AD 80-08-10 R1

80-08-10 R1 BOEING: Amendment 39-3752 as amended by Amendment 39-3830. Applies to all 707/720 series and 727 series airplanes with main deck cargo doors, certificated in all categories. Compliance required as indicated.

To detect cracks in the main deck cargo door cam fittings, accomplish the following:

A. Within the initial compliance times specified below, eddy current inspect all eight (8) main cargo door cam support fittings for cracks in accordance with Boeing Alert Service Bulletin Numbers 707-A3387 and 727-52-A124, as applicable, or later FAA approved revisions, or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Compliance required for aircraft which have accumulated on the effective date of this AD:

1. 30,000 or more landings - within 250 landings after the effective date unless accomplished within the last 750 landings;

2. 20,000 or more landings, but less than 30,000 landings - within 500 landings unless accomplished within the last 500 landings;

3. Less than 20,000 landings - prior to the accumulation of 20,500 landings.

B. Repeat the inspection in accordance with Paragraph A of this AD at intervals not to exceed 1,000 landings.

C. Cracked fittings must be replaced prior to further flight or repaired in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Repaired fittings must be inspected in accordance with Paragraph B of this AD. Replacement fittings must be inspected as follows:

1. Unmodified fittings (Boeing part numbers 69-23588-1 or -2) must be inspected in accordance with paragraph A of this AD prior to the accumulation of 20,000 landings and thereafter at intervals not to exceed 1,000 landings.

2. Fittings modified in accordance with Boeing Service Bulletin Numbers 707/720-A3387, Revision 1, dated June 3, 1980, or 727-52A124, Revision 1, dated June 3, 1980, or later FAA approved revisions, must be inspected in accordance with paragraph A of this AD prior to the accumulation of 30,000 landings after rework and thereafter at intervals not to exceed 1,000 landings.

D. Aircraft with less than five (5) cracked fitting(s) may be ferried unpressurized to a maintenance base for replacement in accordance with FAR 21.197.

E. For the purpose of complying with this AD, pressurization cycles may be substituted for landings, if an operator has complete records of pressurization cycles.

F. Terminating action for this AD consists of replacement of existing main deck cargo door cam support fittings with improved design fittings (Boeing part numbers 69-23588-5 or -6) in accordance with paragraph III of Boeing Service Bulletins 707/720-A3387, Revision 1, dated June 3, 1980, or 727-52A124, Revision 1, dated June 3, 1980, or later FAA approved revisions or a method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).

All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108.

Amendment 39-3752 became effective April 20, 1980.

This Amendment 39-3830 becomes effective July 15, 1980.