2..........…..............…..........…...............…...........…..............1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-00
ALL ú ú 01 Page 537 ú Jul 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
(a)
Make sure the actual differential pressure (. P1) is in the limits for the necessary (. P1) in Table 502.
(b)
Make sure the flaps move to the 30-unit position.
S 865-098
(3)
Slowly decrease the pressure in the pitot-static system until the flaps start to extend.
S 975-099
(4)
Make a record of the actual differential pressure (. P2) in Table 502.
(a)
Make sure the actual differential pressure (. P2) is in the limits for the necessary (. P2) in Table 502.
(b)
Make sure the actual .P1-.P2 is in the limits of the necessary .P1-.P2 shown in Table 502.
(c)
Make sure the flaps move to the 40-unit position.
S 865-101
(5)
Release the pressure in the pitot-static system.
S 085-102
(6)
Remove the vacuum source from the pitot-static system.
S 865-103
(7)
If the airplane is on jacks, compress the right main gear strut approximately 5 inches to the ground position.
S 725-104
(8)
Move the flap load limiter test switch on the equipment bay light panel in the electronics compartment to the SYSTEM TEST position.
(a)
Make sure the flaps retract to the 30-unit position.
S 725-105
(9)
Release the test switch.
(a)
Make sure the flaps extend to the 40-unit position.
S 865-106
(10)
Move the flap control lever to the 30-unit detent.
(a)
Make sure the flaps retract to the 30-unit position.
S 725-107
(11)
Move the flap load limiter test switch to the SWITCH TEST position.
(a)
Make sure the TEST light comes on.
S 725-108
(12)
Release the test switch.
(a)
Make sure the TEST light goes off.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-00
ALL ú ú 01 Page 538 ú Jul 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
S 865-109
(13)
Move the flap control lever to the UP detent to retract the flaps.
F.
Put the Airplane Back to Its Usual Condition
S 865-110
(1)
Remove the system B hydraulic power (AMM 27-51-00/201).
S 865-111
(2)
Remove the electrical power (AMM 24-22-00/201).
TASK 27-51-00-725-112
8. AIRPLANES WITH ARINC 429 RECEIVER; Flap Load Limiter Test______________________
A. References
(1)
AMM 24-22-00/201, Manual Control
(2)
AMM 27-51-00/201, Trailing Edge Flap System
B.
Access
(1)
Location Zone
101, 102 Control Cabin
205 Electronic Compartment
C.
Prepare for the Test of the Flap Load Limiter System
S 865-114
(1)
Make sure these circuit breakers are closed:
(a)
P6-2 Panel 1) FLAP LOAD RELIEF 2) LANDING GEAR LATCH & AIR/GND RELAY & LIGHTS
(b)
P18-2 Panel
1) NO. 1 AIR DATA COMPUTER-1
(2)
Supply the electrical power (AMM 24-22-00/201).
S 865-115
S 865-116
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
_______ SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, TRAILING EDGE FLAPS, LEADING EDGE FLAPS AND SLATS, SPOILERS LANDING GEAR AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
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本文鏈接地址：737-300 400 500 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 3(166)
