position in 3 |1 seconds after you open NOSE AIR/GND. 3) Make sure that the LE FLAPS EXT light (P2 panel) is off. 4) Make sure that the LE FLAPS TRANSIT light (P2 panel) is on.
(c)
Push and hold the AIR SENSING test switch on the E11 landing gear logic shelf. 1) Make sure that the LE FLAPS EXT light is on. 2) Make sure that the LE FLAPS TRANSIT light is off.
(d)
Release the AIR SENSING test switch.
1) Make sure that the LE FLAPS EXT light goes off approximately 12 seconds after you release the AIR SENSING test switch.
2) Make sure that the LE FLAPS TRANSIT light is on.
(e) Open this circuit breaker: 1) P6 Panel a) AUTOSLAT NO. 1 DC
2) Make sure that the LE SLATS retract to the (intermediate) extend position in 5 |1 seconds (hydraulic power from EMP) or in 3.5 |1 seconds (hydraulic power from ground cart) after you open AUTOSLAT NO. 1 DC.
3) Make sure that the LE FLAPS EXT light is on. 4) Make sure that the LE FLAPS TRANSIT light is off.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú
27-83-00
COMPUTER P/N 65-52822 ú CONFIG 2 ú 01 Page 508 ú Nov 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
S 735-013-002
(12)
Do a check of the operation of stall management computer No. 2:
(a)
Close this circuit breaker: 1) P6 Panel a) AUTOSLAT NO. 2 DC 2) Make sure that the LE slats move to the full extend
position in 3 |1 seconds after you close AUTOSLAT NO. 2 DC. 3) Make sure that the LE FLAPS EXT light is off. 4) Make sure that the LE FLAPS TRANSIT light is on.
(b)
Push and hold the AIR SENSING test switch (E11 shelf). 1) Make sure that the LE FLAPS EXT light is on. 2) Make sure that the LE FLAPS TRANSIT light is off.
(c)
Release the AIR SENSING test switch.
(d)
Close this circuit breaker:
1) P6 Panel
a) NOSE AIR/GND
2) Make sure that the LE SLATS retract to the (intermediate) extend position in 5 |1 seconds (hydraulic power from EMP) or in 3.5 |1 seconds (hydraulic power from ground cart) after you close the NOSE AIR/GND circuit breaker.
S 865-014-002
(13)
Close this circuit breaker:
(a)
P6 Panel
1) AUTOSLAT NO. 1 DC
S 865-015-002
(14)
Move the flap control lever to the UP position.
S 865-016-002
(15)
Set the HYD PUMP ELEC 1 switch (P5 panel) to OFF.
S 985-017-002
(16)
Turn the left and right AOA sensors to their lower stops.
S 085-018-002
(17)
Remove the test calibrators from the AOA sensors.
S 865-019-002
(18)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P18 Panel
1) L ALPHA VANE HTR
2) R ALPHA VANE HTR
3) SMC STALL WARN ASYM MODE
(19)
Remove electrical power (Ref 24-22-00/201).
S 865-020-002
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú
27-83-00
COMPUTER P/N 65-52822 ú CONFIG 2 ú 01 Page 509 ú Nov 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
LEADING EDGE AUTOSLAT COMPUTER - REMOVAL/INSTALLATION
_____________________________________________________
1. General
_______
A. This subject contains two tasks, one for the removal and one for the installation of the leading edge autoslat computer. The procedure is the same for autoslat computer 1 or 2.
TASK 27-83-11-004-001
2. Leading Edge Autoslat Computer Removal (Fig. 401)
______________________________________
A. References
(1)
20-40-12/201, Electrostatic Discharge Sensitive Devices
B. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-300 400 500 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 6(130)
