Results
2016-19-07: We are superseding Airworthiness Directive (AD) 2008-19-08, for all Dassault Aviation Model Falcon 10 airplanes. AD 2008-19-08 required repetitive replacement of the flexible hoses installed in the wing (slat) anti-icing system with new hoses. This new AD requires reducing the life limit of these flexible hoses, which reduces the repetitive replacement intervals. This AD was prompted by additional reports of collapse of the flexible hoses installed in the slat anti- icing systems on airplanes equipped with new, improved hoses. We are issuing this AD to prevent collapse of the flexible hoses in the slat anti-icing system, which could lead to insufficient anti-icing capability and, if icing is encountered in this situation, could result in reduced controllability of the airplane.
2016-18-18: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A, A109A II, A109C, A109E, A109K2, A109S, and AW109SP helicopters. This AD requires visually inspecting the tail rotor drive shaft assembly (drive shaft) for a crack. This AD was prompted by the discovery of three cracks on the drive shaft of a Model A109S helicopter. The actions of this AD are intended to detect a crack on the drive shaft to prevent failure of the driveshaft, failure of the tail rotor, and subsequent loss of helicopter control.
2005-14-09: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This AD requires removal of certain Engine Electronic Controller (EEC) part numbers from service. This AD results from nine reports of loss of engine parameters displayed in the airplane cockpit, with the simultaneous loss of capability to change thrust of the affected engine. We are issuing this AD to prevent loss of airplane control after an aborted takeoff due to asymmetric thrust.
98-09-26: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Model Falcon 2000 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with procedures for monitoring and properly setting the fuel booster pump pressure; and repetitive visual inspections of the fuel lines to detect fatigue cracking and fuel leakage. This action also requires a one-time inspection of the fuel lines to detect cracking, replacement of any discrepant part with a new part, and installation of new brackets between the pressure switch and the fuel pump of the numbers 1 and 2 engines, which constitutes terminating action for the repetitive inspections and the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking of the fuel line at the pressure switch pickoff point, which could result in fuel leakage and potential engine fire.
2016-18-14: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 and Model ATR72-212A airplanes. This AD was prompted by a report indicating that interference occurred between a Type III Emergency Exit door and the surrounding passenger cabin furnishing during a production check. This AD requires measuring the gap between the Type III Emergency Exit doors and certain overhead stowage compartment fittings; removing certain fittings from the overhead stowage compartments and measuring the gap between the Type III Emergency Exit doors and the overhead stowage compartment hooks, if necessary; re-installing or repairing, as applicable, the Type III Emergency Exit doors; and modifying the overhead stowage compartments. We are issuing this AD to prevent interference between a Type III Emergency Exit door and the overhead stowage compartment fitting installed on the rail, which could result in obstructed opening of a Type IIIEmergency Exit door during an emergency evacuation.
2010-23-19: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Two cases of main landing gear (MLG) failure to fully extend have been reported. An MLG failing to extend may result in an unsafe asymmetric landing configuration. Preliminary investigation has shown that interference between the MLG door and the MLG fairing seal prevented the MLG door from opening. * * * * * The unsafe condition is possible loss of controllability of the airplane during landing. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
62-05-02: 62-05-02 BRANTLY: Amdt. 402 Part 507 Federal Register February 28, 1962. Applies to All Model B-2 Helicopters With Serial Numbers Prior to 180. Compliance required within the next 25 hours' time in service after the effective date of this directive. To preclude failure of the seals in the engine driven fuel pump due to excessively high temperature conditions in the engine compartment, modify the engine driven fuel pump, Lear- Romec Model RD7790D3, to incorporate high temperature seals in accordance with Brantly Service Bulletin No. 16 and Lear-Romec Service Bulletin No. 3. Reidentify modified units by revising the pump nameplate as follows: (a) Add suffix "-3" to the pump serial number. (b) Change pump model number to "RG7790G". (Brantly Service Bulletin No. 16 and Lear-Romec Service Bulletin No. 3 both cover this same subject.) This directive effective February 28, 1962.
77-14-03: 77-14-03 SOCIETE NATIONAL INDUSTRIELLE AEROSPATIALE (formerly SUD AVIATION): Amendment 39-295l. Applies to Alouette III Helicopter Model SE 3160 and SA 316B, certificated in all categories. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished in accordance with Alouette Service Bulletin No. 05.38, as revised June 14, 1971. To prevent possible binding of the tail rotor directional control, either replace the Houdaille type AV4S2 hydraulic damper with type AV4S3, or modify the type AV4S2 hydraulic damper by incorporating Houdaille Kit 10.338, in accordance with subparagraph 1C(2)(b) of Alouette Service Bulletin 05.38 as revised June 14, 1971, or equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, A.P.O. New York, N.Y. 09667. This amendment becomes effective August 1, 1977.
87-12-09 R1: 87-12-09 R1 SOCATA GROUPE AEROSPATIALE: Amendment 39-5650 as revised by Amendment 39-6224. Applicability: Models TB 20 and TB 21 (Serial Numbers 275 through 700) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD, and each 100 hours TIS thereafter, unless already accomplished in accordance with the original issuance of AD 87-12-09. To prevent structural failure of the aileron, possible flutter, and loss of control, accomplish the following: (a) Visually inspect the five aileron balance weight attachment rivets for any detectable looseness, and the aileron skin for cracks using the procedures described in paragraph A, SOCATA TB Service Bulletin (S/B) No. 28, dated December 1986. (1) If one or more loose rivets, or cracks extending less than 9/16 inch (15 mm) from the center of the rivet is found, prior to further flight, repair as described in paragraph B of SOCATA TB AircraftS/B No. 28, dated December 1986. (2) If a crack 9/16 inch or longer from the center of the rivet is found, prior to further flight, replace the P/N TB 20.15.001.000 aileron with P/N TB 20.15.001.001 or P/N TB 20.15.001.002 aileron as applicable. (b) The repetitive inspections specified in this AD are no longer required when the ailerons have been repaired or replaced per the actions specified in either paragraph (a)(1), or (a)(2) above. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Office, FAA, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium; Telephone (322) 513.38.30. All persons affected by this directive may obtain copies of document(s) referred to herein upon request to SOCATA Groupe AEROSPATIALE, B.P. 38, 65001 Tarbes, France; Telephone 62.51.73.00 or 62.93.99.45 (for recorder); or the Product Support Manager, U.S., AEROSPATIALE, 2701 Forum Drive, Grand Prairie, Texas, 75053; Telephone (214) 641-3614; or may examine these documents referred to herein at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD revises AD 87-12-09, Amendment 39-5650, which became effective on June 26, 1987. This amendment (39-6224, AD 87-12-09 R1) becomes effective on June 25, 1989.
2010-23-11: We are adopting a new airworthiness directive (AD) for the products listed above. 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: The manufacturer has informed Transport Canada that a certain number of the resolver stators, which were installed in the angle of attack (AOA) transducers, were not cleaned correctly. This condition can degrade the AOA transducer performance at low temperatures resulting in freezing of the AOA transducer resolver, which may provide inaccurate AOA data to the Stall Protection System (SPS). If not corrected, this condition can result in early or late activation of the stick shaker and/or stick pusher. These conditions could result in reduced ability of the flight crew to maintain a safe flight and landing of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.