Results
2023-06-02: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL- 600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a determination that, due to a lack of flightcrew awareness, smoke hoods with a certain part number installed throughout the airplane could be mistaken for protective breathing equipment (PBE). This AD requires an inspection or records review to determine if any smoke hood with a certain part number is installed in any location on the airplane and, depending on the results, removing the smoke hood and associated placards and installing new placards. The FAA is issuing this AD to address the unsafe condition on these products.
81-06-02: 81-06-02 FROST ENGINEERING DEVELOPMENT CORPORATION: Amendment 39-4059. Applies to emergency descent devices installed on Boeing 747, Lockheed L-1011, and Airbus Industrie A-300 airplanes. \n\n\tCompliance required as indicated. To prevent failure of emergency descent devices accomplish the following: \n\n\tA.\tWithin 30 days from the effective date of this AD, unless already accomplished, inspect Frost Engineering descent devices for broken handle straps in accordance with paragraph 2, steps (1), (2), and (4) of Frost Engineering Development Corporation Service Bulletin 379103-25-002 dated September 29, 1980, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. \n\n\tB.\tDescent devices found to have a broken handle strap must be modified in accordance with paragraph 2, steps (6) through (9) of Frost Engineering Development Corporation Service Bulletin 379103-25-002 dated September 29, 1980, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. \n\n\tC.\tWithin 120 days from the effective date of this AD, unless already accomplished, modify the descent devices found to have a magnetic handle strap in accordance with paragraph 2, steps (5) through (9) of Frost Engineering Development Corporation Service Bulletin 379103-25-002 dated September 29, 1980, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. \n\n\tD.\tWithin 120 days from the effective date of this AD, replace descent devices P/N 379103-1, serial numbers 1 through 0134, with other FAA approved descent devices. \n\n\tE.\tUpon the request of the operator, and subject to prior approval by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region, an FAA Aviation Safety Inspector may adjust the compliance times if the request contains substantiating data to justify the change. \n\n\tThe manufacturer's specification 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). \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Frost Engineering Development Corporation, P.O. Box 1294, Englewood, Colorado 80150. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective March 19, 1981.
2004-25-17: The FAA adopts a new airworthiness directive (AD) for certain LETECKE ZAVODY Model L 23 SUPER--BLANIK sailplanes. This AD requires you to do a repetitive, non-destructive magnetic test (NDMT) inspection on the elevator rocker lever (part number A 730 201 N) for cracks. If cracks are found, this AD also requires you to return the part to the manufacturer. The manufacturer will send you a replacement part for installation. Installing the improved replacement part terminates the need for the repetitive inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. We are issuing this AD to prevent failure of the elevator rocker lever caused by cracks that resulted from a defect in prior manufacturing procedures. Such failure could lead to loss of control of the sailplane.
67-32-04: 67-32-04 PILATUS: Amdt. 39-525, Part 39, Federal Register December 12, 1967. Applies to Model PC-6 Series Airplanes. Compliance required as indicated. (a) To prevent the possibility of stabilizer trim control cable clamps jamming with the cable guide tubes at bulkhead No. 8, accomplish the following: (1) Within the next 50 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection, inspect guide tubes, P/N 6232.208, for signs of movement or wear in accordance with Pilatus Service Bulletin No. 72, dated June 1967, or later Swiss Federal Air Office-approved revision, or an FAA-approved equivalent. (2) If signs of movement or wear are detected during the inspection required by paragraph (a)(1), before further flight incorporate the modification required by paragraph (a)(3). (3) If no signs of movement or wear are detected during the inspections required by paragraph (a)(1), within the next 200 hours' time in service after the effective date of this AD, modify guide tubes, P/N 6232.208, and install an additional support, P/N 6232.468, in accordance with Pilatus Service Bulletin No. 72, dated June 1967, or later Swiss Federal Air Office-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (b) To prevent excessive rubbing of the rudder control cable with its fairlead at bulkhead No. 2, accomplish the following: (1) Within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the rudder cable phenolic fairlead for signs of wear in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision, or an FAA-approved equivalent. (2) If signs of wear are detected during the inspection required by paragraph (b)(1), within the next 25 hours' time in service replace worn fairlead with a serviceable fairlead. (3) Within the next 600 hours' time in service after the effective date of this AD, replace the pulley and fairlead assembly with a double pulley assembly in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (c) To prevent excessive rubbing of the stabilizer trim control cable with its pulley at bulkhead No. 11, accomplish the following: (1) Within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the cable and its pulley for signs of wear, in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision or an FAA-approved equivalent. (2) If signs of wear are detected during the inspection required by paragraph (c)(1), within the next 25 hours' time in service replace worn cable or pulley with a serviceable cable or pulley. (3) Within the next 600 hours' time in service after the effective date of this AD, modify the double pulley in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (d) The repetitive inspections required by paragraphs (a)(1), (b)(1), and (c)(1) may be discontinued following the incorporation of the applicable modification in accordance with paragraphs (a)(3), (b)(3), and (c)(3), respectively. This amendment effective December 17, 1967.
2011-23-07: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP (type certificate previously held by Israel Aircraft Industries, Ltd.) Model Galaxy and Gulfstream G150 airplanes; and Gulfstream Aerospace LP Model Gulfstream 200 airplanes. 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: A broken aileron servo actuator centering spring rod was discovered on a model G100 aircraft during a routine scheduled maintenance inspection. * * * This latent failure of a centering spring rod, if not detected and corrected, in conjunction with the disconnection of the normal mechanical control system of the same servo actuator would lead to loss [of] control of the flight control surface [aileron or elevator]. This condition would reduce the control capability of the airplane and imposes a higher workload on the flight crew reducing their ability to cope with adverse operating conditions. We are issuing this AD to require actions to correct the unsafe condition on these products.
2023-06-12: The FAA is superseding Airworthiness Directive (AD) 2021-08- 08, which applied to all Airbus SAS Model A350-941 and -1041 airplanes. AD 2021-08-08 required replacing affected bleed duct assemblies and bleed gimbals at the wing-to-pylon interface, and prohibited the installation of affected parts. This AD was prompted by a report of a welding quality issue in the gimbal joint of the air bleed duct at each wing-to-pylon interface and the consequent deformation of the gimbal inner ring, and by new findings that affected bleed gimbals were found on certain airplanes that did not have any maintenance record of affected part replacement. This AD continues to require the actions in AD 2021-08-08 and, for certain airplanes, requires inspection of the bleed gimbals to determine the part number, and replacement if necessary, 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.
84-23-07: 84-23-07 SHORT BROTHERS LTD.: Amendment 39-4950. Applies to Model SD3-60 airplanes as listed in Short Brothers Service Bulletin SD360-71-05, dated March 1984, certificated in all categories. Compliance is required as indicated unless previously accomplished. To prevent icing of the oil cooler air intake scoop, accomplish the following: A. Within 60 days after the effective date of this airworthiness directive (AD), install the "D" type oil cooler air intake scoop on both intake cowls in accordance with Short Brothers Ltd. Service Bulletin SD360-71-05, dated March 1984. 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 December 15, 1984.
96-26-01: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Aircraft Engines (GE) CT7 series turboprop engines, that requires replacement of the gas generator turbine stage 2 forward cooling plates prior to the published cyclic life limits. The AD also defines the new, reduced cyclic life limits for the affected forward cooling plates. This amendment is prompted by reports of gas generator turbine stage 2 forward cooling plate failures. The actions specified by this AD are intended to prevent gas generator turbine stage 2 forward cooling plate failure, which could result in an uncontained engine failure.
2004-25-18: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PT6A-60A and PT6A-65B turboprop engines. This AD requires replacing Woodward propeller governor assemblies, part number (P/N) 8210-212H. This AD results from six incidents during airplane acceptance flight testing where directional control of the airplane was difficult to maintain during landing. We are issuing this AD to prevent loss of directional control and damage to the airplane.
84-18-03 R1: 84-18-03 R1 GARLICK HELICOPTERS, HAWKINS AND POWERS AVIATION, INC., WILCO AVIATION, CALIFORNIA DEPARTMENT OF FORESTRY, PILOT PERSONNEL INTERNATIONAL, INC., AND INTERNATIONAL HELICOPTER, INC. (BELL HELICOPTER TEXTRON, INC.): Amendment 39-4899 as amended by Amendment 39-4997. Applies to Model UH-1 series helicopters certificated in the restricted category. Compliance is required within 10 hours time in service, unless already accomplished, after September 6, 1984, for Garlick Helicopters, Hawkins and Powers Aviation, Inc., and Wilco Aviation UH-1 series helicopters. Compliance is required within 10 hours time in service, unless already accomplished, after the effective date of this amendment for California Department of Forestry, Pilot Personnel International, Inc., and International Helicopter, Inc., UH-1 series helicopters. To detect any improperly repaired or cracked main rotor pitch change link clevis and to prevent possible failure of a clevis, accomplish the following one-time inspection of each clevis, P/N 204-011-136-1 (FSN 5340-00-839-3934). (a) Visually inspect the exposed surfaces of the clevis using a 5-power or higher magnifying glass. If any surface with pits has a golden or silver color within a pit, the clevis has been replated and must be removed before further flight. (b) Visually inspect the exposed threaded area of the clevis shank, above the jam nut, for crack indications. If a crack indication is found, the part must be removed and additionally inspected for cracks using magnetic particle or equivalent inspection method. (c) If a clevis has been replated or has a crack, the clevis must be removed before further flight. Install a serviceable clevis as prescribed in the appropriate military model maintenance or overhaul manual. (d) Compliance with UH-1 series aircraft military message dated July 13, 1984, from Commander AVSCOM satisfies this AD. Amendment 39-4899 became effective September 6, 1984.This Amendment 39-4997 becomes effective on February 22, 1985.