Results
92-02-12: 92-02-12 BOEING: Amendment 39-8148. Docket No. 91-NM-142-AD. \n\n\tApplicability: Model 767 series airplanes, listed in Boeing Alert Service Bulletin 767- 21A0098, dated May 9, 1991, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent halon from escaping through the bulk cargo ventilation flapper valve when the fire extinguishing system is activated, accomplish the following: \n\n\t(a)\tWithin 4,000 flight hours after the effective date of this AD, remove the bulk cargo ventilation flapper valve in accordance with Boeing Alert Service Bulletin 767-21A0098, dated May 9, 1991. \n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, whomay concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t(d)\tThe removal requirements of this AD shall be done in accordance with Boeing Alert Service Bulletin 767-21A0098, dated May 9, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\t(e)\tThis amendment (39-8148, AD 92-02-12) becomes effective on March 2, 1992.
97-05-13: This amendment adopts a new airworthiness directive (AD), applicable to CFM International CFM56-5 series turbofan engines, that requires rework of the air turbine engine starter. This amendment is prompted by three reports of air turbine engine starter failures. The actions specified by this AD are intended to prevent an air turbine engine starter failure, which could result in damage to the engine electrical harnesses.
2021-08-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes; Model A319-111, A319-112, A319- 113, A319-114, A319-115, A319-131, A319-132, and A319-133 airplanes; Model A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes. This AD was prompted by reports that certain oxygen supply solenoid valves are a potential source of increased flow resistance within the flightcrew oxygen system. This AD requires a detailed inspection (flow test) of certain solenoid valves, and replacement if necessary, as specified in European Union Aviation Safety Agency (EASA) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
92-14-09: 92-14-09 FOKKER: Amendment 39-8291. Docket No. 91-NM-63-AD. Applicability: Model F-28 Mark 0100 series airplanes, certificated in any category. Compliance: Required within 180 days after the effective date of this AD, unless accomplished previously. To prevent the pilot and co-pilot from receiving inaccurate flight information, accomplish the following: (a) Inspect the flight mode panel (FMP), part number 622-7477-301 or 622-7477-401, to verify if Modification 6 has been installed. (1) If Modification 6 has been installed, no further action is required. (2) If Modification 6 has not been installed, remove the FMP and replace it with an FMP having Modification 6 installed in accordance with Fokker Service Bulletin SBF100-22-031, dated September 9, 1991. (b) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The removal and replacement of the FMP shall be done in accordance with Fokker Service Bulletin SBF100-22-031, dated September 9, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspectedat the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on August 20, 1992.
2021-09-07: The FAA is superseding Airworthiness Directive (AD) 2019-17- 02, which applied to certain Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. AD 2019-17-02 required inspecting certain part-numbered actuators for corrosion, removing them as necessary, and reporting certain information. This new AD continues to require inspecting certain part-numbered actuators, removing them as necessary, and reporting; and extends the compliance time for the initial inspection, expands the applicability, and includes new requirements for repetitive replacement of affected actuators; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a hard landing of a helicopter and the discovery of a ruptured and displaced tie bar inside the piston of the longitudinal single-axis actuator of the main rotor actuator (MRA). The FAA is issuing this AD to address the unsafe condition on these products.
96-22-04: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model Avro 146-RJ70A, -RJ85A, and -RJ100A airplanes, that requires repetitive inspections for cracking of fuselage frame 29, and repair, if necessary. This amendment is prompted by results of fatigue testing, which revealed fatigue cracking in the web and inboard flange of frame 29. The actions specified by this AD are intended to prevent reduced structural integrity of the fuselage due to fatigue cracking in frame 29.
97-04-03: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. TFE731 series turbofan engines, that requires removal from service of certain first stage low pressure turbine (LPT) seal plates prior to accumulating the new, reduced cyclic life limit, and replacement with serviceable LPT seal plates. This amendment is prompted by a report that the machined LPT seal plate geometry did not meet the design intent due to drawing ambiguity. The actions specified by this AD are intended to prevent fatigue cracking and subsequent uncontained failure of an LPT seal plate.
97-05-08: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 727 series airplanes. This action requires repetitive pre-modification inspections to detect cracks in the forward support fitting of the number 1 and number 3 engines; and repair, if necessary. This AD also provides for an optional high frequency eddy current (HFEC) inspection, and, if possible, modification of the fastener holes; and various follow-on actions. Accomplishment of these optional actions would constitute terminating action for the repetitive pre-modification inspections. This amendment is prompted by reports indicating that fatigue cracks were found in the forward support fitting of the number 1 and number 3 engines. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in failure of the support fitting and consequent separation of the engine from the airplane.
95-19-12: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires various repetitive inspections to detect cracks in certain panels of the lower skin of the wing, and in certain fixed ribs of the leading edge of the wing. This amendment also requires repair or replacement of cracked parts, which would terminate certain repetitive inspections. This amendment is prompted by reports of cracking in certain panels of the lower skin of the wing, and in certain fixed ribs of the leading edge of the wing due to fatigue-related stress. The actions specified by this AD are intended to ensure the structural integrity of the wing by detecting fatigue-related cracking in a timely manner in the panels of the lower skin of the wing or in the fixed ribs of the leading edge of the wing.
2021-08-12: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by crack indications found in the lower aft wing skin bolt holes where the flap tracks attach to the track support fitting. This AD requires repetitive inspections for cracking of the left and right wing, lower aft wing skin aft edge, at certain flap track locations, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.