Results
2021-23-04: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model A109E helicopters. This AD was prompted by reports of cracking in the center fuselage frame assembly in the intersection of the lateral pylon and floor spar at station (STA) 1815 on the left- and right-hand sides. This AD requires repetitive inspections of the intersection of the lateral pylon and floor spar at STA 1815 for cracking and, depending on the findings, repair, 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.
2021-23-10: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW109SP helicopters. This AD was prompted by reports of an ineligible hydraulic pump being installed on Model AW109SP helicopters. This AD requires inspecting each hydraulic pump for damage and, depending on the inspections results, removing parts from service and accomplishing other corrective actions. This AD also requires removing certain parts from service before they exceed their life limits. The corrective actions are required to be accomplished 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.
2004-10-08: The FAA adopts a new airworthiness directive (AD) for all Alexander Schleicher GmbH & Co. Segelflugzeugbau (Alexander Schleicher) Model ASH 25M sailplanes equipped with fuel injected engine IAE50R-AA. This AD requires you to inspect the fuel line for correct fittings, and, if any incorrect fitting is found, replace the fuel line. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct any fuel lines with improper fittings, which could result in fuel leakage and a possible fire hazard.
2004-10-09: This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 series airplanes, that requires repetitive detailed inspections for heat damage to any in-line splice in the auxiliary power unit (APU) and integrated drive generator (IDG) feeder cable circuits, and corrective action if necessary. This AD also provides for optional terminating action for the repetitive inspections. This action is necessary to prevent overheating of the in-line splices of the APU and IDG feeder cables, which can lead to smoke, fumes, and possible fire in the flight deck and cabin. This action is intended to address the identified unsafe condition.
2021-23-20: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by reports that shimming requirements were not met during the assembly of certain structural joints, which can result in reduced fatigue thresholds of the affected structural joints. This AD requires repetitive inspections for cracking of certain areas of the front spar pickle fork and front spar outer chord and repair of any cracking found. The FAA is issuing this AD to address the unsafe condition on these products.
68-23-05: 68-23-05 LOCKHEED: Amendment 39-688. Applies to all Lockheed Model 188A and 188C airplanes. (1) Within the next 50 hours' time in service after the effective date of this AD, unless previously accomplished within the preceding 575 hours' time in service, visually inspect, either internally or externally, No. 1 upper wing plank at No. 2 and 3 nacelles from the forward edge of plank No. 1 aft 4 inches and between wing station 168 and wing station 174, except for those portions of that area hidden by spar cap or rib elements, to detect any evidence of cracks originating at that point and extending aft and outboard. Where the required visual inspection cannot be performed because of existing repairs, the prescribed area will be inspected in accordance with an inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. (2) If cracks exist, appropriate repair must be accomplished before further flight in a manner approved by the Chief, AircraftEngineering Division, FAA Western Region. (3) After initial inspection, such inspection shall thereafter be performed at intervals not to exceed 625 hours' time in service. (4) The repetitive inspection required by (3) may be discontinued upon completion of the appropriate preventive repair installation described in Section I.C.I. or preventive reinforcement of Section I.C.II. of Lockheed Service Bulletin No. 85/SB-665 dated November 11, 1968, (or later FAA approved revision) or upon completion of an equivalent repair approved by the Chief, Aircraft Engineering Division, FAA Western Region. (5) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Airplanes with cracked wing planks may be flown in accordance with special flight permits issued pursuant to FAR 21.197 to a base where repair can be accomplished. Effective July 5, 1968. Revised December 6, 1968.
2004-10-14: The FAA is adopting a new airworthiness directive (AD) that supersedes an existing AD, for Lycoming Engines (formerly Textron Lycoming), direct-drive reciprocating engines (except O-145, O-320-H, O- 360-E, LO-360-E, LTO-360-E, TO-360-E, O-435, and TIO-541 series engines). That AD currently requires inspection of the crankshaft gear installation and rework or replacement of the gears where necessary after a propeller strike, sudden stoppage, at overhaul, or whenever gear train repair is required. This AD requires the same actions but makes the correction that the existing gear retaining bolt and lockplate be removed from service and new hardware installed, and revises the definitions for sudden stoppage and propeller strike. This AD removes the requirement to perform inspections at overhaul and during repair of the gear train, because Lycoming has incorporated those procedures from their Service Bulletin into their Overhaul Manual. This AD results from a change to the definition of a propeller strike or sudden stoppage. We are issuing this AD to prevent loosening or failure of the crankshaft gear retaining bolt, which may cause sudden engine failure.
2012-02-51: We are publishing a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 206L, 206L-1, 206L-3, and 206L-4 helicopters with certain main rotor blades installed to reduce the life limit of those blades. This AD is prompted by two accidents and the subsequent investigations that revealed that, in each accident, a main rotor blade failed because of fatigue cracking. These actions are intended to prevent failure of the main rotor blade and subsequent loss of control of the helicopter.
2021-23-02: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of loss of hydraulic fluid and annunciation of the check fire detect light. This AD requires doing a detailed visual inspection for chafing and proper clearance of the left-hand (LH) and right-hand (RH) main landing gear (MLG) primary zone advanced pneumatic detector (APD) sensing lines, the hydraulic tube assemblies, and the surrounding structure, and doing all applicable corrective action. The FAA is issuing this AD to address the unsafe condition on these products.
70-17-02: 70-17-02 MOONEY: Amdt. 39-1069 as amended by Amendment 39-1072. Applies to Mooney Model M-10 Airplanes. Compliance required before further flight after the effective date of this AD, unless already accomplished. To detect the use of improper screws attaching the left and right rudder pedal shaft assemblies (P/N 720098-1 and 720098-501, respectively) to the nose wheel steering tie rods (P/N 720084 and 720088, respectively), accomplish the following inspection and rework as required or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA, Fort Worth, Texas: a. Remove seats and floorboard. b. Remove screws from left and right rudder pedal shaft assemblies attaching the nose wheel steering tie rods. The screws, nuts and washers should consist of: (1) NAS 221-16 screws (2) AN 363-1032 nuts (3) AN 960-10 washers c. Reinstall the correct hardware specified in b(1), (2) and (3) above. (NOTE: The M-10 Parts Catalog refers to AN 509-10R20 screws, left rudder pedal shaft assembly, P/N 720061, and right rudder pedal shaft assembly, P/N 620062, which are incorrect references.) d. Check the rudder and nose wheel rigging in accordance with the M-10 Service and Maintenance Manual number 10-S.M.-70 dated February, 1970, prior to the reinstallation of the floorboard and seats. Amendment 39-1069 effective on publication in the Federal Register. This amendment 39-1072 becomes effective August 31, 1970.