Stabilizer and Elevator Access Doors and Panels  591 
12-31-81  Figure 201 (Sheet 8)  May 01/01 
Page 208 

BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

NACELLE AND ENGINE-TO-WING FAIRING ACCESS DOORS AND PANELS

G43180 T51543 T51545
533  Nacelle and Engine-to-Wing Fairing Access Doors and Panels 
Feb 20/91  Figure 201 (Sheet 1)  12-31-91 
Page 201 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Nacelle and Engine-to-Wing Fairing Access Doors and Panels  533 
12-31-91  Figure 201 (Sheet 2)  Jan 20/82 
Page 202 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

527  Nacelle and Engine-to-Wing Fairing Access Doors and Panels 
Jan 20/82  Figure 201 (Sheet 3)  12-31-91 
Page 203 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

HARTWELL TYPE LATCHES -ADJUSTMENT/TEST
1.  Hartwell Series 5100, 5101, H502-1 and H503-1 Latches
A.  Test Hartwell Series 5100, 5101, H502-1 and H503-1 Latches
(1)  
Check that door rotates freely to within +0.100 or -0.030 inch of contour at latch position.

(2)  
At latch being checked, press door to its fit and fair position at door edge as shown in figure 501. Lock latch and check that preload exists by depressing latch bolt at location indicated in figure 501. There must be 0.010 to 0.030 inch depression free play at this point. Adjust per paragraph B. if this free play is not obtained.

(3)  
Check that door latch bolt overlap on structure to be 0.25 inch as shown in figure 501.

B.  Adjust Hartwell Series 5100, 5101, H502-1 and H503-1 Latches
(1)  If the 0.010 to 0.030 inch depression free play required (figure 501) is not obtained, add or subtract phenolic shims.
NOTE:  Nominal 0.030 and 0.040 inch shims are installed to obtain the dimensional condition shown in figure 501. Shim thickness may be varied.

500  Hartwell Series 5100, 5101, H502-1 and H503-1 Latches 
Nov 15/68  Figure 501 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  12-32-11 Page 501 

2.  Hartwell Series H856 and H2040 Latch
A.  General
(1)  The adjustment/test of this paragraph applies to H856 and H2040 latches with adjusting screw. H856 latches without adjusting screw may be tested and adjusted per paragraph 1.
B.  Test Hartwell Series H856 and H2040 Latch (See figure 502.)
(1)  
Check that door operates freely on its hinges to within +0.10 or -0.04 inch of contour at each latch location.

(2)  
With the latch closed, check that there is no free play at the end of the latch lever and that thumb pressure only is required to latch and unlatch. Adjust per paragraph C.

C.  Adjust Hartwell Series H856 and H2040 Latch
(1)  
With a piece of 0.005-inch shim between the adjusting screw and the phenolic block on the airframe, turn the adjusting screw until, with the latch closed, there is no free play at the end of the latch lever.

(2)  
Remove the 0.005-inch shim and check that thumb pressure only is required to latch and unlatch.

(3)  
Wire lock the adjusting screw per figure 502.

Hartwell Series H856 and H2040 Latch  500 
12-32-11 Page 502  Figure 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/72 

CLEANING AND WASHING - MAINTENANCE PRACTICES
1. General
A.  Use this procedure to clean and polish the external surfaces of the airplane. Clean the external surfaces frequently to help prevent corrosion and to extend the life of the airplane structure. Clean the surfaces that do not have paint more frequently than the painted surfaces.
B.  The liquids used in this procedure can cause injury to the skin and eyes, or damage to the airplane. Always wear clothing that will prevent injury when you clean the airplane. The cleaners can cause corrosion if they are not removed completely from the airplane surfaces. The solvent that is mixed with the cleaners is flammable. Keep the solvent away from sources of heat.
C.  Failure to remove covers from pitot static probes or coverings from static ports before flight may cause large errors in airspeed-sensing and altitude-sensing signals, which may lead to loss of safe flight.
2.  Clean the External Surfaces of the Airplane
A.  General
(1)  
This section includes these procedures: