AD 93-09-10

93-09-10 MCDONNELL DOUGLAS: Amendment 39-8576. Docket 92-NM-124-AD.

Applicability: All Model DC-8 series airplanes, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent the loss of main landing gear braking effectiveness, accomplish the following:

(a) Within 180 days after the effective date of this AD, inspect the main landing gear brakes having the part numbers indicated below to determine wear. Any brake worn more than the maximum wear limit specified below must be replaced, prior to further flight, with a brake that is within this limit.

Douglas Brake Part Number Bendix Part Number Maximum Wear Limit (inches) 5610206-5001 150787-1 150787-2 0.7 0.7

5713612-5001 151882-1 151882-2 0.7 0.7

5773335-5001 154252-1 0.5

5773335-5501 154252-2 0.5

5759262-5001 2601412-1 2601412-2* 0.5 0.75

* Brakes having this part number include part number 2601412-1 brakes that have been modified in accordance with McDonnell Douglas Service Bulletin 32-181, dated October 29, 1992.

(b) Within 180 days after the effective date of this AD, incorporate the maximum brake wear limits specified in paragraph (a) of this AD into the FAA-approved maintenance inspection program.

(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO.

NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO.

(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane toa location where the requirements of this AD can be accomplished.

(e) This amendment becomes effective on June 21, 1993.