Results
2022-07-10: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that certain overheat detection system (OHDS) sensing elements may not properly detect thermal bleed leak events due to a quality escape during the manufacturing process. This AD requires revising the operator's existing FAA-approved minimum equipment list (MEL) to include dispatch restrictions as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. This AD also allows operators to inspect affected parts for discrepancies, and do applicable replacements, in order to terminate the revision of the operator's existing MEL required by this AD. The FAA is issuing this AD to address the unsafe condition on these products.
2004-15-11: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires cleaning the auxiliary system unit (ASU) board and modifying the wiring and wiring harness. If a temporary modification is done, the AD requires inserting a placard regarding on-ground operation of the emergency landing gear pump (pump). Also, this AD revises the Limitations section of the Rotorcraft Flight Manual (RFM) to limit the operation of the pump. Permanently modifying the wiring and wiring harness and removing the placard and limitations from the RFM is terminating action for the requirements of this AD. This amendment is prompted by the report of an emergency landing with the landing gear retracted. The landing gear failed to extend in normal and emergency extension modes following failure of the ASU board 10 Alpha 2. The actions specified by this AD are intended to prevent an electrical short circuit, failure of landing gear to extend, and a landing gear-up emergency landing.
2022-06-17: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC130T2 helicopters. This AD was prompted by the determination of a certain part needing a life limit and re- identification. This AD requires re-identifying a certain part-numbered engine-to-main gearbox (engine-MGB) coupling shaft, and creating a log card or equivalent record, 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.
66-22-01: 66-22-01\tBOEING: Amdt. 39-284 Part 39 Federal Register September 7, 1966. Applies to Model 707-300B, 707-300B (ADV), and 707-300C Series Airplanes.\n \n\tWithin the next 100 hours' time in service after the effective date of this AD, until an antiskid HF filter is installed in accordance with Boeing Service Bulletin 2367 (R-2), dated June 16, 1966, or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, amend the Certification Limitation Section I of FAA-approved Airplane Flight Manuals, Boeing Model 707-300B (Boeing Document D6-1571), Model 707-300B (ADV) (Boeing Documents D6-1576 and D6-1588) and Model 707-300C (Boeing Documents D6-1575 and D6-1587) to include the following or an FAA-approved equivalent: \n\n\tANTISKID LIMITATIONS \n\n\tUntil antiskid HF filter installation is accomplished either during airplane manufacturer or by Service Bulletin, do not use HF to transmit between 2 and 6.5 mc. with antiskid on during taxi takeoff roll and landing.\n \n\tThis directive effective September 7, 1966.
99-12-03: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan engines, that requires revisions to the engine manufacturer's Time Limits Section (TLS) of the JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR Turbofan Engines Manual to include enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2004-15-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires a one-time inspection to determine the part number of the engine mounting frames, brace struts, and attachment fittings; and related corrective action. This action is necessary to ensure the structural integrity of the engine-to-wing load path and prevent possible separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
2022-07-02: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. Model 205A, 205A-1, 205B, 210, 212, 412, 412CF, and 412EP helicopters with a certain part-numbered tailboom left hand fin spar cap (spar cap) installed. This AD was prompted by reports of cracked spar caps. This AD requires inspecting each spar cap and depending on the inspection results, removing the spar cap from service. The FAA is issuing this AD to address the unsafe condition on these products.
2004-01-20: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B series, RB211-524B, -524C2, -524D4, -524G2, -524G3, and -524H series, and RB211-535C and -535E series turbofan engines with high pressure compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 installed. This AD allows disc assemblies not modified by a certain RR service bulletin to reach their full life only after the disc assemblies are modified with anti-corrosion protection. This AD results from the manufacturer's reassessment of the corrosion risk on HPC stage 3 disc assemblies that have not yet been modified with sufficient application of anti-corrosion protection. We are issuing this AD to prevent corrosion-induced uncontained disc failure, resulting in damage to the airplane.
72-14-02: 72-14-02 SIAI-MARCHETTI: Amdt. 39-1477. Applies to SIAI Marchetti Model S.205 airplanes, Serial Nos. 001 through 003, 101 through 384, 385 through 4-255, and Model S.208 airplanes, Serial Nos. 001 through 003, 1-03 through 2-19, 369, 3-100, 4-231, 4-233, 4-256 through 4-258. Compliance is required as indicated. To prevent the entrance of fuel or fumes into areas of the wing external to the fuel tanks or into the cabin, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished within the last 40 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection until the modification specified in paragraph (c) is accomplished - (1) On Model S.205 airplanes, Serial Nos. 001 through 003 and 101 through 384, which do not incorporate scupper drains, remove the right hand and left hand wing tank fuel level transmitter access covers and visuallyinspect the fuel level transmitter supper recessed areas for water deposits or corrosion. (2) On Model S.205 airplanes, Serial Nos. 385 through 4-255, and Model S.208 airplanes, Serial Nos. 001 through 003, 1-03 through 2-19, 369, 3-100, 4-231, 4-233, and 4-256 through 4-258, which incorporate straight scupper drain tubes, remove the right hand and left hand wing tank fuel level transmitter access covers and visually inspect the welding area between the tubes and fuel level transmitter scupper recessed areas for cracks or signs of fuel seepage into the recessed areas. (b) If water deposits or corrosion are found during an inspection required by subparagraph (a)(1) or cracks or signs of fuel seepage are found during an inspection required by subparagraph (a)(2), comply with paragraph (c) before further flight, except that the airplane may be flown in accordance with Section 21.197 of the Federal Aviation Regulations to a base where the repair can be made. (c) For all ModelsS.205 and S.208 airplanes, within the next 500 hours' time in service after the effective date of this AD, unless already accomplished, install new right hand and left hand wing tank fuel transmitter scupper drain tubes, P/N 205-8-112-37 and P/N 205-8- 112-38, and reinforcing washers, P/N 205-8-112-27, in accordance with SIAI Marchetti Service Bulletin No. 205B29A dated December 15, 1971, or an FAA-approved equivalent. Identify the new scupper drain tubes by painting a ring of white paint approximately 1/8 inch wide on the recessed area of the scupper around the new drain tube where it extends through the scupper. This amendment becomes effective 3 July, 1972.
2022-07-11: The FAA is superseding Airworthiness Directive (AD) 2021-17- 18, which applied to all Leonardo S.p.a. Model A109C, A109K2, A109E, A109S, and AW109SP helicopters. AD 2021-17-18 required an inspection of certain tail rotor (TR) sleeve assemblies for discrepancies, an inspection of certain TR shaft assemblies for discrepancies, a repetitive measurement of the position of the bushing of the TR sleeve assembly in relation to the pitch change slider assembly, and corrective actions if necessary. This AD retains the requirements of AD 2021-17-18, and also requires repetitive inspections of the TR sleeve assemblies, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that additional actions are required to address the unsafe condition. This AD was also prompted by a report of a crack on the TR mast. The FAA is issuing this AD to address the unsafe condition on these products.