Airworthiness directives › 2000-22-20
AD 2000-22-20 Airworthiness Directives; McDonnell Douglas Model DC-9-10, -9-20, -9-30, -9-40, and -9-50 Series Airplanes and C-9 (Military) Airplanes
Models named: DC-9-10, -9-20, -9-30, -9-40, -9-50 series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model DC-9-10, -9-20, -9-30, -9-40, and -9-50 series airplanes and C-9 (military) airplanes, as listed in Boeing Alert Service Bulletin DC9-57A218, dated September 20, 2000; 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 (b) 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.
Compliance
Required as indicated, unless accomplished previously. To prevent failure of the outboard flap idler hinge fitting due to fatigue cracking, which could result in a deflected flap that may cause an asymmetric lift and consequent reduced controllability and structural integrity of the airplane, accomplish the following: Measurement (a) Before the accumulation of 24,000 total landings, or within 90 days after the effective date of this AD, whichever occurs later, measure the diameter of the hole counterbore of the outboard idler hinge fitting of the left and right wing flap, per Boeing Alert Service Bulletin DC9-57A218, including Appendix, dated September 20, 2000. Acceptable Measurement of 0.875 (\7/8\) Inch: Installation of Certain Parts (1) If the diameter of any hole counterbore is 0.875 (\7/8\) inch, before further flight, install a new nut, plain washer, and PLI washer, per the service bulletin. Unacceptable Measurement of 1.125 (1\1/8\) Inches: Repetitive Inspections and Corrective Actions, If Necessary (2) If the diameter of any hole counterbore is 1.125 (1\1/8\) inches, before further flight, do a high frequency eddy current inspection (HFEC) to detect cracks at the flap idler hinge fitting, per the service bulletin. (i) Condition 1. If no crack is detected, before further flight, install a new nut, plain washer, and PLI washer, per the service bulletin. Repeat the HFEC inspection every 1,000 landings until the replacement specified in paragraph (a)(2)(ii) has been done. (ii) Condition 2. If any crack is detected, before further flight, replace the flap idler hinge fitting with a new like part, per the service bulletin. Within 24,000 landings after accomplishment of the replacement, do the HFEC inspection required by paragraph (a)(2) of this AD. Alternative Methods of Compliance (b) 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. 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 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 (c) 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 (d) The actions shall be done in accordance with Boeing Alert Service Bulletin DC9-57A218, including Appendix, dated September 20, 2000. 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 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, 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. Effective Date (e) This amendment becomes effective on November 29, 2000. Issued in Renton, Washington, on November 1, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00-28480 Filed 11-13-00; 8:45 am] BILLING CODE 4910-13-U
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1