Results
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.
2023-04-17: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-8 and 737-9 airplanes, and certain Model 737- 600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of damage to the auxiliary power unit (APU) fuel line shroud located aft of the aft cargo area; investigation revealed that the placement of the pressure switch wire clamp assembly and its fastener allowed interference of the fastener against the APU fuel line shroud. This AD requires inspecting the APU fuel line shroud for damage, inspecting the pressure switch wire clamp for correct bolt orientation and horizontal distance from the APU fuel line shroud, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
63-04-02: 63-04-02 HILLER: Amdt. 535 Part 507 Federal Register February 12, 1963. Applies to All UH-12, UH-12A, UH-12B, and UH-12C Helicopters with P/N's 55008 and 55012 Tail Rotor Blades. Compliance required as indicated. To prevent failures of P/N's 55008 and 55012 tail rotor blades the following shall be accomplished: (a) Within the next 50 hours' time in service, unless already accomplished: (1) Replace all P/N's 55008 and 55012 tail rotor blades with P/N 55064 tail rotor blades in accordance with Hiller Service Bulletin No. 80. (2) On all helicopters equipped with the large diameter (1.375 inch) spar stabilizer, P/N 37003, install the stabilizer strut in accordance with Hiller Service Bulletin No. 75B. (3) On all helicopters equipped with the small diameter (1 inch) spar stabilizer, P/N 37001, install the stabilizer strut in accordance with Hiller Service Bulletin No. 83. (b) Until replacement with the P/N 55064 blade is accomplished, visually inspect the P/N's 55008 and 55012 tail rotor blades prior to each flight and refueling. The outer surface of the skin on both sides of the blade shall be inspected for cracks in the area of the outer tension torsion bar retention bolt and the adjacent rivet pattern through the outer end of the root fitting. Paint must be removed from the areas to facilitate inspection. Any blades found to be cracked must be removed and replaced with P/N 55064 blades prior to further flight. (Hiller Service Bulletins Nos. 75B, 80, and 83 pertain to this subject.) This supersedes AD 58-24-02. This directive effective February 12, 1963.
58-26-02: 58-26-02 BELL: Applies to All Model 47 Series Helicopters Equipped With Marvel- Schebler Automatic Altitude Compensating Carburetor Model MA4-5AA. Compliance required within next 25 hours of operation. With a Marvel-Schebler Model MA4-5AA carburetor installed, it is possible to start and run the engine with the carburetor mixture control in the idle cutoff position if the throttle is partially or fully opened. However, as soon as the throttle is fully closed, the idle cutoff will operate and shut off the engine. Therefore, it would be possible to start the engine, takeoff, and fly with the mixture in idle cutoff as long as the throttle is never closed. The first time the throttle is closed, however, as in autorotation, an immediate engine stoppage would occur. To prevent inadvertent engine stoppage in flight due to failure to place the carburetor mixture control in the "auto" position before takeoff, the following must be accomplished: (a) For Models 47D1, 47G, 47G2, 47H1, and 47J, spring load the cockpit mixture control to the rich or "auto" position by installing a tension spring (Bell P/N 47-631-226-1 or equivalent) between the mixture control cable support bracket (P/N 47-631-125-18) adjacent to the control quadrant and the control cable end of the quadrant mixture control lever. On Models 47D1 and 47H1, attach the spring to the mixture control lever using existing cotter pin hole through flexible control attaching clevis pin. On Models 47G, 47G2, and 47J, attach spring to mixture control lever through existing lower hole in lever. On Model 47D1, remove corners of jog in quadrant mixture control slot. Check that mixture control will return to "auto" position when pulled to "idle cut off" position and released. (b) For Model 47D, remove the quadrant mixture control lever and push-pull mixture control. Place the carburetor mixture control arm in the rich or "auto" position and secure with lockwire. This procedure may be used in lieu of that outlined in (a) for Models 47D1, 47G, 47G2, 47H1, and 47J if preferred. (This same subject is covered in Bell Service Bulletins No. 124SB for Models 47D1, 47G, and 47H1, No. 124SB Supplement 1 for Model 47D, and Service Instruction 257SI for Models 47G2 and 47J.)