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operative engine beep trim is increased. This nose-low
attitude should not be used at extremely low alttiude
because of reduced reaction time, R/D, and the response
of the helicopter. Any time the helicopter assumes a decelerating
attitude in close proximity to the ground, avoid
rotating the aft gear into the ground at touchdown.
TM 1-1520-240-10
9-1-7
Figure 9-1-3. 712 Single - Engine Service Ceiling
TM 1-1520-240-10
9-1-8
Figure 9-1-4. 712 Height Velocity Diagram for Safe Landing After Single-Engine Failure (Sheet 1 of 3)
TM 1-1520-240-10
9-1-9
Figure 9-1-4. 712 Height Velocity Diagram for Safe Landing After Single-Engine Failure (Sheet 2 of 3)
TM 1-1520-240-10
9-1-10
Figure 9-1-4. 712 Height Velocity Diagram for Safe Landing After Single-Engine Failure (Sheet 3 of 3)
TM 1-1520-240-10
9-1-11
Figure 9-1-5. 714A Single-Engine Service Ceiling
TM 1-1520-240-10
9-1-12
Figure 9-1-6. 714A Height Velocity Diagram for Safe Landing After Single-Engine Failure (Sheet 1 of 3)
TM 1-1520-240-10
9-1-13
Figure 9-1-6. 714A Height Velocity Diagram for Safe Landing After Single-Engine Failure (Sheet 2 of 3)
TM 1-1520-240-10
9-1-14
Figure 9-1-6. 714A Height Velocity Diagram for Safe Landing After Single-Engine Failure (Sheet 3 of 3)
TM 1-1520-240-10
9-1-15
Figure 9-1-7. Maximum Glide Distance / Minimum Rate of Decent in Autorotation
TM 1-1520-240-10
9-1-16
Figure 9-1-8. Autorotational Approach Corridor for Second Engine Failure
TM 1-1520-240-10
9-1-17
9-1-12. 714A ENG 1 FAIL or ENG 2 FAIL.
The ENG 1 or ENG 2 FAIL caution is illuminated whenever
the engine failure logic within the DECU recognizes
any of the following:
1. Power turbine shaft failure. N2 is greater
than RRPM by more than 3%.
2. N1 underspeed.
3. Engine flameout.
4. Over temperature start abort (Primary
mode only).
5. Primary system fail freeze (Primary and
Reversionary mode hard faults, FADEC
caution is illuminated).
6. During normal shutdown as the N1 rpm
goes below 48% the ENG 1 FAIL or ENG 2
FAIL caution is illuminated and then turned
off 12 seconds after the N1 rpm drops below
40%.
9-1-13. Single Engine Failure — Low Altitude/Low
Airspeed and Cruise.
If an engine fails under conditions that will permit S/E
flight, thrust and 712 engine beep trim must be adjusted
as required to maintain safe RRPM. Initial thrust reduction
will vary from no reduction at zero airspeed below 20
feet to a significant reduction at higher altitudes and airspeeds.
Attempt to maintainat least 96 percent RRPM.
If the helicopter is below the best S/E climb airspeed,
forward cyclic must be applied to attain a nose-low attitude
of up to 30 in order to gain airspeed. As airspeed
increases to 30 knots, adjust the pitch attitude of the
aircraft to accelerate to the best S/E airspeed.
If an engine fails under conditions that will not permit S/E
flight, the procedures will be essentially the same as for
continued flight, except that cyclic pressures are applied
to decelerate the helicopter for touchdown, rather than
continued acceleration. During deceleration, just prior to
touchdown, avoid rotating the aft landing gear into the
ground.
Continued flight is possible:
1. Thrust control — Adjust as necessary to
maintain RRPM.
2. 712 ENGINE BEEP TRIM switch —RPM
INCREASE as required.
3. External cargo — Jettison (if required).
4. ALT switch — Disengage.
5. Land as soon as practible.
6. EMER ENG SHUTDOWN (when
conditions permit).
NOTE
If S/E flight can be maintained, an attempt to
restart the inoperative engine may be made if
there is no evidence of fire or obvious mechanical
damage.
Continued flight is not possible:
Land as soon as possible.
9-1-14. Engine Restart During Flight.
WARNING
Fire detector and extinguishing systems
are not provided for the APU. Crewman
must monitor APU area for fire.
CAUTION
If abnormal indications are present during
the restart, shut down the engine immediately.
1. APU — Start.
2. 712 ENG COND lever (inoperative engine)
— STOP.
3. 714A ENG COND lever (inoperative engine)
— STOP, then GND.
4. FIRE PULL handle — In.
5. All FUEL PUMP switches — ON.
6. XFEED switch — As required.
7. Starting engine — Perform.
8. APU — OFF.
9-1-15. 712 Normal Engine Beep Trm System
Failure (High Side) or N2 Governor Failure.
Failure of the normal engine beep trim system to the high
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