737 AMM 飞机维护手册 舱门 DOORS(181)

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F. Master caution lights do not illuminate when doors light is depressed to recall an indicated fault G. Lights on door warning module do not light pressed to test  Door warning printed circuit board Door warning module faulty Master caution circuits faulty Door Warning module Airplane wiring faulty  Remove door warning module and check for momentary continuity at pin 10 of D482 while master caution annunciator is depressed. IF --(1) No continuity, check for continuity between pin 10 of module plug and pin 8 of printed circuit plug. IF --(a) Continuity present (b) No continuity (2) Continuity present Remove door warning module and check for 28V dc between pins 5 and round pin 7 on D482. IF --(1) Voltage ok (2) No voltage  Replace door warning printed circuit board Replace or repair module Trouble shoot master caution circuits. See 33-15-0, Master Warning and Caution Circuits Replace door warning module Repair airplane wiring between module and master circuit breakers, Bus 1 and Bus 2 

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DOOR WARNING SYSTEM - ADJUSTMENT/TEST
1.  Door Warning System Adjustment
A.  General
(1)  Adjustments for the door warning system are described in the following paragraphs of this section. Adjustment is accomplished by mechanically positioning individual sensors or switches. Adjustment of a sensor consists of moving the sensor closer or further from the sensor actuator to meet the specified gap requirements. On doors where microswitches are employed, adjustments consist of varying the amount of the projection of the switch plunger or plunger actuator arm. After adjustment of any sensor, perform the Door Warning Sensor Test (Ref par. 2.B).
B.  Forward and Aft Service Door Sensors Adjustment
(1)  Adjust forward and aft service door sensor (Detail A, Fig. 501).
(a)  
On airplanes with alternate sensor loosen nuts (4) attaching sensor (3) to bracket (1) and move sensor so that gap between sensor and sensor actuator (2) is 0.08 +0.02 inch. Tighten nuts.

(b)  
On airplanes with preferred sensor, loosen adjustment nut (62) securing actuator (61) to adjusting screw (63). Move actuator so that gap between sensor and actuator is as shown in Fig. 501. Tighten adjustment nut (62).

C.  Forward and Aft Cargo Compartment Door Sensor Adjustment
(1)  
Equipment and Materials

(a)  
Shim - 65-67304-3

(b)  
Shim - 65-67304-4

 

(2)  
Adjust forward and aft cargo compartment door sensor (Detail B, Fig. 501).

(a)  Use laminated shims if and as required between sensor and mounting bracket or bracket and fitting to meet gap requirements shown on Fig. 501. Remove laminations as required.
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D.  Tire Burst Protector Screen Door Sensor Adjustment (Right and Left Doors) (If Installed)
(1)  Loosen bolts (16, Detail C, Fig. 501), attaching sensor support (15) to screen support (18) and position sensor (14) so that the gap between actuator (20) and the sensor is 0.12 +0.05/-0.05 inch (Section C-C). Tighten bolts.
E.  Forward Entry Door Sensor Adjustment
(1)  Adjust forward entry door sensor.
(a)  Loosen screws (25, Detail D, Fig. 501) attaching sensor (23) to bracket (24) and move sensor until gap between sensor and sensor actuator (22) is 0.08 + 0.02 inch. Tighten screws.
F.  Deleted
G.  Deleted
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5C1  Door Warning System Switch and Sensor Adjustment 
May 01/99  Figure 501 (Sheet 1)  52-71-0 
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Door Warning System Switch and Sensor Adjustment  536 
52-71-0  Figure 501 (Sheet 2)  Oct 20/86 
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557 Door Warning System Switch and Sensor Adjustment May 01/76 Figure 501 (Sheet 2A) Page 504A/504B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

505  Door Warning System Switch and Sensor Adjustment 
Jun 20/86  Figure 501 (Sheet 3)  52-71-0 
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