Results
2004-15-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-202, -203, -223, and -243 airplanes, and A330-300 series airplanes, that requires modification of the control box of the auxiliary power unit (APU). This action is necessary to prevent uncommanded in-flight shutdown of the APU, which could result in loss of critical electrical systems when the airplane is operated in emergency electrical configuration, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
96-18-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Piaggio Model P-180 airplanes, that requires replacement of outflow/safety valves with serviceable valves. This amendment is prompted by a report of cracking and subsequent failure of outflow safety valves in the pressurization system. The actions specified by this AD are intended to prevent such cracking and subsequent failure of the outflow/safety valves, which could result in rapid decompression of the airplane.
2021-03-16R1: The FAA is removing Airworthiness Directive (AD) 2021-03-16, which applied to all Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2021-03-16 required inspecting each sliding door and replacing the upper rail or front roller or removing the front roller from service if necessary. Since the FAA issued AD 2021-03-16, inspection results and further investigation have confirmed that the in-flight loss of a sliding door, which prompted AD 2021-03-16, was an isolated case resulting from incorrect operation and maintenance error. Therefore, the FAA has determined that no unsafe condition is likely to exist or develop on the sliding doors on other helicopters in the fleet. Accordingly, AD 2021-03-16 is removed.
72-08-01: 72-08-01 BOEING: Amdt. 39-1428. Applies to Boeing Model 747 airplanes, listed in Boeing Service Bulletin 747-32-2118, dated December 20, 1971, or later FAA-approved revisions except the Model 747-131. \n\tCompliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 400 hours' time in service, and thereafter at intervals not to exceed 500 hours' time in service from the last inspection, until modified per Boeing Service Bulletin 747-32-2118, dated December 20, 1971, or later FAA-approved revisions. \n\tTo detect failed landing gear alternate extension actuators, accomplish the following: \n\tInspect landing gear alternate extension actuators in accordance with Boeing Service Bulletin 747-32-2118, dated December 20, 1971, or later FAA-approved revisions, until modified in accordance with Boeing Service Bulletin 747-32-2118, dated December 20, 1971, or later FAA-approved revision, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\tThis amendment becomes effective April 7, 1972.
96-18-11: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10 and -15 series airplanes, that requires repetitive inspections to detect cracks in the bulkhead tee caps, and repair and follow-on actions, if necessary. It also provides for an optional terminating modification for the repetitive inspections. This amendment is prompted by reports of cracking in the bulkhead tee caps at a fuselage station in the area of certain longerons due to fatigue. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in loss of pressurization and damage to adjacent structure.
2004-15-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that currently requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate updated Airworthiness Limitation Items, Safe Life Items, and Certification Maintenance Requirements. The actions specified by this AD are intended to ensure the structural integrity of the airplane by ensuring that fatigue cracking of certain structural elements is detected and corrected in a timely manner. This action is intended to address the identified unsafe condition.
2022-07-05: The FAA is superseding Airworthiness Directive (AD) 2022-05- 09, which applied to certain MARS A.S. emergency parachutes. AD 2022- 05-09 required removing emergency parachutes with certain manufacture dates or serial numbers from service. Since the FAA issued AD 2022-05- 09, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on this aviation product. The MCAI identifies the unsafe condition as the length of the ripcord between the pins being too long, which could cause a malfunction of the emergency parachute. This AD retains the actions required by AD 2022-05-09 and expands the applicability.
68-06-02: 68-06-02 GENERAL DYNAMICS (CONVAIR): Amendment 39-564. Applies to General Dynamics (Convair) Type 30A incorporating Supplemental Type Certificate SA414EA- D. Compliance required as indicated: (a) Upon arrival at the next stop, install a placard on each of the three right hand row seats at fuselage station 1344 (row 28 on American Airlines' Drawing No. FCA-2047 Rev. D) stating, "Do Not Occupy". (b) The placard required by part (a) may be removed by incorporating an approved modification strengthening the seat support structure approved by the Chief, Engineering & Manufacturing Branch, Eastern Region. This amendment is effective March 22, 1968.
2004-15-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections for fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors of the bottom skin panel of the wings, and related corrective action. This amendment also provides for an optional terminating action, which ends the repetitive inspections. This action is necessary to prevent fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors and the bottom skin panel of the wings, which could result in reduced structural integrity of the wings. This action is intended to address the identified unsafe condition.
47-47-06: 47-47-06 MARTIN: (Was Service Note 2 of AD-795-1.) Applies to All Model 202 Airplanes With HSP 23260 Propellers With YB2H17F3-48R Blades and Westinghouse D-30 Generators. Compliance required at first major (long period) inspection and thereafter as specified below. Carefully inspect the engine accessory section rear cover for signs of fatigue cracks particularly near the generator mounting pad at the first long period inspection and at every short period inspection thereafter until engine overhaul. After the engine overhaul, the same inspection sequence shall be observed.