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95-06-01: 95-06-01 BOEING: Amendment 39-9171. Docket 94-NM-147-AD. \n\n\tApplicability: Model 747-200 and -300 series airplanes equipped with General Electric CF6-80C2 series engines with Power Management Control (PMC) engine controls, certificated in any category. \n\n\tNOTE 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 use the authority provided in paragraph (e) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. \n\n\tCompliance: Required as indicated, unless accomplished previously.\n \n\tTo ensure the integrity of the fail safe features of the thrust reverser system, accomplish the following:\n \n\t(a)\tWithin 90 days after the effective date of this AD, perform tests of the position switch module and the cone brake of the center drive unit (CDU) on each thrust reverser, and perform an inspection to detect damage to the bullnose seal on the translating sleeve on each thrust reverser, in accordance with paragraphs III.A. through III.C. of the Accomplishment Instructions of Boeing Service Bulletin 747-78A2130, dated May 26, 1994. Repeat the tests and inspection thereafter at intervals not to exceed 1,000 hours time-in-service. \n\n\t(b)\tWithin 9 months after the effective date of this AD, perform inspections and functional tests of thethrust reverser control and indication system in accordance with paragraphs III.D. through III.F., III.H., and III.I. of the Accomplishment Instructions of Boeing Service Bulletin 747-78A2130, dated May 26, 1994. Repeat these inspections and functional tests thereafter at intervals not to exceed 18 months.\n \n\t(c)\tIf any of the inspections and/or functional tests required by this AD cannot be successfully performed, or if any discrepancy is found during those inspections and/or functional tests, accomplish either paragraph (c)(1) or (c)(2) of this AD. \n\n\t\t(1)\tPrior to further flight, correct the discrepancy found, in accordance with Boeing Alert Service Bulletin 747-78A2130, dated May 26, 1994. Or \n\n\t\t(2)\tThe airplane may be operated in accordance with the provisions and limitations specified in an operator's FAA-approved Minimum Equipment List (MEL), provided that no more than one thrust reverser on the airplane is inoperative. \n\n\t(d)\tWithin 10 days after performing each initial inspection and test required by this AD, submit a report of the inspection and/or test results, both positive and negative, to the FAA, Seattle Aircraft Certification Office (ACO), ANM-100S, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; fax (206) 227-1181. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. \n\n\t(e)\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(f)\tSpecial 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. \n\n\t(g)\tThe inspections, corrections of discrepancies, and tests shall be done in accordance with Boeing Alert Service Bulletin 747-78A2130, dated May 26, 1994. 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 Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(h)\tThis amendment becomes effective on April 13, 1995.
80-05-04: 80-05-04 EON CORPORATION: Amendment 39-3706. Applies to EON Model E2900 and E8000 Seat Belts and Harnesses. Compliance required within thirty (30) days from the effective date of this AD. \n\n\tTo prevent inadvertent opening and/or false latching of the seat belt/harness assembly, accomplish the following: \n\n\t(a)\tIf installed, remove bullet head shaped latch depicted below in plan view as Figure 1 and replace with square shaped latch of Figure 2 or other FAA approved, serviceable latch. \n\n\n\n\n\t(b)\tIf installed, remove buckle with open-ended cover depicted below in Figure 3 and replace with an E8000 buckle with cover depicted in Figure 4 or other FAA approved, serviceable buckle. \n\n\tNOTE: EON Corporation Service Bulletin No. 1 dated January 22, 1980, refers to this subject. \n\n\n\n\n\t(c)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective March 10, 1980.
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.