AD 2000-26-15 Airworthiness Directives; McDonnell Douglas Model MD-11 Series Airplanes

Models named: MD-11 series. Read the applicability below — it usually turns on serial or part numbers too.

Model MD-11 series airplanes, as listed in McDonnell Douglas Alert Service Bulletin MD11-33A069, dated March 10, 2000, or Boeing Alert Service Bulletin MD11-33A069, Revision 01, dated November 30, 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 (c) 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 detect an exposed power contactor, which could cause the Captain, First Officer, or Right Observer map light or reading light in the crew rest area to short or overheat and consequent smoke or fire in the cockpit or crew rest area, accomplish the following: Restatement of Requirements of AD 2000-07-02 (a) For airplanes listed in McDonnell Douglas Alert Service Bulletin MD11-33A069, March 10, 2000: Within 30 days after April 20, 2000 (the effective date of AD 2000-07-02, amendment 39-11656), do the actions specified in either paragraph (a)(1), or (a)(2) or (a)(3) of this AD, as applicable, per McDonnell Douglas Alert Service Bulletin MD11-33A069, March 10, 2000, or Boeing Alert Service Bulletin MD11-33A069, Revision 01, dated November 30, 2000. As of the effective date of this AD, only Boeing Alert Service Bulletin MD11-33A069, Revision 01, including Appendix, dated November 30, 2000, shall be used. Option 1 (Deactivate Map Light Assemblies) (1) For Groups 1 and 2 airplanes identified in McDonnell Douglas Alert Service Bulletin MD11-33A069, March 10, 2000: Disconnect, coil, and stow power wires to each Captain, First Officer, and Right Observer map light assembly, until the requirements of paragraph (a)(2) or (a)(3) of this AD, as applicable, have been accomplished. Note 2: Repetitive inspections of the deactivated map light assemblies are not required. Option 2 (Inspect/Replace/Deactivate Map Light Assemblies) (2) For Group 1 airplanes identified in McDonnell Douglas Alert Service Bulletin MD11-33A069, March 10, 2000: Modify and reidentify the insulation blankets adjacent to the Captain and First Officer map light assemblies; and do a general visual inspection to detect damage of the Captain, First Officer, and Right Observer map light assemblies. 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 under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light, 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.” (i) Condition 1 (No Damage Found). If no damage is detected, repeat the general visual inspection of the map light assemblies and adjacent insulation blankets required by paragraph (a)(2) of this AD thereafter every 700 flight hours. (ii) Condition 2 (Damage Found). If any damage is detected, before further flight, do the actions specified in either paragraph (a)(2)(ii)(A) or (a)(2)(ii)(B) of this AD per the service bulletin. (A) Option 1 (Replace Damaged Map Light Assemblies). Replace the map light assembly with a new or serviceable light assembly. Repeat the general visual inspection of the map light assemblies and adjacent insulation blankets required by paragraph (a)(2) of this AD thereafter every 700 flight hours. (B) Option 2 (Deactivate Damaged Map Light Assemblies). Disconnect, coil, and stow power wires to each damaged Captain, First Officer, and Right Observer map light assembly, until the requirements of paragraph (a)(2)(ii)(A) of this AD have been done. (3) For Group 2 airplanes identified in McDonnell Douglas Alert Service Bulletin MD11-33A069, March 10, 2000: Do a general visual inspection to detect damage of the Captain, First Officer, and Right Observer map light assemblies, and do the actions specified in either paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as applicable, at the time(s) indicated in that paragraph. Note 4: For Group 2 airplanes identified in McDonnell Douglas Alert Service Bulletin MD11-33A069, dated March 10, 2000: Modification and reidentification of the insulation blankets are not required. Prior to delivery of Group 2 airplanes, the insulation blankets were modified. New Actions Required by This AD (b) For Groups 3 and 4 airplanes, equipped with Skybunks, identified in Boeing Alert Service Bulletin MD11-33A069, Revision 01, dated November 30, 2000: Within 60 days after the effective date of this AD, do the actions specified in either paragraph (b)(1) or (b)(2), per Boeing Alert Service Bulletin MD11-33A069, Revision 01, including Appendix, dated November 30, 2000. Option 1 (Deactivate Reading Light Assemblies) (1) Disconnect, coil, and stow power wires to each reading light assembly, ensure that deactivated reading lights do not illuminate, and install an inop ring on the circuit breaker. Note 5: Repetitive inspections of the deactivated reading light assemblies are not required. Option 2 (Inspect/Replace/Deactivate Reading Light Assemblies-Skybunk) (2) Do a general visual inspection to detect damage (i.e., cracks, damaged or broken components, or chafed or damaged reading light assembly wires) of the reading light assemblies. Note 6: Where there are differences between the referenced service bulletin and the AD, the AD prevails. (i) Condition 1 (No Damage Found). If no damage is detected, ensure that reading lights do illuminate, and repeat the general visual inspection of the reading light assemblies required by paragraph (b)(2) of this AD thereafter every 700 flight hours. (ii) Condition 2 (Damage Found). If any damage is detected, before further flight, do the actions specified in either paragraph (b)(2)(ii)(A) or (b)(2)(ii)(B) of this AD in accordance with the service bulletin. (A) Option 1 (Replace Damaged Reading Light Assemblies). Replace the reading light assembly with a new or serviceable light assembly, and ensure that the operative reading lights illuminate. Repeat the general visual inspection of the reading light assemblies required by paragraph (b)(2) of this AD thereafter every 700 flight hours. (B) Option 2 (Deactivate Damaged Reading Light Assemblies). Disconnect, coil, and stow power wires to any damaged reading light assembly, and ensure that the deactivated reading lights do not illuminiate, until the requirements of paragraph (b)(2)(i)(A) have been done. Alternative Methods of Compliance (c) 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 7: 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 (d) 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 (e) The actions shall be done in accordance with McDonnell Douglas Alert Service Bulletin MD11-33A069, March 10, 2000, or Boeing Alert Service Bulletin MD11-33A069, Revision 01, including Appendix, dated November 30, 2000; as applicable. (1) The incorporation by reference of Boeing Alert Service Bulletin MD11-33A069, Revision 01, including Appendix, dated November 30, 2000, 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 MD11-33A069, March 10, 2000, was approved previously by the Director of the Federal Register as of April 20, 2000 (65 FR 17763, April 5, 2000). (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, 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 (f) This amendment becomes effective on January 17, 2001. Issued in Renton, Washington, on December 22, 2000. John J. Hickey, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00-33336 Filed 12-29-00; 8:45 am] BILLING CODE 4910-13-P