AD 96-07-51 Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes

Models named: DC-9 series. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-9 series airplanes having fuselage numbers 001 through 631, inclusive; 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.

Required as indicated, unless accomplished previously. To prevent rapid decompression of the fuselage, significant structural damage, and subsequent reduced structural integrity of the airplane, due to problem associated with corrosion and fatigue cracking, accomplish the following: (a) Within 15 days after the effective date of this AD: Perform an internal visual inspection to detect corrosion and cracking of the fuselage forward upper skin and to detect cracking of the fuselage frame in the area of the loop antenna assemblies of the forward and aft automatic direction finder (ADF), in accordance with McDonnell Douglas Alert Service Bulletin DC9-53A282, dated March 20, 1996. (1) If no corrosion or cracking is detected: Repeat the inspections required by paragraph (a) of this AD thereafter at intervals not to exceed six months. (2) If any corrosion or cracking is detected that is within the limits specified in Chapter 53-04, Figure 29, of the DC-9 Structural Repair Manual (SRM): Prior to further flight, repair in accordance with Chapter 53-04, Figure 29, of the SRM. Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed six months. (3) If any corrosion or cracking is detected in the fuselage forward upper skin, or if any cracking is detected in the fuselage frame, and that corrosion or cracking is outside the limits specified in Chapter 53-04, Figure 29, of the SRM: Prior to further flight, repair in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (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 ACO, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may [[Page 15884]] 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. (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. (d) The inspections shall be done in accordance with McDonnell Douglas Alert Service Bulletin DC9-53A282, dated March 20, 1996. 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, Dept. C1-L51 (2-60). This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on April 15, 1996, to all persons except those persons to whom it was made immediately effective by telegraphic AD T96-07-51, issued on March 22, 1996, which contained the requirements of this amendment. Issued in Renton, Washington, on March 28, 1996. Bill R. Boxwell, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 96-8583 Filed 4-9-96; 8:45 am] BILLING CODE 4910-13-U