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87-14-07 R1: 87-14-07 R1 MCDONNELL DOUGLAS: Amendment 39-5630 as amended by Amendment 39-6019. Applies to McDonnell Douglas Model DC-9-10, -20, -30, -40, -50, and C-9 (Military) series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished.\n\n\tTo ensure the continuing structural integrity of these airplanes, accomplish the following:\n\n\tA.\tWithin one year after the effective date of this AD, incorporate a revision into the FAA-approved maintenance inspection program which provides for inspection of the Principal Structural Elements (PSE) defined in Section 2 of Volume I (All Series) of McDonnell Douglas Report No. L26-008, R1, DC-9 Supplemental Inspection Document (SID), dated November 1987, in accordance with Section 2 of Volume III of that document. The non-destructive inspection techniques set forth in Volume II of the SID provide acceptable methods for accomplishing the inspections required by this AD. All inspection results (negative or positive) must be reported to McDonnell Douglas, in accordance with the instructions of Section 2 of Volume III-87 of the SID.\n\n\tB.\tCracked structure detected during the inspections required by paragraph A., above, must be repaired or replaced before further flight, in accordance with an FAA-approved method.\n\n\tC.\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\tD.\tAn alternate means of compliance or an 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, FAA, Northwest Mountain Region.\n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office.\n\n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated by reference 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 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, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California.\n\n\tThis amendment revises AD 87-14-07, Amendment 39-5630, effective August 10, 1987.\n\n\tThis amendment, 39-6019, becomes effective on December 23, 1988.
2019-25-01: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines, LLC (IAE LLC) PW1122G-JM, PW1124G- JM, PW1124G1-JM, PW1127G1-JM, PW1127GA-JM, PW1127G-JM, PW1129G-JM, PW1130G-JM, PW1133GA-JM, PW1133G-JM model turbofan engines. This AD requires replacement of certain low-pressure turbine (LPT) 3rd-stage blades. This AD was prompted by multiple reports of LPT 3rd-stage blade failures causing a reduction of engine thrust. The FAA is issuing this AD to address the unsafe condition on these products.
2019-22-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-214, -216, -232, and -233 airplanes. This AD was prompted by a report of undetected contacts between certain harnesses of the common fuel quantity indicating system and the center tank structure. This AD requires modification of the fasteners for certain harness routings, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
72-07-01: 72-07-01 McCULLOCH AIRCRAFT CORP.: Amendment 39-1410. Applies to Model J-2 Gyroplane, compliance, as indicated, required before further flight unless already accomplished. 1. For serial numbers 10 and subsequent: By means of a propeller protractor, determine that the angle between the rotor mast and pitch bearing case is not less than 3.9 and not greater 5.0 degrees. If the angle measured is not within the tolerance indicated, rerig per paragraph 4.4 of McCulloch Aircraft Corporation Service Bulletin 8C dated February 24, 1972 or later FAA-approved revisions. 2. For serial numbers 10 through 54: (A) Inspect collective stick, part number 27133, for loose rivets at the juncture with collective stick shaft, part number 27104. (B) If loose rivets are found, replace the collective stick assembly with the new collective stick assembly per paragraph 4.1 "Rework-Effectivity (A)" of McCulloch Aircraft Corporation Service Bulletin 8C or with an equivalent approved byChief, Aircraft Engineering Division, FAA Western Region. (C) If no loose rivets are found and until the rework per paragraph 4.1 of McCulloch Aircraft Corporation Service Bulletin 8C is accomplished, reinspect for loose rivets at intervals not to exceed twenty-five (25) hours of flight time. This amendment is effective March 22, 1972 for all persons except those to whom it was made effective by airmail letter dated March 3, 1972, which contained this amendment.
82-17-02: 82-17-02 ROLLADEN SCHNEIDER: Amendment 39-4438. Applies to Model Nos. LS1-f and LS3 sailplanes, certificated in any category, which do not have Rolladen Schneider Technical Bulletin No. 38/3013, dated June 18, 1979, incorporated. Compliance is required as indicated, unless already accomplished. To prevent potential sailplane structural failure or loss of control due to elevator flutter, accomplish the following: a. Within the next 15 hours time in service after the effective date of this AD, unless already accomplished or unless the modification required by paragraph b of this AD has been accomplished, apply red tape to the air speed indicator and alter the airspeed limit placard restricting "never exceed airspeed" (VNE) to 124 MPH (200 km/H, 108 knots) in accordance with Rolladen Schneider Technical Bulletin No. 38/3013, dated June 18, 1979, paragraphs 1(a) and (b), or an FAA approved equivalent. b. Modify the elevator control system in accordance with Rolladen Schneider Technical Bulletin No. 38/3013, dated June 18, 1979, paragraphs 2 and 3, or an FAA approved equivalent, by December 15, 1982. The placard and airspeed indicator alterations required by paragraph a of this AD may be removed when this modification is accomplished. NOTE: Elevator control system modification consists of replacing the spring assembly in the elevator drive parallelogram mechanism with a solid link. An equivalent means of compliance may be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o American Embassy, Brussels, Belgium, or the Chief, Boston Aircraft Certification Branch, ANE- 150, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective August 16, 1982.
2019-22-13: The FAA is adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by reports of lavatory waste bin fire extinguishers found depleted. This AD requires a one-time inspection of the installation of the waste bins for interference (the inspection also includes a weight check of the waste bin fire extinguisher and an inspection of the discharge tubes for damage), modification of affected waste bins, and replacement of affected fire extinguishers, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also requires replacement of the fire extinguisher if any damaged discharge tube is found or the weight of the waste bin fire extinguisher is too low. The FAA is issuing this AD to address the unsafe condition on these products.
70-22-05: 70-22-05 PIPER: Amdt. 39-1099 as amended by Amendment 39-1344. Applies to Piper PA 23-250 type Aircraft S/N 27-3837 and 27-3944 to 27-4442 incl.; PA-30, S/Nos. 30-1717, 30-1746 to 30-2000, Incl.; PA-31 and PA-31-300, S/Nos. 31-228, 31-230, 31-231, 31-233 to 31- 588. Certificated for Instrument Flight. Compliance required within the next 100 hours in service after the effective date of this AD, unless already accomplished. To prevent the hazards associated with the possibility of a complete loss of electrical power while operating under Instrument Flight Rules. Accomplish the following: (a) Modify the aircraft electrical system in accordance with Piper Service Bulletin No. 306 dated January 9, 1970 or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. Amendment 39-1099 was effective November 4, 1970. This Amendment 39-1344 is effective November 30, 1971.
2007-17-16: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During the manufacturing process of the Poppet Covers of the Pressurization Safety Valves, burrs that could damage the Valve Diaphragms were not removed. The damage may eventually cause faulty operation of the relief valves resulting in an unsafe condition when combined with additional failures. The serial numbers of the defective valves and the affected aircraft were identified. The unsafe condition is damage and subsequent failure of the safety relief valves, which could result in rapid decompression of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
88-20-05: 88-20-05\tMCDONNELL DOUGLAS: Amendment 39-6022. Applies to McDonnell Douglas Model DC-9-81, -82, -83, -87, and MD-88 airplanes, certificated in any category, as listed in McDonnell Douglas Model MD-80 Service Bulletins 24-94, Revision 1, dated May 28, 1987, and 24-100, dated March 30, 1988.\n\n\tCompliance required within 12 months after the effective date of this airworthiness directive (AD), unless previously accomplished.\n\n\tTo eliminate a potential source of fire ignition from the generator power feeder cable electrically shorting, accomplish the following:\n\n\tA.\tFor airplanes identified in McDonnell Douglas MD-80 Service Bulletin 24-94, Revision 1, dated May 28, 1987: Inspect for power feeder cable damage, and repair the cable, if necessary; then modify the cable installation, in accordance with the Accomplishment Instructions of that service bulletin.\n\n\tB.\tFor airplanes identified in McDonnell Douglas MD-80 Service Bulletin 24-100, dated March 30, 1988: Modify the power feeder cable installation, in accordance with the Accomplishment Instruction of that service bulletin.\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, FAA, Northwest Mountain Region.\n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Los Angeles 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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California.\n\n\tThis amendment, 39-6022, becomes effective October 31, 1988.
98-24-27: This amendment adopts a new airworthiness directive (AD) that is applicable to First Technology Fire and Safety Ltd. toilet compartment fire extinguishers. This amendment requires inspection of suspect fire extinguishers for leakage, and removal from service and replacement with serviceable parts if the extinguisher is found to be leaking. This amendment is prompted by reports of leakage at the fire extinguisher's eutectic tip. The leakage is the result of a design change. The actions specified by this AD are intended to prevent fire extinguisher failure due to leakage, which in the event of a toilet compartment fire could result in an uncontained fire and damage to the aircraft.