Results
2017-25-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 and A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of a vertical strut penetrating through the cabin floor during an emergency water landing and on airframe ground contact at certain speeds/accelerations. This AD requires modification of the fuselage structure at a certain frame. We are issuing this AD to address the unsafe condition on these products.
2002-04-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 series airplanes; Model MD-88 airplanes; and Model MD-90 airplanes, that currently requires a visual check to determine the part and serial numbers of the upper lock link assembly of the nose landing gear (NLG); repetitive inspections of certain upper lock link assemblies to detect fatigue cracking; and modification of the NLG. The existing AD also provides for terminating action for the repetitive inspections. This amendment requires, among other actions, expanding the applicability of the existing AD, revising compliance times; and adding new inspection requirements. This amendment is prompted by a report indicating that an NLG upper lock link fractured prior to landing and jammed against the NLG shock strut, restricting the NLG from fully extending. The actions specified by this AD are intended to prevent the upper lock link assembly fromfracturing due to fatigue cracking, and the NLG consequently failing to extend fully; this condition could result in injury to passengers and flight crew, and damage to the airplane.
2023-04-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a determination that the surface protection is missing between certain aluminum brackets and the struts to which they are attached in the flight deck air distribution system. This AD requires applying surface protection to the affected aluminum brackets and struts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits modifying an airplane using certain service information. The FAA is issuing this AD to address the unsafe condition on these products.
2017-25-03: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a report of sparks and an electrical smell on the flight deck of a Model F28 Mark 0070 airplane. We are issuing this AD to address the unsafe condition on these products.
2002-04-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 F4-605R airplanes, that requires installation of external doublers at frames 29 and 33. The actions specified by this AD are intended to prevent fatigue cracking of certain circumferential joints, which could result in reduced structural integrity of the fuselage in the vicinity of the upper deck cargo door.
2002-03-09: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) LTS101 series turboshaft and LTP101 series turboprop engines. This amendment requires a one-time visual inspection for surface finish and a one-time fluorescent penetrant inspection for cracks of certain impellers installed on LTS101 series turboshaft and LTP101 series turboprop engines. This amendment is prompted by a report of a machining discrepancy that may have occurred during manufacture of the affected impellers. The actions specified by this AD are intended to prevent impeller failure from cracks in the impeller back face area, which could result in an uncontained engine failure.
2023-04-04: The FAA is superseding Airworthiness Directive (AD) 2020-15- 20, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-15-20 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2020-15- 20 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, 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.
2002-03-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-400 series airplanes, that requires a modification and a replacement affecting the fuel tanks in the wings. All affected airplanes require modification of the clearance of the fuel tank vent lines to the left and the right wing fuel tanks. Some affected airplanes also require replacement of three existing fuel probes from the center fuel tank on the left and right wings with new production fuel probes. This action is prompted by mandatory continuing airworthiness information from a foreign airworthiness authority. The actions specified by this AD are necessary to prevent inadequate clearance between the fuel tank vent lines and the adjacent rib structures of the wings or failure of certain temporary, reworked fuel probes in the center fuel tanks in the wings. Either condition could compromise the airplane's lightning protection system, possibly resulting in a fire or explosion if the airplane were hit by lightning. This action is intended to address the identified unsafe condition.
2002-03-13: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60, SD3-60 SHERPA, and SD3-SHERPA series airplanes, that requires a one-time inspection of the wiring harness and power cables of the heated windshield to detect inadequate clearance, inadequate support, or chafing. This amendment also requires corrective action (including re-routing for adequate clearance or replacing damaged cables, as applicable), if necessary. The actions specified by this AD are intended to prevent chafing or damage of the power cables of the heated windshield, which could cause arcing and result in smoke and fire in the cockpit. This action is intended to address the identified unsafe condition.
60-03-09: 60-03-09 VICKERS: Amdt. 97 Part 507 Federal Register February 3, 1960. Applies to All Viscount 745D and 810 Aircraft. Compliance required as indicated. Failures of the main landing gear uplock lever, which prevent extension of the landing gear with the landing gear retracted, have resulted in wheels up landings. Investigation of these incidents disclosed that failures were caused by overloading of the uplock mechanism due to incorrect rigging. To preclude further failures of the uplock lever, the following must be accomplished. (a) Within the next 50 flights* and every 50 flights thereafter, conduct visual "in situ" inspection of all unmodified main landing gear uplock levers for cracks and loose or failed rivets in accordance with ACTION paragraph 1, PTL 213, Issue 3 (for 745D) or ACTION paragraph 1, PTL 79, Issue 2 (for 810). Levers with cracks or loose rivets must be replaced or repaired in accordance with the manufacturer's instructions. (b) Within next 500 flights determine that adjustment of the uplock mechanism is such that compression spring does not bottom at any time during operating cycle, in accordance with numbered paragraphs 5, TNS 223, Issue 2 (for 745D), or numbered paragraph 5, TNS 82, Issue 2 (for 810.) (c) Remove and inspect uplock levers for cracks, loose rivets, distortion or misalignment in accordance with ACTION paragraphs 2 through 5 of PTL 213, Issue 3. Any lever with loose or failed rivets, cracks, or misalignment in excess of 0.03 inch must be replaced or repaired in accordance with manufacturer's instructions. This inspection shall be accomplished when the levers have reached the following lives and every 500 flights thereafter. (1) New levers, unreinforced (P/N 74450, sheet 15, 70150 sheet 53 or 59, and 70152-1491); 2,500 flights. (2) Levers which were free of cracks and reinforced after a period in service, in accordance with either Fig. 1 or 2, PTL 213, Issue 3 (for 745D); or Fig. 1or 2, PTL 79, Issue 2 (for 810); or Capital Airline drawing V.20132, revisions B or C, or scheme contained in Vickers cable S.S. 4939 dated April 10, 1959: 2,000 flights after reinforcement. (3) New levers reinforced before initial installation in accordance with any plan in preceding paragraph: 4,500 flights. (d) Prior to August 1, 1961, incorporate the following parts or equivalent in the main landing gear uplock mechanism in accordance with Vickers modification Bulletin D.2954 and FG.1745, Issue 2: (1) Strengthened steel uplock lever. (2) Spring loaded actuating rod. (3) Hydraulic release for uplock. The inspections required by (a), (b), and (c) are no longer require after accomplishing this modification. (Vickers-Armstrongs Co. PTL 213, Issue 3 (for 745D); PTL 79, Issue 2 (for 810); TNS 223, Issue 2 (for 745D) and TNS 82, Issue 2 (for 810) cover the same subject. Revised August 1, 1960. * This will require operators to maintain a record of flights to ascertain compliance with this AD. If past records are unavailable, the number of flights prior to this AD may be estimated.