(2)  
Disconnect control rods (3, Fig. 503) from latch torque tube cranks (4).

(3)  
Align torque tube (5), torque tube crank (2) and gate control rod (1) in straight-line relationship (at both upper and lower torque tubes) (Fig. 503, Section A-A). While maintaining the straight-line relationship adjust length of upper and lower control rods (3) as necessary to permit installation of bolt through rod end and crank (4). Install bolts.

NOTE: A locally fabricated tool may be desirable to obtain the straight-line relationship.

(4)  
With mechanism in closed position, check that latch rollers engage latch roller cam fittings with no interference.

4.  Forward Entry Door Test
A.  Equipment and Materials
(1)  Entry Door Torque Wrench - F80171-1
500 
52-11-0 Page 510  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 15/77 

500  Forward  Entry Door Overcenter Adjustment 
May 15/73  Figure 503  52-11-0 
Page 511 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

B.  Test Forward Entry Door
NOTE:  Airplane must be on its wheels to test door (no jack support).
(1)  
Check that snubber operates correctly to retard or snub rapid motion of door toward stowed and cocked position. No snubbing action should be felt when door is moved slowly from the cocked to stowed position or back to the cocked position. The snubber is designed to resist accelerated movement only and if the snubber performs otherwise, it should be replaced.

(2)  
Check forward airstair door lock mechanism for correct operation when door is opened and closed (Ref. 52-61-531, Forward Airstair Door Lock Mechanism).

(3)  
Check that door, with interior trim installed, moves through full cycle of operation smoothly with no binding spots and handle operates within torque limits.

NOTE:  Use entry door torque wrench, or equivalent, to facilitate checking of door handle torque. Force applied shall be perpendicular to handle in a plane parallel to handle cam plate.
(a)  
Unlatch door and move to cocked position and check torque to operate handle does not exceed 420 inch-pounds.

(b)  
Complete door opening from cocked position and close door until seals just contact doorway and check torque required to operate handle does not exceed 600 inch-pounds.

(c)  
Complete door closure from seal contact and check torque to operate handle does not exceed 700 inch-pounds.

(d)  
If handle torque is within requirements, proceed to step (5). If not within requirements, perform step (4).

(4)  
If requirements in step (2) are not obtained, remove door lining and insulation panels (Ref. 52-11-31, Forward Entry Door Lining and Insulation).

(a)  
Attach a 60-pound weight to inside doorframe at approximate midpoint of lower half of door to simulate the escape slide weight.

(b)  
Unlatch door and move to cocked position and check torque to operate handle does not exceed 420 inch-pounds.

(c)  
Complete door opening from cocked position and close door until seals just contact doorway and check torque to operate handle does not exceed 600 inch-pounds.

(d)  
Complete door closure from seal contact and check torque to operate handle does not exceed 550 inch-pounds.

(e)  
If limits are not exceeded, reinstall and adjust door interior trim to satisfy
requirements in step (3). If limits are exceeded, adjust door per par. 1.

(5)  
Check door warning system for correct operation when door is opened and closed (Ref. 52-71-0, Door Warning System).

500 
52-11-0 Page 512  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 15/77 

501  Forward Entry Door Striker Pin Fitting Adjustment 
Feb 01/74  Figure 504  52-11-0 
Page 513 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500 
52-11-0 Page 514  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 15/77 

FORWARD ENTRY DOOR - INSPECTION/CHECK
1.  Forward Entry Door Inspection
A.  Examine Forward Entry Door
(1)  
Examine external and internal skins for cracks, and corrosion; hinge fairings for looseness and missing screws.

(2)  
Examine frames, internal brackets, handle mechanism housing, and hinges for cracks, corrosion, and loose bolts.

(3)  
Examine window and frame for cracks, and corrosion.
　
中國航空網(wǎng) www.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(cè) 艙門 DOORS(27)