Results
2020-23-10:
2006-25-15: The FAA is adopting a new airworthiness directive (AD) for Sicma Aero Seat third occupant seat assemblies, 133 series. This AD requires visually inspecting the installation of the two headrest bushings and installing Mecanindus pins to secure the bushings. This AD results from Sicma's determination that missing or incorrectly secured bushings could loosen and cause disengagement of the headrest from the seat during a high-energy stop of the airplane, possibly injuring the seat occupant. We are issuing this AD to prevent disengagement of the headrest from the seat during a high-energy stop of the airplane that could injure the seat occupant.
2020-22-16: The FAA is superseding Airworthiness Directive (AD) 2017-25- 04, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The FAA is also superseding AD 2019-03-17, which applies to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, and -271N airplanes; and Model A321 series airplanes. AD 2019-03-17 required revising the existing maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. This AD retains the requirements of AD 2019-03-17 and also requires new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2006-25-09: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD-11F airplanes. This AD requires a general visual inspection for installation of conduit and chafing damage on the auxiliary power unit (APU) power feeder wires and the upper surface of the auxiliary fuel tank and repair if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to detect and correct unprotected APU power feeder wires that come into close proximity to the upper surface of the auxiliary "piggy back'' fuel tank, which could result in a potential ignition source, and in combination with flammable fuel vapors, could cause a fuel tank explosion and consequent loss of the airplane.
2020-22-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD requires inspecting the affected parts and associated frame bores for discrepancies, applicable corrective actions, and reporting certain information if necessary. This AD was prompted by reports of corrosion on attachment screws and fittings fastening the main gearbox (MGB) suspension bars to the fuselage. The actions of this AD are intended to address an unsafe condition on these products.
2006-25-08: The FAA is adopting a new Airworthiness Directive (AD) for all Columbia Aircraft Manufacturing (previously The Lancair Company) Models LC41-550FG and LC42-550FG airplanes equipped with Kelly Aerospace Thermal Systems Supplemental Type Certificate (STC) SA02260CH, Thermawing Deice System (also known as E-Vade). This AD requires you to deactivate the deice system and install a placard in clear view of the pilot. This AD results from problems with the installation of the Kelly Aerospace Thermal Systems Thermawing Deice System following STC SA02260CH. We are issuing this AD to prevent a short circuit condition at the deice heater connector, which could result in damage to the wings and horizontal stabilizer. This damage could lead to reduced structural integrity of the airplane.
2020-21-10: The FAA is superseding Airworthiness Directive (AD) 2017-19- 24, which applies to Model A319-111, -112, -113, -114, -115, -131, - 132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The FAA is also superseding AD 2018-16-04, which applies to Airbus SAS Model A320-216, -251N, and -271N airplanes; and Model A321-251N, -253N, and -271N airplanes; as well as the models in AD 2017-19-24. Those ADs required revising the existing maintenance or inspection program, as applicable, to incorporate new or more \n\n((Page 65191)) \n\nrestrictive maintenance requirements and airworthiness limitations. Since AD 2018-16-04 was issued, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
80-08-07: 80-08-07 ROCKWELL INTERNATIONAL: Amendment 39-3750. Model NA265-40 (all), -60 (all) and -70 S/N 370-2 through -6 and 370-8 and -9 series airplanes except those modified by Supplemental Type Certificate SA687NW, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent adverse flight characteristics resulting from elevator delamination accomplish the following: (a) On aircraft with honeycomb elevator trailing edge surfaces in service for one calendar year or more, or with 1,000 hours' time in service, whichever occurs earlier; (1) Within 100 hours' additional time in service, or within 30 days from the effective date of this AD, whichever occurs earlier, inspect left and right elevator trailing edges for delamination as specified in paragraphs 1(a) and 1(b) of "Modification Instructions" of Rockwell International Service Bulletin No. 48 dated January 9, 1980, and; (2) At intervals not to exceed 500 hours' timein service or 6 months from the last such inspection, whichever occurs sooner, repeat the inspection of paragraph (a)(1) of this AD. (b) Repair delaminated elevator trailing edges prior to further flight per paragraph 3 of "Modification Instructions" of Rockwell International Service Bulletin No. 48 dated January 9, 1980 and prior to the accumulation of 1,000 hours' additional time in service on new trailing edges, inspect per paragraph (a)(1) of this AD and reinspect at repetitive intervals specified per paragraph (a)(2) of this AD. (c) Installation of non-honeycomb trailing edges constitutes terminating action for the inspections required by this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective April 21, 1980.
2020-21-11: The FAA is superseding Airworthiness Directive (AD) 2015-22- 08, which applied to all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-211, -212, -214, -231, -232, and -233 airplanes. The FAA is also superseding AD 2018-17-19, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, - 131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, and -271N airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -253N, and -271N airplanes. The FAA is also superseding AD 2019-19-15, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, and -271N airplanes; and Model A321 series airplanes. AD 2019-19-15 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
65-08-02: 65-08-02 SIKORSKY: Amdt. 39-54 Part 39 Federal Register April 9, 1965. Applies to Models S-55, S-62, and S-61 Series Helicopters. Compliance required as indicated. Pitting in main rotor blade spars has resulted in fatigue cracks. To detect possible pitting and cracking, accomplish the following: (a) Within 10 hours' time in service after the effective date of this AD and at intervals thereafter within 10 hours' time in service from the last inspection, until (b) has been accomplished, conduct a visual inspection for cracks of the spars of S14-10-2100 Series main rotor blades, Serial Numbers 55MH15340 through 55MH19858, in accordance with the inspection procedures specified in Sikorsky Service Bulletin 55B10-4 or 62B10-3. Replace all main rotor blades found with cracks in the spar before further flight. (b) Unless already accomplished, within 25 hours' time in service after the effective date of this AD accomplish the following: (1) On S-55 and S-62 helicopters, conduct an X-ray inspection of the spar of S14-10-2100 Series and S14-10-2201 Series main rotor blades, Serial Numbers 55MH15340 through 55MH19858, for pitting in accordance with the inspection procedures specified in Sikorsky Service Bulletin 55B10-4 or 62B10-3. (2) On S-61 helicopters, conduct an X-ray inspection of the spar of S6115- 20501 Series main rotor blades, Serial Numbers 61M101 through 61M1429, for pitting in accordance with the inspection procedures specified in Sikorsky Service Bulletin 61B15-3. (3) Replace all blades with pitting in the spar, before further flight. This directive effective April 9, 1965.