AD 99-08-05 Airworthiness Directives; McDonnell Douglas Model DC-9 and C-9 (Military) Series Airplanes

Model DC-9 and C-9 (military) series airplanes, as listed in McDonnell Douglas Service Bulletin DC9-53-267, dated October 20, 1997; 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 (e) 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 [[Page 29778]] been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent fatigue cracking of the fuselage frames and longerons 16R and 17R, which could result in reduced structural integrity of the airplane, accomplish the following: (a) Prior to the accumulation of 30,000 total landings, or within 3,000 landings after the effective date of this AD, whichever occurs later, perform a visual inspection to detect fatigue cracking of the fuselage frames and longerons 16R and 17R above the forward lower cargo door, in accordance with paragraph 3.B.1. of the Accomplishment Instructions of McDonnell Douglas Service Bulletin DC9-53-267, dated October 20, 1997. (b) Condition 1. If no cracking is detected during the inspection required by paragraph (a) of this AD, accomplish the requirements of either paragraph (b)(1) or (b)(2) of this AD, in accordance with McDonnell Douglas Service Bulletin DC9-53-267, dated October 20, 1997. (1) Option 1. Repeat the visual inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 19,000 landings. Or (2) Option 2. Prior to further flight, modify the fuselage frames and longerons 16R and 17R. Prior to the accumulation of 19,000 landings after accomplishment of the modification, perform the visual inspection specified in paragraph 3.B.1.D. of the Accomplishment Instructions of the service bulletin to detect fatigue cracking of the skin adjacent to the modification. (i) If no cracking is detected, repeat the visual inspection thereafter at intervals not to exceed 19,000 landings. (ii) If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (c) Condition 2. If any cracking is detected during the inspection required by paragraph (a) of this AD, prior to further flight, repair the cracked area and modify the fuselage frames and longerons 16R and 17R; in accordance with McDonnell Douglas Service Bulletin DC9-53-267, dated October 20, 1997. Prior to the accumulation of 19,000 landings after accomplishment of the modification, perform the visual inspection specified in paragraph 3.B.1.D.(5) of the Accomplishment Instructions of the service bulletin to detect fatigue cracking of the skin adjacent to the modification, in accordance with the service bulletin. (1) If no cracking is detected, repeat the visual inspection thereafter at intervals not to exceed 19,000 landings. (2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, Los Angeles ACO. (d) Accomplishment of the inspections required by this AD constitutes terminating action for the inspections of Principal Structural Element 53.09.055A (reference McDonnell Douglas Model DC- 9 Supplemental Inspection Document, Report No. L26-008, Section 2 of Volume I, Revision 5, dated July 1997), as required by AD 96-13-03, amendment 39-9671. Alternative Methods of Compliance (e) 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, Los Angeles ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. Special Flight Permits (f) 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 (g) Except as provided by paragraphs (b)(2)(ii) and (c)(2) of this AD, the actions shall be done in accordance with McDonnell Douglas Service Bulletin DC9-53-267, dated October 20, 1997. The incorporation by reference of this document was approved previously by the Director of the Federal Register as of May 12, 1999 (64 FR 16805, April 7, 1999). Copies may be obtained from Boeing Commercial Aircraft Group, Douglas Products Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Technical Publications Business Administration, Dept. C1-L51 (2-60). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) The effective date of this amendment remains May 12, 1999. Issued in Renton, Washington, on May 14, 1999. Donald E. Gonder, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-12829 Filed 6-2-99; 8:45 am] BILLING CODE 4910-13-P