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ROTORCRAFT FLIGHT MANUAL

SUPPLEMENT

INCREASED TAKEOFF HORSEPOWER212-704-153

CERTIFIED16 DECEMBER 1991

This supplement shall be attached to the Bell Helicopter 212 Flight Manual when the Increased Takeoff Horsepower kit has been installed.

Information contained herein supplements information in the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, refer to the basic Flight Manual.

BHT-212-FMS-29

14 AUGUST 1995 REVISION 1 — 20 JULY 2009

COPYRIGHT NOTICECOPYRIGHT 2009BELL ® HELICOPTER TEXTRON INC.AND BELL HELICOPTER TEXTRONCANADA LTD.

ALL RIGHTS RESERVED

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

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———Rev. 1—20 JUL 2009

BHT-212-FMS-29

These data are proprietary to Bell Helicopter Textron Inc. Disclosure,reproduction, or use of these data for any purpose other than helicopteroperation or maintenance is forbidden without prior written authorization from Bell Helicopter Textron Inc.

PROPRIETARY RIGHTS NOTICE

These commodities, technology, or software were exported from theUnited States in accordance with the Export Administration Regulations(EAR). Diversion contrary to U.S. law prohibited. The data contained inthis manual are classified as ECCN EAR99.

DESTINATION CONTROL STATEMENT

Original ..................... 0...................... 16 DEC 91Reissue ..................... 0...................... 22 OCT 92

Reissue......................0 ..................... 14 AUG 95Revision.....................1 ...................... 20 JUL 09

20 JUL 2009—Rev. 1———A/B

BHT-212-FMS-29

NOTE

Revised text is indicated by a black vertical line. A revised page with only a vertical line next to the page number indicates that text has shifted or that non-technical correction(s) were made

on that page. Insert latest revision pages; dispose of superseded pages.

LOG OF REVISIONS

LOG OF PAGES

REVISION REVISIONNO. NO.PAGE PAGE

FLIGHT MANUAL

Title.............................................................1NP ...............................................................1A/B..............................................................1C/D..............................................................11 ..................................................................12 – 34..........................................................0

MANUFACTURER’S DATA

35/36........................................................... 0

BHT-212-FMS-29

20 JUL 2009—Rev. 1———C/D

LOG OF FAA/ODA* APPROVED REVISIONS

Original ..................... 0...................... 16 DEC 91Reissue ..................... 0...................... 22 OCT 92

Reissue......................0 ..................... 14 AUG 95Revision.................... 1* ..................... 20 JUL 09

WAYNE BARBINI BHTI ODA LEAD ADMINISTRATOR ODA-710621-SW P.O. BOX 482 FT. WORTH, TX 76101

ORGANIZATION DESIGNATION AUTHORIZATION (ODA)

APPROVED DATE

20 JULY 2009

FAA APPROVED BHT-212-FMS-29

20 JUL 2009—Rev. 1———1ECCN EAR99

Section 1LIMITATIONS

11-13. POWER PLANT

1-13-D. ENGINE TORQUE

NOTE

For normal twin engine operation,maximum permissible ENG TORQUEdifferential of 4% is not applicablewith engine No. 2 Governor TrimSwitch installed.

1-13-D-1. PT6T-3B

SINGLE ENGINE OPERATION ENGINE SCALE

1-13-D-2. PT6T-3

SINGLE ENGINE OPERATION ENGINE SCALE

1-14. TRANSMISSION

1-14-C. TRANSMISSION TORQUE

1-14-C-1. PT6T-3B

TWIN ENGINE OPERATION TRANSMISSIONSCALE (Δ)

1-14-C-2. PT6T-3

TWIN ENGINE OPERATION TRANSMISSIONSCALE (Δ)

30-Minute Power Range 63.9 to 79.4%

Maximum 79.4%

30-Minute Power Range 63.9 to 71.8%

Maximum 71.8%

Maximum ContinuousLimit

87.5%

Takeoff Power Range(5 minute)

87.5 to 104.3%

Maximum 104.3%

Maximum ContinuousLimit

87.5%

Takeoff Power Range(5 minute)

87.5 to 104.3%

Maximum 104.3%

BHT-212-FMS-29

INSTRUMENT MARKINGS

DUAL TORQUE INDICATORPT6T 3

TRANSMISSION (TWINENGINE OPERATION)

0 to 87.5%

87.5 to 104.3%

104.3%

ENGINE (SINGLE ENGINE

OPERATION)

63.9 to 71.8%

71.8%

1

I

DUAL TORQUE INDICATORPT6T 3B

TRANSMISSION (TWINENGINE OPERATION)

0 to 87.5%

87.5% to 104.3%

104.3%

ENGINE (SINGLEENGINE OPERATION)

63.9 to 79.4%

I

I

I

I

I

1

79.4% I

FAA APPROVED

212-FMS29-1

Figure 1-1. Instrument markings

I

I

2

.-+

_U)

E

EE

a00

G)"'

FAA APPROVED

Section 2NORMAL PROCEDURES

2-7. BEFORE TAKEOFF 2-8. TAKEOFF

Throttles - Full open. Adjust friction.

RPM switch - Minimum beep (DECR for 4to 5 seconds).

RPM switch - Minimum trim (-2 for 4 to 5seconds).

ROTOR - Check 95% or greater.

RPM switch - Adjust to obtain matchingTORQUE or ITT at 100% ROTOR.

Flight instruments - Check operation andset.

Section 3

Area - Clear.

NOTE

BHT-212-FMS-29

As collective is increased, it maybe necessary to rematch enginetorques prior to reaching hover.

RPM switch - Adjust to obtain matchingTORQUE or ITT, as required, and 100%ROTOR.

Hover power - Check TORQUE requiredto hover at four feet skid height

EMERGENCY/MALFUNCTION PROCEDURES

No change from basic manual.

3

911

..,,

,.,

.911 91

1

3'N

z

300

a-.

000R')

BHT-212-FMS-29

Section 4AP 0

4-1. INTRODUCTION

Performance data presented herein arederived from engine manufacturer'sspecification power for engine lessinstallation losses when used withIncreased Takeoff Horsepowermodification. These data are applicable tobasic helicopter without any optional

FAA APPROVED

equipment which would appreciably affectlift, drag, or power available (Figure 4-1and 4-2).

Figures 4-3 through 4-6 presentperformance data for winterization heater,external cargo, and amphibiousoperations.

4

00,

FAA APPROVED

HOVER CEILINGOUT OF GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH

14,000 FT. DEN. ALT. LIMIT

BHT 212-FMS-29

SKID HEIGHT 60 FEETHEATER OFF0° TO 52°C

MAXIMUM GRO SSWEIGHT LIMIT

O

OAT - °C

O° HOT DAYLIMI T O

OO

°O° 1 \

30

1 QD ..

1O°0

D

1

so

I \0o° I \

Y \

PJ°o

oi1 L

0 10 20 30 40 50OAT - O C

8r-T35

I

9 10

40 45GROSS WEIGHT

Figure 4-1. Hover ceiling chart (sheet 1 of 4)

11 12 LB X 1000

50 KG x 100212-FMS29-4-1-1

5

?pp

L!)

BHT-212-FMS-29




8

MAXIMUM GROSS

0O0WEIGHT LIMIT

OAT - °C

00

00O0

0000

00O

000ti

Q

00

0 10 20 30 40 50 9 10

FAA APPROVED

SKID HEIGHT 60 FEETHEATER ON0° TO 20°C

11 12 LB X 1000

35 40 45 50 KG x 100GROSS WEIGHT 212-FMS29-4-1-2


6

000

00,

FAA APPROVED




BHT 212-FMS-29

SKID HEIGHT 60 FEETHEATER OFF

00 TO -54OC

MA XIMUM GR OSSco, WE IGHT LIMIT

Oo° `so OAT - -C

00

o°0 7-Z0o

K Vo°o

iJ

JI

I I X Av'

-60 -50 -40 -30 -20 -10 0

OAT - OC

9 10 11 12 LB X 1000S

r'-'35 40 45 50 KG x 100

GROSS WEIGHT 212-FMS29-4-1-3


7

8°°0

o°O

o°°

200

000

BHT 212-FMS-29 FAA APPROVED




SKID HEIGHT 60 FEETHEATER ON

00 TO -54OC

Op MA XIMU M GR OSSO WEI GHT LIMIT

OAT-OC

Op0 Q

co

pOo

-5 0

wry,

XO -71OpO

OJvOo QJ 00p

tiQ p0

-60 -50 -40 -30 -20 -10 0

OAT - OC9 10 11 12 LB X 1000

35 40 45 50 KG x 100GROSS WEIGHT 212-FMS29-4-1-4


8

!I/

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

ono

0

(off so L ;aays) gwll0 so ele.l aulBue ulm.L -Z-y aanBlj

L-Z-t,-6ZSW:I-Z LZ NIW113 - 8WIIO 30 31VEI

009£ OOZE 0082 OOtiZ OOOZ 009L OOZL m- OOb

S mImmwMMMmMMMMMMMMMM nimmummommommoommom NIMEMENEENNEEMEMEME mimml!mmmmmmmmmmmmm

NINE lmMMMMMMMMMMMM aimmmmm MEMNON

0 11 Ill 161, a E MEMEME

0002

OOOb

0009

0008

000,0L

No IMEMEMMEMEMEME 000'Z L

No NERNMEMMEMEMEM 000'ti L

000'9 L

E 1001,11 000"8 L

OOO,OZ

'81 OOOL 1HO13M SSOUD

330 Ii31V3H S1ONH 991t13A

NlW/ld OOZ 3SV3U33a 111M 8W113 30 31VU `N3dO SU00a 11V HIM

SW113 :1O 31VU 3NIJN3 NIMl

H3V3 SdWV 09L H0iVH3N3J %OO L WdU 3NION3

W3M0d 3303)lVl

6Z-SW:I-Z L Z-1H8 a3A0Uddd VV:f

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

DnT 212-FMS-29 FAA APPROVED

TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF

CLIMB WILL DECREASE 200 FT/MIN

TAKEOFF POWER VCAL 55 KNOTSENGINE RPM 100% HEATER ONGENERATOR 150 AMPS EACH

GROSS WEIGHT 7000 LB.

20,000

18,000

16,000

14,000

12,000

10,000

8000

6000

4000

2000

HEATER ON

0 400 800 1200 1600 2000 2400 2800 3200 3600

RATE OF CLIMB - FT/MIN 212-FMS29-4-2-2

Figure 4-2. Twin engine rate of climb (sheet 2 of 10)

10

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

VA

w,,%

/

(,)

FAA APPROVED


20,000

I

18,000

16,000

14,000WWLL

12,000

10,000

8000

6000

4000

2000

D0 400



BHT 212-FMS-29

VCAL 55 KNOTSHEATER OFF


04

OAT,LIMIT

-L 1

UP

-30

0

19

800 1200 1600 2000 2400 2800 3200

RATE OF CLIMB - FT/MIN


212-FMS29-4-2-3

11

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

1333

000

00

BHT 212-FMS-29





20,000

FAA APPROVED

VCAL 55 KNOTSHEATER ON

OAT - aC --

18,000

16,000

14,000

12,000

10,000

8000

6000

4000

2000

0

OATF LIMIT

HEATER ON1 I_

0 400 800 1200 1600 2000 2400 2800 3200

RATE OF CLIMB - FT/MIN212-FMS29-4-2-4


12

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

iris

mm

-

FAA APPROVED BHT-212-FMS-29




20,000

18,000

16,000

14,000

12,000

10,000

8000

6000

4000

2000

0


0

OATLIMIT

-30

OR

OAT oC


0 400 800 1200 1600 2000 2400 2800 3200



212-FMS29-4-2-5

ix

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

cr.

BHT 212-FMS-29


CLUB WILL DECREASE 200 FT/MIN


GROSS WEIGHT 9000 I.B.

20,000

18,000

16,000

14,000

12,000

10,000

8000

6000

4000

2000

0

OAT - OC

FAA APPROVED


-L--N

-- ",\ N" I

i

OATF LIMIT

HEATER ON

0 400 800 1200 1600 2000 2400 2800 3200



212-FMS29-4-2-6

14

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

X91

1333

FAA APPROVED


20,000

18,000

16,000

14,000

12,000

10,000

8000

6000

4000



BHT 212-FMS-29


GROSS WEIGHT 10,000 I.B.

MEMMIN

0.10011k,,,"0,,,,,",I

0

BREEN

MOLE19,

OAT - OC

ONE Wlam. MINE

MMMMMEMMISM

mmmmmmmlismmmmmmmm Ism

400 800 1200 1600 2000 2400


2000


2800 3200

212-FMS29-4-2-7

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

1333

BHT 212-FMS-29




GROSS WEIGHT 10,000 I.B.

20,000

18,000OAT - O C

-30

16,000

14,000

12,000

10,000

8000

6000

4000

2000

0

i

HEATER ON

0

0 400

FAA APPROVED


800 1200 1600 2000 2400 2800 3200



212-FMS29-4-2-8

16

6

d-Z

OOZE 008Z 0091 008

000'0

000'9

000'8

NIW/13 OOZ 111M

NIMI

L FAA APPROVED




GROSS WEIGHT 11,200

16,000

18,000

14,000

12,000

6000

4000

212-FMS-29


400 800 1200 1600 2000 2400

RATE OF CLIMB FT/MIN

Figure 4-2. Twin engine rate of climb (sheet of 10)

2800 3200

PR

ES

SU

RE

ALT

ITU

DE

- F

EE

T

0O O O

co O O O

r.o.

Loi03

O O O

.om

.mm

. mm

mE

ME

MM

MM

MIM

V

OD O 0 N O O O O w N O O

I w 0

%E%/E/MEMME

mmmmmmmmmmm

m .. EM

.ME

.ER

M 10E

lArr

'Arim

,pi

llM

E

M%

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n

m r

D m ;K

m Z

00

TCl)

C2Z m Z

0

PR

ES

SU

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ALT

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DE

FE

ET

BHT 212-FMS-29




GROSS WEIGHT 11,200 LB.

20,000

18,000

16,000

14,000

12,000

10,000

8000

6000

4000.

2000

00

HEATER ON

400 800 1200 1600 2000 2400



-40

FAA APPROVED


2800 3200

212-FMS29-4-2-10

18

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

0

1333

0

FAA APPROVED



20,000

18,000

16,000

14,000

I-W

LL 12,0001

W

J" 10,000aWCC

8000WCra

6000

4000-

2000

0L0 400

WINTERIZATION HEATER


CLIMB WILL DECREASE 200 FT/MIN.

800

OAT .LIMIT

1200 1600 2000 2400


BHT-212-FMS-29

55 KCASWINTERIZATION HEATER ON

2800

OAT - °C

-20

3200 3600

212-FMS29-4-3-1

Figure 4-3. Twin engine rate of climb with winterization heater (sheet 1 of 5)

19

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

dam

1333

BHT 212-FMS-29






20,000

18,000

16,000

14,000

12,000

10,000

8000

6000

4000

2000

0

0

FAA APPROVED


-50 OAT - °C

-40

)AT-30

AT -201 N

O

O

O

DO

400 800 1200 1600 2000 2400 2800 3200



20

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

0

133

FAA APPROVED







20,000

18,000

16,000

14,000

12,000

10,000

8000

6000

4000

2000

0

0 400

COAT -

BHT 212-FMS-29


\ NNI I I IN,\\ '-

800 1200 1600 2000 2400 2800 3200

212-FMS29-4-3-3


21

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

zn0,

1333

BHT 212-FMS-29






1

-50

-40

0

OAT

FAA APPROVED


- °C

0 400 800 1200 1600 2000 2400 2800 3200



20,000

18,000

16,000

14,000

12,000

10,000

8000

6000

4000

2000

22

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

CA

)

C71

FAA APPROVED






HWWLL

20,000

18,000

16,000

14,000

-50

-40

-30 OAT -

12,000

10,000

8000

6000

4000

O ``

t

2000

0

0 400 800

BHT 212-FMS-29


1200 1600 2000 2400 2800 3200



23

0

070

009

BHT 212-FMS-29




V14,000 FT. DEN. ALT. LIMIT

8

OAT - °C

00O M AXI MUM GRO SS,gyp' , I W EIG HT LI MIT

00O

O

X00

p0

20

O

00X0

POOO

00Oi

0 10 20 30 40 50OAT - °C

9 10

FAA APPROVED

SKID HEIGHT 60 FEETWINTERIZATION HEATER ON

0° TO 20°C

11 12 LB x 1000

35 40 45 50 KG x 100GROSS WEIGHT

212-FMS29-4-4-1

Figure 4-4. Hover ceiling with winterization heater (sheet 1 of 2)

24

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

c 00

BHT 212-FMS-29

EXTERNAL CARGO



20,000

18,000

16,000

14,000 t12,000

10,000

8000

6000

4000

FAA APPROVED


GROSS WEIGHT 10,000 TO 11,200 LB.

OAT - °C

O

2000

L(OAT

0

LIMI T)

10,000 10,200 10,400 10,600 10,800 11,000 11,200 LB

4600 4700 4800 4900 5000 5100 KGGROSS WEIGHT

Figure 4-5. External cargo (sheet 1 of 6)

212-FMS29-4-5-1

26

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

c -I_

000

FAA APPROVED

EXTERNAL CARGO



20,000

18,000

16,000

14,000

12,000

10,000

8000

6000

4000

2000

0

BHT 212-FMS-29


GROSS WEIGHT UP TO 10,000 LB.

* C

5

OA

0

T -

(OAT LIMI T) 20\ X

-

--4 0-30-

2 0-

(OAT LIMIT) 30o

0OO

O

(OA T LIM IT) 40

QFOR OVER

GW10 000 LBo .,

SEEEXPANDED

CHART

(OA T LIM IT) 50

6000 7000 8000

2500

9000 10,000 11,200 LB

3000 3500 4000 4500 5000 KGGROSS WEIGHT


212-FMS29-4-5-2

27

g-ti

DPI

008'O 009-O 000'O

000,0

000`9

000,8L

NO 133:109

212-FMS-29

EXTERNAL CARGO


18,000

16,000

14,000

12,000

8000

6000

4000

2000


10,000 10,200 10,400 10.600 10,800 11,000 11,200 LB

4600 4700 4800 4900 5000 5100 KGGROSS WEIGHT

Figure 4-5. External cargo (sheet 3 of

FAA APPROVED


GROSS WEIGHT 10,000 TO 11,200 LB.

B

m x

a) O V O 0

0 N O O 0 O O 0 0 0 co O O O O FO

ON

) 0

PR

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P,00

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mom

mm

mm

mam

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ME

ME

ME

ME

ME

MIN

ME

MM

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EM

MM

ME

ME

ME

ME

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PR

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FE

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FAA APPROVED

EXTERNAL CARGO



20,000

18,000

-50

16,000

14,000

12,000

10,000

8000

6000

4000

2000

0

(OAT LIMI

6000 7000

BHT 212-FMS-29


GROSS WEIGHT UP TO 10,000 LB.

-40

OAT-°C

-30

-20

2141 <I-FOR OVER

10,000 LB. GWSEE

EXPANDEDCHART

8000 9000 10,000 11,200 LB

2500 3000 3500 4000 4500 5000 KGGROSS WEIGHT


212-FMS29-4-5-4

29

X00

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

coo

BHT-212-FMS-29

EXTERNAL CARGO

HOVER CEILINGIN GROUND EFFECT


20,000

18,000

16,000(OAT LI MIT) 20

14,000

12,000

10,000

8000

6000

(OAT LI MIT)

0

=2

30

(OAT LIMIT) 40

4000

2000

0

(OAT LIMIT 50)

6000 7000 8000 9000 10,000

-' -'2500

11,200 LB

3000 3500 4000 4500 5000 KGGROSS WEIGHT


FAA APPROVED


0

212-FMS29-4-5-5

30

0 0 0 0

PR

ES

SU

RE

ALT

ITU

DE

FE

ET

p`'

0 0

FAA APPROVED

EXTERNAL CARGO

HOVER CEILINGIN GROUND EFFECT


20,000 °OAT

18,000

16,000

14,000

12,000

10,000

8000

6000

4000

2000

0

(OAT LI

6000

MIT)

7000 8000

-40

0

9000 10,000 11,200 LB

2500 3000 3500 4000 4500 5000 KG

GROSS WEIGHT


BHT 212-FMS-29


212-FMS29-4-5-6

31

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MANUFACTURER'S DATA

Section 5WEIGHT AND BALANCE

No change from basic manual.

SectionM AD

1-1. RPM SWITCH

RPM switch, located on pilot collectivecontrol panel, is a five position,momentary on type switch.

INCR/DECK positions increase/decreaseENG RPM (NO by controlling governors onboth engines simultaneously.

-242 positions (trim) increase/decreaseengine 2 ENG RPM (NO to provideTORQUE or ITT matching. Trim range is2.0 to 2.5% ENG RPM (NO. Engine 2governor should be at least 95% minimumtrim and beep.

021

BHT-212-FMS-29

DECR

Figure 1-1. Pilot collective control panel

35/36

Documents

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