AD 2001-05-10 Airworthiness Directives; McDonnell Douglas Model DC-10 and MD-11 Series Airplanes, and KC-10A (Military) Airplanes

Models named: DC-10 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model DC-10 series airplanes, MD-11 series airplanes, and KC-10A (military) 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 (j) 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 unwanted deployment of the thrust reverser, which could result in reduced controllability of the airplane, accomplish the following: Modification of Certain Model DC-10 Series Airplanes (a) For Model DC-10-10, -30, and -40 series airplanes listed in McDonnell Douglas DC-10 Service Bulletin 78-40, Revision 1, dated July 24, 1979: Within 3,000 flight hours or 12 months after the effective date of this AD, whichever occurs first, install a thrust reverser interlock (in-flight lockout) by installing two relays on the forward relay panel and revising the associated wiring, per the service bulletin. The requirements of this paragraph must be done before or with the requirements of paragraph (b) or (c) of this AD, as applicable. Inspection of Model DC-10 Airplanes Powered by General Electric Engines (b) For DC-10-10, -15, and -30 series airplanes listed in McDonnell Douglas Alert Service Bulletin DC10-78A056, Revision 02, dated February 18, 1999: Within 3,000 flight hours or 12 months after the effective date of this AD, whichever occurs first, do a detailed visual inspection, functional check, and torque checks of the thrust reverser system and the thrust reverser interlocks to detect discrepancies [i.e., below minimum torque required to overcome the pneumatic drive motor (PDM) disc brake; cuts, tears, or missing sections of the translating cowl seals; dents, cracks, holes, or loose fasteners on the Dagmar fairing or aft frame; improper alignment of the feedback rod; hidden faults in the translating cowl auto re-stow system; a failed over pressure shutoff valve (OPSOV); and improper operation of the fan reverser actuation system], per the service bulletin. Repeat the inspections thereafter every 6,000 flight hours or 18 months, whichever occurs first. Note 2: For the purposes of this AD, a detailed visual 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.” Note 3: Inspection of the thrust reverser system accomplished before the effective date of this AD per McDonnell Douglas Alert Service Bulletin DC10-78A056, dated January 19, 1998, or Revision 01, dated June 4, 1998, is considered acceptable for compliance with the initial inspections required by paragraph (b) of this AD. Note 4: McDonnell Douglas Alert Service Bulletin DC10-78A056, Revision 02, dated February 18, 1999, references Middle River Aircraft Systems (MRAS) Service Bulletin 78-3001, Revision 2, dated December 18, 1997, and MRAS Service Bulletin 78-2004, Revision 1, dated December 18, 1997, as additional sources of service information for accomplishment of the inspections and corrective actions. Inspection of Model DC-10-40 Series Airplanes Powered by Pratt & Whitney Engines (c) For Model DC-10-40 series airplanes listed in McDonnell Douglas Alert Service Bulletin DC10-78A057, Revision 01, dated February 18, 1999: Within 3,000 flight hours or 12 months after the effective date of this AD, whichever occurs first, do a detailed visual inspection, functional check, and torque checks of the thrust reverser system to detect discrepancies [i.e. damaged or improperly functioning stow latch hooks; cuts, gouges, and holes in the pneumatic seal/bullnose seal; improper functioning of the pneumatic drive unit (PDU) position locking retention feature; improper installation or improper operation of the system wiring, switches, or indicator lights; damage to the fan reverser flexshafts, actuators, translating sleeve tracks, or sliders; improper function of the in-flight interlock system; and improper operation of the thrust reverser power source, translating sleeve, throttle interlocks, or cockpit indicators], per the service bulletin. Repeat the inspections thereafter every 6,000 flight hours or 18 months, whichever occurs first. Note 5: Inspection of the thrust reverser system per McDonnell Douglas Alert Service Bulletin DC10-78A057, dated November 30, 1998, accomplished before the effective date of this AD, is considered acceptable for initial compliance with the applicable action specified in paragraph (c) of this AD. Inspection of Model MD-11 Series Airplanes Powered by General Electric Engines (d) For Model MD-11 series airplanes equipped with General Electric engines: Do a detailed visual inspection and functional check of the two position microswitches on the Center Drive Unit (CDU) and their associated wiring to detect failed open switches or open wire runs, and the aerodynamic seal between the reverser translating sleeves and the main reverser structure to detect damage to the aerodynamic seal or its interface surface on the reverser structure; and do an inspection to determine the torque value of the cone brake within the CDU to detect slipping or a failed CDU brake. These inspections and the functional check shall be done per pages 17 and 18 of the Boeing MD-11 Certification Maintenance Requirements (CMR), Report Number MDC-K4174, Revision P, dated April 5, 1999, or Revision Q, dated December 22, 1999; at the times specified in paragraph (d)(1) or (d)(2) of this AD, as applicable. (1) For airplanes on which the modification (i.e., translating cowl double P-seal configuration) specified in MRAS CF6-80C2D1F Alert Service Bulletin 78A1005, dated March 29, 1995; Revision 1, dated June 6, 1996; Revision 2, dated October 18, 1996; Revision 3, dated August 18, 1997; or Revision 4, dated December 21, 1998; has been accomplished: Inspect within 7,000 flight hours after the effective date of this AD. Repeat the inspections thereafter every 7,000 flight hours. (2) For airplanes on which the modification (i.e., translating cowl double P-seal configuration) specified in MRAS Service Bulletin 78A1005, dated March 29, 1995; Revision 1, dated June 6, 1996; Revision 2, dated October 18, 1996; Revision 3, dated August 18, 1997; or Revision 4, dated December 21, 1998; has not been accomplished: Inspect within 2,000 flight hours after the effective date of this AD. Repeat the inspections thereafter every 2,000 flight hours. Note 6: The type certificate for these airplanes includes a CMR to perform this same inspection at intervals not to exceed 17,000 flight hours. This CMR is still in effect and must be complied with. If the CMR requires an inspection before the compliance time stated in paragraph (d)(1) or (d)(2) of the AD, as applicable, operators may take credit for doing the CMR, and then repeat the inspection at the intervals specified in that applicable paragraph. (e) For Model MD-11 series airplanes equipped with General Electric engines, without an electronic control unit (ECU) listed in Table 1 installed: Within 2,000 flight hours after the effective date of this AD, test the thrust reverser pressurization system to detect an uncommanded pressurized thrust reverser system and/or a failed thrust reverser pressure switch, as applicable, per pages 52 and 53 of the Boeing MD-11 CMR, Report Number MDC-K4174, Revision P, dated April 5, 1999. Repeat the inspections thereafter every 2,000 flight hours. Table 1 is as follows: Table 1 ECU P/N 1519M91P06 1519M91P07 1519M91P09 1820M34P01 1820M34P02 1820M34P04 (f) For Model MD-11 series airplanes equipped with General Electric engines: Within 7,000 flight hours after the effective date of this AD, inspect the thrust reverser in-flight lockout system (IFLS) to detect failure of the flight control computer (FCC), radio altimeter input to the FCC, main landing gear wheel speed input to the FCC, ground sensing system, or wiring that causes an on-ground status in the IFLS while the airplane is airborne, per page 54 of the Boeing MD-11 CMR, Report Number MDC-K4174, Revision P, dated April 5, 1999. Repeat the inspections thereafter every 7,000 flight hours. (g) For Model MD-11 series airplanes equipped with General Electric engines: Within 600 flight hours after the effective date of this AD, accomplish the actions specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD per MRAS CF6-80C2D1F Alert Service Bulletin 78A1082, dated August 25, 1999. (1) Perform a pressure differential inspection of the directional pilot valves (DPV) to detect a partially open solenoid or failed O-ring. If any partially open solenoid or failed O-ring is detected, before further flight, replace the discrepant DPV with a DPV that has been inspected per this paragraph. Repeat the inspection thereafter every 2,000 flight hours. Or (2) Replace the DPV with a DPV that has been inspected per paragraph (g)(1) of this AD. Repeat the replacement thereafter every 2,000 flight hours. Or (3) Deactivate the thrust reverser per the MD-11 Master Minimum Equipment List, and reactivate the thrust reverser only after accomplishing the actions specified in paragraph (g)(1) or (g)(2) of this AD. Inspection of Model MD-11 Series Airplanes Powered by Pratt & Whitney Engines (h) For MD-11 series airplanes equipped with Pratt & Whitney engines: Within 7,000 flight hours after the effective date of this AD, do a detailed visual inspection and functional checks, as applicable, of the thrust reverser system and the thrust reverser IFLS to detect failed open pressure switches on the hydraulic control unit, to detect failed stow position microswitches and associated wiring, or failed locking mechanisms; and failure of the FCC, radio altimeter input to the FCC, main landing gear wheel speed input to the FCC, ground sensing system, or wiring that causes an on-ground status in the IFLS while the aircraft is airborne, per pages 19, 20, and 54 of the Boeing MD-11 CMR, Report Number MDC-K4174, Revision P, dated April 5, 1999. Repeat the inspections thereafter every 7,000 flight hours. Note 7: The type certificate for these airplanes includes a CMR to perform this same inspection at intervals not to exceed 13,800 flight hours. This CMR is still in effect and must be complied with. If the CMR requires an inspection before the compliance time stated in paragraph (h) of the AD, operators may take credit for doing the CMR, and then repeat the inspection at the intervals specified in that paragraph. Corrective Actions (i) If any discrepancy is detected during any inspection required by this AD, before further flight, do the actions specified in either paragraph (i)(1) or (i)(2) of this AD. (1) Do the applicable corrective action per the following service documents: (i) Chapter 78 of McDonnell Douglas DC-10 Aircraft Maintenance Manual; (ii) Chapter 78 of McDonnell Douglas DC-10 Turn Around Fault Isolation Manual; Chapter 78 of General Electric Shop Manual; (iii) MRAS CF6-6 Service Bulletin 78-2004, Revision 1, dated December 18, 1997; (iv) MRAS CF6-50 Service Bulletin 78-3001 Revision 2, dated December 18, 1997; (v) McDonnell Douglas Alert Service Bulletin DC10-78A056, dated January 19, 1998, Revision 01, dated June 4, 1998, or Revision 02, dated February 18, 1999; (vi) McDonnell Douglas Alert Service Bulletin DC10-78A057, dated November 30, 1998, or Revision 01, dated February 18, 1999; (vii) Chapter 78 of McDonnell Douglas MD-11 Aircraft Maintenance Manual; (viii) Chapter 78 of McDonnell Douglas MD-11 Fault Isolation Manual; or (ix) A method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. (2) Deactivate the thrust reverser in accordance with the DC-10 Master Minimum Equipment List or the MD-11 Master Minimum Equipment List, as applicable. Alternative Methods of Compliance (j) 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. 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 8: 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 (k) 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 (l) Except as provided by paragraphs (i)(1) and (i)(2) of this AD, the actions shall be done per the applicable service bulletins identified in Table 2, which contain the specified list of effective pages. Table 2 is as follows: Table 2 Document and date Page numbers Revision level shown on page Date shown on page McDonnell Douglas DC-10 Service Bulletin 78-40, Revision 1, July 24, 1979 1-20 1 July 24, 1979. McDonnell Douglas Alert Service Bulletin DC10-78A056, Revision 02, February 18, 1999 1-15 02 February 18, 1999. Attachment A 1-4 02 February 18, 1999. McDonnell Douglas Alert Service Bulletin DC10-78A057, Revision 01, February 18, 1999 1-42 01 February 18, 1999. Attachment A 1-4 01 February 18, 1999. Boeing MD-11 Certification Maintenance Requirements, Report Number MDC-K4174, Revision P, April 5, 1999 List of Effective Pages Pages LIST-1 through LIST-2 P (Only indicated on the cover page; no other page contains this information) April 5, 1999 (Only indicated on the cover page; no other page of the document is dated). Boeing MD-11 Certification Maintenance Requirements, Report Number MDC-K4174, Revision Q, December 22, 1999 List of Effective Pages Pages LIST-1 through LIST-2 Q (Only indicated on the cover page; no other page contains this information) December 22, 1999 (Only indicated on the cover page; no other page of the document is dated). Middle River Aircraft Systems CF6-80C2D1F Alert Service Bulletin 78A1082, August 25, 1999 1-15 Original August 25, 1999. Middle River Aircraft Systems CF6-6 Service Bulletin 78-2004, Revision 1, December 18, 1997 1-36 1 December 18, 1997. Middle River Aircraft Systems CF6-50 Service Bulletin 78-3001, Revision 2, December 18, 1997 1-43 2 December 18, 1997. McDonnell Douglas Alert Service Bulletin DC10-78A056, January 19, 1998 1-15 Original January 19, 1998. Attachment A 1-4 Original December 17, 1997. McDonnell Douglas Alert Service Bulletin DC10-78A056, Revision 01, June 4, 1998 1-15 01 June 4, 1998. McDonnell Douglas Alert Service Bulletin DC10-78A057, November 30, 1998 1-41 Original November 30, 1998. Attachment A 1-4 Original November 30, 1998. McDonnell Douglas Alert Service Bulletin DC10-78A057, Revision 01, February 18, 1999 1-42 01 February 18, 1999. Attachment A 1-4 01 February 18, 1999. 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, 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 (m) This amendment becomes effective on April 25, 2001. Issued in Renton, Washington, on March 7, 2001. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-6282 Filed 3-20-01; 8:45 am] BILLING CODE 4910-13-U