11430.0 12192.8 12954.0 13716.0 14478.0 15240.0 16002.0 16764.0 17526.0 18288.0 19050.0 19812.0 20574.0 21336.0 22098.0 22860.0 23622.0 24384.0 25146.0 25908.0 26670.0 27432.0

9429.8 10287.0 11144.3 12001.5 12858.8 13716.0 14573.3 15430.5 16287.8 17145.0 18002.3 18859.5 19716.8 20574.0 21431.3 22288.5 23145.8 24003.0 24860.3 25717.5 26574.8 27432.0 28289.3 29146.5 30003.8 30861.0

10477.5 11430.0 12382.5 13335.0 14287.5 15240.0 16192.5 17145.0 18097.5 19050.0 20002.5 20955.0 21907.5 22860.0 23812.5 24765.0 25717.5 26670.0 27622.5 28575.0 29527.5 30480.0 31432.5 32385.0 33337.5 34290.0 (TABLE

5-12

7620.0 8572.5 9525.0

I.D. 911215)

BHT-212VFR-FM-1

MANUFACTURER'S DATA Table 5-4.

Baggage loading

BAGGAGE LOADING TABLE (ENGLISH) LOAD BAGGAGE FROM FORWARD END OF COMPARTMENT 400 POUND MAXIMUM WEIGHT (LB)

APPROX. CG (FS)

MOMENT

WEIGHT (LB)

APPROX. CG (FS)

MOMENT

20 40 60 80 100 120 140 160 180 200

245 247 249 251 253 255 257 259 261 263

4900 9880 14940 20080 25300 30600 35980 41440 46980 52600

220 240 260 280 300 320 340 360 380 400

265 267 269 271 273 275 277 279 281 283

58300 64080 69940 75880 81900 88000 94180 100440 106780 113200

BAGGAGE LOADING TABLE (METRIC) LOAD BAGGAGE FROM FORWARD END OF COMPARTMENT 181.4 KILOGRAMS MAXIMUM WEIGHT (KG)

APPROX. CG (MM)

MOMENT (KG * MM/100)

WEIGHT (KG)

APPROX. CG (MM)

MOMENT (KG MM/100)

10 20 30 40 50 60 70 80 90 100

6228 6284 6340 6396 6452 6507 6563 6619 6675 6734

622.8 1256.8 1902.0 2558.4 3226.0 3904.2 4594.1 5295.2 6007.5 6734.0

110 120 130 140 150 160 170 180 181.4

6789 6845 6901 6957 7013 7069 7125 7181 7188

7467.9 8214.0 8971.3 9739.8 10519.5 11310.4 12112.5 12925.8 13039.0 (TABLE I.D. 911213)

5-13

MANUFACTURER'S DATA

BHT-212VFR-FM-1 Table 5-5. Fuel loading Helicopterserial numbers prior to 35049 ENGLISH ASTM D-1655 TYPE A, A-1, JP-5, AND JP-8

ASTM D-1655 TYPE B AND JP-4

(6.5LBS/GAL)

(6.8 LBS/GAL)

QUANTITY (U.S. GAL)

WEIGHT (LB)

10 20 30 40 50 60 70 *72.6 80 90 100 110 120 130 140 150 160 170 180 190 200 210 "216.8

68 136 204 272 340 408 476 494 544 612 680 748 816 884 952 1020 1088 1156 1224 1292 1360 1428 1474

CG (IN) 143.6 143.6 140.2 134.8 131.6 129.4 127.9 127.6 128.3 130.6 134.6 137.8 140.4 142.6 144.6 146.1 147.6 148.8 149.9 150.9 151.9 152.7 153.3

MOMENT (IN-LB)

QUANTITY (U.S. GAL)

9765 19530 28601 36666 44744 52795 60880 63034 69795 79927 91528 103074 114566 126058 137659 149022 160589 172013 183478 194963 206584 218056 225964

10 20 30 40 50 60 70 '72.6 80 90 100 110 120 130 140 150 160 170 180 190 200 210 **216.8

WEIGHT (LB) 65 130 195 260 325 390 455 472 520 585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365 1409

CG (IN) 143.6 143.6 140.2 134.8 131.6 129.4 127.9 127.6 128.3 130.6 134.6 137.8 140.4 142.6 144.6 146.1 147.6 148.8 149.9 150.9 151.9 152.7 153.3

MOMENT (IN-LB) 9334 18668 27339 35048 42770 50466 58195 60227 66716 76401 87490 98527 109512 120497 131586 142448 153504 164424 175383 186362 197470 208436 216000

Mostcritical fuel amountfor most forward flight condition. **Most critical fuel amountfor most aft flight condition. NOTE:All data aboverepresentsusable fuel basedon nominaldensity at 15°C(59°F). (TABLE

5-14

I.D. 911211)

MANUFACTURER'S DATA

BHT-212VFR-FM-1 Table 5-5. Fuel loading (Cont) Helicopterserial numbersprior to 35049 METRIC

ASTM D-1655 TYPE A, A-1, JP-5, AND JP-8 (0.815 KG/L)

LITERS

WEIGHT (KG)

40 80 120 160 200 240 274.8 280 320 360 400 440 480 520 560 600 640 680 720 760 800 **820.7

32.6 65.2 97.8 130.4 163.0 195.6 224.0 228.2 260.8 293.4 326.0 358.6 391.2 423.8 456.4 489.0 521.6 554.2 586.8 619.4 652.0 668.9

ASTM D-1655 TYPE B AND JP-4 (.779 KG/L)

CG (MM)

MOMENT KG MM 100

LITERS

WEIGHT (KG)

3647 3647 3541 3399 3322 3272 3241 3246 3277 3368 3470 3541 3609 3665 3708 3744 3777 3805 3833 3858 3884 3894

1188.9 2377.8 3463.1 4432.3 5414.9 6400.0 7259.8 7407.4 8546.4 9881.7 11312.2 12698.0 14118.4 15532.3 16923.3 18308.2 19700.8 21087.3 22492.0 23896.5 25323.7 26047.0

40 80 120 160 200 240 *274.8 280 320 360 400 440 480 520 560 600 640 680 720 760 800 **820.7

31.2 62.3 93.5 124.6 .155.8 187.0 214.1 218.1 249.3 280.4 311.6 342.8 373.9 405.1 436.2 467.4 498.6 529.7 560.9 592.0 623.2 639.3

CG (MM) 3647 3647 3541 3399 3322 3272 3241 3246 3277 3368 3470 3541 3609 3665 3708 3744 3777 3805 3833 3858 3884 3894

MOMENT KG MM 100 1137.9 2272.1 3310.8 4235.2 5175.7 6118.6 6939.0 7079.5 8169.6 9443.9 10812.5 12138.5 13494.1 14846.9 16174.3 17499.5 18832.1 20155.1 21499.3 22839.4 24205.1 24894.3

Most critical fuel amount for mostforward flight condition. **Mostcritical fuel amount for most aft flight condition. NOTE:All data aboverepresentsusable fuel basedon nominaldensity at 15C (59°F). (TABLE

I.D. 911212)

5-15

BHT-212VFR-FM-1

MANUFACTURER'S DATA Table 5-6. Fuel loading Helicopterserial numbers35049and subsequent ENGLISH

ASTM D-1655 TYPE A, A-1, JP-5, AND JP-8

ASTM D-1655 TYPE B AND JP-4

(6.5 LBS/GAL)

(6.8 LBS/GAL) QUANTITY (U.S. GAL) 10 20 30 40 50 60 70 *78.5 80 90 100 110 120 130 140 150 160 170 180 190 200 210 218.6

WEIGHT (LB) 68 136 204 272 340 408 476 534 544 612 680 748 816 884 952 1020 1088 1156 1224 1292 1360 1428 1486

CG (IN)

MOMENT (IN-LB)

143.9 144.0 141.6 135.7 132.2 129.9 128.2 127.3 127.4 129.5 133.4 136.7 139.3 141.7 143.6 145.2 146.8 148.1 149.3 150.3 151.3 152.1 152.6

9785 19584 28886 36910 44948 52999 61023 67953 69306 79254 90712 102252 113669 125263 136707 148104 159718 171204 182743 194188 205768 217199 226837

QUANTITY (U.S. GAL) 10 20 30 40 50 60 70 '78.5 80 90 100 110 120 130 140 150 160 170 180 190 200 210 218.6

WEIGHT (LB) 65 130 195 260 325 390 455 510 520 585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365 1421

CG (IN)

MOMENT (IN-LB)

143.9 144.0 141.6 135.7 132.2 129.9 128.2 127.3 127.4 129.5 133.4 136.7 139.3 141.7 143.6 145.2 146.8 148.1 149.3 150.3 151.3 152.1 152.6

9354 18720 27612 35282 42965 50661 58331 64955 66248 75758 86710 97741 108654 119737 130676 141570 152672 163651 174681 185621 196690 207617 216829

*Most critical fuel amountfor most forward flight condition. NOTE:All data aboverepresentsusablefuel basedon nominal density at 15°C(59°F). (TABLE I.D. 911330)

5-16

MANUFACTURER'S DATA

BHT-212VFR-FM-1

Table 5-6. Fuel loading (Cont) Helicopterserial numbers35049and subsequent METRIC ASTM D-1655 TYPE A, A-1, JP-5, AND JP-8 (0.815 KG/L)

LITERS

WEIGHT (KG)

40 80 120 160 200 240 280 297.1 320 360 400 440 480 520 560 600 640 680 720 760 800 827.4

32.6 65.2 97.8 130.4 163.0 195.6 228.2 242.1 260.8 293.4 326.0 358.6 391.2 423.8 456.4 489.0 521.6 554.2 586.8 619.4 652.0 674.3

CG (MM)

MOMENT KG MM 100

3655 3658 3561 3421 3340 3284 3246 3233 3249 3343 3434 3515 3579 3635 3683 3721 3757 3790 3818 3843 3866 3876

1191.5 2385.0 3482.7 4461.0 5444.2 6423.5 7407.4 7827.1 8473.4 9808.4 11194.8 12604.8 14001.1 15405.1 16809.2 18195.7 19596.5 21004.2 22404.0 23803.5 25206.3 26135.9

ASTM D-1655 TYPE B AND JP-4 (.779 KG/L)

LITERS 40 80 120 160 200 240 280 297.1 320 360 400 440 480 520 560 600 640 680 720 760 800 827.4

WEIGHT (KG) 31.2 62.3 93.5 124.6 155.8 187.0 218.1 231.4 249.3 280.4 311.6 342.8 373.9 405.1 436.2 467.4 498.6 529.7 560.9 592.0 623.2 644.5

CG (MM)

MOMENT KG MM 100

3655 3658 3561 3421 3340 3284 3246 3233 3249 3343 3434 3515 3579 3635 3683 3721 3757 3790 3818 3843 3866 3876

1140.4 2278.9 3329.5 4262.6 5203.7 6141.1 7079.5 7481.2 8099.8 9373.8 10700.3 12049.4 13381.9 14725.4 16065.3 17392.0 18732.4 20075.6 21415.2 22750.6 24092.9 24980.8

Most critical fuel amount for most forward flight condition. NOTE:All data aboverepresentsusable fuel based on nominaldensity at 15°C(59°F). (TABLE

I.D. 911329)

5-17

MANUFACTURER'S DATA

BHT-212VFR-FM-1

SAMPLE LOADING PROBLEM (ENGLISH UNITS) HELICOPTER SERIAL NUMBERS PRIOR TO 35049 FIRST LEG WEIGHT (LBS)

CO

+Oil +Pilot +Passengers (5 man seat) +Passengers (4 man seat) +Baggage Basic Operating Weight + Payload Basic Operating Weight + Payload +Takeoff Fuel (216.8 gallons Type B)

CG (INCHES)

MOMENT (IN-LBS)

24.5 *170.0

4146 7990

*850.0 *680.0 180.0

99450 59160 46980

8433.9

1157722

8433.9

1157722 216000

'1409.0 139.6

1373722

Takeoff Weight, CG & Moment

9842.9

Basic Operating Weight + Payload

8433.9

1157722

+Critical Fuel (72.6 gallons Type B)

*472.0

60227

Critical Weight, CG & Moment

8905.9

Basic Operating Weight + Payload

8433.9

+Landing Fuel (60 gallons Type B)

*390.0

Landing Weight, CG & Moment

8823.9

136.8

1217949 1157722 50466

136.9

1208188

(* Information obtained from loading charts) (TABLE I.D. 911217)

5-18

MANUFACTURER'S DATA

BHT-212VFR-FM-1

SAMPLE LOADING PROBLEM (ENGLISH UNITS) HELICOPTER SERIAL NUMBERS PRIOR TO 35049 SECOND LEG WEIGHT (LBS)

CG (INCHES)

MOMENT (IN-LBS)

Licensed Empty Weight

6529.4

939996

+Oil +Pilot Basic Operating Weight (No Payload)

24.5 170.0 6723.9

4146 7990 952132

+Takeoff Fuel (216.8 gallons Type B)

*1409.0

216000

Takeoff Weight, CG & Moment

8132.9

Basic Operating Weight (No Payload)

6723.9

952132

+Critical Fuel (72.6 gallonsType B)

*472.0

60227

Critical Weight, CG & Moment

7195.9

Basic Operating Weight (No Payload)

6723.9

+Landing Fuel (60 gallons Type B)

'390.0

Landing Weight, CG & Moment

7113.9

143.6

140.7

1168132

1012359 952132 50466

140.9

1002598

(TABLE I.D. 911218)

5-19

MANUFACTURER'S DATA

BHT-212VFR-FM-1

SAMPLE LOADING PROBLEM (METRIC UNITS) HELICOPTER SERIAL NUMBERS PRIOR TO 35049 FIRST LEG WEIGHT (KG)

CG (MM)

MOMENT (KG.MM 100)

2961.7

108298.7

11.1 *90.0

477.7 1074.6

+Passengers (5 man seat) +Passengers (4 man seat) +Baggage

*375.0 *300.0 *80.0

11145.0 6630.0 5295.2

Basic Operating Weight + Payload Basic Operating Weight + Payload

3817.8 3817.8

132921.2 132921.2

Licensed Empty Weight +Oil +Pilot

+Takeoff Fuel (820.7 liters Type B)

24894.3

*639.3

Takeoff Weight, CG & Moment

4457.1

Basic Operating Weight + Payload

3817.8

132921.2

+Critical Fuel (274.8 liters Type B)

*214.1

6939.0

Critical Weight, CG & Moment

4031.9

Basic Operating Weight + Payload +Landing Fuel (227.1 liters Type B) Landing Weight, CG & Moment

3541

157815.5

3469

139860.2 132921.2

3817.8 *176.9 3994.7

5814.5 3473

138735.7

(* Information obtained from loading charts) (TABLE

5-20

I.D.

911219)

BHT-212VFR-FM-1

MANUFACTURER'S DATA

SAMPLE LOADING PROBLEM (METRIC UNITS) HELICOPTER SERIAL NUMBERS PRIOR TO 35049 SECOND LEG

WEIGHT (KG) Licensed Empty Weight

CG (MM)

2961.7

MOMENT (KG MM 100) 108298.7

11.1

477.7

*90.0

1074.6

Basic Operating Weight (No Payload)

3062.8

109851.0

+Takeoff Fuel (820.7 liters Type B)

*639.3

24894.3

Takeoff Weight, CG & Moment

3702.1

Basic Operating Weight (No Payload) +Critical Fuel (274.8 liters Type B)

3062.8

109851.0

214.1

6939.0

Critical Weight, CG & Moment

3276.9

Basic Operating Weight (No Payload)

3062.8

+Oil

+Pilot

+Landing Fuel (227.1 liters Type B) Landing Weight, CG & Moment

3640

3564

116790.0 109851.0 5814.5

176.9 3239.7

134745.3

3570

115665.5 (TABLE I.D. 911220)

5-21

MANUFACTURER'S DATA

BHT-212VFR-FM-1

SAMPLE LOADING PROBLEM (ENGLISH UNITS) HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT FIRST LEG WEIGHT (LBS) Licensed Empty Weight +011 +Pilot +Passengers (5 man seat) +Passengers (4 man seat) +Baggage Basic Operating Weight + Payload Basic Operating Weight + Payload +Takeoff Fuel (218.6 gallons Type B)

MOMENT (IN-LBS)

6529.4

939996

24.5 '170.0 *850.0 *680.0 *180.0

4146 7990 99450 59160 46980

8433.9

1157722

8433.9

1157722

*1421.0

Takeoff Weight, CG & Moment

9854.9

216829 139.5

1374551 1157722

8433.9

Basic Operating Weight + Payload +Critical Fuel (78.5 gallons Type B)

CG (INCHES)

64955

*510.0 136.7

1222677

Critical Weight, CG & Moment

8943.9

Basic Operating Weight + Payload

8433.9

1157722

+Landing Fuel (60 gallons Type B)

*390.0

50661

Landing Weight, CG & Moment

8823.9

136.9

1208383

(* Information obtained from loading charts) (TABLE

5-22

I.D. 911328)

MANUFACTURER'S DATA

BHT-212VFR-FM-1

SAMPLE LOADING PROBLEM (ENGLISH UNITS) HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT SECOND LEG WEIGHT (LBS)

CG (INCHES)

MOMENT (IN-LBS)

Licensed Empty Weight

6529.4

939996

+Oil +Pilot Basic Operating Weight (No Payload)

24.5 *170.0 6723.9

4146 7990 952132

+Takeoff Fuel (218.6 gallons Type B)

*1421.0

Takeoff Weight, CG & Moment

8144.9

Basic Operating Weight (No Payload)

6723.9

+Critical Fuel (78.5 gallonsType B)

*510.0

Critical Weight, CG & Moment

7233.9

Basic Operating Weight (No Payload)

6723.9

+Landing Fuel (60 gallons Type B)

*390.0

Landing Weight, CG & Moment

7113.9

216829 143.5

1168961 952132 64955

140.6

1017087 952132 50661

141.0

1002793

(TABLE I.D. 911327)

5-23

MANUFACTURER'S DATA

BHT-212VFR-FM-1

SAMPLE LOADING PROBLEM (METRIC UNITS) HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT FIRST LEG WEIGHT (KG)

CG (MM)

MOMENT (KG-MM 100)

2961.7

108298.7

11.1 *90.0

477.7 1074.6

(5 man seat) +Passengers +Passengers (4 man seat) +Baggage

*375.0 *300.0 *80.0

11145.0 6630.0 5295.2

Basic Operating Weight + Payload Basic Operating Weight + Payload

3817.8 3817.8

132921.2 132921.2

+Takeoff Fuel (827.4 liters Type B)

*644.5

24980.8

Takeoff Weight, CG & Moment

4462.3

Basic Operating Weight + Payload

3817.8

+Critical Fuel (297.1 liters Type B)

'231.4

Critical Weight, CG & Moment

4049.2

Licensed Empty Weight +011 +Pilot

Basic Operating Weight + Payload

3817.8

+Landing Fuel (227.1 liters Type B)

*176.9

Landing Weight, CG & Moment

3994.7

3539

157902.0 132921.2 7481.2

3467

140402.4 132921.2 5838.8 138760.0

3474

(* Information obtained from loading charts) (TABLE

5-24

I.D. 911326)

MANUFACTURER'S DATA

BHT-212VFR-FM-1

SAMPLE LOADING PROBLEM (METRIC UNITS) HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT SECOND LEG

WEIGHT (KG)

CG (MM)

MOMENT (KG MM 100)

Licensed Empty Weight

2961.7

108298.7

+Oil +Pilot Basic Operating Weight (No Payload)

11.1 *90.0 3062.8

477.7 1074.6 109851.0

+Takeoff Fuel (827.4 liters Type B) Takeoff Weight, CG & Moment Basic Operating Weight (No Payload) +Critical Fuel (297.1 liters Type B)

*644.5 3707.3

Basic Operating Weight (No Payload)

3062.8

7481.2 3562

117332.2 109851.0

*176.9 3239.7

134831.8 109851.0

3062.8

3294.2

Landing Weight, CG & Moment

3637

*231.4

Critical Weight, CG & Moment

+Landing Fuel (227.1 liters Type B)

24980.8

5838.8 3571

115689.8 (TABLE I.D. 911325)

5-25/5-26

BHT-212VFR-FM-1

MANUFACTURER'S DATA

Appendix A EQUIPMENT A-1. OPTIONAL

or install such changes, additions, improvements, etc., on products

Bell Helicopter Textron's policy is one of continuous product improvement. Bell reserves the right to incorporate design changes, make additions to, and improve

manufactured. previously previously manufactured Flight manual supplement for each kit listed in table A-1 must be carried in helicopter at all times if subject kit is

its product without imposing any obligation upon the company to furnish for Table A-1.

installed

FLIGHT MANUAL SUPPLEMENTS FAA APPROVED

REVISION NO.

205-706-047

01 MAR 72

Reissue 14 AUG 95

BHT-212-FMS-2 Winterization Heater

212-706-008

29 OCT 70

Reissue 14 AUG 95

BHT-212-FMS-3 Cargo Hook

212-706-103

29 OCT 70

Revision 1 12 SEP 97

BHT-212-FMS-4 Auxiliary Fuel Tanks

205-706-044 205-706-045

29 OCT 70

Revision 1 12 SEP 97

BHT-212-FMS-5 Internal Rescue Hoist (Breeze)

205-706-030

01 MAR 71

Reissue 14 AUG 95

BHT-212-FMS-6 Fixed Floats

205-706-050

01 APR 71

Reissue 14 AUG 95

18 AUG 72

Revision 1 12 SEP 97

NAME OF EQUIPMENT

KIT NUMBER

BHT-212-FMS-1 Litters

BHT-212-FMS-7 Category A Operations BHT-212-FMS-8 Emergency Flotation

212-706-021

28 AUG 72

Reissue 14 AUG 95

BHT-212-FMS-9 Emergency Flotation

212-706-042

09 AUG 73

Reissue 14 AUG 95

BHT-212-FMS-10.1

Incorporated into

Battery Temperature Sensor

basic manual.

Rev. 2

A-1

BHT-212VFR-FM-1

MANUFACTURER'S DATA Table A-1.

FLIGHT MANUAL SUPPLEMENTS (Cont)

NAME OF EQUIPMENT

KIT NUMBER

BHT-212-FMS-10.2

Incorporated into

Battery Temperature

basic manual.

FAA APPROVED

REVISION NO.

Sensor BHT-212-FMS-11 VLF-1000 Navigation System

212-899-118

21 MAY 74

Reissue 14 AUG 95

BHT-212-FMS-12 Heated Windshield

212-899-244

03 JUN 74

Reissue 14 AUG 95

BHT-212-FMS-13 Environmental Control Unit

212-706-025 (30597 and sub)

17 JUN 74

Reissue 14 AUG 95

BHT-212-FMS-14 20/90 Auxiliary Fuel

212-899-243

30 OCT 74

Reissue 14 AUG 95

BHT-212-FMS-15 212-899-131 KNC 610 Area Navigation System

20 NOV 74

Reissue 14 AUG 95

BHT-212-FMS-16 Heated Windshield

212-706-053 (30554 and sub)

01 NOV 74

Reissue 14 AUG 95

BHT-212-FMS-17 Internal Rescue Hoist (Western Gear)

214-706-003

20 NOV 75

Reissue 14 AUG 95

BHT-212-FMS-18 AFCS/Autopilot

212-961-620 (30597 thru 30849)

15 DEC 76

Reissue 14 AUG 95

BHT-212-FMS-19 AFCS/Autopilot

212-706-111 (30850 and sub)

14 JUN 77

Reissue 14 AUG 95

BHT-212-FMS-20 Altitude Hold System

212-899-143

12 DEC 77

Reissue 14 AUG 95

BHT-212-FMS-21

212-899-375

29 JAN 80

Reissue 14 AUG 95

Tanks

Crash Position Indicator (Argentine Air Force) BHT-212-FMS-22 Transmission

212-040-001-131

BHT-212-FMS-23

Incorporated into

PT6T-3B Engine

basic manual

A-2

Rev. 2

MANUFACTURER'S DATA

BHT-212VFR-FM-1

Table A-1.

FLIGHT MANUAL SUPPLEMENTS

NAME OF EQUIPMENT

KIT NUMBER

BHT-212-FMS-24 Seat Cushion BHT-212-FMS-25 Fixed Step

(Cont)

FAA APPROVED

REVISION NO.

212-706-019

24 JUL 87

Reissue 14 AUG 95

212-706-057

27 SEP 89

Reissue 14 AUG 95

09 NOV 89

Reissue 14 AUG 95

BHT-212-FMS-28 214-706-003 Two-Speed Internal Hoist

07 MAY 92

Reissue 14 AUG 95

BHT-212-FM-29 Increased Takeoff

212-704-153

16 DEC 91

Reissue 14 AUG 95

BHT-212-FMS-30 Airline Passenger Seating

412-706-028

18 JUN 93

Reissue

BHT-212-FMS- 31

Reserved

BHT-212-FMS-32

TB 212-93-145

28 JUL 94

Original 28 JUL 94

212-899-234

07 OCT 94

Original 07 OCT 94

BHT-212-FMS-34 212-899-835 TRIMPAC GPS Navigator

07 OCT 94

Reissued 24 FEB 95

BHT-212-FMS-35

212-704-129

22 MAR 96

Original

Increased Weight Altitude Temperature Limit

212-704-153

BHT-212-FMS-CAN-26 Internal Rescue Hoist and Cargo Hook

BHT-212-FMS-27 Alternate Static Air

Incorporated into basic manual

Valve

Horsepower

14 AUG 95

Engine No. 2 Governor

Trim Actuator BHT-212-FMS-33 Bendix/King RDS 81 Weather Radar

issue

Rev. 2

A-3/A-4

BHT-212-FMS-1

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

LITTERS 205-706-047 CERTIFIED MARCH 1, 1972

This supplement shall be attached to the Bell Helicopter Model 212 Flight Manual when litter kit has been installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter COPYRIGHT NOTICE COPYRIGHT 1995

A Subsidiary ol Textron Inc

BELL ® HELICOPTERINC1

POSTOFFICE BOX 42·

ANDBELLHELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD ALLRIGHTS RESERVED

REISSUE -

FORT WOPITH.TEXAS 76101

14 AUGUST 1995

BHT-212-FMS-1

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. O. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-1

FAA APPROVED LOG OF REVISIONS

Original...........0

.............

01 MAR 72

Revision .......... Reissue...........0

1 .............. .............

07 NOV 80 14 AUG 95

LOG OF PAGES

a*

REVISION NO.

PAGE

A-B

FLIGHTMANUAL Title -NP

..............................

*^^kb~~

0

REVISION NO.

PAGE

..................................

0

0 1-2 ...................................

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-1

FAA APPROVED LOG OF APPROVED

Original...........0

Revision....... Reissue...........

............

.............. 0.............

01 MAR 72

07 NOV 80 14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

REVISIONS

FAA APPROVED

BHT-212-FMS-1

Section

1-4.

1

FLIGHT CREW

1-6. WEIGHT AND CENTER OF GRAVITY

Minimum flight crew for litter operations shall

consist

of a pilot

and a second

crewmember or cabin attendant, both of whom shall be trained in and capable of

assisting

in litter patient emergency

Actual weight change shall be determined

after litter kit is installed and ballast readjusted,

if necessary,

to return empty

weight CG to within allowable limits.

evacuation procedures.

Section 2 2-3.

PREFLIGHT CHECK

can be opened.

Refer to Section

3, Emergency and Malfunction

Procedures for unloading Secure

patient(s)

to litter(s),

then load

litter(s) aboard helicopter in sequence from top to bottom. When only two patients are carried, they should occupy top and center litter positions. When only one patient is carried, center litter position should be used.

2-12.

POSTFLIGHT

procedures when passenger

doors can not be opened.

Open passenger door and unload litters and patients from helicopter in sequence from bottom to top.

CHECK

NOTE

Normal unloading procedures apply when either passenger door 1

FAA APPROVED

BHT-212-FMS-1

Section 3 EMERGENCY PROCEDURES

3-1.

3-1-B. DOORS WITH EMERGENCY

INTRODUCTION

Litter patients can be unloaded through

passenger door emergency exits in

accordance with procedures specified below for appropriate passenger door configuration in event passenger doors can not be opened. After all litter patients have been removed, ambulatory patients may then exit. 3-1-A.

DOORS WITH EMERGENCY

EGRESS PANELS Remove emergency egress panel. Secure patients to litters, then unload litters through emergency exit in sequence from bottom to top.

PUSH OUT WINDOWS Remove emergency push out window. Unstrap patient on center litter and remove patient through window opening. Disconnect top litter at end near open window and lower end to rest on center

litter. Remove patient retention straps and slide patient down litter and out through window opening. Raise top and center litter ends near open window and engage center litter in

brackets for top litter.

Raise bottom

litter at end near open window and rest

handles on lower surface of window opening. Unstrap patient and slide patient up litter and through window opening.

Section 4 No change from basic manual.

2

BHT-212-FMS-2

ROTORCRAFT FLIGHT MANUAL

0b

~SUPPLEMENT

WINTERIZATION HEATER 212-706-008 CERTIFIED OCTOBER 29, 1970

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when winterization heater is installed.

Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

NOTICE COPYRIGHT COPYRIGHT 1995 BELL HELICOPTER INC. ANDBELLHELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD. RESERVED ALLRIGHTS

otTextron Inc. A Subsidiary POSTOFFICEBOX4U2. FORTWORTH. TEXAS76101

REISSUE -

14 AUGUST 1995

BHT-212-FMS-2

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

BHT-212-FMS-2 LOG OF REVISIONS

Original .......... Revision..........1 Revision ..........

..............

29 OCT 70

Revision ..........

3 ..............

07 APR 93

.............. 2 .............

07 DEC 71 07 MAR 80

Reissue...........0

.............

14 AUG 95

LOG OF PAGES REVISION PAGE

NO. FLIGHT MANUAL

Title - NP..............................

*&

0

REVISION PAGE A1-

B .................................. 16 ..................................

NO. 0 0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-2 LOG OF APPROVED

REVISIONS

Original ...........

0 ..............

29 OCT 70

Revision ..........

3 ..............

07 APR 93

Revision..........1 Revision..........2

.............. .............

07 DEC 71 07 MAR 80

Reissue...........0

.............

14 AUG 95

APPROVED:

MANAGER

/ ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

BHT-212-FMS-2

FAA APPROVED

Section

1

1-6. WEIGHT AND CENTER OF GRAVITY

1-21.

HEATER

Actual weight change shall be determined

above 21°C.

Heater shall not operate when OAT is

after winterization heater kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

Section 2 INTERIOR AND

2-4.

PRESTART CHECK CABIN HTR circuit breaker BATTERY switch -

In.

NOTE Bleed air heater check in Basic Flight Manual is also applicable to winterization heater.

ON DC BUS 2.

SYSTEM SELECTOR switch - HEATER; check HEATER AIR LINE caution light illuminates, then switch to OFF.

2-6.

SYSTEMS CHECK

2-6-A. HEATER OPERATION CHECK

Do not operate heater above 21°C OAT. 1

FAA APPROVED

BHT-212-FMS-2

Section 3 No change from basic manual.

Section 4 NOTE

All HEATER OFF performance charts in Basic Flight Manual are when applicable heater is OFF.

winterization

4-6.

Takeoff distance chart in Basic Flight Manual is applicable to either winterization heater or bleed air heater.

4-7. 4-5.

HOVER CEILING

In ground effect (IGE) Hover Ceiling charts in Basic Flight Manual are applicable to either winterization heater or bleed air heater.

Charts for out of ground effect (OGE) hover ceiling with winterization heater ON are presented in figure 4-1.

2

TAKEOFF DISTANCE

CLIMB AND DESCENT

Charts for Twin Engine Rate of Climb with winterization heater ON are presented in figure 4-2.

BHT-212-FMS-2

FAA APPROVED

HOVER CEILING OUT OF GROUND TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

EFFECT SKID HEIGHT 60 FEET WINTERIZATION HEATER ON 0° TO 20°C

14,000 FT. DEN. ALT. LIMIT

-- OAT- °C--

0

10 20 30 40 50 OAT - 'C

12 10 11 9 8 (3.63) (4.08) (4.54) (4.99) (5.44) GROSS WEIGHT - LBS (kg) X 1000

2i2-FS2-4-1-1

Figure 4-1.

Hover ceiling out of ground effect (Sheet 1 of 4)

3

BHT-212-FMS-2

FAA APPROVED

HOVER CEILING OUT OF GROUND

TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

0

EFFECT

SKID HEIGHT 60 FEET WINTERIZATION HEATER ON 0 ° TO -54°C

14,000 FT. DEN ALT LIMIT

-60-50-40-30-20-10 OAT - °C 212-FS2-4-1-2

Figure 4-1.

4

0

8 9 (3.63) (4.08)

10 (4.54)

11 12 (4.99) (5.44)

GROSS WEIGHT - LBS (kg) X 1000 Hover ceiling out of ground effect (Sheet 2 of 4)

FAA APPROVED

BHT-212-FMS-2

HOVER CEILING OUT OF GROUND

MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

EFFECT

SKID HEIGHT 60 FEET WINTERIZATION HEATER ON 0 ° TO 20°C

14.000 FT DEN. ALT LIMIT

OAT-

C

20

0

10 20 30 40 50 OAT - C

8 9 10 11 12 (3.63) (4.08) (4.54) (4.99) (5.44) GROSS WEIGHT - LBS (kg) X 1000

212-FS2-4-1-3

Figure 4-1.

Hover ceiling out of ground effect (Sheet 3 of 4)

5

BHT-212-FMS-2

FAA APPROVED

HOVER CEILING OUT OF GROUND

MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

EFFECT

SKID HEIGHT 60 FEET WINTERIZATION HEATER ON 0° TO-54°C

14,000 FT. DEN. ALT. LIMIT

OAT -

°C

__

-60-50-40-30-20-10 08 OAT - °C 212-FS2-4-1-4

Figure 4-1.

9

10

11

12

(3.63) (4.08) (4.54) (4.99) (5.44) GROSS WEIGHT - LBS (kg) X 1000

Hover ceiling out of ground effect (Sheet 4 of 4)

FAA APPROVED

BHT-212-FMS-2

TWIN ENGINE RATE OF CLIMB WITH ALL DOORSOPEN. RATE OF CLIMB WILL DECREASE200 FT/MIN. TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

KCAS 55 WINTERIZATION HEATER ON

GROSS WEIGHT 7000 LB. 20.000

18.000

OAT 40"C

16.000

80 0 0

2000

0

400

800

1200

1600

RATE OF CLIMB -

Figure 4-2.

2000

FT/MIN

2400

2800

3200

212-FS2-4-2-1

Twin engine rate of climb chart (Sheet 1 of 10)

7

BHT-212-FMS-2

FAA APPROVED

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN,RATE OF CLIMB WILL DECREASE200 FT/MIN. TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

55 KCAS WINTERIZATION HEATER ON

GROSS WEIGHT 8000 LB. 20.000 40°C

18,000

30°C

OAT

16.000

0

Figure 4-2.

8

400

800

1200 1600 2000 2400 RATE OF CLIMB- FT/MIN212-FS2-4-2-2

2800

Twin engine rate of climb chart (Sheet 2 of 10)

FAA APPROVED

BHT-212-FMS-2

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF

CLIMB WILL DECREASE200 FT/MIN. TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

55 KCAS WINTERIZATION HEATER ON

GROSS WEIGHT 9000 LB. 20,000

18,000

400

8000 8.000

4000

2000

0

400

800

1200 RATE

Figure 4-2.

OF

1600 CLIMB

-

*

2000

FT/MIN

2400

2800 212-FS2-4-2

Twin engine rate of climb chart (Sheet 3 of 10)

9

FAA APPROVED

BHT-212-FMS-2

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN,RATE OF CLIMB WILL DECREASE200 FT/MIN. TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

55 KCAS WINTERIZATION HEATER ON

GROSS WEIGHT 10,000 LB. 20.000

16.000

Figure 4-2. 2000

0

212-FS2-4Twin engine rate of climb chart (Sheet 4 of 10) 400

800 160000

1200 200

1600

OF CLIMB CLIMB RATE OF

Figure 4-2.

10

2000 FT/MIN

2400

2800 212-FS2-4-2-4

Twin engine rate of climb chart (Sheet 4 of 10)

FAA APPROVED

BHT-212-FMS-2

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATEOF CLIMB WILL DECREASE200 FT/MIN. TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

55 KCAS WINTERIZATION HEATER ON

GROSS WEIGHT 11,200 LB.

18,000

14,000

12,000

8000

000

_ 0

200

400

600

800

1000

RATEOF CLIMB- FT/MIN

Figure 4-2.

1200

1400 212-FS2-4-2-5

Twin engine rate of climb chart (Sheet 5 of 10)

11

BHT-212-FMS-2

FAA APPROVED

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF

CLIMB WILL DECREASE200 FT/MIN. MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

55 KCAS WINTERIZATION HEATER ON

GROSS WEIGHT 7000 LB.

14.000

12.000 4000 20000

Figure 4-2.

12

400

800

1200 OF CLIMB 1600 RATE

2400 2000 FT/MIN2S4-2-6

2800

Twin engine rate of climb chart (Sheet 6 of 10)

FAA APPROVED

BHT-212-FMS-2

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN.RATE OF CLIMB WILL DECREASE200 FT/MIN. MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

55 KCAS WINTERIZATION HEATER ON

GROSS WEIGHT 8000 LB. 20.000

12.000 12.000

10.000

8000

0

400

800

1200

1600

RATE OF CLIMB -

Figure 4-2.

FT/MIN

2000

2400 212-FS2-4-2-7

Twin engine rate of climb chart (Sheet 7 of 10)

13

BHT-212-FMS-2

FAA APPROVED

TWIN ENGINE RATE OF CLIMB WITH ALL DOORSOPEN. RATEOF CLIMB WILL DECREASE200 FT/MIN. MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

55 KCAS WINTERIZATION HEATER ON

GROSS WEIGHT 9000 LB. 20.000

18.000

212-F62-4-2-8

RATE OF CLIMB - FT/MIN

4.000 8000 6000

4000

2000

400

200 1600 2000 RATE OF CLIMB- FT/MIN

oo00

2400 212-FS2-4-2-8

Figure 4-2. Twin engine rate of climb chart (Sheet 8 of 10)

14

FAA APPROVED

BHT-212-FMS-2

TWIN ENGINE RATE OF CLIMB WITH ALL DOORSOPEN, RATE OF CLIMB WILL DECREASE200 FT/MIN. MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

i

_____ ~~GROSS

55 KCAS WINTERIZATION HEATER ON

WEIGHT 10.000 LB.

20.000

Figure 4-2.

Twin engine rate of climb chart (Sheet 9 of 10)

15

BHT-212-FMS-2

FAA APPROVED

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF

CLIMB WILL DECREASE200 FT/MIN. MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

55 KCAS WINTERIZATION HEATER ON

GROSS WEIGHT 11,200 LB.

14,000

4000

---

<

RATE OF CLIMB

__ _ _

FT/MIN.

212-FS2-4-2-10

Figure 4-2.

16

Twin engine rate of climb chart (Sheet 10 of 10)

BHT-212-FMS-3

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

CARGO HOOK 212-706-103 CERTIFIED

OCTOBER 29,1970 This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when cargo hook kit has been

installed.

Information contained herein supplements information of basic Flight Manual. For Limitations,

Procedures, and

Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter NOTICE COPYRIGHT COPYRIGHT 1997 INC. BELL e HELICOPTER TEXTRON ANDBELLHEUCOPTER TEXTRON INC.

of Textron Inc. A Subsidiary TEXAS 76101 . FORTWORTH. POSTOFFICEBOX 482

14 AUGUST 4 AUGUST

A DIVISION OFTEXTRON CANADA LTD. ALLRIGHTS RESERVED

REVISION 1 -

12 SEPTEMBER

1995

1995 1997

BHT-212-FMS-3 NOTICE PAGE

PROPRIETARY RIGHTS NOTICE

Manufacturer's Data portion of this supplement 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.

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-3 LOG OF REVISIONS

Original ........... Revision..........1

Revision ..........

29 OCT 70

Revision .......... 3 ..............

01 OCT 84

..............

07 DEC 71

Reissue ...........

14 AUG 95

2 .............

21 MAR 80

Revision ..........

0 ..............

0.............

..............

12 SEP 97

LOG OF PAGES REVISION PAGE

REVISION

NO.

PAGE

FLIGHT MANUAL

Title.....................................

1

NP ......................................

0

i/ii ......................................

0

2...................................0

4A/4B ...................................

1

5 - 22 ..................................

0

MANUFACTURER'S DATA

A- B..................................1 1-

NO.

23 -

24.................................

0

0

25/26....................................

3-4 ...................................1

NOTE

Revised text is Indicated by a black vertical line. Insert latest revision pages; dispose of superseded

pages. Rev.1

A

BHT-212-FMS-3 LOG OF FAA APPROVED

REVISIONS

Original...........0

..............

29 OCT 70

Revision ..........

3 ..............

01 OCT 84

Revision..........1

..............

07 DEC 71

Reissue ...........

.............

14 AUG 95

2 .............

21 MAR 80

Revision..........1

..............

12 SEP 97

Revision ..........

APPROVED:

MANAGER

ROTORCRAFT CERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

Rev.1

DATE:

BHT-212-FMS-3

FAA APPROVED GENERAL INFORMATION

External cargo suspension hook, when installed, will permit operator to utilize

helicopter for transportation of external cargo, when operated by a qualified pilot.

i//

FAA APPROVED

BHT-212-FMS-3

Section 1-3.

1

TYPES OF OPERATION

1-6-A.

WEIGHT

Operation of the helicopter with no load on the external cargo suspension hook is

Maximum external cargo load is 5000 pounds and shall not exceed GW listed in

airworthiness certificate under VFR or IFR conditions without removing the unit from

1-6-B.

authorized

the helicopter. the The installation

under the standard helicopter.

BasicFlightManual.

CENTER OF GRAVITY

Refer to Gross Weight Center Of Gravity

and use of the rear view

mirror contained in the kit is left to operators discretion. The rear view mirror shall be covered or

chart in Basic Flight Manual.

Refer to Weight-altitude-temperature limitations chart in Basic Flight Manual for takeoff and landing weight limits.

removed for night flight. 1-3-C.

NOTE

Refer to Section

VFR OPERATION

performance variation altitude and temperature.

With a load attached to the suspension

4 for with

AIRSPEED

assembly, operation shall be conducted in

1-7.

rules

VNE Is 80 knots at or below 10,000 feet HD

accordance with appropriate operating for

external

conditions. 1-3-D.

loads

under

VFR

IFR OPERATION

for all GW with external cargo on suspension unit. Decrease VNE3 knots per thousand feet above 10,000 feet H,.

External load operations are permitted

t CAUTION

provided the operator substantiates to the

,,C..........

Administrator that the rotorcraft - load combinations meets IFR handling

requirements and insures that the Rotorcraft External Load Operator Certificate reflects same with appropriate restrictions.

1-6.

WEIGHT AND CENTER OF

GRAVITY

AIRSPEED

WITH EXTERNAL

CARGO IS LIMITED BY CONTROLLABILITY. CAUTION SHOULD BE EXERCISED WHEN CARRYING EXTERNAL CARGO AS HANDLING CHARACTERISTICS MAY BE AFFECTED DUE TO SIZE, WEIGHT, AND SHAPE OF CARGO

LOAD

Actual weight change shall be determined after cargo hook kit is installed and ballast readjusted, if necessary, to return empty

1-20. INSTRUMENT MARKINGS AND PLACARDS

weight CG to within allowable limits.

Refer to figure 1-1. 1

BHT-212-FMS-3

FAA APPROVED

OCCUPANCY LIMITED TO CREW WITH EXTERNAL LOAD CLASS B LOADING APPROVED

(Located on forward right side of overhead console)

CARGo RELEASE

(Light) ARMED 0

(Located on instrument panel)

EXTERNAL LOAD LIMIT 5000 LBS

(Located on under side of helicopter near suspension assembly) 212.FMS3-1-1

Figure 1-1. 2

Placards and decals

BHT-212-FMS-3

FAA APPROVED

Section 2

.

2-2.

FLIGHT PLANNING

WARNING

Instruct ground personnel to discharge

helicopter static electricity, before attaching cargo sling, by touching airframe with a ground wire. If a metal sling is used, hook up ring can be struck against

cargo hook to discharge static electricity.

If contact has been lost after initial

grounding, helicopter should beLAR

USE OF INAPPROPRIATELY SIZED LOAD RINGS MAY RESULT IN LOAD HANG-UP WHEN LOAD

RING

IS TOO

SMALL

OR

ASE

electrically regrounded and, If possible, contact maintained until hook up is

LOAD RING IS TOO LARGE. REFER TO WARNING PLATE ON

complete.

CARGO HOOK.

2-3. PREFLIGHTCHECK Cargo hook -

Check that only one primary ring is captured in the load beam and only one

Condition and security.

Check primary load ring and secondary load ring for condition and proper size (Table 2-1). Check for correct rigging.

secondary ring with correct crosssection dimension is captured in the primary ring. Additional rings, slings, or shackles shall be attached to the secondary load ring.

See figure 2-1.

Rear view mirror (if installed) -

Secure

and clean.

Table 2-1.

O

RING SIZES -

CARGO HOOK WITH LONG LOAD BEAM.

PRIMARY RING INSIDE DIAMETER

PRIMARY RING CROSS SECTION

MAXIMUM CROSS SECTION OF SECONDARY RING

3.0 to 3.1 in. (76.2 to 78.7 mm.)

1.0 In. (25.4 mm.)

0.625 in. (15.9 mm.)

3.1 to 4.0 In. (78.7 to 101.6 mm.)

1.0 In. (25.4 mm.)

0.75 in. (19.0 mm.)

Rev.1

3

BHT-212-FMS-3 Table 2-2.

FAA APPROVED RING SIZES -

CARGO HOOK WITH SHORT LOAD BEAM.

PRIMARY RING INSIDE DIAMETER

PRIMARY RING CROSS SECTION

MAXIMUM CROSS SECTION OF SECONDARY RING

2.38 to 2.5 (60.5 to 63.5 mm.)

1.0 in. (25.4 mm.)

0.625 in. (15.9 mm.)

2.5 to 2.75 in. (63.5 to 69.8 mm.)

1.0 in. (25.4 mm.)

0.75 in. (19.0 mm.)

4

Rev.1

FAA APPROVED

BHT-212-FMS-3

CORRECT RIGGING

*

CROSS-SECTION OF

DIMENSIONS ARE SHOWN IN

SECONDARYRING

TO LOAD(S)

INCORRECT RIGGING

INCORRECT RIGGING

BEAM

PRIMARYRING

MULTIPLE

LOAD

Rev. 1

4A/4B

FAA APPROVED

BHT-212-FMS-3

2-4. INTERIORAND PRESTART CHECK

operations.

Refer to Critical

Relative Wind Azimuths for Hover Flight illustration in Section 4.

CARGOHOOK REL circuit breaker - In.

Hover helicopter at sufficient height to allow ground personnel to discharge static electricity and to attach cargo

BATTERY switch -

sling to cargo hook.

CARGO

ON DC BUS 1.

REL switch

-

CARGO RELEASE illuminates.

ARM;

check

ARMED

light Attachment of cargo sling to cargo hook can be observed by

Cyclic CARGO RELEASE switch -

Press

and hold; pull down on cargo hook, hook should open.

NOTE

Release switch and

cargo hook; hook should close and lock.

means of rear view mirror.

Ascend vertically directly over cargo,

then slowly lift cargo from surface.

Pedals - Check for adequate directional Cargo release pedal -

Push and hold;

pull down on cargo hook, hook should open. Release pedal and cargo hook; hook should close and lock.

Pedal release will function regardless of CARGO REL switch

position.

BEFORE TAKEOFF

Cargo cargo.

Secured; sling attached to

Ground personnel -

Positioned as

required.

hover with external load.

2-9. IN-FLIGHT OPERATIONS NOTE NOTE Control movements should be made smoothly and kept to a minimum to prevent oscillation of sling load. CARGO REL switch -

Airspeed -

CARGO REL switch -

ARM; check

CARGO RELEASE ARMED light illuminates.

2-8.

Hover power - Check torque required to Take off into wind if possible, allowing adequate sling load clearance over obstacles.

NOTE

2-7.

control.

OFF.

Within limits for adequate

controllability of rotorcraft-load configuration.

Flight path - As required to avoid flight with external load over any person, vehicle, or structure.

TAKEOFF NOTE

Avoid critical relative winds while

performing external cargo 5

BHT-212-FMS-3

FAA APPROVED

2-10. DESCENTAND LANDING LANDING

slowly until cargo contacts surface. Maintain tension on sling.

CARGO RELEASE switch CARGO REL switch - ARM prior to final approach. Flight

path and approach

Press to

release cargo sling from cargo hook. NOTE

NOTE angle -

As

required for wind direction and obstacle clearance.

Release of cargo sling from cargo

hook can be confirmed visually through rear view mirror.

Terminate approach to a high hover. When stabilized at a hover, descend

Section 3 3-15. CARGO FAILS TO

Maintain tension on cargo sling.

RELEASE ELECTRICALLY

Cargo release pedal -

Push.

In the event cargo hook will not release cargo sling when CARGO RELEASE switch is pressed, proceed as follows:

Section 4 4-5.

HOVER CEILING

performance shown in Basic Flight Manual

is reduced to ensure adequate tail rotor

In ground effect (IGE) and out of ground

control margins in relative winds up to 20

effect (OGE) hover ceiling charts (figures 4-1 and 4-2) are based upon engine

knots from any direction. Caution, therefore, should be exercised when

manufacturer's minimum specification power for PT6T-3 or PT6T-3B engine with

hovering at high GW and high HD , as tail rotor control margins may not be available,

maximum hovering capability

relative wind azimuth area (figure 4-3).

installation losses. These charts reflect of helicopter

in zero wind conditions, whereas hover 6

particularly when winds are within critical

FAA APPROVED

BHT-212-FMS-3

HOVER CEILING IN GROUND EFFECT TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

SKID HEIGHT 4 FEET HEATER OFF

20,000

16.000

(OATLIMIT)20C

14,000

12,000 (OAT LIMT) 30C

10,000 10,000

,00

6000

2000

(OAT LIMIT) 40'C

°

(OAT LIMIT)50 C

6000

7000

8000

9000

10,000

11.200

GROSSWEIGHT - POUNDS

212-FMS3-4-1-1

Figure 4-1.

Hover ceiling in ground effect (Sheet 1 of 6)

7

FAA APPROVED

BHT-212-FMS-3

HOVER CEILING IN GROUND EFFECT SKID HEIGHT 4 FEET HEATER ON

TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

20.000

(OAT

_

LIMIT) 20 C

14.000

12,000

is __ __ _

_-

---

S

4000

2000 10,000

6000

7000

8000

9000

10,000

11,200

GROSS WEIGHT - POUNDS 212-FMS3-4-1-2

Figure 4-1.

8

Hover ceiling in ground effect (Sheet 2 of 6)

FAA APPROVED

BHT-212-FMS-3

HOVER CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

SKID HEIGHT 4 FEET HEATER OFF GROSS WEIGHTUP TO 10.000 LBS.

20,000

16000

OAT LIMIT) 20 C

(OAT LIMIT) 14000

6000

7000

8000

9000

10,000

GROSSWEIGHT - POUNDS

Figure 4-1.

11.200

212-FMS3-4-1-3

Hover ceiling in ground effect (Sheet 3 of 6)

9

BHT-212-FMS-3

FAA APPROVED

HOVER CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER SKID HEIGHT 4 FEET ENGINE RPM 100% HEATER OFF GENERATOR150 AMPS EACH GROSS WEIGHT 10,000 TO 11,200 LBS. 20.000…

18.000

16.000

14.000

10,000

10.200

10.400

10600

10,800 GROSSWEIGHT

11,000

11.200

- POUNDS 212-FMS3-4-1-4

Figure 4-1.

10

Hover ceiling in ground effect (Sheet 4 of 6)

FAA APPROVED

BHT-212-FMS-3

HOVER CEILING IN GROUND MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

EFFECT SKID HEIGHT 4 FEET HEATER ON GROSS WEIGHT UP TO 10,000 LBS.

20.000

16,000IOATLIMIT20C

_

__

i.

14,000

12,000

8000

6000

7000

8000

9000

10,000

11,200

FOR OVER 10.000 LB. GW EXPANDED CHART

6000

70GRO Figure 4-1. Hoverceil

Figure 4-1.

8000

9000 O10,000 11,200 - POUNDS GROSSWEIGHT

Hover ceiling In ground effect (Sheet 5 of 6)

11

BHT-212-FMS-3

FAA APPROVED

HOVER CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER SKID HEIGHT 4 FEET ENGINE RPM 100% HEATER ON GENERATOR 150 AMPS EACH GROSS WEIGHT 10,000 TO 11,200 LBS.

18,000

14.000

12.000 12.000

2000

10.000

10,200

10.400

10.600

10.800 GROSS

11.000 EIGHT

11.200

- POUNDS

212-FMS3-4-1-6

Figure 4-1. Hover ceiling in ground effect (Sheet 6 of 6)

12

BHT-212-FMS-3

FAA APPROVED

HOVER CEILING OUT OF GROUND EFFECT SKID HEIGHT 60 FEET HEATER OFF GROSS WEIGHT UP TO 10,000 LBS.

TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH 20,000

-

OAT

18,000

16,000 (OAT LIMIT)20°C-

14,000

12,000

(OAT LIMIT)30°C

(OAT LIMIT) 40°C

SEE EXPANDED CHART

(OAT LIMIT) 50°C

6000

7000

8000

9000

GROSS WEIGHT - POUNDS

Figure 4-2.

10,000

11,000

212-FMS3-4-2-1

Hover ceiling out of ground effect (Sheet 1 of 8)

13

BHT-212-FMS-3

FAA APPROVED

HOVER CEILING OUT OF GROUND EFFECT TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

SKID HEIGHT 60 FEET HEATER OFF GROSS WEIGHT 10.000 TO 11,200 LBS.

14,000

12.000

Figure 4-2.

14 14

Hover ceiling out of ground

effect (Sheet 2 of 8)

FAA APPROVED

BHT-212-FMS-3

HOVER CEILING OUT OF GROUND TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

EFFECT

SKID HEIGHT 60 FEET HEATER ON GROSS WEIGHT UP TO 10.000 LBS.

20,000

18,000

Figure 4-2.

6000

Hover ceiling out of ground effect (Sheet 3 of 8)

15

FOR OVER

Figure 4-2.

Hover ceiling out of ground effect (Sheet 3 of 8)

15

BHT-212-FMS-3

FAA APPROVED

HOVER CEILING OUT OF GROUND EFFECT TAKEOFF POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

SKID HEIGHT 60 FEET HEATER ON GROSS WEIGHT 10,000 TO 11,200 LBS.

16.000 16.000

12,000

10,000

10,200

10,400

10.600

10,800 11.000 GROSS WEIGHT- POUNDS

11,200

212-FMS3-4-2-4

Figure 4-2.

16

Hover ceiling out of ground effect (Sheet 4 of 8)

FAA APPROVED

BHT-212-FMS-3

HOVER CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

Figure 4-2.

SKID HEIGHT 60 FEET HEATER OFF GROSS WEIGHT UP TO 9000 LBS.

Hover ceiling out of ground effect (Sheet 5 of 8)

- POUNDS Figure 4-2. Hover ceilingGROSS out WEIGHT of ground effect (Sheet 5 212-FMS3-4-2of 8)

5

17

17

BHT-212-FMS-3

FAA APPROVED

HOVER CEILING OUT OF GROUND MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

16,00

-

-

-

EFFECT

SKID HEIGHT 60 FEET HEATER OFF GROSS WEIGHT 9000 TO 11.200 LBS.

-

16,000

1400______

Figure 4-2.

18

Hover ceiling out of ground effect (Sheet 6 of 8)

FAA APPROVED

BHT-212-FMS-3

HOVER CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS EACH

SKID HEIGHT 60 FEET HEATER ON GROSS WEIGHT UP TO 9000 LBS.

20,00

16,000

14.000 14,000

12,000

FOR OVER

9000LB.GW SCALE

6000

7000

8000

9000

10,000

GROSSWEIGHT - POUNDS

Figure 4-2.

11,000

212-FMS3-4-2-7

Hover ceiling out of ground effect (Sheet 7 of 8)

19

BHT-212-FMS-3

FAA APPROVED

HOVER CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 160 AMPS EACH

SKID HEIGHT 60 FEET HEATER ON GROSS WEIGHT 9000 TO 11,200 LBS.

18.000

000_______

212-FMS3-4-2-8

Figure 4-2.

20

Hover ceiling out of ground effect (Sheet 8 of 8)

FAA APPROVED

BHT-212-FMS-3

CRITICAL RELATIVE WIND AZIMUTHS

270

-

°

180

212-FMS3-4-3

Figure 4-3. Critical relative wind azimuths for hover flight

21/22

MANUFACTURER'S DATA

BHT-212-FMS-3

Section 5 59.

kilograms

EXTERNAL CARGO LOADING TABLE

CG at fuselage

(table 5-1 and 5-2).

Moments

have been calculated for external cargo millimeters).

station

138.0

(3505

External cargo weights and moments are

listed in 50 pound increments from 50 through 5000 pounds and 25 kilogram

increments

from 25 through

2268

23

BHT-212-FMS-3

MANUFACTURER'S DATA Table 5-1. Externalcargoloadingtable (Imperial)

24

WEIGHT (LB)

MOMENT (IN-LB)

WEIGHT (LB)

50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800 850 900 950 1000 1050 1100 1150 1200 1250 1300 1350 1400 1450 1500 1550 1600 1650 1700 1750 1800 1850 1900 1950 2000 2050 2100 2150 2200 2250 2300 2350 2400 2450 2500

6900 13800 20700 27600 34500 41400 48300 55200 62100 69000 75900 82800 89700 96600 103500 110400 117300 124200 131100 138000 144900 151800 158700 165600 172500 179400 186300 193200 200100 207000 213900 220800 227700 234600 241500 248400 255300 262200 269100 276000 282900 289800 296700 303600 310500 317400 324300 331200 338100 345000

2550 2600 2650 2700 2750 2800 2850 2900 2950 3000 3050 3100 3150 3200 3250 3300 3350 3400 3450 3500 3550 3600 3650 3700 3750 3800 3850 3900 3950 4000 4050 4100 4150 4200 4250 4300 4350 4400 4450 4500 4550 4600 4650 4700 4750 4800 4850 4900 4950 5000

MOMENT (IN-LB)

351900 358800 365700 372600 379500 386400 393300 400200 407100 414000 420900 427800 434700 441600 448500 455400 462300 469200 476100 483000 489900 496800 503700 510600 517500 524400 531300 538200 545100 552000 558900 565800 572700 579600 586500 593400 600300 607200 614100 621000 627900 634800 641700 648600 655500 662400 669300 676200 683100 690000 (TABLEI.D. 911320)

BHT-212-FMS-3

MANUFACTURER'S DATA Table 5-2. WEIGHT (KG)

IB

S

External cargo loading table (Metric)

MOMENT (KG * MM/100)

WEIGHT (KG)

MOMENT (KG * MM/100)

25 50 75 100 125 150 175

876.3 1752.5 2628.8 3505.0 4381.3 5257.5 6133.8

1175 1200 1225 1250 1275 1300 1325

41183.8 42060.0 42936.3 43812.5 44688.8 45565.0 46441.3

200

70100

1350

47317.5

225 250 275 300 325 350 375 400 425 450 475 500 525 550 575 600

7886.3 8762.5 9638.8 10515.0 11391.3 12267.5 13143.8 14020.0 14896.3 15772.5 16648.8 17525.0 18401.3 19277.5 20153.8 21030.0

1375 1400 1425 1450 1475 1500 1525 1550 1575 1600 1625 1650 1675 1700 1725 1750

48193.8 49070 0 49946.3 50822.5 51698.8 52575.0 53451.3 54327.5 55203.8 56080.0 56956.3 57832.5 58708.8 59585.0 60461.3 61337.5

625 650 675 700 725 750 775 800 825 850 875 900 925 950

21906.3 22782.5 23658.8 24535.0 25411.3 26287.5 27163.8 28040.0 28916.3 29792.5 30668.8 31545.0 32421.3 33297.5

1775 1800 1825 1850 1875 1900 1925 1950 1975 2000 2025 2050 2075 2100

62213.8 63090.0 63966.3 64842.5 64718.8 66595.0 67471.3 68347.5 69223.8 70100.0 70976.3 71852.5 72728.8 73605.0

975

34173.8

2125

74481 3

35050.0 35926.3 36802.5 37678.8 38555.0 39431.3 40307.5

2150 2175 2200 2225 2250 2268

75357.5 76233.8 77100.0 77986.3 78862.5 79493.4

1000 1025 1050 1075 1100 1125 1150

(TABLE I.D. 911319)

25/26

BHT-212-FMS-4

ROTORCRAFT FLIGHT MANUAL

*

SUPPLEMENT

AUXILIARY FUEL TANKS 205-706-044 OR 205-706-045 CERTIFIED 29 OCTOBER 1970

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when auxiliary fuel tanks are

installed. Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

COPYRIGHT NOTICE COPYRIGHT 1997

Inc. A Subsdiaryof Textron

BHT-212-FMS4 NOTICE PAGE

PROPRIETARY RIGHTS NOTICE

Manufacturer's Data portion of this supplement 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.

Additional copies of this publication may be obtained by contacting: Commercial Publication Distrlbution Center Bell Helicopter Textron Inc. P. 0. Box 482 Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-4 LOG OF REVISIONS

Original .0........

0..............

29 OCT 70

Revision ..........

4 ..............

01 OCT 84

Revision .......... Revision ..........

.............. 2..............20

11 OCT 73 FEB 75

Reissue...........0 Reissue...........0

............. ..............

14 AUG 95 12 SEP 97

Revision ..........

3 ..............

13 FEB 76

REVISION NO.

PAGE FLIGHT MANUAL Title -

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REVISION NO.

PAGE

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1-6 ...................................0

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MANUFACTURER'S DATA

9/10.....................................

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-4 LOG OF FAA APPROVED

REVISIONS

Original...........0

..............

29 OCT 70

Revision ..........

4 ..............

01 OCT 84

Revision..........1

..............

11 OCT 73

Reissue...........0

.............

14 AUG 95

20 FEB 75 13 FEB 76

Reissue...........0

..............

12 SEP 97

Revision .......... 2 .............. .............. Revision..........3

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

DATE:

BHT-212-FMS-4 GENERAL INFORMATION

The 205-706-044kit installs two 20 gallon fuel tanks In the helicopter.

The 205-706-045kit Installs two 90 gallon tanks in the helicopter.

I/II

FAA APPROVED

Section

1-6.

BHT-212-FMS-4

1

WEIGHT AND CENTER OF

WARNING

GRAVITY Actual weight change shall be determined

after auxiliary fuel tanks kit is installed and ballast readjusted, if necessary, to

INDISCRIMINATE LOADING OF HELICOPTER MAY RESULT IN

return empty weight CG to within allowable limits.

VIOLATION OF PERMISSIBLE CG LIMITATIONS WHEN HELICOPTER IS EQUIPPED WITH 212-706-045

AUXILIARY

FUEL

KIT AND

OPERATED IN IFR CONDITIONS.

Section 2 No change from basic manual.

1

FAA APPROVED

BHT-212-FMS-4

Section 3 No change from basic manual.

Section 4 No change from basic manual.

2

BHT-212-FMS-4

Section 5 5-7. FUEL LOADING

kilograms) compartment.

in

baggage

Fuel loading tables for helicopters prior to

Pilot and copilot can carry a combination of 5 passengers in mid-row seats and 2

serial number 35049 are shown in table 5-1

forward seats,

and 5-2 . Fuel loading tables for helicopters serial numbers 35049 and

in mid-row seats when CG is forward of above restriction.

4 in forward seats and

subsequent are shown In table 5-3 and 5-4. NOTE

NOTE All nine passenger seats may be

CG examples herein apply only to

occupied with 80 pounds (36.3

706-045 auxiliary fuel kit operated in IFR conditions. Examples assume each passenger weighs 170 pounds (77.1 kilograms).

compartment.

helicopters equipped with 205-

kilograms)

In baggage

WARNING

Pilot and copilot can carry a maximum of 8

BAGGAGE

passengers when CG is at or near (0.10 inch) aft limit.

WEIGHT SHALL BE REMOVED FOR SINGLE PILOT OPERATION.

COMPARTMENT

NOTE All nine passenger

seats may be

occupied with 25 pounds (11.3

3

BHT-212-FMS-4 Table 5-1. FUEL LOADING TABLE 2 x 20 GALLON AUXILIARY TANKS INSTALLED S/N PRIOR TO 35049 GAL.

WEIGHT 6.5 LB/GAL

C.G.

HORIZONTAL MOMENT

10 20 30 40 50 60 70 *72.6 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260

65 130 195 260 325 390 455 472 520 585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365 1430 1495 1560 1625 1690

143.6 143.6 140.2 134.8 131.6 129.4 127.9 127.6 128.3 130.9 134.0 136.3 138.3 140.0 141.3 142.6 143.7 144.7 145.7 146.7 147.7 148.6 149.5 150.4 151.2 151.9 152.6

9334 18668 27339 35048 42770 50466 58195 60227 66716 76577 87100 97455 107874 118300 128583 139035 149448 159894 170469 181175 192010 202839 213785 224848 235872 246838 257894

*Most Critical Fuel Amount for Most Forward C.G.Condition (TABLE

4

I.D. 910462)

BHT-212-FMS-4

Table 5-2. FUEL LOADING TABLE 2 x 90 GALLON AUXILIARY TANKS INSTALLED S/N PRIOR TO 35049 GAL. 10 20 30 40 50 60 70 *72.6 80 90 100 110 120 130 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 360 370 380 390 397

WEIGHT 6.5 LB/GAL

C.G.

HORIZONTAL MOMENT

65 130 195 260 325 390 455 472 520 585 650 715 780 845 845 910 975 1040 1105 1170 1235 1300 1365 1430 1495 1560 1625 1690 1755 1820 1885 1950 2015 2080 2145 2210 2275 2340 2405 2470 2535 2580

143.6 143.6 140.2 134.8 131.6 129.4 127.9 127.6 128.3 130.9 133.8 136.1 138.1 139.5 139.5 140.7 141.7 142.6 143.4 144.2 144.9 145.5 146.0 146.5 146.9 147.4 147.7 148.1 148.5 148.8 149.1 149.4 149.6 149.9 150.1 150.3 150.5 150.7 150.8 151.0 151.1 151.2

9334 18668 27348 35055 42771 50480 58186 60176 66706 76577 86970 97312 107718 117878 117878 128037 138158 148304 158457 168714 178952 189150 199290 209495 219616 229944 240013 250289 260618 270816 281054 291330 301444 311792 321965 332163 342388 352638 362674 372970 383039 390096

'Most Critical Fuel Amount for Most Forward C.G. Condition (TABLE

I.D. 910463)

5

BHT-212-FMS-4 Table 5-3. FUEL LOADING TABLE S/N 35049 & SUBSEQUENT AUXILIARY FUEL OPERATIONS - 2 x 20 GALLON AUX TANKS English Units Jet A, JP-5 (6.8 Ib./US Gallon) VOLUME (U.S. GAL) 10 20 30 40 50 60 70 78.5 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 256.6

WEIGHT (LB)

LONG. CG (IN)

MOMENT (IN-LBS)

68 136 204 272 340 408 476 534 544 612 680 748 816 884 952 1020 1088 1156 1224 1292 1360 1428 1496 1564 1632 1700 1745

143.9 144.0 141.6 135.7 132.2 129.9 128.2 127.3 127.4 129.7 133.1 135.4 137.3 139.0 140.5 141.8 143.0 144.1 145.1 146.2 147.4 148.4 149.3 150.2 151.0 151.7 152.1

9785 195846 28886 36910 44948 52999 61023 67953 69306 79376 90508 101279 112037 122878 133756 144636 155584 166580 1777602 188890 200464 211915 223353 234913 239741 257890 265483

Jet B, JP-4 (6.5 Ib./US gallon) VOLUME (U.S. GAL) 10 20 30 40 50 60 70 78.5 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 240 256

WEIGHT (LB)

LONG. CG (IN)

MOMENT (INLBS)

31.2 130 195 260 325 390 455 510 520 585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365 1430 1495 1560 1625 1668

3655.1 144.0 141.6 135.7 132.2 129.9 128.2 127.3 127.4 129.7 133.1 135.4 137.3 139.0 140.5 141.8 143.0 144.1 145.1 146.2 147.4 148.4 149.3 150.2 151.0 151.7 152.1

113893 18720 27612 35282 42965 50661 58331 64955 66248 75875 86515 96811 107094 117455 127855 138255 148720 159231 169767 180557 191620 202566 213499 224549 235560 246513 253771

NOTE: All data aboverepresentsusable fuel (basic & auxiliary) basedon nominaldensity at 15deg.C (59 deg.F).

* Most critical fuel quantity for most forward C. G. condition. (78.5gallons US) (TABLE

6

I.D. 911668)

BHT-212-FMS-4 Table 5-4. FUEL LOADING TABLE SIN 35049 & SUBSEQUENT AUXILIARY FUEL OPERATIONS Jet A, JP-5 (6.8 lb./US Gallon) VOLUME

(gal. US) 10 20 30 40 50 60 70 78.5 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 360 370 380 390 396.6

WEIGHT

(lb.)

68 136 204 272 340 408 476 534 544 612 680 748 816 884 952 1020 1088 1156 1224 1292 1360 1428 1496 1564 1632 1700 1768 1836 1904 1972 2040 2108 2176 2244 2312 2380 2448 2516 2584 2652 2697

LONG. CG

(Ins.)

143.9 144.0 141.6 135.7 132.2 129.9 128.2 127.3 127.4 129.6 132.9 135.1 136.9 138.4 139.7 140.9 141.9 142.8 143.6 144.2 144.9 145.5 146.0 146.5 146.9 147.3 147.7 148.1 148.4 148.7 148.9 149.2 149.4 149.7 149.9 150.1 150.3 150.5 150.7 150.9 150.9

MOMENT

(lb. Ins) 9785 19584 28886 36910 44948 52999 61023 67953 69306 79315 90372 101055 111710 122346 132994 143718 154387 165077 175766 186306 197064 207774 218416 229126 239741 250410 261134 271912 282554 293236 303756 314514 325094 335927 346569 357238 367934 378658 389409 400187 406959

2 x 90 GALLON AUX TANKS Jet B, JP-4 (6.5 Ib./US gallon) VOLUME

(gal. US) 10 20 30 40 50 60 70 * 78.5 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 360 370 380 390 396.6

WEIGHT

LONG. CG

MOMENT

(lb.)

(Ins.)

(lb. Ins)

65 130 195 260 325 390 455 510 520 585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365 1430 1495 1560 1625 1690 1755 1820 1885 1950 2015 2080 2145 2210 2275 2340 2405 2470 2535 2578

143.9 144.0 141.6 135.7 132.2 129.9 128.2 127.3 127.4 129.6 132.9 135.1 136.9 138.4 139.7 140.9 141.9 142.8 143.6 144.2 144.9 145.5 146.0 146.5 146.9 147.3 147.7 148.1 148.4 148.7 148.9 149.2 149.4 149.7 149.9 150.1 150.3 150.5 150.7 150.9 150.9

9354 18720 27612 35282 42965 50661 58331 64955 66248 75816 86385 96597 106782 116948 127127 137378 147576 157794 168012 178087 188370 198608 208780 219018 229164 239363 249613 259916 270088 280300 290355 300638 310752 321107 331279 341478 351702 361953 372229 382532 389005

NOTE: All data above representsusable fuel (basic & auxiliary) basedon nominal density at 15 deg.C (59 deg.F).

*Most critical fuel quantity for most forward C. G. condition. (78.5gallons US) (TABLE

1.D. 911608)

7/8

BHT-212-FMS-4

MANUFACTURER'S DATA

Section

1

No change from basic manual.

Section 2 2-11. FUEL SYSTEM SERVICING

Total usable fuel capacity with 205-706045 (2 - 90 gallon) tanks Is 398.6 U.S. gallons (978.8 liters) for S/N 35049 and

subsequent.

Total usable fuel capacity with 205-706044 (2 - 20 gallon) tanks is 256.8 U.S.

NOTE

gallons (972 liters) for S/N prior to

Initial fuel cutoff will occur at a

Total usable fuel capacity with 205-706-

pressure fueling helicopters with the 205-706-045 auxiliary fuel kit

35049.

044 (2 - 20 gallon) tanks is 258.6 U.S. gallons (978.8 liters) for S/N 35049 and

tank capacity of total approximately 336 gallons, when installed.

subsequent. Total usable fuel capacity with 205-706045 (2 - 90 gallon) tanks is 396.8

U.S.

gallons (1501.8 liters) for S/N prior to 35049.

9/10

BHT-212-FMS-5

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

INTERNAL RESCUE HOIST (BREEZE) 205-706-030 CERTIFIED MARCH 1, 1971

This supplement shall be attached to Model 212

Flight Manual when internal rescue hoist (BREEZE) kit has been installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter Inc A Subsidiary of Textron

COPYRIGHT NOTICE ®

INC BELL HELICOPTER ANDBELLHELICOPTER TEXTRON INC A DIVISION OFTEXTRON CANADA LTD ALLRIGHTS RESERVED

76101 TEXAS BOX482. FORTWORTH, POSTOFFICE

REISSUE

-

14 AUGUST

1995

BHT-212-FMS-5

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P.

O. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

BHT-212-FMS-5 LOG OF REVISIONS

Original ...........

0 .............

Revision..........1..............05

Revision..........2 .............. Revision .......... 3 ..............

01 MAR 71

Revision ..........

4 ..............

01 OCT 84

DEC 75

Revision .......... Reissue...........0

5 .............. .............

26 JUL 88 14 AUG 95

15 FEB 76 22 NOV 82

LOG OF PAGES REVISION PAGE

NO. FLIGHT MANUAL

REVISION PAGE A-

Title- NP.............................. 0

B ..................................

i/ii .......................................

NO. 0

1- 10..................................0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-5 LOG OF APPROVED

REVISIONS

Original ...........

0 .............

01 MAR 71

Revision ..........

4 ..............

01 OCT 84

Revision .......... Revision..........2

1 .............. ..............

05 DEC 75 15 FEB 76

Revision .......... Reissue...........0

5 .............. .............

26 JUL 88 14 AUG 95

Revision..........3

..............

22 NOV 82

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

FAA APPROVED

BHT-212-FMS-5 GENERAL INFORMATION

hoist enables cargo and Internal emergency rescue operations in areas

locations allows hoist to be extended 90 degrees outboard. A caution light on hoist

where landing cannot be accomplished. Hoist can raise or lower loads up to 600 Three-sixteenth pounds (272 kilograms). inch hoist cable is 256 feet (78 meters) in length. Each of four cabin mounting

control box illuminates when hook reaches 20 feet (6 meters) below skids during An electrically actuated cable retraction. cutting device allows either pilot or hoist operator to sever cable in an emergency.

0

0

i/ii

BHT-212-FMS-5

FAA APPROVED

Section 1-3.

1

TYPES OF OPERATION

Hoist operations shall be conducted under appropriate operating rules for external loads. Passenger operations with hoist installed are approved if hoist is stowed and hoist electrical system is deactivated.

Hoist operations are prohibited during instrument meteorological conditions.

Hoisting

or lowering

litter

an empty

In

open position (except Stokes litter) Is prohibited. prohibited. Flight Manual Refer to appropriate Supplement(s) for additional limitations, procedures, and performance data. procedures, and performance data.

1-6.

WEIGHT AND CENTER OF

GRAVITY Actual weight change shall be determined

after internal rescue hoist kit is installed and ballast readjusted, if necessary, to

1-4. FLIGHT CREW

return empty weight CG within

Minimum flight crew with hoist installed in forward right position is one pilot in right crew seat.

A second crewmember in passenger compartment is required to operate hoist if hoist is installed in any position other than

forward right. Hoist operator shall wear an approved safety harness and protective gloves for guiding cable during operation. Hoist operator shall be familiar with hoist operating procedures and limitations.

allowable

limits. Maximum hoist load is 600 pounds (272.2

kilograms) not to exceed GW of 11,200 pounds (5080.3 kilograms). This is a structural limitation only and does not ensure that longitudinal

or lateral CG will

remain within approved limits. Maximum allowable hoist load varies with GW, CG, and hoist location. Refer to appropriate Hoist Loading Schedule. NOTE

1-5.

CONFIGURATION

Butt line of load with hoist In

forward position is 60 inches 1-5-B.

(1524.0 millimeters)

OPTIONAL EQUIPMENT

centerline.

Fixed passenger step shall not be installed concurrently with internal hoist. *

Retractable passenger steps shall be stowed during hoist operations. Amphibious

flotation

gear shall

not be

installed concurrently with internal hoist.

from

Butt line of load with

hoist in aft position is 64.4 Inches from (1635.8 millimeters) centerline.

1-7. AIRSPEED VNE with hinged panels locked open and

cargo doors open is 20 KIAS. 1

BHT-212-FMS-5

FAA APPROVED

VNE with hinged panels removed and cargo

doors removed or secured is 60 KIAS.

1-22.

HOIST

DUTY

CYCLE

2.5 hour rest required before repeating a

duty cycle.

Following shall apply to all hoist operations:

Table 1-1.

Number of consecutive operations listed for each weight condition represents one duty cycle.

DUTY CYCLES - 250 FOOT CABLE LENGTH

Weight (Pounds)

Direction

Consecutive Operations

600 600 500 500 450 450 400 400 350 350 250 250

Lower Raise Lower Raise Lower Raise Lower Raise Lower Raise Lower Raise

(1) one (2) two (3) three (3) three (5) five (8) eight

Table 1-2.

2

30 second rest required between change in cable direction.

DUTY CYCLES - 210 FOOT CABLE LENGTH

Weight (Pounds)

Direction

Consecutive Operations

600 600 600 -0-0600 -0440

Lower Raise Lower Raise Lower Raise Lower Raise

(2) two (3) three (3) three (4) four

BHT-212-FMS-5

FAA APPROVED

1-22-C. RESCUE OPERATIONS FOOT FCABLELENGRTH 91(1 210 FOOT CABLE LENGTH Weight

(Pounds)

installed.

GW

representing number of crewmembers on board. Then proceed horizontally to left to

Operation

read allowable hoist load.

250 250

Lower attendant Raise patient Lower hook and

-0-

sling

Repeatraising

Enter schedule at helicopter

prior to hoisting. Proceed vertically to intersect appropriate diagonal line

T

Hoist loading schedules are based

on most adverse

patient and lowering hook and sling eight times. 250 Raise attendant This is equivalent to ten consecutive

loading

combinations of pilot, copilot, and hoist operator, each weighing 170 to 200 pounds (77.1 to 90.7 kilograms). If crewmember weights are not within this range, these schedules are invalid and

rescueoperations

pilot shall compute allowable

and is considered one duty cycle.

hoist load. For computation, assume hoist operator is located

laterally

at BL 40.0 (1016.0

millimeters).

1-23. ALLOWABLE HOIST LOAD Select Hoist Loading Schedule (figure 1-1)

appropriate for position in which hoist is

HOISTIN FORWARDRIGHTPOSITION BOOM FULLY EXTENDED PILOT AND COPILOT: ALLOWABLE HOIST LOAD 600 LB IUP TO 10,600 LB G.W.I

HOIST

, 300

6800

7200

7600

8000

8400

6800

9200

9600

10.000

GROSS WEIGHT PRIOR TO HOISTING - POUNDS

Figure 1-1.

10,400

10.800

11.200

212-FS5-1-1-1

Hoist loading schedules (Sheet 1 of 4) 3

BHT-212-FMS-5

FAA APPROVED HOISTIN AFT RIGHTPOSITION BOOMFULLY EXTENDED

600

LOADING THISAREA IN PROHIBITED

500

400 300

200

100

6800

7200

7600

8000

8400

8800

9200

9600

10.000 10.400 10.800

GROSSWEIGHTPRIORTO HOISTING- POUNDS

Figure 1-1.

11.200

212-FS5-1-1-2

Hoist loading schedules (Sheet 2 of 4) HOISTIN FORWARD LEFTPOSITION BOOM FULLY EXTENDED

600 LOADING IN THIS AREA PROHIBITED

500

300

6800

7200

7600

8000

8400

8800

9200

9600

10000

10.400 10.800

GROSSWEIGHTPRIORTO HOISTING- POUNDS

Figure 1-1.

4

Hoist loading schedules (Sheet 3 of 4)

11.200

212-FS5-1-1-3

BHT-212-FMS-5

FAA APPROVED HOISTIN AFT LEFTPOSITION ROOMFULLY EXTENDED

400

6800

7200

7600

8000

8400

8800

9200

9600

10,000

10,400

10.800

WEIGHTPRIOR TO HOISTING- POUNDS GROSS

Figure 1-1.

Hoist loading schedules

11.200

212-FS5-1-14

(Sheet 4 of 4)

5

BHT-212-FMS-5

FAA APPROVED

Section 2 2-2. FLIGHTPLANNING

and bumper assembly firmly seated

2-2-B. WEIGHTAND BALANCE

Boom actuator - Installed in proper position; all fittings secured.

against cable guide/boom head.

WARNING HOIST

LOAD

Hook -

CAN

CAUSE

Rotates freely on cable.

Cable - Proper routing through guide rollers, pulleys, and drums.

LONGITUDINAL OR LATERAL CG TO EXCEED LIMITS. GW AND CG

Cable

SHALL

Position and security.

BE COMPUTED

ASSURE LOADING APPROVED LIMITS.

TO

Loads should be placed on side of

helicopter opposite hoist position if additional loads are carried during hoisting operations. hoist load.

2-4.

Compute with and without

INTERIOR AND

-

Do not use filler port dipstick

to

check oil level when hoist is installed in helicopter.

Gearbox - Sight glass oil level. Hoist operator pendant -

Installed;

connectors secured.

Electrical power cables connectors secured.

Condition;

CAUTION

HOIST INSTALLATION

CHECK

ACTUATION OF CABLE CUT SWITCH ON PEDESTAL WILL CUT CABLE REGARDLESS OF HOIST

NOTE Hoist shall be installed in forward

right position if pilot plans to operate hoist. Hoist - Installed in desired position; roof and floor stud adapters and locking collars properly secured. Ensure hook 6

on gearbox

NOTE

PRESTART CHECK 2-4-A.

(four)

IS WITHIN

NOTE

GW and CG -

guards

PWR SWITCH POSITION. ACTUATION OF CABLE CUT SWITCH

ON HOIST

CONTROL

BOX WILL CUT CABLE EVEN IF HOIST CABLE CUT CIRCUIT BREAKER IS OPEN.

CABLE CUT switches (pedestal and hoist) - Off; covers safetied.

FAA APPROVED

BHT-212-FMS-5

Safety vests, tether straps, hoisting slings, and litters - Condition; secured or stowed.

stops; release and check hoist resumes operation.

Hoist speed -

2-4-B. HOIST OPERATIONCHECK

Reduce as cable

approaches up limit. Ensure hoist stops when hook reaches up limit without excess tension on cable.

NOTE

Hoist - Stowed for flight.

Perform hoist operation check

HOISTPWRswitch - OFF

anticipated.

Pilot or crewmember - Ensure hook and bumper assembly firmly seated against

only If hoist operations are Cargo doors and hinged panels Secured open or removed.

HOIST PWR, HOIST CONT, AND HOIST CABLE CUT circuit breakers - In.

BATTERY switch -

cable guide/boom head. NON ESS BUS switch BATTERY switch -

NORMAL.

OFF.

ON (or connect

external power).

NOTE

NON ESS BUS switch -

Ground

MANUAL.

ICS - Check intercom between pilot and hoist operator using hoist pendant ICS trigger and HOT MIC switch (right ICS box only).

HOIST PWRswitch -

ON; check amber

20 FOOT CAUTION light on hoist control

box illuminates.

personnel

be

should

instructed to discharge helicopter static electricity when possible, before attaching load to hoist.

2-4-C.

PRESTART CHECK

Cargo doors and hinged panels Secured open or removed. CABLE CUT switches (pedestal hoist) - Off; covers safetied.

NOTE

and

HOIST PWR, HOIST CONT, and HOIST CABLE CUT circuit breakers - In.

Maintain tension on hoist cable while reeling in and out to prevent

slack. and

2-4-D BEFORE TAKEOFF

operator) - Actuate to check all hoist functions for proper operation. Check pilot HOIST switch overrides operator

Safety vests and straps elcopter. secured

pendant HOIST switch.

Gloves -

Hoist cable -

STEP switch (if installed) - STOW.

HOIST and BOOM switches

(pilot

Check for corrosion,

kinks, flat spots, fraying, or broken

On and

On.

strands.

Gearbox -

Sight glass oil level while

HOIST PWR switch -

hoist is operating.

Up limit switch actuator -

2-9. IN-FLIGHT OPERATIONS ON.

Raise while

hoist is reeling in and check hoist motor 7

BHT-212-FMS-5

FAA APPROVED WARNING

CAUTION

HOIST OPERATOR SHALL BE

AIRSPEED

SECURED TO HELICOPTER WITH

LOAD

AN

APPROVED

SAFETY

HARNESS DURING OPERATIONS. Hover area.

HOIST

Establish over hoist operation

BOOM switch (or pilot HOIST switch) OUT.

HOISTswitch -

WITH EXTERNAL

IS

LIMITED

CONTROLLABILITY.

BY

CAUTION

SHOULD BE EXERCISED WHEN CARRYING EXTERNAL LOAD, AS HANDLING CHARACTERISTICS MAY BE AFFECTED BY SIZE, WEIGHT, AND SHAPE OF LOAD.

Airspeed -

As required for adequate

not to exceed limits for controllability, hoist operations (20 or 60 KIAS, as

applicable).

DOWN.

Static electricity - Discharge, when possible, and connect hook to load observing allowable hoist load.

OPERATE HOIST NORMALLY AT

FAST SPEED TO AVOID EXCESSIVE MOTOR AND GEARBOX HEATING.

AVOID CONTACTING UP LIMIT AT FULL SPEED.

USE SLOW SPEED AS LOAD APPROACHES GROUND OR

2-9-A.

LITTER HOISTING

When emergency transportation of a patient by litter is essential, every effort

landing is not feasible and condition of patient precludes use of personnel

hoistingsling.

In addition to all other procedures

contained herein, following shall apply to litter hoisting operations.

2-9-A-1.

EMPTY LITTER

LANDING GEAR.

WARNI

USE CARE TO PREVENT CABLE,

HOOK, AND LOAD FROM FOULING

ON FUSELAGE

OR

LANDINGGEAR.

HOISTING

EMPTY

OR LOWERING

LITTER

IN

POSITION IS PROHIBITED.

HOISTswitch -

UP.

Ground speed - Maintain zero until load is clear of obstructions. BOOM switch - IN to swing hoist boom and load into cabin, if possible.

Takeoff -

Into wind, if possible,

allowing adequate hoist load clearance over obstacles if load has not been placed inside of helicopter. 8

AN

OPEN AN

EMPTY LITTER SUSPENDED FROM HOIST IN OPEN POSITION C A N O S C I LL A T E IN ROTOR UNCONTROLLABLY WASH AND CAN FLY UPWARD, STRIKING FUSELAGE OR TAIL ROTOR.

Prior to hoisting or lowering an empty

litter, litter shall be closed and secured with straps. Litter should be suspended in

BHT-212-FMS-5

FAA APPROVED

.......

a near vertical position and sling straps

A LOADED LITTER CAN ROTATE

2-9-A-2. LOADED LITTER

ABOUT

CABLE

DURING

HOIST OPERATOR HOISTING. MAY HAVE TO GRASP LITTER

LITTER PATIENT SHALL BE SECURED TO LITTER SAFETY STRAPS.

WITH

HOIST HOOK CATCH SHALL BE SECURED WITH SAFETY PIN

2-9-B. AFTER EXITING HELICOPTER Hoist -

Condition and security.

Ensure

hook and bumper assembly firmly seated against cable guide/boom head.

PRIOR TO HOISTING LITTER PATIENT.

NOTE

Litter sling straps should be adjusted so that litter is 24 to 28 inches (61.0 to 71.1 centimeters) below hoist hook.

After flighthoist of day if hoist has been last used, maintenance action is required.

NOTE If litter is suspended too far below hook, litter can not be loaded into

helicopter with hoist hook at up limit.

Section 3 EMERGENCY PROCEDURES

3-14.

HOIST LOAD JETTISON

CABLE CUT switch (pedestal or hoist) -

Actuate to jettison

hoist load in an

emergency.

9

BHT-212-FMS-5

FAA APPROVED

Section 4 4-11. HOIST PERFORMANCE Figure 4-1 presents maximum hoist cable

speed attainable at various loads with pendant switch in FAST.

600

HOIST LOWERING

500 400 HOIST RAISING

0

300 200

0 100

0

20

40

60

80

100

120

140

160

180

MAXIMUM CABLE SPEED - FEET/MINUTE 212-FS5-4-1

Figure 4-1.

10

Hoist performance

BHT-212-FMS-6

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

FIXED FLOATS 205-706-050 CERTIFIED APRIL 1, 1971

This supplement shall be attached to Model 212 Flight Manual when fixed floats kit has been installed.

Information contained herein supplements

information of basic Flight Manual. For

Limitations, Procedures, and Performance Data not contained In this supplement, consult basic Flight Manual.

Bell Helicopter COPYRIGHT NOTICE 1995 COPYRIGHT BELL® HELICOPTER INC. TEXTRON INC ANDBELLHELICOPTER A DIVISION OFTEXTRON CANADA LTD. ALLRIGHTS RESERVED

POST

A Subsidiary ofTextronInc. TEXAS 78101 OFFICEBOX482· FORTWORIH,

REISSUE -

14 AUGUST 1995

BHT-212-FMS-6

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

BHT-212-FMS-6 LOG OF REVISIONS

Original ........... Revision ..........

0.............. .............

01 APR 71 05 MAY 71

Revision .......... Revision ..........

3 ............. 4 ..............

06 MAY 74 01 OCT 84

Revision ..........

2 ..............

28 JAN 72

Reissue...........0

.............

14 AUG 95

~LOG

OF PAGES REVISION NO.

PAGE FLIGHT MANUAL

A-

Title- NP..............................0

a^^>~~~

PAGE B ..................................

REVISION NO. 0

1- 10..................................0 11/12...................................0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-6 LOG OF APPROVED

REVISIONS .............

06 MAY 74

Original...........

..............

01 APR 71

Revison.........3

Revision ..........

.............

05 MAY 71

Revision ..........

4 ..............

01 OCT 84

Revision..........2

............

28 JAN 72

Reissue...........0

.............

14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

BHT-212-FMS-6

*

Section 1 Maximum lateral CG limits are 4.0 inches

NOTE

(101.6 millimeters) left and right of

Contents of this supplement shall be used in conjunction

fuselage centerline.

with Basic

Flight Manual for helicopters

equipped for amphibious

1-7. AIRSPEED

operation.

1-7-A.

1-3.

TYPES OF OPERATION

Helicopter is approved for amphibious operation under day and night VFR, nonicing conditions with all doors closed. Safe operations

have been demonstrated

in wave height of 12 inches (trough to crest); however, wave height limits have not been established.

1-6.

AIRSPEED - TWIN ENGINE

Twin engine VNE is 115 knots at 8100 pounds (3674.2 kilograms) GW and below,

decreasing linearly to 100 knots at 10,000 pounds (4536.0 kilograms) GW and above from sea level to 3000 feet HD (figure 1-2).

1-7-B. AIRSPEED - SINGLE

ENGINE

NNE

Single engine VNE is 80 knots at all GW from sea level to 10,000 feet HD .

WEIGHT AND CENTER OF

GRAVITY

1-8. ALTITUDE

Maximum GW is 11,200 pounds (5216.4 kilograms) for land and water operation.

Maximum operating -10,000 feet.

Actual weight change shall be determined

after fixed floats kit is installed and ballast readjusted,

Refer to Basic Flight Manual.

if necessary, to return empty

weight CG to within allowable limits.

CG limits are from station 130.0 to station 143.0 (figure 1-1). CG operational range is variable, depending on GW and shall be computed from weight and balance data. NOTE

Station 0 (datum line) is located 20 inches (500.8 millimeters) aft of most forward point of cabin nose. 1

BHT-212-FMS-6

CENTEROF GRAVITYVSGROSS WEIGHTCHART 112000

12-FS6-1-1

CENTER OF GRAVITY GROSS S S. L. chart Figure 1-1. Center of VS900 gravity vs.WEIGHT gross weight PLACARD 212-070-667-0.000 FT. - KNOTS OPERATING LIMIA/S MODEL 212 WITH FLOAT KIT 205-706-050

TWIN ENGINE

5INGLE ENGINE

LOCATED ON INSTRUMENT

PANEL

Figure 1-2. Operating limits decal

2

212-FS6-1-2

BHT-212-FMS-6

Section 2 ENGINE START

2-5.

PREFLIGHT CHECK

2-3.

Helicopter - Anchor or moor if necessary,

2-3-B. EXTERIORCHECK Floats -

when on water, prior to starting engine to

prevent helicopter rotation due to torque prior to tail rotor reaching effective RPM.

Condition and inflation.

Float pressure - Normal, 1.5 PSI (figure 21).

BEFORE TAKEOFF

2-7.

Taxi at slow speed to prevent float bows from nosing under. NOTE

When floats

NOTE

are installed,

temperature changes when moving helicopter from warm hangar to cold outside and vice

Safe operations in wave heights of 12 inches (trough to crest) and 360 turns in winds to 20 knots

versa will cause changes in float

have been demonstrated.

inflation pressure as shown in figure 2-1 and following example.

2-12. EXAMPLE: Helicopter storage temperature is 40 °F and ambient operating OAT will be 0 °F. This represents a 40 °F change in temperature and as shown by dotted line, a 1.2 PSI change in float bag pressure will

POSTFLIGHT

Helicopter -

CHECK

Anchor or moor if on water.

occur. In addition to pressure variations

caused

by temperature changes, there will be pressure increases when helicopter GW increases. Correct relationship of inflation vs. GW is shown in Section III of Service Instruction 212-14.

2-4. INTERIOR AND PRESTART CHECK NOTE

Searchlight azimuth control is inoperative when fixed floats are installed. 3

BHT-212-FMS-6

3

212.FS6.2-1

Figure 2-1.

4

Float pressure variation vs. temperature change

BHT-212-FMS-6

Section 3 EMERGENCY PROCEDURES

3-1.

INTRODUCTION

Autorotation run-on touchdown speed, on land or water, should be reduced to as low as practical.

Section 4 4-5.

HOVER CEILING

4-7.

CLIMB AND DESCENT

Reduce climb performance 230 feet per Figure 4-1 presents out of ground effect hover ceiling charts. Refer to BHT-2121FR- minute from that shown in Basic Flight FM-1 or BHT-212VFR-FM-1 for in ground

Manual.

effect hover ceiling charts.

4-6.

TAKEOFF DISTANCE

Takeoff distances in fixed float

configuration are 200 feet greater than shown in Basic Flight Manual.

5

BHT-212-FMS-6

HOVER CEILING OUT-OF-GROUND EFFECT TAKE OFF POWER

SKID HEIGHT 60 FT.

ENGINERPM100% GENERATOR150 AMPS(EA)

HEATEROFF AMPHIBIOUS OPERATIONS

OAT 9000

-

(OAT LIMIT) 50°C

7000\

6000

(OAT

212-FS6-4-1-1

LIMIT)40°C

5000

3000

2000

1000 (OAT

7000

LIMITI

50°C

8000

9000

10,000 GROSS

Figure 4-1.

6

WEIGHT

11,000

- POUNDS

Hover ceiling out of ground effect (Sheet 1 of 6)

BHT-212-FMS-6

HOVER CEILING OUT-OF-GROUND EFFECT MAXIMUMCONTINUOUS POWER ENGINERPM100% GENERATOR150AMPS(EAI

7000

8000

SKIDHEIGHT60 FT. HEATEROFF AMPHIBIOUS OPERATIONS

9000

10.000

11.000

11.200 GROSS

WEIGHT

- POUNDS

212-FS6-4-1-2

Figure 4-1.

Hover ceiling out of ground effect (Sheet 2 of 6)

7

BHT-212-FMS-6

HOVER CEILING OUT-OF-GROUND EFFECT

10 000

-

-

TAKEOFF POWER

SKID HEIGHT60 FT.

ENGINE RPM 100%

HEATER ON

GENERATOR150 AMPS(EA)

AMPHIBIOUS OPERATIONS

-

9000

7000

7000

10.000

11.000 11 200

GROSS WEIGHT

-

POUNDS

212-FS6-4-1-3

Figure 4-1.

8

Hover ceiling out of ground effect (Sheet 3 of 6)

BHT-212-FMS-6

HOVER CEILING OUT-OF-GROUND EFFECT MAXIMUMCONTINUOUS POWER ENGINERPM100% GENERATOR 150 AMPS(EA)

Figure 4-1.

SKIDHEIGHT60 FT. HEATERON AMPHIBIOUS OPERATIONS

Hover ceiling out of ground effect (Sheet 4 of 6)

9

BHT-212-FMS-6

HOVER CEILING OUT-OF-GROUND EFFECT TAKE OFFPOWER

SKIDHEIGHT60 FT.

ENGINE RPM 100%

WINTERIZATION HEATER ON

GENERATOR150 AMPS(EA)

AMPHIBIOUS OPERATIONS

1000-

7000

800

9000

10.000

11,000 11.200

GROSS WEIGHT - POUNDS

212-FS6-4-1-5

Figure 4-1.

10

Hover ceiling out of ground effect (Sheet 5 of 6)

BHT-212-FMS-6

HOVER CEILING OUT-OF-GROUND EFFECT MAXIMUMCONTINUOUS POWER ENGINERPM100% GENERATOR150AMPSIEA)

GROSS WEIGT

SKID HEIGHT60 FT. WINTERIZATION HEATERON AMPHIBIOUS OPERATIONS

POUNDS

212-FS6-4-1-6

Figure 4-1.

Hover ceiling out of ground effect (Sheet 6 of 6)

11/12

BHT-212-FMS-7

2

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

CATEGORY A OPERATIONS CERTIFIED 18 AUGUST 1972

This supplement shall be attached to the Bell Helicopter Model 212 Flight Manual when conducting

Category A

flight operations.

Information contained herein supplements information of basic Flight Manual. For Limitations,

Procedures, and

Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter COPYRIGHT NOTICE COPYRIGHT 1997 BELL ® HELICOPTERTEXTRONINC. ANDBELLHELICOPTER TEXTRON INC A DIVISION OFTEXTRON CANADA LTD RESERVED ALLRIGHTS

A Subsidiary of TextronInc POST OFFICE BOX 482 · FORT WORTH. TEXAS 76101

14 AUGUST 1995 14 REVISION 1 -

12 SEPTEMBER

1997

BHT-212-FMS-7

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-7 LOG OF REVISIONS Original...........0

.............

18 AUG 72 11 APR 75

Revision .......... 2 .............. Revision .......... 3 .............. Revision..........4 ..............

24 SEP 76 18 NOV 76 26 JAN 77

Revision ..........

5 ..............

Revision ..........

6 ..............

01 OCT 84

.............

14 AUG 95

1 ..............

12 SEP 97

Reissue...........0

Revision ..........

03 APR 78

LOG OF PAGES REVISION NO. FLIGHT MANUAL

REVISION NO.

PAGE

30 - 31 ................................. SECTION 2 B.............................

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76 .................................

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded

pages. Rev.1

A

BHT-212-FMS-7 LOG OF FAA APPROVED

REVISIONS

18 AUG 72

Revision

5 ..............

03 APR 78

Revision ..........

1 ..............

11 APR 75

Revision ..........

6 ..............

01 OCT 84

Revision..........2

..............

24 SEP 76

Reissue...........0

.............

14 AUG 95

18 NOV 76 26 JAN 77

Revision ..........

1 ..............

12 SEP 97

Original..........

Revision .......... Revision ..........

0.............

3 .............. 4 ..............

APPROVED:

MANAGER

ROTORCRFT CERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

Rev. 1

.........

DATE:

BHT-212-FMS-7

FAA APPROVED GENERAL INFORMATION

INTRODUCTION

Part A provides data for vertical takeoffs and landings from 72 by 150 feet heliports.

A Category A takeoff is defined as follows: Operation of helicopter in such a manner

that if one engine fails at any time after Part start of takeoff, helicopter can:

B provides data for stadard takeoffs

and landigs

from 550 feet runways.

Return to, and safely stop on, takeoff

Part C provides data for standard takeoffs

area; or

and landings from 2300 feet runways.

Continue takeoff, climb out, and attain single engine forward flight. as is defined A landing A Category follows: Operation of helicopter in such a manner that if one engine fails at any point during approach, helicopter can:

Land and stop safely

Bell Model 212 is authorized for Category A operation in accordance with Parts A, B, and C. Category A operation under Part A requires installation of an approved copilot instrument kit, an approved dual control kit, and 212-706-029 altimeter.

on intended

landing area; or

Portions

Climb out from point of failure and attain

duplicated

single engine forward flight.

continuity.

of each Part are

in all three Parts to aid

Category A operations are covered in Parts A, B, and C. Each section specifies limitations, procedures, and performance

for a given set of conditions.

i/ii

FAA APPROVED

BHT-212-FMS-7

Section 1A PART A

1A-4.

1A-6-B.

CREW

FLIGHT

CENTER OF GRAVITY

Minimum crew for vertical type takeoff and landing operations consists of two pilots.

Center of gravity limits are from 130.0 to 142.0. The center of gravity operational range is variable, depending on gross weight. The center of gravity shall be

1A-5. CONFIGURATION

computed from weight and balance data.

Helicopter shall be equipped with skid

Refer to Figure 1A-1, Center of Gravity Limits.

landing gear. NOTE

All doors shall be installed on helicopter.

Station 0 (datum) is located 20 1A-5-D. ALTIMETER (VERTICAL TAKEOFF ALTIMETER) For vertical

takeoffs,

vertical

takeoff

altimeter shall be set, ENG RPM shall be 100% at flat pitch, doors and windows shall be closed, heater and vent shall be

off.

NOTE Doors and windows remain closed, heater off, and vent off until critical decision point (CDP) is reached. This is required to prevent possible errors in vertical takeoff altimeter

1A-6. WEIGHT AND CENTER OF GRAVITY

inches aft of most forward of cabin nose.

point

Maximum lateral CG limits are 3.5 inches

to left and right of fuselage centerline. 1A-6-C.

TAKEOFF AND LANDING

WEIGHT VS ALTITUDE

Maximum takeoff and landing weight varies with temperature and altitude. Refer to Gross weight limits for takeoff and landing chart (figure 1A-2). NOTE Minimum length

heliport

width

and

are 72 feet and 150 feet,

respectively, for Category A vertical operations from ground level or elevated heliports.

1A-6-A. WEIGHT Maximum GW is 10,000 pounds. 1

BHT-212-FMS-7

1A-8.

ALTITUDE

FAA APPROVED

1A-12. 1A-12-B.

1A-8-A. ALTITUDE LIMIT FOR TAKEOFF AND LANDING Altitude limit for takeoff and landing is 2500 feet Hp.

ELECTRICAL GENERATOR

Output generator.shall

not exceed 75 amps per

BHT-212-FMS-7

FAA APPROVED

I

NOTE: SEE HEADWIND COMPONENT

212FMS7A-1-2

CHART, SECTION4.

Figure 1A-2.

Gross weight limits for takeoff and landing

3

BHT-212-FMS-7

FAA APPROVED

Section 2A PART A

2A-7. BEFORETAKEOFF

Flight altimeter -

2A-7-A. CHECK

Hover (2 to 4 feet) torque.

POWER ASSURANCE

Perform Power assurance

check -

Set to correct station

pressure or elevation.

Refer

Note transmission

Collective - Apply smoothly to obtain a steady rate of climb along takeoff flight

to Performance Data.

path using transmission torque, not to exceed an additional 15% torque in

2A-8. TAKEOFF

excess of value noted in hover.

Pilot shall control flight path by visual reference to far right corner of heliport and

2A-8-A. VERTICAL TYPE TAKEOFF

takeoff index marks. As altitude above heliport is increased to approximately 40

to 60 feet, it will be necessary to transition

NOTE

into rearward flight at a very slow speed in order to maintain visual reference with far

Refer to Vertical Takeoff Profile (figures 2A-1) and Vertical Takeoff

right corner of heliport (figure 2A-2, sheet 1). Takeoff will be continued by visual reference to far right corner of heliport

(figure 2A-2, sheets 1 through 3).

Takeoff shall be initiated with helicopter positioned such that takeoff index marks are directly

opposite crew doors and helicopter centered on heliport. This will ensure tail rotor is within confines of heliport. Triple tachometer - 100%.

NOTE Visual reference with heliport is defined as that position where far right corner of heliport is aligned approximately halfway between edge of instrument panel and

lower corner of windshield.

Collective - Full down (flat pitch). Doors and windows - Closed.

Amount of heliport area visible to pilot will vary with height above ground. At all points in takeoff,

Heater and vent blower takeoff.

boundary.

Off, during

Vertical takeoff altimeter - Set to zero. 4

(figure 2A-2, sheet 2) until CDP is reached (figure 2A-2, sheet 3).

maintain visual contact with forward corner of forward right right corner of heliport he

FAA APPROVED

BHT-212-FMS-7

Copilot shall call out following altitudes

from vertical takeoff altimeter during takeoff:

Flight altimeter

reportingstation.

-

Set to nearest

From an airspeed of 30 knots indicated At 60 feet Indicated: "60 feet".

At 80 feet indicated: "80 feet". At 100 feet indicated: "100 feet".

At 120feet indicated: "120 feet". At 140feet indicated: "140 feet". At 160 feet indicated:

"CDP, Rotate".

At indicated CDP, transition into forward flight to obtain takeoff safety speed (VTOSS) of 30 knots plus wind (55 knots maximum). Apply power of not less than 72% torque and climb to 200 feet above takeoff point at VTOSS.Accelerate to best rate of climb airspeed (55 knots) and climb enroute. Copilot should monitor power and systems parameters.

plus wind velocity and a height of 200 feet,

pilot shall initiate approach when LDP is reached. LDP is reached when pilot obtains correct sight picture of heliport (figure 2A-4, sheet 1). Pilot calls "LDP" and initiates approach.

Approach is Initiated by raising nose of helicopter to obtain correct approach sight picture (figure 2A-4, sheet 2) and

simultaneously lowering collective to establish approach angle.

During descent, visual contact Is maintained with forward right corner of heliport (figure 2A-4, sheets 1 and 2).

Approach angle Is such that tail rotor will clear a 25 foot obstacle on approach end of heliport.

2A-10. DESCENT AND LANDING 2A-10-A. VERTICAL TYPE LANDING

As helicopter crosses approach end of heliport with required tail rotor obstacle clearance, a slight flare is initiated so helicopter is brought to a landing with pilot door even with or slightly forward of takeoff mark on heliport. NOTE

A vertical type landing is initiated from landing decision point (LDP) which Is 30 knots indicated airspeed plus reported wind velocity and at an altitude of 200 feet above level of heliport surface (figure 2A-

Copilot shall call out airspeed and altitude information prior to LDP (ie., 'Airspeed high' or 'Airspeed low', and 'Altitude high' or 'Altitude low') and then shall call

out rotor rpm, torque, Flight controls desired.

Adjust frictions as

GOVswitches- AUTO. Throttles -

Full open, friction adjusted

and

interturbine temperature (ITT) during approach from LDP. In event of an engine failure after LDP, pilot will adjust power as

soon as possible to obtain

maximum single engine power available during descent.

as desired. ENG RPM -

100%.

FORCE TRIM -

As desired. 5

BHT-212-FMS-7

FAA APPROVED

160 FT.

*REF. SHEET2 APPROXIMATE

40-60FT. *REF.SHEET1 *REFER TO FIGURE 2A-2

Figure 2A-1.

6

Rev. 1

Vertical takeoff profile

212FMS7-2A-1

FM

APPROVED

Figure

2A-2.

FM APPROVED

Figure 2A-2. Vertical takeoff (Sheet 3 of 3)

Figure 2A-3.

2

Rev-1

Vertical landing profile

FAA APPROVED

Figure

2A-4.

Vertical

landing

(Sheet

1 of 2)

Figure

2A-4.

Vertical

landing

(Sheet

2 of 2)

BHT-212-FMS-7

FAA APPROVED

Section 3A PART A

3A-3. ENGINE

headwind using 30 minute power rating to 200 feet above heliport and then accelerate

to best rate of climb speed (55 knots).

3A-3-A. ENGINE FAILURE

Copilot should monitor power.

affected engine.

Throttle (affected engine) - Closed.

NOTE Immediately

after

Shut down

an engine

failure, power on remaining engine shall be Increased to maximum permissible power limits (30 minute power rating) while maintaining rotor within limits.

BOOST PUMP switch (affected engine)

- OFF.

FUEL switch (affected engine) FUEL XFEEDswitch INTCON switch -

OFF.

OVRDCLOSE.

OPEN.

3A-3-J. DURING TAKEOFF PRIOR TO CDP

3A-3-L. DURING LANDING PRIOR TO LDP TO LDP

An engine failure prior to reaching CDP (160 feet above heliport) will necessitate a

Helicopter should be accelerated to best

landing back to heliport.

Landing is

accomplished by descending back toward takeoff surface while maintaining 97% rotor. While maintaining a level attitude, as necessary to Increase collective cushion landing. Perform normal engine shutdown.

rate-of-climb

speed for climbout,

depending on terrain and obstacles. Shut down affected engine. Throttle (affected engine) - Closed. BOOST PUMP switch (affected engine) - OFF.

3A-3-K. DURING TAKEOFF AFTER CDP

FUEL switch (affected engine) -

In event of an engine failure during or

INTCONswitch -

following rotation at CDP, helicopter

should be accelerated to VTOSSof 30 knots

Indicated plus wind velocity.

While

accelerating to VTOSS,maintain rotor within limits

and accomplish

a climbout

at an

airspeed of 30 knots Indicated plus 10 Rev.1

FUEL XFEED switch -

OFF.

OVRD CLOSE.

OPEN.

Or, proceed to LDP and use following

procedure.

FAA APPROVED

3A-3-M. LDP

BHT-212-FMS-7

DURING LANDING AT

3A-3-N. LDP

Maintain rotor within limits and accomplish a climbout or accelerate to best rate of climb speed (55 knots), depending on terrain and obstacles.

DURING LANDING AFTER

Helicopter is committed to land after LDP. Landing is accomplished using 30 minute power rating of remaining engine while maintaining rotor within limits and

maintaining visual contact with sight Or, proceed to a landing using following

picture of two sides of heliport. After

procedure.

landing, perform normal engine shutdown.

Table 3A-1.

WARNING LIGHT ILLUMINATION PRIOR TO CDP

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil pressure below limits.

Land.

C BOX OIL TEMP

Combining gearbox oil temperature above limit.

Land.

XMSN OIL TEMP

Transmission oil temperature above limit.

Land.

XMSN OIL PRESS

Transmission

Land.

oil pressure

below limit. BAGGAGE FIRE

Smoke in baggage compartment.

Land.

FIRE 1 PULL

Fire indication in No. 1 engine compartment.

Land, pull No. 1 handle, select MAIN bottle, then RESERVE if

FIRE 2 PULL

Fire indication in No. 2 engine compartment.

Land, pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle.

ENG 1 OUT

No. 1 engine GAS PROD below limit.

Refer to Engine Out Procedure.

ENG 2 OUT

No. 2 engine GAS PROD

Refer to Engine Out Procedure.

below limit.

FAA APPROVED

BHT-212-FMS-7

Table 3A-2.

WARNING LIGHT ILLUMINATION AFTER CDP

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil pressure below limits,

Accelerate to VTOSSand land as soon as practical.

C BOX OIL TEMP

Combining gearbox oil temperature above limit.

Accelerate to VTOSSand land as soon as practical.

XMSN OIL TEMP

Transmission oil temperature above limit,

Accelerate to VTOSSand land as soon as practical.

XMSN OIL PRESS

Transmission below limit,

Accelerate to VTOssand land as soon as practical.

BAGGAGE FIRE

Smoke in baggage compartment.

Accelerate to VTOssand land as soon as practical.

FIRE 1 PULL

Fire indication in No. 1 engine compartment.

Accelerate to VTOSS,pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle.

FIRE 2 PULL

Fire indication in No. 2 engine compartment.

Accelerate to VTOSS,pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle.

ENG 1 OUT

No. 1 engine GAS PROD

Refer to Engine Out Procedure.

oil pressure

below limit. ENG 2 OUT

No. 2 engine GAS PROD

below limit.

12

Refer to Engine Out Procedure.

FAA APPROVED

Table 3A-3.

BHT-212-FMS-7

WARNING LIGHT ILLUMINATION PRIOR TO LDP

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil

Reduce power. Land as soon as

pressure below limits.

practical.

Combining gearbox oil temperature above limit.

Reduce power. Observe temperature within limits. land as soon as possible.

Transmission oil temperature above limit.

Reduce power. Observe temperature within limits.

Transmission

Reduce power. Land as soon as

C BOX OIL TEMP

XMSN OIL TEMP

XMSN OIL PRESS

oil pressure

If not,

If not,

below limit.

possible.

BAGGAGE FIRE

Smoke in baggage compartment.

Reduce power to minimum required. Land as soon as possible and inspect tail boom area for damage.

FIRE 1 PULL

Fire indication in No. 1 engine compartment.

Pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle.

FIRE 2 PULL

Fire indication in No. 2 engine compartment.

Pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle.

ENG 1 OUT

No. 1 engine GAS PROD

Refer to Engine Out Procedure.

below limit. ENG 2 OUT

No. 2 engine GAS PROD

Refer to Engine Out Procedure.

below limit.

13

FAA APPROVED

BHT-212-FMS-7

Table 3A-4.

WARNING LIGHT ILLUMINATION AFTER LDP

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil pressure below limits.

Land.

C BOX OIL TEMP

Combining gearbox oil temperature above limit.

Land.

XMSN OIL TEMP

Transmission oil temperature above limit.

Land.

XMSN OIL PRESS

Transmission

oil pressure

Land.

below limit. BAGGAGE FIRE

Smoke in baggage compartment.

Land.

FIRE 1 PULL

Fire indication in No. 1 engine compartment.

Land, pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle.

FIRE 2 PULL

Fire indication in No. 2 engine compartment.

Land, pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle.

ENG 1 OUT

No. 1 engine GAS PROD

Refer to Engine Out Procedure.

below limit. ENG 2 OUT

No. 2 engine GAS PROD

below limit.

14

Refer to Engine Out Procedure.

FAA APPROVED

BHT-212-FMS-7

Section 4A PART A

4A-1. INTRODUCTION

Determine OAT Determine Hp

Minimum heliport

29 °C 1000 feet

size, using vertical

takeoff and landing procedures, is 72 by 150 feet. A chart (figure 4A-1) is presented

Enter chart at OAT,

showing minimum heliport size and

proceedvertically

approved heliport marking. Heliport marking shown was used during type

upward to H proceed horizontally to right to GW, then proceed vertically downward to

tests. GW limits for takeoff and landing varies with component of headwind directly

opposed to flight

path. Headwind

component chart (figure 4A-2) presents a method of obtaining headwind component

torquemeterscale and read ercent torque required t

for use on Gross weight limits for takeoff and landing chart (section 1A-1). Maximum crosswind demonstrated was 15 knots and

is shown

as a limit

on headwind

hover (transmission

torque)

62%

component chart.

Interpolation of all data is allowable but extrapolation

Torque Available (Twin Engine)

is not permitted.

4A-14. HOVER PERFORMANCE

Enter chart at OAT, proceed vertically upward to Hp, proceed

horizontally to right to takeoff

Hover performance chart (figure 4A-3) is presented to show percent torque required to hover in ground effect (IGE) at a four

power available curves, then proceed vertically

foot skid height and percent torque

downwardto

available as shown in following example:

torquemeter scale and read percent torque available

Torque Required To Hover

100% 15

BHT-212-FMS-7

FAA APPROVED

4A-15. TAKEOFF PERFORMANCE

Takeoff flight

path - obstacle

clearance

(figure 4A-6).

These charts are used as in following example:

4A-15-A.

TAKEOFF SAFETY SPEED

Determine

VTOSSvaries with wind (VToss = 30 KIAS + wind).

ALTIMETER

15 °C

Sea level

VTOSS

(30 KIAS + headwind component of 10 knots) Determine actual GW Check maximum

40 knots 7850 pounds

allowable GW (if

CALIBRATION

Takeoff performance is based on altimeter

calibration

OAT

Determine Hp

(VTOSS)

4A-15-B.

Determine

shown in Takeoff altimeter

actual GW is less than maximum allowable, proceed)

10,000 pounds

Enter figure 4A-5

calibration

chart (figure 4A-4).

at OAT Move vertically up to Hp

4A-15-C.

TAKEOFF DISTANCE

Move right horizontally to actual

GW for takeoff

Vertical Takeoff Distance -

150 Ft.

Using vertical takeoff procedure, takeoff distance measured from aft end of heliport

when in takeoff position, is maximum distance needed to land after a rejected takeoff (single engine failure prior to or at CDP for vertical takeoff procedure).

This

takeoff distance applies to all conditions of GW, Hp, and OAT when operating within

allowable limits. 4A-15-D.

TAKEOFF FLIGHT PATH

Takeoff flight path begins at end of takeoff distance, at 35 feet above takeoff surface, and at Vross. Two charts are involved in

determination of takeoff flight path and are titled as follows: Takeoff flight path - climb index (figure 4A-5). 16

Move vertically down to VTOSS

correction curves

Move diagonally,

parallel to VTOSS

correction

curves

to VTOSS Move vertically down to climb index scale and

read climb index

46.0

FAA APPROVED

On figure 4A-6, locate climb index point, which has just been determined, at a height above takeoff surface of 200 feet. A line

from this point through 35 foot height at 0 horizontal distance represents minimum height flight path from end of takeoff distance and

should be compared with

BHT-212-FMS-7

only, since a takeoff net flight path is presented for flight path determination. 4A-16-B. SINGLE ENGINE AT BEST RATE OF CLIMB SPEED Single engine rate of climb at best rate of climb speed (55KCAS) is unchanged from

Section 1A.

4A-17.

LANDING

PERFORMANCE 4A-17-A. LANDING DISTANCE VERTICAL PROCEDURE Actual landing

110 feet

distance Scheduled landing

138 feet

distance

height of known obstacles along flight path for obstacle

Using vertical landing procedure, landing distance is actual distance needed for tail

clearance

rotor to clear a 25 foot height and

helicopter to come to a stop on landing surface with only one engine operating.

4A-16. CLIMB

Actual landing distance is 110 feet. For scheduled landings, landing distance is

PERFORMANCE

138 feet. These landing distances apply to all conditions of GW, Hp, and OAT when

operating within allowable limits. 4A-16-A.

SINGLE ENGINE AT

MINIMUM

VTOSS

Single engine rate of climb at minimum VTOSS (30 KIAS) is shown in figure 4A-7. These curves are for general information

17

BHT-212-FMS-7

FAA APPROVED

-I

FT.

4 FT. (TYP)

1 FT. (TYP.)

-

4 FT. X 4 FT. X 4 FT. (TYP.)

8 FT. (TYP.)-36 FT. 72 FT. MINIMUM HELIPORT SIZE AND APPROVED HELIPORT MARKING Figure 4A-1.

18

Heliport size and markings

212FMS7A212FMS7A-4-1

BHT-212-FMS-7

FAA APPROVED

HEADWIND COMPONENT- KNOTS 0

10

5 °

° 90° 80 70

60°

15 C 20

50

35

30

25

CROSSWIND COMPONENT

40

LIMIT

40°

KNOTS

WINDDIRECTION FROM TAKE OFF HEADING

CROSSWIND COMPONENT KNOTS 0 KNOTS

0°

0

10

5

15

20

30

25

35

40

REPORTEDWINDSPEED- KNOTS

EXAMPLE:

1 TAKEOFFHEADING.

..................

.

.... .. .. 170°

200 . REPORTEDWIND DIRECTION...... ° ...... 30 WIND DIRECTION. DEGREESFROM TAKE OFF HEADING ............ 20 KNOTS .......... REPORTEDWIND SPEED ..... ENTER CHART AT REPORTEDWIND SPEED.POINT A PROCEEDUPWARD.FOLLOWINGTHE SHAPEOF THE CURVED LINES. TO WIND DIRECTION, DEGREESFROM TAKEOFF HEADING, POINT B. 7. PROCEEDVERTICALLY UPWARDTO THE HEADWIND 17.5 KNOTS COMPONENTSCALEAND READ HEADWIND COMPONENT.

2. 3. 4. 5. 6

212FMS7A-4-2

Figure 4A-2.

Headwind component chart

19

BHT-212-FMS-7

FAA APPROVED

HOVER PERFORMANCE IGE (4 FT. SKID HT.) POWER REQUIRED TO HOVER AND TAKE-OFF POWER AVAILABLE HEATER OFF ENGINE RPM100% GENERATOR150 AMPS NO WIND

OATLIMIT

TORQUE AVAILABLE

TORQUE 60

20

.40

.20

60

70

REQUIRED 80

I TORQUEMETER

90100

212 212FMS7A-4-3

Figure 4A-3. Hover Performance

20

BHT-212-FMS-7

FAA APPROVED

260

.

240 220 200---180

CRITICAL DECISION POINT

Figure 4A-4. Takeoff altimeter calibration

21

FAA APPROVED

BHT-212-FMS-7

TAKEOFF FLIGHT PATH CLIMB INDEX 30 MINUTE POWER ENGINERPM 97% GENERATOR 150 AMPS

HEATEROFF INOPERATIVEENGINESECURED AIRSPEED= VTOSS(30 KT. IAS + HEADWIND)

VTOSS (30 KT.

HEADWIND)

Figure 4A-5. Takeoff flight path - climb index Figure 4A-5. Takeoff flight path - climb index

22

212FMS7A-4-5

BHT-212-FMS-7

FAA APPROVED

TAKEOFF FLIGHT PATH

*

O

OBSTACLE CLEARANCE HEATER OFF

30 MINUTE POWER ENGINE

RPM

GENERATOR

200

ENGINE SECURED

97%

INOPERATIVE

150 AMPS

AIRSPEED VTOSS = 30 KT. IAS + HEADWIND

10080 60 50

40

30

CLIMB INDEX 20 25

18

16

14

12

212-FMS-7A-4-6

Figure 4A-6.

Takeoff flight path - obstacle clearance

23

BHT-212-FMS-7

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB 7,000 LB. GROSS WEIGHT 30 MIN. POWER ENGINE RPM 97% GENERATOR 150 AMPS

Figure 4A-7.

24

AIRSPEEDVTOSS= 30 KT. IAS HEATER OFF INOPERATIVE ENGINESECURED

Single engine rate of climb (Sheet 1 of 4)

FAA APPROVED

BHT-212-FMS-7

*SINGLE ENGINE RATE OF CLIMB 8,000 LB. GROSS WEIGHT 30 MIN. POWER ENGINERPM 97% GENERATOR 150 AMPS

AIRSPEEDVTOSS= 30 KT. IAS HEATEROFF INOPERATIVEENGINESECURED

16,000

14,000

12,000

Figure 4A-7.

Single engine rate of climb (Sheet 2 of 4)

25

FAA APPROVED

BHT-212-FMS-7

SINGLE ENGINE RATE OF CLIMB 9,000 LB. GROSS WEIGHT AIRSPEEDVTOSS= 30 KT. IAS HEATEROFF INOPERATIVEENGINESECURED

30 MIN. POWER ENGINERPM 97% GENERATOR 150 AMPS

14.000

-

2.000

6.,000

I 0.000

8.000

--

--

2,000

0

200

400

600

800

1.000

1.200

1.400

RATE OF CLIMB - FT./MIN. 212FMS7A-4-7 3

Figure 4A-7.

26

Single engine rate of climb (Sheet 3 of 4)

FAA APPROVED

O

BHT-212-FMS-7

SINGLE ENGINE RATEOF CLIMB 10,000 LB. GROSS WEIGHT 30 MIN. POWER ENGINE RPM97% GENERATOR150 AMPS

AIRSPEEDVTOSS= 30 KIAS HEATER OFF INOPERATIVEENGINESECURED

10,000

8,000

6,000

4,000

2.000

-

-

-

-

-

-

-

-

212FMS7A-4-7-4

Figure 4A-7.

Single engine rate of climb (Sheet 4 of 4)

27/28

FAA APPROVED

BHT-212-FMS-7

SectionlB PART B

w*----------

1B-4. FLIGHT CREW

Maximum lateral CG limits

ALTITUDE

I Minimum crew consists of one pilot.B8. 1B-5.

are 3.5 inches

to left and right of fuselage centerline.

CONFIGURATION

1B-8-A. ALTITUDE LIMIT FOR TAKEOFF AND LANDING

Skid landing gear only.

Altitude limit for takeoff and landing is

1B-6. WEIGHT AND CENTER OF GRAVITY

2500 feet Hp.

1B-8-B. CROSSWIND Crosswind limit is that combination of wind velocity and direction where

1B-6-A. WEIGHT Maximum takeoff and landing weight

crosswind component exceeds 15 knots. Refer to Headwind component chart In Performance Data.

Refer to Gross weight limits for takeoff and landing chart (figure 1B-1).

1B-12.

Maximum GW Is 10,000 pounds.

1B-12-B.

1B-6-B. 113-6-1B. CENTER CENTER OF OF GRAVITY GRAVITY

Output generator.shall

CG limits are from Station 130.0 to Station 144.0 (figure 1B-2). CG operational range is variable, depending upon GW and shall

1 B23.

data.

Minimum runway length is 550 feet.

varies with temperature and altitude.

be computed from weight and balance

Station

0 (datum)

Is located

ELECTRICAL GENERATOR not exceed 75 Amps per I

MINIMUM RUNWAY LENGTH

20

inches aft of most forward point of cabin nose.

Rev. 1

29

FAA APPROVED

BHT-212-FMS-7

550 FT. RUNWAY LENGTH

51.7 10 5 0 30 20 HEADWIND - KT.

0

5

10

15

20 OAT-

25 °

30

35

40

NOTE: SEE HEADWIND COMPONENT CHART. SECTION 4. Figure 1B-1.

30

45

50

C

212FMS7B-1-1 Gross weight limits for takeoff and landing

BHT-212-FMS-7

FAA APPROVED

10,000

9,000

STANDARD

TAKEOFF AND LANDING

7,000

O PERATION

6,000

5,000 130

134

132

136

LONGITUDINAL

140

138 C.G STATION

144

142

INCHES 212FMS7B-1-2

Figure 1B-2. Center of gravity limits

Section 2B PART B

2B-7. 2B-7-A. CHECK

2B-8.

BEFORE TAKEOFF POWER ASSURANCE

Perform power assurance check to Basic Flight Manual.

TAKEOFF

2B-8-A. STANDARD TYPE TAKEOFF Refer NOTE

A standard type takeoff is a takeoff accomplished

from a 4 to

5 foot hover height with a transition into forward flight.

this type of takeoff,

For

critical 31

BHT-212-FMS-7

FAA APPROVED

decision point (CDP) is that point in flight path where takeoff safety

decision point (LDP) which is 30 knots indicated airspeed plus

speed (VTOSS) of 30 knots is attained at a height of 10 feet.

reported wind velocity and at an altitude of 100 feet above runway

Refer to Performance Data for required takeoff length and climb

Refer to Performance Data for

path.

required runway lengths.

Collective -

Full down (flat pitch).

Triple tachometer - 100%. Flight altimeter -

Set to correct station

pressure or elevation. Hover (2 to 4 feet) -

Flight controls desired.

GOV switches - AUTO Throttles - Full open, friction adjusted as desired. ENG RPM -

Note transmission

Adjust frictions as

100%.

FORCE TRIM -

As desired.

torque. Passenger step -

As desired.

Takeoff - Initiate from a hover using transmission torque not to exceed an additional 10% torque in excess of value noted in hover. CDP is attained at an indicated airspeed of 30 knots and 10 feet above surface. Power - Apply not less than 72% torque and climb to 200 feet above takeoff point at VTOSS. Accelerate to best rate of climb airspeed (55 knots) and climb enroute.

2B-10.

DESCENT AND

LANDING 2B-10-A. STANDARD TYPE LANDING NOTE

A standard type landing is a landing initiated from landing 32

reporting station. As helicopter crosses approach end of runway, initiate a flare and adjust power to start a descent to normal landing.

BHT-212-FMS-7

Section 3B PART B

3B-3. ENGINE

200 feet above runway and then accelerate

to best rate of climb speed (55 knots). Shut down affected engine.

3B-3-A. ENGINE FAILURE

Throttle (affected engine) -

Closed.

FUEL switch (affected engine) -

NOTE

OFF.

BOOST PUMP switch (affected engine)

Immediately after an engine failure, power on remaining

-

OFF.

engine should be increased to

FUEL XFEEDswitch -

limits (30 minute power rating)

INTCONswitch - OPEN.

maximum permissible power while maintaining rotor within

OVRDCLOSE.

limits.

3B-3-L. 3B-3-J.

DURING LANDING PRIOR

TO LDP

DURING TAKEOFF PRIOR

LDP

TO CDP

In event of an emergency condition

during

An engine failure prior to reaching CDP

landing prior to LDP (100 feet above runway), accelerate to best rate of climb speed for climbout, depending on terrain

(160 feet above runway) will necessitate

and obstacles.

landing back to runway.

a

If altitude

Shut down affected engine.

permits, initiate a flare to dissipate airspeed to approximately 20 KIAS. Adjust collective to obtain maximum power

Throttle (affected engine) -

approximately 15 feet, level helicopter and pull collective, as required, to cushion and

BOOST PUMP switch (affected engine) - OFF.

available from remaining engine. At

Closed.

FUELswitch (affected engine)-

OFF.

complete landing. FUEL XFEED switch -

3B-3-K. CDP

DURING TAKEOFF AFTER

In event of an engine failure during or

following

CDP, airspeed should be

maintained at VTOSSof 30 knots.

INTCON

switch

-

OVRD CLOSE.

OPEN.

Or, proceed to LDP and use following procedure

Maintain

rotor within limits and accomplish a climbout using 30 minute power rating to

Rev. 1

33

FAA APPROVED

BHT-212-FMS-7

3B-3-M. LDP

DURING LANDING AT

and limits rotor within Maintain accomplish a climbout or accelerate to best rate of climb speed (55 knots), depending on terrain and obstacles. Or, proceed

to a landing

3B-3-N. LDP

DURING LANDING AFTER

Helicopter Is committed to land after LDP. Landing is accomplished using 30 minute power rating of remaining engine while maintaining rotor within limits. After landing, perform normal engine shutdown.

using following

procedure. Table 3B-1.

WARNING LIGHT ILLUMINATION PRIOR TO CDP

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil pressure below limits. Combining gearbox oil temperature above limit. Transmission oil temperature above limit. Transmission oil pressure

Land.

C BOX OIL TEMP XMSN OIL TEMP XMSN OIL PRESS BAGGAGE FIRE FIRE 1 PULL

Land. Land. Land.

below limit. Smoke in baggage compartment. Fire indication in No. 1 engine compartment.

FIRE 2 PULL

Fire indication in No. 2 engine compartment.

ENG 1 OUT

No. 1 engine GAS PROD

Land. Land, pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle. Land, pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle. Refer to Engine Out Procedure.

below limit. ENG 2 OUT

Table 3B-2.

No. 2 engine GAS PROD

Refer to Engine Out Procedure.

below limit.

WARNING LIGHT ILLUMINATION AFTER CDP

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil pressure below limits. Combining gearbox oil temperature above limit. Transmission oil temperature above limit. Transmission oil pressure below limit. Smoke in baggage compartment.

Accelerate to VTOSSand soon as practical. Accelerate to VTOSSand soon as practical. Accelerate to VTOss and soon as practical. Accelerate to VTOSsand soon as practical. Accelerate to VTOSSand soon as practical.

C BOX OIL TEMP XMSN OIL TEMP XMSN OIL PRESS BAGGAGE FIRE 34

land as land as land as land as land as

FAA APPROVED

Table 3B-2.

BHT-212-FMS-7

WARNING LIGHT ILLUMINATION AFTER CDP (Cont)

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

FIRE 1 PULL

Fire indication in No. 1 engine compartment.

FIRE 2 PULL

Fire indication in No. 2 engine compartment.

ENG 1 OUT

No. 1 engine GAS PROD

Accelerate to VTOSS,pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle. Accelerate to VTOSS,pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle. Refer to Engine Out Procedure.

below limit. ENG 2 OUT

No. 2 engine GAS PROD

Refer to Engine Out Procedure.

below limit.

Table 3B-3.

WARNING LIGHT ILLUMINATION PRIOR TO LDP

SEGMENT WORDING

FAULT CONDITION

C BOX OIL PRESS

Combining gearbox oil

CORRECTIVE ACTION Reduce power. Land as soon as

pressure below limits.

practical.

C BOX OIL TEMP

Combining gearbox oil temperature above limit.

XMSN OIL TEMP

Transmission oil temperature above limit.

XMSN OIL PRESS

Transmission

Reduce power. Observe temperature within limits. If not, land as soon as possible. Reduce power. Observe temperature within limits. If not, land as soon as possible. Reduce power. Land as soon as

BAGGAGE FIRE

oil pressure

below limit.

possible.

Smoke in baggage compartment.

Reduce power to minimum required. Land as soon as

possible and inspect tailboom FIRE 1 PULL

Fire indication in No. 1 engine compartment.

FIRE 2 PULL

Fire indication in No. 2 engine compartment.

ENG 1 OUT

No. 1 engine GAS PROD

DW

ENG 2 OUT

area for damage. Pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle. Pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle. Refer to Engine Out Procedure.

below limit. No. 2 engine GAS PROD

below limit.

Refer to Engine Out Procedure.

35

FAA APPROVED

BHT-212-FMS-7

WARNING LIGHT ILLUMINATION AFTER LDP

Table 3B-4. SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil pressure below limits. Combining gearbox oil temperature above limit. Transmission oil temperature above limit. Transmission oil pressure

Land.

C BOX OIL TEMP XMSN OIL TEMP XMSN OIL PRESS

Land. Land. Land.

below limit. BAGGAGE FIRE

Smoke in baggage compartment. Fire indication in No. 1 engine compartment.

FIRE 1 PULL FIRE 2 PULL

Fire indication in No. 2 engine compartment.

ENG 1 OUT

No. 1 engine GAS PROD

Land. Land, pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle. Land, pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle. Refer to Engine Out Procedure.

below limit. No. 2 engine GAS PROD

ENG 2 OUT

Refer to Engine Out Procedure.

below limit.

Section 4B PART B NOTE The minimum runway length using

the standard takeoff and landing procedure is 550 feet.

crosswind demonstrated was 15 knots and

is shown as a limit component chart. Interpolation extrapolation

on headwind

of all data is allowable is not permitted.

but

4B-1. INTRODUCTION GW limits for takeoff and landing varies

with component of headwind directly opposed to flight path. Headwind component chart (figure 4B-1) presents a method of obtaining headwind component for use on Gross weight limits for takeoff and landing chart (section 1B). Maximum 36

4B-14.

HOVER

PERFORMANCE

Hover performance chart (figure 4B-2) is presented to show percent torque required to hover in ground effect (IGE) at a 4 foot

FAA APPROVED

BHT-212-FMS-7

skid height and percent torque available as shown in following example:

4B-15

TAKEOFF

PERFORMANCE

Torque Required To Hover

4B-15-A. Determine OAT Determine Hp Determine GW

24 °C

SPEED

TAKEOFF SAFETY

1000 feet 8500 pounds

Enter chart at OAT,

be used for standard takeoff procedures.

STANDARD TAKEOFF

proceed vertically upward to Hp, proceed

4B-15-B.

horizontally to right to GW, then proceed vertically

Using normal takeoff procedure from unconfined areas, takeoff distance measured from helicopter in takeoff

DISTANCE

downward to

position, is distance needed to land after a

torquemeter scale and read percent torque required to

rejected takeoff (single engine failure prior to or at CDP) for standard takeoff procedure. This takeoff distance is 550

hover

feet for all conditions of GW, Hp, and OAT

(transmission torque)

62%

when operating within allowable limits. 4B-15-C.

Torque Available (Twin Engine)15C.

TAKEOFF TAKEOFF FLIGHT PATH

FLIGHT PATH

Takeoff flight path begins at end of takeoff distance, at 35 feet above takeoff surface, and at VTOSS. Two charts are involved in determination of takeoff flight path and are

Enter chart at OAT, proceed vertically upward to Hp,

titled as follows:

proceed horizontally to right to takeoff

Takeoff flight path - climb index (figure

power available

4B-3).

curves, then proceed vertically

Takeoff flight path - obstacle clearance

downward to

(figure 4B-4).

torquemeter scale and read percent torque available

100%

These charts example:

are used as in following

Determine OAT

15 °C

Determine Hp

Sea level

Headwind component

10 knots

Determine actual GW

7850 pounds 37

BHT-212-FMS-7

FAA APPROVED

Check maximum

On figure 4B-4,

allowable GW (if actual GW is less

locate climb index point, which has

than maximum

just been

proceed)

10,000 pounds

Enter figure 4B-3 at OAT Move vertically to Hp

deterined t height above takeoff surface of 200 feet. A line

from this point

up

through 35 foot height at 0

Move horizontally right to actual GW for takeoff

horizontal distance represents minimum height

Move vertically down to headwind

flight path from end of takeoff distance and

component correction curves

should be compared

compared with height of known

Move diagonally,

obstacles along flight path for obstacle clearance

parallel to headwind component correction curves to headwind component

Move vertically down to climb index scale and read climb index

4B-16. CLIMB PERFORMANCE 46.0

4B-16-A.

SINGLE ENGINE AT

VToSS Single engine rate of climb at VTOSS (30

KIAS) is shown in figure 4B-5. These curves are for general information only, since a takeoff net flight path is presented

for flight path determination. 4B-16-B. SINGLE ENGINE AT BEST RATE OF CLIMB SPEED Single engine rate of climb at best rate of climb speed (55 KCAS) is unchanged from Section 1B. 38

0

FAA APPROVED

4B-17.

BHT-212-FMS-7

LANDING

foot height and helicopter to come to a

PERFORMANCE

engine operating. Landing distance is 185 feet for all GW, Hp, and OAT when operating within allowable limits.

4B-17-A. LANDING DISTANCE STANDARD PROCEDURE

Using standard procedure, landing distance is distance needed to clear a 50

39

FAA APPROVED

BHT-212-FMS-7

HEADWIND COMPONENT - KNOTS 5

0 °

° 900 80

°

70

10

15

60°

50°

C 20

25

30

35

CROSSWIND COMPONENT

40

LIMIT 40

DIRECTION

10 KNOTS

1

TAKE OFF HEADING.

..170°

..............

WINDDIRECTION.......... 2. REPORTED

....

200°

300 WIND DIRECTION. DEGREES FROM TAKE OFF HEADING ....... . ................20 KNOTS ........ REPORTEDWIND SPEED..... .......... ENTER CHART AT REPORTEDWIND SPEED.POINT A. PROCEED UPWARD. FOLLOWING THE SHAPE OF THE CURVED LINES, TO WIND DIRECTION. DEGREES FROM TAKE-OFF HEADING. POINT B. 7. PROCEED VERTICALLY UPWARD TO THE HEADWIND COMPONENTSCALE AND READ HEADWIND COMPONENT ............ 17.5 KNOTS 3. 4. 5. 6

212FMS7B-4.1

Figure 4B-1.

40

Headwind component

chart

0

BHT-212-FMS-7

FAA APPROVED

HOVER PERFORMANCE IGE (4 FT. SKID HT.) POWER REQUIRED TO HOVER AND TAKE-OFF POWER AVAILABLE HEATER OFF NO WIND

ENGINERPM100% GENERATOR150 AMPS

OATLIMIT

2.000

FT

I

-60

.40

20

0

20

40

60

-60

40

20

0

20

40

60

60

50

70 80

90

100

TO HOVER

50

60

90

100

212FMS7B-4-2

Figure 4B-2. Hover performance chart

41

BHT-212-FMS-7

FAA APPROVED

TAKEOFF FLIGHT PATH CLIMB INDEX 30 MINUTE POWER ENGINE RPM97% GENERATOR150 AMPS

HEATEROFF INOPERATIVEENGINESECURED VTOSS=30 KIAS

Figure 4B-3. Takeoff flight path - climb index

42

BHT-212-FMS-7

FAA APPROVED

*

TAKEOFF FLIGHT PATH OBSTACLE CLEARANCE 30 MINUTE POWER ENGINE RPM 97% 150 AMPS GENERATOR

HEATER OFF INOPERATIVE ENGINE SECURED VTOSS = 30 KIAS

CLIMB INDEX 10080 60 50

40

30

25

20

18

16

14 _

12

212FMS7B-4-4

Figure 4B-4. Takeoff flight path - obstacle clearance

43

FAA APPROVED

BHT-212-FMS-7

SINGLE ENGINE RATE OF CLIMB 7,000 LB.GROSS WEIGHT 30 MIN. POWER ENGINE RPM 97% GENERATOR 150AMPS

VTOSS = 30 KIAS HEATEROFF INOPERATIVEENGINESECURED

16.000

14.000

------

12.000

10.000 -

8,000

6.000

4

4.000

20 TO 540C 2.000

OATLIMIT

2.000

0

200

400

600

800

RATE OF CLIMB

Figure 4B-5.

44

-

1.000 FT./MIN

1 200

1 400

1.600 212FMS7B-4-5-1

Single engine rate of climb (Sheet 1 of 4)

FAA APPROVED

O

BHT-212-FMS-7

SINGLE ENGINE

RATE OF CLIMB

8,000 LB. GROSS WEIGHT VTOSS = 30 KIAS HEATEROFF INOPERATIVEENGINESECURED

30 MIN. POWER ENGINE RPM 97% GENERATOR 150 AMPS 16.000

14.000

12,000

I0.000

-

8.000-

2.000_A

X

-

-

-

-

-

-

--

-

-

Figure 4B-5. Single engine rate of climb (Sheet 2 of 4)

45

FAA APPROVED

BHT-212-FMS-7

SINGLE ENGINE RATE OF CLIMB 9,000 LB. GROSS WEIGHT VTOSS = 30 KIAS HEATEROFF INOPERATIVEENGINESECURED

30 MIN. POWER ENGINERPM 97% GENERATOR 150AMPS

-

14,000

12.000

10.000

8.000

--

6.000

4.000

-

AT LIMIT 20 TO 54°C O.4

___2~.0

2.000

\ \Oo

.2.000

0

200

400

600

800

RATE OF CLIMB - FT /MIN.

Figure 4B-5.

46

1.000

1.200

1.400

212FMS7B-4-5-3

Single engine rate of climb (Sheet 3 of 4)

FAA APPROVED

BHT-212-FMS-7

SINGLE ENGINE RATE OF CLIMB 10,000 LB. GROSS WEIGHT 30 MIN. POWER ENGINERPM 97% GENERATOR 150 AMPS

0^B

VTOSS = 30 KIAS HEATEROFF INOPERATIVEENGINESECURED

10.000

8,000

Figure 4B-5.

Single engine rate of climb (Sheet 4 of 4)

47/48

BHT-212-FMS-7

*

Section 1C PART C

1C-1.

INTRODUCTION

-----Minimum crew for standard type takeoff and and landing operations consists of one pilot.

is variable, depending upon GW and shall be computed from weight and balance data Maximum lateral CG limits are 3.5 inches to left and right of fuselage centerline.

1C-5.

CONFIGURATION

1C-8.

ALTITUDE

Skid landing gear only. 1C-8-A.

1C-6.

WEIGHT AND CENTER

OF GRAVITY 1C-6-A.

ALTITUDE LIMIT FOR

TAKEOFF AND LANDING Refer to Gross weight vs altitude - ambient air temperature limits chart (figure 1C-1).

WEIGHT

1C-12.

ELECTRICAL

1C-12-B.

GENERATOR

NOTE

Maximum takeoff and landing weight varies with temperature and altitude. Refer to Gross Weight VS Altitude/Ambient Air Temperature

1C-1).

Output shall not exceed 75 amps per generator

Limits Chart (Figure

1C-22.

Maximum GW is 11,200 pounds.

1C-6-B.CENTER OFGRAVITY

CROSSWIND

LIMITATIONS Crosswind limit is that combination of and direction where wind velocity crosswind component exceeds 15 knots. Refer to Headwind component chart.

NOTE

Station 0 (datum) is located 20 inches aft of most forward point of cabin nose. CG limits are from Station 130.0 to Station 144.0 (figure 1C-2). CG operational range

1C-23.

MINIMUM RUNWAY

LENGTH

Minimum runway length is 2300 feet. Minimum runway length s 2300 feet

Rev. 1

49

BHT-212-FMS-7

FAA APPROVED

2300 FT. RUNWAY LENGTH

GROSS WEIGHT vs ALTITUDEAMBIENT AIR TEMPERATURE LIMITS 1 GROSS WEIGHT CURVES ARE BASED ON A CONSTANT 150 FT/MIN RATE OF CLIMB AT 1000 FT. ABOVE THE TAKEOFF SURFACE. USING SINGLE ENGINE 30 MIN POWER. B5 KT AIRSPEED.

2

3

LOWER GROSS WEIGHTS THAN SHOWN ARE LIMITED TO 10.000 FT DENSITY ALTITUDE UMIT FOR TAKEOFF AND LANDING

DASHED LINE PORTION OF 9000 LB GROSS WEIGHT TO BE USED FOR INTERPOLATION ONLY

8100C-- --

Figure 1C-1. Gross weight vs altitude - ambient air temperature limits

50

BHT-212-FMS-7

FAA APPROVED

11,000

8000

7000

5000 130

132

134

136

138

140

142

144

LONGITUDINAL C.G.STATION - INCHES 212FMS7C 1-2

Figure 1C-2.

Center of gravity limits

51

FAA APPROVED

BHT-212-FMS-7

Section 2C PART C

2C-7. BEFORETAKEOFF

Takeoff - Initiate from a hover using transmission torque of 5% above that required to hover.

2C-7-A. CHECK

POWER ASSURANCE NOTE

Perform power assurance to Performance Data.

2C-8.

check -

Refer

transmission Do not exceed torque or ITT limits CDP is attained at an indicated airspeed of 55 knots and approximately 35 feet above surface.

TAKEOFF

Power -

Apply not less than 72% torque

2C-8-A. STANDARDTYPE

and climb to 200 feet above takeoff point

TAKEOFF

at VTOSS.

2C-10. DESCENT AND

NOTE

Takeoff is accomplished as follows:

Hover at approximately

10 foot skid height, increase torque an additional

LANDING

a

5% over

NOTE

torque required to hover as

A standard type landing is

helicopter begins to move forward during takeoff. As airspeed

initiated from an LDP of 40 KIAS and an altitude of 150 feet above

slightly so as to hold 55 knots for

than 500 feet per minute.

approaches approximately 50 knots, raise nose of helicopter

runway, either In level flight or with a rate of descent of not more Landing

climb. VTOSS(55 knots) airspeed is attained at approximately 35

is accomplished by lowering collective, as required, to

feet altitude.

establish descent.

Power is then

Collective - Full down (flat pitch).

adjusted, as required, to control rate of descent while holding 40 KIAS. Forty KIAS is maintained

Triple tachometer- 100%.

until a further

Flight altimeter - Set to correct station pressure or elevation,

helicopter is flared for landing. A normal landing is accomplished to a hover or to ground, as desired.

Hover (approximately 10 feet skid height) - Note transmission torque. 52

reduction of

airspeed is necessary as

FAA APPROVED

BHT-212-FMS-7 ENG RPM -

STANDARD TYPE

2C-10-A. LANDING

100%.

FORCE TRIM -

Flight controls desired.

Adjust frictions as

As desired.

Passenger step - As desired.

Flight altimeter Throttles -

Set to nearest

reporting station.

GOV switches - AUTO. Full open, friction adjusted

as desired.

Section 3C PART C

3C-3.

3C-3-K. CDP

ENGINE

I 3C-3-A.

ENGINE FAILURE

In event of an engine failure at or following CDP, airspeed should be maintained at 55

NOTE

Immediately after an engine failure, power on remaining

knots, single engine climb initiated, and appropriate traffic procedures followed.

engine should be increased to

NOTE

limits (30 minute power rating) while maintaining rotor within limits.

During takeoff, after CDP, it is permissible during transition from dual engine to single engine flight

maximum permissible power

following an engine failure, to

droop rotor speed to as low as

3C-3-J. DURING TAKEOFF PRIOR

91%. Rotor should be regained to

TO CDP

normal operating range at or before attaining best rate of climb speed (55 knots).

An engine failure prior to reaching CDP

W)

will necessitate a landing back to runway.

If altitude permits, initiate a flare toRIN dissipate airspeed to approximately 20

KIAS.

)

DURING TAKEOFF AFTER

Adjust collective

to obtain

3C-3-L.

TO LDP

ANDIN PRIOR DURING LANDING PRIOR

maximum power available from remaining

engine. At approximately 15 feet, level helicopter and pull collective, as required, to cushion and complete landing.

In event of an emergency condition during landing prior to LDP (150 feet above runway), accelerate to best rate of climb speed for climbout, depending on terrain and obstacles.

Shut down affected engine. Rev. 1

53

FAA APPROVED

BHT-212-FMS-7

Throttle (affected engine)-

best rate of climb speed (55 knots), depending on terrain and obstacles.

Closed.

FUEL switch (affected engine) -

OFF.

BOOST PUMP switch (affected - OFF.

engine)

FUEL XFEED switch INTCON switch -

Or, proceed to a landing using following

3C-3-N. LDP

OVRD CLOSE.

DURING LANDING AFTER

Helicopter is committed

OPEN.

Or, proceed to LDP and use following procedure. 3C-3-M. LDP

procedure.

procedure

to land after LDP.

Landing is accomplished using 30 minute power rating of remaining engine while maintaining rotor within limits. After landing, perform normal engine shutdown.

DURING LANDING AT

Maintain rotor within limits and accomplish a climbout or accelerate to Table 3C-1.

WARNING LIGHT ILLUMINATION

PRIOR TO CDP

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil

Land.

pressure below limits. C BOX OIL TEMP XMSN OIL TEMP XMSN OIL PRESS

Combining gearbox oil temperature above limit. Transmission oil temperature above limit. Transmission oil pressure

Land. Land. Land.

below limit. BAGGAGE FIRE

Smoke in baggage

Land.

compartment. FIRE 1 PULL

Fire indication

in No. 1

engine compartment. FIRE 2 PULL

ENG 1 OUT

Fire indication

In No. 2

Land, pull No. 1 handle, select

MAIN bottle, then RESERVEif necessary, close No. 1 throttle. Land, pull No. 2 handle, select

engine compartment.

MAIN bottle, then RESERVEif

No. 1 engine GAS PROD

necessary, close No. 2 throttle. Refer to Engine Out Procedure.

below limit. ENG 2 OUT

No. 2 engine GAS PROD

below limit.

54

Refer to Engine Out Procedure.

FAA APPROVED

Table 3C-2.

BHT-212-FMS-7

WARNING LIGHT ILLUMINATION AFTER CDP

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil pressure below limits. Combining gearbox oil temperature above limit. Transmission oil temperature above limit. Transmission oil pressure below limit. Smoke in baggage compartment. Fire indication in No. 1 engine compartment.

Accelerate to VTOSSand land as soon as practical. Accelerate to VTOSSand land as soon as practical. Accelerate to VTOSSand land as soon as practical. Accelerate to VTOSSand land as soon as practical. Accelerate to VTOSSand land as soon as practical. Accelerate to VTOSS,pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle. Accelerate to VTOSS,pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle. Refer to Engine Out Procedure.

C BOX OIL TEMP XMSN OIL TEMP XMSN OIL PRESS BAGGAGE FIRE FIRE 1 PULL

FIRE 2 PULL

ENG 1 OUT

Fire indication in No. 2 engine compartment. No. 1 engine GAS PROD

below limit. ENG 2 OUT

No. 2 engine GAS PROD

Refer to Engine Out Procedure.

below limit.

Table 3C-3.

WARNING LIGHT ILLUMINATION PRIOR TO LDP

SEGMENT WORDING

FAULT CONDITION

C BOX OIL PRESS

Combining gearbox oil

Reduce power. Land as soon as

pressure below limits.

practical.

C BOX OIL TEMP

Combining gearbox oil temperature above limit.

XMSN OIL TEMP

Transmission oil temperature above limit.

XMSN OIL PRESS

Transmission

Reduce power. Observe temperature within limits. If not, land as soon as possible. Reduce power. Observe temperature within limits. If not, land as soon as possible. Reduce power. Land as soon as

BAGGAGE FIRE

oil pressure

CORRECTIVE ACTION

below limit.

possible.

Smoke in baggage compartment.

Reduce power to minimum required. Land as soon as

possible and inspect tailboom FIRE 1 PULL

Fire indication in No. 1 engine compartment.

area for damage. Pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle. 55

BHT-212-FMS-7

Table 3C-3.

FAA APPROVED

WARNING LIGHT ILLUMINATION PRIOR TO LDP (Cont)

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

FIRE 2 PULL

Fire indication in No. 2 engine compartment.

Pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle.

ENG 1 OUT

No. 1 engine GAS PROD

Refer to Engine Out Procedure.

below limit. ENG 2 OUT

No. 2 engine GAS PROD

Refer to Engine Out Procedure.

below limit.

Table 3C-4.

WARNING LIGHT ILLUMINATION AFTER LDP

SEGMENT WORDING

FAULT CONDITION

CORRECTIVE ACTION

C BOX OIL PRESS

Combining gearbox oil pressure below limits.

Land.

C BOX OIL TEMP

Combining gearbox oil temperature above limit.

Land.

XMSN OIL TEMP

Transmission oil temperature above limit.

Land.

XMSN OIL PRESS

Transmission

Land.

oil pressure

below limit. BAGGAGE FIRE

Smoke in baggage compartment.

Land.

FIRE 1 PULL

Fire indication in No. 1 engine compartment.

Land, pull No. 1 handle, select MAIN bottle, then RESERVE if necessary, close No. 1 throttle.

FIRE 2 PULL

Fire indication in No. 2 engine compartment.

Land, pull No. 2 handle, select MAIN bottle, then RESERVE if necessary, close No. 2 throttle.

ENG 1 OUT

No. 1 engine GAS PROD below limit.

Refer to Engine Out Procedure.

ENG 2 OUT

No. 2 engine GAS PROD

Refer to Engine Out Procedure.

below limit.

56

FAA APPROVED

BHT-212-FMS-7

Section 4C PART C

I

4C-2.

POWER ASSURANCE

CHECK CHECK Perform

4C-6-B. TAKEOFF DISTANCE Takeoff distance is horizontal distance necessary to achieve 55 KIAS and CDP of

power assurance

check in

35 feet above takeoff surface. Refer to

accordance with Basic Flight Manual.

figure 4C-2.

If engine performance

4C-6-C. TAKEOFF FLIGHT PATH -

does not meet that

shown in Power assurance check chart, steps should be taken to ascertain cause of engine power loss.

4C-5. HOVER CEILING Figure 4C present Hover ceiling charts for

hovering in ground effect at a 10 foot skid height.

4C-6.

OBSTACLECLEARANCE Takeoff flight path begins at end of takeoff distance, at 35 feet above takeoff surface, and at VTOSS. Charts are involved in determination of takeoff flight path and are

titled as follows:

Takeoff flight path - climb index (figure 4C-3).

TAKEOFF

DISTANCE

Correction of Climb index (figure 4C-4). Takeoff flight

Minimum runway length required to

accelerate and stop is 2300 feet and is based on a rejected takeoff after an engine

failure.

This runway length was

established as that which an average pilot could accomplish a successful landing after a rejected takeoff, therefore a degree of conservatism

is included.

Interpolation of all data Is allowable but extrapolation

Is not permitted.

4C-6-A. TAKEOFF SAFETY

path - obstacle clearance

(figure4C-5). These charts

example:

are used as in following

Determine GW Determine OAT Determine Hp Vo VTOSS Determine headwind component (refer to figure 4C-6)

9000 pounds 15 °C Sea level

55 knots

17.5 knots

SPEED Takeoff safety speed (VToss) is 55 KCAS. 57

BHT-212-FMS-7 On appropriate Take Off Flight

Check maximum allowable GW (If

actual GW is less

Path - Obstacle

than maximum

Clearance for

Climb, figure 4C-

allowable, proceed)

11,200 pounds

Enter figure 4C-3 at

5,(Sheet 1 of 3)

locate climb Index point, corrected

OAT

for wind, which has just been determined, at a

Move vertically up to Hp

height above takeoff surface of 200 feet. Aline from this point through 35 foot

Move horizontally right to actual GW for takeoff Move vertically

height at 0

down to climb

index scale and read climb index On correction of climb index for wind chart (figure

17.0

4C-4), enter at

horizontal distance represents minimum height flight path from of takeoff takeoff of end distance and should be

climb index for zero wind (17.0), move horizontally to headwind component, (17.5

compared with height of known obstacles along flight path for obstacle clearance

knots), move

vertically downward and read climb index, corrected for wind.

25.0

4C-7. CLIMB AND DESCENT 4C-7-A. SINGLE ENGINE AT BEST RATE OF CLIMB SPEED Single engine rate of climb at VTOSS Is same as single engine rate of climb at best rate of climb speed and is unchanged from Section 1C.

4C-9. LANDING DISTANCE 4C-9-A. LANDING DISTANCE UNSCHEDULED Landing distance is distance necessary to come to a stop from a 25 foot height above

landing surface with only one engine operating. Refer to figure 4C-7. 58

Rev. 1

FAA APPROVED

O

BHT-212-FMS-7

4C-9-B. LANDING DISTANCE SCHEDULED For scheduled landings, landing distance is 25% more than unscheduled landing distance.

0

0

0 0 59

BHT-212-FMS-7

FAA APPROVED

HOVER CEILING IN-GROUND TAKE-OFF POWER ENGINE RPM 100% GENERATOR 150 AMPS

Figure 4C-1.

60

EFFECT SKID HEIGHT 10 FT. HEATER OFF GROSSWEIGHT TO 11,200 LB.

Hover ceiling chart (Sheet 1 of 3)

FAA APPROVED

BHT-212-FMS-7

IN-GROUND TAKE-OFF POWER ENGINE RPM 100% GENERATOR 150 AMPS

EFFECT SKID HEIGHT 10 FT HEATER ON GROSSWEIGHT TO 11,200 LB.

20.000

8..ooo

(OATLIMIT) 20C

Figure 4C-1.

40'C

Hover ceiling chart (Sheet 2 of 3)

61

FAA APPROVED

BHT-212-FMS-7

HOVER CEILING EFFECT

IN-GROUND

SKID HEIGHT 10 FT. WINTERIZATION HEATER ON GROSSWEIGHT TO 11,200 LB.

TAKE-OFF POWER ENGINE RPM 100% GENERATOR 150 AMPS

18,000

(OATLIMIT) 20°C

50

16,000

40°C

14,0000

8,000

6,000

4,000 -

2,000

6,000

7.000

8,000

9.000

10.000

11,000

GROSSWEIGHT -POUNDS

212FMS7C-4-1-3

Figure 4C-1.

62

Hover ceiling chart (Sheet 3 of 3)

FAA APPROVED

BHT-212-FMS-7

TAKE-OFF DISTANCE DISTANCE REQUIRED TO ATTAIN C.D.P. (35 FT. AND 55 KNOTS) POWERREQUIRED TO INITIATED FROM 10 FT SKID HT. HOVER+5%TORQUE ENGINE RPM 100% VTOSS = 55 KIAS GENERATOR75 AMPSEACH HEATER OFF OR ON ZERO WIND WINTERIZATIONHEATER OFF OR ON

GROSS WEIGHT 8000 LB. 14000

12000

10000 FT -DENSITY

ALTITUDE LIMIT

10000

63

BHT-212-FMS-7

FAA APPROVED

TAKE-OFF DISTANCE DISTANCE

REQUIRED

TO ATTAIN

POWER REQUIRED TO HOVER +5% TORQUE ENGINE RPM 100% GENERATOR 75 AMPS EACH ZERO WIND

C.D.P. (35 FT. AND 55 KNOTS)

INITIATED

FROM 10 FT SKID

HT.

VTOSS = 55 KIAS HEATER OFF OR ON WINTERIZATION HEATER OFF OR ON

GROSS WEIGHT

9000

LB.

14000 10000 FT.

DENSITY ALTITUDE

10000

ENGINE

4000 FT/MIN.) (150

2000

650

700

750

800

850

900

950

1000

TAKE-OFFDISTANCE'FEET 212FMS7C-4-2-2

Figure 4C-2.

64

Takeoff distance (Sheet 2 of 4)

BHT-212-FMS-7

FAA APPROVED

TAKE-OFF DISTANCE DISTANCE

REQUIRED

TO ATTAIN

POWER REQUIRED TO HOVER +5% TORQUE ENGINE RPM 100% GENERATOR 75 AMPS EACH ZERO WIND

C.D.P. (35 FT. AND 55 KNOTS)

INITIATED

FROM 10 FT SKID HT.

VTOSS = 55 KIAS HEATER OFF OR ON WINTERIZATION HEATER OFF OR ON

GROSS WEIGHT 10,000 LB. 14000

12000

10000

Figure 4C-2.

Takeoff distance (Sheet 3 of 4)

65

BHT-212-FMS-7

FAA APPROVED

TAKE-OFF DISTANCE DISTANCE REQUIRED TO ATTAIN C.D.P. (35 FT. AND 55 KNOTS) POWER REQUIRED TO INITIATED FROM 10 FT SKID HT. HOVER +5%TORQUE ENGINE RPM 100% VTOSS = 55 KIAS GENERATOR 75 AMPS EACH HEATER OFF OR ON ZERO WIND WINTERIZATION HEATER OFF OR ON GROSS WEIGHT 11,200 LB.

Figure 4C-2.

66

Takeoff distance (Sheet 4 of 4)

0

BHT-212-FMS-7

FAA APPROVED

10.000 FT

Figure 4C-3.

Takeoff flight path - climb index

Rev. 1

67

BHT-212-FMS-7

FAA APPROVED

KNOTS

35

20 15

10

0

10

20

30

40

50

60

70

80

90

100

110

CLIMB INDEX - CORRECTED FOR WIND 212FMS7-4C-4

Figure 4C-4.

68

Rev. 1

Correction of climb index

FAA APPROVED

BHT-212-FMS-7

INDEX = 104-12 CLIMB INDEX - CORRECTEDFOR WIND

Figure 4C-5.

Takeoff flight path - obstacle clearance for climb (Sheet 1 of 3)

Rev. 1

69

BHT-212-FMS-7

FAA APPROVED

INDEX =12 TO 5

CLIMB INDEX

0

20

HORIZONTAL DISTANCE- FT (FROM END OF TAKE--OFF DISTANCE) 212FMS7-4C-5-2

Figure 4C-5.

70

Rev. 1

Takeoff flight path - obstacle clearance for climb (Sheet 2 of 3)

BHT-212-FMS-7

FAA APPROVED

INDEX =5 TO 3.5

CLIMB INDEX

180

60

40 0

1000

2000

HORIZONTAL DISTANCE -

3000

4000

5000

6000

7000

FT (FROM END OF TAKE-OFF DISTANCE) 212FMS7-4C-5-3

Figure 4C-5.

Takeoff flight path - obstacle clearance for climb (Sheet 3 of 3)

Rev.1

71

BHT-212-FMS-7

FAA APPROVED

HEADWIND COMPONENT- KNOTS 0

5

90° 80° 70°

10

15

60°

50°

C 20

25

30

35

CROSSWIND COMPONENT

40

LIMIT

40°

WIND DIRECTION 15 KNOTS

FROM TAKE OFF HEADING

10 KNOTS CROSSWIND COMPONENT 5 KNOTS

0 KNOTS

0

5

10

15

20

25

30

35

40

REPORTED WINDSPEED -KNOTS

EXAMPLE

1 TAKE OFF HEADING .

...

........

..... .

° 170

2 3. 4 5. 6.

REPORTEDWIND DIRECTION .. ................. ..................................... 200 ° WIND DIRECTION, DEGREESFROM TAKE OFF HEADING .................... 30 REPORTEDWIND SPEED ........................... .... .................... 20 KNOTS ENTER CHART AT REPORTEDWIND SPEED,POINT A PROCEEDUPWARD. FOLLOWING THE SHAPE OF THE CURVED LINES. TO WIND DIRECTION, DEGREESFROM TAKE-OFF HEADING, POINT B. 7. PROCEEDVERTICALLY UPWARD TO THE HEADWIND COMPONENTSCALE AND READ HEADWIND COMPONENT............. 17 5 KNOTS 212FMS7C-4-6

Figure 4C-6.

72

Headwind component chart

BHT-212-FMS-7

FAA APPROVED

SINGLE ENGINE LANDING DISTANCE FROM

25 FT. HEIGHT 40 KIAS RATE OF DESCENT 500 FPM LANDING DECISION POINT 100 FEET HARD SURFACED RUNWAY, ZERO WIND

POWER AS REQUIRED ENGINE RPM 97% GENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)

GROSS WEIGHT 8000 LB. AND LESS 16.000

14,000 OAT

I 0

50C 12.000 40C 30C 20. 12,000_30 10° 10,000

100

Figure 4C-7. 120

Landing distance (Sheet 1 of 4)

140

121

Figure 4C-7.

160

200

180

FEET LANDING DISTANCE DISTANCE- FEET LANDING

Landing distance

(Sheet

220

240

73

2FMS7C-4-7-1 212FMS7C-4-7-1

of 4)

73

BHT-212-FMS-7

FAA APPROVED

SINGLE ENGINE

LANDING DISTANCE FROM 25 FT. HEIGHT POWERAS REQUIRED ENGINE RPM 97% GENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)

40 KIAS RATE OF DESCENT500 FPM LANDING DECISIONPOINT 100 FEET HARD SURFACEDRUNWAY, ZERO WIND

GROSSWEIGHT 9000 LB. 16.000

-40°C 0

-30° C

-20°C 12.000 10,000 FT DENSITY

ALTITUDELIMIT

8000

LIMIT CLIMB PERFORMANCE (I50

6000

2000 4000

FT/MIN)

-

100

200

300

400

LANDINGDISTANCE- FEET 212FMS7C-4-7-2

Figure 4C-7.

74

Landing distance (Sheet 2 of 4)

FAA APPROVED

BHT-212-FMS-7

SINGLE ENGINE

LANDING DISTANCE FROM 25 FT. HEIGHT POWERAS REQUIRED

40 KIAS

ENGINE RPM 97%

RATE OF DESCENT 500 FPM

GENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)

LANDING DECISIONPOINT 100 FEET HARD SURFACEDRUNWAY ZERO WIND

GROSSWEIGHT 10,000 LB. 16,000

14,000

12.000

-

OAT -50°C 40 C

-30C 10,000

LIMIT CLIMB PERFORMANCE (150 FT/MIN)

6000

4000

LANDING DISTANCE- FEET 212FMS7C-4-7-3

Figure 4C-7.

Landing distance (Sheet 3 of 4)

75

BHT-212-FMS-7

FAA APPROVED

SINGLE ENGINE

LANDING DISTANCE FROM 25 FT. HEIGHT POWERAS REQUIRED

40 KIAS

ENGINE RPM 97%

RATE OF DESCENT 500 FPM

GENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)

LANDING DECISIONPOINT 100 FEET HARD SURFACED RUNWAY, ZERO WIND

GROSSWEIGHT 11.200 LB. 16.000

14,000

40C

8,000

4000

CLIMB PERFORMANCE LIMIT

4000-(150

100

120

FT/MIN)

140

160

180

200

220

LANDINGDISTANCE- FEET 212FMS7C-4-7-4

Figure 4C-7.

76

Landing distance (Sheet 4 of 4)

BHT-212-FMS-8

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

EMERGENCY FLOTATION 212-706-021 CERTIFIED AUGUST 28, 1972

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when emergency flotation kit has been installed.

Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter COPYRIGHT NOTICE COPYRIGHT 1995 BELL

HELICOPTERINC.

ANDBELLHELICOPTER TEXTRON INC. A DIVISIONOF TEXTRONCANADALTD. ALLRIGHTSRESERVED

A Subsidiary of Textron Inc POST OFFICE BOX 482 · FORT WORTH, TEXAS 76101

REISSUE

-

14

BHT-212-FMS-8 NOTICE PAGE

PROPRIETARY RIGHTS NOTICE

Manufacturer's Data portion of this supplement 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.

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

NP

FAA APPROVED

BHT-212-FMS-8 LOG OF REVISIONS

Original...........0

.............

28 AUG 72

Revision ..........

2 ..............

01 OCT 84

Revision..........1

..............

20 FEB 75

Reissue...........0

.............

14 AUG 95

LOG OF PAGES REVISION PAGE

NO.

REVISION PAGE

FLIGHT MANUAL

MANUFACTURER'S DATA

Title- NP.............................. 0 A-B .................................. 0 1-

4 ...................................

5/6 ......................................

NO.

0

7- 8 ................................... 0 9/10..................................... 0

0

NOTE Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-8

FAA APPROVED LOG OF APPROVED

Original...........0 Revision..........1

............ ..............

28 AUG 72 20 FEB 75

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

REVISIONS

Revision .......... Reissue...........0

2 .............. .............

01 OCT 84 14 AUG 95

FAA APPROVED

Section 1-3.

BHT-212-FMS-8

1

TYPES OF OPERATION

Emergency flotation kit (212-706-021) is Installed

for emergency

ditching

INSTALLATION

LIMITATIONS.

ADDITIONAL EQUIPMENT

and Is

RESTRICT

OF

OPTIONAL

MAY FURTHER

CG RANGE.

(SEE

approved for VFR operations only.

SECTION OF MANUFACTURER'S 1DATA TO THIS

Ferry flight with floats inflated is prohibited. In event of unintended

SUPPLEMENT FOR LOADING EXAMPLES.)

inflation, a landing must be accomplished at first suitable location (not on water) and

system deflated and stowed or removed prior to further flight. Further flight after a water landing is prohibited. It is mandatory to have FLOAT switch in OFF position and SAFE INFLATE light extinguished when operating over land.

Provisions for life rafts, life preservers, and survival equipment are included as part of emergency flotation kit.

AIRSPEED

1-7

Float inflation airspeed is 55 knots or less.

1-7-A. POWERON inflated

1-7-B.

float VNE is 60 knots.

POWER OFF

Inflated float 60 knots for GW up to 10,500 pounds

1-6.

WEIGHT AND CENTER OF

GRAVITY

(4762.8 kilograms). 65 knots for GW 10,500 to 11,200 pounds (4762.8 to 5080.3 kilograms).

Actual weight change shall be determined

after emergency flotation kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable lim i ts . CG limits are from Station 132.0 to 142.5 (figure 1-1).

Maximum water speed for landing is 25 knots. WARNING UNDESIRABLE NOSE UP PITCHING WILL OCCUR AT

WARNING

AIRSPEEDS ABOVE 55 KNOTS DURING INFLATION CYCLE.

INDISCRIMINATE LOADING OF HELICOPTER MIGHT RESULT IN VIOLATION OF PERMISSIBLE CG

AUTOROTATION SPEEDS ABOVE 60 KNOTS WILL RESULT IN UNDESIRABLE NOSE UP

FAA APPROVED

BHT-212-FMS-8

1-20.

PITCHING WHEN AT OR NEAR AFT CG AND LIGHTER GW. NOTE

Operation automatic

INSTRUMENT

MARKINGS AND PLACARDS FLOAT INFLATION ABOVE 55 KTS IS PROHIBITED

is based on use of arming system and

visual SAFE INFLATE light.

1-8.

ALTITUDE

Maximum operating Is 10,000 feet.

11,000

8000

6000

130

132

134

136

13B

140

LONGITUDINALC.G. STATION- INCHES

142

144

212-FS8-1-1

Figure 1-1. Center of gravity vs. gross weight chart

2

FAA APPROVED

BHT-212-FMS-8

Section 2 2-3. PREFLIGHT CHECK

NOTE

SAFE INFLATE light must be to inflate floats illuminated electrically.

2-3-B. EXTERIORCHECK Floats - Stowed. Clean and

When system is armed, SAFE INFLATE light will illuminate

Secured; pressure

float inflation above safe inflate speed.

Float covers and support -

between 0 and 55 knots to prevent

secured.

Nitrogen bottles within

blue or green area on chart for

ambient temperature.

SAFE INFLATE light extinguished

NOTE NOTE Ensure floats have had periodic

inflation

performed.

shall be

above 55 knots.

It is advisable to have FLOAT switch in POWER position during

takeoff and landing, or when

and inspection

operating below 500 feet above

water.

Auxiliary stabilizer - Secured. FLOAT switch shall be off and land.

2-7-C.

OVER WATER

2-9.

OPERATIONS Manual inflation

lever -

Down and

safetied. FLOAT switch -

IN-FLIGHT OPERATIONS

2-9-C.

BEFORE LANDING

POWER.

safetied.

INFLATEswitch cover - Down. FLOAT POWER caution Illuminated. SAFE INFLATE light -

light

-

FLOAT switch -

POWER.

INFLATE switch cover -

Down.

Illuminated. Illuminated. SAFE INFLATElight - Illuminated. 3

BHT-212-FMS-8

FAA APPROVED

Section 3 3-7.

ELECTRICAL SYSTEM

Manual inflate lever -

AFTER INFLATE SWITCH HAS BEEN ACTUATED

Pull. Manual inflate lever -

3-7.

Pull.

ELECTRICAL SYSTEM

3-7-A.

FLOATS FAIL TO INFLATE EMERGENCY LANDING

3-12.

LANDING

illuminated with FLOAT switch in

GEAR

POWER position.

Airspeed shall be reduced below 55 knots

and FLOAT switch positioned to POWER when it is determined that a water landing is necessary. If power on landing is to be made, floats may be inflated on approach below 55 knots or, If conditions warrant,

during hover. For full autorotation landing, refer to WATER LANDING

3-12-B.

MANUAL ACTUATION

MODE Manual inflate handle -

(POWER OFF).

3-12-A.

WARNING

ELECTRICAL ACTUATION

MODE

MANUAL INFLATION DOES NOT

HAVE AIRSPEED SWITCH

FLOAT POWERlight - Illuminated. SAFE INFLATE light (below 55 knots).

-

Float INFLATE switch -

NOTE

Float inflation

Illuminated

FLOATS OTECTION. FLOATS SALL SHALL NOT BE MANUALLY INFLATED ABOVE SAFE INFLATE AIRSPEED OF 55 KNOTS.

Lift guard and

NOTE

system is

automatically armed below 55 knots when SAFE INFLATE light is 4

Pull.

REFER

TO SECTION

1 FOR

MAXIMUM AIRSPEED WITH FLOATS INFLATED.

FAA APPROVED

3-12-C.

BHT-212-FMS-8

WATER LANDING (POWER

OFF)

Adjust cyclic and collective

sufficiently

to perform a touchdown with nose up attitude

and a water speed as low as

possible. After water landing, inspect

Complete electrical actuation mode or manual actuation mode to inflate floats. Establish an autorotative glide speed of 55 to 60 knots for GW up to 10,500 pounds (4762.8 kilograms) or 60 to 65 knots for GW above 10,500 pounds

for damage and determine If helicopter

should be abandoned. NOTE

Continued flight is prohibited after a water landing.

(4762.8 kilograms). Execute a moderate cyclic flare at 100

feet altitude to reduce airspeed to approximately 30 knots.

Section 4 No change from basic manual.

5/6

BHT-212-FMS-8

MANUFACTURER'S DATA

Section 5 A

5-8.

SAMPLE LOADING

5-8-B. EMERGENCYFLOTATION KIT (212-706-021) AND AUXILIARY

PROBLEM NOTE Following examples assume that

each passenger weighs 170

INSTALLED 5-8-B-1.

7000 POUNDS (3175.2

pounds (77.1 kilograms).

5-8-A. EMERGENCY FLOTATION KIT (212-706-021) ONLY INSTALLED 5-8-A-1.

WEIGHT EMPTY BELOW 7100 POUNDS (3220.6 KILOGRAMS):

Pilot and copilot can carry a maximum of seven passengers in forward and mid-row seats when aft seats (facing outboard) are

WEIGHT EMPTY BELOW KILOGRAMS):

Pilot and copilot can carry a maximum of four passengers if seated in forward seats, or a combination of five passengers in mid-row seats (facing forward) and two in forward seats.

NOTE With 110 pounds (49.9 kilograms) in baggage compartment, all nine seats may mid-row seats forward be may be forward and mid-row occupied wit a seas emp

unoccupied. For each two passengers in aft seats, one passenger can be carried in additional forward or mid-row seats.

5-8-B-2.

WEIGHT EMPTY 7000 TO 7400 POUNDS (3175.2 TO 3356.6 KILOGRAMS):

Pilot and copilot can carry a combination

WARNING

0I Iw

of four passengers in forward seats and one in mid-row seats, or five in mid-row seats and three in forward seats.

BAGGAGE COMPARTMENT WEIGHT SHALL BE REMOVED FOR SINGLE PILOT OPERATION. NOTE

NOTE With 75 pounds (34.0 kilograms) in baggage compartment, all nine forward and mid-row seats may be occupied with aft seats empty.

With 50 pounds (22.7 kilograms) in baggage compartment, all nine forward and mid-row seats may be occupied with aft seats empty. 7

MANUFACTURER'S DATA

BHT-212-FMS-8

5-8-B-3.

WEIGHT EMPTY GREATER THAN 7400 POUNDS (3356.6 KILOGRAMS):

Pilot and copilot can carry a combination of four passengers in forward seats and three in mid-row seats, or five In mid-row seats and three in forward seats.

7470 POUNDS (3265.9 TO 3388.4 KILOGRAMS): Pilot and copilot can carry a maximum of

eight passengers in forward and mid-row seats If aft seats are unoccupied. With two passengers in aft seats (facing outboard), one additional passenger may be seated in forward or mid-row seats.

WARNING

BAGGAGE COMPARTMENT

COMPARTMENT

WEIGHT SHALL BE REMOVED

BAGGAGE

FOR SINGLE PILOT OPERATION.

WEIGHT SHALL BE REMOVED FOR SINGLE PILOT OPERATION.

NOTE With 40 pounds (18.1 kilograms) in baggage compartment, all nine forward and mid-row seats may be occupied with aft seats empty.

5-8-C. EMERGENCY FLOTATION KIT (212-706-021) AND AUXILIARY FUEL KIT (212-899-243, 90 GALLON) INSTALLED

NOTE With 25 pounds (11.3 kilograms) in baggage compartment, all nine forward and mid-row seats may be occupied with aft seats empty.

5-8-D. EMERGENCY FLOTATION KIT (212-706-021) AND AUXILIARY FUEL KIT (212-899-243, 20/90 GALLON) INSTALLED

5-8-C-1. WEIGHT EMPTY BELOW 7200 POUNDS (3265.9 KILOGRAMS):

5-8-D-1.

Pilot and copilot can carry a maximum of five passengers in mid-row seats and two in forward seats, or four in forward seats and one In mid-row seats If aft seats are With two passengers in aft unoccupied. seats (facing outboard), one additional passenger may be seated in forward or mid-row seats.

Pilot and copilot can carry a maximum of four passengers in forward seats and one in mid-row seats, or five in mid-row seats and two in forward seats if aft seats are With two passengers in aft unoccupied. seats, one additional passenger may be seated in forward or mid-row seats.

NOTE

NOTE

With 85 pounds (38.6 kilograms) in baggage compartment, all nine forward and mid-row seats may be occupied with aft seats empty.

With 90 pounds (40.8 kilograms) in baggage compartment, all nine forward and mid-row seats may be occupied with aft seats empty.

5-8-C-2. 8

WEIGHT EMPTY BELOW 7000 POUNDS (3175.2 KILOGRAMS):

WEIGHT EMPTY 7200 TO

5-8-D-2.

WEIGHT EMPTY 7000 TO

MANUFACTURER'S DATA

BHT-212-FMS-8

7500 POUNDS (3175.2 TO 3402.0 KILOGRAMS):

7300 POUNDS (3311.3 KILOGRAMS):

Pilot and copilot can carry a maximum of four passengers in forward seats and three

Pilot and copilot can carry a maximum of six passengers In forward and mid-row

in mid-row seats, or five in mid-row seats

seats when aft seats (on tanks) are

and three in forward seats if aft seats are unoccupied. With two passengers in aft seats, one additional passenger may be seated in forward or mid-row seats.

unoccupied. For each two passengers in aft seats, one additional passenger may be seated in forward or mid-row seats.

5-8-E-2.

BAGGAGE COMPARTMENT WEIGHT SHALL BE REMOVED FOR SINGLE PILOT OPERATION.

BAGGAGE

COMPARTMENT

WEIGHT SHALL BE REMOVED FOR SINGLE PILOT OPERATION.

NOTE With 45 pounds (20.4 kilograms) in baggage compartment, all nine forward and mid-row seats may be occupied with aft seats empty.

NOTE With 60 pounds (27.2 kilograms) in baggage compartment, all nine forward and mid-row seats may be occupied with aft seats empty.

5-8-E. EMERGENCY FLOTATION KIT (212-706-021) AND AUXILIARY FUEL KIT (212-706-044) INSTALLED 5-8-E-1.

WEIGHT EMPTY BELOW

9/10

BHT-212-FMS-9

~SUPP ROTORCRAFT FLIGHT MANUAL

0*

EMERGENCY FLOTATION 212-706-042 CERTIFIED AUGUST 9, 1973

This supplement shall be attached to Model 212 Flight Manual when emergency flotation kit has been installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Helicop ll1 ,___Bell 0g*~ of Textron Inc. A Subsidiary

NOTICE COPYRIGHT COPYRIGHT

1995

BELL HELICOPTER INC. ANDBELLHELICOPTER TEXTRON INC. A DIVISIONOF TEXTRON CANADALTD ALLRIGHTS RESERVED

POST OFFICE BOX 452 * FORT WORTH.TEXAS 76101

REISSUE

-

14 AUGUST

1995

BHT-212-FMS-9

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P.

O. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

BHT-212-FMS-9

Original...........0

.............

09 AUG 73

Revision ..........

4 ..............

30 APR 79

Revision..........1

..............

01 JAN 74

Revision ..........

5 ..............

01 OCT 84

30 AUG 74

Reissue...........0

.............

14 AUG 95

Revision ..........

2.............

Revision .......... 3 ..............

18 APR 75 LOG OF PAGES

a*

REVISION NO.

PAGE FLIGHT MANUAL

Title - NP ..............................

REVISION NO.

PAGE A -B

..................................

0

1-4 ...................................0

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded

pages. A

FAA APPROVED

BHT-212-FMS-9 LOG OF APPROVED REVISIONS 09 AUG 73

Revision ..........

4 ..............

30 APR 79

Revision ..........

1 ..............

01 JAN 74

Revision ..........

5 ..............

01 OCT 84

Revision ..........

2 .............

30 AUG 74

Reissue ...........

0 .............

14 AUG 95

Revision ..........

3 ..............

18 APR 75

Original...........0

.............

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

BHT-212-FMS-9

FAA APPROVED

Section

1-1.

1

1-5.

INTRODUCTION

Emergency

flotation

kit (212-706-042)

is

installed for assistance during emergency

equipment,

for life rafts, survival and life preservers

are

included as part of this kit.

1-3.

It is mandatory to have FLOAT ARM switch

OFF and FLOAT ARM caution extinguished

ditching.

Provisions

CONFIGURATION light

when operating over land.

It is mandatory to have emergency flotation safety pin removed prior to flight over water.

TYPES OF OPERATION

1-6.

Kit is approved for VFR and IFR operations. Emergency flotation system is not designed to be inflated in flight. EMER INFLATION - PULL lever may be used for Inflating flotation bags in event immersion

switches malfunction, or at option of pilot,

while in hover, before initiating

an

emergency landing.

WEIGHT AND CENTER OF

GRAVITY Actual weight change shall be determined

after emergency flotation kit is Installed and ballast readjusted, if necessary, to bring empty weight CG to within allowable limits.

1-7. AIRSPEED Autorotation

WARNING

airspeed is 80 knots.

Maximum water speed for ditching

is 24

SEVERE NOSE UP PITCHING WILL OCCUR IF EMERGENCY

knots with lowest possible sink rate upon water contact. Flight operations with float

FLOTATION BAGS ARE INFLATED

bags inflated are not intended.

IN FORWARD

FLIGHT

OR

DESCENT.

Inflation of emergency flotation during forward flight is prohibited.

bags

Forward flight after inflation of emergency flotation bags is prohibited.

WARNING SEVERE NOSE UP PITCHING WILL OCCUR IF EMERGENCY FLOTATION BAGS ARE INFLATED IN FORWARD FLIGHT. CREW AND PASSENGER DOOR MUST REMAIN CLOSED DURING DITCHING. 1

BHT-212-FMS-9

1-8.

FAA APPROVED

ALTITUDE

1-19.

Maximum Hp for inflation of floats is 10,000 feet. Helicopter operation above 10,000 feet is permitted provided floats are

LANDING GEAR

When landing occurs on land, bags must be deflated, stowed, or removed prior to further flight.

not inflated above 10,000 feet, ARM switch

is in OFF position, and FLOAT ARM caution light is extinguished. Inflation of floats above 5000 feet and below 10,000 feet Hp requires different pressure limits for nitrogen bottle. Refer to Section 2, EXTERIOR INSPECTION.

1-9.

1-20. INSTRUMENT

MARKINGS AND PLACARDS Refer to table 1-1.

MANEUVERING

In event of unintended inflation, reduce airspeed, adjust sink rate to 200 feet per minute or less, and land immediately. Table 1-1. PLACARDS INFLATION

AND DECALS

OR OPERATION IN FORWARD FLIGHT IS PROHIBITED REMOVE PIN BEFORE FLIGHT

EMER INFLATION - PULL (TABLE

I.D. 911206)

Section 2 2-3. 2-3-B.

PREFLIGHT CHECK

temperature

as shown on chart decal,

located on floats inflation bottle.

For

float inflation above 5000 feet and below 10,000 feet Hp, fill bottle to a pressure

EXTERIOR CHECK

150 PSIG below pressure required by

chart decal. Ensure bottle is filled at an

Float covers and supports -

Clean and

secured. Nitrogen bottle -

Check bottle pressure to ensure

that it does not exceed 3100 PSIG or drop below 2850 PSIG, prior to takeoff.

Secured and pressure

within allowable limits for ambient 2

above.

FAA APPROVED

BHT-212-FMS-9 NOTE

O^^

Ensure floats

Emergency

FLOAT ARM caution light -

Illuminated.

have had periodic

flotation

safety

pin -

Remove.

It is advisable to have FLOAT ARM switch in ARM with FLOAT

a2-7__-„ 2-7. BEFORE

.,.

ARM caution light illuminated

during takeoff and landing.

-.

TAKEOFF

Passenger step -

FLOAT ARM switch should be in OFF and FLOAT ARM caution light

Retracted.

extinguished when operating over land.

EMER INFLATION - PULL lever and safetied. FLOAT ARM switch -

Down

ARM.

2-12.

POSTFLIGHT CHECK

Emergency flotation safety pin - Install.

Section 3 3-3. ENGINE

It is recommended in order to ensure low sink rate and low forward speed that

flare be held until tail rotor contacts

NOTE

water.

Float bags should inflate

Rapid reduction of collective will result in undesirable nose up

automatically on water contact. If automatic system does not operate immediately, pull EMER INFLATION -

pitching.

PULL handle.

3-3-J. EMERGENCY OVER WATER

NG FLOTATION

Establish an autorotative glide speed of

IF AUTOMATIC

55 to 60 knots for GW up to 10,500 pounds (4762.8 kilograms) and 60 to 65

SYSTEM DOES NOT OPERATE UPON WATER IMMEDIATELY

(4762.8 kilograms).

INFLATION - PULL LEVER.

At 100 feet altitude, execute a moderate

CREW AND PASSENGER DOOR

perform a touchdown with nose up attitude and water speed as low as possible.

After water landing, inspect for damage and determine if helicopter should be abandoned.

knots for GW above 10,500 pounds

cyclic flare to reduce airspeed to approximately 30 knots. Adjust collective and cyclic sufficiently to

CONTACT,

PULL

EMER

MUSTREMAINCLOSEDDURING DITCHING.

3

FAA APPROVED

BHT-212-FMS-9

ELECTRICAL ACTUATION MODE determine if helicopter should be WHEN

FLOAT

INFLATED,

CREW

BAGS

abandoned.

ARE

EGRESS THROUGH

MAY

DOORS

ACCOMPLISHED

BE

BY

JETTISONING CREW DOORS.

3-3-J-1.

CREW AND PASSENGER DOOR MUST REMAIN CLOSED DURING

DITCHING.

ELECTRICAL ACTUATION MODE

FLOAT ARM switch -

NOTE

ARM.

Further flight after a water landing

FLOAT ARM caution light - Illuminated.

is prohibited.

3-14. ELECTRICAL 3-3-J-2.

FAILURES

MANUAL ACTUATION MODE

EMER INFLATION - PULL lever -

If FLOAT ARM caution light illuminates with FLOAT ARM switch OFF breaker.

Pull.

If FLOAT ARM caution light remains illuminated after pulling circuit breaker -

3-3-K. EMERGENCY- WATER LANDING (AUTOROTATION) WITH ELECTRICAL FAILURE Establish an autorotative

Land as soon as practical. Inflation may be made manually by pulling EMER INFLATION - PULL lever.

knots for GW above 10,500 pounds (4762.8 kilograms). At 100 feet altitude, execute a moderate

flare to reduce airspeed

approximately up attitude.

30 knots, maintain

to nose

Adjust collective and cyclic sufficiently to perform a touchdown with nose up attitude and a water speed as low as possible. Pull EMER INFLATION - PULL

lever when water contact is imminent.

Approach and landing should be in same manner as controlled 4

NOTE

glide speed of

55 to 60 knots for GW up to 10,500 pounds (4762.8 kilograms) and 60 to 65

cyclic

Pull circuit

Certification

of emergency

flotation kit is based on both electrical and manual systems operating.

If floats fail to inflate upon water contact

with float arm switch in ARM. INFLATION - PULL lever -

Pull.

EMER

BHT-212-FMS-1

1

* MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

VLF-1000 NAVIGATION SYSTEM 212-899-118 CERTIFIED MAY 21, 1974

This supplement shall be attached to the Bell Helicopter Model 212 Flight Manual when VLF1000 Navigation System is installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter NOTICE COPYRIGHT COPYRIGHT INC.1995 BELL

HELICOPTER INC.

ANDBELLHELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD. ALLRIGHTS RESERVED

of TettronIn A Subsidiary POSTOFFICE BOX482 * FORTWORTH. TEXAS 76101

REISSUE -

14 AUGUST 1995

FAA APPROVED

BHT-212-FMS-11 NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-11

FAA APPROVED LOG OF REVISIONS Original...........0 Reissue...........0

............. .............

21 MAY 74 14 AUG 95 LOG OF PAGES REVISION NO.

PAGE

A-B

FLIGHTMANUAL Title - NP..............................

~

0

REVISION NO.

PAGE

..................................

1/2............

0

.................... 0

NOTE

Revised text Is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-11

FAA APPROVED LOG OF APPROVED REVISIONS

Original...........0 ......... Reissue...........0.............

21 MAY 74 14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

BHT-212-FMS-11

FAA APPROVED

Section

1

TYPES OF OPERATION

1-3.

1-20.

INSTRUMENT

MARKINGS AND PLACARDS No flight operation which depend of usage of VLF-1000 will be conducted.

NO OPERATION PREDICATED ON USE OF VLF-1000 NAV SYSTEM

WEIGHT AND CENTER OF

1-6.

GRAVITY

VLF-1000 nav system shall be operated in

accordance with manufacturer's instructions.

Actual weight change shall be determined

after VLF-1000 navigation system kit is

installed and ballast readjusted, if necessary,

to return empty weight CG to

within allowable limits.

Section2 2-3. 2-3-C.

PREFLIGHT CHECK VLF-1000 NAV SYSTEM

VLF NAV circuit breaker -

In.

NOTE

Refer to manufacturer's data for preflight and operating instructions required for VLF-1000 NAV SYSTEM.

1/2

BHT-212-FMS-1 2

12

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

HEATED WINDSHIELD 212-899-244 CERTIFIED JUNE 3, 1974

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when Heated Windshield is installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

ell Helicopters COPYRIGHT NOTICE COPYRIGHT 1995 ® BELL HELICOPTER INC. ANDBELLHELICOPTER TEXTRON INC. A DIVISION OF TEXTRON CANADA LTD ALLRIGHTS RESERVED

POST

A Subidiaryof Textron Inc OFFICEBOX42 * FORTWORTH. TEXAS 7101

REISSUE -

14 AUGUST 1995

BHT-212-FMS-12

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

BHT-212-FMS-12 LOG OF REVISIONS

Original ...........

0.............

03 JUN 74

Reissue ...........

0.............

14 Aug 95 LOG OF PAGES

a*

PAGE

REVISION NO.

Title - NP ..............................

0

1- 2 ...................................

0

PAGE

REVISION NO.

A-B ..................................0

Revised text Is Indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-12 LOG OF APPROVED 0........0 ........ Original .. Reissue...........0.............

03 JUN 74 14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

REVISIONS

FAA APPROVED

Section

1-6.

BHT-212-FMS-12

1

WEIGHT AND CENTER OF

GRAVITY

1-20.

INSTRUMENT

MARKINGS AND PLACARDS

Actual weight change shall be determined after heated windshield kit is installed and ballast readjusted, If necessary, to bring

WINDSHIELD HEAT LH RH

empty weight CG to within allowable limits.

DIM

BRT

TEST

CAUTION STANDBY COMPASS UNRELIABLE WITH WINDSHIELD HEAT ON.

Section 2 2-3. PREFLIGHT CHECK WSHLD HEAT LH switch switch --

OFF. OFF.

2-7. BEFORE TAKEOFF WSHLD

HEAT RH RH switch--OFF. switch - OFF. WSHLD HEAT WSHLD

HEAT LH switch - ON (if (green) 'desired), illuminates. LH ON segment

WINDSHIELD HEAT circuit breakers IN.

WSHLD HEAT RH switch

BATTERYswitches - ON.

illuminates.

illuminates.

-

ON (if

desired), RH ON segment (green)

Windshield heat test switch - TEST, LH ON and RH ON (green), LH FAIL and RH FAIL (yellow) segments illuminate.

Position to BRT for daylight operations.

NOTE LH ON and RH ON windshield heat

segments (green) will illuminate and extinguish as windshield

cycle occurs.

heat

BHT-212-FMS-12

FAA APPROVED

Section 3 EMERGENCY PROCEDURES

3-7.

3-7-C.

3-7-D. WINDSHIELD HEAT CIRCUIT BREAKER(S) TRIPPED

SYSTEM

ELECTRICAL

WSHLD HEAT switch(es) -

DC GENERATOR FAILURE

NON ESS BUS switch -

OFF.

MANUAL.

NOTE

Power for heated windshields is furnished by non essential bus. Table 3-1. PANEL WORDING

CAUTION LIGHTS

FAULT CONDITION

CORRECTIVE

ACTION

WINDSHIELD FAIL LH

HEAT

heating Left windshield element inoperative.

WSHLD HEAT LH switch -

OFF.

WINDSHIELD FAIL RH

HEAT

heating Right windshield element inoperative.

WSHLD HEAT RH switch -

OFF.

2

BHT-212-FMS-13

a

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

ENVIRONMENTAL CONTROL UNIT (AIR CONDITIONING) 212-706-025 SN 30597 AND SUB CERTIFIED JUNE 17, 1974

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when environmental control unit is installed.

*^b

*^&b

Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

of TextronInc A Subsidiary

NOTICE COPYRIGHT BELL HELICOPTER INC. ^ BELL HELICOPYRIGHT 995 --AND HELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD ALLRIGHTS RESERVED

POST

OFFICE BOX42 * FORT WORTH,TEXAS71101

REISSUE -

14 AUGUST 1995

BHT-212-FMS-13

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P.

O. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-13

FAA APPROVED LOG OF REVISIONS

Original...........0

..............

17 JUN 74

Reissue...........

.............

14 AUG 95 LOG OF PAGES REVISION NO.

PAGE

A-B

FLIGHTMANUAL Title -

NP ..............................

REVISION NO.

PAGE

..................................

1 - 8 ...................................

0

0

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-13 LOG OF APPROVED Original...........0.............. Reissue...........0.............

17 JUN 74 14 AUG 95

APPROVED:

MANAGER

/

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

REVISIONS

FAA APPROVED

BHT-212-FMS-13

Section

1-3.

1

TYPES OF OPERATION

Takeoff(s) and landing(s) with

1-20.

INSTRUMENT

MARKINGS AND PLACARDS

environmental control unit (ECU) operating

TURN

are prohibited.

ECU

OFF DURING

1-6.

WEIGHT AND CENTER OF

TAKEOFF

AND AND LANDING

GRAVITY Actual weight change shall be determined

after environmental control unit kit is

installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

Section 2 Throttles- Full open.

INTERIOR AND

2-4.

PRESTART CHECK

SYSTEM SELECTOR switch

-

AIR

CONDITIONER. SYSTEM SELECTOR switch -

OFF.

AIR COND TEMP CONT switch -

observe cool airflow from outlets.

2-6.

SYSTEMS CHECK

COOL,

AIR COND TEMP CONT switch -

Full

counterclockwise, observe airflow NOTE

Operation check may be accomplished at this time or any time environmental control unit operation is desired.

temperature Increases. desired.

Position as

SYSTEMSELECTORswitch - OFF.

1

BHT-212-FMS-13

FAA APPROVED NOTE

AIR COND TEMP CONT switch

desired.

Condensation may be visible from outlets when humidity is high.

2-10.

As

DESCENT AND

LANDING

2-7. BEFORE TAKEOFF SYSTEM SELECTOR switch -

-

SYSTEM SELECTOR switch -

OFF.

OFF.

2-9. IN-FLIGHT OPERATIONS SYSTEM SELECTOR switch desired.

-

As

Section 3 3-3.

3-14-A. BLOWER FAN MALFUNCTION

ENGINE NOTE ECU will automatically shut off if either engine fails.

SYSTEM SELECTOR switch -

OFF.

Indication of a blower fan malfunction of a normal be absence would (approximately 60 amp) load on electrical system when SYSTEM SELECTOR switch is positioned to AIR CONDITIONER.

If it is determined that blower fan is 3-3-G. ENGINE COMPRESSOR STALL SYSTEM SELECTOR switch -

OFF.

inoperative, position switch to OFF.

SYSTEM SELECTOR

3-14-B. BLEED AIR VALVE MALFUNCTION

3-14. ENVIRONMENTAL CONTROL UNIT

MALFUNCTION There are two components

Indication of a bleed air valve malfunction would be as follows:

Hot airflow coming from outlets after

SYSTEM SELECTOR switch is that may fail in

positioned to OFF.

environmental control unit (ECU); blower fan and bleed air valve.

Smoke or fumes

coming

from

outlets

after SYSTEMSELECTORswitch is positioned to OFF.

If it is determined bleed air valve has malfunctioned, by failing to close when 2

BHT-212-FMS-13

FAA APPROVED SYSTEM SELECTOR switch is positioned to OFF, proceed as follows: NOTE

or Position SYSTEM SELECTOR switch to AIR CONDITIONER and adjust AIR COND TEMP CONT switch as desired.

If bleed air valve remains open without blower fan operating, heat exchanger will deteriorate due to extreme high temperatures.

SYSTEMSELECTORswitch -

WARNING

IT IS MANDATORY

THAT UNIT

Position to PRIOR T

AIR CONDITIONER, then OFF

LANDING.

or Reduce GAS PROD RPM, momentarily

if

practical, to allow bleed air valve to manually close.

Section 4 Performance data charts for environmental control unit are presented in figure 4-1.

3

BHT-212-FMS-13

FAA APPROVED

TWIN ENGINE RATE OF CLIMB MAXIMUMCONTINUOUSPOWER

VCAL = 55 KNOTS

ENGINE RPM 100%

GENERATOR150 AMPS(EA)

AIR CONDITION - ON

GROSS WEIGHT 7000 LB.

12000

10000

---

--

8000

0

400

800

1200 1600 2000 RATE OF CLIMB -- FT./MIN.

2400

2800

3200 212FS13-4-1-1

Figure 4-1.

4

Twin engine rate of climb (Sheet 1 of 5)

FAA APPROVED

BHT-212-FMS-13

TWIN ENGINE RATE OF CLIMB MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 150 AMPS (EA)

VCAL = 55 KNOTS AIR CONDITION -

ON

GROSS WEIGHT 8000 LB.

16000

14000

10000

8000 OAT LIMIT 6000

4000

2000

0

400

Figure 4-1.

800 1200 RATE OF CLIMB

1600 FT./MIN.

2000

2400 212FS13-4-1-2

Twin engine rate of climb (Sheet 2 of 5)

5

FAA APPROVED

BHT-212-FMS-13

TWIN ENGINE RATE OF CLIMB POWER MAXIMUMCONTINUOUS

VCAL = 55 KNOTS

ENGINE RPM 100% GENERATOR 150 AMPS (EA)

AIR CONDITION - ON

GROSS WEIGHT 9000 LB. 16000

14000

12000

10000

8000

2000

4000 OAT LIMIT

2000

0

Figure 4-1.

6

400

1600 1200 800 RATE OF CLIMB - FT./MIN.

2000

Twin engine rate of climb (Sheet 3 of 5)

2400 212FS13-4-1-3

FAA APPROVED

BHT-212-FMS-13

|TWIN

ENGINE RATE OF CLIMB

POWER MAXIMUM CONTINUOUS

0D

VCAL

=

55 KNOTS

ENGINE RPM 100%

GENERATOR150 AMPS(EAI

AIR CONDITION- ON

GROSS WEIGHT 10000 LB.

16000

14000

12000

0000

8000

q 6000

4000 OAT LIMIT

2000

RATE OF CLIMB

^^-)|~

Figure 4-1.

FT /MIN

.

212F13-4-1-4 212FS13-4-1-4

Twin engine rate of climb (Sheet 4 of 5)

7

BHT-212-FMS-13

FAA APPROVED

TWIN ENGINE MAXIMUM

CONTINUOUS POWER

RATE OF CLIMB VCAL = 55 KNOTS

ENGINE RPM 100%

GENERATOR150 AMPS(EAI

AIR CONDITION- ON

GROSS WEIGHT 11200 LB. 16000

2000

Figure 4-1.

8

Twin engine rate of climb (Sheet 5 of 5)

BHT-212-FMS-14

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

20/90 AUXILIARY FUEL TANKS 212-899-243 CERTIFIED MARCH 3, 1975

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when 20/90 auxiliary fuel tanks are installed.

Information contained herein supplements information of basic Flight Manual. For

Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

A Subsidiary of Textron Inc.

COPYRIGHT NOTICE TWORTH. INC. BELL HELICOPTER ANDBELLHELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD ALL RIGHTS RESERVED

OT OFFICEOX482 FORT

REISSUE -

TEXA87»101

14 AUGUST 1995

BHT-212-FMS-1 4 NOTICE PAGE

PROPRIETARY RIGHTS NOTICE

Manufacturer's Data portion of this supplement 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.

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

NP

FAA APPROVED

BHT-212-FMS-14 LOG OF REVISIONS

Original...........0............. Reissue...........0 .............

03 MAR 75 14 AUG 95 LOG OF PAGES

PAGE

~REVISION

NO.

FLIGHT MANUAL Title-

NP ..............................

NO. MANUFACTURER'S DATA

0

A-B A--B .................................. 0

1/2 ......................................

REVISION

PAGE

3-

8.................................

0

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-14 LOG OF APPROVED REVISIONS ............ Original............ Reissue...........0.............

03 MAR 75 14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

FAA APPROVED

Section

BHT-212-FMS-14

1

No change from basic manual.

Section 2 No change from basic manual.

Section 3 No change from basic manual.

Section 4 No change from basic manual.

1/2

MANUFACTURER'S DATA

BHT-212-FMS-14

Section 5 No change from basic manual.

0

0 3

BHT-212-FMS-14

Section

MANUFACTURER'S DATA

1

No change from basic manual.

Section 2 2-1.

FUEL LOADING TABLES

Fuel loading tables are shown in figure 21. SERVICING

2-2. FUEL

Total fuel capacity

Total fuel capacity

Helicopter 90 gallon auxiliary fuel kit

Total fuel

Helicopter 20/90 auxiliary fuel kit

217 gallons 110 gallons

Total fuel

327 gallons

4

217 gallons 90 gallons 307 gallons

MANUFACTURER'S DATA

O*

BHT-212-FMS-14

90 GALLON AUXILIARY FUEL TANK ON LEFT SIDE OF HELICOPTER CABIN AND 20 GALLON TANK ON RIGHT GAL

WEIGHT

10 20 30 40 50 60 70 *72.6 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 327

65 130 195 260 325 390 455 472 520 585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365 1430 1495 1560 1625 1690 1755 1820 1885 1950 2015 2080 2126

LONGITUDINAL ARM MOMENT 143.6 143.6 140.2 134.8 131.6 129.4 127.9 127.6 128.3 130.9 134.0 136.2 138.2 139.7 141.2 142.3 143.2 144.1 144.9 145.6 146.3 146.9 147.5 148.0 148.5 149.0 149.4 149.9 150.3 150.6 151.0 151.2 151.4 151.6

9334 18668 27348 35055 42771 50480 58186 60176 66706 76577 87100 97383 107796 118047 128492 138743 148928 159231 169533 179816 190190 200519 210925 221260 231660 232440 252486 263075 273546 283881 294450 304668 314912 322302

LATERAL ARM MOMENT 0 0 0 0 0 0 0 0 0 -0.1 -0.6 -1.0 -1.5 -2.0 -2.4 -2.8 -3.0 -3.3 -3.6 -3.9 -4.3 -4.8 -5.2 -5.6 -6.0 -6.4 -6.7 -7.0 -7.3 -7.6 -7.8 -8.1 -8.4 -8.5

0 0 0 0 0 0 0 0 0 -59 -390 -715 -1170 -1690 -2184 -2730 -3120 -3647 -4212 -4817 -5590 -6552 -7436 -8372 -9360 -9984 -11323 -12285 -13286 -14326 -15210 -16322 -17472 -18071

*Most critical fuel amount for most forward C.G. condition.

0)

Figure 2-1.

212FSMD14-2-1-1

Fuel loading table (Sheet 1 of 4)

5

MANUFACTURER'S DATA

BHT-212-FMS-14

90 GALLON AUXILIARY FUEL TANK ON RIGHT SIDE OF HELICOPTER CABIN AND 20 GALLON TANK ON LEFT LONGITUDINAL GAL

WEIGHT

ARM

MOMENT

10 20 30 40 50 60 70 *72.6 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 327

65 130 195 260 325 390 455 472 520 585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365 1430 1495 1560 1625 1690 1755 1820 1885 1950 2015 2080 2126

143.6 143.6 140.2 134.8 131.6 129.4 127.9 127.6 128.3 130.9 134.0 136.2 138.2 139.7 141.2 142.3 143.2 144.1 144.9 145.6 146.3 146.9 147.5 148.0 148.5 149.0 149.4 149.9 150.3 150.6 151.0 151.2 151.4 151.6

9334 18668 27348 35055 42771 50480 58186 60176 66706 76577 87100 97383 107796 118047 128492 138743 148928 159231 169533 179816 190190 200519 210925 221260 231660 232440 252486 263075 273546 283881 294450 304668 314912 322302

LATERAL ARM 0 0 0 0 0 0 0 0 0 +0.1 +0.6 +1.0 +1.5 +2.0 +2.4 +2.8 +3.0 +3.3 +3.6 +3.9 +4.3 +4.8 +5.2 +5.6 +6.0 +6.4 +6.7 +7.0 +7.3 +7.6 +7.8 +8.1 +8.4 +8.5

MOMENT 0 0 0 0 0 0 0 0 0 +59 +390 +715 +1170 +1690 +2184 +2730 +3120 +3647 +4212 +4817 +5590 +6552 +7436 +8372 +9360 +9984 +11323 +12285 +13286 +14326 +15210 +16322 +17472 +18071

*Most critical fuel amount for most forward C.G. condition.

Figure 2-1.

6

Fuel loading table (Sheet 2 of 4)

212FSMD14-2-1-2

0

BHT-212-FMS-14

MANUFACTURER'S DATA

ONE 90 GALLON AUXILIARY FUEL TANK ON LEFT SIDE OF HELICOPTER CABIN LONGITUDINAL GAL 10 20 30

WEIGHT

ARM

MOMENT

LATERAL ARM MOMENT

65 130 195

143.6 143.6 140.2

9334 18668 27348

0 0 0

0 0 0

40

260

134.8

35055

0

0

50

325

131.6

42771

0

0

60

390

129.4

50480

0

0

70 *72.6

455 472

127.9 127.6

58186 60176

0 0

0 0

80 90

520 585

128.3 130.3

66706 76226

0 - 0.7

-

100

650

133.0

86450

- 2.0

- 1300

110 120 130

715 780 845

136.0 138.4 140.0

97240 107952 118300

- 3.0 - 3.8 - 4.6

- 2145 - 2964 - 3887

140

910

141.4

128674

- 5.4

- 4914

150 160 170 180 190 200 210 220 2:30 240 250 260 270 280 290 300

975 1040 1105 1170 1235 1300 1365 1430 1495 1560 1625 1690 1755 1820 1885 1950

142.7 143.8 145.0 145.8 146.6 147.3 148.0 148.4 148.9 149.4 149.8 150.2 150.6 151.0 151.4 151.8

139133 149552 160225 170586 181051 191490 202020 212212 222606 233064 243425 253838 264303 274820 285389 296019

- 6.1 - 6.8 - 7.2 - 7.6 - 7.9 - 8.3 - 8.5 - 8.8 -19.1 - 9.3 - 9.5 - 9.7 - 9.9 -10.0 -10.2 -10.3

- 5948 - 7072 - 7956 - 8892 - 9757 -10790 -11603 -12584 -13605 -14508 -15438 -16393 -17375 -18200 -19227 -20085

307

1994

152.0

303088

-10.4

-20738

*Most critical fuel amount for most forward C.G. condition.

Figure 2-1.

0 410

212FSMD14213

Fuel loading table (Sheet 3 of 4)

7

BHT-212-FMS-14

MANUFACTURER'S DATA

ONE 90 GALLON AUXILIARY FUEL TANK ON RIGHT SIDE OF HELICOPTER CABIN LONGITUDINAL GAL

WEIGHT

ARM

MOMENT

LATERAL ARM MOMENT

10 20 30 40 50 60 70 *72.6 80

65 130 195 260 325 390 455 472 520

90 100 110 120 130 140 150 160 170 180 190 200 210-

585 650 715 780 845 910 975 1040 1105 1170 1235 1300 1365

130.3 13:3.0 136.0 138.4 140.0 141.4 142.7 143.8 145.0 145.8 146.6 147.3 148.0

76226 86450 97240 107952 118300 128674 139133 149552 160225 170586 181051 191490 202020

+ + + + + + + + + + + + +

220

1430

148.4

212212

+ 8.8

+12584

230 240 250 260 270

1495 1560 1625 1690 1755

148.9 149.4 149.8 150.2 150.6

222606 233064 243425 253838 264303

+ + + + +

+13605 +14508 +154:38 +16393 +17375

280 290

1820 1885

151.0 151.4

274820 285389

+10.0 +10.2

300

1950

151.8

296019

+10.3

+20085

307

1994

152.0

30:3088

+10.4

+20738

143.6 143.6 140.2 134.8 131.6 129.4 127.9 127.6 128.3

9334 18668 27348 35055 42771 50480 58186 60176 66706

0 0 0 0 0 0 0 0 0

0.7 2.0 3.0 3.8 4.6 5.4 6.1 6.8 7.2 7.6 7.9 8.3 8.5 9.1 9.3 9.5 9.7 9.9

0 0 0 0 0 0 0 0 0

+ 410 + 1300 + 2145 + 2964 + :3887 + 4914 + 5948 + 7072 + 7956 + 8892 + 9757 +10790 +11603

+1820() +19227

*Mostcritical fuel amount for most forward (.G. condition. 212FSMD14-2-1-4

Figure 2-1.

8

Fuel loading table (Sheet 4 of 4)

BHT-212-FMS-15

MODEL

*

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

KNC 610 AREA NAV SYSTEM 212-899-131 CERTIFIED APRIL 4, 1975

This supplement shall be attached to the Bell Helicopter Model 212 Flight Manual when the KNC 610 Area Nav system is installed.

Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

0

_____Bell

COPYRIGHT NOTICE 1995 COPYRIGHT BELL HELICOPTER INC. ANDBELLHELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD ALLRIGHTS RESERVED

h~Il! Helicopter Inc A Subsidiary ofTextron

76101 TEXAS POeT OFFICEOX 2 FORTWORTH.

REISSUE -

14 AUGUST 1995

FAA APPROVED

BHT-212-FMS-15 NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. O. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-15

FAA APPROVED LOG OF REVISIONS

Original ........... Reissue...........0

0 ............

04 APR 75

.............

14 AUG 95 LOG OF PAGES

PAGE

REVISION NO.

Title - NP ..............................

0

1/2 ......................................

0

A- B ..................................

PAGE

REVISION NO.

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-15

FAA APPROVED LOG OF APPROVED

Original ......... 0.............. Reissue...........0.............

REVISIONS

04 APR 75 14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

0

FAA APPROVED

BHT-212-FMS-15

Section

1-20.

1

INSTRUMENT

MARKINGS AND PLACARDS THE KNC 610 AREA NAV SYSTEM IS NOT ELIGIBLE FOR USE IN IFR CONDITIONS.

Section 2 2-4. INTERIOR AND CHECK PRESTART PRESTART CHECK

NAV DISTANCE - Displayed nautical mile indication.

OBS (CDI) 2-4-A.

KNC 610 AREA NAV

degrees

SYSTEM AREA NAV circuit breakers NAV SELECTOR -

local VORstation. local V

station RNAV

MODE T sS h - R . Waypoint distance - Set to approximately TEST button -

bearing.

Release.

2-9. IN-FLIGHT OPERATIONS

In.

Select and identify a

MODE SELECT switch -

Centered within a few

of waypoint

TEST button -

and 25

Use of KNC 610 area nav system

for

Use of KNC 610 area Isnav system forIf selection of waypolnts conventional. additional information

is required,

refer to

current manufacturer's operating instructions

25 nautical miles. CAUTION

Press and hold.

NAV DISTANCE display flag Retracted. Retracted.

RNAV DISTANCE Retracted

display

flag

-

PILOT MUST CAREFULLY PILOT MUST CAREFULLY MONITOR

KNC 610 MODE

APPROPRIATE RAW DATA OR APPREANAV INFORMATION IS

AREA NAV INFORMATION IS BEING PRESENTED ON DISPLAY. 1/2

BHT-212-FMS-1 6

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

HEATED WINDSHIELD 212-706-053 SN 30554 AND SUB CERTIFIED NOVEMBER 1, 1974

This supplement shall be attached to the Bell

Helicopter Model 212 Flight Manual when heated windshield is installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

A Subsidiary ol Textron Inc

COPYRIGHT NOTICE BELL® HELICOPTER INC. BELL HELICOPTER INC.POST AND BELL HELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD. ALLRIGHTS RESERVED

OFFICE BOX42 . FORTWoRTH,TEXS8 61101

REISSUE -

14 AUGUST 1995

BHT-212-FMS-16

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

.

BHT-212-FMS-16 LOG OF REVISIONS

Original...........0

..............

01 NOV 75

Revision .......... Reissue...........0

1 .............. .............

01 OCT 84 14 AUG 95

LOG OF PAGES REVISION NO.

PAGE FLIGHT MANUAL

Title - NP.............................. i/ii ......................................

PAGE A-

0 00

B ..................................

REVISION NO. 0

1-2 .................................. 0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-16 LOG OF APPROVED REVISIONS

Original ........... 0 .............. .............. Revision..........1

01 NOV 75 01 OCT 84

Reissue...........0.............

14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

FAA APPROVED

BHT-212-FMS-16 GENERAL INFORMATION

Heated windshield

allows crew to

electrically defrost/defog windshield. Installation consists of electrically heated

windshield

panels, a switch,

and

necessary wiring to complete installation.

i/ii

BHT-212-FMS-16

FAA APPROVED

1

Section

WEIGHT AND CENTER OF

1-6.

1-20.

INSTRUMENT

GRAVITY

MARKINGS AND PLACARDS

Actual weight change shall be determined after heated windshield kit is installed and

LH

ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

WINDSHIELD HEAT RH CAUTION STANDBY COMPASS UNRELIABLE WITH WINDSHIELD HEAT ON.

Section 2 2-4. INTERIOR AND PRESTART

WSHLD HEAT LH switch WSHLDHEAT

DIM switch.

operations,

During

daylight

OFF.

switch WSHLD HEAT

WINDSHIELD HEAT circuit breakers -

TAKEOFF

WSHLD HEAT LH switch - ON (if desired), LH ON (green segment)

In.

illuminates.

BATTERYswitches - ON.

WSHLD HEAT RH switch

Windshield heat segments test.

heat

windshield

segments should be in bright.

CHECK

ON (green segments)

-

ON (if

desired), RH ON (green segment) Press to

illuminates.

and FAIL

NOTE

(yellow segments) illuminate. NOTE Bright and dim intensity of heated windshield segments is controlled

LH

ON

and

RH

ON

(green

segments) will illuminate and extinguish as windshield heat cycle occurs.

by MASTER CAUTION panel BRT 1

BHT-212-FMS-16

FAA APPROVED

Section 3 3-7.

ELECTRICAL SYSTEM

NOTE Current for heated windshield is

3-7-A. DC POWERFAILURE NON ESS BUS switch -

provided by non essential bus.

MANUAL Table 3-1.

CAUTION LIGHTS

PANEL WORDING

FAULT CONDITION

CORRECTIVE ACTION

WINDSHIELD FAIL LH

HEAT

Left windshield heating element inoperative.

WSHLD HEAT LH switch -

OFF.

WINDSHIELD FAIL RH

HEAT

Right windshield heating element inoperative.

WSHLD HEAT RH switch -

OFF.

3-13. LH WINDSHIELD HEAT CIRCUIT BREAKERS TRIP

3-14. RH WINDSHIELD HEAT CIRCUIT BREAKERS TRIP

WSHLD HEAT LH switch -

WSHLD HEAT switch -

2

OFF.

OFF.

BHT-212-FMS-1 7

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

INTERNAL RESCUE HOIST (WESTERN GEAR) 214-706-003 CERTIFIED NOVEMBER 20, 1975

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when internal rescue hoist is installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

9D__________ NOTICE COPYRIGHT COPYRIGHT 1995 BELL HELICOPTER INC. ANDBELLHELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD. ALLRIGHTS RESERVED

Bell

HelicopterL

POSTOFFICE BOX41

REISSUE

I

Inc A Subsidilryof Textron FORTWORTH. TEXAS 76101

-

14 AUGUST

1995

FAA APPROVED

BHT-212-FMS-17 NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P.

O. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-17

FAA APPROVED LOG OF REVISIONS

Original...........0

..............

20 NOV 75

Revision ..........

3 ..............

01 OCT 84

Revision..........1

..............

15 FEB 76

Reissue...........0

.............

14 AUG 95

Revision..........2

..............

11 JUN 82 LOG OF PAGES REVISION

REVISION NO.

PAGE FLIGHT MANUAL

Title- NP..............................

NO.

PAGE A-

B .................................

l/11........ .

.

............. ................

-10 ..................................

0

0

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

A

BHT-212-FMS-17

FAA APPROVED LOG OF APPROVED

Original........... Revision..........1

0 .............. ..............

Revision ..........

2 ..............

20 NOV 75 15 FEB 76

11 JUN 82

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

REVISIONS

Revision .......... Reissue...........0

3 .............. .............

01 OCT 84 14 AUG 95

FAA APPROVED

BHT-212-FMS-17

Internal rescue hoist, when Installed, will permit operator to raise or lower loads up to 600 pounds (272 kilograms), allowing hoisting operations in confined areas. The

side of hoist illuminate when hook reaches 20 feet (6 meters) below skids during retraction. An electrically actuated cable cutting device allows crew to sever cable

3/16inch hoist cable is 256 feet (78 meters)

in an emergency.

in length. Each of four cabin mounting

cable cutter, accessible to operator, may

locations allow hoist to be extended 90 degrees outboard. Caution lights on each

be used to sever cable if electrical cutter fails.

A manually

operated cable

i/ii

FAA APPROVED

BHT-212-FMS-17

Section

1

1-3. TYPES OF OPERATION Hoist operations shall be conducted under appropriate operating rules for external loads. Passenger operations with hoist installed are approved, providing hoist is stowed and hoist electrical system is deactivated. Hoist operations are prohibited during instrument meteorological conditions.

1-4. FLIG|HTCREW A crewmember,

wearing an approved

safety harness in passenger compartment,

is required during all phases of hoist operations. Crewmember shall wear protective gloves for guiding cable during operation. Hoist operator shall be familiar with hoist operating procedures and limitations.

flight

Refer to appropriate

manual

supplement(s) (FMS) for additional limitations, procedures, data

1-6.

and performance

WEIGHT AND CENTER OF

AIT

GRAVITY 1-6-A WEIGHT Actual weight change shall be determined after internal rescue hoist is installed and ballast readjusted,

if necessary, to return

empty weight CG to within allowable limits. Maximum GW including

hoist load is

11200 pounds (5080 kilograms).

1-6-B. CENTEROF GRAVITY Maximum hoist load is 600 pounds (272.2 kilograms). This is a structural limitation only and does not ensure that longitudinal

1-5. CONFIGURATION 1-5-B. OPTIONAL EQUIPMENT

limits. Maximum allowable hoist load varies with GW, CG, and hoist location.

Refer to appropriate hoist loading schedule (figure 1-1).

Fixed passenger step shall not be installed

concurrently with internal rescue hoist. Retractable passenger steps shall be

stowed during hoist operations.

Amphibious flotation gear (fixed floats) shall not be installed concurrently with internal rescue hoist.

NOTE Butt line of load with hoist in with hoist in forward position is 60 inches (1524 millimeters) from centerline. Butt line of load with hoist in aft

position is 64.4 inches (1636 millimeters) from centerline.

Hoisting or lowering an empty litter in open position (except Stokes litter) is prohibited. 1

BHT-212-FMS-17

FAA APPROVED

1-7. AIRSPEED

position

in which hoist is installed.

Enter

schedule at helicopter GW, proceed vertically to intersect appropriate diagonal

panels locked open and cargo doors open is 20 KIAS. VNE with hinged

VNE

line representing

number of crewmembers

horizontally to left then proceed load. onboard, to to read read allowable allowable hoist hoist load.

with hinged panels removed and cargo

doors removed or secured open is 60 KIAS.

NOTE Hoist loading schedules are based

on most adverse loading 1-22. HOIST DUTY CYCLE

combinations of pilot, copilot, and hoist operator, each weighing 170

to 200 pounds

kilograms).

Hoist is approved for continuous operation with loads not to exceed 600 pounds

(272.2kilograms). 1-23.

ALLOWABLE

LOAD Prior to hoisting, select hoist loading schedule (figure 1-1) appropriate for

2

weights are not within this range, these schedules are invalid and

pilot shall compute allowable hoist load.

HOIST

(77.1 to 90.7

If crewmember

FAA APPROVED

BHT-212-FMS-17

HOIST IN AFT RIGHT POSITION BOOM FULLY EXTENDED

HOIST LOADING

AREA

500

PROHIBITED

400

Figure 1-1. Hoist loading schedules (Sheet 1 of 4)

300

212-FS17-1-1-1

200

6800

7200

7600

8000

8400

8800

9200

9600

10.000 10,400

10,800

11.200

GROSSWEIGHT PRIOR TO HOISTING - POUNDS

212-FS17-1-1-1

Figure 1-1.

Hoist loading schedules (Sheet 1 of 4)

3

FAA APPROVED

BHT-212-FMS-17

HOIST IN FORWARDRIGHT POSITION BOOM FULLY EXTENDED

600

PILOT AND COPILOT: ALLOWABLE HOIST LOAD 600 LB IUP TO 10,600 LB G.W.I

800

7200

7600

80

84

8800

92

6800

7200

7600

8000

8400

8800

9200

10000

9600

10

10800

200

10.000 10.400 10.800

11,200

GROSSWEIGHT PRIOR TO HOISTING - POUNDS

Figure 1-1.

4

Hoist loading schedules (Sheet 2 of 4)

212-FS17-1-1-2

BHT-212-FMS-17

FAA APPROVED

HOISTIN FORWARDLEFT POSITION BOOM FULLY EXTENDED 600

.

THIS

LOADING IN AREA PROHIBITED

400

300

4

100

6800

7200

7600

8000

8400

8800

9200

9600

10,000 10.400

GROSSWEIGHT PRIOR TO HOISTING- POUNDS

10,800

11,200

212-FS17-1-1-3

Figure 1-1. Hoist loading schedules (Sheet 3 of 4)

5

FAA APPROVED

BHT-212-FMS-17

HOIST IN AFT LEFT POSITION BOOM FULLY EXTENDED

.

PROHIBITED

500

300

212-FS17-1-1-4

Figure 1-1. Hoist loading schedules (Sheet 4 of 4)

6

FAA APPROVED

BHT-212-FMS-17

Section 2 2-2.

FLIGHT PLANNING WARNING

HOIST

LOAD

CAN CAUSE

LONGITUDINAL OR LATERALCG TO EXCEED LIMITS. GW AND CG

SHALL BE COMPUTED TO ASSURE LOADING IS WITHIN APPROVED LIMITS.

NOTE

AIRCRAFT Hook -

Compute with and without

2-4.

INTERIOR AND PRESTART CHECK 2-4-A. HOIST INSTALLATION CHECK

Rotates freely on cable.

Gearbox oil levels -

If pilot plans to operate hoist, hoist shall be installed in forward right position.

Check sight

glasses

Hoist operator pendant connectors secured.

Electrical power cables connectors secured.

Installed, Condition,

CAUTION ACTUATION OF CABLE CUT SWITCH, ON PEDESTAL, CAN CUT CABLE REGARDLESS OF HOIST PWR SWITCH POSITION. ACTUATION OF CABLE CUT

SWITCH, ON HOIST CONTROL BOX, CAN CUT CABLE EVEN IF CABLE CUT CIRCUIT BREAKER IS OUT.

CABLE

CUT switches

hoist control box) NOTE

(on hoist

Set in proper position.

Cable - Check proper routing through guide rollers, pulleys, and drums.

If additional loads are carried during hoisting operations, loads should be placed on side of helicopter opposite hoist position. GW and CG hoist load.

POSITION switch

control box) -

(pedestal

and

Off, covers

safetied.

Safety vests, tether straps, hoisting slings, and litters - Condition, secured or stowed.

Hoist - Installed in desired position, check roof and floor stud adapters and locking collars properly secured.

2-6.

Boom actuator - Installed in proper position, all fittings secured.

2-6-L. HOIST OPERATION CHECK

SYSTEMS CHECK

Cargo doors and hinged panels Secured open or removed. 7

BHT-212-FMS-17

FAA APPROVED

HOIST PWR, HOIST CONT, and HOIST CABLE CUT circuit breakers - In.

BATTERY switch power connected).

ON (or external

NON ESS BUS switch ICS -

NOTE

Ground crewmember should be instructed to discharge helicopter static electricity before attaching load to hoist, when possible.

MANUAL.

Check intercom between pilot and

hoist operator using hoist pendant ICS switch and HOT MIC switch (right ICS

2-7. BEFORE TAKEOFF Cargo doors and hinged panels Secured open or removed.

box only). HOIST PWR switch -

ON, check green

(power on) light on hoist control box Illuminates, check amber 20 FOOT CAUTION lights on hoist control box and instrument panel illuminate.

Hoist OVERTEMPwarning lights Press to test.

CABLE

CUT switches

hoist control safetied.

(pedestal

box) -

HOIST PWR, HOIST CONT, and HOIST CABLE CUT circuit breakers - In.

Safety vests and straps secured to helicopter. NOTE

and

Off, covers

Gloves -

On and

On.

Maintain tension on hoist cable while reeling in and out to prevent

STEP switch (if installed) -

STOW.

slack. HOIST and BOOM switches

operator) functions

(pilot

and

Actuate to check all hoist

for proper operation.

Check

pilot HOIST switch overrides operator

2-9.

IN-FLIGHT OPERATIONS

HOIST PWR switch -

ON.

pendant HOIST switch.

Hoist cable -

Check for corrosion,

kinks, flat spots, fraying, or broken strands. strands

HOIST OPERATOR SHALL BE A A SERED E TO OTER T HARNESS DURING HOIST

Up limit switch actuator - Raise while hoist is reeling in and check hoist motor

SECURED TO HELICOPTER WITH

stops, release and check hoist resumes

OPERATIONS. OPERATIONS.

operation. operation. Reduce hoist speed as cable approaches up limit. Check hoist stops when hook

NOTE

reaches up limit without excess tension on cable.

Height-velocity diagram is not a limitation for internal rescue hoist operations under an appropriate operating certificate.

Hoist - Stowed for flight, hook restraint secured.

HOVER HOIST PWR switch -

BATTERYswitch 8

OFF.

OFF.

Established over hoist

operation area.

Hoist hook restraint - Removed.

BHT-212-FMS-17

FAA APPROVED BOOM switch (or pilot HOIST switch) OUT.

HOIST switch

-

DOWN.

Static electricity - Discharge when possible and connect hook to load, ' observing allowable hoist load.

2-9-C

LITTER HOISTING

of a When emergency transportation patient by litter Is essential, every effort should be made to land helicopter for litter loading. Litter hoisting can be hazardous and should be accomplished only when a landing is not feasible and condition of

patient precludes use of personnel hoisting sling.

NOTE As hook nears up or down limits, hoist speed automatically slows.

HOIST switch-UP.

In addition to all other procedures contained herein, following shall apply to litter hoisting operations. EMPTY LITTER

CAUTION

WARNING USE CARE TO PREVENT CABLE,

HOOK, AND LOAD FROM FOULING

ON

FUSELAGE

LANDINGGEAR. Ground speed -

OR

Maintain at zero until

load is clear of obstructions.

allowing

OR LOWERING

EMPTY LITTER

AN

IN OPEN

POSITION IS PROHIBITED.

AN

EMPTY LITTER SUSPENDED

FROM HOIST IN OPEN POSITION

BOOM switch - IN to swing hoist boom and load Into cabin, if possible.

Takeoff -

HOISTING

Into wind, if possible,

CAN OSCILLATE

UNCON-

TROLLABLY IN ROTOR WASH AND CAN FLY UPWARD, STRIKING

ROTOR.

FUSELAGE

OR TAIL

adequate hoist load clearance

over obstacles if load is not internal. CAUTION

Prior to hoisting or lowering an empty litter, litter shall be closed and secured with straps. Litter should be suspended in a near vertical position and sling straps should be drawn tight.

AIRSPEED

LOAD

IS

WITH EXTERNAL

LIMITED

BY

2-9-C-2. LOADED LITTER

CONTROLLABILITY. CAUTION SHOULD BE EXERCISED WHEN CARRYING AN EXTERNAL LOAD,

AS HANDLING

TERISTICS MAY BE AFFECTED BY SIZE, WEIGHT, AND SHAPE OF LOAD.

Airspeed - As required for adequate controllability, not to exceed limits for hoist operations.

WARNING

CHARAC-

LITTER PATIENT SHALL BE TO LITTER WITH SECURED

SAFETYSTRAPS. HOIST HOOK CATCH SHALL BE

SECURED WITH SAFETY PIN PRIOR TO HOISTING LITTER PATIENT. 9

BHT-212-FMS-17 SAFETY STRAPS.

FAA APPROVED HOISTING. HOIST OPERATOR MAY HAVE TO GRASP LITTER

SLING STRAPS TO CONTROL HOIST HOOK CATCH SHALL BE SECURED WITH SAFETY PIN

ROTATION AS LITTER APPROACHES LANDING GEAR.

PRIOR TO HOISTING LITTER PATIENT.

NOTE

Adjust litter sling straps so litter is 24 to

If litter Is suspended too far below hook, litter can not be loaded into

48 inches (61 to 71 centimeters) below hoist hook.

helicopter with hoist hook at up limit.

CAUTION

A LOADED LITTER CAN ROTATE

ABOUT CABLE DURING

Section 3 3-14. HOIST LOAD JETTISON

present operation until hoist is reeled in. Leave HOIST PWR switch ON (for cooling

To jettison hoist load in an emergency - Actuate CABLE CUT switch (located

fan operation) and allow hoist to cool. When OVERTEMP light extinguishes,

on pedestal or hoist control box)

hoisting may be resumed as desired.

In event of failure of CABLE CUT switch - Sever cable with manual cable cutter

(if installed).

3-15. HOIST OVERTEMP WARNING LIGHT In event OVERTEMP warning light (located

on hoist control box) Illuminates, continue

10

BHT-212-FMS-18

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT AUTOMATIC FLIGHT CONTROL SYSTEM/ AUTOPILOT 212-961-620 SN 30597 THROUGH 30849 CERTIFIED DECEMBER 15, 1976

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when Automatic Flight Control System/Autopilot is installed.

Information contained herein supplements information of basic Flight Manual. For

Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter Inc A Subsidiry of Textron

NOTICE COPYRIGHT COPYRIGHT ®

1995

BELL HELICOPTER INC. INC. TEXTRON ANDBELLHELICOPTER A DIVISION OF TEXTRON CANADA LTD. RESERVED ALLRIGHTS

POST OFFICE BOX 42 . FORT WORTH.TEXAS 76101

REISSUE -

14 AUGUST 1995

BHT-212-FMS-18

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P.

O. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-18

FAA APPROVED LOG OF REVISIONS

Original..........0

..............

15 DEC76

Revision .......... 1 ..............

06 DEC 77

Reissue...........0

14 AUG 95

.............

LOG OF PAGES REVISION NO.

PAGE

A-B

FLIGHTMANUAL Title - NP ..............................

0

REVISION NO.

PAGE

..................................

1-6 ................................... 0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-18

FAA APPROVED LOG OF APPROVED

Original...........0 Revision.......

.............. ..............

Reissue...........0.............

REVISIONS

15 DEC 76 06 DEC 77 14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

0

BHT-212-FMS-18

FAA APPROVED

Section

1

.

1-3. TYPESOF OPERATION

autopilot

Day and night VFR operations only are

weight CG to within allowable limits.

kit is installed

readjusted, if necessary,

and ballast

to return empty

approved.

AFCS/Autopilot kit is approved for skid gear and popout floats only.

1-7.

AIRSPEED

Due to control authorities

required for

flight at airspeeds below 40 knots,

Flight with fixed floats is prohibited.

automatic flight control system (AFCS) shall not be utilized at less than 40 knots

WEIGHT AND CENTER OF

1-6.

except

for ground

checks.

GRAVITY Actual weight change shall be determined

after automatic flight control system/

Section 2 2-6. SYSTEMS CHECK

Following

SYSTEM

CHECK

procedures ensure proper operation of AFCS.

2-6-G. 2-6-G.

AFCS CHECK AFCS CHECK

AFCS POWER switch

NOTE NOTE

AFCS mode of operation annunciated

on instrument

is

-

POWER.

CAUTION

panel

by a three segment light - PITCH,

DURING AFCS CHECKOUT,

ROLL, and YAW. AFCS functions in two modes: automatic with turn

MONITOR ALL CONTROLS E N S U R E CONTROL

and trim functions, and steering using pilot cyclic control. AFCS annunciation

is applicable

on instrument

panel

to both modes.

DEFLECTIONS EXCESSIVE.

ARE

TO

NOT

FAA APPROVED

BHT-212-FMS-18 Channel ARM switches -

ATTD.

ATTD switch

SCAS NO GO lights - Illuminated, within several should extinguish seconds to indicate system null.

-

ENGA,

AFCS lights

illuminate, SCAS lights extinguish. Pilot AFCS RELEASE switch - Press, extinguish, SCAS AFCS lights disengages.

Cyclic - Move forward/aft and hold, check PITCH NO GO light Illuminates then extinguishes after several seconds.

SCAS switch illuminate.

Cyclic - Move laterally and hold, check ROLL NO GO light illuminates then extinguishes after several seconds.

ATTD switch - ENGA, AFCS lights illuminate, SCAS lights extinguish.

Pedals - Move and hold, check YAW NO GO light illuminates and then extinguishes after several seconds. SCAS switch illuminate.

SCAS, SCAS lights

SCAS switch - Off (down), SCAS lights extinguish. SCAS switch

-

SCAS, SCAS lights

illuminate.

SCAS, SCAS lights

Copilot AFCS RELEASE switch (if installed) - Press, AFCS lights extinguish, SCASdisengages.

SCAS, SCAS lights

SCAS switch illuminate.

ATTD switch - ENGA, AFCS lights illuminate, SCAS lights extinguish. NOTE

For proper AFCS flight operation,

INV 1 switch -

OFF, SCAS disengages.

INV 1 switch - ON, check no. 1 AC voltmeter for 104 to 122 volts. SCAS switch illuminate.

SCAS, SCAS lights

Pilot AFCS RELEASE switch -

Press,

SCAS disengages.

a slight amount of cyclic friction

is required. Adjust cyclic friction as desired to prevent cyclic feedback. Cyclic friction - Adjust. AFCS automatic follows:

Check as

SCAS, SCAS lights

Pitch - Actuate PITCH trim wheel through cycle. Cyclic should follow and AFCS PITCH light remain illuminated. Center cyclic as desired

Copilot AFCS RELEASE switch (if

with cyclic FORCE TRIM switch.

SCAS switch - SCAS, SCAS lights

and AFCS pitch

SCAS switch illuminate. installed) -

Press, SCAS disengages.

Illuminate.

FORCE TRIM switch -

ON.

ATTD switch - ENGA, AFCS lights illuminate, SCAS lights extinguish. ATTD switch - DSENGA, AFCS lights extinguish, SCAS lights illuminate.

Actuate AFCS TRIM switch (cyclic) forward and aft. Cyclic should follow

light

remain

illuminated. Center cyclic as desired with cyclic FORCETRIM switch. Roll - Actuate ROLL trim wheel through cycle. Cyclic should follow and AFCS ROLL light remain illuminated. Center cyclic as desired with cyclic FORCE TRIM switch. Actuate AFCS TRIM switch (cyclic) laterally. Cyclic should follow and AFCS ROLL light

2

mode -

remain illuminated.

FAA APPROVED

BHT-212-FMS-18

Center cyclic as desired with cyclic FORCE TRIM switch.

Turn - Actuate TURN knob through cycle. Cyclic should follow and AFCS PITCH and ROLL lights remain

illuminated.

AFCS YAW light

extinguishes. Center cyclic as desired with cyclic FORCE TRIM switch.

AFCS pilot cyclic steering mode -

2-9.

IN-FLIGHT OPERATIONS

Maneuvering with AFCS on may be accomplished by either: Press TURN knob and select desired

angle of bank.

Apply pedals as

necessary to maintain coordinated flight. Use PITCH trim as necessary to maintain

desired attitude.

Check as follows: NOTE

Pitch -

Displace

forward

and release.

cyclic

slightly

AFCS PITCH

light extinguishes, SCAS PITCH light illuminates. Displace cyclic slightly AFCS PITCH light

aft and release.

extinguishes, illuminates.

SCAS PITCH light

Roll - Displace cyclic slightly left and release. AFCS ROLL light extinguishes, SCAS ROLL light illuminates. Displace cyclic slightly right and release.

extinguishes,

AFCS ROLL light

SCAS ROLL light

illuminates. Yaw - Displace pedals slightly left and release. AFCS YAW light

extinguishes, illuminates. right

SCAS YAW light

Displace pedals slightly

and release.

extinguishes, illuminates.

AFCS YAW light

SCAS YAW light

If ROLL trim wheel is used during turn, helicopter may not return to

level flight (in roll) when turn is terminated OR

Move cyclic to desired bank angle and

pitch attitude. Apply pedals as necessary to maintain coordinated flight during turning maneuver. OR

Press cyclic FORCE TRIM switch and maneuver as desired. Release switch when maneuver is completed and with helicopter in level attitude.

2-10.

DESCENT AND

LANDING

ATTD switch 40 knots.

2-11. CYCLIC CONTROL MAY MOTOR TO STOP IF AFCS IS LEFT ENGAGED WHILE HELICOPTER IS ON GROUND.

DSENGA as desired above

ENGINE SHUTDOWN

AFCS POWER switch -

Off (down).

WARNING

ATTD switch - DSENGA (prior to takeoff). IF AFCS IS LEFT ENGAGED ON

2-8.

TAKEOFF

ATTD switch -

GROUND, FLIGHT CONTROLS MAY MOTOR TO STOPS.

ENGA as desired above 40

knots. 3

FAA APPROVED

BHT-212-FMS-18

Section 3 INSTALLED, INOPERATIVE.

3-6. HYDRAULIC SYSTEM 3-6-A.

HYDRAULIC FAILURE -

SYSTEM

3-7-D. AC FAILURE - SYSTEM NO. 2

1

Yaw channel switch OFF.

BE

WILL

Disengage by turning YAW NOTE

3-6-B. HYDRAULIC FAILURE -

Normally, number 3 inverter will supply power to either bus if a

SYSTEM2

failure of No. 1 or No. 2 inverter

should occur.

Pitch and roll channels -

Disengage by

turning PITCH and ROLL switches OFF.

3-7.

SYSTEM

ELECTRICAL

CAUTION

NO. 2 ENGINE INSTRUMENTS

3-7-C.

AC FAILURE - SYSTEM NO.

NOTE

Normally, number 3 inverter will supply power to either bus if a failure of No. 1 or No. 2 inverter

should occur.

If no power is

available on No. 1 bus, proceed as

follows: PITCH, ROLL, and YAW channel

ARM

switches - OFF.

POWERED

PRESSURE

AND PILOT AC

INSTRUMENTS

WILL

BE INOPERATIVE.

3-9. AUTOMATIC FLIGHT CONTROLS SYSTEM

CONTROLS

3-9-A. AFCSWILL NOTENGAGE ANY CHANNEL FORCE TRIM switch (pedestal) ON.

Channel ARM switches -

Check

Check in

ATTD position. CAUTION

NO. 1 ENGINE

PRESSURE

INSTRUMENTS AND COPILOT AC IF POWERED INSTRUMENTS, 4

SCAS switch -

SCAS.

Attitude gyros - Wait until fully erected. AFCS circuit breakers -

Check In.

FAA APPROVED

BHT-212-FMS-18

3-9-B. AFCS WILL NOT ENGAGE YAW CHANNEL ONLY TURN trim knob not pressed.

Check centered and

Pedals - Force trim centered. „Yawchannel Yaw channel ARM ARM switch switch -- Check Check in.D in AFCS HDG circuit breakers -

Check in.

Copilot directional gyro (if installed) Check operative.

being reset, do not attempt further resetting. SCAS POWER switch - POWER. SCAS POWER switch POWER. Individual channel NO GO lights -

Move

appropriate flight control and observe each light illuminates. Do not attempt to engage a channel that did not illuminate when control was moved.

Individual channel NO GO lights Extinguished

(do not attempt to engage

ifilluminated). channel light is Individual channel ARM switches (operative channels) - SCAS or ATTD, as desired.

NOTE Yaw AFCS channel will drop out if

SCAS switch -

pilot uses manual slaving switch on copilot directional gyro.

control input, disengage SCAS. ATTD switch -

3-9-G.

Insufficient cyclic friction applied. Adjust

SCAS

ENGA (if desired).

If any

INOPERATIVE CHANNEL -

Affected channel -

3-9-D. OSCILLATIONS IN AFCS ANY CHANNEL

If any unusual

unusual control input, disengage AFCS.

3-9-C. FEEDBACK FELT IN CYCLIC DURING SCAS ONLY FLIGHT per BHT-212-MM-1.

SCAS.

positioning appropriate switch to OFF.

Disengage by

channel ARM

Affected channel - Disengage and refer to

3-9-H.

BHT-212-MM-1.

AFCS

3-9-E.

Affected channel - Disengage by turning appropriate channel ARM switch to SCAS or OFF.

SYSTEM

HYDRAULIC FAILURE NO 1.

Disengage yaw channel by turning yaw select switch OFF.

3-9-F. SYSTEM REENGAGE AFTER DISENGAGE. No. 1 AC voltmeter -

Check for proper

voltage. If voltage not available, all channels will be inoperative.

Circuit breakers - In. If a circuit

3-9-J.

INOPERATIVE INOPERATIVE CHANNEL CHANNEL --

INOPERATIVE

GYRO - COPILOT GYRO - COPILOT

ATTITUDE

ATTD PITCH and ROLL channels Disengage.

-

NOTE NOTE SCAS will work normally on all channels unless gyro failure was caused by AC system failure.

breaker has tripped and trips again after 5

FAA APPROVED

BHT-212-FMS-18

3-9-K.

INOPERATIVE HEADING

GYRO GYRO-- COPILOT COPILOT ATTD YAW channel -

AFCS RELEASE switch drop out.

Disengage.

SCAS channel switches -

NOTE SCAS will work

Press, check

AFCS control panel for SCAS switch OFF.

NOTE

normally

on all

channels unless gyro failure was caused by AC system failure.

3-9-L. HYDRAULIC FAILURE SYSTEM NO 2 Disengage pitch and roll channels by turning pitch and roll select switches OFF.

After resuming

flight,

straight and level

channels of SCAS and

AFCS can be re-engaged.

3-9-N. EMERGENCY EVASIVE MANEUVER Flight controls - Use as needed to maneuverhelicopter. FORCE TRIM switch (cyclic) -

Press

and hold until back to desired attitude to

3-9-M. AFCS RUNAWAY,

resume

HARDOVER, OR UNUSUAL CHARACTERISTIC

AFCS control panel desired attitude.

Helicopter attitude and pedals.

6

Correct with cyclic

AFCS control.

Use to re-attain

BHT-212-FMS-19

ROTORCRAFT FLIGHT MANUAL

*

SUPPLEMENT AUTOMATIC FLIGHT CONTROL SYSTEM/ AUTOPILOT 212-706-111 SN 30850 AND SUB CERTIFIED JUNE 14, 1977

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when Automatic Flight Control System/Autopilot installed.

is

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopteri Inc. A Subsidiary ot Textron

COPYRIGHT NOTICE

A DIVISIONOF TEXTRONCANADA LTD

ALLRIGHTS RESERVED

REISSUE

-

14 AUGUST

1995

FAA APPROVED

BHT-212-FMS-19 NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P.

O. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-19

FAA APPROVED LOG OF REVISIONS

Original ...........

0..............

14 JUN 77

Revision .......... Reissue...........0

1 .............. .............

06 DEC 77 14 AUG 95

LOG OF PAGES REVISION NO.

PAGE

A-B

FLIGHTMANUAL Title -

NP ..............................

0

REVISION NO.

PAGE

..................................

0

1-6 ................................... 0

NOTE Revised text Is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-19 LOG OF APPROVED

..............

14 JUN 77

.............. Revision Reissue...........0.............

06 DEC 77 14 AUG 95

Original...........0

REVISIONS

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

0

BHT-212-FMS-19

FAA APPROVED

Section 1-3.

1

TYPES OF OPERATION

Day and night VFR operations approved.

only are

1-6. WEIGHT AND CENTER OF GRAVITY Actual weight change shall be determined after AFCS/autopilot kit has been installed

1-5. CONFIGURATION

and ballast readjusted, if necessary, to return empty weight CG to within allowable

AFCS/Autopilot kit is approved for skid gear and popout floats only.

limits.

Flight with fixed floats is prohibited.

1-7. AIRSPEED Due to control authorities

required for

flight at airspeeds below 40 knots,

automatic flight control system (AFCS) shall not be utilized at less than 40 knots except for ground checks.

Section 2 2-6. SYSTEMSCHECK

procedures

AFCS POWER switch -

NOTE

AFCS mode of operation

ensure

operation of AFCS.

is

annunciated on instrument panel by a three segment light - PITCH,......... ROLL, and YAW. AFCS functions

proper

POWER.

.... CAUTION

in two modes: automatic with turn and trim functions, and steering

DURING AFCS CHECKOUT, MONITOR ALL CONTROLS TO

using pilot cyclic control.

E N S U R E

AFCS

annunciation on instrument panel is applicable to both modes. SYSTEM CHECK Following

DEFLECTIONS EXCESSIVE.

C O N T R O L

ARE

NOT

BHT-212-FMS-19

FAA APPROVED

Channel ARM switches -

ATTD.

ATTD switch

SCAS NO GO lights - Illuminated, should extinguish within several seconds to indicate system null. Cyclic - Move forward/aft and hold, check PITCH NO GO light illuminates then extinguishes after several seconds. Cyclic - Move laterally and hold, check ROLL NO GO light illuminates then extinguishes after several seconds. Pedals - Move and hold, check YAW NO GO light illuminates and then extinguishes after several seconds. SCAS switch illuminate. SCAS switch extinguish. SCAS switch

SCAS, SCAS lights Off (down), SCAS lights

-

SCAS,

INV 1 switch -

ENGA, AFCS lights

Pilot AFCS RELEASE switch - Press, AFCS lights extinguish, SCAS disengages. SCAS switch illuminate.

SCAS, SCAS lights

ATTD switch - ENGA, AFCS lights illuminate, SCAS lights extinguish.

Copilot AFCS RELEASE switch (if installed) - Press, AFCS lights extinguish, SCAS disengages. SCAS switch illuminate.

SCAS, SCAS lights

ATTD switch - ENGA, AFCS lights illuminate, SCAS lights extinguish.

SCAS lights

illuminate.

-

illuminate, SCAS lights extinguish.

NOTE

For proper AFCS flight operation, OFF, SCAS disengages.

INV 1 switch -

ON, check no. 1 AC

voltmeter for 104 to 122 volts,

SCAS switch illuminate.

Press,

SCAS disengages.

SCAS switch illuminate.

SCAS, SCAS lights

Cyclic friction -

installed) - Press, SCAS disengages.

SCAS switch - SCAS, SCAS lights illuminate.

Adjust.

AFCS automatic follows:

mode -

Check as

Pitch - Actuate PITCH trim wheel through cycle. Cyclic should follow and AFCS PITCH light remain illuminated.

Copilot AFCS RELEASE switch (if

FORCE TRIM switch -

is required. Adjust cyclic friction as desired to prevent cyclic feedback.

SCAS, SCAS lights

Pilot AFCS RELEASE switch -

a slight amount of cyclic friction

Center cyclic

as desired

with cyclic FORCE TRIM switch.

Actuate AFCS TRIM switch (cyclic) forward and aft. Cyclic should follow

and AFCS pitch

light

remain

illuminated. Center cyclic as desired with cyclic FORCE TRIM switch.

ON.

ATTD switch - ENGA, AFCS lights illuminate, SCAS lights extinguish. ATTD switch - DSENGA, AFCS lights extinguish, SCAS lights illuminate.

Roll - Actuate ROLL trim wheel through cycle. Cyclic should follow and AFCS ROLL light remain illuminated. Center cyclic as desired with cyclic FORCE TRIM switch. Actuate AFCS TRIM switch (cyclic) laterally. Cyclic should follow and AFCS ROLL light remain Illuminated.

2

FAA APPROVED

BHT-212-FMS-19

Center cyclic as desired with cyclic FORCE TRIM switch.

Turn - Actuate TURN knob through cycle. Cyclic should follow and AFCS PITCH and ROLL lights remain

illuminated.

AFCS YAW light

extinguishes. Center cyclic as desired with cyclic FORCE TRIM switch.

AFCS pilot cyclic steering mode -

2-9. IN-FLIGHT OPERATIONS Maneuvering with AFCS on may be accomplished by either: Press TURN knob and select desired

angle of bank.

Apply pedals as

necessary to maintain coordinated flight. Use PITCH trim as necessary to maintain

desired attitude.

Check as follows: NOTE

Pitch - Displace cyclic slightly forward and release. AFCS PITCH light extinguishes, SCAS PITCH light illuminates. Displace cyclic slightly

If ROLL trim wheel is used during turn, helicopter may not return to level flight (in roll) when turn is terminated.

aft and release. AFCS PITCH light extinguishes, SCAS PITCH light

OR

illuminates. Roll -

Displace cyclic slightly left and

release.

AFCS ROLL light

extinguishes, SCAS ROLL light illuminates. Displace cyclic slightly right and release.

extinguishes, illuminates. Yaw -

pitch

attitude.

Apply

pedals

as

necessary to maintain balanced flight during turning maneuver. OR

Press cyclic FORCE TRIM switch and

Displace

and release.

extinguishes, illuminates. right

AFCS ROLL light

SCAS ROLL light

Move cyclic to desired bank angle and

pedals slightly

left

AFCS YAW light

SCAS YAW light

Displace pedals slightly

and release.

extinguishes, illuminates.

AFCS YAW light

SCAS YAW light

CYCLIC CONTROL MAY MOTOR

TO STOP IF AFCS IS LEFT

maneuver as desired. Release switch when maneuver is completed and with

helicopter in level attitude.

2-10.

DESCENT AND

2-11.

ENGINE SHUTDOWN

LANDING

AFCS POWERswitch - Off (down).

ENGAGED WHILE HELICOPTER IS ON GROUND.

WARNING

ATTD switch -

takeoff).

DSENGA (prior to IF AFCS IS LEFT ENGAGED ON

2-8. TAKEOFF ATTD switch -

MAY MOTOR TO STOPS.

ENGA as desired above 40

knots. 3

BHT-212-FMS-19

FAA APPROVED

Section 3 3-6.

HYDRAULIC SYSTEM

3-7.

ELECTRICAL

UToNi

SYSTEM

NO. 2 ENGINE PRESSURE INSTRUMENTS AND PILOT AC POWERED INSTRUMENTS WILL

3-7-C. AC FAILURE - SYSTEM NO.

BE INOPERATIVE.

1

3-9. AUTOMATIC FLIGHT CONTROLS SYSTEM

NOTE Normally, number 3 inverter will supply power to either bus If a failure of No. 1 or No. 2 inverter

should occur.

If no power is

available on No. 1 bus, proceed as follows: PITCH, ROLL, and YAW channel

3-9-A. AFCS WILL NOT ENGAGE -

ANYCHANNEL FORCE TRIM switch (pedestal) ON.

Check

ARM

switches - OFF.

Channel ARM switches -

Check in

ATTD position.

SCAS switch - SCAS.

iCAUTIN

Attitude gyros - Walt until fully erected. NO. 1 ENGINE

PRESSURE

INSTRUMENTS AND COPILOT AC POWERED INSTRUMENTS, IF

INSTALLED,

WILL BE

INOPERATIVE.

AFCS circuit breakers -

Check in.

3-9-B. AFCSWILL NOTENGAGEYAW CHANNEL ONLY

3-7-D. 2

AC FAILURE - SYSTEM NO.

NOTE

4

TURN trim knob not pressed. Pedals -

Check centered and

Force trim centered.

Normally, number 3 inverter will supply power to either bus If a

Yaw channel ARM switch ATTD.

Check in

failure of No. 1 or No. 2 inverter should occur.

AFCS HDG circuit breakers -

Check in.

FAA APPROVED

BHT-212-FMS-19

Copilot directional gyro (if installed) Check operative.

channel ARM switches Individual (operative channels) - SCAS or ATTD, as desired.

NOTE

SCAS switch -

SCAS.

If any unusual

Yaw AFCS channel will drop out if pilot uses manual slaving switch

control input, disengage SCAS. ATTD switch - ENGA (if desired).

on copilot directional gyro.

unusual control input, disengage AFCS.

If any

3-9-C. FEEDBACK FELT IN CYCLIC DURING SCAS ONLY FLIGHT

3-9-G. SCAS

Insufficient cyclic friction applied. Adjust per BHT-212-MM-1.

Affected channel - Disengage by positioning appropriate channel ARM

INOPERATIVE CHANNEL -

switch to OFF.

IN AFCS -

3-9-D. OSCILLATIONS ANY CHANNEL Affected channel BHT-212-MM-1.

Disengage and refer to

3-9-H. AFCS

INOPERATIVE CHANNEL -

Affected channel -

Disengage by turning

appropriate channel ARM switch to SCAS 3-9-E. SYSTEM

HYDRAULIC FAILURE

or OFF.

NO. 1

Yaw channel switch OFF.

Disengage by turning YAW

3-9-J. INOPERATIVE ATTITUDE GYRO - COPILOT ATTD PITCH and ROLL channels

3-9-F. SYSTEM REENGAGE AFTER DISENGAGE

NOTE

No. 1 AC voltmeter - Check for proper voltage. If voltage not available, all

SCAS will work normally on all channels unless gyro failure was

channels will be inoperative.

caused by AC system failure.

Circuit breakers -

In. If a circuit

breaker has tripped and trips again after

being reset, do not attempt further resetting. SCAS POWER switch -

Individual channel NO GO lights -

3-9-K. INOPERATIVE HEADING

GYRO- COPILOT ATTD YAW channel -

POWER. Move

-

Disengage.

Disengage.

NOTE

appropriate flight control and observe each light illuminates. Do not attempt to engage a channel that did not illuminate

SCAS will work normally on all channels unless gyro failure was

when control was moved.

caused by AC system failure.

Individual channel NO GO lights Extinguished

(do not attempt to engage

channel if light is illuminated). 5

FAA APPROVED

BHT-212-FMS-19

3-9-L.

HYDRAULIC FAILURE -

SYSTEM SYSTEM 22

Paragraph

Pitch and roll channels - Disengage by turning PITCHand ROLL switches OFF. 3-9-M. AFCS RUNAWAY, .HARDOVER, OR OTHERUNAWAYFlight HARDOVER, OR OTHER UNUSUAL CHARACTERISTIC Helicopter attitude -

Correct with cyclic

3-9-F.

3-9-N. EMERGENCY EVASIVE MANEUVER controls - Use as needed to maneuver helicopter. FORCE TRIM switch (cyclic) - Press and hold until back to desired attitude to resume AFCS control.

and pedals. AFCS RELEASE switch -

Press, check

AFCS control panel for SCAS switch drop out. SCAS channel switches -

OFF.

NOTE

After resuming straight and level flight, channels of SCAS and

6

AFCS can be carefully re-engaged by utilizing procedures listed in

AFCS control panel -

desired attitude.

Use to re-attain

BHT-212-FMS-20

* MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

ALTITUDE HOLD SYSTEM 212-899-143 CERTIFIED DECEMBER 12, 1977

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when altitude hold system is installed.

Information contained herein supplements

information of basic Flight Manual. For

Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter Inc of Textron A Subsidiary

NOTICE COPYRIGHT COPYRIGHT

1995

INC. BELL HELICOPTER ANDBELLHELICOPTER TEXTRON INC. A DIVISION OF TEXTRON CANADA LTD RESERVED ALLRIGHTS

POST OFFICE BOX 482 * FORT WORTH. TEXAS 76101

REISSUE

-

14 AUGUST

1995

FAA APPROVED

BHT-212-FMS-20 NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P.

O. Box

482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

BHT-212-FMS-20 LOG OF REVISIONS

Original...........0

..............

12 DEC 77

Revision .......... Reissue...........0

1..............01 .............

OCT 84 14 AUG 95

LOG OF PAGES

a*

REVISION NO.

PAGE

FLIGHTMANUAL Title - NP..............................

A-B 0

REVISION NO.

PAGE

..................................

0

1 -2...................................0

NOTE Revised text Is Indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-20 LOG OF APPROVED

Original...........0 Revision.......

.............. ..............

12 DEC 77 01 OCT 84

Reissue...........0

.............

14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

REVISIONS

FAA APPROVED

Section

BHT-212-FMS-20

1

1-6. WEIGHT AND CENTER OF GRAVITY

and ballast readjusted, if necessary, to return empty weight CG to within allowable

limits.

Actual weight change shall be determined

after altitude hold system kit is installed

Section 2 2-6. SYSTEMS CHECK

ALT HOLD switch -

Engage.

2-9. IN-FLIGHT OPERATIONS 2-6-G. AFCSCHECK

ALT HOLD system

automatically

holds

altitude through pitch channel of AFCS when engaged. System is interlocked to pitch ATTD mode and may be released in same manner as ATTD.

Following...

Operation of AFCS trim switch on cyclic or pitch trim wheel on AFCS trim panel is not required when ALT HOLD Is engaged.

CAUTION

CYCLIC CONTROLS MAY MOTOR

TO STOPS IF AFCS IS LEFT ENGAGEDWHILE HELICOPTERIS ON GROUND. ATTD switch -

desired altitude even if helicopter is climbing or descending (500 ft/min maximum).

ENGA.

ALT HOLD power switch -

System may be engaged upon reaching

ON.

BHT-212-FMS-20

FAA APPROVED

Section 3 If ALT HOLD system fails, turn power off and continue operation in ATTD mode If

desired.

2

0

BHT-212-FMS-24

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

SEAT CUSHION 412-706-019 CERTIFIED JULY 24, 1987

This supplement shall be attached to Bell Helicopter

Model 212 Flight Manual when seat

cushion kit has been installed.

Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter COPYRIGHT NOTICE COPYRIGHT 1995

A Subsidiary ofTextronInc POSTOFFICE BOX412* FORTWORTH. TEXAS76101

ANDBELLHELICOPTER TEXTRON INC. A DIVISION OF TEXTRON CANADA LTD ALLRIGHTS RESERVED

REISSUE -

14 AUGUST 1995

BHT-212-FMS-24

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. O. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-24

FAA APPROVED LOG OF REVISIONS

Original...........0

..............

24 JUL 87

Reissue...........0

.............

14 AUG 95 LOG OF PAGES REVISION NO.

PAGE

A -B

FLIGHT MANUAL

Title - NP..............................

0

REVISION NO.

PAGE ..................................

1/2 ......................................

0

0

NOTE Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-24

FAA APPROVED LOG OF APPROVED

Original ........... .......... Reissue...........0.............

24 JUL 87 14 AUG 95

APPROVED:

MANAGER

/

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

REVISIONS

FAA APPROVED

Section

.

BHT-212-FMS-24

1

1-6. WEIGHT AND CENTER OF GRAVITY

1-20. INSTRUMENT MARKINGS AND PLACARDS

Actual weight change shall be determined

after seat cushion kit Is Installed and ballast readjusted, if necessary, to return limits. empty weight empty weight CG CG to to within within allowable allowable limits.

DOORS MUST BE KEPT

CLOSED DURINGFLIGHTIF

SEAT CUSHIONS INSTALLED

Section 2 2-7. BEFORE TAKEOFF Passenger doors - Closed.

1/2

BHT-212-FMS-25

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

FIXED STEP 212-706-057 CERTIFIED SEPTEMBER 27, 1989

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when fixed step is installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

BHT-212-FMS-25

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P.

O. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

' BHT-212-FMS-25 LOG OF REVISIONS

Original...........0

..............

27 SEP 89

Reissue...........

.............

14 AUG 95 LOG OF PAGES REVISION NO.

PAGE

A -B

FLIGHT MANUAL

REVISION NO.

PAGE ..................................

1/2 ...................................... Title - NP ..............................

0

0

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-25

FAA APPROVED LOG OF APPROVED

Original...........0.............. Reissue...........0.............

27 SEP 89 14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

REVISIONS

FAA APPROVED

Section

BHT-212-FMS-25

1

1-5. CONFIGURATION

readjusted,

if necessary, to return empty

weight CG to within allowable limits.

Emergency float kit (212-706-050 or 212706-042), passenger power step kit (212706-105), and internal rescue hoist kit (214-

706-003) shall not be installed conjunction with fixed step kit.

1-6.

in

WEIGHT AND CENTER OF

GRAVITY Actual weight change shall be determined

after fixed step kit is installed and ballast

1/2

BHT-212-FMS-CAN-26

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

INTERNAL RESCUE HOIST AND CARGO HOOK CANADIAN ADDENDUM CERTIFIED NOVEMBER 9, 1989

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when internal rescue hoist and cargo hook are installed.

Information contained herein supplements

information of basic Flight Manual. For

Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter COPYRIGHT NOTICE COPYRIGHT 1995 INC. BELL HELICOPTER ANDBELLHELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD. ALLRIGHTS RESERVED

A Subsidiary of Textron Inc. 76101 · FORTWORTH,TEXAS BOX 482 POSTOFFICE

REISSUE -

14 AUGUST 1995

BHT-212-FMS-CAN-26

FAA APPROVED SUPPLEMENT FOR DOT NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED SUPPLEMENT FOR DOT

BHT-212-FMS-CAN-26

LOG OF REVISIONS Original...........0

Reissue...........0

.....

.......

November 9, 1989

August 14, 1995 LOG OF PAGES

PAGE

REVISION NO.

Cover - Title ..........................

0

1/2 ......................................

0

A--B ..................................

PAGE

REVISION NO.

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

A

FAA APPROVED SUPPLEMENT FOR DOT

BHT-212-FMS-CAN-26 LOG OF APPROVED Original...........

.....

Reissue...........

.......

REVISIONS

November 9, 1989

August 14, 1995

NOTICE

This addendum provides additional information to that contained within the Internal Hoist and External Cargo Hook Operation FAA Flight Manual Supplements.

This addendum applies to Canadian Registered helicopters

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

only.

FAA APPROVED SUPPLEMENT FOR DOT

Section

1-3.

BHT-212-FMS-CAN-26

1

TYPES OF OPERATION

1-10.

HEIGHT-VELOCITY

No person shall be carried during internal hoisting or cargo hook operations unless

Height-velocity limitations of BHT-2121FRFM-1 or BHT-212VFR-FM-1 are not limitations for internal hoisting or cargo

that person:

hook operations.

is a crewmember; is a crewmember trainee; or

performs a function essential to operation.

This page applies to Canadian Registered helicopters only.

1/2

BHT-212-FMS-28

ROTORCRAFT

~*

FLIGHT MANUAL SUPPLEMENT

TWO-SPEED INTERNAL HOIST 214-706-003 CERTIFIED 7 MAY 1992

This supplement shall be attached to the Bell Helicopter

212 VFR Flight Manual when the 214-

706-003 Two-Speed Internal Hoist has been installed.

Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter Wi i COPYRIGHT NOTICE COPYRIGHT 1995 BELL HELICOPTER INC.

ANDBELLHELICOPTER TEXTRON INC A DIVISION OFTEXTRON CANADA LTD RESERVED ALLRIGHTS

A Subsidiary of Textron Inc POST OFFICE BOX 42 · FORT WORTH, TEXAS 76101

REISSUE

-

14 AUGUST

95

BHT-212-FMS-28

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. O. Box 482

Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-28

FAA APPROVED LOG OF REVISIONS Original...........0 Reissue...........0

............. .............

07 MAY 92 14 AUG 95 LOG OF PAGES REVISION NO.

PAGE

PAGE A-

FLIGHT MANUAL

Title- NP.............................. 0

B ..................................

i/ii.......................................

REVISION NO. 0

1-8...................................0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-28

FAA APPROVED LOG OF APPROVED

Original...........0............. Reissue...........0.............

07 MAY 92 14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

REVISIONS

FAA APPROVED

BHT-212-FMS-28 GENERAL INFORMATION

The Internal Hoist enables cargo and emergency rescue operations in areas where landing cannot be accomplished. The hoist can raise or lower loads up to

600 pounds (272 kilograms).

The hoist

contains 250 usable feet (76.2 meters) of 3/ 16 inch (4.76 mm) diameter cable. The hoist provides two extend/retrieve speeds

(HIGH and LOW). With LOW speed selected, a continuously variable speed

range from zero to 125 feet/minute (45.7 meters/minute) is available. With HIGH speed selected, a continuously variable speed range from zero to 250 feet/minute

(76.2 meters/minute) is available.

An

electrically actuated cable cutting device allows either the pilot or hoist operator to sever the cable if necessary. A manually

actuated cutting device is provided for use in the event of an electrical failure.

0

i/ii

FAA APPROVED

Section

BHT-212-FMS-28

1

1-3. TYPES OF OPERATION

Flight Manual Refer to appropriate Supplement(s) for additional limitations,

Hoist operations shall be conducted under

procedures, and performance data.

appropriate operating rules for external loads.

1-6.

Passenger operations with hoist installed are approved, providing hoist is stowed system is and the hoist electrical

GRAVITY

Hoist operations are prohibited during instrument meteorological conditions.

weight CG within allowable limits.

deactivated.

WEIGHT AND CENTER OF

Actual weight change shall be determined/

after hoist is installed and ballast readjusted,

if necessary, to return empty

Maximum gross weight including

hoist

load is 11,200 pounds (5080 kilograms).

1-4. FLIGHT1-4. CREW CREW FLIGHT

Maximum hoist load is 600 pounds (272 This is a structural

limitation

A crewmember wearing an approved safety

kilograms).

harness in passenger compartment is required during all phases of hoist

only and does not ensure that longitudinal or lateral CG will remain within approved limits. Maximum allowable hoist load with gross gross weight, weight, center center of of gravity, gravity, varies with hoist location, and cable speed. Refer to ppropriate Hoist Loading Schedule.

operations. operations Crewmember shall wear Crew membersvaries

protective gloves for guiding cable during operation. The shall be operation. The hoist hoist operator operator shall be familiar with hoist operating procedures and limitations.

1-7. AIRSPEED 1-5.

CONFIGURATION

VNE with hinged panels locked open and cargo doors open is 20 KIAS.

1-5-B. OPTIONAL EQUIPMENT Fixed passenger step shall not be installed

concurrently with internal hoist.

VNE with hinged panels removed and cargo doors removed or secured open is 60 KIAS

Retractable passenger steps shall be stowed during hoist operations.

1-22. HOISTLIMITATIONS

Amphibious

1-22-A. HOIST SPEED

flotation

gear shall

not be

installed concurrently with internal hoist. Hoisting or lowering an empty litter in

open position (except stokes litter) is prohibited.

HIGH speed - Limited to hoist loads of 300 Ibs. (136 Kg) or less.

BHT-212-FMS-28

LOW speed -

FAA APPROVED

Limited to hoist loads of

600 lbs. (272 Kg) or less.

combinations of pilot, copilot, and hoist operator, each weighing 170

to 200 pounds

kilograms). 1-22-B.

HOIST DUTY CYCLE

The hoist is approved for continuous operation with loads not to exceed 600 pounds (272 kilograms).

weights are not within this range, these schedules are invalid, and

pilot pilot shall shall compute compute allowable allowable hoist load. Select Hoist Loading Schedule appropriate

for position In which hoist is installed. Enter schedule at helicopter gross weight prior to hoisting. Proceed vertically to

LOAD

intersect NOTE

Hoist loading schedules are based on the most adverse loading

2

(77.1 to 90.7

If crewmember

appropriate diagonal line

representing number of crewmembers on board. Then proceed horizontally to the

left to read allowable hoist load.

FAA APPROVED

BHT-212-FMS-28 HOIST IN FORWARD RIGHT POSITION BOOM FULLY EXTENDED

600

PILOT AND COPILOT

ALLOWABLE HOIST LOAD 600 LB (UP TO 10,600 LB GW.)

IN THIS AREA PROHIBITED

400

0 200

100 6800

1200

7600

8000

8400

8800

9200

9600

10.000

10.400

10800

11.200

GROSS WEIGHT PRIOR TO HOISTING - POUNDS

HOIST IN AFT RIGHT POSITION BOOM FULLY EXTENDED 600

LOADING IN THIS AREA PROHIBITE

30

400

300

400

6800

7200

7600

8000

8400

8800

9200

9600

10.000

10,400

10,800

11,200

GROSS WEIGHT PRIOR TO HOISTING - POUNDS 212-FMS28-1-1

Figure 1-1.

Hoist loading schedule (Sheet 1 of 2)

3

FAA APPROVED

BHT-212-FMS-28 HOIST IN FORWARD LEFT POSITION BOOM FULLY EXTENDED 600

IN THIS AREA

500

PROHIBITED

200

6800

7200

7600

8000

8400

8800

9200

9600

10,000

10,400

10,800

11.200

GROSS WEIGHT PRIOR TO HOISTING - POUNDS

HOIST IN AFT LEFT POSITION BOOMFULLY EXTENDED 600 LOADING INTHIS AREA PROHIBITED

500

200

6800

7200

7600

8000

8400 GROSSWEIGHT

Figure 1-1.

4

8800

9200

9600

10,000

10400

PRIOR TO HOISTING - POUNDS

Hoist loading schedule (Sheet 2 of 2)

10.800

11.200

212-FMS28-1-2

FAA APPROVED

*

BHT-212-FMS-28

Section 2

.

2-2. FLIGHT PLANNING

AIRCRAFT POSITION switch (on hoist control box) - Set in proper position.

Cable -

Check proper routing through

guide rollers, pulleys, and drums.

Hoist load can cause longitudinal

or lateral CG to exceed limits.

Gearbox oil levels - Check sight glasses.

Gross weight and center of gravity shall be computed to

assure loading within approved limits.

Hoist operators pendant -

Installed;

Electrical power cables -

Condition;

connectors secured.

NOTE

connectors secured.

If additional loads are carried during hoisting operations, loads

. CAUTION

should be placed on side of

....

helicopter opposite hoist position. Actuation

Gross weight and CG - compute with and without hoist load.

2-4.

of CABLE CUT switch

on pedestal can cut cable, regardless of HOIST PWR switch position. Actuation of CABLE CUT switch on hoist control box can cut cable, even if CABLE CUT circuit breaker is out.

INTERIOR AND

PRESTART CHECK

CABLE CUT switches (pedestal and hoist)

B

2-4-A.

HOIST INSTALLATION

-

CHECK

ff; covers safetied.

Safety vests, tether straps, hoisting slings, and litters - Condition and secured or stowed. NOTE

If pilot plans to operate hoist, it shall be Installed in forward right

2-4-B. HOIST OPERATION CHECK

position.

Cargo doors and hinged panels open or removed.

Hoist - Installed in desired position; check roof and floor

stud adapters

and

locking locking collars properly secured.

Boom actuator position;

Installed in proper

all fittings secured.

Secured

HOIST PWR, HOIST CONT, and HOIST

CABLE CUT circuit breakers - In.

BATTERY switch external power).

ON (or connect 5

BHT-212-FMS-28

FAA APPROVED

NON ESNTL BUS switch -

MANUAL.

BATTERY switch -

ICS - Check intercom between hoist operator using hoist pendant ICS trigger

OFF.

NOTE

and HOT MIKE switch (right ICS box only).

Ground

HOIST PWRswitch - ON. Check that blue

instructed to discharge helicopter electricity to before attaching

HOIST POWER light on hoist control box

static electricity before

and amber CAUTION light

on hoist

crewmember

should

be

load to hoist when possible.

pendant illuminates.

Cargo doors and hinged panels -

Hoist pendant CAUTION and OVER TEMP indicators - Press to test.

open or removed. CABLE CUT switches (pedestal and hoist)

HOIST UP/DOWN, BOOM IN/OUT, and

-

SPEED HIGH/LOW

HOIST

switches

(pilot

and

operator) - Actuate to check all hoist functions for proper operation. Check that

Secured

ff; covers safetied. PWR, CONT,

circuit breakers -

and

CABLE

CUT

In.

pilot HOIST switch overrides pendant 2-7.

HOIST switch. Hoist OVERTEMP warning lights -

to test.

Press

BEFORE TAKEOFF

Safety vests and straps -

to helicopter. Gloves -

NOTE

On and secured

On.

STEP switch (if installed) - STOW.

Maintain tension on hoist cable while reeling in and out to prevent

slack.

2-9. IN-FLIGHT OPERATIONS

HOIST and BOOM switches

(pilot

and

operator) - Actuate to check all hoist functions for proper operation. Check that pilot HOIST switch overrides operator pendant HOIST switch. Hoist cable - Check for corrosion, kinks, flat spots, fraying, or broken strands.

NOTE The Height-Velocity Diagram is not a limitation for internal hoist operations under an appropriate operating certificate. HOIST PWR switch -

Up limit switch actuator -

ON.

Raise while

hoist is reeling in and check hoist motor

stops; then release and check hoist

WARNING

resumes operation. Reduce hoist speed as cable approaches

up limit. Check that hoist stops when hook reaches up limit without excessive tension on cable. Hoist - Stowed for flight; secured. HOIST PWR switch -

helicopter with an approved safety harness during hoist operations.

Establish hover over hoist operation area. Hoist hook restraint -

OFF.

NON ESNTL BUS switch 6

hook restraint

Hoist operator shall be secured to

NORMAL.

Removed.

BHT-212-FMS-28

FAA APPROVED

SPEED switch -

As desired (refer to

2-9-A. LITTER HOISTING

LIMITATIONS).

BOOM switch (or pilot HOIST switch) -

of a When emergency transportation patient by litter is essential, every effort

OUT.

should be made to land the helicopter for

HOIST switch - DOWN.

litter loading. Litter hoisting can be hazardous and should be accomplished only when a landing is not feasible and the

DW

Discharge static electricity when possible, and connect hook to load, observing allowable hoist load.

condition of the patient precludes the use of the personnel hoisting sling.

In addition to all other procedures

contained herein, the following shall apply to litter hoisting operations.

NOTE As hook nears the up or down limits, hoist speed automatically slows.

2-9-A-1.

EMPTY LITTER RNING

HOIST switch - UP.

Hoisting or lowering an empty

CAUTION

litter

in open position

prohibited. Use care to prevent cable, hook, and load from fouling on fuselage or landing gear. Maintain zero ground

speed until load is

clear of obstructions.

is

An empty litter

suspended from hoist in open oscillate can position uncontrollably in rotor wash and

can fly upward, striking fuselage or tail rotor.

Takeoff into wind, if possible, allowing

Prior to hoisting or lowering an empty litter, litter shall be closed and secured with straps. Litter should be suspended in a near-vertical position and sling straps should be drawn tight.

obstacles if load is not internal.

2-9-A-2.

BOOM switch - IN to swing hoist boom and load into cabin, if possible.

adequate hoist load clearance over

LOADED LITTER WARNING

CAUTION

Airspeed with external load is limited by controllability. Caution

should

be exercised

Litter patient shall be secured to litter with safety straps.

carrying

an external

Hoist hook catch shall be secured

when

load,

as

handling characteristics may be affected by the size, weight, and shape of load.

Airspeed - As required for adequate controllability, not to exceed limits for hoist operations (20 or 60 KIAS, as applicable).

with safety pin prior to hoisting litter patient.

Litter sling straps should be adjusted so that litter is 24 to 28 inches (61 to 71 centimeters) below hoist hook.

7

FAA APPROVED

BHT-212-FMS-28 NOTE If litter Is suspended too far below

hook, litter cannot be loaded into helicopter with hoist hook at up

limit.

CAUTION

A loaded litter can rotate about

cable during hoisting.

Hoist

operator may have to grasp litter

sling straps to control rotation as litter approaches landing gear.

Section 3 HOISTING 3-13. OPERATIONS

3-13-B. HOIST OVERTEMP WARNING LIGHT In the event the OVER TEMP warning light

3-13-A.

HOIST LOAD JETTISON

To jettison a load in an emergency, actuate CABLE CUT switch (located on pedestal or

hoist). In event of failure of CABLE CUT switch,

sever cable with manual cable cutter (stowed in pouch on hoist.

8

(located on the pendant) illuminates, continue present operation until hoist cable is reeled in. Leave HOIST POWER switch ON (for cooling fan operation).

When OVER TEMP light extinguishes, hoisting operations desired.

may be continued

as

BHT-212-FMS-29

* MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

INCREASED TAKEOFF HORSEPOWER 212-704-153 CERTIFIED 16 DECEMBER 1991

This supplement shall be attached to the Bell Helicopter

Model 212 Flight

Manual when the

increased takeoff horsepower modification has been installed.

Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter Inc A SubsidiaryofTextron

NOTICE COPYRIGHT BELL® HELICOPTER INC. BELL HELICOPTER INC. ANDBELL HELICOPTER TEXTRON INC. A DIVISION OFTEXTRON CANADA LTD ALLRIGHTS RESERVED

OFFICE BOX482· FORT WORTH.TEXAS 78101

REISSUE

-

14 AUGUST 95

BHT-212-FMS-29 NOTICE PAGE

PROPRIETARY RIGHTS NOTICE

Manufacturer's Data portion of this supplement 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.

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

NP

FAA APPROVED

BHT-212-FMS-29 LOG OF REVISIONS

Original...........0

..............

16 DEC 91

Reissue...........0

..............

22 OCT 92

Reissue...........0

.............

14 AUG 95

LOG OF PAGES

PAGE

~REVISION NO.

REVISION PAGE

FLIGHT MANUAL

MANUFACTURER'S DATA

Title- NP.............................. A-B .................................. 0 1-

34 ..................................

NO.

35/36 ....................................

0

0

NOTE Revised text Is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-29 LOG OF APPROVED Original ......

0 .16

DEC 91

Reissue...........0

..............

22 OCT 92

Reissue...........

.............

14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

REVISIONS

FAA APPROVED

BHT-212-FMS-29

Section 1-13.

1

POWER PLANT

1-14.

TRANSMISSION

1-13-D. ENGINE TORQUE

1-14-C. TRANSMISSION TORQUE

1-13-D-1.

1-14-C-1.

PT6T-3B

SINGLE ENGINE OPERATION ENGINE SCALE 30 Minute power range

63.9% to 79.4%

Maximum

79.4%

PT6T-3B

TWIN ENGINE OPERATION TRANSMISSION SCALE (A) Maximum

Continuous Limit

87.5%

Takeoff Power Range 87.5 to 104.3% (5 minute)

1-13-D-2.

PT6T-3

Maximum

104.3%

SINGLE ENGINE OPERATION ENGINE SCALE 1-14-C-2. PT6T-3 30 Minute power range

63.9% to 71.8%

Maximum

71.8%

TWIN ENGINE OPERATION TRANSMISSION SCALE (A) Maximum

Continuous Limit

87.5%

Takeoff Power Range 87.5 to 104.3% (5 minute) Maximum

104.3%

1

FAA APPROVED

BHT-212-FMS-29

Section 2 2-7.

BEFORE TAKEOFF

2-8. Area -

TAKEOFF Clear.

Throttles - Full open. Adjust friction. NOTE RPM switch to 5 seconds).

Minimum beep (DECR for 4

RPM switch -

Minimum trim (-2 for 4 to 5

seconds).

As collective is increased,

RPM switch -

Adjust to obtain matching

TORQUE or ITT, as required, ROTOR -

Check 95% or greater.

and 100%

ROTOR. Hover power -

RPM switch -

It may

be necessary to rematch engine torques prior to reaching hover.

Adjust to obtain matching

Check TORQUE required

to hover at four feet skid height

TORQUE or ITT at 100% ROTOR.

Flight instruments - Check operation and set.

Section 3 No change from basic manual.

3

FAA APPROVED

BHT-212-FMS-29

Section 4 4-1. INTRODUCTION Performance data presented herein are

equipment which would appreciably

affect

lift, drag, or power available (Figure 4-1 and 4-2).

derived from engine manufacturer's specification power for engine less

Figures 4-3 through 4-6 present through 4-6 present Figures 4-3

Increased Takeoff Horsepower

externaal cargo, and amphibious

installation

losses

when used with

modification. These data are applicable to

basic helicopter without any optional

4

performance data for winterization heater,

operatons.

FAA APPROVED

BHT-212-FMS-29

HOVER CEILING OUT OF GROUND EFFECT SKID HEIGHT 60 FEET HEATEROFF

TAKEOFF POWER ENGINERPM 100%

0° TO 52°C

GENERATOR 150 AMPSEACH 14,000 FT. DEN. ALT. LIMIT

MAXIMUMGROSS WEIGHT LIMIT

HOT DAY

LIMIT

30

OAT

35

40

45

GROSSWEIGHT

Figure 4-1.

50

KG x 100 212-FMS29-4-1-1

Hover ceiling chart (sheet 1 of 4)

5

FAA APPROVED

BHT-212-FMS-29

HOVER CEILING OUTOFGROUNDEFFECT SKIDHEIGHT60 FEET ON HEATER 0° TO20°C

POWER TAKEOFF ENGINERPM100% 150 AMPSEACH GENERATOR 14,000 FT. DEN. ALT. LIMIT

Figure 4-1.

6

Hover ceiling chart (sheet 2 of 4)

BHT-212-FMS-29

FAA APPROVED

HOVER CEILING OUT OF GROUNDEFFECT SKID HEIGHT 60 FEET HEATEROFF

TAKEOFF POWER ENGINE RPM 100%

TO0° -54°C

150 AMPSEACH GENERATOR 14,000 FT. DEN. ALT. LIMIT

MAXIMUMGROSS WEIGHTLIMIT

OAT-°C

-60 -50 -40 -30 -20 -10 OAT- C

8

0 35

9

10

11

40

45

50

GROSSWEIGHT

Figure 4-1.

12 LBX1000 KGx 100 212-FMS29-4-1-3

Hover ceiling chart (sheet 3 of 4)

7

FAA APPROVED

BHT-212-FMS-29

HOVER CEILING EFFECT OUTOF GROUND SKIDHEIGHT60 FEET ON HEATER 0° TO-54°C

TAKEOFFPOWER ENGINERPM100% GENERATOR 150 AMPSEACH 14,000 FT.DEN.ALT.LIMIT

MAXIMUMGROSS WEIGHT LIMIT

'

OAT °C

0

-60 -50 -40 -30 -20 -10 OAT- °C

Figure 4-1.

8

8

0 35

9

10

45 40 GROSSWEIGHT

Hover ceiling chart (sheet 4 of 4)

11

12LBX1000

50

KG x 100 212-FMS29-4-1-4

FAA APPROVED

BHT-212-FMS-29

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF

CLIMBWILLDECREASE 200 FT/MIN TAKEOFF POWER ENGINE RPM 100% GENERATOR150 AMPS EACH

VCAL 55 KNOTS HEATEROFF

GROSSWEIGHT 7000 LB.

20,000

18,000

30 20

16,000

14,000 12,000

6000 8000

4000

0

400

800

1200

1600

2000

2400

2800

RATE OF CLIMB - FT/MIN

Figure 4-2.

3200 3600 212-FMS29-4-2-1

Twin engine rate of climb (sheet 1 of 10)

9

FAA APPROVED

DnT-212-FMS-29

TWIN ENGINE RATE OF CLIMB WITHALL DOORSOPEN,RATEOF 200 FT/MIN CLIMBWILL DECREASE VCAL 55 KNOTS HEATERON

TAKEOFFPOWER ENGINERPM 100% GENERATOR150 AMPS EACH GROSS WEIGHT 7000 LB.

20.000 OAT

30

18,000

16.000 OAT

LIMIT 14,000

12,000

8000

6000

4000

2000 HEATER ON

0

400

800

1200

1600

2000

2400

2800

RATE OF CLIMB - FT/MIN

Figure 4-2. Twin engine rate of climb (sheet 2 of 10)

10

3200

3600

212-FMS29-4-2-2

BHT-212-FMS-29

FAA APPROVED

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF CLIMB WILL DECREASE200 FT/MIN VCAL 55 KNOTS HEATEROFF

TAKEOFF POWER ENGINE RPM 100% GENERATOR150 AMPS EACH

GROSSWEIGHT8000 LB.

0

400

B00

1200

1600

2000

2400

2800

RATE OF CLIMB - FT/MIN

Figure 4-2.

3200 212-FMS29-4-2-3

Twin engine rate of climb (sheet 3 of 10)

11

FAA APPROVED

BHT-212-FMS-29

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN. RATEOF

200 FT/MIN CLIMBWILL DECREASE VCAL 55 KNOTS HEATERON

TAKEOFFPOWER ENGINERPM 100% GENERATOR150 AMPS EACH GROSS WEIGHT 8000 LB.

20,000 18,000

OAT -C

40

-30 OAT

-20

14,000

12,000

8000

4000

RATE OF CLIMB - FT/MIN 212-FMS29-4-2-4

Figure 4-2.

12

Twin engine rate of climb (sheet 4 of 10)

FAA APPROVED

BHT-212-FMS-29

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF

CLIMBWILL DECREASE 200 FT/MIN VCAL 55 KNOTS HEATEROFF

TAKEOFFPOWER ENGINERPM 100% GENERATOR150 AMPS EACH GROSS WEIGHT 9000 LB.

Figure 4-2.

Twin engine rate of climb (sheet 5 of 10)

13

BHT-212-FMS-29

FAA APPROVED

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN. RATE OF

200 FT/MIN CLIMBWILL DECREASE VCAL 66 KNOTS HEATERON

TAKEOFFPOWER ENGINERPM 100% GENERATOR150 AMPS EACH GROSS WEIGHT 9000 LB.

20,000 -50

OAT - C

-40

18,000

16,000

LU

2000 HEATER ON 0

400

800

1200

1600

2000

2400

2800

RATE OF CLIMB - FT/MIN

Figure 4-2. 14

Twin engine rate of climb (sheet 6 of 10)

3200 212FMS29-4-2-6

FAA APPROVED

BHT-212-FMS-29

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF

CLIMBWILLDECREASE 200 FT/MIN TAKEOFFPOWER ENGINERPM 100% GENERATOR150 AMPS EACH

VCAL 55 KNOTS HEATEROFF

GROSSWEIGHT 10,000 LB.

Figure 4-2.

Twin engine rate of climb (sheet 7 of 10)

15

FAA APPROVED

BHT-212-FMS-29

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN. RATE OF

CLIMBWILLDECREASE 200 FT/MIN TAKEOFF POWER ENGINERPM 100% GENERATOR150 AMPS EACH

VCAL 55 KNOTS HEATERON

GROSS WEIGHT 10.000 LB.

20,000 50

14,000 12,000

4000 2000

Figure 4-2.

0

400

Twin engine rate of climb (sheet 8 of 10)

HEATER 800 ON 1200

1600

2000

2400

2800

RATE OF CLIMB - FT/MIN

Figure 4-2. Twin engine rate of climb (sheet 8 of 10)

16

3200

FAA APPROVED

BHT-212-FMS-29

TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF CLIMB WILL DECREASE200 FT/MIN TAKEOFF POWER ENGINERPM 100% GENERATOR150 AMPS EACH

VCAL 55 KNOTS HEATEROFF

GROSSWEIGHT 11.200 LB.

20,000

18,000

- 50 40

OAT- °C

16,000

14.000

12,000

10,000 8000

6000

4000 OAT LIMIT

2000

0 0

400

800

1200

1600

2000

2400

2800

RATE OF CLIMB - FT/MIN

Figure 4-2.

3200 212-FMS29-4-2-9

Twin engine rate of climb (sheet 9 of 10)

17

FAA APPROVED

BHT-212-FMS-29

TWIN ENGINE RATE OF CLIMB WITHALL DOORSOPEN,RATEOF 200 FT/MIN CLIMBWILL DECREASE VCAL55 KNOTS ON HEATER

TAKEOFFPOWER ENGINERPM100% 150 AMPSEACH GENERATOR GROSSWEIGHT11,200 LB. 20,000

18.000 OAT-C

-\40 16,000

Lu

2000 HEATERON 0

400

800

1200

1600

2000

2400

2800

RATEOFCLIMB- FT/MIN Figure 4-2. Twin engine rate of climb (sheet 10 of 10)

18

3200 212-FMS29-4-2-10

FAA APPROVED

BHT-212-FMS-29

WINTERIZATION HEATER TWIN ENGINE RATE OF CLIMB WITHALL DOORSOPEN,RATEOF CLIMBWILLDECREASE 200 FT/MIN. TAKEOFF POWER ENGINERPM100% GENERATOR 150 AMPSEACH

55 KCAS WINTERIZATION HEATER ON GROSSWEIGHT7000 LB.

20,000 50

OAT °C

18,000 -3

OAT

12,000

10,000

8000

6000

4000

2000

0

400

800

1200

1600

2000

2400

RATE OF CLIMB - FT/MIN

Figure 4-3.

Twin engine rate of climb with winterization

2800

3200

3600

212-FMS29-4-3-1

heater (sheet 1 of 5) 19

FAA APPROVED

BHT-212-FMS-29

WINTERIZATION HEATER TWIN ENGINE RATE OF CLIMB WITH ALLDOORSOPEN,RATEOF 200 FT/MIN. CLIMBWILL DECREASE POWER TAKEOFF ENGINERPM100% 150 AMPSEACH GENERATOR

55 KCAS ON HEATER WINTERIZATION GROSSWEIGHT8000 LB.

20,000 18,000 OAT LIMIT

-20

16,000

12,000 000

8000

6000

4000

2000

0

400

800

1200

1600

2000

2400

RATEOFCLIMB- FT/MIN Figure 4-3.

20

Twin engine rate of climb with winterization

2800

3200 212-FMS294-3-2

heater (sheet 2 of 5)

FAA APPROVED

BHT-212-FMS-29

WINTERIZATION HEATER TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF

CLIMBWILLDECREASE 200 FT/MIN. TAKEOFF POWER

55 KCAS

ENGINERPM 100% GENERATOR150 AMPS EACH

WINTERIZATION HEATERON GROSS WEIGHT 9000 LB.

20.000

18,000

16,000

14,000 12.000

\

\

1200

1800

6000

4000

2000

0

400

800

2000

2400

RATE OF CLIMB - FT/MIN

Figure 4-3.

Twin engine rate of climb with winterization

2800

3200 212-FMS29-4-3 3

heater (sheet 3 of 5)

21

BHT-212-FMS-29

FAA APPROVED

WINTERIZATION HEATER TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF

CLIMBWILL DECREASE 200 FT/MIN. TAKEOFFPOWER ENGINERPM 100% GENERATOR150 AMPS EACH

55 KCAS WINTERIZATION HEATERON GROSS WEIGHT 10,000 LB.

20,000-

-50 -40

OAT

18,000

16,000

14,000

12,000 10,000

8000

6000

4000

2000

0

400

800

1200

1600

2000

2400

RATEOFCLIMB- FT/MIN Figure 4-3.

22

Twin engine rate of climb with winterization

2800

3200 212-FMS29-4-3-4

heater (sheet 4 of 5)

BHT-212-FMS-29

FAA APPROVED

WINTERIZATION HEATER TWIN ENGINE RATE OF CLIMB WITH ALL DOORS OPEN, RATE OF

CLIMBWILLDECREASE 200 FT/MIN. TAKEOFFPOWER

55 KCAS

ENGINERPM 100% GENERATOR150 AMPS EACH

WINTERIZATION HEATERON GROSS WEIGHT 11,200 LB.

20.000

-50 -40 16,000

-30

OAT-

-C

12,000

8000,

6000 4000

Figure 4-3.

Twin engine rate of climb with winterization

heater (sheet 5 of 5)

23

BHT-212-FMS-29

FAA APPROVED

WINTERIZATION HEATER HOVER CEILING OUTOFGROUNDEFFECT SKIDHEIGHT60 FEET WINTERIZATION HEATER ON 0 ° TO 20°C

TAKEOFF POWER ENGINERPM100% GENERATOR 150 AMPSEACH

14,000 FT.DEN. LT.LIMIT

0

10

20

30

40 50

8

9

10

11

12 LB x 1000

heater (sheet 1 of 2) Figure 4-4. Hover ceiling with winterization GROSS WEIGHT Figure 4-4. 24

Hover ceiling with winterization

heater (sheet 1 of 2)

FAA APPROVED

BHT-212-FMS-29

WINTERIZATION HEATER HOVER CEILING OUT OF GROUND EFFECT TAKEOFFPOWER ENGINERPM 100%

SKID HEIGHT 60 FEET WINTERIZATION HEATERON

0 ° TO-54°C

GENERATOR 150 AMPSEACH 14,000 FT. DEN. ALT. LIMIT

MAXIMUMGROSS WEIGHT LIMIT

TO-40

0

Coo

-60-50-40-30-20-10 OAT-

0

8

°C

9

10

11

12LBx1000

|

35

40

45

GROSSWEIGHT

Figure 4-4. Hover ceiling with winterization

50

KG x 100 212-FMS29-4-4-2

heater (sheet 2 of 2)

25

FAA APPROVED

BHT-212-FMS-29

EXTERNAL CARGO HOVER CEILING OUT OF GROUNDEFFECT SKID HEIGHT60 FEET HEATEROFF GROSS WEIGHT 10,000 TO 11,200 LB.

TAKEOFF POWER ENGINERPM 100% GENERATOR150 AMPS EACH

20,000

18,000

16,000 OAT - 'C

14,000

8000

-

2000

10.000 10,200 4600

10,400 10,600 4700

4800

10,800 4900

11,000 11,200 LB 5000

GROSS WEIGHT

Figure 4-5.

26

External cargo (sheet 1 of 6)

5100 KG 212-FMS29-4-5-1

BHT-212-FMS-29

FAA APPROVED

EXTERNAL CARGO HOVER CEILING OUT OF GROUND EFFECT TAKEOFF POWER ENGINERPM 100% GENERATOR150 AMPS EACH

SKID HEIGHT 60 FEET HEATEROFF GROSSWEIGHT UP TO 10,000 LB.

18,000

14.000

LU

Figure 4-5. External cargo (sheet 2 of 6) 27

FAA APPROVED

BHT-212-FMS-29

EXTERNAL CARGO HOVER CEILING OUT OF GROUND EFFECT SKID HEIGHT 60 FEET HEATERON GROSS WEIGHT 10,000 TO 11.200 LB.

TAKEOFF POWER ENGINERPM 100% GENERATOR150 AMPS EACH

20.000

18,000 OAT- °C 16,000

14,000

12,000

10,000

8000

6000

4000

2000

0 10,000 10,200 10,400 10.600 4600

4700

4800

10,800 11,000 4900

11,200 LB

5000

GROSS WEIGHT

Figure 4-5.

28

External cargo (sheet 3 of 6)

5100 KG 212-FMS29-4-5-3

FAA APPROVED

*^&~~

BHT-212-FMS-29

_______EXTERNAL CARGO HOVER CEILING OUT OF GROUND EFFECT

TAKEOFFPOWER

SKID HEIGHT 60 FEET

ENGINERPM100%

HEATER ON

GENERATOR150 AMPS EACH

GROSSWEIGHT UP TO 10,000 LB.

20,000 OAT -

18 000

C

0 00 0

1 61000 .

LB. GW

I

'1

''

1 I'

1

FOR OVER

10,000 LB.GW SEE CHART

2000-----------

6000 2500

7000 3000

8000

9000

10,000

3500 4000 4500 GROSSWEIGHT WEIGHT GROSS

Figure 4-5.

11,200 LB 5000 KG 212-FMS29-45-4

External cargo (sheet 4 of 6)

29

FAA APPROVED

BHT-212-FMS-29

EXTERNAL CARGO HOVER CEILING IN GROUND EFFECT SKID HEIGHT 4 FEET HEATEROFF

TAKEOFF POWER ENGINERPM 100% GENERATOR150 AMPS EACH

20,000

OAT- °C

(OATLIMIT)20

16,000

14,000

12,000 (OATLIMIT)30 10,000

8000

6000 6000

(OAT LIMIT) 40

c

4000

2000 (OATLIMIT50) 6000 2500

8000

7000 3000

3500

9000 4000

10.000 4500

11.200 LB 5000

GROSSWEIGHT

Figure 4-5.

30

External cargo (sheet 5 of 6)

KG

212-FMS29-4-5-5

FAA APPROVED

BHT-212-FMS-29

*^R§~

EXTERNAL CARGO HOVER CEILING IN GROUND EFFECT

TAKEOFF POWER ENGINERPM 100% GENERATOR150 AMPS EACH

*

SKID HEIGHT 4 FEET HEATERON

18,000

16,000 - ---

__

(OATLIMIT)20

-30

14.000

12,000

6000

4000

6000

a.1'

'1

8000

7000

9000

.I

10,000

11,200

LB

1

GROSSWEIGHT

Figure 4-5.

External cargo (sheet 6 of 6)

31

FAA APPROVED

BHT-212-FMS-29

AMPHIBIOUS OPERATIONS HOVER CEILING OUT OF GROUND EFFECT SKID HEIGHT 60 FEET HEATERON AMPHIBIOUS OPERATIONS

TAKEOFF POWER ENGINERPM 100% GENERATOR150 AMPS EACH

10,000 OAT 9000

8000

6000

4000

3000

3500 Figure 4-6. 32 32

4000 GROSSWEIGHT

4500

Amphibious operations (sheet 1 of 3)

5000 KG 212FMS29-4-6-1

BHT-212-FMS-29

FAA APPROVED

AMPHIBIOUS OPERATIONS HOVER CEILING OUTOFGROUNDEFFECT SKIDHEIGHT60 FEET HEATER OFF AMPHIBIOUS OPERATIONS

POWER TAKEOFF ENGINERPM100% GENERATOR 150 AMPSEACH 10,000

9000

8000

\

7000 6000

(OATLIMIT)40

5000 4000 000 4000

1000

(OATLIMIT)50

7000

8000 I

3500

9000

10,000

4000

4500

GROSS WEIGHT

Figure 4-6.

Amphibious

11,000

LB

5000 KG 212-FMS29-4-6-2

operations (sheet 2 of 3)

33

FAA APPROVED

BHT-212-FMS-29

AMPHIBIOUS OPERATIONS HOVER CEILING OUT OF GROUND EFFECT TAKEOFF POWER ENGINERPM 100% GENERATOR150 AMPS EACH

SKID HEIGHT 60 FEET HEATER ON AMPHIBIOUS OPERATIONS

MAX. G.W.

10,000

9000

__ 6000 6000 _

2000

1000

7000

8000 3500

9000

10,000

4000

4500

GROSS WEIGHT

Figure 4-6.

34

Amphibious

operations (sheet 3 of 3)

11,000 LB 5000 KG 212-FMS29.4-6-3

MANUFACTURER'S DATA

BHT-212-FMS-29

Section 5 No change from basic manual.

Section

1-1.

1

RPM SWITCH

212-FMS29-MD-1

Figure 1-1.

Pilot collective control panel

35/36

BHT-212-FMS-30

12

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

AIRLINE PASSENGER SEATING 412-706-028 CERTIFIED 18 JUNE 1993

This supplement shall be attached to Bell Helicopter Model 212 Flight Manual when airline passenger seating has been installed.

Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopters COPYRIGHT NOTICE COPYRIGHT 1995 BELL HELICOPTER INC. ANDBELLHELICOPTER TEXTRON INC. ADIVISION OFTEXTRON CANADA LTD ALLRIGHTS RESERVED

A Subsidiary of Textron Inc TEXAS 76101 POSTOFFICEBOX482 FORTWORTH. REISSUE

14

AUGUST

995

BHT-212-FMS-30 NOTICE PAGE

l PROPRIETARY RIGHTS NOTICE

Manufacturer's Data portion of this supplement 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.

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

NP

FAA APPROVED

BHT-212-FMS-30 LOG OF REVISIONS

Original...........0

..............

18 JUN 93

Reissue...........0

.............

14 AUG 95 LOG OF PAGES REVISION NO.

PAGE

PAGE

FLIGHT MANUAL

REVISION NO. MANUFACTURER'S DATA

Title- NP.............................. 0 A - B .................................. 0 1- 2 ................................... 0

3- 6 ...................................0 7/8......................................

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

FAA APPROVED

BHT-212-FMS-30 LOG OF APPROVED

Original...........0

..............

Reissue...........0.............

18 JUN 93 14 AUG 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATIONADMINISTRATION FT. WORTH,TX 76193-0170

B

REVISIONS

BHT-212-FMS-30

FAA APPROVED

Section

1

1-6. WEIGHT AND CENTER OF GRAVITY

if necessary, to return empty weight CG to

within allowable limits.

Actual weight change shall be determined after kit is installed and ballast readjusted,

Section 2 No change from basic manual.

Section 3 No change from basic manual.

BHT-212-FMS-30

FAA APPROVED

Section 4 No change from basic manual.

2

MANUFACTURER'S DATA

BHT-212-FMS-30

Section 5 5-3. GROSS WEIGHT CENTER OF GRAVITY

5-5-B.

SAMPLE LOADING

PROBLEM A sample loading problem is provided.

Figure 5-1 presents

fuselage station

and

buttock line data to aid In weight and balance computations.

5-5.

COCKPIT AND CABIN

LOADING Refer to table 5-1 for personnel weights and moments.

3

BHT-212-FMS-30

MANUFACTURER'S DATA NOTE Station 0 (reference datum) is located 20 inches (508 millimeters) aft of most forward point of cabin nose.

FUSELAGE STATIONS

__t

_r----

J-l

- J FS13800 r."-i,3

BAGGAGE

>

STANDARDFRONTROW CONFIGURATION FUSELAGE STATIONS °

23

(

4

SEAT COPILOTORPASSENGER

MANUFACTURER'S DATA

BHT-212-FMS-30

Table 5-2.

Pilot and Weight Copilot* (LB) FS 47 100 4700 110 5170 120 5640 130 6110 140 6580 150 7050 160 7520 170 7990 180 8460 190 8930 200 9400 210 9870 220 10340 *Left Forward Seat

Crew and passenger table of moments

Passenger (Forward 4-Man Seat) FS 85.7 8570 9427 10284 11141 11998 12855 13712 14569 15426 16283 17140 17997 18854

Passenger (Aft 5-Man Seat) FS 114.7 11470 12617 13764 14911 16058 17205 18352 19499 20646 21793 22940 24087 25234

Passenger Facing Outboard Fwd Seat Aft Seat FS 139.7 FS 156.8 13970 15680 15367 17248 16764 18816 18161 20384 19558 21952 20955 23520 22352 25088 23749 26656 25146 28224 26543 29792 27940 31360 29337 32928 30734 34496

(TABLE

I.D. 910525)

5

BHT-212-FMS-30

MANUFACTURER'S DATA

SAMPLE LOADING PROBLEM The helicopter Is chartered to transport nine passengers and 180 pounds of baggage on a trip that will require approximately 155 gallons of fuel. The 190-pound pilot will return alone. Determine extreme CG conditions for both trips. OUTBOUND FLIGHT WEIGHT

CG

MOMENT

Empty Weight

5942

857728

+Oil +Pilot

22 * 190

3703 8930

+Passengers, Aft Row (5) +Passengers, Forward Row (4) +Baggage

* 850 * 680 * 180

97495 58276 46980

Basic Operating Weight + Payload

7864

Basic Operating Weight + Payload

7864

1073112

*1409

216030

+Takeoff Fuel (216.8 gallons)

136.5

Takeoff Weight, CG & Moment

9273

Basic Operating Weight + Payload

7864

1073112

+Critical Fuel (72.6 gallons)

* 472

60227

Critical Weight, CG & Moment

8336

Basic Operating Weight + Payload

7864

1073112

* 390

50480

+Landing Fuel (60 gallons) Landing Weight, CG & Moment

8254

139.0

1073112

136.0

136.1

1289142

1133339

1123592

From Gross weight center of gravity chart in Section 1 of basic flight manual, it can be determined that CG will remain within limits for outbound and return flights. (TABLE

6

I.D.

910523)

MANUFACTURER'S DATA

BHT-212-FMS-30

SAMPLE LOADING PROBLEM (Cont) RETURN FLIGHT WEIGHT Empty Weight

.

CG

MOMENT

5942

857728

+Oil +Pilot Basic Operating Weight (No Payload)

22 * 190 6154

3703 8930 870361

+Takeoff Fuel (216.8 gallons)

*1409

216030

Takeoff Weight, CG & Moment and Most Aft CG Basic Operating Weight (No Payload) +Critical Fuel (72.6 gallons)

7653 6154

870361 60227

6626

Basic Operating Weight (No Payload)

6154

Fuel (60 gallons)

* 390

Landing Weight, CG & Moment

1086391

* 472

Critical Weight, CG & Moment

+Landing

143.7

6544

140.4

930588 870361 50480

140.7

920841

(*Information obtained from loading tables) (TABLE

I.D. 910524)

7/8

BHT-212-FMS-32

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

ENGINE NO. 2 GOVERNOR TRIM ACTUATOR TB 212-93-145 CERTIFIED 28 JULY 1994 This supplement shall be attached to applicable Model 212 Flight Manual when the Engine No. 2 Governor Trim Actuator has been installed per TB 212-93-145. Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained In this supplement, consult basic Flight Manual.

Bell Helicopter NOTICE COPYRIGHT COPYRIGHT 1994 ® BELL HELICOPTER INC. 1994 ANDBELLHELICOPTER TEXTRON.

A DIVISION OFTEXTRON CANADA LTD. ALLRIGHTS RESERVED

of Textron Inc. A Subsidiary

POSTOFFICE B0X 482 FORTWORTH, TEXAS 76101

28

JULY

1994

BHT-212-FMS-32 NOTICE PAGE

PROPRIETARYRIGHTSNOTICE Manufacturer's Data portion of this supplement 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.

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron P. O.Box 482 Fort Worth, Texas 76101-0482

NP

BHT-212-FMS-32 LOG OF REVISIONS

Original...........0

............

28 JUL 1994 LOG OF PAGES REVISION

PAGE

NO.

REVISION PAGE

FLIGHT MANUAL

NO. MANUFACTURER'S DATA

Title- NP.............................. 0 A--B .................................. 0 1-2 ...................................0

3-4 ................................... 0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. A

BHT-212-FMS-32

FAA APPROVED

LOG OF APPROVED REVISIONS Original

..........

0............28

JUL 1994

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

FAA APPROVED

BHT-212-FMS-32

Section

1 No change from basic manual.

Section 2 TAKEOFF

BEFORE TAKEOFF Throttles - Full open. Adjust friction. RPM switch -

lear NOTE

Minimum beep (DECR

for 4 to 5 seconds). RPM switch - Minimum trim (-2 for 4 to 5 seconds). greater. ROTOR- Check 95% or or greaterrequired,

Dw

Area -

ROTOR95Check

RPM switch -

Adjust to obtain

matching TORQUE or ITT at 100%

operation and set.

RPM switch matching matching

Check

Adjust to obtain

or ITT, TORQUE or as ITT, as TORQUE

and 100% ROTOR.

Hover power -

Check TORQUE

required to hover at four feet skid height

ROTOR.

Flight instruments -

As collective is increased, it may be necessary to rematch engine torques prior to reaching hover.

FAA APPROVED

BHT-212-FMS-32

Section 3 No change from basic manual.

Section 4 No change from basic manual.

Section 5 No change from basic manual.

2

BHT-212-FMS-32

Section

MANUFACTURER'S DATA

No change from basic manual.

Section7

MANUFACTURER'S

NOTE

INCR/DECR positions

Section 7 is no longer used in flight manual. Section 7 of this supplement

has been designated

SYSTEMSDESCRIPTION.

switch,

located

decrease

on

pilot

collective control panel, is a five position, momentary on type switch.

increase/

ENG RPM by controlling

governors on both simultaneously. -2/+2 positions

RPM RPM SWITCH InTrim RPM

DATA

(trim)

engines

increase/

decrease engine 2 ENG RPM to *provide TORQUE or ITT matching. range Is 2.0 to 2.5% ENG RPM. Engine 2 governor should be at least 95% minimum trim and beep.

3

BHT-212-FMS-32

LDG LT ON

EXT

OFF

RET

IDLE STOP

N

N2

M

SLT

SLT

OFF

RETR

-- DECR-

1

2 212-FMS-32-7-1

Figure 7-1.

4

Engine RPM INCR/DECR Switch

12

MODEL

BHT-212-FMS-33

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

BENDIX/KING RDS 81 WEATHER RADAR 212-899-234 CERTIFIED 7 OCTOBER 1994

This supplement shall be attached to the Bell Helicopter Model 212 flight manual when the Bendix/King

RDS 81 Weather Radar has been

installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter NOTICE COPYRIGHT

BELL HELICOPTER INC 1994 ANDBELLHELICOPTER TEXTRON. A DIVISION OFTEXTRON CANADA LTD ALLRIGHTS RESERVED

TEXAS POSTOFFICE BOX482* FORTWORTH

Inc. of Textron A Subsidiary 76101

7 OCTOBER 1994

FAA APPROVED

BHT-212-FMS-33

NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

BHT-212-FMS-33

LOG OF REVISIONS

Original...........0

..............

07 OCT 94 LOG OF PAGES REVISION NO.

PAGE

3/4 ......................................

FLIGHT MANUAL

Title -

REVISION NO.

PAGE

0

MANUFACTURER'SDATA

NP..............................0

A- B .................................. 0 0 i/ii ....................................... 1-2 ................................... 0

5/6 ......................................

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded

pages. A

BHT-212-FMS-33

FAA APPROVED

LOG OF APPROVED Original ...........

0

.......

07 OCT 94

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH,TX 76193-0170

B

REVISIONS

0

0

FAA APPROVED

BHT-212-FMS-33

GENERAL INFORMATION

The Bendix/King

RDS 81 Weather Radar

mapping.

The weather mode detects and

installation (212-899-834) consists of a digital indicator, combination antenna and receiver/transmitter, wiring, and hardware necessary for installation. The digital indicator is mounted in the instrument

locates various types of storms along the flight path of the helicopter, and gives the pilot a visual indication of storm intensity. After proper evaluation, the pilot can chart his course around the storm areas. The

panel and contains

mapping mode enables the pilot to identify

all controls

necessary

to operate the radar. The combination receiver/transmitter is located in the nose of the helicopter. The weather radar is used for weather detecting and analysis and for ground

coastlines, hilly or mountainous regions, and cities. The weather radar performs only the functions of weather detection and ground mapping and shall not be used, or relied upon for proximity warning or collision avoidance.

i/ii

BHT-212-FMS-33

FAA APPROVED

Section

1-5. 1-5-D.

1

CONFIGURATION WEATHER RADAR GROUND

OPERATION

WARNI RDS

81

weather

weather detection mapping.

Radar system shall not be operated on the ground or in hover when personnel are in the danger area shown in figure 1-1.

system

and ground

It shall not be used for

proximity ground collision avoidance.

1-6. Radar system shall not be operated within 300 feet (91.5 m) of any fueling operation.

radar

performs only functions of warning

or

WEIGHT AND CENTER OF

GRAVITY

Actual weight change shall be determined

Radar shall not be operated on ground anytime a large metallic object is forward of the helicopter

nose, within 65 degrees

of helicopter centerline and at a distance of less than 300 feet (91.5 m).

after kit is installed and ballast readjusted.

BHT-212-FMS-33

FAA APPROVED

iDANGER AREA

Figure 1-1.

Danger area

Section 2 2-1.

INTRODUCTION

Refer to Bendix/King RDS 81/82 Pilot's Guide for operation of weather radar.

Section 3 No change from basic manual. 2

FAA APPROVED

BHT-212-FMS-33

Section 4 No change from basic manual.

3/4

MANUFACTURER'S DATA

BHT-212-FMS-33

Section 5 *

No change from basic manual.

0 0 0 5/6

CERTIFIED 7 OCTOBER 1994

This supplement shall be attached to the Bell Helicopter Model 212 Flight Manual when the TRIMPACK

GPS

NAVIGATOR

kit

has

been

installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

*eI

___,Bell COPYRIGHT NOTICE COPYRIGHT 1995 BELL HELICOPTER INC. ANDBELLHELICOPTER TEXTRON INC.

ADIVISION OFTEXTRON CANADA LTD ALLRIGHTS RESERVED

Helicopteri

al1i

A Subsidiary ol TextronInc rOSTOFFICEBOX482 · FORTWORTH. TEXAS 76101

REISSUE- 24 FEBRUARY 1995

BHT-212-FMS-34

FAA APPROVED NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482

NP

FAA APPROVED

BHT-212-FMS-34 LOG OF REVISIONS

Original...........0 Reissue...........0

.............. ..............

07 OCT 94 24 FEB 95 LOG OF PAGES REVISION NO.

PAGE FLIGHT MANUAL Title -

NP ..............................

1 -2

....

.................

...................................

0

0

MANUFACTURER'S DATA

A-B .................................. 0 .........

REVISION NO.

PAGE

0

3/4 ......................................

0

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded

pages. A

BHT-212-FMS-34

FAA APPROVED LOG OF APPROVED

Original...........0 Reissue...........0

.............. ..............

07 OCT 94 24 FEB 95

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

REVISIONS

BHT-212-FMS-34

FAA APPROVED GENERAL INFORMATION

TRIMPACK NAVIGATOR Global positioning

system (GPS) (212-899-835) consists of the Trimpack unit with integral display.

i/ii

FAA APPROVED

BHT-212-FMS-34

Section

.

1-5.

CONFIGURATION

1-20.

INSTRUMENT

MARKINGS AND PLACARDS 1-5-B.

OPTIONAL EQUIPMENT

GPS NOT APPROVED

FOR NAVIGATION

The Trimpack Navigator Global Positioning

System is not approved for primary navigation.

Section 2 2-1.

INTRODUCTION

For Trimpack GPS Navigator operating procedures, refer to Trimble Navigation

Section 3 3-1.

INTRODUCTION

If GPS navigation system becomes inoperative, resume basic navigation procedures.

TRIMPACK GPS Maintenance guide.

Operation

and

BHT-212-FMS-34

FAA APPROVED

Section 4 No change from basic manual.

2

0

MANUFACTURER'S DATA

*

BHT-212-FMS-34

Section 5 No change from basic manual.

3/4

BHT-212-FMS-35

MODEL

ROTORCRAFT FLIGHT MANUAL SUPPLEMENT

INCREASED WEIGHT ALTITUDE TEMPERATURE LIMIT 212-704-129 AND

212-704-153 CERTIFIED 22 MARCH 1996

This supplement shall be attached to Model 212 Flight Manual when both 212-704-129 Tail Rotor

Install and 212-704-153 Increased Takeoff Horsepower Kits have been installed.

Information contained herein supplements

information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

Bell Helicopter NOTICE COPYRIGHT COPYRIGHT 1996 INC BELL® HELICOPTER ANDBELLHELICOPTER TEXTRON INC A DIVISIONOF TEXTRONCANADA LTD

RESERVED ALLRIGHTS

of Textron Inc A Subsidiary 76101 TEXAS POSTOFFICE BOX482* FORTWORTH.

22 MARCH 1996

BHT-212-FMS-35 NOTICE PAGE

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. 0. Box 482

Fort Worth, Texas 76101-0482 NP

BHT-212-FMS-35 LOG OF REVISIONS Original...........0

..............

22 Mar 96 LOG OF PAGES REVISION NO.

PAGE FLIGHT MANUAL

Title- NP..............................

A-

0

REVISION NO.

PAGE B ..................................

i/ii .......................................

0

1- 16..................................0

NOTE Revised text is indicated by a black vertical line. Insert latest revision superseded pages.

pages; dispose of

A

BHT-212-FMS-35

FAA APPROVED LOG OF APPROVED REVISIONS

Original ...........

0 .......

. 22 Mar 96

APPROVED:

MANAGER

ROTORCRAFTCERTIFICATIONOFFICE FEDERALAVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

B

FAA APPROVED

BHT-212-FMS-35 GENERAL INFORMATION

This supplement

approves

an increase Weight-Altitude-Temperatures

(WAT) Limit

for

takeoff, landing and in-ground-effect maneuvers when the 212-704-129 Tail Rotor Modification is installed in conjunction with the 212-704-153 Increased Takeoff Horsepower Kit (BHT-212-FMS-29). Limitations, procedures and performance data associated with the increased WAT limit are presented for Basic Helicopter plus Winterization Heater.

i/ii

BHT-212-FMS-35

FAA APPROVED

Section 1-5.

1

CONFIGURATION

1-5-A. REQUIREDEQUIPMENT

1-10.

HEIGHT-VELOCITY

The height-velocity limitations are critical in the event of single engine failure during takeoff, landing, or other operation near the surface (figure 1-2). The AVOID area of

The following kits shall be installed prior to taking advantage of the Increased Weight Altitude Temperature Limit supplement BHT-212-FMS-35.

the Height-Velocity diagram defines the combinations of airspeed and height above ground from which a safe single engine landing on a smooth, level, firm surface cannot be assured.

The H-V diagram is valid only when the Tail Rotor Install (212-704-129)

Weight-Altitude-Temperature are not exceeded (figure 1-1).

limitations

Increased Takeoff Horsepower (212704-153)

1-6.

WEIGHT AND CENTER OF

1-13.

POWER PLANT

Refer to Basic FMS-29.

Manual and/or

BHT-212-

GRAVITY Refer to Weight-Altitude-Temperature (WAT) Limitations chart (figure 1-1) for maximum allowable weight for takeoff, landing and IGE hover operation.

1

BHT-212-FMS-35

FAA APPROVED

NOTE: ALLOWABLEGROSSWEIGHTSOBTAINEDFROMTHISCHARTMAY EXCEED CONTINUOUSHOVERCAPABILITYUNDERCERTAINAMBIENTCONDITIONS. REFERTO HOVERCEILINGCHARTSIN SECTION4.

14,000 FOOT DENSITY ALTITUDELIMIT

14000

8000

- 6000

38

Figure 1-1.

2

42

46

50

54

WAT for takeoff, landing and IGE maneuver

KG X 100

FAA APPROVED

BHT-212-FMS-35

450 NOTE: THEHELICOPTER CONFIGURATION SHALLCOMPLYWITHTHEWEIGHTTO BE VALID

300

z

Figure 1-2.

Single engine height-velocity chart

3

BHT-212-FMS-35

FAA APPROVED

Section 2 Refer to Basic Manual and/or BHT-212-FMS-29.

Section 3 No change from basic manual.

4

FAA APPROVED

BHT-212-FMS-35

Section 4 4-1.

INTRODUCTION

The improved performance

4-7. data contained

in this supplement is applicable for HD altitudes up to 12,000 feet. Data for HD altitudes 12,000 to 14,000 feet is the same

as Basic Manual and/or BHT-212-FMS-29.

CLIMB AND DESCENT

TWIN ENGINETAKEOFF CLIMBOUTSPEED

4-7-A.

Twin engine takeoff climbout speed (VTOCS)

is that indicated airspeed which will allow takeoff distance over a 50 foot (15.2 meter)

4-5.

obstacle to be realized and will comply with HV restrictions to allow a safe landing

HOVERCEILING

4-5-A.

in case of an engine failure (figure 4-4).

4-7-B. TWIN ENGINE RATE OF CLIMB CLIMB

IGE

Figure 4-1 presents IGE IGE hover hover performance performance as allowable GW for conditions

of Hp and

For twin engine rate of climb refer to BHT-

212-FMS-29

OAT for basic helicopter.

4-9.

4-5-B. OGE

LANDING DISTANCE

Single engine landing distance over 50 foot (15.2 meters) obstacle is shown in figure 4-5 as a function

Figure 4-2 presents OGE hover performance as allowable GW for conditions helicopter

of OAT, Hp and

GW.

of Hp and OAT for basic

and winterization

heater.

4-6. TAKEOFF DISTANCE Takeoff distance required to clear a 50 foot (15.2 meter) obstacle is presented in figure 4-3 as a function of OAT, Hp and GW.

5

BHT-212-FMS-35

FAA APPROVED HOVER CEILING IN GROUNDEFFECT

POWER:SEE NOTEBELOW ENGINERPM100%(N2) GENERATOR150 AMPS EACH

14,000

K HT FT HEATERON OR OFF HEATERON OROFF

FT Ho LIMIT

NOTE: THESE IGE HOVER CEILINGS

-HOVERED

IGE

POWER

11,200 LB

0

10 20 30 40 50 60

8000 3600

Figure 4-1.

6

9000

10000 11000 12000 LB

4000 4400 4800 5200 KG GROSS WEIGHT

Hover ceiling in ground effect chart (sheet 1 of 2)

AT

THE

FAA APPROVED

BHT-212-FMS-35 HOVER CEILING IN GROUNDEFFECT

POWER:SEENOTE BELOW ENGINERPM100%(N2) GENERATOR150 AMPSEACH 0° TO--54°C

14,000

SKID HEIGHT4 FT HEATERONOR OFF WINTERIZATIONKIT HTRON OR OFF

FT HD LIMIT

NOTE: THESE IGE HOVER CEILINGS ARE BASED ON DENSITY ALTITUDE LIMITS FOR TAKEOFF AND LANDING. THIS HELICOPTER CAN BE HOVERED IGE AT THE INDICATED GROSS WEIGHTS WITH LESS THAN TAKEOFF POWER

11,200LB (5080KG)

-60-50-40-30-20-10 OAT - °C

Figure 4-1.

0

8000 I

3600

9000

10000 11000 12000 LB

I

4000 4400 4800 5200 KG GROSS WEIGHT

Hover ceiling in ground effect chart (sheet 2 of 2)

7

FAA APPROVED

BHT-212-FMS-35 HOVER CEILING OUTOF GROUNDEFFECT CALMWIND TAKEOFFPOWER ENG RPM100%(N2) GENERATOR150AMPS EACH

SKID HEIGHT60 FT HEATEROFF TO0° 52°C

14,000 FT HD LIMIT MAXIMUMGW LIMIT

10 20 0

40 50 60

8000

OAT °C - 40 50 60 10 OAT 20 30 -

I 8000 3600

Figure 4-2.

8

9000

10000 11000 12000 LB

I I11000 12000 LB 9000 10000 4000 4400 4800 5200 KG GROSS WEIGHT

Hover ceiling out of ground effect chart (sheet 1 of 6)

BHT-212-FMS-35

FAA APPROVED

t

HOVER CEILING OUTOF GROUNDEFFECT SKID HEIGHT60 FT HEATEROFF o0TO --54°C

TAKEOFFPOWER ENGRPM100%(N2) GENERATOR150AMPS EACH

11,200LB (5080KG)

-60-50-40-30-20-10 OAT - °C

0

8000 I 3600

9000 10000 11000 12000 LB I I I I 4000 4400 4800 5200 KG GROSS WEIGHT

9

BHT-212-FMS-35

FAA APPROVED HOVER CEILING OUTOF GROUNDEFFECT

TAKEOFFPOWER ENGRPM100% (N2) GENERATOR150 AMPSEACH

CALMWIND

SKID HEIGHT60 FT HEATERON 00TO --54°C

14,000 FT HD LIMIT

Figure 4-2.

10

Hover ceiling out of ground effect chart (sheet 3 of 6)

BHT-212-FMS-35

FAA APPROVED

TAKEOFFPOWER ENGRPM100% (N2) GENERATOR150 AMPSEACH

HOVER CEILING OUTOF GROUNDEFFECT CALMWIND

SKID HEIGHT60 FT HEATERON TO 20°C

14,000 FT HD LIMIT MAXIMUMGW LIMIT

TORQUE LIMIT

11,200LB (5080KG)

0

10 20 30 40 50 60 OAT - °C

Figure 4-2.

8000 I 3600

9000 10000 11000 12000 LB I I 4000 4400 4800 5200 KG GROSS WEIGHT

Hover ceiling out of ground effect chart (sheet 4 of 6)

11

BHT-212-FMS-35

FAA APPROVED HOVER CEILING OUTOF GROUNDEFFECT

TAKEOFFPOWER ENGRPM100%/(N2)

CALMWIND

SKID HEIGHT60 FT WINTERIZATION ON

11,200LB (5080 KG) -

GROSS WEIGHT Figure 4-2.

12

Hover ceiling out of ground effect chart (sheet 5 of 6)

FAA APPROVED

BHT-212-FMS-35 HOVER CEILING OUT OF GROUNDEFFECT CALM WIND

TAKEOFFPOWER ENG RPM100%(N2) GENERATOR150AMPS EACH

SKID HEIGHT60 FT WINTERIZATION ON 0 TO 20°C

14,000 FT HD LIMIT MAXIMUMGW LIMIT

TORQUELIMIT

11,200LB (5080KG)

0

10 20 30 40 50 OAT - °C

60

8000 3600

Figure 4-2.

9000 10000 11000 12000 LB I I I 4000 4400 4800 5200 KG GROSS WEIGHT

Hover ceiling out of ground effect chart (sheet 6 of 6)

13

BHT-212-FMS-35

FAA APPROVED

TAKEOFF DISTANCE OVER50 FT (15.2m) OBSTACLE HOVER POWER + 15% TORQUE ENG RPM 100% (N2) GENERATOR 150 AMPS

INITIATED FROM 4 FT SKID HEIGHT HEATERON OR OFF WINTERIZATION KIT HTR ON OR OFF

REFERTO VTOCS CHART FOR TAKEOFF SPEED

MAXIMUM 14,000FT HD LIMIT

HD

FOR TAKEOFF

HOT DAY TEMPERATURE LIMIT

-60-40-20

0 20 40 60

OAT -

C

200

400

600

800

(61)

1000

(122)

1200

(183)

(244)

(305)

(366)

TAKEOFF DISTANCE

Figure 4-3.

14

- FT (M)

Takeoff distance over 50 foot (15.2 meter) obstacle

FAA APPROVED

BHT-212-FMS-35

GW- LB (KG) HD - FT

7000 (3175)

8000 (3629)

9000 (4082)

10,000 (4536)

10,500 (4763)

11,000 (4989)

11,200 (5080)

0

30

30

30

35

38

40

40

1000

30

30

30

35

38

40

40

2000

30

30

30

35

38

40

40

3000

30

30

30

36

38

40

42

4000

30

30

32

36

40

42

42

5000

30

30

32

38

40

42

42

6000

30

30

34

38

42

42

44

7000

30

30

34

40

42

44

44

8000

30

30

34

40

42

9000

30

30

36

42

44

10,000

30

32

36

42

11,000

30

32

38

12,000

30

34

38

13,000

30

34

14,000

30

36

0^^^b~ ~Figure

4-4.

Twin engine takeoff climbout speed

15

BHT-212-FMS-35

FAA APPROVED

SINGLE ENGINE LANDING DISTANCE OVER 50 FT (15.2 M) OBSTACLE POWERAS REQUIRED ENGRPM97%(N2) GENERATOR150 AMPS

ViAS40 KNOTS RATEOF DESCENT500 FPM HARDSURFACEDRUNWAY INOPERATIVEENGINESECURED

LANDING DISTANCE - M

60

-60 -40

0

-20

OAT -

Figure 4-5.

16

20

40

60

DEGREESCELCIUS

20

90

120 150 180 210 240 270 300

400

600

800

LANDING DISTANCE - FT

Single engine landing distance over 50 foot (15.2 meter) obstacle

1000