NOTE:  Removal of foil and splice angles may not be required on readjusted doors if only minor adjustment to seal depressor is required.

(2)  
Adjust seal depressor to obtain 0.60 (+0.08/-0.00) inches between depressor and reveal (Fig. 501).

(3)  
Fasten depressor splice angles to seal depressors.

(4)  
Thoroughly clean area on depressor above splice angle.

(5)  
Bond foil to depressors.

(a)  
Thoroughly blend adhesive in accordance with the manufacturer's instructions. The adhesive shall not be thinned.

(b)  
Apply a thin, uniform coat of the blended adhesive to each faying surface.

(c)  
Locate foil on depressor as shown in Fig. 201 and apply sufficient pressure to ensure complete contact of the faying surfaces. A continuous bead of extruded adhesive around the foil usually indicates proper contact.

Feb 15/79 52-14-1 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(d)  Cure adhesive.
1)  The time required to obtain handling strength is 16 hours at 75 to 80 degrees Fahrenheit.
NOTE:  A Rex Model A Durometer (preferred) reading of 30 or a Shore A Durometer reading of 20 will indicate attainment of handling strength. Curing may be accelerated by applying heat not to exceed a bond line temperature of 120 degrees Fahrenheit. As a rough rule of thumb, the cure time will be reduced by 50 percent for each 20 degrees Fahrenheit rise in temperature. Conversely, temperatures below 75 degrees Fahrenheit will greatly increase the cure time.

Seal Depressor Splicing  500 
52-14-1  Figure 501  May 15/68 
Page 502 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

AFT AIRSTAIR CONTROL CONSOLE - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes with Aft Airstair
1.  Equipment and Materials
A.  Grease, MIL-G-21164, or equivalent
2.  Remove Aft Airstair Control Console
A.  Open aft airstair circuit breakers on P6 panel.
B.  Extend airstair using emergency mode.
C.  Remove access panel on inboard side of control console shroud (figure 401).
D.  Remove bolts (2) attaching control handle (1) and remove handle.
E.  Disconnect electrical wiring from interior control operating switch.
F.  Remove control console shroud.
G.  Disconnect exterior control telescopic unit (15) from bellcrank (16).
H.  Remove end fittings (10) that connect radius rod (8) to control arm (4) by removing two bolts.
I.  Disconnect inboard end of door latch control rod (7) from cam follower(11).
J.  Disconnect upper end of emergency extension control rod (13) from bellcrank (12).
K.  Disconnect electrical wiring from door arming switch (17).
L.  Remove five bolts (14) attaching control console to floor (three at inboard edge and two at outboard edge) and remove console.
3.  Install Aft Airstair Control Console
A.  Adjust control console. Refer to Aft Airstair Control Console -Adjustment/Test.
B.  With aft airstair fully extended and aft airstairs circuit breaker on P6 panel open, position control console at installation location and install five attaching bolts (14, figure 401).
Feb 15/79 52-14-11 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

Aft Airstair Control Console Installation  500 
52-14-11 Page 402  Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Nov 15/67 

500  Aft Airstair Control Console Installation 
Feb 15/68  Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-14-11 Page 403 

Aft Airstair Control Console Installation  500 
52-14-11 Page 404  Figure 401 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/81 

C.  Place interior control lever (3) in the door latched position. This may be accomplished by holding stop bolt (6) away from boss (5) while the lever is being moved.
D.  Connect inboard end of door latch control rod (7) to cam follower (11) as follows:
(1)  
Adjust length of door latch control rod (7) to obtain 1.67 (+0.03/-0.03) inches extension of latch pin (9) beyond latch support fitting (19). (See detail B.) Check that latch pin (9) overlaps door stop fitting a minimum of 0.75 inch.

(2)  
Check that gap between door warning switch (18) and sensor plate (20) is 0.08 (+0.02/-0.02) inch. If switch adjustment is necessary, refer to 52-71-0, Door Warning System.
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 艙門 DOORS(50)