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switch to OFF, check the BITE indicators in
the ESU, and record the display for maintenance.
c. APU ON indicating light — Check on.
d. UTIL HYD SYS caution — Check out. If
the light does not go out within 30 seconds
after APU ON indicating light
comes on, APU switch OFF.
* 7. APU GEN switch — ON. No. 1 and No. 2
RECT OFF.
NOTE
If either HYD FLT CONTR caution capsule does
not go out in 30 seconds, after the PWR XFER
switches are set to ON, set the PWR XFER
switch to OFF. Do not fly the helicopter.
* 8. PWR XFER — Check. PWR XFER 1 and 2
switches — ON. Check HYD FLT CONTR
caution capsules out.
F* 9. MAINTENANCE PANEL — Check.
a. GND switch — TEST, then RESET.
b. GROUND CONTACT indicating lights —
Check on.
c. Systems — Normal.
* 10. Avionics — On as required.
O 11. HUD — ON. As required.
F 12. CARGO HOOKS HOIST/WINCH — Check
operation as required. Refer to Chapter 4,
Section III.
F 13. ANTI-ICE systems — Check as required.
a. PITOT switch — ON. Physically check for
pitot tube and yaw port heat. Then switch
OFF.
b. W/S switches — ON. Physically check for
windshield heat. Then switch OFF.
14. SLT-FIL switches — Check and set as required.
* 15. PARKING BRAKE — Set.
16. CRUISE GUIDE indicator — Check for pointer
in white test band when the CGI TEST switch
is at FWD and AFT TEST.
F* 17. Altimeters — Set and check as follows:
a. Barometric altimeter — Set and check.
b. Radar altimeter — ON and set.
18. FIRE DETR switch — TEST. Check fire warning
lights on, release switch, and check fire
warning lights out.
* 19. Fuel quantity — Check as required.
TM 1-1520-240-10
8-2-8
* 20. Cyclic trim — Check GND position.
F* 21. Rotor blades — Check position. Make sure
that a rotor blade is not within 30 of the
centerline of the fuselage throughout control
check.
* 22. AFCS SYSTEM SEL switch — Check as follows:
a. Select individual system and check opposite
AFCS caution capsule remains on.
b. Select BOTH and check both AFCS caution
capsules go out.
c. AFCS SYSTEM SEL switch — OFF.
F* 23. Flight control travel and hydraulics —
Check as follows: (For thru flights, complete
steps b thru e with FLT CONTR switch —
BOTH).
CAUTION
If a helicopter is parked on a slope greater
than 4, longitudinal stick travel may be restricted
to less than 7 inches forward (up
slope) or 4 inches aft (down slope).
NOTE
Mixing of flight control inputs during ground operation
on a single hydraulic system should be
avoided. If the Flight Controls are moved rapidly
or erratically during the control check, unusual
vibrations may be felt, or flight boost hydraulic
fail indication may result.
NOTE
Check caution capsules as the check is being
performed. With slow smooth flight control
inputs, check each axis individually thru full
travel for smoothness of operation. Check for
corresponding movement of the fore and aft
rotors during the check.
a. FLT CONTR hydraulic switch — 1 ON.
b. Check cyclic for freedom of movement
in all quadrants. Check for a minimum
of 7 inches forward and 4 inches aft
travel.
c. Check thrust through full travel for freedom
of movement and magnetic brake for
proper operation.
d. Check pedals through full travel for freedom
of movement.
e. Position the cyclic and pedals at neutral,
thrust at ground detent.
f. FLT CONTR hydraulic switch — 2 ON,
Repeat steps b thru e.
g. FLT CONTR hydraulic switch — BOTH.
24. Avionics — Perform operational check and
set as required.
O 25. HUD — Program as required.
NOTE
If the DECU display is other than 88, place the
ENG COND levers to STOP, turn B/U PWR
switch off, and remove all power from the
DECU by pulling the respective ENGINE PRI
and REV CONT circuit breakers on the PDP.
Reset circuit breakers and perform another
DECU prestart BIT. If other than 88’s consult
DECU Fault Code List/Matrix in Chapter 2.
F* 26. 714A DECU PRESTART BIT — Perform
as follows:
a. B/U PWR switch — ON.
b. Wait until ENG FAIL, FADEC, and REV
caution lights go out.
c. ENG COND levers — GND.
F d. DECUs — Check displays read 88.
e. ENG COND LEVERS — STOP.
27. 712 ENGINE BEEP TRIM switch (NO. 1
& 2) — Decrease for 8 seconds.
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