AD 89-10-04

89-10-04 McDONNELL DOUGLAS: Amendment 39-6204.

Applicability: Model DC-8 series airplanes, equipped with left (LH) or right (RH) main landing gear (MLG) attach fitting, P/N(s) 5611425-1 through -508, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent severe structural damage to the airplane during takeoff or landing due to stress corrosion failure of the MLG attach fittings, accomplish the following:

A. Within the next 12 calendar months after the effective date of this AD, unless already accomplished within the last 12 calendar months, and thereafter at intervals not to exceed 24 calendar months, except as provided below, perform a visual inspection of the MLG attach fittings for cracks at locations in accordance with Figure 1. of McDonnell Douglas DC-8 Service Bulletin 57-94, Revision 1, dated June 23, 1987 (hereafter referred to as the Service Bulletin).

B. If no cracks are found, apply LPS-3 corrosion inhibiting oil to the fitting in accordance with the Service Bulletin, and repeat inspections for cracks in accordance with paragraph A. of this AD.

C. If cracks are found, accomplish the following:

1. If cracks are located in area 1 or 3, as defined in Figure 1. of the Service Bulletin, before further flight, replace the fitting, P/N(s) 5611425-1, -2, -501, -502, -503, -504, -505, -506, -507, or -508, with respective P/N(s) 5893930-1, -2, -1, -2, -509, -510, -507, -508, -505, or -506.

2. If cracks are located in area 2, as defined in Figure 1. of the Service Bulletin, accomplish the following:

a. If cracks are within limits as prescribed by Figure 1. of the Service Bulletin, apply LPS-3 corrosion inhibiting oil to the fitting in accordance with the Service Bulletin, and repeat visual inspections for crack development at intervals not to exceed 7 calendar days, in accordance with the Service Bulletin.

b. If cracks exceed limits as prescribed by Figure 1. of the Service Bulletin, replace the fitting in accordance with paragraph C.1. of this AD before further flight.

D. Replacement of both the LH and RH MLG attach fittings in accordance with paragraph C.1. of this AD constitutes terminating action for the inspection requirements of this AD.

E. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspection (PMI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office.

F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-LOO (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring, Long Beach, California.

This amendment (39-6204, AD 89-10-04) becomes effective on May 29, 1989.