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71-25-09: 71-25-09 MCDONNELL DOUGLAS: Amendment 39-1358 as amended by Amendment 39-1384. Applies to all Model DC-8 Series Airplanes. \n\n\tCompliance required within the next 3,000 hours' time in service after the effective date of this AD, unless already accomplished within the last 17,000 hours' time in service, and thereafter at each FAA approved normal gear overhaul period, but not to exceed 20,000 hours' time in service from the last inspection. \n\n\tTo prevent failures of the main landing gear retract cylinder attach pin, accomplish the following in accordance with McDonnell Douglas DC-8 Service Bulletin No. 32-102, Revision 4, dated 4 May 1970, or later FAA approved revisions, or an equivalent procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(a)\tRemove the retract pin and inspect the retract pin lock bolt hole, the surface of retract pin, and the inner surface of the retract pin boss for corrosion and cracks. \n\n\t(b)\tIf corrosion is found, rework the affected areas to remove all traces of corrosion. If no more than .003 inches on the diameter is removed from the boss hole during rework, further shot peening of the reworked area is not required. If cracks or corrosion are found in the retract pin, discard the pin. \n\n\t(c)\tReinstall uncracked and uncorroded pins, with particular care being used in obtaining a moisture proof seal around the retract pin lock bolt. It is recommended that a beak of PR 1436G sealant or equivalent be applied around the boss lip, where the retract pin protrudes, to seal out moisture. If the boss is heated to facilitate installation of the retract pin, Parker-O-Lube or equivalent should be substituted for the 463-6-1 Cat-A-Lac primer. \n\n\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. \n\n\tAmendment 39-1358 became effective January 11, 1972. \n\n\tThis Amendment 39-1384 becomes effective January 29, 1972.
2000-03-16: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time visual inspection of the 90 percent brake pedal position switch to determine if certain date codes are present; and corrective action, if necessary. This amendment is prompted by reports indicating that the threaded insert connectors pulled free from the casing of the 90 percent brake pedal position switch, which allowed the insert connector contact to burn through the nose wheel steering cable. The actions specified by this AD are intended to prevent the threaded insert connector from pulling free from the casing of the 90 percent brake pedal position switch and burning through the nose wheel steering cable, which could result in reduced aircraft directional control while on the ground.
99-23-26 R1: This amendment revises an existing airworthiness directive (AD), that is applicable to General Electric Aircraft Engines (GE) CF34 series turbofan engines. That AD currently requires: (1) replacement of Buna-N O-rings with Viton O-rings; or (2) a new location of the vent groove on the MFC mounting flange; or (3) installation of an MFC with improved overspeed protection. This amendment requires the installation of an MFC with improved overspeed protection. If this action can not be completed within 30 days of the effective date of this AD, then either: (1) replace Buna-N O-rings with Viton O-rings, followed by replacement with an MFC with improved overspeed protection within a specified time; or (2) replace with an MFC with a relocated vent groove on the MFC mounting flange and improved overspeed protection. This amendment is prompted by nonsubstantive revisions to the manufacturer s service bulletins and comments from the manufacturer regardingvarious typographical errors in the AD. The actions specified by this AD are intended to prevent uncommanded engine accelerations, which could result in an engine overspeed, uncontained engine failure, and damage to the airplane.
82-27-11 R1: 82-27-11 R1 MCDONNELL DOUGLAS: Amendment 39-4530 as amended by Amendment 39-4660. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, and -30F series airplanes with operable galley lifts, certificated in all categories. Compliance required by January 30, 1984, unless already accomplished. To minimize the potential operational hazard to personnel associated with galley lift electrical interlock system malfunctions, accomplish the following: \n\n\tA.\tReplace the galley lift system electrical interlock switches with hermetically sealed switches as outlined in the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin 25-266, dated July 23, 1979, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tReplace the plunger type interlock switch actuators with leaf spring actuators, install structural protection for the interlock switches, and install additional warning placards as outlined in the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin 25-307, Revision 1, dated March 25, 1983, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: Airplanes modified in accordance with Service Bulletin 25-307 dated May 5, 1982, require rework. \n\n\tC.\tAlternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received these documents fromthe manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tAmendment 39-4530 became effective February 16, 1983. \n\n\tThis Amendment 39-4660 becomes effective June 15, 1983.
2014-17-06: We are superseding Airworthiness Directive (AD) 2011-17-08 for all Airbus Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes. AD 2011-17-08 required revising the maintenance program by incorporating certain Airworthiness Limitation Items (ALIs). This new AD requires a revision to the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. This AD was prompted by a revision of certain airworthiness limitations items (ALI) documents, which specifies more restrictive instructions and/or airworthiness limitations. We are issuing this AD to detect and correct fatigue cracking, damage, and corrosion in certain structure, which could result in reduced structural integrity of the airplane.
2000-03-07: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB211-524H-36 series turbofan engines. This action requires, prior to further flight, installing an improved combustion liner with a strengthened head and improved heat shields. This amendment is prompted by a report of burn through of a combustor case that lead to burning away of the thrust reverser and translating cowl and subsequent fire damage to the engine pylon. The actions specified in this AD are intended to prevent burn through of the combustor case due to combustion liner cracking, which can result in an engine fire and damage to the aircraft.
90-23-10: 90-23-10 MCDONNELL DOUGLAS: Amendment 39-6798. Docket No. 89-NM-215-AD. \n\n\tApplicability: Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) series airplanes and Model MD-88 airplanes; equipped with Whittaker Controls power transfer unit shutoff (PTU S/O) valve, Part Number (P/N) 240695 or P/N 240695-1; certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent dual hydraulic system failure, accomplish the following: \n\n\tA.\tFor those airplanes with Whittaker Controls PTU S/O valve P/N 240695 installed, \n\n\t\t1.\tPrior to the accumulation of 2,000 landings, or within 200 landings after October 23, 1989 (the effective date of Amendment 39-6356, AD 89-22-02), whichever occurs later, unless accomplished within the last 1,800 landings, replace the PTU S/O valve body attachment screws, P/N NAS 1101E-14, with new screws of the same part number, in accordance with the installation instructions of McDonnell Douglas Telex MD-80-COM-24/JCE, dated September 18, 1989. Thereafter, replace the attachment screws at intervals not to exceed 2,000 landings until replacement of the valves in accordance with paragraph A.2. of this AD is accomplished. Replacement of Whittaker Controls PTU S/O valve P/N 240695, with PTU S/O valve P/N 240695-2 constitutes terminating action for the requirements of this paragraph. \n\n\t\t2.\tWithin 90 days after the effective date of this amendment, replace all Whittaker Controls PTU S/O valves P/N 240695, with Whittaker Controls PTU S/O valves P/N 240695-2; or modify the valves P/N 240695 to the P/N 240695-2 configuration in accordance with Whittaker Controls Service Bulletin 240695-29-1, dated March 15, 1988, and Service Bulletin 240695-29-3, dated May 14, 1990. (Accomplishment of the procedures specified in both service bulletins is required.) \n\n\tB.\tFor those airplanes with the Whittaker Controls PTU S/O valve P/N 240695-1 installed, within 180 days after the effective date of this amendment, replace all Whittaker Controls PTU S/O valve P/N 240695-1, with PTU S/O valve P/N 240695-2; or modify the valve P/N 240695-1 to the P/N 240695-2 configuration in accordance with Whittaker Controls Service Bulletin 240695-29-3, dated May 14, 1990. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already receivedthe appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90801, ATTN: Business Unit Manager, Technical Publications, C1-HCW (54-60); or from Whittaker Controls, 12838 Saticoy Street, North Hollywood, California 91605. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tAirworthiness Directive 90-23-10 supersedes AD 89-22-02, Amendment 39-6356. \n\n\tThis amendment (39-6798, AD 90-23-10) becomes effective on December 10, 1990.
89-26-02: 89-26-02 MCDONNELL DOUGLAS: Amendment 39-6418. Docket No. 89-NM-73-AD. \n\n\tApplicability: Model DC-9-10 through -80, Model MD88, and C-9 (Military) series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo preclude failure of the rudder control sector, accomplish the following: \n\n\tA.\tWithin 60 days after the effective date of this airworthiness directive (AD), visually inspect the rudder control sector for cracks and acceptable wall thickness, in accordance with Figure 2 of McDonnell Douglas Alert Service Bulletin A27-302, dated February 17, 1989. \n\n\t\t1.\tIf no cracks are found and the wall thickness is more than .020 inch, no further action is required. \n\n\t\t2.\tIf cracks are found or if a wall thickness of .020 inch or less is found, prior to further flight, perform either a permanent or temporary repair or replace the rudder control sector, in accordance with the accomplishment instructions of McDonnellDouglas Service Bulletin A27-302, dated February 17, 1989. \n\n\t\t3.\tIf a temporary repair is performed, replace or permanently repair the rudder control sector within 6 months or 1,000 landings, whichever occurs earlier, in accordance with McDonnell Douglas Service Bulletin A27-302, dated February 17, 1989. \n\n\tB.\tWithin 15 days after the inspection required by paragraph A., above, submit a report of findings, positive or negative, to the Los Angeles Aircraft Certification Office, Attention: ANM-108L, FAA, Northwest Mountain Region, 3229 East Spring Street, Long Beach, California 90806-2425. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance times, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to theManager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C2-165 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6418, AD 89-26-02) becomes effective January 13, 1990.
2022-18-06: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-110B1 and GE90-115B model turbofan engines and certain GE90-76B, GE90-85B, GE90-90B, and GE90-94B model turbofan engines. This AD was prompted by the detection of melt-related freckles in the forgings and billets, which may reduce the life of certain rotating compressor discharge pressure (CDP) high-pressure turbine (HPT) seals (rotating CDP seals), interstage HPT rotor seals, and HPT rotor stage 2 disks. This AD requires revising the airworthiness limitations section (ALS) of the applicable GE90-100 Engine Manual (EM) and the operator's existing approved maintenance program or inspection program, as applicable, to incorporate reduced life limits for these parts. This AD also requires the removal and replacement of certain interstage HPT rotor seals, identified by serial number (S/N), installed on GE90-76B, GE90-85B, GE90-90B, and GE90-94B model turbofan engines. The FAA is issuing this AD to address the unsafe condition on these products.
90-06-06: 90-06-06 BOEING: Amendment 39-6490. Docket No. 89-NM-68-AD. \n\tApplicability: Model 747 series airplanes, listed in Boeing Document No. D6-35999, dated March 31, 1989, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent structural failure, accomplish the following: \n\n\tA.\tPrior to reaching the incorporation thresholds listed in Boeing Document No. D6-35999, dated March 31, 1989 (hereinafter called "the Document"), or within the next 4 years after the effective date of this AD, whichever occurs later, except as noted in paragraph B., below, accomplish the structural modifications listed in Section 3 of the Document. \n\n\tB.\t1.\tAccomplish replacement of the trailing edge flap tracks in accordance with Boeing Alert Service Bulletin 747-57A2229, Revision 8, dated January 31, 1989, within the next 5 years after the effective date of this AD. \n\n\tNOTE: For the purpose of complying with this AD, replacement of trailing edge flap tracks in accordance with Boeing Alert Service Bulletin 747-53A2229, Revision 8, dated January 31, 1989, is considered equivalent to replacement in accordance with either Boeing Alert Service Bulletin 747-57A2229, Revision 7, dated October 13, 1988, or Revision 9, dated November 2, 1989, or Boeing Service Bulletin 747-57-2146, Revision 3, dated May 9, 1986. \n\n\t\t2.\tIncorporation thresholds expressed as "at next overhaul," shall be accomplished within the next 6 years after the effective date of this AD, or prior to the accumulation of 20,000 flights, whichever occurs later. \n\n\t\t3.\tAccomplish the APU cutout reinforcement in accordance with Boeing Service Bulletin 747-53-2275, Revision 3, dated January 25, 1990, prior to the accumulation of 20,000 flights, or within the next 5,000 flights after the effective date of this AD, whichever occurs later. \n\n\t\t4.\tIf the 1241 bulkhead splice strap is cracked, replace the strap in accordance with Boeing Service Bulletin 747-53-2283, Revision 3, dated November 1, 1989, within the next 4 years after the effective date of the AD, or prior to the accumulation of 20,000 flight cycles, or within 2 years of crack discovery, whichever occurs latest. \n\n\tNOTE: For the purpose of complying with this AD, the incorporation of the terminating modification for the longitudinal floor beams contained in Boeing Service Bulletin 747-53-2224, Revision 6, dated July 27, 1989, is considered equivalent to the incorporation of the terminating actions contained in Service Bulletins 747-53-2176, Revision 3, dated December 15, 1978, and 747-53-2183, Revision 1, dated March 14, 1980. \n\n\tNOTE: The modifications required by paragraphs A. and B., above, do not terminate the inspection requirements of any other AD unless that AD specifies that any such modification constitutes terminating action of the inspection requirements. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tThe modifications shall be done in accordance with Boeing Document No. D6-35999, dated March 1989, "Aging Airplane Service Bulletin Structural Modification Program - Model 747." 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 Airplanes, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington; or at the Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington; or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C. \n\n\tThis amendment (39-6490, AD 90-06-06) becomes effective on April 17, 1990.