AD 99-21-06 Airworthiness Directives; McDonnell Douglas Model DC-9-81, -82, - 83, and -87 Series Airplanes (MD-81, -82, -83, and -87), and Model MD- 88 Airplanes

Models named: DC-9-81, -82, -83, -87 series, MD-88. Read the applicability below — it usually turns on serial or part numbers too.

All Model DC-9-81, -82, -83, and -87 series airplanes (MD-81, -82, -83, and -87); and Model MD-88 airplanes; 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 (h)(1) 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 inadvertent slat retraction in flight, accomplish the following: Restatement of Certain Requirements of AD 91-21-11, Amendment 39-8058 (a) Prior to the accumulation of 10,000 total landings or within 30 days after October 30, 1991 (the effective date of AD 91-21-11), whichever occurs later, perform a visual or eddy current inspection to detect cracks of the actuator cylinder support brackets of the slat drive mechanism assembly, part numbers 5938886--(any configuration) and 5938887--(any configuration), in accordance with the instructions in McDonnell Douglas MD-80 Alert Service Bulletin A27-322, dated August 22, 1991 (hereinafter referred to as ``A27- 322''). [[Page 54520]] (b) If no crack is found during the inspection required by paragraph (a) of this AD, repeat the inspection at the following intervals: (1) If the immediately preceding inspection was accomplished using visual means, conduct the next inspection within 1,000 landings. (2) If the immediately preceding inspection was accomplished using eddy current means, conduct the next inspection within 3,000 landings. (c) If any crack is found during any inspection required by paragraph (a) or (b) of this AD, prior to further flight, remove and replace the slat drive mechanism with a new part, part numbers 5938887--(any configuration) and 5938886--(any configuration), in accordance with A27-322. New Requirements of This AD Initial and Repetitive Inspections (d) Perform visual and/or eddy current inspections, as applicable, to detect cracks of the actuator cylinder support brackets of the slat drive mechanism assembly, in accordance with McDonnell Douglas Alert Service Bulletin MD80-27A322, Revision 03, dated August 4, 1998, at the time specified in paragraph (d)(1), (d)(2), or (d)(3), as applicable, of this AD. (1) For airplanes on which no inspection has been performed in accordance with AD 91-21-11: Perform both visual and eddy current inspections prior to the accumulation of 10,000 total landings or within 30 days after the effective date of this AD, whichever occurs later. (2) For airplanes on which the immediately preceding inspection was performed using visual means in accordance with AD 91-21-11, accomplish the requirements of paragraphs (d)(2)(i) and (d)(2)(ii) of this AD. (i) Within 1,000 landings after the immediately preceding visual inspection, perform a visual inspection; and (ii) Within 6 months after the last visual inspection required by paragraph (d)(2)(i) of this AD, perform an eddy current inspection. (3) For airplanes on which the immediately preceding inspection was performed using eddy current means in accordance with AD 91-21- 11: Perform an eddy current inspection within 3,000 landings after the last eddy current inspection. (e) If no crack is found during any inspection required by paragraph (d) of this AD, repeat the eddy current inspection thereafter at intervals not to exceed 3,000 landings until the actions specified in paragraph (g) of this AD are accomplished for both actuator cylinder support brackets of the slat drive mechanism assembly. Corrective/Terminating Action (f) If any cracking is found during any inspection required by paragraph (d) or (e) of this AD, prior to further flight, modify the actuator cylinder support bracket of the slat drive mechanism assembly (Option 1 or 2 for Group 1 or 2 airplanes, as applicable) in accordance with McDonnell Douglas Service Bulletin MD80-27-322, Revision 02, dated February 11, 1998, as specified in paragraph (f)(1) or (f)(2), as applicable, of this AD. (1) For airplanes identified as Group 1 in the service bulletin: Accomplish the actions as identified in the service bulletin as Group 1 Option 1 or Group 1 Option 2. (2) For airplanes identified as Group 2 in the service bulletin: Accomplish the actions as identified in the service bulletin as Group 2 Option 1 or Group 2 Option 2. (g) Accomplishment of the modification of the actuator cylinder support bracket specified in paragraph (f) of this AD constitutes terminating action for the repetitive inspections required by this AD, provided that both actuator cylinder support brackets are modified. Alternative Methods of Compliance (h)(1) 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 Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. 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. (2) Alternative methods of compliance, approved previously in accordance with AD 91-21-11, amendment 39-8058, are approved as alternative methods of compliance for this AD. 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 (i) 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 (j) The actions shall be done in accordance with McDonnell Douglas MD-80 Alert Service Bulletin A27-322, dated August 22, 1991; McDonnell Douglas Service Bulletin MD80-27-322, Revision 02, dated February 11, 1998; or McDonnell Douglas Alert Service Bulletin MD80- 27A322, Revision 03, dated August 4, 1998; as applicable. (1) The incorporation by reference of McDonnell Douglas Alert Service Bulletin MD80-27A322, Revision 03, dated August 4, 1998; and McDonnell Douglas Service Bulletin MD80-27-322, Revision 02, dated February 11, 1998, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of McDonnell Douglas MD-80 Alert Service Bulletin A27-322, dated August 22, 1991, was approved previously by the Director of the Federal Register as of October 30, 1991 (56 FR 51645, October 15, 1991). (3) Copies may be obtained from Boeing Commercial Aircraft Group, Long Beach 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. (k) This amendment becomes effective on November 12, 1999. Issued in Renton, Washington, on September 28, 1999. D.L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-25764 Filed 10-6-99; 8:45 am] BILLING CODE 4910-13-U