AD 79-19-10

79-19-10 MCDONNELL DOUGLAS: Amendment 39-3566. Applies to the McDonnell Douglas DC-8-62, -62F and DC-8-63, -63F Series airplanes certificated in all categories, incorporating 7079-T6 aluminum wing front spar pylon support fittings, (P/N) 5753054-1/-2 and 5753055-1/-2.

NOTE: This AD is not applicable to 7075-T73 aluminum fittings (P/N) 5753054-501/-502 and 5753055-501/-502. Operators who are unable to verify part numbers visually, may ascertain the fitting material by NDT methods presented in the McDonnell Douglas DC-8 Alert Service Bulletin A57-87, Revision 1, dated September 10, 1979.

Compliance required as indicated.

To detect cracks and prevent failure of the wing front spar pylon support fittings, accomplish the following:

(a) Within the next 300 hours' time in service after the effective date of this AD, unless already accomplished within the last 2,700 hours' time in service in an approved equivalent manner:

(1) Before inspection, thoroughly cleaneach wing front spar pylon support fitting in accordance with the procedures outlined in McDonnell Douglas DC-8 Alert Service Bulletin A57-87 Revision 1, dated September 10, 1979,

(2) Conduct a visual inspection of all four wing front spar pylon support fittings in accordance with the procedures outlined in McDonnell Douglas DC-8 Alert Service Bulletin A57-87, Revision 1, dated September 10, 1979.

(b) If no cracks are found during the inspections per paragraph (a), conduct repetitive inspections in accordance with paragraph (a) at intervals not to exceed 3,000 hours' time in service or one (1) year, whichever comes first.

(c) If cracks are found which are repairable as defined in McDonnell Douglas DC-8 Alert Service Bulletin A57-87, Revision 1, dated September 10, 1979, make repairs per DC-8 Structural Repair Manual, Chapter 54 or McDonnell Douglas DC-8 Alert Service Bulletin A57-87, Revision 1, as applicable prior to further flight, and revert to the repetitive inspection requirements of paragraph (b).

(d) If cracks are found which are defined as non-repairable in McDonnell Douglas DC-8 Alert Service Bulletin A57-87, Revision 1, dated September 10, 1979, remove and replace the fitting prior to further flight.

(e) If a cracked fitting is replaced with a 7079-T6 aluminum fitting, inspect the replacement fitting in accordance with the repetitive inspection requirements of paragraph (b).

(f) Within 24 hours after the inspection, report the results of the inspection per paragraph (a) to the Chief, Aircraft Engineering Division, FAA Western Region, through the principal maintenance inspector for the operator.

(g) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD.

(h) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.

This amendment becomes effective September 27, 1979.