Results
68-12-03: 68-12-03 PRATT & WHITNEY: Amendment 39-608. Applies to all Model JT4A Series Turbojet Engines. Compliance required as indicated unless previously accomplished.: To preclude penetration of the diffuser case in the event of a high compressor rotor blade failure, accomplish the following: Within the next 11,000 hours' time in service after the effective date of this AD, rework all P/N's 361176, 397231, 419006, 406242, 429614, 447328, and 450862 diffuser case assemblies in accordance with Pratt & Whitney Aircraft Turbojet Engine Service Bulletin No. 1033 dated September 8, 1965, and FAA-approved revisions or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment becomes effective June 12, 1968.
2017-20-10: We are adopting a new airworthiness directive (AD) for all Airbus Model A319 series airplanes, Model A320-211, -212, -214, -231, - 232, and -233 airplanes, and Model A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes. This AD was prompted by a runway excursion due to an unexpected thrust increase leading to an unstable approach performed using the current flight management and guidance computer (FMGC) standard. This AD requires identification of potentially affected FMGCs, replacement of any affected FMGC, and applicable concurrent actions. We are issuing this AD to address the unsafe condition on these products.
2017-20-03: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a review showing that inadequate clearance may exist between certain electrical wiring and nearby structures. This AD requires an inspection of certain electrical wiring bundles and feeders, modifications, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2002-01-22: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3 series airplanes, that requires a one-time inspection of the installation of the bearing housings of the elevator torque shaft assembly, and corrective action if necessary. This action is necessary to prevent failure of the elevator torque shaft, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
78-13-03: 78-13-03 BURKHART GROB: Amendment 39-3244. Applies to Model G102 Astir CS gliders, Serial numbers, 1001 to 1234 and 1300 to 1315, certificated in all categories. Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To reduce the possibility of elevator control failure due to possible loss of an elevator control pivot bolt, modify the elevator control assembly by installing a mechanical stop to the elevator control pivot (bearing) bolt, part no. 4205.06, in accordance with Burkhart Grob Technical Information TM102-4 dated August 16, 1976, or an equivalent, approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. This amendment becomes effective July 5, 1978.
2017-19-05: We are adopting a new airworthiness directive (AD) for certain Siemens S.A.S. smoke detectors installed on various transport category airplanes. This AD requires inspection and replacement of the affected smoke detectors. This AD was prompted by a report that the affected smoke detectors failed an acceptance test. We are issuing this AD to correct the unsafe condition on these products.
2017-20-05: We are superseding Airworthiness Directive (AD) 2011-01-15, which applied to certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 2011-01-15 required repetitive inspections for cracking of the fuselage skin of the crown skin panel along the chem-milled step at certain stringers, and repair if necessary. This AD adds repetitive inspections for cracking in additional areas, and repair if necessary; removes airplanes from the applicability; adds an optional skin panel replacement, which terminates all inspections; adds an optional preventive modification, which terminates certain inspections; and reduces the compliance time for certain inspections. This AD was prompted by reports of the initiation of new fatigue cracking in the fuselage skin of the crown skin panel along locally thinned channels adjacent to the chem-milled steps. We are issuing this AD to address the unsafe condition on these products.
2017-20-08: We are superseding Airworthiness Directive (AD) 2009-17-01, which applied to certain Gulfstream Model G-IV, GIV-X, GV-SP airplanes and Model GV airplanes. AD 2009-17-01 required an inspection for sealant applied to the exterior of the auxiliary power unit (APU) enclosure (firewall), and a revision of the airplane flight manual (AFM), as applicable. This AD requires revising the AFM and revising the applicability to include additional airplanes. This AD was prompted by a report indicating that the type design sealant applied to the APU enclosure failed certain tests. We are issuing this AD to address the unsafe condition on these products.
2002-01-28: This amendment adopts a new airworthiness directive (AD) that is applicable to Dowty Aerospace Propellers Type R334/4-82-F/13 with propeller hub assemblies, part number (P/N) 660709201. This action requires a one-time ultrasonic inspection of the propeller hub for cracks. This amendment is prompted by a report of an in-flight loss of a propeller. The actions specified in this AD are intended to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane.
78-17-01: 78-17-01 MOONEY AIRCRAFT CORPORATION: Amendment 39-3279. Applies to Model M20C, Serial Number 20-1186 through 20-1258, M20F, Serial Number 22-1306 through 22-1486, and M20J, Serial Number 24-0001 through 24-0454 airplanes, with Pacific Communications, Inc., Aircraft Products Division, Model Alert 50, Part No. 01070-5 emergency locator transmitter system installed. Compliance is required as indicated. To assure that the emergency locator transmitter will radiate a proper signal when activated during emergency conditions, accomplish the following: 1. Rework the aircraft skin in accordance with Mooney Aircraft Corporation Service Bulletin M20-213 dated July 21, 1978, within ten hours operating time but no later than 30 days from the effective date of this AD. 2. Upon completion of the Mooney Service Bulletin No. 20-213 instructions, measure the resistance between the antenna and the aircraft skin using an appropriate meter and assure that a reading of 9,000 to 13,000 ohms isobtained. Determine that the ELT transmits properly by testing it in accordance with FAA Advisory Circular No's. 91-44 or 20-81. 3. The 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). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Mooney Aircraft Corporation, P. O. Box 72, Kerrville, Texas 78028. These documents may also be examined at Southwest Regional Office, Regional Counsel, Building 3B, Room 100, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective August 21, 1978.