Results
50-19-02: 50-19-02 CONVAIR: Applies to All Model 240 Aircraft. Compliance required as indicated. Failures of the rudder flight tab balance weight brackets and of the rudder closing spar ahead of the flight tab have been experienced on service aircraft. In order to preclude the possibility of these failures progressing to such an extent that the airworthiness of the airplane is impaired, it is considered necessary that the following be accomplished on all CVAC Model 240 Series aircraft: A. To be accomplished as soon as practicable but not later than next No. 1 inspection and to be repeated at each No. 2 inspection thereafter. Inspect the rudder flight tab balance weight brackets for cracks in the neck down areas approximately 1 inch from the flight tab and also adjacent to the edges of the counterweight. Inspect the rudder closing spar for cracks in the areas adjacent to the rudder flight tab hinge brackets. All cracks, when found, must be replaced or suitably repaired before next flight. B. To be accomplished by January 1, 1951. Reinforce the rudder flight tab balance weight brackets, and the attachment of the brackets to the tab and to the balance weight. (CVAC Service Bulletin 240-355A covers this same subject.) NOTE: Although evidence indicates that these failures will be materially reduced after incorporation of the above, sufficient evidence of trouble-free operation is not available. Therefore, it will be necessary that the inspections outlined under part A, be continued at each No. 3 inspection after the incorporation of part B, until sufficient evidence of trouble-free operation has been supplied to the FAA to warrant discontinuance of this inspection. This supersedes AD 50-06-03.
2004-14-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that currently requires deactivating both thrust reversers and revising the airplane flight manual (AFM) to ensure safe and appropriate performance during certain takeoff conditions. This amendment requires installing modifications that will add an independent third line of defense on the thrust reversers, which would enhance their redundancy and terminate the requirements of the existing AD. The actions specified by this AD are intended to prevent in-flight deployment of the thrust reversers, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2022-04-01: The FAA is adopting a new airworthiness directive (AD) for DG Flugzeugbau GmbH Model DG-1000T gliders and Schempp-Hirth Flugzeugbau GmbH Model Duo Discus T gliders with a Solo Kleinmotoren GmbH Solo Model 2350C or 2350D engine installed. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of the bearing of the upper pulley of the belt driven reduction gear resulting in separation of the propeller from the engine. This AD requires replacing a certain hex-nut and establishing a life limit for the ball bearing assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2022-05-01: The FAA is adopting a new airworthiness directive (AD) for certain Learjet, Inc., Model 35, 35A (C-21A), 36, 36A, 55, 55B, 55C, and 60 airplanes. This AD was prompted by a report indicating that a repair station approved Learjet spoiler assemblies for return to service after extending their life limit. This AD requires removing certain spoiler assemblies from service and prohibits their installation. The FAA is issuing this AD to address the unsafe condition on these products.
48-12-04: 48-12-04 LOCKHEED: Applies to All 49 and 149 Aircraft As Specified by Civil Air Regulations Amendments 41-3, 42-2, and 61-2. To be accomplished not later than the dates specified in the above amendments as revised by special Civil Air Regulations Serial Nos. 385, 390, 390A, 390B and any subsequent regulations affecting these compliance dates. All air carrier aircraft must be modified in all necessary respects to comply with the fire prevention requirements outlined in CAR Amendments 41-3, 42-2, and 61-2. Compliance with the requirements may be completed by accomplishing the modifications outlined in the following listed Lockheed Service Bulletins. Other rework shown to be equivalent to that covered by the Service Bulletins will also be acceptable. 49/SB-175, Installation of Cabin Door Louver Covers and Door Stops; 49/SB-179, Inspection and Replacement of Crew Seat Upholstery Covers; 49/SB-180, Rework of Receptacles for Used Towels, Paper, and Waste; 49/SB-181, Rework ofBaggage Compartment Lining; 49/SB- 183B, Installation of Smoke Detectors; 49/SB-184, Installation of CO2 Provisions in Cargo Compartment; 49/SB-188, Enclosure of Cabin Heater Fuel Control System Components; 49/SB- 191, Replacement of Firewall and Fire Seal Fittings and Cable Seals; Installation of CO2 Fire Extinguisher Check Valves; 49/SB-153, Sealing of Access Doors in Stub Wing Fillet; 49/SB-216, Relocation of Fenwal Fire Detectors; 49/SI-44, Installation of Metal Main Landing Gear Aft Doors.
2004-14-20: The FAA supersedes Airworthiness Directive (AD) 2003-21-07, which applies to certain The Cessna Aircraft Company (Cessna) Model 525 airplanes. AD 2003-21-07 currently requires you to disengage the pitch trim circuit breaker and AP servo circuit breaker and then tie strap each of them to prevent them from being engaged. Not utilizing this equipment prevents a single-point failure. This AD is the result of Cessna having now developed and made changes in the design of the affected trim printed circuit board (PCB) assembly to allow the use of the assembly and the prevention of the single-point failure, and identification of additional airplanes that have the same unsafe condition. Consequently, this AD requires you to remove and replace an old trim PCB assembly with a new design assembly or modify an old trim PCB assembly to the new design. We are issuing this AD to correct this single-point failure in the electric pitch trim system, which will result in a runaway pitch trim condition where the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.
2022-04-07: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B64, -1B64/P1, -1B64/P2, - 1B67, -1B67/P1, -1B67/P2, -1B70, -1B70/75/P1, -1B70/75/P2, -1B70/P1, - 1B70/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76/P2, - 1B76A/P2, GEnx-2B67, -2B67B, and -2B67/P model turbofan engines. This AD was prompted by an in-flight shutdown (IFSD) of an engine and subsequent investigation by the manufacturer that revealed an improperly torqued fuel metering unit (FMU) bypass valve (BPV) plug. This AD requires a shim check inspection of the FMU BPV plug and, depending on the results of the inspection, replacement of the FMU. The FAA is issuing this AD to address the unsafe condition on these products.
2022-03-17: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332L2 and EC225LP helicopters. This AD was prompted by a report of loss of tightening torque on the nut that attaches the tail gear box (TGB) bevel wheel. This AD requires repetitive inspections (measurements) of the angular clearances of the TGB, and, depending on the findings, replacement of the TGB with a serviceable TGB, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also provides terminating action for certain repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
2022-03-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -300, -800, and -900 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports that the instructions on the doghouse door lock placard are unclear and incomplete. This AD requires replacing the placard with an improved instruction placard, 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 under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
47-32-08: 47-32-08 BELL: (Was Mandatory Note 8 of AD-1H-1.) Applies to Models 47B and 47B3 Serial Numbers 2 Through 5, 7 Through 11, 13 Through 17, 19 Through 25, 27 Through 78. Compliance required not later than 25 hours operation after September 15, 1947. The stabilizer bar dampers should be inspected for the presence of an "AL" stamped on one of the attachment lugs. If such a marking does not appear, thoroughly inspect visually for leakage or other defects and replace if necessary with P/N A12141 (Houds) (stamped "AL"). A cracking or failing of the phenolic abutments has been reported, wherein the subject dampers have been rendered ineffective, thus affecting the flight characteristics of the helicopter. (Bell Service Bulletin 47C47 covers this same subject.)