Results
72-25-06: 72-25-06 BEECH: Amdt. 39-1572. Applies to Beech Models C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), RC-45J (SNB-5P) D18C, D18S, E18S, E18S-9700, G18S, H18, JRB- 6, 3N, 3NM and 3TM Aircraft certificated in all categories with STC SA4-1531, STC SA111WE, STC SA1832WE or any other STC modification incorporating the provisions of the Volpar TriGear Installation. Compliance required as indicated. To prevent possible failure of the nose landing gear to extend from the retracted position on those aircraft with Volpar TriGear installed, accomplish the following: For airplanes incorporating Volpar Tricycle Landing Gear, within the next 100 hours' time in service after the effective date of this AD unless already accomplished, modify the Volpar nose walking beam assembly, P/N 261, in accordance with Volpar Service Bulletin No. 21, as revised 7 August 1972, or later FAA-approved revision, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. NOTE: For bulletins, parts or service information contact: Volpar Incorporated 16300 Stagg Street Van Nuys, California 91406 Phone 213-787-4393 NOTE: Pilots are cautioned to conduct a through pre-flight inspection in this area. A decal should be located on the nose gear shock strut housing listing the recommended strut inflation pressure. This amendment becomes effective December 9, 1972.
2024-24-10: The FAA is superseding Airworthiness Directive (AD) 2023-05- 02, which applied to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2023-05-02 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, 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.
47-21-22: 47-21-22 REPUBLIC: (Was Service Note 2 of AD-769-2.) Applies to Model RC-3 Aircraft. Inspection required before next flight and at each subsequent 25 hours of operation. If no tab type lockwashers are installed, check tightness of engine mounting bolts to torque of 25 foot-pounds on 3/8-inch bolts and 30 foot-pounds on 7/16-inch bolts. If it is found that loosening has occurred it will be necessary to install tab type lockwashers under all engine mounting bolts. (AMI P/N 15175 for 3/8-inch bolts, AMI P/N 15176 for 7/16-inch bolts.) If tab type lockwashers have been installed previously and tabs are in place, inspection is required only at the regular 100-hour periods. (Aircooled Motors Service Bulletin No. 47 pertains to this subject.)
2024-24-09: The FAA is superseding Airworthiness Directive (AD) 2022-24- 05, which applied to all Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2022-24-05 required repetitive inspections of certain galleys for corrosion of trolley retainer aluminum blocks and delamination of the upper panel of the trolley compartment, and applicable corrective action. This AD was prompted by the list of affected galleys being revised, and a new modification that was developed to restore the design integrity of the affected galleys. This AD continues to require the actions in AD 2022-24-05, provides optional terminating action for the repetitive inspections, revises the list of affected parts, and prohibits the installation of affected parts under certain conditions; 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.
48-13-04: 48-13-04 PIPER: Applies to PA-12 Aircraft Serial Numbers 12-1 Through 12-3450; 12- 3452; 12-3454 Through 12-3467; 12-3469 Through 12-3471; 12-3473 Through 12-3491; 12- 3993 Through 12-3504; 12-3506; 12-3507; 12-3511 Through 12-3520; 12-3522 Through 12- 3531; 12-3533; 12-3535 Through 12-3543; 12-3545 Through 12-3548; 12-3553; 12-3901 Through 12-3958; 12-3960 Through 12-3962; 12-3965 Through 12-3976; 12-3983; 12-3984; 12- 3988; 12-3990 Through 12-3994. Compliance required by May 1, 1948. To avoid arcing between the fuse clip and the wire attachment plate on the fuse block caused by loosening of the fuse clip attaching rivets, replace rivets by No. 4 machine screws and stake threads. (Piper Service Bulletin No. 105 dated February 18, 1948, covers this same subject.)
47-31-02: 47-31-02 NAVION: (Was Mandatory Note 11 of AD-782-3.) Applies to Serial Numbers NAV-4-2 Through NAV-4-850. To be accomplished not later than November 1, 1947. Remove carburetor vapor return line hose P/N 75696 and install fire-resistant hose P/N 76701. This change is necessary to prevent premature failure of the vapor return line in the event of an engine compartment fire. (NAA Field Service Bulletin No. 23 dated April 11, 1947, covers this rework.)
2008-26-09: 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: Bombardier Aerospace has completed a system safety review of the CL-600-2B19 aircraft fuel system against the new fuel tank safety standards * * *. The assessment showed that insufficient electrical bonding between the refuel/defuel shutoff valves and the aircraft structure could occur due to the presence of a non-conductive gasket (Gask-O- Seal). In addition, it was also determined that the presence of an anodic coating on the shutoff valve electrical conduit connection fitting could affect electrical bonding. The above conditions, if not corrected, could result in arcing and potential ignition source inside the fuel tank during lightning strikes andconsequent fuel tank explosion. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2016-05-10: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS 365 N3, EC 155B, and EC155B1 helicopters with certain external life rafts. This AD requires installing a sheath kit on the left-hand and right-hand raft deployment control systems. This AD is prompted by a report that the life raft deployment control could not be adjusted due to problems with the life raft deployment linkage. This unsafe condition, if not corrected, could result in failure of the external life raft to deploy and prevent evacuation of passengers during an emergency.
46-12-01: 46-12-01 CESSNA: (Was Mandatory Note 8 of AD-722-5.) Applies Only to AT-17 and UC-78 Series Airplanes. Inspection required immediately. On all AT-17 or UC-78 Series airplanes that have not been re-covered with grade A fabric at time of (or subsequent to) the original civil certification, inspect the fabric on wings and control surfaces to determine that the fabric complies with grade A fabric standards and has a sample breaking strength of at least 56 pounds. The lacing cord should also be checked and should have a breaking strength of at least 56 pounds when tested double. This inspection will require the testing of one or more samples of fabric and cord, the location from which the samples are to be taken and the number necessary will be determined by the CAA representative.
2024-23-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A321-251NX, -252NX, -253NX, -271NX, and -272NX airplanes. This AD was prompted by the discovery during a quality review performed during manufacturing, that a torque strip indicator (material "Dykem") had been applied on the orifice fitting on certain slides' inflation reservoirs' venting holes. This AD requires an inspection for discrepancies of affected parts (certain reservoirs having certain orifices) and replacement of discrepant affected parts, and prohibits installing affected parts, 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.