Results
2020-22-11: The FAA is superseding Airworthiness Directive (AD) 2017-18- 17, which applied to all Airbus SAS Model A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 F4-605R, A300 F4-622R, and A300 C4-605R Variant F airplanes. AD 2017-18-17 required modifying certain fuselage frames and a repair on certain modified airplanes. This AD continues to require the actions in AD 2017-18-17, and also requires, for certain airplanes, an inspection to determine if rotating probe inspections were performed prior to oversizing of the open-holes, and repair if necessary; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report indicating that the material used to manufacture the upper frame feet was changed and negatively affected the fatigue life of the frame feet, and a determination that more work is required for certain airplanes that were previously modified. The FAA is issuing this AD to address the unsafe condition on these products.
2014-20-11: We are superseding Airworthiness Directive (AD) 2011-07-05 for certain Sicma Aero Seat 9140, 9166, 9173, 9174, 9184, 9188, 9196, 91B7, 91B8, 91C0, 91C2, 91C4, 91C5, and 9301 series passenger seat assemblies; and Sicma Aero Seat 9501311-05, 9501301-06, 9501311-15, 9501301-16, 9501441-30, 9501441-33, 9501311-55, 9501301-56, 9501441-83, 9501441-95, 9501311-97, and 9501301-98 passenger seat assemblies. AD 2011-07-05 required a general visual inspection for cracking of backrest links, replacement with new links if cracking is found, and eventual replacement of all links with new links. This new AD requires a new general visual inspection for cracking of backrest links, which includes new seat backrest links; replacement with new links if cracking is found; and eventual replacement of all links with new links. This AD was prompted by a report that new seat backrest links could be affected by cracks similar to those identified on the backrest links with the previous design. We are issuing this AD to detect and correct cracks in the backrest links, which could affect the structural integrity of seat backrests. Failure of the backrest links could result in injury to an occupant during emergency landing conditions.
2014-20-05: We are adopting a new airworthiness directive (AD) for Empresa Brasileira de Aeronautica S. A. (EMBRAER) Models EMB-110P1 and EMB- 110P2 airplanes. This AD results from 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 corrosion and cracking on the rudder trim tab actuator terminal. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-14-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet series 100 & 400) airplanes, that requires a one-time inspection of the aft edge of the left and right main windshields to determine whether a certain placard is installed, and corrective actions if necessary. This action is necessary to prevent stress-related cracking of the windshields, and subsequent excessive frequency of abnormal procedures specified in the airplane flight manual and/or an emergency descent be accomplished, which poses an increased risk to passengers and crew members. This action is intended to address the identified unsafe condition.
2020-09-14: The FAA is superseding Airworthiness Directive (AD) 2020-03- 12, which applied to all Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-03-12 required revising the existing airplane flight manual (AFM) to define a liquid-prohibited zone in the flight deck and provide procedures following liquid spillage on the center pedestal. This AD continues to require revising the existing AFM, and also requires installing a removable integrated control panel (ICP) cover in the flight deck and further revising the AFM to include instructions for ICP cover use, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by the FAA's determination that a removable integrated control panel (ICP) cover must be installed to prevent damage from spillage and that the existing AFM must be revised. The FAA is issuing this AD to address the unsafe condition on these products.
97-20-15: This amendment supersedes an existing airworthiness directive (AD), applicable to Hiller Aircraft Corporation Model UH-12A, UH-12B, UH-12C, UH-12D, and UH-12E helicopters, that currently requires a dye penetrant inspection of the head of the main rotor outboard tension- torsion (T-T) bar pin for cracks; a visual inspection of the outboard T-T bar pin for proper alignment and an adjustment, if necessary; and, installation of shims at the inboard end of the drag strut. This amendment requires the same actions required by the existing AD, but allows a magnetic particle inspection of the T-T bar pin as an alternative to the currently required dye penetrant inspection, and requires reporting the results of the inspections only if cracks are found, rather than reporting all results of inspections as required by the existing AD. This amendment is prompted by an FAA analysis of a comment to the existing AD, and the fact that no cracks have been reported since the issuance of the existing AD. The actions specified by this AD are intended to prevent cracks in the head area of the outboard T-T bar pin, which could result in loss of in-plane stability of the main rotor blade and subsequent loss of control of the helicopter.
2014-20-09: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of missing clamps that are required to provide positive separation between the alternating current (AC) feeder cables and the hydraulic line of the landing gear alternate extension. This AD requires an inspection for missing clamps that are required to provide positive separation between the AC feeder cables and the hydraulic line of the landing gear alternate extension, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct chafing of the AC feeder cable. A chafed and arcing AC feeder cable could puncture the adjacent hydraulic line, which, in combination with the use of the alternate extension system, could result in an in- flight fire.
74-23-07: 74-23-07 CESSNA: Amendment 39-2010. Applies to Cessna Model A188B (Serial Numbers 18801375 through 18801824, including those serial numbers with suffix "T") airplanes. Compliance: Required as indicated, unless already accomplished. To preclude induction air inlet duct collapse and resulting in engine power loss within the next 25 hours' time in service after the effective date of this AD, accomplish the following: Replace the existing induction air inlet duct with Cessna P/N 1650044-1 bellows type induction air inlet duct or equivalent, in accordance with Cessna Service Letter No. SE 74-23, dated October 4, 1974, or later approved revisions. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective November 15, 1974.
2014-20-04: We are superseding Airworthiness Directive (AD) 94-12-03 for certain Airbus Model A320 series airplanes. AD 94-12-03 required modification of the belly fairing structure. This new AD requires repetitive inspections for cracking of the four titanium angles between the belly fairing and the keel beam side panel, an inspection for cracking of the open holes if any cracking is found in the titanium angles, and repair or replacement if necessary; this new AD also expands the applicability of AD 94-12-03. This AD was prompted by reports of cracks at the lower riveting of the four titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage. We are issuing this AD to detect and correct cracking of the titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage, which could affect the structural integrity of the airplane.
2019-19-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-202, -243, -243F, -302, -323, and -343 airplanes. This AD was prompted by a report that cracks have been found within the ring gears of the slat geared rotary actuators (SGRAs) due to a change in the manufacturing process and inadequate post-production non-destructive testing for potential cracking. This AD requires an inspection to determine the part number and serial number of the SGRAs, and replacement of each affected SGRA with a serviceable part, 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.