Results
2021-11-24: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by significant changes made to the airworthiness limitations (AWLs) related to fuel tank ignition prevention and the nitrogen generation system (NGS). This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate the April 2019 or November 2020 revision of the airworthiness limitations document. The FAA is issuing this AD to address the unsafe condition on these products.
97-15-02: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR42 and ATR72 series airplanes, that requires replacement of the attachment clips on the wing-to-fuselage fairings and on the upper cowlings of the engine nacelle with new improved attachment clips, and adding cup washers on the wing-to-fuselage fairing panels on certain airplanes. This amendment also requires a one-time inspection of certain fairings and the upper cowlings of the engine nacelle to detect discrepancies of the attachment hardware and the fairing panel; and replacement of the panel with a serviceable panel, if necessary. This amendment is prompted by a report of deformed attachment clips found on the wing-to-fuselage fairings and on the upper cowlings of the engine nacelle, and by a report of severe inflight vibration due to a loose wing/body fairing panel. The actions specified by this AD are intended to prevent deformation of the attachment clips due to insufficient strength of the attachment clip material. Such deformation of the attachment clips could result in the fairings and cowlings detaching from the airplane during flight and subsequently causing damage to the empennage or posing a hazard to persons or property on the ground.
2018-06-10: We are adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC Model HA-420 airplanes. This AD requires incorporating a temporary revision into the airplane flight manual and replacing faulty power brake valves upon condition. This AD was prompted by reports of unannunciated asymmetric braking during ground operations and landing deceleration. We are issuing this AD to address the unsafe condition on these products.
2013-10-04: We are superseding an existing airworthiness directive (AD) for all Piper Aircraft, Inc. Models PA-31, PA-31-325, and PA-31-350 airplanes. That AD currently requires a detailed repetitive inspection of the exhaust system downstream of the turbochargers and repair or replacement of parts as necessary. This new AD requires visual repetitive inspections, expanding the inspection scope to include the entirety of each airplane exhaust system. This AD was prompted by reports of exhaust system failures upstream of aircraft turbochargers and between recurring detailed inspections. We are issuing this AD to correct the unsafe condition on these products.
2003-11-17: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC- 12/45 airplanes. This AD requires you to inspect the front and rear surfaces of the pressure dome for damage and cracks, and, if necessary, accomplish repairs. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to detect and correct damage and cracks to the pressure dome, which could lead to rapid decompression.
2013-16-14: We are adopting a new airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) EC 135 P1, P2, P2+, T1, T2, and T2+ helicopters equipped with a certain main transmission housing upper part. This AD requires installing a corrugated washer in the middle of the main transmission filter housing upper part and modifying the main transmission housing upper part. This AD was prompted by an inspection of housing upper parts that revealed the bypass inlet in the oil filter area was not manufactured in accordance with applicable design specifications. The actions of this AD are intended to prevent failure of the main transmission and subsequent loss of control of the helicopter.
73-26-09: 73-26-09 CESSNA: Amendment 39-1763 as amended by Amendment 39-1983. Applies to Model 500 (Serial Numbers 500-0001 through 500-0183) airplanes, with 400 or more hours' time in service. Compliance: Required as indicated, unless already accomplished. To detect cracks in the left and right flight compartment side windows (P/Ns 5511265-3 and -4), within the next 25 hours' time in service after the effective date of this AD, (on all airplanes with 400 or more hours' time in service) and thereafter at intervals not to exceed 200 hours' time in service, except as provided in Paragraph B(2), accomplish the following in accordance with the inspection procedures set forth in Cessna Service Letter SL56-2, dated November 9, 1973, or FAA-approved revisions or any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region: A) Either by use of x-ray procedures outlined in Cessna Service Letter SL56-2, dated November 9, 1973, inspect the flight compartment side windows (P/Ns 5511265-3 and -4) at the attachment locations, or in the alternative, visually inspect the window attachment locations by first removing the window outside retainers in accordance with the manufacturer's service instructions. B) (1) Prior to further pressurized flight replace unairworthy windows if as a result of any inspection required by this AD any of the following conditions are found: (a) A crack is visible in the window pane which has progressed past the edge of the retainer. (b) Any three or more screw holes are interconnected by a crack. (c) A crack has progressed to three inches or longer. (d) The sum of individual crack lengths exceeds six inches. (2) If a crack is discovered in a window pane but does not exceed any of the conditions specified in Paragraph B(1), inspect the window panes each 100 hours' time in service thereafter per Paragraph A of the AD until the window panes are replaced. C) Upon accumulation of 400 hours' time in service inspect replacement window panes in accordance with the requirements of this AD. D) The inspections and 400 hour window replacement requirements of this AD may be discontinued upon installation of left and right flight compartment side windows (P/N 5511285-3 and -4) in accordance with Cessna Service Bulletin SB 56-4 dated July 24, 1974, or later approved revisions. Any equivalent method must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-1763 became effective December 26, 1973. This Amendment 39-1983 becomes effective October 9, 1974.
2013-17-01: We are adopting a new airworthiness directive (AD) for certain Eurocopter France (Eurocopter) Model AS350 and AS355 helicopters. This AD [[Page 54381]] requires inspecting the tail rotor control stop screws to determine if they are correctly aligned and adjusting the screws if they are misaligned. This AD is prompted by the discovery of a loose nut on the tail rotor control stop and a misaligned tail rotor control stop screw. The actions of this AD are intended to detect a loose nut or a misaligned stop screw, which, if not corrected, could limit yaw authority, and consequently, result in a loss of helicopter control.
2018-06-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. This AD was prompted by a report of fatigue cracking found in a certain fuselage frame, which severed the inner chord and web. This AD requires inspecting the fuselage frame for existing repairs, repetitive inspections, and applicable repairs. We are issuing this AD to address the unsafe condition on these products.
2003-11-15: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-90-30 airplanes, that requires replacing the lanyards on the pressure relief door for the thrust reverser with new, improved lanyards, and doing associated modifications. This action is necessary to ensure that the lanyards on the pressure relief door have adequate strength. Lanyards of inadequate strength could allow the pressure relief door to detach from the thrust reverser in the event that an engine bleed air duct bursts, which could result in the detached door striking and damaging the horizontal stabilizer, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.