(2)
Access Panel 452DR Access Door, Midlower Strut (Forward) - Nacelle Strut 1 462DR Access Door, Midlower Strut (Forward) - Nacelle Strut 2 472DR Access Door, Midlower Strut (Forward) - Nacelle Strut 3 482DR Access Door, Midlower Strut (Forward) - Nacelle Strut 4
C.
Prepare to Do the Functional Test
(1)
Supply electrical power (AMM 24-22-00/201).
S 865-002
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(2) S 865-050Make sure there is no pressure in the pneumatic system (AMM 36-00-00/201).
(3) S 865-003Put the ENGINE BLEED switches (engines 1, 2, 3, and 4) on the Pilot's Overhead Panel, P5 to the ON position.
(4) S 215-037After 10 seconds, make sure that no engine bleed SYS FAULT lights are shown.
(5) S 215-038Make sure that no bleed system EICAS messages are present.
(6) S 715-039Push the STAT key on the EICAS display select panel and show the status page on the auxiliary EICAS display. (a) Make sure that no bleed system status messages are present.
(7) S 715-040Get access to the CMCS input monitoring and enter the applicable input codes as follow (AMM 45-10-00/201):
~............................................................ | E/59/352/10 (Engine 1) | E/59/353/10 (Engine 1) | .............................................................. | E/59/352/01 (Engine 2) | E/59/353/01 (Engine 2) | .............................................................. | E/59/352/11 (Engine 3) | E/59/353/11 (Engine 3) | .............................................................. | E/59/352/00 (Engine 4) | E/59/353/00 (Engine 4) | 2..............................….............................1
(8) S 215-041Make sure that the applicable labels and bits are set as follows: label 352, bit 23 is set to 0, label 352, bit 24 is set to 1, label 353, bit 11 is set to 0, label 353, bit 12 is set to 1.
(9) S 865-005Open these circuit breakers and attach DO-NOT-CLOSE tags: (a) On the main power distribution panel, P6: 1) 6H32, ENG 1 AIR SUPPLY CONT 2) 6H33, ENG 2 AIR SUPPLY CONT 3) 6H34, ENG 3 AIR SUPPLY CONT 4) 6H35, ENG 4 AIR SUPPLY CONT
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S 045-017
WARNING: DO THE DEACTIVATION PROCEDURE FOR THE THRUST REVERSER TO
_______ PREVENT THE OPERATION OF THE THRUST REVERSER. ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(10)
Do the deactivation procedure for the thrust reverser (forward thrust position) for ground maintenance (AMM 78-31-00/201).
S 015-007
(11)
For the applicable system, remove the access door that follows for the mid-lower forward strut (AMM 54-62-00/201):
(a)
452DR
(b)
462DR
(c)
472DR
(d)
482DR
D.
Do the Functional Test
S 035-059
WARNING: THE BLEED AIR OVERTEMPERATURE SWITCH LEAD WILL HAVE ELECTRICAL
_______ POWER APPLIED DURING THE TEST. TAKE STEPS TO AVOID CONTACT WITH THE BARE LEADS. COULD CAUSE ELECTRICAL SHOCK.
(1)
Remove the bleed air overtemperature switch (AMM 36-22-01/401).
S 865-060
(2)
Close these circuit breakers:
(a)
Main Power Distribution Panel, P6
1) H32 ENG 1 AIR SUPPLY CONT
2) H33 ENG 2 AIR SUPPLY CONT
3) H34 ENG 3 AIR SUPPLY CONT
4) H35 ENG 4 AIR SUPPLY CONT
S 715-033
(3)
After a time delay of 4 to 8 seconds,
(a)
Make sure that only the applicable engine bleed SYS FAULT light comes on.
(b)
Make sure that only the applicable (BLEED 1, 2, 3, or 4 OVHT) or (BLD 1, 2, 3, or 4 OVHT/PRV) advisory message come to view on primary EICAS display.
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