AD 96-23-07 Airworthiness Directives; McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes

Models named: MD-88. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87) series airplanes and Model MD-88 airplanes, as listed in McDonnell Douglas MD-80 Service Bulletin 57-184, Revision 1, dated December 22, 1994; 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 prevent fatigue cracking in the vertical leg of the rear spar lower cap of the wing, which could lead to reduced structural integrity of the wing, accomplish the following: Note 2: Actions specified in this AD that have been performed prior to the effective date in accordance with McDonnell Douglas MD- 80 Service Bulletin 57-184, dated March 16, 1989, are considered acceptable for compliance with the applicable requirement of this AD. (a) Visual/Dye Penetrant Inspection and Ultrasonic Inspection. Perform visual/dye penetrant and ultrasonic inspections to detect cracks in the vertical leg of the rear spar lower cap of the wings below and in the adjacent area of the two lower attaching stud holes for the inboard hinge fitting of the outboard flap at station Xrs=164.000, in accordance with McDonnell Douglas MD-80 Service Bulletin 57-184, Revision 1, dated December 22, 1994; at the time specified in paragraph (a)(1), (a)(2), (a)(3), or (a)(4) of this AD, as applicable. (1) For airplanes that have accumulated less than 8,000 total landings as of December 19, 1996, (the effective date of AD 96-23- 01): Perform the inspection prior to the accumulation of 10,000 landings or within 3,000 landings after December 19, 1996, whichever occurs later. (2) For airplanes that have accumulated 8,000 or more total landings but less than 10,000 total landings as of December 19, 1996: Perform the inspection within 3,000 landings after December 19, 1996. (3) For airplanes that have accumulated 10,000 or more total landings but less than 15,000 total landings as of December 19, 1996: Perform the inspection within 2,400 landings after December 19, 1996. (4) For airplanes that have accumulated 15,000 or more total landings as of December 19, 1996: Perform the inspection within 1,800 landings after December 19, 1996. (b) Condition 1 (No Cracks). If no crack is detected during any 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 MD-80 Service Bulletin 57-184, Revision 1, dated December 22, 1994. (1) Condition 1, Option 1 (Terminating Action). Prior to further flight, tighten the four mounting studs of the flap hinge fitting in the rear spar caps (2 studs in the upper cap and 2 studs in the lower cap) to the applicable torque value, in accordance with the service bulletin. Accomplishment of this tightening of the mounting studs of the flap hinge fitting constitutes terminating action for the repetitive inspection requirements of paragraph (b)(2) of this AD. (2) Condition 1, Option 2 (Repetitive Inspection). Repeat the visual/dye penetrant and ultrasonic inspections required by paragraph (a) of this AD thereafter at intervals not to exceed 3,000 landings until paragraph (b)(1) of this AD is accomplished. (c) Condition 2 (Cracks). If any crack is detected during any inspection required by paragraph (a) or (b)(2) of this AD, prior to further flight, perform a high frequency eddy current inspection to confirm the existence of cracking, in accordance with McDonnell Douglas MD-80 Service Bulletin 57-184, Revision 1, dated December 22, 1994. After this inspection, accomplish the requirements of either paragraph (c)(1), (c)(2), or (c)(3) of this AD, as applicable. (1) No Cracking Confirmed. If no cracking is confirmed, accomplish the requirements of either paragraph (b)(1) [``Condition 1, Option 1 (Terminating Action)''] or (b)(2) [``Condition 1, Option 2 (Repetitive Inspection)''] of this AD. (2) Condition 2, Option 1 (Permanent Repair). If any cracking is confirmed, prior to further flight, replace the entire spar cap or accomplish the permanent splice repair of the spar cap, and tighten the four mounting studs of the flap hinge fitting in the rear spar caps (2 studs in the upper cap and 2 studs in the lower cap) to the applicable torque value, in accordance with the service bulletin. Accomplishment of this tightening of the mounting studs constitutes terminating action for the repetitive inspection requirements of paragraph (c)(3) of this AD. (3) Condition 2, Option 2 (Temporary Repair). If cracking is confirmed and it does not extend beyond the location limits and does not exceed the maximum permissible crack length of 2 inches, prior to further flight, accomplish the temporary repair modification of the spar cap in accordance with the service bulletin. Thereafter, repeat the eddy current inspection at intervals not to exceed 3,000 landings until paragraph (c)(2) of this AD is accomplished. (i) If any crack progression is found during any repetitive eddy current inspection following accomplishment of the temporary repair, prior to further flight, contact the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate, telephone (562) 627-5237, fax (562) 627-5210, to establish the appropriate repair or replacement interval. Note 3: Operators should note that, unlike the recommended compliance time of ``within 3,000 landings after discovery of cracking,'' which is specified in the service bulletin as the time for accomplishing the permanent splice repair or replacement of the spar cap, this AD requires that operators contact the FAA prior to further flight. The FAA finds that the repair/replacement interval should be established based on the crack progression. Where there are differences between the AD and the service bulletin in this regard, the AD prevails. (ii) If any new crack is found during any repetitive eddy current inspection following accomplishment of the temporary repair, prior to further flight, accomplish the permanent repair in accordance with the service bulletin. (d) Reporting Requirement. Within 10 days after accomplishing the initial visual/dye penetrant and ultrasonic inspections required by paragraph (a) of this AD, submit a report of the inspection results (both positive and negative findings) to the Manager, Los Angeles ACO, FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5237; fax (562) 627-5210. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120- 0056. (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. [[Page 44211]] Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (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. (g) The actions shall be done in accordance with McDonnell Douglas MD-80 Service Bulletin 57-184, Revision 1, dated December 22, 1994. This incorporation by reference was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of December 19, 1996 (61 FR 58323, November 14, 1996). 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, 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 September 4, 1997. Issued in Renton, Washington, on August 13, 1997. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 97-22042 Filed 8-19-97; 8:45 am] BILLING CODE 4910-13-U