AD 2003-08-08 Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F Airplanes

The following airplanes listed in Table 1 of this AD, certificated in any category: Table 1.—Applicability Model As listed in— Excluding airplanes— MD-11 and MD-11F airplanes Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated January 9, 2002 None. MD-11 and MD-11F airplanes Boeing Alert Service Bulletin MD11-24A068, Revision 02, dated May 16, 2001 Modified from a passenger to a freighter configuration on which the entry door (L1) sliding panel described in Boeing Alert Service Bulletin MD11-24A068, Revision 02, dated May 16, 2001, has been removed. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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) 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 chafing of electrical wire assemblies above the forward passenger doors and above the entry door (L1) sliding panel of the forward drop ceiling on the passenger compartment, which could result in electrical arcing, and consequent electrical fire in the passenger compartment, accomplish the following: Requirements of AD 2000-24-11 Detailed Inspection (a) For airplanes listed in McDonnell Douglas Alert Service Bulletins MD11-25A194, Revision 05, dated June 21, 1999; and MD11-24A068, Revision 01, dated March 8, 1999: Within 10 days after December 28, 1998 (the effective date of AD 98-25-11 R1, amendment 39-10988), perform a detailed inspection of the aircraft wiring to detect discrepancies that include but are not limited to frayed, chafed, or nicked wires and wire insulation in the areas specified in paragraphs (a)(1) and (a)(2) of this AD. Note 2: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” (1) At the area of the forward drop ceiling just outboard of mod block S3-735, and forward and inboard of the light ballast for the entry light on the sliding ceiling panel above the forward left passenger door (1L) at station location x = 24.75, y = 435, and z = 64.5. (2) At the area above the forward right passenger door (1R) at station location x = −30, y = 430, and z = 70 in the ramp deflector assembly part number 4223570-501. Corrective Action (b) If any discrepancy is detected during the detailed inspection required by paragraph (a) of this AD, prior to further flight, repair in accordance with Chapter 20, Standard Wiring Practices of the MD-11 Wiring Diagram Manual, dated January 1, 1998, or April 1, 1998. Inspection, Installation, and Modification (c) For airplanes listed in McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999; or MD11-24A068, Revision 01, dated March 8, 1999: Within 6 months after March 23, 2000 (the effective date of AD 2000-03-10, amendment 39-11569), accomplish the actions specified in paragraphs (c)(1), (c)(2), (c)(4), and (c)(5) of this AD, as applicable. (1) For Group 1 airplanes listed in McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999: Install a ramp deflector assembly on the right side forward entry drop ceiling structure in accordance with McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999; McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000; or Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated January 9, 2002. After the effective date of this AD, only Revision 07 of the alert service bulletin shall be used. (2) For Group 2 airplanes listed in McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999: Install a ramp deflector assembly on the right side forward entry drop ceiling structure in accordance with McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999; McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000; or Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated January 9, 2002. After the effective date of this AD, only Revision 07 of the alert service bulletin shall be used. (3) Installation of a ramp deflector assembly in accordance with McDonnell Douglas Service Bulletin MD11-25-194, dated March 15, 1996; Revision 01, dated May 1, 1996; Revision 02, dated July 12, 1996; Revision 03, dated December 12, 1996; or Revision 04, dated March 8, 1999; is acceptable for compliance with the requirements of paragraph (c)(2) of this AD. (4) For Group 3 airplanes listed in McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999: Modify the previously installed ramp deflector assembly bracket in accordance with McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999; McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000; or Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated January 9, 2002. After the effective date of this AD, only Revision 07 of the alert service bulletin shall be used. (5) For airplanes listed in McDonnell Douglas Alert Service Bulletin MD11-24A068, Revision 01, dated March 8, 1999: Perform a general visual inspection of the wire assembly support installation for evidence of chafing, in accordance with the service bulletin. If any chafing is detected, prior to further flight, repair or replace any discrepant part with a new part in accordance with the service bulletin. Note 3: For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.” One-Time Inspection (d) For airplanes other than those identified in paragraph (a) of this AD: Within 10 days after January 8, 2001 (the effective date of AD 2000-24-11, amendment 39-12018), perform a detailed inspection of the aircraft wiring to detect discrepancies that include but are not limited to frayed, chafed, or nicked wires and wire insulation in the areas specified in paragraphs (a)(1) and (a)(2) of this AD. If any discrepancy is found, prior to further flight, repair in accordance with the requirements of paragraph (b) of this AD. (e) Accomplishment of the inspection required by paragraph (a) of AD 98-25-11 R1, amendment 39-10988, prior to the effective date of this AD, is acceptable for compliance with paragraph (d) of this AD. Modification (f) For airplanes listed in Group 3 of McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000: Within 6 months after January 8, 2001, modify the ramp deflector assembly support bracket on the right side forward entry door drop ceiling structure, in accordance with McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000; or Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated January 9, 2002. After the effective date of this AD, only Revision 07 of the alert service bulletin shall be used. New Actions Required by This AD Inspection, Corrective Action, if Necessary, and Replacement (g) For airplanes listed in Groups 1 and 2 in Boeing Alert Service Bulletin MD11-24A068, Revision 02, dated May 16, 2001: Within 6 months after the effective date of this AD, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Do a general visual inspection of the wire assembly support installation above the entry door (L1) sliding panel of the forward drop ceiling of the passenger compartment for chafing per the service bulletin. If any chafing is found, before further flight, repair per the service bulletin. (2) Replace the wire support bracket with new support clip assemblies and ensure adequate clearance exists for all parts of the wire assembly, including breakouts to module blacks and grounds, per the service bulletin. Alternative Methods of Compliance (h) 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 4: 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) Unless otherwise specified in this AD, the actions shall be done in accordance with McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999; McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000; Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated January 9, 2002; and Boeing Alert Service Bulletin MD11-24A068, Revision 02, dated May 16, 2001; as applicable. (1) The incorporation by reference of Boeing Alert Service Bulletin MD11-24A068, Revision 02, dated May 16, 2001; and Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated January 9, 2002; 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 Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999, was previously approved by the Director of the Federal Register as of March 23, 2000 (65 FR 8034, February 17, 2000). (3) The incorporation by reference of McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000, was previously approved by the Director of the Federal Register as of January 8, 2001 (65 FR 75612, December 4, 2000). (4) Copies may be obtained from Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024). 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 (k) This amendment becomes effective on May 27, 2003. Issued in Renton, Washington, on April 10, 2003. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-9429 Filed 4-18-03; 8:45 am] BILLING CODE 4910-13-P