(2)
LANDING GEAR LIGHTS
(3)
LEVEL LATCH AND PRESS WARN
(4)
ENGINES - EPR WARNING
(5)
ENGINE NO. 1 - EPR AND L.G. WARNING
(6)
ENGINE NO. 1 - EPR AND L.G. WARNING
2. Trouble Chart
T53076 T53185
518
Aug 15/78 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 31-26-0 Page 101
563
31-26-0 Page 102 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/78
3. Flap/Landing Gear Fault Isolation/Corrective Procedure
T53195
518
Aug 15/78 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 31-26-0 Page 103
4. Thrust Lever/Landing Gear Fault Isolation/Corrective Procedure
T53209
518
31-26-0 Page 104 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/78
5. Engine No. 1 Thrust Lever/EPR Logic Fault Isolation/Corrective Procedure.
T53214 T53225
563
Aug 15/78 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 31-26-0 Page 105
563
31-26-0 Page 106 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/78
8. Warning Switch Fault Isolation/Corrective Procedure
T53236
565
Nov 15/78 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 31-26-0 Page 107
AURAL WARNING SYSTEM - ADJUSTMENT/TEST
1. General
A. The procedures provide a complete test of the aural warning systems and contain individual tests for systems and components. Each individual test is complete within itself and can be performed separately to check only the system or component in question.
B. Procedures are provided to enable the following tests to be performed.
(1)
Paragraph 2, Aural Warning Devices Box Test
(2)
Paragraph 3, Cabin Altitude Warning Switch Test
(3)
Paragraph 4, Landing Gear Warning System Test
(4)
Paragraph 5, Takeoff Warning System Adjustment
(5)
Paragraph 6, Takeoff Warning System Test
C. For all adjustments and tests, which require positioning of, thrust levers, the thrust lever position is given in degrees from idle stop. If it is desirable to use linear dimensions (arc length at control stand cover top) for positioning thrust levers, refer to 76-11-0 MP, for conversion data.
D. For all adjustments and tests, which require movement of the landing gear, it will be necessary to jack the airplane. If unable to jack the airplane it will be necessary to simulate landing gear position.
(1)
To simulate nose gear retracted perform the following:
(a)
Place landing gear lever in OFF position. Check all red gear lights come on, green lights will remain on, and warning horn remains silent.
(b)
Insert an aluminum or copper deactuator shield between nose gear downlock sensor switch S75 and steel actuator arm located on nose gear lock brace. Make sure the nose gear green light goes off.
(c)
Put a steel actuator bar on the nose gear up and lock sensor switch S76.
(2)
To simulate retraction of left main gear:
(a)
Deactuate left gear down and lock sensor S71 located beside left main gear side brace.
(b)
Insert steel actuator bar over left main gear up and lock sensor switch S72 located on left main gear uplock hook.
(3)
To simulate retraction of right main gear:
(a)
Deactuate right main gear down and lock sensor S73.
(b)
Place steel actuator bar over right main gear up and lock sensor switch S74 located on the right main gear uplock hook.
(4)
Simulate extension of any gear by removing any aluminum or copper deactuators or steel actuator bars. Green light on P2 panel comes on and red light goes off.
500
Feb 20/94 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 31-26-0 Page 501
2. Aural Warning Devices Box Test (65-54499 Series)
A. General
(1) This test provides a check of the noise generating devices contained in the aural warning devices box. The test assumes the airplane is not on jacks. This test is sufficient after replacing the aural warning devices box.
B. Equipment and Materials
(1)
Actuator bars for the proximity sensors:
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 通訊描述和操作(57)
