AD 98-18-22 Airworthiness Directives; McDonnell Douglas Model DC-9-10, -15, and -30 Series Airplanes, and C-9 (Military) Airplanes

Models named: DC-9-10, -15, -30 series. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-9-10, -15, and -30 series airplanes, and C-9 (military) airplanes; as listed in McDonnell Douglas Service Bulletin DC9-53-276, dated September 30, 1996; 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 been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To detect and correct fatigue cracking in the fuselage skin or doubler at the corners of the upper cargo doorjamb, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane, accomplish the following: Note 2: Where there are differences between the service bulletin and the AD, the AD prevails. Note 3: The words ``repair'' and ``modify/modification'' in this AD and the referenced service bulletin are used interchangeably. Note 4: This AD will affect principal structural element (PSE) 53.09.023 of the DC-9 Supplemental Inspection Document (SID). (a) Prior to the accumulation of 41,000 total landings, or within 3,000 landings after the effective date of this AD, whichever occurs later, perform a one-time visual inspection to determine if the corners of the upper cargo doorjamb have been modified prior to the effective date of this AD. (b) If the visual inspection required by paragraph (a) of this AD reveals that the corners of the upper cargo doorjamb have not been modified, prior to further flight, perform an x-ray inspection to detect cracks of the fuselage skin and doubler at all corners of the upper cargo doorjamb, in accordance with McDonnell Douglas Service Bulletin DC9-53-276, dated September 30, 1996. (1) If no crack is detected during the x-ray inspection required by this paragraph, accomplish the requirements of either paragraph (b)(1)(i) or (b)(1)(ii) of this AD, in accordance with McDonnell Douglas Service Bulletin DC9-53-276, dated September 30, 1996. (i) Option 1. Repeat the x-ray inspection required by paragraph (b) of this AD thereafter at intervals not to exceed 3,000 landings; or (ii) Option 2. Prior to further flight, modify the corner skin of the upper cargo doorjamb, in accordance with the service bulletin. Prior to the accumulation of 28,000 landings after accomplishment of the modification, perform an eddy current inspection to detect cracks on the skin adjacent to the modification, in accordance with the service bulletin. (A) If no crack is detected on the skin adjacent to the modification during the eddy current inspection required by this paragraph, repeat the eddy current inspection thereafter at intervals not to exceed 20,000 landings. (B) If any crack is detected on the skin adjacent to the modification during any eddy current inspection required by this paragraph, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (2) If any crack is found during any x-ray inspection required by this paragraph and the crack is 2 inches or less in length: Prior to further flight, modify/repair it in accordance with the service bulletin. Prior to the accumulation of 28,000 landings after accomplishment of the modification, perform an eddy current inspection to detect cracks on the skin adjacent to the modification, in accordance with the service bulletin. (i) If no crack is detected during the eddy current inspection required by this paragraph, repeat the eddy current inspection thereafter at intervals not to exceed 20,000 landings. (ii) If any crack is detected during any eddy current inspection required by this paragraph, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. (3) If any crack is found during any x-ray inspection required by this paragraph and the crack is greater than 2 inches in length: Prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. (c) If the visual inspection required by paragraph (a) of this AD reveals that the corners of the upper cargo doorjamb have been modified previously: Prior to the accumulation of 28,000 landings after accomplishment of that modification, or within 3,000 landings after the effective date of this AD, whichever occurs later, perform an eddy current inspection to detect cracks on the skin adjacent to the modification, in accordance with McDonnell Douglas Service Bulletin DC9-53-276, dated September 30, 1996. (1) If no crack is detected during the eddy current inspection required by this paragraph, repeat the eddy current inspection thereafter at intervals not to exceed 20,000 landings. (2) If any crack is detected during any eddy current inspection required by this paragraph, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. (d) Accomplishment of the actions required by this AD constitutes terminating action only for certain requirements of AD 96-13-03, amendment 39-9671 (61 FR 31009, dated June 19, 1996), with respect to PSE 53.09.023, of DC-9 Supplemental Inspection Document (SID) L26-008. (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 5: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Los Angeles ACO. (f) Special flight permits may be issued in accordance with Secs. 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. (g) Except as provided in paragraphs (a), (b)(1)(ii)(B), (b)(2)(ii), (b)(3), and (c)(2) of this AD, the actions shall be done in accordance with McDonnell Douglas Service Bulletin DC9-53-276, dated September 30, 1996. 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 The Boeing Company, Douglas Products Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Technical Publications Business Administration, Department 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) This amendment becomes effective on October 20, 1998. Issued in Renton, Washington, on August 28, 1998. Vi L. Lipski, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-24246 Filed 9-14-98; 8:45 am] BILLING CODE 4910-13-P