Results
2011-27-01: We are adopting a new airworthiness directive (AD) for Turbomeca Arriel 1B turboshaft engines. 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 an increase in hot gas ingestion and an increase of temperature in the gas generator (GG) turbine rotor, potentially resulting in turbine damage and an uncommanded in-flight shutdown. We are issuing this AD to prevent over-temperature damage of the GG turbine, which could result in an uncommanded in-flight engine shutdown, and a subsequent forced autorotation landing or accident.
2021-19-13: The FAA is adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport Regional Model ATR42-500 and ATR72- 212A airplanes. This AD was prompted by reports indicating that certain Thales global positioning system (GPS) satellite based augmentation system (SBAS) receivers provided, under certain conditions, erroneous outputs on aircraft positions. This AD requires replacing affected GPS SBAS receivers with new, improved receivers, 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.
2021-19-06: The FAA is superseding Airworthiness Directive (AD) 2007-02- 13, which applied to certain Dornier Luftfahrt GmbH (type certificate currently held by RUAG Aerospace Services GmbH) Model Dornier 228-212 airplanes. AD 2007-02-13 required inspecting the landing gear carbon brake assembly. This AD requires inspecting certain carbon brake assemblies and corrective actions if necessary. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the European Union Aviation Safety Agency (EASA) to correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as loose bolts and nuts on the landing gear carbon brake assembly. The FAA is issuing this AD to address the unsafe condition on these products.
58-17-03: 58-17-03 CURTISS-WRIGHT AND MARTIN: Applies to C-46 Series (including C- 46/CW20-T) and 202, 202A, 404 aircraft having propeller hydraulic feathering lines routed over or attached to engine cylinder assemblies. Compliance recommended at the next engine overhaul but required by June 1, 1959. Several cases of engine cylinder failures have occurred in which it was subsequently impossible to feather the propeller. In these cases, the feathering line which was routed over a front row cylinder was severed by a dislodged cylinder, thus preventing feathering and causing an additional fire hazard from oil being pumped over the engine. The record of cylinder failures from studs loosening or breaking indicates that the front row cylinders are mainly involved. To prevent loss of feathering control from such failures, either of the following is required: 1. The propeller feathering line must be routed between cylinders. It must be supported in a manner avoiding attachment toa cylinder, and the line located at least three to four inches from the cylinder flanges. 2. The propeller feathering line must be routed between cylinders on the front row of cylinders in the manner described above. However, it will be acceptable for the line to be routed over a rear row cylinder provided it can be determined that sufficient flexibility is provided to prevent feathering line damage in the event of cylinder failure.
96-09-15: This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in freezing rain or freezing drizzle conditions by providing more clearly defined procedures and limitations associated with such conditions.
2004-09-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes powered by General Electric or Pratt & Whitney engines, that currently requires repetitive inspections to detect discrepancies of the four aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions, if necessary. That AD also provides an optional terminating action for repetitive inspections. This amendment expands the area on which the inspections are required. The actions specified by this AD are intended to prevent fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine. This action is intended to address the identified unsafe condition.
59-10-03: 59-10-03 CESSNA: Applies to Cessna Models 172, Serial Numbers 28000 Through 36003; 180, 180A, Serial Numbers 30000 Through 32991; 182, 182A, Serial Numbers 33000 Through 34500. Compliance required by July 15, 1959. The Narco Model 300 position light flasher is of non-fail-safe design and to comply with the Civil Air Regulations a three position switch should be installed to permit steady operation of the lights in case of flasher failure. In addition, a means should be provided to enable the pilot to tell when the flasher has failed. Plexiglas reflectors at the wing tip lights or a monitor light on the instrument panel are acceptable means. The Van Dusen flasher (Cessna P/N 0511309-1) is acceptable as a fail-safe design. (Cessna Service Letter 180/182-41 covers this same subject.)
98-12-21: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA. 315B helicopters that requires an initial and repetitive visual inspections and modification, if necessary, of the horizontal stabilizer spar tube (spar tube). This amendment is prompted by an in-service report of fatigue cracks that initiated from corrosion pits. The actions specified by this AD are intended to prevent fatigue failure of the spar tube, separation and impact of the horizontal stabilizer with the main or tail rotor and subsequent loss of control of the helicopter.
2004-09-18: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires repetitively inspecting the seat rails located in the passenger cabin for evidence of damage and corrosion, repairing any damage or corrosion, and replacing any floor panels found to be "soft" due to ingress of moisture. This action is necessary to detect and correct corrosion on the seat rails for the passenger seats, which could result in the reduced structural integrity of the passenger seats, detachment of the seats from the seat rails, and injury to passengers. This action is intended to address the identified unsafe condition.
69-23-05: 69-23-05 MESSERSCHMITT-BOLKOW Gmb.H.: Amdt. 39-873. Applies to Bolkow Model Bolkow Junior Aircraft, Serial Numbers 505 through 684. Compliance is required as indicated unless already accomplished. To prevent failures of the lower engine-mounting bolts within the next 100 hours' time in service after the effective date of this AD, replace the lower engine-mounting bolts P/N 298-21093.22 with new bolts P/N 208- 21093.22 in accordance with Messerschmitt-Bolkow Mounting Instructions No. 04/68, dated October, 1968, or an FAA-approved equivalent (Messerschmitt-Bolkow Service Bulletin No. 208-1/68, dated November 14, 1968, covers this same subject). This amendment becomes effective December 11, 1969.