4. Repair of Main Landing Gear Axle Sleeves
A. Wear Limits
(1)
Check diameters of inboard and outboard bearing boss for wear as shown on figure 802.
(2)
If wear on bearing boss exceeds specified wear Limits and clearance between bearing and boss exceeds 0.0006 inch, axle sleeves must be removed for replacement or repaired per OHM 32-11-11.
(3)
If wear on bearing boss exceeds specified wear Limits, but clearance between bearing and boss does not exceed 0.0006 inch, axle sleeves may continue in service for 65 hours flying time before being removed for replacement or repair per OHM 32-11-11.
B. Local Damage Between Bearing Surfaces
(1) Remove sharp edges and blend damage to a 0.50-inch radius and use a smooth finish. Rework must not reduce wall thickness be more than 0.025-inch for P/N 65C33516-1, 65-46147-1 and 65-46147-2 or 0.012-inch for P/N 65-46147-3.
C. Damage to Bearing Surfaces
(1)
Remove sharp edges and blend damage to a 0.05-inch radius and a smooth finish. Rework must not reduce wall thickness by more than 0.025-inch or exceed 30% of the total bearing area of any 90 degree segment.
(2)
If damage exists at the anti-rotation bolt hole, either replace sleeve or contact Boeing for evaluation of possible repair.
500 Allowable Wear Limits of Installed Axle Sleeves
Oct 20/92 Figure 802 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-11-111 Page 803
MAIN GEAR ELECTRICAL HARNESS - REMOVAL/INSTALLATION
1. Remove Electrical Harness (Fig. 401)
A. On airplanes installed with gravel protection shield, remove clamp from shield. Remove shield.
B. Remove antiskid transducer (32-42-11, Removal/Installation) to gain access to connectors.
C. Pull electric connectors out of axle and disconnect wires.
D. Remove fittings (l, 2), washer(s) (4) and expandable fitting (3) from hole in axle (Detail C, Fig. 401).
NOTE: Note number of washers to facilitate reassembly.
E. Remove hose clamps.
NOTE: Do not remove ratchet clamps and tape from hose unless replacement is necessary.
F. Remove hose assembly.
2. Install Electrical Harness (Fig. 401)
A. Position hose assembly on main gear and secure with clamps. Take care that markers V-1 thru V-4 on hose are located correctly in respect to clamp as shown in Fig. 401.
NOTE: Special care must be exercised during installation of this hose to assure a minimum clearance of 1.00 inch with adjacent control cables.
B. If tape needs replacement, wrap two layers of new tape around hose per BAC5801 and to dimensions shown (Detail B, Fig. 401). Overlap wraps by approximately 0.25 inch. Secure ends of taped areas with ratchet clamps. Keep the ratchet portion turned away from gear structure to prevent galling.
C. Slide washer or washers (4) on expandable fitting (3). Position expandable fitting in bore of main gear axle. Insert fitting (2) in expandable fitting with tapered end showing forward. Hold expandable fitting stationary. Screw fitting (l) into expandable fitting and tighten. Check for snug fit of expandable fitting in axle bore. If still loose, add washers.
D. Feed pigtail ends of hose assembly through fittings (l and 2) and through expandable fitting (3) into bore of axle. Pull pigtails out of axle ends and crimp on connector (Detail A, Fig. 401) (Ref Chapter 20). Use sleeves if required to make clamp fit tight.
E. Screw elbow of hose assembly on fitting (l), and tighten. Lockwire fitting to expandable fitting.
F. Reinstall antiskid transducer (Ref 32-42-11, Removal/Installation).
G. On airplane installed with gravel protection shield, install shield. Install clamp on shield.
501
Oct 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-11-121 Page 401
Main Gear Electrical Harness Installation 513
32-11-121 Page 402 Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/76
513 Main Gear Electrical Harness Installation
May 15/78 Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-11-121 Page 403
Main Gear Electrical Harness Installation 501
32-11-121 Page 404 Figure 401 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/76
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