ROTORCRAFT FLIGHT MANUALthecontrols.ca/References/Flight Manuals/212... · HOVER CEILING IN GROUND...
22
--I J 3.0 -. z > BHT-212-FMS-35 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. ell Helicopter COPYRIGHT NOTICE COPYRIGHT 1996 BELL HELICOPTER INC. AND BELL HELICOPTER TEXTRON INC. A DIVISION OF TEXTRON CANADA LTD. ALL RIGHTS RESERVED A Subsidiary of Textron Inc. POST OFFICE BOX 482 FORT WORTH, TEXAS 76101 22 MARCH 1996
Transcript of ROTORCRAFT FLIGHT MANUALthecontrols.ca/References/Flight Manuals/212... · HOVER CEILING IN GROUND...
--I
J
3.0
-.
z
>
BHT-212-FMS-35
ROTORCRAFTFLIGHT MANUAL
SUPPLEMENTINCREASED WEIGHT
ALTITUDE TEMPERATURELIMIT
212-704-129AND
212-704-153
CERTIFIED22 MARCH 1996
This supplement shall be attached to Model 212Flight Manual when both 212-704-129 Tail RotorInstall and 212-704-153 Increased TakeoffHorsepower Kits have been installed.
Information contained herein supplementsinformation of basic Flight Manual. ForLimitations, Procedures, and Performance Datanot contained in this supplement, consult basicFlight Manual.
ell HelicopterCOPYRIGHT NOTICE
COPYRIGHT 1996BELL HELICOPTER INC.AND BELL HELICOPTER TEXTRON INC.A DIVISION OF TEXTRON CANADA LTD.
ALL RIGHTS RESERVED
A Subsidiary of Textron Inc.
POST OFFICE BOX 482 FORT WORTH, TEXAS 76101
22 MARCH 1996
05'
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. O. Box 482
Fort Worth, Texas 76101-0482
NP
o°0
BHT-212-FMS-35
LOG OF REVISIONS
Original ...........0 .............. 22 Mar 96
LOG OF PAGES
REVISION REVISIONPAGE NO. PAGE NO.
FLIGHT MANUAL A - B .................................. 0i/ii .......................................0
Title - NP .............................. 0 1 - 16 .................................. 0
NOTE
Revised text is indicated by a black vertical line. Insert latest revision pages; dispose ofsuperseded pages.
A
wca
r 07m
0LL.cad
Owl
BHT-212-FMS-35 FAA APPROVED
LOG OF APPROVED REVISIONS
Original ...........0 .............. 22 Mar 96
APPROVED:
MANAGER
ROTORCRAFT CERTIFICATION OFFICEFEDERAL AVIATION ADMINISTRATIONFT. WORTH, TX 76193-0170
B
.0) N03
0-0
(!)
S31
p33
BC
D.2.
O.-0.-
FAA APPROVED BHT-212-FMS-35
GENERAL INFORMATION
This supplement approves an increase Weight-Altitude-Temperatures (WAT) Limit fortakeoff, landing and in-ground-effect maneuvers when the 212-704-129 Tail RotorModification is installed in conjunction with the 212-704-153 Increased TakeoffHorsepower Kit (BHT-212-FMS-29).
Limitations, procedures and performance data associated with the increased WAT limitare presented for Basic Helicopter plus Winterization Heater.
i/i i
CD
.C
D
D)_
,,+
3 .a+
V)3 -O
N -"*
(1)
.D-
Q.--
O4)
0)>
FAA APPROVED
Section 1
BHT-212-FMS-35
LIMITATIONS
1-5. CONFIGURATION
1-5-A. REQUIRED EQUIPMENT
The following kits shall be installed priorto taking advantage of the IncreasedWeight Altitude Temperature Limitsupplement BHT-212-FMS-35.
1-10. HEIGHT-VELOCITY
The height-velocity limitations are criticalin the event of single engine failure duringtakeoff, landing, or other operation nearthe surface (figure 1-2). The AVOID area ofthe Height-Velocity diagram defines thecombinations of airspeed and heightabove ground from which a safe singleengine landing on a smooth, level, firmsurface cannot be assured.
Tail Rotor Install (212-704-129)
Increased Takeoff Horsepower (212-704-153)
1-6. WEIGHT AND CENTER OFGRAVITY
Refer to Weight-Altitude-Temperature(WAT) Limitations chart (figure 1-1) formaximum allowable weight for takeoff,landing and IGE hover operation.
The H-V diagram is valid only when theWeight-Altitude-Temperature limitationsare not exceeded (figure 1-1).
1-13. POWER PLANT
Refer to Basic Manual and/or BHT-212-FMS-29.
1
MIN
IMU
M O
AT
LIM
IT
DE
NS
ITY
ALT
ITU
DE
moo
a=te
BHT-212-FMS-35 FAA APPROVED
NOTE: ALLOWABLE GROSS WEIGHTS OBTAINED FROM THIS CHART MAY EXCEEDCONTINUOUS HOVER CAPABILITY UNDER CERTAIN AMBIENT CONDITIONS.REFER TO HOVER CEILING CHARTS IN SECTION 4.
14,000 FOOT DENSITY ALTITUDE LIMIT
6000
-40 -20 0 20 40OAT - 0C
0 It Im m
38 42 46 50 54 KG X 100
Figure 1-1. WAT for takeoff, landing and IGE maneuver
BHT-212-FMS-35
20 30 40 50 60 70INDICATED AIRSPEED KNOTS
Figure 1-2. Single engine height-velocity chart
3H1
0w
L " 0 ro M M
I I M M
Mrxxx\\N
llow
LE M
M IN
N I M
E P
..t,1", M
EN
1011,101",
1333 - 4Nno80 3n08d 1H
O13H
BHT-212-FMS-35
Section 2NORMAL PROCEDURES
Refer to Basic Manual and/or BHT-212-FMS-29.
Section 3
FAA APPROVED
EMERGENCY/MALFUNCTION PROCEDURES
No change from basic manual.
4
ail
+O
+
3U.
FAA APPROVED
Section 4
BHT-212-FMS-35
PERFORMANCE
4-1. INTRODUCTION 4-7. CLIMB AND DESCENT
The improved performance data containedin this supplement is applicable for Hpaltitudes up to 12,000 feet. Data for Hpaltitudes 12,000 to 14,000 feet is the sameas Basic Manual and/or BHT-212-FMS-29.
4-5. HOVER CEILING
4-5-A. I G E
Figure 4-1 presents IGE hover performanceas allowable GW for conditions of HP andOAT for basic helicopter.
4-5-B. OGE
Figure 4-2 presents OGE hoverperformance as allowable GW forconditions of HP and OAT for basichelicopter and winterization heater.
4-6. TAKEOFF DISTANCE
Takeoff distance required to clear a 50 foot(15.2 meter) obstacle is presented in figure4-3 as a function of OAT, HP and GW.
4-7-A. TWIN ENGINE TAKEOFFCLIMBOUT SPEED
Twin engine takeoff climbout speed (VTOCS)is that indicated airspeed which will allowtakeoff distance over a 50 foot (15.2 meter)obstacle to be realized and will complywith HV restrictions to allow a safe landingin case of an engine failure (figure 4-4).
4-7-B. TWIN ENGINE RATE OFCLIMB
For twin engine rate of climb refer to BHT-212-FMS-29.
4-9. LANDING DISTANCE
Single engine landing distance over 50foot (15.2 meters) obstacle is shown infigure 4-5 as a function of OAT, HP andGW.
5
ZO
O
0000
z
BHT-212-FMS-35
POWER: SEE NOTE BELOWENGINE RPM 100% (N2)GENERATOR 150 AMPS EACH0° TO 52°C
14,000 FT Hp LIMIT
FAA APPROVED
SKID HEIGHT 4 FTHEATER ON OR OFF
WINTERIZATION KIT HTR ON OR OFF
I NOTE THESE IGIARE BAE
OO
ALTITUDETAKEOFF
yTHIS HELHOVEREDINDICATE[
o --WITH LE!POWER
1
00
i
OI
i
O
I
OI
11 2 00 LBI- MAXIMUM OAT HEAT ER ON (21°C) (5
,
08 0 K G)
1 0 2 0 30 40 sn An ---- ...,. ,... . _ _ _ _ . __OAT - °C
HOVER CEILINGIN GROUND EFFECT
9000
HOVER CEILINGSED ON DENSITY
LIMITS FORAND LANDING.
COPTER CAN BEIGE AT THE
GROSS WEIGHTSS THAN TAKEOFF
0 LB
3600 4000 4400 4800 5200 KGGROSS WEIGHT
Figure 4-1. Hover ceiling in ground effect chart (sheet 1 of 2)
6
0
00 0 0
000
Moo
r-
MME
z0z
030
FAA APPROVED
HOVER CEILINGIN GROUND EFFECT
BHT-212-FMS-35
POWER: SEE NOTE BELOW SKID HEIGHT 4 FTENGINE RPM 100% (N2) HEATER ON OR OFFGENERATOR 150 AMPS EACH WINTERIZATION KIT HTR ON OR OFF0° TO --54°C
14,000 FT Hp LIMIT
o NOTE: THESE IC.ARE BAALTITU D
V`' TAKEOFI
oo ooo,THIS HEIHOVEREINDICATEWITH LE
o POWER
o°
O
o°0
0
11 200 LBQ
,
(5080 KG)
-60 -50 -40 -30 -20 -10 0OAT - °C
,E HOVER CEILINGSSED ON DENSITYE LIMITS FOR
= AND LANDING.LICOPTER CAN BED IGE AT THED GROSS WEIGHTS:SS THAN TAKEOFF
8000 9000 10000 11000 12000 LB
3600 4000 4400 4800 5200 KGGROSS WEIGHT
Figure 4-1. Hover ceiling in ground effect chart (sheet 2 of 2)
7
App
Opt
B HT-212-FMS-35
TAKEOFF POWERENG RPM 100% (N2)GENERATOR 150 AMPS EACH
/9 Zvv O
HOVER CEILINGOUT OF GROUND EFFECT
CALM WIND
14,000 FT Hp LIMIT
\,7
FAA APPROVED
SKID HEIGHT 60 FTHEATER OFF
0° TO 52°C
MAXIMUM GW LIMIT
clip/
O
X00
O
ATORQUE LIMIT s
O
iO
00,
0 10 20 30 40 50 60OAT - °C
11,200 LB(5080 KG)
8000 9000 10000 11000 12000 LB
3600 4000 4400 4800 5200 KGGROSS WEIGHT
Figure 4-2. Hover ceiling out of ground effect chart (sheet 1 of 6)
8
--I
D
(910ZlaayS)aeyo13911apunoa6;oIno6u11103aanoH-Z-Vaan6ld
1H013MSS080ONOOZS008'100$,.V000$1009£
1IIII
81OOOZL000LL0000L00060008
(ml0805)8lOOZ'LL
Il
0,-1d000t-OZ-0£-0ir-OS-09-
Mp"MEMWAMES
E
%
rwiiMJwnwlxewIIIII
O-bB--0100330H31V3H
1:109M913HGINS
111411°H13000'tL
ONIMWIVO103333aNnouo30in0
ON1-1130a3AOH
HOV3SdV4VOSLHOIV83N30(ZN)%OOLWdHON3
113MOd3303)IVI
SE-SW3-ZLZ-1H8a3A0addVVV=I
z7°
B HT-212-FMS-35
TAKEOFF POWERENG RPM 100% (N2)GENERATOR 150 AMPS EACH
HOVER CEILINGOUT OF GROUND EFFECT
CALM WIND
14,000 FT Ho LIMIT -__1n
FAA APPROVED
SKID HEIGHT 60 FTHEATER ON0° TO --54°C
mMAXIMUM GW LIMIT
\_N'F.A -I00
O"71 k
-\ o
11,
O
00
OTORQUE LIMIT
00O
O
11,200 LB(5080 KG)
-60-50 -40 -30 -20-10 0OAT - °C
8000 9000 10000 11000 12000 LB
3600 4000 4400 4800 5200 KGGROSS WEIGHT
Figure 4-2. Hover ceiling out of ground effect chart (sheet 3 of 6)
10
Obi 0
FAA APPROVED BHT-212-FMS-35
HOVER CEILINGOUT OF GROUND EFFECT
TAKEOFF POWERENG RPM 100% (N2)GENERATOR 150 AMPS EACH
CALM WIND
14,000 FT Ho LIMIT
O
SKID HEIGHT 60 FTHEATER ON
0° TO 20°C
MAXIMUM GW LI
TORQUE LIMIT
All
11,200 LB(5080 KG)
0 10 20 30 40 50 60OAT - °C
MIT
8000 9000 10000 11000 12000 LB
3600 4000 4400 4800 5200 KGGROSS WEIGHT
Figure 4-2. Hover ceiling out of ground effect chart (sheet 4 of 6)
11
or`
B HT-212-FMS-35
TAKEOFF POWERENG RPM 100% (N2)GENERATOR 150 AMPS EACH
o°
FAA APPROVED
SKID HEIGHT 60 FTWINTERIZATION ON
0° TO --54°C
MAXIMUM GW LI
0
11,200 LB(5080 KG)
HOVER CEILINGOUT OF GROUND EFFECT
CALM WIND
14,000 FT Hp LIMIT
-60 -50 -40 -30 -20 -10 0OAT - °C
MIT
8000 9000 10000 11000 12000 LB
3600 4000 4400 4800 5200 KGGROSS WEIGHT
Figure 4-2. Hover ceiling out of ground effect chart (sheet 5 of 6)
12
ono
C.)
040
FAA APPROVED
HOVER CEILINGOUT OF GROUND EFFECT
CALM WIND
TAKEOFF POWERENG RPM 100% (N2)GENERATOR 150 AMPS EACH
BHT-212-FMS-35
14,000 FT Ho LIMIT
0
O
lz
7
10 20 30 40 50 60OAT - °C
TO
SKID HEIGHT 60 FTWINTERIZATION ON
0° TO 20°C
MAXIMUM GW LIMIT
RQU
N
6
E LIMIT
11,200 LB(5080 KG)
8000 9000 10000 11000 12000 LB
3600 4000 4400 4800 5200 KGGROSS WEIGHT
Figure 4-2. Hover ceiling out of ground effect chart (sheet 6 of 6)
13
mom
0
009
BHT-212-FMS-35
TAKEOFF DISTANCEOVER 50 FT (15.2m) OBSTACLE
HOVER POWER +15%o TORQUEENG RPM 100% (N2)GENERATOR 150 AMPS
FAA APPROVED
INITIATED FROM 4 FT SKID HEIGHTHEATER ON OR OFF
WINTERIZATION KIT HTR ON OR OFF
REFER TO VTOCS CHART FOR TAKEOFF SPEED
14,000 FT HD LIMIT
A I I I I I
HOT DAYTEMPERATURE LIMIT
OO/
-60 -40 -20 0 20 40 60OAT - °C
200
MAXIMUMHD
FOR TAKEOFF
400 600 800 1000 1200(61) (122) (183) (244) (305) (366)
TAKEOFF DISTANCE - FT (M)
Figure 4-3. Takeoff distance over 50 foot (15.2 meter) obstacle
14
m
CID
L()
L()
0
FAA APPROVED BHT-212-FMS-35
TWIN ENGINE TAKEOFF CLIMBOUT SPEED - KIAS
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
Figure 4-4. Twin engine takeoff climbout speed
15
