Results
2004-25-09: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This AD requires repetitive inspections of the left and right support ribs for the main landing gear (MLG) trunnion, related investigative/ corrective actions if necessary, and other specified actions. This AD is prompted by reports of in-service cracking of the support ribs for the MLG trunnion. We are issuing this AD to detect and correct corrosion and cracking of the support ribs for the MLG trunnion, which could result in collapse of the MLG.
2023-07-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by several unscheduled PW1500G engine removals due to certain crew alerting system (CAS) messages being displayed, high vibration, or debris found on the magnetic chip collector of a bearing compartment. This AD prohibits dispatch of an airplane with an affected engine having an applicable CAS message displayed, unless the bearing compartment chip collector and oil filter are inspected and any debris found is dispositioned, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
84-10-05: 84-10-05 MESSERSCHMITT-BOLKOW-BLOHM-GmbH: Amendment 39-4864. Applies to HFB-320 airplanes as listed in HFB-320 Service Bulletin 57-19 dated February 5, 1982, certificated in all categories. Compliance is required within the next 150 hours time in service or 90 days, whichever occurs first after the effective date of this AD for airplanes with 2400 hours total time in service on the effective date. All others must comply before accumulating 2550 hours time in service, but no later than 90 days after accumulating 2400 hours. To prevent failure of the upper surface wing structure accomplish the following, unless previously accomplished: A. Perform a one-time inspection of the wing upper skin in accordance with the service bulletin. Repair cracks per the manufacturer's instructions. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain 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 May 29, 1984.
2004-25-12: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135 and -145 series airplanes. This AD requires a one-time inspection of each passenger service unit (PSU) to determine the serial number of the printed circuit board (PCB) installed in each PSU, replacement of the PCB if necessary, related investigative actions, and other specified actions. This AD is prompted by reports that PSUs on two airplanes emitted smoke. We are issuing this AD to prevent failure of a PSU, which could result in smoke or fire in the airplane's passenger cabin.
85-08-08: 85-08-08 McCAULEY ACCESSORY DIVISION: Amendment 39-5046. Applies to the following Model D3A32C90 series propellers installed on, but not limited to, Bellanca 17-30, 17- 30A; Cessna A185E, F, A188B, P206A, TP206A, U206A, B, C, D, E, F, TU206A, B, C, D, E, F, 207, 207A, T207; and Navion A thru H: D3A32C90, D3A32C90-A, -B, -C, -J, -K, -L, -BLM, - CLM, -JLM, -KLM, -LM, and -M. Compliance is required as indicated unless already accomplished. To detect propeller hub cracks and prevent possible failure, accomplish the following: (a) Propeller models D3A32C90, D3A32C90-A, -B, -C, -J, -K, and -L: Within the next 50 hours time in service after the effective date of this AD or prior to accumulating 1200 hours total time in service, whichever occurs later, replace hubs with shot peened hubs and modify to the oil filled hub configuration in accordance with Supplement 1 to McCauley Service Manual No. 720415 dated January 7, 1977, or FAA approved equivalent. (b) Propeller models D3A32C90-BLM, -JLM, -KLM, -LM, and -M: Within the next 50 hours time in service after the effective date of this AD or prior to accumulating 1200 hours total time in service, whichever occurs later, inspect the hub in accordance with McCauley Service Letter 1974-3 dated March 29, 1974, or FAA approved equivalent, end modify to the oil filled hub configuration in accordance with Supplement 1 to McCauley Service Manual No. 720415 dated January 7, 1977, or FAA approved equivalent. (c) Propellers with unknown service histories must comply with paragraphs (a) or (b), as applicable, within the next 50 hours time in service after the effective date of this AD. (d) Modified propellers showing signs of red dyed oil leakage must be removed from service and replaced with a serviceable propeller. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, ACE-140C, 2300 East Devon Avenue, Des Plaines, Illinois 60018, telephone (312) 694-7130. 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 McCauley Accessory Division, Cessna Aircraft Company, 3535 McCauley Drive, P.O. Box 430, Vandalia, Ohio 45377. These documents also may be examined at the Office of Regional Counsel, FAA, Attn: Rules Docket No. 85-ANE-1, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective May 13, 1985.
2014-04-10: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, -300 and -200 Freighter series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by a report that an airplane equipped with Angle of Attack (AOA) sensors installed with conic plates recently experienced blockage of all sensors during climb, leading to autopilot disconnection and activation of the alpha protection (Alpha Prot) when Mach number was increased. This AD requires, for certain airplanes, revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for addressing AOA sensor blockage. This AD also requires replacing the AOA sensor conic plates with AOA sensor flat plates, which is a terminating action for the AFM revision. We are issuing this AD to prevent reduced control of the airplane.
2023-03-20: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-400, -400D, and -400F series airplanes. This AD was prompted by the FAA's analysis of the Model 747 airplane fuel system reviews conducted by the manufacturer, and by the determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
86-10-08: 86-10-08 FAIRCHILD: Amendment 39-5315. Applies to Models SA226 and SA227 airplanes (Serial Numbers (S/N) SA226-T, S/N T201 through T275, T277 through T291; SA226-T(B), S/N T(B)276, T(B)292 through T(B)417; SA226-AT, S/N AT001 through AT074; SA226-TC, S/N TC201 through TC419; SA227-TT, S/N TT421 through TT555; SA227-AT, S/N AT423 through AT631B; SA227-AC, S/N AC406, AC415, AC416, and AC420 through AC632) airplanes certificated in any category. Compliance: Required within the next 200 hours time-in-service or the next 30 calendar days, whichever comes first, after the effective date of this AD, unless already accomplished. To prevent the elevator gust lock from engaging in flight, accomplish the following: (a) Remove the elevator gust lock system components and install the alternate elevator gust lock and associated hardware in accordance with the instructions in Fairchild Aircraft Corporation Service Bulletin (S/B) 226-27-041 revised February 18, 1986, for the SA226 airplane models, or S/B 227-27-016 revised February 18, 1986, for the SA227 airplane models. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance may be used if approved by the Manager of the Airplane Certification Branch, ASW-150, Southwest Regional Office, FAA, Fort Worth, Texas 76101; telephone (817) 877-2070. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Fairchild Aircraft Corporation, Post Office Box 32486, San Antonio, Texas 78284, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on May 28, 1986.
2000-05-14: This amendment supersedes two existing airworthiness directives (AD's), applicable to AlliedSignal Inc. ALF502 and LF507 series turbofan engines, that require rework or replacement of No. 4 and 5 bearing oil system hardware, initial and repetitive inspections of the oil system, optional installation of an improved oil filter bypass valve, and repetitive inspection of No. 4 and 5 bearing oil inlet tube, to ensure the integrity of the reduction gear system and overspeed protection system. This action would require replacement of the existing power turbine bearing housing assembly with a new, improved power turbine bearing housing assembly, and installation of a reworked or modified fourth turbine rotor disk assembly as a part of a design change to the new No. 4 bearing configuration that eliminates the requirement for repetitive inspections of oil system and No. 4 and 5 bearing oil inlet tube assembly. This amendment is prompted by one report of a contained power turbine rotor shaft separation forward of the Stage 4 low pressure turbine (LPT) rotor on an AlliedSignal Inc. ALF502R-5 engine. The LPT failure was caused by improper inspection of the engine oil system required by AD 97-05-11 R1. The actions specified by this AD are intended to prevent a No. 4 and 5 duplex bearing failure, which can result in a Stage 4 LPT rotor failure, an uncontained engine failure, and damage to the airplane.
2004-25-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-300 and -400ER series airplanes, that requires replacing the tie rods for the waste tank cradle, related investigative actions, corrective actions, and special retrofit action if necessary. This action is necessary to prevent possible failure of the main deck floor stanchions and consequent collapse of the main floor during an emergency landing, which could result in passenger injury and impede passenger evacuation from the airplane. This action is intended to address the identified unsafe condition.