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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 Insert latest revision pages; dispose of superseded pages.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
HOVER CEILINGOUT OF GROUND EFFECT
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
14,000 FT. DEN. ALT. LIMIT
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
Figure 4-1. Hover ceiling chart (sheet 2 of 4)
6
000
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 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
Figure 4-1. Hover ceiling chart (sheet 3 of 4)
7
8°°0
o°O
o°°
200
000
BHT 212-FMS-29 FAA APPROVED
HOVER CEILINGOUT OF GROUND EFFECT
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
14,000 FT. DEN. ALT. LIMIT
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
Figure 4-1. Hover ceiling chart (sheet 4 of 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
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
20,000
I
18,000
16,000
14,000WWLL
12,000
10,000
8000
6000
4000
2000
D0 400
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN
BHT 212-FMS-29
VCAL 55 KNOTSHEATER OFF
GROSS WEIGHT 8000 LB.
04
OAT,LIMIT
-L 1
UP
-30
0
19
800 1200 1600 2000 2400 2800 3200
RATE OF CLIMB - FT/MIN
Figure 4-2. Twin engine rate of climb (sheet 3 of 10)
212-FMS29-4-2-3
11
PR
ES
SU
RE
ALT
ITU
DE
FE
ET
1333
000
00
BHT 212-FMS-29
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
GROSS WEIGHT 8000 LB.
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
Figure 4-2. Twin engine rate of climb (sheet 4 of 10)
12
PR
ES
SU
RE
ALT
ITU
DE
FE
ET
iris
mm
-
FAA APPROVED BHT-212-FMS-29
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
20,000
18,000
16,000
14,000
12,000
10,000
8000
6000
4000
2000
0
GROSS WEIGHT 9000 LB.
0
OATLIMIT
-30
OR
OAT oC
VCAL 55 KNOTSHEATER OFF
0 400 800 1200 1600 2000 2400 2800 3200
RATE OF CLIMB - FT/MIN
Figure 4-2. Twin engine rate of climb (sheet 5 of 10)
212-FMS29-4-2-5
ix
PR
ES
SU
RE
ALT
ITU
DE
FE
ET
cr.
BHT 212-FMS-29
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLUB WILL DECREASE 200 FT/MIN
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
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
VCAL 55 KNOTSHEATER ON
-L--N
-- ",\ N" I
i
OATF LIMIT
HEATER ON
0 400 800 1200 1600 2000 2400 2800 3200
RATE OF CLIMB - FT/MIN
Figure 4-2. Twin engine rate of climb (sheet 6 of 10)
212-FMS29-4-2-6
14
PR
ES
SU
RE
ALT
ITU
DE
FE
ET
X91
1333
FAA APPROVED
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
20,000
18,000
16,000
14,000
12,000
10,000
8000
6000
4000
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN
BHT 212-FMS-29
VCAL 55 KNOTSHEATER OFF
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
RATE OF CLIMB - FT/MIN
2000
Figure 4-2. Twin engine rate of climb (sheet 7 of 10)
2800 3200
212-FMS29-4-2-7
PR
ES
SU
RE
ALT
ITU
DE
FE
ET
1333
BHT 212-FMS-29
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
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
VCAL 55 KNOTSHEATER ON
800 1200 1600 2000 2400 2800 3200
RATE OF CLIMB - FT/MIN
Figure 4-2. Twin engine rate of climb (sheet 8 of 10)
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
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
GROSS WEIGHT 11,200
16,000
18,000
14,000
12,000
6000
4000
212-FMS-29
VCAL 55 KNOTSHEATER OFF
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%
7pej
vlA
, I AP
IA J
,A
M I,I
21P
AIvo
ld"AA
0
n
m r
D m ;K
m Z
00
TCl)
C2Z m Z
0
PR
ES
SU
RE
ALT
ITU
DE
FE
ET
BHT 212-FMS-29
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
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
RATE OF CLIMB - FT/MIN
Figure 4-2. Twin engine rate of climb (sheet 10 of 10)
-40
FAA APPROVED
VCAL 55 KNOTSHEATER ON
2800 3200
212-FMS29-4-2-10
18
PR
ES
SU
RE
ALT
ITU
DE
FE
ET
0
1333
0
FAA APPROVED
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
GROSS WEIGHT 7000 LB.
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
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN.
800
OAT .LIMIT
1200 1600 2000 2400
RATE OF CLIMB - FT/MIN
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
WINTERIZATION HEATER
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN.
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
GROSS WEIGHT 8000 LB.
20,000
18,000
16,000
14,000
12,000
10,000
8000
6000
4000
2000
0
0
FAA APPROVED
55 KCASWINTERIZATION HEATER ON
-50 OAT - °C
-40
)AT-30
AT -201 N
O
O
O
DO
400 800 1200 1600 2000 2400 2800 3200
RATE OF CLIMB - FT/MIN 212-FMS29-4-3-2
Figure 4-3. Twin engine rate of climb with winterization heater (sheet 2 of 5)
20
PR
ES
SU
RE
ALT
ITU
DE
FE
ET
0
133
FAA APPROVED
WINTERIZATION HEATER
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN.
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
GROSS WEIGHT 9000 LB.
RATE OF CLIMB - FT/MIN
20,000
18,000
16,000
14,000
12,000
10,000
8000
6000
4000
2000
0
0 400
COAT -
BHT 212-FMS-29
55 KCASWINTERIZATION HEATER ON
\ NNI I I IN,\\ '-
800 1200 1600 2000 2400 2800 3200
212-FMS29-4-3-3
Figure 4-3. Twin engine rate of climb with winterization heater (sheet 3 of 5)
21
PR
ES
SU
RE
ALT
ITU
DE
FE
ET
zn0,
1333
BHT 212-FMS-29
WINTERIZATION HEATER
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN.
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
GROSS WEIGHT 10,000 LB.
1
-50
-40
0
OAT
FAA APPROVED
55 KCASWINTERIZATION HEATER ON
- °C
0 400 800 1200 1600 2000 2400 2800 3200
RATE OF CLIMB - FT/MIN 212-FMS29-4-3-4
Figure 4-3. Twin engine rate of climb with winterization heater (sheet 4 of 5)
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
WINTERIZATION HEATER
TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN, RATE OF
CLIMB WILL DECREASE 200 FT/MIN.
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
GROSS WEIGHT 11,200 LB.
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
55 KCASWINTERIZATION HEATER ON
1200 1600 2000 2400 2800 3200
RATE OF CLIMB - FT/MIN 212-FMS29-4-3-5
Figure 4-3. Twin engine rate of climb with winterization heater (sheet 5 of 5)
23
0
070
009
BHT 212-FMS-29
WINTERIZATION HEATER
HOVER CEILINGOUT OF GROUND EFFECT
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
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
HOVER CEILINGOUT OF GROUND EFFECT
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
20,000
18,000
16,000
14,000 t12,000
10,000
8000
6000
4000
FAA APPROVED
SKID HEIGHT 60 FEETHEATER OFF
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
HOVER CEILINGOUT OF GROUND EFFECT
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
20,000
18,000
16,000
14,000
12,000
10,000
8000
6000
4000
2000
0
BHT 212-FMS-29
SKID HEIGHT 60 FEETHEATER OFF
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
Figure 4-5. External cargo (sheet 2 of 6)
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
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
18,000
16,000
14,000
12,000
8000
6000
4000
2000
HOVER CEILINGOUT OF GROUND EFFECT
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
SKID HEIGHT 60 FEETHEATER ON
GROSS WEIGHT 10,000 TO 11,200 LB.
B
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EXTERNAL CARGO
HOVER CEILINGOUT OF GROUND EFFECT
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
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
SKID HEIGHT 60 FEETHEATER ON
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
Figure 4-5. External cargo (sheet 4 of 6)
212-FMS29-4-5-4
29
X00
PR
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SU
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ALT
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FE
ET
coo
BHT-212-FMS-29
EXTERNAL CARGO
HOVER CEILINGIN GROUND EFFECT
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
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
Figure 4-5. External cargo (sheet 5 of 6)
FAA APPROVED
SKID HEIGHT 4 FEETHEATER OFF
0
212-FMS29-4-5-5
30
0 0 0 0
PR
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SU
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ALT
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FAA APPROVED
EXTERNAL CARGO
HOVER CEILINGIN GROUND EFFECT
TAKEOFF POWERENGINE RPM 100%GENERATOR 150 AMPS EACH
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
Figure 4-5. External cargo (sheet 6 of 6)
BHT 212-FMS-29
SKID HEIGHT 4 FEETHEATER ON
212-FMS29-4-5-6
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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