AD 98-26-09 Airworthiness Directives; McDonnell Douglas Model DC-9-10, -20, - 30, -40, and -50 Series Airplanes, and C-9 (Military) Airplanes

Models named: DC-9-10, -20, -30, -40, -50 series. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, as listed in McDonnell Douglas Service Bulletin DC9-53-280, Revision 01, dated July 30, 1998; 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 (g) of this AD. The request should include an assessment of [[Page 70008]] 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 doorstops and corners of the doorjamb of the forward passenger door, 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. (a) Prior to the accumulation of 48,000 total landings, or within 3,575 landings after the effective date of this AD, whichever occurs later, perform a one-time visual inspection to determine if the doorstops and corners of the forward passenger door doorjamb have been modified. Perform the inspection in accordance with McDonnell Douglas Service Bulletin DC9-53-280, dated December 1, 1997, or Revision 01, dated July 30, 1998, (b) For airplanes identified as Group 1 in McDonnell Douglas Service Bulletin DC9-53-280, Revision 01, dated July 30, 1998: If the visual inspection required by paragraph (a) of this AD reveals that the doorstops and corners of the forward passenger door doorjamb have not been modified, prior to further flight, perform a low frequency eddy current (LFEC) or x-ray inspection to detect cracks at all corners and doorstops of the forward passenger door doorjamb, in accordance with McDonnell Douglas Service Bulletin DC9- 53-280, dated December 1, 1997, or Revision 01, dated July 30, 1998. (1) Group 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. (i) Option 1. Repeat the LFEC inspection required by this paragraph thereafter at intervals not to exceed 3,575 landings, or the x-ray inspection required by this paragraph thereafter at intervals not to exceed 3,075 landings; or (ii) Option 2. Prior to further flight, modify the doorstops and corners of the forward passenger 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. (A) If no crack is detected on the skin adjacent to the modification during any HFEC inspection required by paragraph (b)(1)(ii) of this AD, repeat the HFEC 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 HFEC inspection required by paragraph (b)(1)(ii) of this AD, 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) Group 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 0.50 inch or less in length: Prior to further flight, modify the doorstops and corners of the forward passenger door doorjamb 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. (i) If no crack is detected on the skin adjacent to the modification during any HFEC inspection required by paragraph (b)(2) of this AD, repeat the HFEC inspection thereafter at intervals not to exceed 20,000 landings. (ii) If any crack is detected on the skin adjacent to the modification during any HFEC inspection required by paragraph (b)(2) of this AD, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. (3) Group 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 0.5 inch in length: Prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. (c) Group 2, Condition 1. For airplanes identified as Group 2 in McDonnell Douglas Service Bulletin DC9-53-280, Revision 01, dated July 30, 1998: If the visual inspection required by paragraph (a) of this AD reveals that the doorstops and corners of the forward passenger door doorjamb have been modified previously in accordance with the McDonnell Douglas DC-9 Structural Repair Manual (SRM), using a steel doubler, accomplish either paragraph (c)(1) or (c)(2) of this AD in accordance with McDonnell Douglas Service Bulletin DC9-53-280, dated December 1, 1997, or Revision 01, dated July 30, 1998. (1) Option 1. Prior to the accumulation of 28,000 landings after accomplishment of the modification, or within 3,500 landings after the effective date of this AD, whichever occurs later, perform a HFEC inspection to detect cracks on the skin adjacent to the modification, in accordance with the service bulletin. (i) If no crack is detected on the skin adjacent to the modification during any HFEC inspection required by paragraph (c)(1) of this AD, repeat the HFEC inspection thereafter at intervals not to exceed 20,000 landings. (ii) If any crack is detected on the skin adjacent to the modification 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. (2) Option 2. Prior to further flight, modify the doorstops and corners of the forward passenger door doorjamb in accordance with the service bulletin. Prior to the accumulation of 28,000 landings after the accomplishment of the modification, perform a HFEC inspection to detect cracks on the skin adjacent to the modification, in accordance with the service bulletin. (i) If no crack is detected on the skin adjacent to the modification during any HFEC inspection required by paragraph (c)(2) of this AD, repeat the HFEC inspection thereafter at intervals not to exceed 20,000 landings. (ii) If any crack is detected on the skin adjacent to the modification during any HFEC inspection required by paragraph (c)(2) of this AD, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. (d) Group 2, Condition 2. For airplanes identified as Group 2 in McDonnell Douglas Service Bulletin DC9-53-280, Revision 01, dated July 30, 1998: If the visual inspection required by paragraph (a) of this AD reveals that the doorstops and corners of the forward passenger door doorjamb have been modified previously in accordance with McDonnell Douglas DC-9 SRM or Service Rework Drawing, using an aluminum doubler, prior to the accumulation of 28,000 landings after the accomplishment of the modification, or within 3,500 landings after the effective date of this AD, whichever occurs later, perform a HFEC inspection to detect cracks on the skin adjacent to the modification, in accordance with McDonnell Douglas Service Bulletin DC9-53-280, dated December 1, 1997, or Revision 01, dated July 30, 1998. (1) If no crack is detected on the skin adjacent to the modification during any HFEC inspection required by paragraph (d) of this AD, repeat the HFEC inspection thereafter at intervals not to exceed 20,000 landings. (2) If any crack is detected on the skin adjacent to the modification during any HFEC inspection required by paragraph (d) of this AD, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. (e) Group 2, Condition 3. For airplanes identified as Group 2 in McDonnell Douglas Service Bulletin DC9-53-280, Revision 01, dated July 30, 1998: If the visual inspection required by paragraph (a) of this AD reveals that the doorstops and corners of the forward passenger door doorjamb have been modified previously, but not in accordance with McDonnell Douglas DC9 SRM or the Service Rework Drawing, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles ACO. (f) Accomplishment of the actions required by this AD constitutes terminating action for inspections of Principal Structural Element (PSE) 53.09.031 (reference McDonnell Douglas Model DC-9 Supplemental Inspection Document) required by AD 96-13- 03, amendment 39-9671. (g) 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 4: Information concerning the existence of approved alternative methods of [[Page 70009]] compliance with this AD, if any, may be obtained from the Los Angeles ACO. (h) 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. (i) Except 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 with McDonnell Douglas Service Bulletin DC9-53-280, dated December 1, 1997; or McDonnell Douglas Service Bulletin DC9-53-280, Revision 01, dated July 30, 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 The Boeing Company, 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. (j) This amendment becomes effective on January 22, 1999. Issued in Renton, Washington, on December 11, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-33389 Filed 12-17-98; 8:45 am] BILLING CODE 4910-13-U