B  Main Landing Gear Areas
(1)  Examine the main landing gear areas as follows:
(a)  
Examine the outer and inner cylinder lugs for distortion, cracks and other types ofdamage.

(b)  
Examine the side brace, drag brace, trunnion link, forward and aft trunnion attachments, and torsion links for cracked paint, distortion, or other damage.

(c)  
Examine the gear side brace downlock linkage for cracks or other types of damage.

(d)  
Look at the hydraulic fluid levels in the shock struts.  1) Do a two point servicing check or service the shock struts per AMM 12-15-31. 2) If a high drag or side load landing, and a hard landing occur at the same time,

remove the main gear inner cylinders. Do this also if the shock strut servicing was not correct. a) Then dimensionally check the barrel of the inner cylinder and axles for
distortion or bending, and examine for cracking.  b) Inspect the interior components of the shock strut for damage.
(e)  
Examine bolts and pin connections in the main gear (not inspected in Phase I) fordistortion.  1) Remove trunnion link per AMM 32-11-11/401, and NDT inspect the forward

trunnion fuse bolt (Fig. 201, Sheet 4, Detail A).

(f)  
Remove grease reservoir and inspect the aft trunnion fuse nut to ensure nut is secureand not cracked or distorted (Fig. 201, Sheet 5). 

NOTE: This inspection should be done only after the trunnion link has been reinstalled.

(g)  
Remove the retention pin for the main landing gear outboard fuse pin, and rotate the pin to ensure no crank shafting or deformation of the pin. (Fig. 201, Sheet 1).

C.  Nose Landing Gear Areas
(1)  Examine the nose landing gear areas as follows:
(a)  Look at the hydraulic fluid levels in the shock struts.   1) Do a two point servicing check or service the shock struts per AMM 12-15-31. 2) If a high drag or side load landing, and a hard landing occur at the same time, or
if the nose gear hits hard, remove the nose gear inner cylinders. Do this also ifthe shock strut servicing was not correct.  a) Then dimensionally check the barrel of the inner cylinder and axles for
distortion or bending, and examine for cracking.  b) Inspect the interior components of the shock strut for damage.
(b)  
Make sure the nose wheel steering system operates correctly and the steering mechanism is rigged correctly (Ref 32-51-00/201).

(c)  
If any landing gear wheels are removed because of a blown tire, do the steps thatfollow (Ref AMM 05-51-251):

500 
5-51-51 Page 204  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/01 

L90230 L90238L90244 L90270 L90276
500  Landing Gear Support Beam Attachments 
May 01/01  Figure 201 (Sheet 1)  5-51-51 
Page 205 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Main Gear Lower Drag Strut Wear Limits  500 
5-51-51  Figure 201 (Sheet 2)  May 01/01 
Page 206 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Main Landing Gear Beam Link Attachments to Wing Rear Spar 
May 01/01  Figure 201 (Sheet 3)  5-51-51 
Page 207 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Forward Trunnion Fuse Bolt  500 
5-51-51 Page 208  Figure 201 (Sheet 4) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/01 

500  Aft Trunnion to Landing Gear Beam Attachment 
May 01/01  Figure 201 (Sheet 5)  5-51-51 
Page 209 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

1) Examine the nose wheel structure for cracks.
2) Examine the nose wheel bearings for smooth operation (no roughness)

C.  Fuselage
(1)  Examine the lower fuselage structure for skin buckling, flaking paint, cracks, and loose fasteners.
NOTE:  Examine the area below the body crease and from station 727 to 100 inches aft.
(a)  Make sure the fasteners are installed in the correct positions.
(2)  
Examine the wing to fuselage joints at stations 540 and 664 for distortion, flaking paint, cracks, and loose fasteners.

(a)  Make sure the fasteners are installed in the correct positions.

(3)  
Examine the upper fuselage structure between S-6 LH and S-6 RH at station 540, 664,and 727 for buckling, distortion, flaking paint, cracks, and loose fasteners.
　
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