Results
2003-03-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that currently requires a one-time inspection of the rail release pins and parachute pins of the escape slide/raft pack assembly for correct installation, and corrective actions, if necessary. This amendment adds a requirement to modify the escape slides/slide rafts on the passenger, crew, and emergency exit doors. The actions specified by this AD are intended to prevent improper deployment of the escape slide/raft and blockage of the door in the event of an emergency evacuation. This action is intended to address the identified unsafe condition.
2011-17-01: This amendment supersedes an existing emergency airworthiness directive (EAD) for the specified Agusta S.p.A. (Agusta) model helicopters. That EAD currently requires inspecting the main rotor scissor fitting assembly to determine if there are 2 washers installed under the head of each main rotor scissor fitting assembly fixing bolt (fixing bolt). If there are not 2 washers installed under the head of each fixing bolt, that EAD requires replacing each fixing bolt and installing 2 washers under the head of each fixing bolt. This superseding airworthiness directive (AD) is prompted by the determination that a wrong part number (P/N) for the main rotor scissor fitting assembly was listed in the EAD. This AD retains the requirements of the EAD and corrects a P/N for the main rotor scissor fitting assembly. The actions specified by this AD are intended to prevent a crack in a fixing bolt, failure of a fixing bolt, and subsequent loss of control of the helicopter.
94-21-05 R1: This amendment clarifies an existing airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that currently requires modification, adjustments, and tests of the thrust reverser system; and repair, if necessary. This amendment clarifies a requirement specified in the AD concerning the performance of the operational test of the system. This amendment is prompted by an inquiry from an operator of the affected airplanes concerning that aspect of the existing AD. \n\n\tThe incorporation by reference of certain publications listed in the regulations was approved by the Director of the Federal Register as of November 25, 1994 (59 FR 53573, October 25, 1994).
2011-16-05: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. This action requires you to disconnect the high level fuel switches in the fuel tanks on the affected helicopters. In addition, for helicopters without a crossfeed between the fuel filler necks, you must install a placard on or near the center console fuel panel that specifies fuel transfer limitations. This amendment is prompted by a report that a high level fuel switch probe unit installed on a Model SA-365N helicopter in the rear (right-hand) auxiliary fuel tank group separated, causing damage to the insulation of the electrical wires which supply electrical power to the high level indicator light on the fuel control panel during a fuel transfer. This condition, if not corrected, could lead to exposure of the electrical wires, which could lead to a short circuit and activation of the indicator light without the high fuel level actually being reached.Additionally, a short circuit could become an ignition source inside the fuel tank, and result in a fuel tank explosion and subsequent loss of control of the helicopter.
2011-17-12: 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: Several cases have been reported of cracks in the joint extrusions securing the outer bondment to the acoustic panel of the nacelle transcowl assemblies. Although there is no effect on flight safety (thrust reverser stowed), thrust reverser deployment under rejected take-off or emergency landing load conditions could potentially result in acoustic panel failure and possible runway debris. * * * * * The loss of an acoustic panel during rejected take-off or emergency landing load conditions could leave debris on the runway. This debris, if not removed, creates an unsafe condition for other airplanes during take-off or landing, as those airplanes couldimpact debris on the runway and sustain damage. We are issuing this AD to require actions to correct the unsafe condition on these products.
2011-17-15: We are adopting a new airworthiness directive (AD) for the products listed above. 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: It has been found that moisture may accumulate and freeze, under certain conditions, in the gap between the AOA vane base assembly and the stationary ring of the sensor's body. If freezing occurs both AOA sensors may get stuck and the Stall Warning Protection System (SWPS) will be no longer effective without alerting. This may result in inadvertent aerodynamic stall and loss of controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
97-17-04: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, that currently requires cleaning of front compressor front hubs (fan hubs); initial and repetitive eddy current (ECI) and fluorescent penetrant inspections (FPI) of tierod and counterweight holes for cracks; removal of bushings; the cleaning and ECI and FPI of bushed holes for cracks; and, if necessary, replacement with serviceable parts. In addition, the current AD requires reporting the findings of cracked fan hubs. This amendment does not change the current AD's inspection procedures, or the effectivity date that starts the cycle count for the initial inspection schedules. This AD does, however, add an additional inspection schedule that requires the initial inspection of certain fan hubs with standard drilled holes and coolant channel drilled (CCD) holes to occur earlier than the existing AD requires. Also, this AD requires reporting the results of the initial fan hub inspections. This amendment is prompted by additional investigation since publication of the current AD that reveals that certain fan hubs with standard drilled holes and CCD holes may be more susceptible to cracking. The actions specified by this AD are intended to prevent fan hub failure due to tierod, counterweight, or bushed hole cracking, which could result in an uncontained engine failure and damage to the aircraft.
2011-17-04: 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: One in-service incident has been reported on [a] DHC-8 Series 400 aeroplane in which the right hand main landing gear (MLG) failed to extend using the alternate gear extension system. * * * Failure of [the] MLG to extend and lock could adversely affect the safe landing of the aeroplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
67-18-05: 67-18-05 TECO: Amdt. 39-429, Part 39, Federal Register May 30, 1967. Applies to TECO Model 603 aircraft seats. Compliance required as indicated. To preclude failure of TECO Model 603 aircraft seats installed in civil aircraft, within 100 hours' time in service after the effective date of this AD, remove these seats from service, and replace with FAA-approved seats. This amendment effective June 30, 1967.
95-01-08: This amendment supersedes AD 81-09-03 R1, which currently requires repetitively inspecting the rudder pedal adjusting mounting bracket for cracks on Jetstream Aircraft Limited (JAL) HP137 Mk1 and Jetstream series 200 airplanes, and replacing any cracked bracket. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate, or in certain instances, reduce the number of repetitions of certain short-interval inspections when improved parts or modifications are available. This action requires replacing the mounting bracket with a new mounting bracket of improved design as terminating action for the repetitive inspections that are currently required by AD 81-09-03 R1. The actions specified by this AD are intended to prevent inadvertent rudder movement caused by a cracked rudder pedal adjusting bracket, which, if not detected and corrected, could result in loss of rudder control.