98-23-11: Forward Service Door Doorjamb

98-23-11 MCDONNELL DOUGLAS: Amendment 39-10877. Docket 97-NM-99-AD. \n\n\tApplicability: Model DC-9-31 series airplanes, as listed in McDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997, certificated in any category. \n\n\tNOTE 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 (g) 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. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo detect and correct fatigue cracking in the fuselage skin or doubler at the corners of the forward service door doorjamb, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane, accomplish the following: \n\n\tNOTE 2: Where there are differences between the service bulletin and the AD, the AD prevails. \n\n\tNOTE 3: The words "repair" and "modify/modification" in this AD and the referenced service bulletin are used interchangeably. \n\n\t(a)\tPrior to the accumulation of 50,000 total landings, or within 3,225 landings after the effective date of this AD, whichever occurs later, perform a one-time visual inspection to determine if the corners of the forward service door doorjamb have been modified. Perform the inspection in accordance with McDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997. \n\n\t(b)\tFor airplanes identified as Group 1 in McDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997: If the visual inspection required by paragraph (a) of this AD reveals that the corners of the forward service door doorjamb have not been modified, prior to further flight, perform a low frequency eddy current (LFEC) or x-ray inspection to detect cracks of the fuselage skin and doubler at all corners of the forward service door doorjamb, in accordance with McDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997. \n\n\t\t(1)\tGroup 1, Condition 1. If no crack is detected during any LFEC or x-ray inspection required by paragraph (b) of this AD, accomplish the requirements of either paragraph (b)(1)(i) or (b)(1)(ii) of this AD, in accordance with the service bulletin. \n\n\t\t\t(i)\tOption 1. Repeat the LFEC inspection required by this paragraph thereafter at intervals not to exceed 3,225 landings, or the x-ray inspection required by this paragraph thereafter at intervals not to exceed 3,075 landings; or \n\n\t\t\t(ii)\tOption 2. Prior to further flight, modify the corner skin of the forward service door doorjamb in accordance with the service bulletin. Prior to the accumulation of 28,000 landings after accomplishment of the modification, perform a high frequency eddy current (HFEC) inspection to detect cracks on the skin adjacent to the modification, in accordance with the service bulletin. \n\n\t\t\t\t(A)\tIf no crack is detected on the skin adjacent to the modification during the HFEC required by this paragraph, repeat the HFEC inspection thereafter at intervals not to exceed 20,000 landings. \n\n\t\t\t\t(B)\tIf any crack is detected on the skin adjacent to the modification during any HFEC 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. \n\n\t\t(2)\tGroup 1, Condition 2. If any crack is found during any LFEC or x-ray inspection required by paragraph (b) of this AD, and the crack is 2 inches or less in length: Prior to further flight, modify/repair the corners of the doorjamb of the forward service door in accordance with the service bulletin. Prior to the accumulation of 28,000 landings after accomplishment of the modification, perform a HFEC inspection to detect cracks on the skin adjacent to the modification, in accordance with the service bulletin. \n\n\t\t\t(i)\tIf no crack is detected during the HFEC inspection required by this paragraph, repeat the HFEC inspection thereafter at intervals not to exceed 20,000 landings. \n\n\t\t\t(ii)\tIf any crack is detected during any HFEC inspection required by this paragraph, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. \n\n\t\t(3)\tGroup 1, Condition 3. If any crack is found during any LFEC or x-ray inspection required by paragraph (b) of this AD, and the crack is greater than 2 inches in length: Prior to further flight, repair itin accordance with a method approved by the Manager, Los Angeles ACO. \n\n\t(c)\tGroup 2, Condition 1. For airplanes identified as Group 2 in McDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997: If the visual inspection required by paragraph (a) of this AD reveals that the corners of the forward service door doorjamb have been modified previously in accordance with the McDonnell Douglas DC-9 Structural Repair Manual, using a steel doubler, accomplish either paragraph (c)(1) or (c)(2) of this AD in accordance with McDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997. \n\n\t\t(1)\tOption 1. Prior to the accumulation of 6,000 landings after accomplishment of that modification, or within 3,225 landings after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks on the skin adjacent to the modification, in accordance with the service bulletin. \n\n\t\t\t(i)\tIf no crack is detected during the HFEC inspection required by paragraph (c)(1) of this AD, repeat the HFEC inspection thereafter at intervals not to exceed 3,000 landings. \n\n\t\t\t(ii)\tIf any crack is detected during any HFEC inspection required by paragraph (c)(1) of this AD, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. \n\n\t\t(2)\tOption 2. Prior to further flight, modify the corner skin of the forward service door doorjamb in accordance with the service bulletin. Prior to the accumulation of 28,000 landings after accomplishment of the modification, perform an HFEC inspection to detect cracks on the skin adjacent to the modification, in accordance with the service bulletin. \n\n\t\t\t(i)\tIf no crack is detected on the skin adjacent to the modification during the HFEC required by this paragraph, repeat the HFEC inspection thereafter at intervals not to exceed 20,000 landings. \n\n\t\t\t(ii)\tIf any crack is detected on the skin adjacent to the modification during any HFEC inspection required by this paragraph, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. \n\n\t(d)\tGroup 2, Condition 2. For airplanes identified as Group 2 in McDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997: If the visual inspection required by paragraph (a) of this AD reveals that the corners of the forward service door doorjamb have been modified previously in accordance with McDonnell Douglas DC-9 Structural Repair Manual, using an aluminum doubler, prior to the accumulation of 28,000 landings after accomplishment of that modification, or within 3,225 landings after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks on the skin adjacent to the modification, in accordance with McDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997. \n\n\t\t(1)\tIf no crack is detected on the skin adjacent to the modification during the HFEC required by this paragraph, repeat theHFEC inspection thereafter at intervals not to exceed 20,000 landings. \n\n\t\t(2)\tIf any crack is detected on the skin adjacent to the modification during any HFEC inspection required by this paragraph, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. \n\n\t(e)\tGroup 2, Condition 3. For airplanes identified as Group 2 in McDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997: If the visual inspection required by paragraph (a) of this AD reveals that the corners of the forward service door doorjamb have been modified previously, but not in accordance with McDonnell Douglas Structural Repair Manual, prior to further flight, repair the corners in accordance with a method approved by the Manager, Los Angeles ACO. \n\n\t(f)\tAccomplishment of the actions required by this AD constitutes terminating action for inspections of Principal Structural Element (PSE) 53.09.033 (reference McDonnell Douglas Model DC-9 Supplemental Inspection Document) required by AD 96-13-03, amendment 39-9671. \n\n\t(g)\tAn 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. \n\n\tNOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. \n\n\t(h)\tSpecial 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. \n\n\t(i)\tExcept as provided by paragraphs (b)(1)(ii)(B), (b)(2)(ii), (b)(3), (c)(1)(ii), (c)(2)(ii), (d)(2), and (e) of this AD, the actions shall be done in accordance withMcDonnell Douglas Service Bulletin DC9-53-288, dated February 10, 1997. 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 McDonnell Douglas Corporation, 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. \n\n\t(j)\tThis amendment becomes effective on December 17, 1998.