AD 99-19-29 Airworthiness Directives; Boeing Model 767 Series Airplanes

Models named: 767 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 767 series airplanes, line positions 1 through 177 inclusive, certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent cracking of the H-11 tension bolts on the side-of- body kick-load fitting due to stress corrosion, which could result in reduced structural integrity of the wing-to-body joint structure, accomplish the following: (a) Within 90 days after the effective date of this AD: Perform a detailed visual inspection of the four H-11 tension bolts at each side-of-body kick-load fitting located on the wing rear spar to detect damaged or broken bolts; and accomplish the requirements in either paragraph (a)(1) or (a)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-57A0064, Revision 1, dated July 9, 1998. (1) Option 1: Repeat the detailed visual inspection of the bolts at each side-of-body kick-load fitting thereafter at intervals not to exceed 90 days, until accomplishment of the actions specified in paragraph (c) of this AD. Or (2) Option 2: Perform a detailed visual inspection of the four H-11 tension bolts on the lower splice plate located on the wing rear spar to detect damaged or broken bolts. Repeat the detailed inspection of each side-of-body kick-load fitting and the lower splice plate thereafter at intervals not to exceed 18 months, until accomplishment of the actions specified in paragraph (c) of this AD. Note 2: For the purposes of this AD, a detailed visual inspection is defined as: ``An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc. may be used. Surface cleaning and elaborate access procedures may be required.'' (b) If evidence of any damaged or broken bolt is detected, prior to further flight, replace the discrepant bolt with a new, improved bolt in accordance with Boeing Service Bulletin 767-57A0064, Revision 1, dated July 9, 1998. Thereafter, repeat the detailed inspection in either paragraph (a)(1) or (a)(2) of this AD, as applicable, until accomplishment of the actions specified in paragraph (c) of this AD. (c) Within 9,000 flight cycles or 48 months after the effective date of this AD, whichever occurs first, replace all four H-11 tension bolts at each side-of-body kick-load fitting with new, improved bolts, and perform a detailed visual inspection to detect any damaged or broken bolt of the lower splice plate located on the wing rear spar, in accordance with Boeing Service Bulletin 767- 57A0064, Revision 1, dated July 9, 1998. If any damaged or broken bolt is detected during the inspection, prior to further flight, replace the discrepant bolt with a new, improved bolt in accordance with Boeing Service Bulletin 767-57A0064, Revision 1, dated July 9, 1998. Accomplishment of the actions specified in this paragraph constitutes terminating action for the repetitive inspection requirements of this AD. Alternative Methods of Compliance (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permits (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (f) The inspections and replacements shall be done in accordance with Boeing Service Bulletin 767-57A0064, Revision 1, dated July 9, 1998. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 20, 1999. [[Page 49979]] Issued in Renton, Washington, on September 2, 1999. Dorenda D. Baker, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-23471 Filed 9-14-99; 8:45 am] BILLING CODE 4910-13-P