AD 85-12-01 R1

85-12-01 R1 BOEING: Amendment 39-5073 as amended by Amendment 39-5439. Applies to Model 707/720 series airplanes, certificated in all categories. Compliance is required as indicated in the body of the AD.

To ensure continuing structural integrity, accomplish the following, unless already accomplished:

A. Within 180 days after the effective date of the amendment, incorporate a revision into the FAA-approved maintenance inspection program which requires accomplishment of the inspection and repairs, as necessary, of each Significant Structural Detail (SSD) as listed in Boeing Document D6-44860, Supplemental Structural Inspection Document (SSID), Revision M, or later FAA-approved revision. The revision to the maintenance program must include procedures to notify the manufacturer when SSD's are found cracked. The inspection thresholds, repetitive inspection intervals, inspection techniques, and terminating action for each SSD are listed in the SSID. Incorporate this revision to the maintenance program in accordance with paragraphs B., C., and D., below.

B. The increase of inspection intervals in accordance with Section 5.2 of Boeing Document D6-44860, Revision M, is not permitted, except as provided in paragraphs F. and G., below.

C. Inspect each Significant Structural Detail (SSD) which has exceeded the initial threshold specified in Boeing Document D6-44860, Revision M, within 180 days after the effective date of this amendment. Significant Structural Details which are below the inspection thresholds specified in Boeing Document D6-44860, Revision M, must have an initial inspection within 180 days after the effective date of this amendment or prior to reaching the threshold, whichever is later. Accomplish these inspections in accordance with Boeing Document D6- 44860, Revision M, or later FAA-approved revisions.

D. If cracks are found, prior to further flight: (1) replace with a serviceable FAA approved part of the same part number, or an FAA approved replacement part provided by the manufacturer; or (2) repair in accordance with the Boeing Structural Repair Manual or repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.

E. Aircraft may be ferried to a maintenance base for repair in accordance with FAR 21.197 and 21.199.

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

G. Upon request of the operator, an FAA Principal Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD, if the request contains substantiating data to justify the increase for that operator.

H. Operators who have acceptably incorporated the requirements of paragraphA., above, into their approved maintenance program, including the limitations listed in paragraphs B., C. and D., above, are exempt from the provisions of this AD.

I. Significant Structural Details (SSD) which are the subject of separate AD action are exempted from the requirements of 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 39-5073 became effective July 5, 1985. This amendment, 39-5439, becomes effective November 14, 1986.