(j)
Install one end of fuel pressure hose assembly (42) on fuel pressure port (43); install other end of hose assembly (42) to tester fuel pressure coupling (3).
(k)
Remove cap from control air pressure port (41) on load control thermostat.
(l)
Install one end of control air pressure hose assembly (40) on control air pressure port (41); install other end of hose assembly (40) to tester control air pressure coupling (11).
(m)
Remove cap from oil pressure connection port (39) on oil pressure switch manifold.
(n)
Install one end of oil pressure hose assembly (38) on oil pressure connection port (39); install other end of hose assembly (38) to tester oil pressure coupling (9).
(o)
Disconnect tachometer generator electrical plug (37) from tachometer generator (36).
(p)
Connect the electrical cable or test cable assembly (46) to tachometer generator
(36) and to electrical plug (37).
(4) Prestart Procedure
(a) Check that the following circuit breakers on circuit breaker panel P6 are closed: 1) LANDING GEAR, ANTISKID, LIGHTS 2) LANDING GEAR, ANTISKID, TEST 3) FIRE PROTECTION, DETECTION, APU 4) FIRE PROTECTION, DETECTION, MASTER WARN & CONTR 5) MASTER CAUTION BUS, BAT 6) PANEL & INSTRUMENT, DIM & TEST 7) Nine circuit breakers under INDICATOR LTS & MASTER DIM BUS 8) APU GEN CONTROL. 9) HOT BAT, BAT BUS CONT. 10) HOT BAT, GEN CONT. 11) HOT BAT BUS.
504
49-21-01 Page 506 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/95
(b) Close APU CONT circuit breaker on circuit breaker panel P6.
(c) Check that circuit breaker on generator control unit is closed. (Generator control unit
is located in P6 panel area.)
(d) Check that circuit breaker on face of APU control unit is closed. (APU control unit is
located in electrical & electronic bay.)
(e) Position DC METERS selector switch to BAT BUS.
(f) Position AC METERS selector switch to APU GEN.
(g) Position BATTERY switch to ON.
(h) Check that APU BLEED valve switch is OFF.
(i) Momentarily position either APU generator switch to ON to close field relay.
(j) Position No. 1 tank forward boost pump switch to ON.
NOTE: No. 1 tank forward boost pump requires ac power. Provide airplane with
external power.
Aug 01/95 49-21-01 Page 506A/506B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(5) Test Engine Start, Acceleration, Operation, and Automatic Controls
(a)
Observe engine operating precautionary requirements given in par. 1.D.
(b)
APUs WITHOUT ALLIEDSIGNAL SB GTCP85-49-7096; if you must operate the APU with the lower shroud removed, make sure all persons are not in the hazard area (AMM 49-11-0/201).
WARNING: DO NOT OPERATE THE APU WITH THE LOWER SHROUD REMOVED IF PERSONS ARE IN OR DIRECTLY BELOW THE APU COMPARTMENT. YOU MUST BE A MINIMUM OF 3 FEET AWAY FROM THE OUTER EDGE OF THE APU COMPARTMENT OPENING TO OPERATE THE APU WITH THE LOWER SHROUD REMOVED. AN APU TURBINE WHEEL SEPARATION DURING OPERATION CAN CAUSE INJURY TO PERSONS.
NOTE: APUs with AlliedSignal SB GTCP85-49-7096 have an external shield around the turbine plenum and have no hazard area.
(c)
On forward overhead panel, position APU master switch to START and release.
NOTE: If APU master switch is positioned initially to ON and air inlet door fully opens before APU master switch is moved to START, CLOSE coil of start and stop relay K1 will not be energized and engine will not start.
(d)
Observe the following sequence of events on APU tester: 1) Low oil pressure light (17) should come on immediately. 2) The starter light (19) should come on when air inlet door is fully open and crank
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 機載輔助動力AIRBORNE AUXILIARY POWER(50)
