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AR IAC APPROVED Ka-32A11BC FLIGHT MANUAL Section 1

ISSUE 1 1-1

TABLE OF CONTENTS

Paragraph Page

Number

OPERATING LIMITATIONS .....................................................................................................1-3

BASIS OF CERTIFICATION......................................................................................................1-3

TYPE OF OPERATIONS ............................................................................................................1-3

OCCUPANTS LIMITATIONS....................................................................................................1-3ENGINE INLET SCREEN LIMITATIONS ................................................................................1-3

OPTIONAL EQUIPMENT...........................................................................................................1-3

FLIGHT CREW LIMITATIONS .................................................................................................1-3

DOORS OPEN .............................................................................................................................1-4

WEIGHT/CG LIMITATIONS......................................................................................................1-4

WEIGHT LIMITS ...............................................................................................................1-4

LONGITUDINAL CENTER OF GRAVITY LIMITS .......................................................1-4

LATERAL CENTER OF GRAVITY LIMITS ...................................................................1-4

INTERNAL CARGO LOADING .......................................................................................1-4

AIRSPEED LIMITATIONS.........................................................................................................1-4

WINDSPEED LIMITATIONS.....................................................................................................1-5DESCENT LIMITATIONS..........................................................................................................1-5

ALTITUDE LIMITATIONS ........................................................................................................1-5

AMBIENT AIR TEMPERATURE LIMITATIONS....................................................................1-5

HEIGHT-VELOCITY LIMITATIONS........................................................................................1-5

MANEUVERING LIMITATIONS ..............................................................................................1-10

PITCH LIMITS ...................................................................................................................1-10

ROLL LIMITS.....................................................................................................................1-10

YAW LIMITS .....................................................................................................................1-10

SLOPE LANDING LIMITATIONS.............................................................................................1-10

ROTOR RPM (NR ) LIMITATIONS.............................................................................................1-10ROTOR RPM (NR ) LIMITS - POWER ON .......................................................................1-10

ROTOR RPM (NR ) LIMITS OEI........................................................................................1-10

ROTOR (NR ) LIMITS - POWER OFF ...............................................................................1-10

ROTOR RPM (NR ) LIMITS FOR BRAKE APPLICATION.............................................1-11

POWERPLANT LIMITATIONS.................................................................................................1-11

DURATION OF MODES...................................................................................................1-11

GAS GENERATOR RPM (N1) LIMITS ............................................................................1-11

GAS TEMPERATURE LIMITS.........................................................................................1-11

OIL PRESSURE LIMITS ...................................................................................................1-11

OIL TEMPERATURE LIMITS ..........................................................................................1-11

TRANSMISSION (MAIN GEARBOX) LIMITATIONS............................................................1-12TRANSMISSION OIL PRESSURE LIMITS.....................................................................1-12

TRANSMISSION OIL TEMPERATURE LIMITS............................................................1-12

S E C T I O N 1 LIMITATIONS



Section 1 Ka-32A11BC FLIGHT MANUAL AR IAC APPROVED

1-2 ISSUE 1

TABLE OF CONTENTS

Paragraph Page

Number

AUXILIARY POWER UNIT LIMITATIONS..................................................................... 1-12

FUEL AND OIL LIMITATIONS......................................................................................... 1-12

FUEL........................................................................................................................... 1-12

OIL............................................................................................................................... 1-12

ELECTRICAL LIMITATIONS............................................................................................ 1-13

BATTERY LIMITATIONS.................................................................................................. 1-13

HYDRAULIC LIMITATIONS............................................................................................. 1-13

HYDRAULIC PRESSURE LIMITS........................................................................... 1-13MAIN WHEEL BRAKES........................................................................................... 1-13

HYDRAULIC TEMPERATURE LIMITS.................................................................. 1-13

AUXILIARY PUMP LIMITS ..................................................................................... 1-13

HYDRAULIC OIL ...................................................................................................... 1-13

LIST OF FIGURES

Figure Title Page

Number

1-1 Category A. Weight-altitude-temperature limitations for takeoff and

flight operations .............................................................................................................. 1-6

1-2 Category B. Weight-altitude-temperature limitations for takeoff................................. 1-14

1-3 Category A. Height-Velocity diagram.......................................................................... 1-16

1-4 Minimum Rotor RPM for autorotation......................................................................... 1-18

1-5 Instrument markings ..................................................................................................... 1-22

1-6 Placards......................................................................................................................... 1-26

1-7 Ambient air temperature limits for the APU operation ................................................ 1-29

LIST OF TABLES

Table Title Page

Number

1-1 Vne limits for flight with static pressure selector switched to

EMERGENCY or if airspeed limiting system has failed............................................. 1-20

1-2 Engine and APU Fuels.........................................................................................1-31/1-32

1-3 Engine and Gearbox Oils.....................................................................................1-31/1-321-4 Hydraulic Oil .......................................................................................................1-31/1-32




ISSUE 1 1-3

OPERATING LIMITATIONS

Compliance with the limitations in this section

is mandatory. Anytime an operating limitation

is exceeded, an appropriate entry shall be

made in the helicopter logbook. The entry

shall state which limit was exceeded, the

duration of time, the extreme value attained,and any additional information essential in

determining the maintenance action required.

BASIS OF CERTIFICATION

This helicopter is certified according to A and

B Categories and in compliance with the

requirements of Airworthiness Standard 32.29

(AS 32.29), equivalent to FAR-29.

TYPE OF OPERATIONS

The helicopter is approved for operation in

compliance with the operating limitations

specified in the RFM under VFR, restricted

VFR, IFR, in day and night time, over land

and overwater up to latitude 75°, including

icing conditions.

OCCUPANTS LIMITATIONS

13 passengers maximum.

11 persons maximum – for the overwater

flights.

9 persons maximum – according to

Category B.

CAUTION

• When transporting external loads

passenger carrying is prohibited

• Prior to passenger transportation

crew seat located behind navigator

seat must be removed

• Smoking is prohibited during flight

• Safety harness must be fastened

before takeoff, in flight and before

landing.

ENGINE INLET SCREEN

LIMITATIONS

In connection with the installation of a

medium sized bird ingestion heated protection

screen in the engine inlet:

• day operation at temperatures below

plus 5°C with visible moisture is

prohibited,

• night operation at temperatures below plus5°C is prohibited.

OPTIONAL EQUIPMENT

Refer to appropriate Flight Manual

Supplements for additional limitations,

procedures and performance data with

optional equipment installed.

FLIGHT CREW LIMITATIONS

The minimum crew is one pilot only for the

flights under VFR without the persons

carrying.

The crew consists of pilot and navigator for

the flights under IFR.

S E C T I O N 1 LIMITATIONS




1-4 ISSUE 1

DOORS OPEN

Helicopter may be flown with crew doors

open. Flight operation is approved for the

following alternative configurations:

• Both sliding crew doors secured fully open

at hover and at speeds of 0 KIAS

(0 km/h) IAS to 27 KIAS (50 km/h) IAS;

• One of the sliding crew doors (left or right)

open for not more than 10 cm (4 in) and

secured at speeds of 27 KIAS

(50 km/h) IAS to 108 KIAS (200 km/h)

IAS.

The doors must be kept closed and locked at

speeds above 108 KIAS (200 km/h) IAS.

NOTE

Check that all personal equipment and

flight documents reliably fastened prior

to opening any door

WEIGHT/CG LIMITATIONS

WEIGHT LIMITS

Maximum weight - 24250 lb. (11000 kg)

Refer to Weight-Altitude-Temperature

Limitations chart (Figure 1-1) for maximum

allowable takeoff weight, Category A.

Maximum weight permitting rejected landingCategory A, with the landing site pressure

altitude:

• 3000 m (9480 feet).... 9000 kg (19845 lb.)

• 2000 m (6560 feet).. 10000 kg (22050 lb.)

• 1000 m (3280 feet).. 11000 kg (24250 lb.)

Maximum weight for take-off and landing,

Category B, is 24250 lb. (11000 kg)


Limitations chart (Figure 1-2) for maximum

allowable weight for takeoff, Category B.

For weight correction for humid air ref. figure

4-2, Section 4.

Minimum flying weight is 15870 lb.

(7200 kg).

LONGITUDINAL CENTER OF GRAVITY

LIMITS

Reference datum line (Station zero) is located

207.87 inches (5280 mm) forward of the main

rotor axis.

Longitudinal center of gravity limits vary from

station 196.85 to 209.06 inches (5000 to

station 5310 m) during the flight under VFR.

During the flights under IFR it is

196.85…208 inches (from 5000 m to

5280 m).

LATERAL CENTER OF GRAVITY LIMITS

Lateral center of gravity is not critical if the

cargoes are located in compliance with the

instructions of the present RFM, Section 5.

INTERNAL CARGO LOADING

Maximum cargo weight is limited to

8157 lb. (3700 kg)Maximum allowable deck loading for cargo is

limited to:

• 614 lbs/sq.ft (3000 kg/sq.m) between

frames No. 4 to No. 7;

• 307 lbs/sq.ft (1500 kg/sq.m) between

frames No. 7 to No. 13.




ISSUE 1 1-5

AIRSPEED LIMITATIONS

Basic Vne is limited to 140 KIAS

(260 km/h) IAS at sea level.

Vne is limited for ambient conditions and

weights in accordance with the position of the

red index on pilot ASI.

Airspeed limiting system should be on for

Category A operation.

Refer to Table 1-1 for Vne limits in case of

airspeed limiting system failure or when the

static pressure selector is switched to

EMERGENCY.

Vne is limited to 95 KIAS (180 km/h) IAS

during autorotation.

Minimum IAS at altitudes higher than OGE

hover ceiling is limited to 27 KIAS

(50 km/h) IAS in level flight.

During the flights under VFR – 51 KIAS

(95 km/h).

Minimum steady IAS during autorotation is

limited to 54 KIAS (100 km/h) IAS.

WINDSPEED LIMITATIONS

Maximum allowable tailwind and crosswind

speed for takeoff, landing and hover

operations is 20 knots (10 m/s).

Maximum allowable windspeed for engine

start and shutdown procedures:

• headwind is limited to 40 knots (20 m/s)

• tailwind and crosswind speed is limited to

20 knots (10 m/s)

DESCENT LIMITATIONS

Maximum rate of descent is limited:

• to 590 ft/min (3 m/s) at speeds up to

27 KIAS (50 km/h) IAS;• to 1575 ft/min (8 m/s) at speeds 108 KIAS

(200 km/h) IAS and above.

ALTITUDE LIMITATIONS

Maximum operational pressure altitude is

limited to 16400 ft (5000 m).


Limitations charts (Figures 1-1 and 1-2) to

determine the maximum pressure altitude for

takeoff.

Maximum pressure altitude for takeoff and

landing is 9840 feet (3000 m)

Maximum pressure altitude for the APU

ground and in-flight start-up and operation islimited to 9840 feet (3000 m).

AMBIENT AIR TEMPERATURE

LIMITATIONS

The maximum sea level ambient air

temperature for operation is ISA plus 25oC to

16400 feet (5000 m).

The minimum ambient air temperature for

operation at all altitudes is minus 50o

C.

HEIGHT-VELOCITY LIMITATIONS

The AVOID area of Height-Velocity diagram

(Figure 1-3) defines the combinations of

airspeed and height above ground prohibiting

a safe single engine landing on a smooth,

level, firm surface.

The H-V diagram is valid only when the

Weight-Altitude-Temperature limitations arenot exceeded (Figure 1-1).




1-6 ISSUE 1

CATEGORY A

Figure 1-1. (Sheet 1 of 4) Weight-altitude-temperature limitations

for takeoff and in flight operations

(IMPERIAL)

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

TEMPERATURE, C

16000

17000

18000

19000

20000

21000

22000

23000

24000

25000

26000

W E I G H T , P O U N D S

0

2000

4000

6000

8000

9840

PRESSURE ALTITUDE,

FEET

MAX WEIGHT

TAKEOFF POWERAIS ON




ISSUE 1 1-7

CATEGORY A

Figure 1-1. (Sheet 2 of 4)

Weight-altitude-temperature limitations for takeoff

and in flight operations

(METRIC)




1-8 ISSUE 1

CATEGORY A


Weight-altitude-temperature limitations for takeoff and in- flight operations

(IMPERIAL)

0 10 20 30 40 50

TEMPERATURE, C

16000

17000

18000

19000

20000

21000

22000

23000

24000

25000

26000

27000

W E I G H T , P O U N D S

MAX WEIGHT

PRESSUREALTITUDE,FEET

0

2000

4000

6000

8000

9840

TAKEOFF POWERAIS OFF




ISSUE 1 1-9

CATEGORY A


Weight-altitude-temperature limitations for takeoff and in flight operations

(METRIC)




1-10 ISSUE 1

MANEUVERING LIMITATIONS

PITCH LIMITS

Maximum in straight flight duringacceleration: - 30 degrees

Maximum in straight flight during

deceleration: + 25 degrees

Maximum in all other modes: ± 20 degrees

ROLL LIMITS

Airspeed 32…108 KIAS

(60…200 km/h) IAS and pressure altitude up

to 3280 ft (1000 m):

maximum bank angle: ± 35 degrees

All other airspeeds and pressure altitudes

above 3280 ft (1000 m):

maximum bank angle ± 20 degrees

YAW LIMITS

Yaw is limited to two ball diameters of

deviation to the left and right sides.

Acrobatic maneuvers are prohibited.

SLOPE LANDING LIMITATIONS

Slope landings are limited to slopes not

exceeding 6 degrees in any direction.

ROTOR RPM (NR ) LIMITATIONS

ROTOR RPM (NR ) LIMITS - POWER ON

Maximum steady 92 percent

Maximum transient at airspeeds below

108 KIAS (200 km/h) IAS 98 percent (not to

exceed 8 s if above 92 percent)

Maximum transient at airspeeds above108 KIAS (200 km/h) IAS 92 percent

(no time limitations)

Minimum steady 87 percent

Minimum transient 83 percent

(not to exceed 30 s if below 87 percent)

ROTOR RPM (NR ) LIMITS OEI


Maximum transient at airspeeds below

108 KIAS (200 km/h) IAS 98 percent

(not to exceed 8 s if above 92 percent )

Maximum transient at airspeeds above

108 KIAS (200 km/h) IAS 92 percent

(no time limitations)

Minimum steady 87 percent

Minimum transient 83 percent

(not to exceed 30 s if below 87 percent)

Minimum at OEI landing moment

73 percent

(not to exceed 10 s if below 83 percent,

4 times during the engine service life only)

ROTOR RPM (NR ) LIMITS - POWER OFF


Maximum transient 98 percent

(not to exceed 8 s if above 92 percent )

Minimum rotor RPM (NR ) - refer to chart

(Figure 1-4)




ISSUE 1 1-11

ROTOR RPM (NR ) LIMITS FOR BRAKE

APPLICATION

Rotor brake application is limited to ground

operation with both engines shut down and

rotor RPM NR 20 percent or below.

CAUTION

At a wind speed exceeding 16 knots

(8 m/s) the rotor braking by transfer of

the braking level upwards against the

stop is obligatory

POWER PLANT LIMITATIONS

NOTE2.5 minutes OEI rating has been

demonstrated at block and flight

tests. The helicopter performance

figures are indicated in the RFM

without consideration to this rating.

DURATION OF MODES

Twin Engine Operation

Takeoff, max 5 minutes

Idle, max 20 minutes

One Engine Inoperative (OEI)

2.5 minutes rating, max 2.5 minutes

30 minutes rating, max 30 minutes

NOTE

During the engine time between

overhauls 2.5 minutes rating can beused 8 times and 30 minutes rating 2

times.

Minimum interval between usage of

2.5 minutes, 30 minutes and take-off

ratings is 5 minutes.

GAS GENERATOR ROTOR RPM (N1)

LIMITS


Takeoff rating, max 101 percent

Max continuous, max 99 percent

The difference between LH and RH enginegas generator rotors RPM (N1) is limited to:• in steady-state conditions, max 2 percent• at takeoff rating, when ITT limiter operates,

max 3 percentNOTE

• In transient conditions the difference between gas generators RPMs (N1)is not limited

• The maximum gas generator RPM(N1) at engine in flight start is 7

percent


2.5 minutes rating, max 101 percent

30 minutes rating, max 101 percentMax continuous rating, max 99 percent

GAS TEMPERATURE LIMITS

At engine starting, max 780°C


• Takeoff rating, max 990°C

• Max continuous, max 955°C


• 2.5 min rating 990°C

• 30 min rating 990°C

• max continuous 955°C

OIL PRESSURE LIMITS

Min oil pressure at Idle rating 2 kg/sq.cm

Min oil pressure at ratings exceeding Idle3.0 kg/sq.cm

Max allowable oil pressure at engine starting4.8 kg/sq.cm

OIL TEMPERATURE LIMITS

Min oil temperature is limited to:• to start engine on the ground and in flight

- minus 40°C• at ratings exceeding Idle - plus 30°C

Max oil temperature - plus 150°C




1-12 ISSUE 1

NOTE

1) Prior to engine start at oil

temperatures between minus

35°C and minus 40°C carry out

dry motoring run (cranking).2) At oil temperatures below minus

40°C preheat engine and oil

systems. Ref Maintenance

Manuals for instructions

TRANSMISSION (MAIN GEARBOX)

LIMITATIONS

TRANSMISSION OIL PRESSURE LIMITS

Minimum oil pressure

• at idle 0.5 kg/sq.cm

• at ratings exceeding idle 2.5 kg/sq.cm

Maximum oil pressure at engine

starting 5.0 kg/sq.cm

TRANSMISSION OIL TEMPERATURE

LIMITS

Minimum oil temperature at engine starting

minus 40°C

Minimum oil temperature before increasing

the power above Idle

minus 15°C

Minimum oil temperature for continuous

operation plus 30°C

Maximum allowable oil temperature plus 90°C

AUXILIARY POWER UNIT

LIMITATIONS

The limits mentioned below refer to APU

ground start and the APU air start.

For ambient air temperature limits refer to

figure 1-7.NOTE

At ambient temperatures of minus

25°C or less it is recommended to

preheat the APU with hot air or to

crank it before starting.

Turbine Exhaust Gas Temperature(EGT) is

limited:

• during APU starting to plus 850°C;• during air bleeding for main engines

starting to plus 720°C for OAT plus

15°C and below; to plus 750°C for OAT

exceeding plus 15°C.

Maximum number of APU successive

attempted starts, crankings or false starts is 3

with minimum 3 min cooling intervals

between them.

After three successive APU attempted starts,

crankings or false starts at least a 15 min cool

down is required.

Minimum cool down period after APU

operation is 15 minutes.

The period of APU continuous operation is

not more than 13 minutes.

For the period of the APU continuous

operation not more than 5 APU air bleeds for

the main engine starting, crankings or false

starting are allowed.

HELICOPTER FUELING LIMITATION

WITH THE ENGINES OPERATING

Only single-point fueling can be used when

the helicopter is fueled with the engines

operating

FUEL AND OIL LIMITATIONS

FUEL

Grades of fuel authorized for use are listed inTable 1-2.

NOTE

The anti-ice fluid shall be used atOAT plus 5° and below inaccordance with Table 1-2.

OIL

Grades of oil authorized for use in engines,

APU and gear box are listed in Table 1-4.




ISSUE 1 1-13

ELECTRICAL LIMITATIONS

BATTERY LIMITATIONS

Maximum battery temperature is 65°C, asindicated by illumination of LH BAT HOT or

RH BAT HOT warning lights.

Minimum voltage 20 V DC.

HYDRAULIC LIMITATIONS

HYDRAULIC PRESSURE LIMITS

Main hydraulic system


64 kg/sq.cm.

Maximum oil pressure

90 kg/sq.cm

Standby hydraulic system


64 kg/sq.cm.Maximum oil pressure

90 kg/sq.cm.

Auxiliary hydraulic system


75 kg/sq.cm


90 kg/sq.cm.

Auxiliary pump


200 kg/sq.cm.


240 kg/sq.cm

MAIN WHEEL BRAKES

Maximum pressure for taxiing

13 kg/sq.cm

Maximum pressure for parking

30 kg/sq.cm

Maximum time of brakes applications for

parking is limited by pressure in main wheels

brakes as follows:

• maximum continuous 17 kg/sq.cm

• maximum 30 min 17...25 kg/sq.cm

• maximum 5 min 25...30 kg/sq.cm

HYDRAULIC TEMPERATURE LIMITS

Minimum hydraulic oil temperature before

engine start up

minus 50°C

Maximum hydraulic oil temperature

plus 85°C

Minimum hydraulic oil temperature beforetakeoff

minus 10°C

AUXILIARY PUMP LIMITS

Maximum time of Auxiliary pump operation:

• 30 minutes on ground

• 150 minutes in flight

HYDRAULIC OIL

Grades of oil authorized for use are listed in

Table 1-4.




1-14 ISSUE 1

CATEGORY B

Figure 1-2. (Sheet 1 of 2) Weight-altitude-temperature limitations for takeoff

(IMPERIAL)




ISSUE 1 1-15

CATEGORY B

Figure 1-2. (Sheet 2 of 2) Weight-altitude-temperature limitations for takeoff

(METRIC)




1-16 ISSUE 1

Figure 1-3. (Sheet 1 of 2). Height – Velocity diagram

(IMPERIAL)




ISSUE 1 1-17

Figure 1-3. (Sheet 2 of 2). Height – Velocity diagram

(METRIC)




1-18 ISSUE 1

Figure 1-4. (Sheet 1 of 2). Minimum rotor RPM for autorotation

(IMPERIAL)




ISSUE 1 1-19

Figure 1-4. (Sheet 1 of 2). Minimum rotor RPM for autorotation

(METRIC)




1-20 ISSUE 1

Vne, knots

WEIGHT < 19800 LB (9000 KG)

t°CHp,ft

+40 +30 +20 +10 0 -10 -20 -30 -40 -50

0 120 120 125 125 125 125 125 125 125 115

2000 115 115 120 120 120 125 125 125 120 110

4000 110 110 115 115 120 120 125 125 115 105

6000 105 105 110 110 115 115 120 125 110 102

8000 100 100 105 105 110 110 115 120 105 98

10000 95 95 100 100 105 105 110 115 100 94

12000 75 85 90 95 100 100 105 110 95 90

14000 55 65 70 80 85 95 100 105 93 85

16000 40 45 55 60 70 80 85 90 90 82

19800 LB (9000 KG) < WEIGHT < 22000 LB (10000 KG)

t°CHp,ft

+40 +30 +20 +10 0 -10 -20 -30 -40 -50

0 120 120 125 125 125 125 125 125 125 115

2000 115 115 120 120 120 125 125 125 120 110

4000 110 110 115 115 120 120 125 125 115 105

6000 105 105 110 110 115 115 120 125 110 102

8000 90 100 105 105 110 110 115 120 105 98

10000 70 80 90 95 105 105 110 115 100 94

12000 55 60 70 80 85 95 105 110 95 90

14000 35 40 50 60 70 75 85 95 93 85

16000 40 50 60 70 75 85 82

Table 1-1. (Sheet 1 of 2).

Vne limits for flight with static pressure selector switched to

EMERGENCY or if airspeed limiting system has failed




ISSUE 1 1-21

Vne, knots

22000 LB (10000 KG) < WEIGHT < 24200 LB (11000 KG)

t°C

Hp,ft+40 +30 +20 +10 0 -10 -20 -30 -40 -50

0 120 120 125 125 125 125 125 125 125 115

2000 115 115 120 120 120 125 125 125 120 110

4000 105 110 115 115 120 120 125 125 115 105

6000 90 100 105 110 115 115 120 125 110 102

8000 70 80 90 95 105 110 115 120 105 98

10000 55 65 70 80 85 95 105 115 100 94

12000 35 45 55 60 65 75 85 95 95 90

14000 40 50 60 65 80 85 85

16000 35 45 60 70 80

Table 1-1. (Sheet 2 of 2).

Vne limits for flight with static pressure selector switched to

EMERGENCY or if airspeed limiting system has failed




1-22 ISSUE 1

AIRSPEED INDICATOR RED

95 knots- Maximum speed at autorotationRED

Vne - Movable symbolRED

140 knots - Basis Vne limit at sea levelYELLOW

0...27 knots - Caution rangeGREEN

27...140 knots- Normal operating

OIL PRESSURE MAIN ENGINES INDICATOR RED

2 kg/sq.cm - minimum limit

YELLOW(2...3) kg/sq.cm - caution range

GREEN

(3...4) kg/sq.cm - normal operatingYELLOW

(4...4.8) kg/sq.cm - caution rangeRED

4.8 kg/sq.cm - maximum limit

OIL TEMPERATURE MAIN ENGINES

INDICATOR RED

minus 40°C - minimum limit for startRED

30°C - minimum limitYELLOW

(30...70)°C - caution rangeGREEN

(70...150)°C - normal operatingRED

150°C - maximum limit

OIL PRESSURE MAIN GEARBOXRED

0.5 kg/sq.cm - minimum limitat starting (IDLE)

RED

2.5 kg/sq.cm - minimum limitYELLOW

(2.5...3) kg/sq.cm - caution rangeGREEN

(3...4) kg/sq/cm - normal operatingYELLOW

(4...5) kg/sq.cm - caution rangeRED

5 kg/sq.cm - maximum limit

Figure 1.5. (Sheet 1 of 4) Instrument markings

kg/sq.cm

8

6

4

2

0

8

6

4

2

0

Х 10

18

12

6

0

- 6

200

20

40

60

80

120 100140

160

180

KN TS

kg/sq.cm




ISSUE 1 1-23

OIL TEMPERATURE MAIN GEARBOXRED

minus 40°C - minimum limit for start

REDminus 15°C - minimum limit

YELLOW

(minus 15...13) °C - caution rangeGREEN

(30...80) °C - normal operatingYELLOW

(80...90) °C - caution rangeRED

90°C - maximum limitENGINES RPM N1 INDICATOR

RED

25% - maximal speed whenrotors are to start rotatingRED

101% - maximum limit for normal and OEIoperating

YELLOW

(99...101)% - caution range for normaland OEI operating

GREEN(65...99)% - normal operating range,

OEI included

ROTOR RPM NR INDICATOR

WHITE 20% - maximum limit whenrotor brake is set ON

RED

73% - minimum limit, OEIRED

83% - minimum limit with twoengines operating

YELLOW(73...87)% - caution range

GREEN(87...92)% - normal operating

YELLOW (92...98)% - maximum limit

RED98% - maximum limit

TOT APU INDICATOR GREEN

(0...720) °C - normal operatingRED

720°C - maximum limit(during bleeding at TR < 15°C)

YELLOW

(720...750) °C- caution rangeRED

750°C - maximum limit(during bleeding at TR > 15°C)

RED850°C - maximum limit for start

Figure 1-5. (Sheet 2 of 4) Instrument markings

Х 10

15

10

5

0

- 5

100

2

46

8RPM

nx10%

n 10%RPM

10

0

2

4

6

8

0

3 6

9

Х 100 Со

DEG

х




1-24 ISSUE 1

ITT ENGINES INDICATOR RED

7800 C - maximum limit start

RED 990o C - maximum limitYELLOW

(955...990)°C - caution range for normal

operating and OEIGREEN

(450...955)°C - normal operating

OIL TEMPERATURE MAIN AND STANDBY

HYDRAULIC SYSTEMS

RED minus 50°C - minimum limit for start

YELLOW

minus (50...10) °C - caution rangeRED

minus 10°C - minimum limitGREEN

(−10...+85)°C - normal operatingRED

85°C - maximum limit

OIL PRESSURE MAIN AND STANDBY

HYDRAULIC SYSTEMRED

64 kg/sq.cm. - minimum limitGREEN

(64...90) kg/sq.cm. - normal operatingRED

90 kg/sq.cm - maximum limit

OIL PRESSURE AUXILIARY HYDRAULIC

SYSTEMRED

75 kg/sq.cm - minimum limitGREEN

(75...90) kg/sq.cm. - normal operatingRED

90 kg/sq.cm. - maximum limit


Х 100 СО

960 Со

40 4060 60

20 2080 800 0

63

0 0

9 9

12 12

36

Х 10

24

12

0

- 6

КГ/СМ2

Х 10

10

5

0

Х 10

kg/sq.cm kg/sq.cm

kg/sq.cm

10 10

5 5

0 0

Х 10 Х 10

24

12

0

- 6




ISSUE 1 1-25

OIL PRESSURE HYDRAULIC PUPM

Red 200 kg/sg.cm - minimum limit

Green (200…220) kg/sq.cm - normal operating

Yellow (220…240) kg/sq.cm - caution range

Red 240 kg/sq.cm - maximum limit

PRESSURE DROP INDICATOR ON THE GEAR BOX

FINE OIL FILTER

Green (0…1.3) kg/sg.cm - normal working range

Yellow (1.3…2.0) kg/sg.cm - partial contamination

WHEEL BRAKE PRESSURE INDICATOR

Green (0…17) kg/sg.cm - normal operating

Yellow (17…30) kg/sg.cm - caution range

Red 30 kg/sg.cm - maximum limit (5 minute

max)

VERTICAL SPEED INDICATOR

Red 590 ft/min - maximum rate of descent

limit at speed 27 knots and

below

Red 1575 ft/min - maximum rate of descent

limit at speed above 108 knots

Yellow (2200 + 150) h/p

Green (1700 + 150) h/p

Green (15000 + 150) h/p


КГ/СМ2

2

1

0kg/sq.cm

КГ/СМ2

Х 100

2

1

0kg/sq.cm

0

2

4

10х kg/sq.cm

UP VERTICAL SPEEDTHOUSAND FT PER MINUTE

DOWN

10

9

8

7

6

5

21

1

4

6

4

5

5

2




1-26 ISSUE 1

- located above the door of the cargo

compartment, on the port-side.

White letters and frame on red background

- located on the emergency hatch cover, above

the lever.


- located near the crew door handle, on the

starboard.

White letters on red background

- illuminated sign in the partition upper

portion along frame No 13 (the cargo

compartment aft wall) and on the fuselage

RH side between frames Nos. 5 and 6. Red

letters and arrows on white background

- placards on the rear wall of the cargo

compartment and on transportation cabin

RH wall above seat No. 12

Red letters and frame on white background

- located on the emergency hatch cover and on

the door of the cargo compartment.Red letters and frame on white background

- located on the left side of the overhead panel.

White letters on black background

Figure 1-6. (Sheet 1 of 3). Placards

TO OPEN THE DOOR

PRESS THE HANDLE BUTTON

EXIT

NO SMOKING FASTEN SEAT BELTS

THIS HELICOPTER IS

APPROVED FOR OPERATION UNDER

VFR, RESTRICTED VFR, IFR IN DAY

AND NIGHT TIME, OVER LAND AND

OVERWATER, INCLUDING ICING

CONDITIONS IN COMPLIANCE WITH

THE OPERATING LIMITATIONS

SPECIFIED IN THE APPROVED RFM

PULL COVER DOWN

TURN HANDLE AND PUSH

EXIT

PULL THE HANDLE

PUSH THE DOOR

РУЧКУ ПОТЯНУТЬ

ДВЕРЬ ВЫТОЛКНУТЬ




ISSUE 1 1-27

- located on the port-side front wall of the

cargo compartment

Red letters, arrow and frame on white

background

- illuminated sign on the port-side front wall

of the cargo compartment.

Red letters on yellow background

- located above the handle of the cargo

compartment

White letters arrow and frame on red

background

- located on the inside of the cargo

compartment door in the lower left corner.


- located on the aft wall, cargo compartment

port-side and starboard.

3 placards on the rear wall;

3 placards on the starboard;

2 placards on the port-side.

Red letters and frame on white background.

- located on the front wall of the cargocompartment.

- located on the front wall of the cargo

compartment.


NO SMOKING

FASTEN SEAT BELTS

TO OPEN DOOR PULL

HANDLE DOWN TO 90°

AND SLIDE DOOR AFT

ВЫХОД-EXIT

PUSH HERE

ТОЛКАТЬ ЗДЕСЬ

LIFE VEST

UNDER

YOUR SEAT

MAXIMUM ALLOWABLE INTERNAL

CARGO WEIGHT IS 3700 KG (8157 LB)

REFER TO RFM FOR LOADING

INSTRUCTIONS

MAXIMUM ALLOWABLE BAGGAGE

WEIGHT IS 150 KG (330 LB)

REFER TO RFM FOR BAGGAGE

ARRAGEMENT INSTRUCTIONS




1-28 ISSUE 1

- placard, located on operator ′s seatback


- placard, located on copilot′s seatback


- placard, located above seat No. 15


- placard, located on starboard of

transportation cabin in emergency hatch area

and in the front part of the cargo

compartment


- placard, located on the frame wall near RH

front door of the crew compartment


- placard located on the emergency hatch

cover


THIS SEAT MUST

BE REMOVED

WHEN PASSENGERS ARE

TRANSPORTED

OR

LIFE RAFTS ARE

INSTALLED

DURING PASSENGERS EVACUATIONTURN HANDLE DOWN AND FOLD

SEAT BACK FORWARD

FIREX IS INSTALLED UNDER THIS

SEAT

EMERGENCY LIGHT


TO JETTISON DOOR

PULL COVER OFF

TURN HANDLE

AND PUSH DOOR

FOLD LEVER UNDER HANDLE FLAT

AND CLOSE TRANSPARENT COVER

BEFORE FLIGHT




ISSUE 1 1-29

- 50 0 + 50

0

5000

10000

PRESSURE

ALTITU

DE,FEET

OAT min OAT max

OUTSIDE AIR TEMPERATURE Со

Figure 1-7. (Sheet 1 of 2). Ambient air temperature limits for the APU

operation on the ground and in flight(IMPERIAL)




1-30 ISSUE 1

- 50 0 + 50

1000

2000

3000

OAT min OAT max

PRESSUREALTITUDE,M

OUTSIDE AIR TEMPERATURE, Со

Figure 1-7. (Sheet 2 of 2). Ambient air temperature limits for the APU

operation on the ground and in flight

(METRIC)




Table 1-2. Engine and APU Fuels

FUEL GRADES

Basic Alternative GOSTs, Specifications

Airport air temperature for

which the use of fuel is

recommended

TS(TC)-1 GOST 10227-85 AnyRT(PT) GOST 10227-85 Any

Jet A-1 DEF STAN 91-91 Any

DERD 2494 Any

ASTM D1655 Any

CAN CGSB 3-23 Any

Jp-8 MIL-T-83133 Any

Jet A ASTM, D1655 >-20°C

CAN CGSB 3-23 >-20°C

Jp-5 MIL-T-5624 >-20°C

Jet B ASTM, D1655 <0°C

CAN CGSB 3-23 <0°CJp-4 MIL-T-5624 <0°C

NOTES

At airport ambient temperature below plus 5 deg. C anticrystallization fluid shall be added to fuels:

- Russian fuels need ethyl cellosolve (liquid I (И), GOST 8313-88) in the amount of 0.1% of the fuel

volume;

- Western fuels Jet A-1, Jet A, Jet B -need methyl cellosolve (AL-31) DEF STAN 68-251 (DERD 2451)

or MIL-I- 27686E, or CAN CGSB 3.526 in the amount of (0.1-0.15) % of the fuel volume.

Fuels Jp-4, Jp-5 and Jp-8 contain the additive already and do not need it be added.

Table 1-3. Engine and Gearbox Oils Basic Alternative GOSTs, Specifications

B-3V - ТУ 38.101295-85Castrol 98 DERD 2487Castrol 599 DERD 2497

Aeroshell Turbine Oil 560 DERD 2499Exxon-Jet Oil 25 DOD-L-85734Mobil-Jet Oil 254 MIL-L-23699

Castrol 5000 MIL-L-23699Turbonycoil 525-1A MIL-L-23699

Table 1-4. Hydraulic OilBasic

Alternative SpecificationsAMG-10 - GOST 6794-78AeroShell Fluid 41 MIL-H-5606F

Grade OM-15 DEF STAN 91-48/1,Gade SuppercleanAIR-3520/B

Brayco Micronic 756D MIL-H-5606FRoyco Micronic 756B MIL-H-5606F

FH-51 AIR 3520/B,MIL-H-5606FDEF STAN 91-48/1

FH-15 -

CAUTION. THE PURITY OF HYDRAULIC FLUID BEFORE FILLING THE HYDRAULICSYSTEM SHALL BE NOT BELOW CLASS 6 BY GOST 17216-71 OR CLASS

ka 32 limitations

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