Results
95-22-03: This amendment adopts a new airworthiness directive (AD) that applies to Beech Aircraft Corporation (Beech) Models 60 and A60 airplanes. This action requires incorporating flight manual supplement revisions into the Airplane Flight Manual (AFM) that would specify a minimum airspeed for operating the affected airplanes in icing conditions. Reports of several incidents and accidents on the affected airplanes related to flight in icing conditions prompted the proposed action. The actions specified by the proposed AD are intended to prevent loss of control of the airplane because of the airplane traveling too slowly in icing conditions.
2023-09-13: The FAA is superseding Airworthiness Directive (AD) 2019-18- 09, which applied to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes; and Model C-130A, HP-C-130A, EC-130Q, C-130B, and C-130H airplanes. AD 2019-18-09 required a visual inspection of the center wing upper and lower rainbow fittings for cracks, an eddy current inspection of the center wing lower rainbow fittings for cracks, and replacement if necessary. This AD was prompted by an analysis of reported cracks showing repetitive inspections are needed to adequately address cracked inner tangs of the center wing lower rainbow fittings. This AD requires repetitive inspections of the center wing upper and lower rainbow fittings for cracks and replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
81-14-04: 81-14-04 SHORT BROTHERS LIMITED: Amendment 39-4152. Applies to Model SD3-30 series airplanes, certificated in all categories, which have Menasco Manufacturing main landing gear actuator assembly P/N 17900, Serial numbers MMC-003 through MMC-111, installed. To prevent gear-up landing caused by the main landing gear actuator's inability to unlock, accomplish the following within 500 landings after the effective date of this AD, unless already accomplished: Rework the actuator by cutting a venting groove across the contoured face of the profiled washer in accordance with Short Brothers Limited Service Bulletin No. SD3-32-86 Rev. 2 dated March 4, 1981, or later FAA approved revisions, or in a manner acceptable to the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. 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 the addresses listed above. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective July 8, 1981.
2004-25-19: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This AD requires revising the airplane flight manual to provide the flightcrew with procedures and limitations for operating an airplane with out-of-tolerance angle of attack (AOA) transducers. This AD also requires repetitive linearity tests of the AOA transducers, and corrective action if necessary. This AD is prompted by a report of premature wear of the potentiometers in AOA transducers having a certain part number. We are issuing this AD to prevent a delay in the stall computer commands for stall warning, stick shaker, and stick pusher operation, due to premature wear of the potentiometers of the AOA transducers, which may cause the airplane to enter a stall condition, and result in loss of control of the airplane.
2023-08-03: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model G-1159A and G-1159B airplanes and all Model G-IV and GIV-X airplanes. This AD was prompted by a report that the ground spoiler actuator installation does not preclude improper hydraulic line connections that could result in unintended asymmetrical spoiler deployment. This AD requires incorporating corrective actions that physically prevent improper connection of the hydraulic lines to the ground spoiler actuator. The FAA is issuing this AD to address the unsafe condition on these products.
2023-09-10: The FAA is adopting a new airworthiness directive (AD) for all Saab AB, Support and Services Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports of excessive wear on certain starter generator brushes installed in the starter generator. This AD requires repetitive general visual inspections of the starter generator brushes installed in the starter generator and, depending on findings, replacement of the starter generator, and limits installation of affected generators, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
88-19-07: 88-19-07 EMPRESA BRAZILEIRA DE AERONAUTICA S.A. (EMBRAER): Amendment 39-6008. Applicable to all Model EMB-120 series airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To reduce the potential for flap asymmetry that could lead to loss of control of the airplane in a critical phase of flight, accomplish the following: A. Within 15 days after the effective date of this AD, revise the FAA-approved Airplane Flight Manual (AFM) to include Revision 9 (for EMB-120RT AFM 120/794) or Revision 14 (for EMB-120 AFM 120/624), as applicable. B. Within 90 days after the effective date of this AD accomplish the following: 1. Replace the flap actuator solenoid valves with new valves equipped with new filters, in accordance with Embraer Service Bulletin 120-027-0050, dated April 13, 1988; 2. Replace the inlet filter fitting of the flap actuators, in accordance with Embraer Service Bulletin 120-027-0042, dated February 10, 1988; and 3. Install in-line filters to the flap control hydraulic plumbing, in accordance with Embraer Service Bulletin 120-027-0038, dated November 16, 1987. C. An 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, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: The request for an alternate means of compliance should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Atlanta Certification Office. D. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Embraer, 276 S.W. 34th Street, Fort Lauderdale,Florida 33315. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia. This amendment supersedes AD 87-11-03, Amendment 39-5663. This amendment, 39-6008, becomes effective October 7, 1988.
82-22-51: 82-22-51 FAIRCHILD REPUBLIC: Amendment 39-4543. Applies to Fairchild Republic Models F-27 and FH-227 airplanes certificated in all categories. To prevent moisture separator assembly shell failure, accomplish the following: A. Prior to accumulating 100 landings or within 20 days, whichever occurs first, unless accomplished within the last 12 months, inspect the aircraft's moisture separator assembly P/N's 890469, 890469-01, 890469-02, 891572, or 891572-01, as applicable (two per aircraft), for the following: 1) Any of the above separator assemblies having upper shell assemblies P/N 841665 or 841665-01 which have been in service for three years or 20,000 cycles, whichever occurs first, must be immediately removed from service and replaced with a serviceable shell assembly. 2) Any shell assembly P/N 841665 or 841665-01 confirmed to have been installed less than three years or 20,000 cycles accumulated service, whichever comes first, which has not had the annualfluorescent penetrant inspection of shell assembly specified by the Walter Kidde Maintenance and Overhaul Manual F-41024B must be removed from service for the inspection and overhaul specified. Strict compliance with the crack and corrosion detection criteria of the Walter Kidde Manual is mandatory. 3) Any shell assembly P/N 841665 or 841665-01 with manufacturing dates stamped on the top of the shell housing prior to September 1979 which have never been in service must be inspected in accordance with Kidde Manual F-41024B before being put in service. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective February 3, 1983, and was effective earlier to those recipients of Telegraphic AD T82-22-51 dated October 27, 1982.
2004-25-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes. This action requires various repetitive inspections for cracking of the drag and shear angles that attach the nacelle to the wing, and related corrective action. This action also requires eventual modification of the drag and shear angles, which would end the repetitive inspections. This action is necessary to prevent fatigue cracking of the drag and shear angles, which could result in reduced structural integrity of the nacelle attachment to the wing. This action is intended to address the identified unsafe condition.
2023-07-11: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) Model LEAP-1B engines. This AD was prompted by a report of multiple aborted takeoffs and air turn- backs (ATBs) caused by high-pressure compressor (HPC) stall, which was induced by high levels of non-synchronous vibration (NSV). A subsequent investigation by the manufacturer revealed that wear on the No. 3 bearing spring finger housing can lead to high levels of NSV. This AD requires repetitive calculations of the oil filter delta pressure (OFDP) data and, depending on the results of the calculation, replacement of the No. 3 bearing spring finger housing. This AD also prohibits installation of an engine with an affected No. 3 bearing spring finger housing onto an airplane that already has one engine with an affected No. 3 bearing spring finger housing installed. The FAA is issuing this AD to address the unsafe condition on these products.