Results
2015-15-04: We are adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron, Inc. (Bell), Model 204B, 205A, 205A-1, and 212 helicopters. This AD requires removing a certain part-numbered main rotor (M/R) blade grip (grip) from service. This AD is prompted by an error in a parts manufacturer approval (PMA) that incorrectly allows installation of the grips on the Bell Model 212. The actions specified in this AD are intended to prevent grip failure, separation of the M/R blade, and subsequent loss of control of the helicopter.
58-17-04: 58-17-04 PIAGGIO: Applies to All Models P.136-L1 and P.136-L2 Aircraft. Compliance required by December 1, 1958. Several cases have occurred where the water rudder inadvertently dropped into the extended position during water landings. In order to avoid future occurrences, Piaggio & Co. recommends that a hook be incorporated at the water rudder retraction cylinder, which is controllable by the pilot. In addition, the forward section of the water rudder should be cut off, in order to prevent any interference with the retraction of the water rudder because of the accumulation of debris. This modification is considered mandatory by the Registro Aeronautico Italiano. The FAA concurs and considers compliance therewith mandatory. (Piaggio & Co. Change Order No. 36 L-42, dated May 29, 1958, covers the same subject.)
2001-26-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires replacement of the observer's seat latch assembly with a new, improved seat latch assembly. This action is necessary to prevent the observer's seat from separating from its attachment points in the event of an accident or emergency landing, due to an understrength seat latch assembly. This action is intended to address the identified unsafe condition.
2015-12-04: We are superseding airworthiness directive (AD) 2006-15-08 for all Honeywell International Inc. TPE331-1, -2, -2UA, -3U, -3UW, -5, - 5A, -5AB, -5B, -6, -6A, -10, -10AV, -10GP, -10GT, -10P, -10R, -10T, - 10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR turboprop engines with certain Honeywell part numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies, installed. AD 2006-15- 08 required initial and repetitive dimensional inspections of the fuel control drives for wear, and replacement of the FCU and fuel pump. This new AD requires initial and repetitive dimensional inspections of the affected fuel control drives and insertion of certain airplane operating procedures into the applicable flight manuals. This AD was prompted by reports of loss of the fuel control drive, leading to engine overspeed, overtorque, overtemperature, uncontained rotor failure, and asymmetric thrust in multi-engine airplanes. We are issuing this AD to prevent failureof the fuel control drive that could result in damage to the engine and airplane.
81-07-06: 81-07-06 TELEDYNE CONTINENTAL MOTORS: Amendment 39-4071. Applies to Continental A-65, A75, C75, C85, C90, A-100, C125, and O-200 series engines with AC fuel pumps, TCM part number 40585, 40695 or 631391 installed. Compliance required within 30 days after the effective date of this AD, or within the next 25 hours time in service after the effective date of this AD, whichever occurs first, unless already accomplished within the last 12 months and at intervals not to exceed 12 months after the last inspection. To prevent fuel starvation due to fuel flow restriction through the pump screen accomplish the following: a. Remove safety wire and bolt from fuel pump top cover. Discard fiber washer under bolt. b. Remove the fuel pump top cover. Discard cork cover gasket. c. Remove fuel pump screen. d. Inspect the fuel pump and fuel pump screen for contamination. (1) If contaminated, clean fuel pump and fuel pump screen. (2) If fuel pump is damaged by corrosion, replace with an applicable serviceable fuel pump. (3) If fuel pump screen is damaged by corrosion or handling, replace with a serviceable fuel pump screen, TCM P/N 643913. e. Reinstall fuel pump screen, fuel pump cover with new cork cover gasket, TCM P/N 643915 and new bolt gasket P/N 643914. Torque bolt to 30 5 inch-pounds. f. Resafety wire fuel pump top cover bolt and check for leaks. g. Make the appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Teledyne Continental Motors Service Bulletin M81-8, dated March 9, 1981, pertains to this subject. This amendment becomes effective April 1, 1981.
2019-22-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-200B, 747-200C, 747-200F, 747-300, 747- 400, 747-400D, 747-400F, 747-8F, and 747-8 series airplanes. This AD was prompted by reports of uncommanded fore and aft movement of the Captain's and First Officer's seats. This AD requires, for the Captain's and First Officer's seats, repetitive horizontal actuator identifications, repetitive checks of the horizontal movement system (HMS), a detailed inspection of the HMS for certain airplanes, and applicable on-condition actions. This AD also requires an inspection to determine the part number and, if applicable, the serial number of the Captain's and First Officer's seats, and applicable on-condition actions. This AD also provides an optional terminating action for the repetitive actions for certain seats. The FAA is issuing this AD to address the unsafe condition on these products.
2017-21-05: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by the determination that new inspection tasks for the drag brace support fitting of the main landing gear (MLG) and corrosion prevention and control program (CPCP) related tasks are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate airworthiness limitations, including new inspection tasks for the drag brace support fitting of the MLG and to implement CPCP related tasks. We are issuing this AD to address the unsafe condition on these products.
2025-02-11: The FAA is adopting a new airworthiness directive (AD) for certain FS 2001 Corp, FS 2002 Corporation, FS 2003 Corporation, Piper, and Piper Aircraft, Inc. (Piper) airplanes. This AD was prompted by reports of broken rudders. This AD requires replacing any rudder equipped with a rudder post made from a certain carbon steel with a rudder equipped with a rudder post made from a certain low-alloy steel. The FAA is issuing this AD to address the unsafe condition on these products.
61-01-02: 61-01-02 MARTIN: Amdt. 239 Part 507 Federal Register January 5, 1961. Applies to All Models 202, 202A and 404 Aircraft With Main Landing Gear Torque Arms Having More Than 12,000 Hours' Time In Service. Compliance required as indicated. Failures of Model 404 main landing gear torque arms have occurred in the lower attachment point where the torque scissors attach to the strut. Also, a failure was found in the apex (upper to lower torque arm attach point). As a result, the following must be accomplished within the next 225 hours' time in service, unless already accomplished within the last 225 hours' time in service, and every 450 hours' time in service thereafter. Inspect all surfaces of the torque arm lugs which attach the torque scissors to the strut for cracks or corrosion, using dye penetrant, ultrasonic or radiographic method, or FAA approved equivalent. Beginning with the first repetitive inspection, also inspect all surfaces of the torque arm apex using dye penetrant, ultrasonic or radiographic method, or FAA approved equivalent. Removal of bolts and bushings is required only if dye penetrant is used. If cracks or corrosion are found, the torque arm must be replaced before the next flight. This directive effective January 6, 1961.
2015-06-02 R1: We are revising an airworthiness directive (AD) 2015-06-02 for GA 8 Airvan (Pty) Ltd Model GA8-TC320 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 missing required engine mount fire seal washers, which could reduce the engine retention capability in the event of a fire. We are issuing this AD to require actions to address the unsafe condition on these products.