3.
LAND AS SOON AS PRACTICABLE.
9.15 INCREASING % RPM R.
% RPM R increasing will result from an engine control system failing to the high side. % RPM 1 and 2 (Np) will increase with the rotor % RPM R. Increasing the collective will probably increase the malfunctioning engine’s TGT TEMP above 900°C. If an engine control unit fails to the high side:
1. ENG POWER CONT lever -Retard high % TRQ/TGT TEMP engine, maintain % TRQ approximately 10% below other engine.
2.
LAND AS SOON AS PRACTICABLE.
If the affected engine does not respond to ENG POWER CONT lever movement in the range between FLY and IDLE, the HMU may be malfunctioning inter-nally.
Change 4 9-7
TM 1-1520-253-10
EXAMPLE
WANTED:
A TAKEOFF PROFILE WHICH WILL PERMIT A SAFE LANDING AFTER AN ENGINE SUDDENLY BECOMES INOPERATIVE.
UH.60Q
HEIGHT VELOCITY AVOID REGIONS
SINGLE.ENGINE FAILURE
SEA LEVEL STANDARD
650
600
550
500
AVOID AREA
450
400
KNOWN:
WHEEL HEIGHT ~ FT WHEEL HEIGHT ~ FT
AIRCRAFT GROSS WEIGHT = 22,000 LBS
AMBIENT CONDITIONS: GROSS
WEIGHT
350TEMPERATURE = 15oC
PRESSURE ALTITUDE = SEA LEVEL
WIND = 0 KTS
~ 1000 LBS
300
250
METHOD:
200
D
TRACE ALONG GROSS WEIGHT LINE NOTING WHEEL HEIGHT / AIRSPEED 150 16,000
18,000
22,000
20,000
LB
COMBINATIONS WHICH WILL KEEP LB
LB
LB
THE TAKEOFF PROFILE BELOW AND 100 TO THE RIGHT OF THE AVOID REGION. 50
B
C
A
A1010 0
B 20 10
POINT AIRSPEED WHEEL HEIGHT
0 10 20 30 40 506070 C 30 15
AIRSPEED ~ KTS
D 42 155
4000 FT 35OC (95oF)
850 800 750 AVOID AREA700 650 600
550
500
450 400 350 GROSS WEIGHT ~ 1000 LBS
300 250 22,000 LB
200
150 100 12,000 LB 14,000 LB 16,000 LB 18,000 LB 20,000 LB
50
NOTE:
0
BASED ON AN ETF OF .85 OF
0 10203040506070
MAXIMUM RATED POWER.
AB0838
AIRSPEED ~ KTS
DATA BASIS: CALCULATED
SA
Figure 9-2. Height Velocity Diagram
9-8
.75 .70 .65 .60 .55 .50
4600
4400
4200
4000
3800
3600
3400
3200
3000
2800
2600
2400
2200
2000
WANTED:
STATE AUTOROTATION AT IAS’S OF:
A. 130 KIAS
B. 50 KIAS
DATA BASIS:FLIGHT TEST
GLIDE RATIO ~NAUTICAL MILES PER 1000 FT
RATE OF DESCENT ~ FT/MIN
AUTOROTATION
CLEAN CONFIGURATION 100% RPM R ZERO WIND
GROSS WEIGHT = 18,000 LB MOVE UP TO INTERSECTION OF R / D LINE,
MOVE LEFT, READ RD = 3,560 FT / MIN
B. ENTER AUTOROTATION CHART AT 50 KIAS,
MOVE UP TO 18,000 LB GW LINE, MOVE LEFT,
READ R / D = 2,325 FT / MIN
THE GLIDE RATIO IS NOT PROVIDED FOR LOW
AIRSPEEDS AA0322B
SA
9-9
TM 1-1520-253-10
.75 .70 .65 .60 .55 .50 .45 4600 4400 4200 4000 3800 3600 3400 3200 3000 2800 2600 2400 2200 2000
GLIDE RATIO ~ GRNAUTICAL MILES TRAVELEDRATE OF DESCENT ~ FT / MIN PER 1000 FT ALTITUDE LOSS
DATA BASIS: FLIGHT TEST
AUTOROTATION
HIGH DRAG CONFIGURATION
100% RPM R ZERO WIND
NOTE: DASH LINE FOR FERRY MISSION ONLY
INDICATED AIRSPEED ~ KNOTS
AA1253A
SA
9-10
If this occurs:
3.
Establish single engine airspeed.
4. Perform EMER ENG SHUTDOWN (affected engine).
5.
Refer to single engine failure emergency proce-dure.
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：UH-60Q 直升機(jī)技術(shù)手冊(cè) 直升機(jī)操作手冊(cè) 2(62)
