88-17-06 BOEING: Amendment 39-5988. Applies to Model 727 series airplanes, except Model 727-200F, certificated in any category. \n\n\tCompliance required as indicated, unless previously accomplished. \n\n\tTo ensure the structural integrity of the wing upper surface stringers, accomplish the following: \n\n\tA.\tUsing eddy current, x-ray, or visual inspection techniques, inspect wing upper surface stringers for cracks, in accordance with Boeing Alert Service Bulletin 727-57A159, Revision 1, dated October 29, 1982, as follows: \n\n\t\t1.\tFor airplanes with 45,000 or more landings on August 16, 1983, inspect prior to the accumulation of 1,000 additional landings after August 16, 1983. \n\n\t\t2.\tFor airplanes with at least 40,000 and less than 45,000 landings on August 16, 1983, inspect prior to the accumulation of 2,000 additional landings after August 16, 1983. \n\n\t\t3.\tFor all other airplanes, inspect prior to the accumulation of 3,000 additional landings after August 16, 1983, or priorto accumulating 33,000 total landings, whichever occurs later. \n\n\tB.\tRepeat the inspections required by paragraph A., above, and, if applicable, paragraph C., below, at the following intervals: \n\n\t\t1.\tIf the immediately preceding inspection was performed using eddy current methods, reinspect within the next 22,000 landings. \n\n\t\t2.\tIf the immediately preceding inspection was performed using x-ray or visual methods, reinspect within the next 11,000 landings. \n\n\tC.\tIf cracks are detected during the inspections required by paragraph A. or B., above, unless previously accomplished, inspect the stringer-to-rib attachment at wing stations (WS) 519.0 and 546.5 for cracks, using eddy current, x-ray, or visual techniques, in accordance with Boeing Alert Service Bulletin 727-57A159, Revision 3, dated September 18, 1986, in accordance with the following schedule: \n\n\t\t1.\tPrior to the accumulation of 4,500 landings after the effective date of this AD, for airplanes on which cracks have been detected prior to the effective date of this AD. \n\n\t\t2.\tPrior to further flight, for airplanes on which cracks have been detected after the effective date of this AD. \n\n\tD.\tAny cracked structure detected as a result of the inspections required by paragraphs A., B., C., E., or F. of this AD, must be repaired prior to further flight, in accordance with a procedure listed in Boeing Alert Service Bulletin 727-57A159, Revision 3, dated September 18, 1986. Repair or modification in accordance with Boeing Alert Service Bulletin 727-57A159, Revision 3, dated September 18, 1986, eliminates the repetitive inspection requirements of paragraph B., above, and constitutes terminating action for only those attachments so repaired or modified. \n\n\tE.\tWithin the next 4,500 landings after the effective date of this AD, unless previously accomplished in accordance with Boeing Service Bulletin 727-57A159, Revision 3, dated September 18, 1986, inspect and modify stringers (excluding stringer tabs)previously repaired utilizing the preventative modification in accordance with Figure 12 of Boeing Service Bulletin 727-57A159, Revision 1, dated October 29, 1982, or Revision 2, dated March 30, 1984. \n\n\tF.\tFor airplanes with affected wing stringer rib attach locations previously repaired in accordance with Structural Repair Manual Subject 57-10-4 or any other FAA-approved method (except those identified in paragraph E., above), that have accumulated 22,000 landings prior to August 16, 1983, inspect in accordance with paragraph A., above, within the next 11,000 landings after August 16, 1983, or prior to the accumulation of 33,000 landings since repair, whichever occurs later, and thereafter at intervals in accordance with paragraph B. of this AD. \n\n\tG.\tSpecial 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. \n\n\tH.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, 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 Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment supersedes AD 83-13-03, Amendment 39-4673. \n\tThis amendment, 39-5988, becomes effective September 5, 1988.