Results
2013-07-06: We are adopting an airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332C, AS332L, and AS332L1 helicopters and superseding an AD for Model AS332L2 and EC225LP helicopters. This AD requires inspecting the chip detector and modifying the chip collector, both installed on the main gearbox (MGB). This AD is prompted by an investigation which showed a failure within the epicyclic reduction gear module (epicyclic module) resulted in the rupture of the MGB case and separation of the main rotor head of a Model AS332L2 helicopter. These actions are intended to prevent failure of the MGB and subsequent loss of control of the helicopter.
2013-08-04: We are adopting a new airworthiness directive (AD) for Grob- Werke Model G115EG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 cracks in the elevator trim tab arms on several Grob G 115 airplanes, which could result in failure of the part and consequent loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
92-12-04: 92-12-04 DE HAVILLAND, INC.: Amendment 39-8264. Docket No. 91-NM-267-AD. Applicability: de Havilland Model DHC-7 series airplanes; serial numbers 1 through 23; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of flap track no. 1, accomplish the following: (a) Within 6 months after the effective date of this AD, perform a one-time dye penetrant inspection to detect cracks in flap track no. 1, in accordance with de Havilland Service Bulletin 7-53-15, Revision A, dated November 27, 1981. (b) If cracks are evident or suspected as a result of the inspection required by paragraph (a) of this AD, prior to further flight, replace the flap track in accordance with de Havilland Service Bulletin 7-53-15, Revision A, dated November 27, 1981. (c) If no cracks are evident or suspected as a result of the inspection required by paragraph (a) of this AD, within 6 months after theeffective date of this AD, modify the lower surface of flap track no. 1 in accordance with de Havilland Service Bulletin 7-53-15, Revision A, dated November 27, 1981. (d) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, ANE-170, FAA, Engine and Propeller Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office, ANE-170. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York Aircraft Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.(f) The inspections and repairs shall be done in accordance with de Havilland Service Bulletin 7-53-15, Revision A, dated November 27, 1981. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (h) This amendment becomes effective on July 24, 1992.
2003-10-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections for cracking of the skin, bear strap, and sill chord of the lower lobe cargo door cutout, and repair, if necessary. For certain airplanes, the AD also provides an optional modification of the lower lobe cargo door cutout, which ends the pre-modification repetitive inspections, but necessitates new post-modification repetitive inspections after a certain time. The actions specified by this AD are intended to find and fix cracking of the skin, bear strap, and sill chord of the lower lobe cargo door cutout, which could lead to reduced structural integrity of the lower lobe cargo door cutout, and result in rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
69-08-11: 69-08-11 CESSNA: Amdt. 39-755. Applies to Models 210-5 (205), Serial Numbers 205-0001 through 205-0577; Models 206, U206 and P206, Serial Numbers 206-0001 through U206-1284 and P206-0001 through P206-0566; Models 210 and T210, Serial Numbers 21058221 through 21059111 and T210-0001 through T210-0424 series airplanes. Compliances: Within 50 hours' time-in-service after the effective date of this airworthiness directive, unless already accomplished: To prevent complete loss of engine power when using the fuel boost pump, accomplish the following: Modify the fuel boost pump electrical circuit by installing a resistor in accordance with Cessna Service Letter No. SE 69-9, dated April 11, 1969, or any equivalent method approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region. This amendment becomes effective April 22, 1969.
2021-06-10: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747 series airplanes and Model 767 series airplanes. This AD was prompted by a report of an un-commanded fuel transfer between the main and center fuel tanks. This AD prohibits operation of an airplane with any inoperative refuel valve (fueling shut-off valve) failed in the open position. The FAA is issuing this AD to address the unsafe condition on these products.
2003-10-14: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-231 series airplanes; equipped with International Aero Engines (IAE) V2500-A5 series engines. This action requires revising the airplane flight manual to incorporate new procedures to follow in the event of an oil filter clog message. This action is necessary to require the flightcrew to follow the procedures necessary to prevent smoke caused by an oil filter clog from entering the cabin during flight. This action is intended to address the identified unsafe condition.
2000-05-15: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS355N helicopters. This action requires inspecting the: 4 engine exhaust pipe ejector attachment lugs (lugs) for cracks; starter-generator (S-G) shaft for radial play; S-G attachment flange for cracks; and S-G attachment half- clamps for cracks. This amendment is prompted by 9 reports of S-G damage; 3 reports of the discovery of cracks in the lugs; and 1 report of an in-flight loss of the exhaust pipe ejector. The actions specified in this AD are intended to prevent separation of an engine exhaust pipe ejector from the helicopter, which could result in a tail rotor strike and subsequent loss of control of the helicopter.
2021-05-07: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model BO-105A, BO-105C, BO-105S, MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB- BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. This AD was prompted by a report of a loss of electrical ground between the starter-generator and the generator voltage regulator (regulator). This AD requires inspecting the starter-generator electrical ground connection, retrofitting the starter-generator wire harness, and depending on model, revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
2003-10-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Model Mystere-Falcon 50 series airplanes. This action requires a detailed inspection for clearance and chafing of the entire length of the hydraulic lines located within the engine pylons, and follow-on/corrective actions, as applicable. This action also requires a revision of the maintenance manual to ensure that the clamps that hold the hydraulic lines are in their initial position during normal maintenance, and that the position is identified with a yellow paint line. This action is necessary to prevent chafing and consequent leakage of the hydraulic lines located within the No. 1 and No. 3 engine pylons, which can result in failure of the No. 1 and No. 2 hydraulic systems, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.