AD 86-17-05 R1

86-17-05 R1 BOEING: Amendment 39-5391 as amended by Amendment 39-5714. Applies to Boeing Model 727-200 series airplanes equipped with the Number 3 cargo door, certificated in any category, listed in Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986.

To detect cracks in the forward frame of the Number 3 cargo door cutout, accomplish the following:

A. Within the next 300 landings after the effective date of this AD or prior to accumulating 29,000 landings, whichever occurs later, unless accomplished within the last 1900 landings, visually inspect the forward frame of the Number 3 cargo door cutout for cracks in accordance with paragraph C. of the Accomplishment Instructions in Boeing Alert Service Bulletin Number 727-53A0169, Revision 2, dated May 23, 1986, or later FAA-approved revisions. If any cracks are detected, repair in accordance with paragraph C. of this AD. Repeat the inspections at intervals not to exceed 2,200 landings.

B. Withinthe next 300 landings after the effective date of this AD or prior to accumulating 35,000 landings, whichever occurs later, unless accomplished within the last 1900 landings, visually inspect the forward frame of the Number 3 cargo door cutout for cracks in accordance with paragraphs D. and E. of the Accomplishment Instructions in Boeing Alert Service Bulletin Number 727-53A0169, Revision 2, dated May 23, 1986, or later FAA-approved revisions. If any cracks are detected, repair in accordance with paragraph C. of this AD. Repeat the inspections at intervals not to exceed 2,200 landings.

C. Repair, prior to further flight, any cracks detected in the forward frame of the Number 3 cargo door cutout, in accordance with paragraph G. of the Accomplishment Instructions in Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986, or later FAA-approved revisions. Reinspect, at intervals not to exceed 2,200 landings, all areas of the forward frame not covered by the repair, in accordance with the Accomplishment Instructions of paragraphs C., D., and E. of Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986, or later FAA-approved revisions.

D. Modification of uncracked frames in accordance with Figure 2 of Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986, or later FAA-approved revisions constitutes terminating action for repetitive inspections required by this AD.

E. Alternate means of compliance or adjustment of compliance time, which provide an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.

F. 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 and/or modifications required by 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 the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

Amendment 39-5391 became effective September 5, 1986, and superseded AD 84-21-04, Amendment 39-4938. This Amendment 39-5714 becomes effective September 3, 1987.