Results
2000-11-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 and 767 series airplanes, that currently requires revising the FAA-approved Airplane Flight Manual (AFM) to prohibit the use of certain fuels; and either replacing an existing placard with a new placard, or replacing all dribble flow fuel nozzles (DFFN) with standard fuel nozzles, which terminates the requirements for the new placard and AFM revision. This amendment continues these requirements and adds identical requirements applicable to airplanes on which standard fuel nozzles are not installed. This amendment is prompted by a report of an engine flameout due to use of JP-4 or Jet B fuel during certification testing on an engine with DFFN's installed. The actions specified by this AD are intended to prevent such engine flameouts and consequent engine shutdown.
2015-05-51: We are publishing a new airworthiness directive (AD) for Agusta Model A109A and A109A II helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires replacing a certain part-numbered blade with an approved part- numbered blade. This AD is prompted by an error in the Illustrated Parts Catalog (IPC) that incorrectly allows installation of a certain part-numbered blade on the affected helicopters. These actions are intended to prevent blade failure and subsequent loss of control of the helicopter.
2000-11-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires repetitive inspections of the sliding tube subassembly on the main landing gear (MLG) to detect cracks, and replacement of a cracked subassembly with a new subassembly. This amendment also eventually requires a more extensive, one-time inspection of the same area and corrective actions, if necessary; which terminates the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracking of the MLG sliding tube subassembly, which could result in collapse of the MLG.
2000-11-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that currently requires repetitive high frequency eddy current (HFEC) inspections to detect cracking of the front spar web of the center section of the wing, and repair, if necessary. This amendment requires that the existing inspection be accomplished at a reduced threshold, and adds a requirement that the existing HFEC inspection be accomplished on repaired areas. This amendment is prompted by reports of cracking in repaired areas of the front spar web and cracking of the front spar web on an airplane that had accumulated fewer flight cycles than the inspection threshold of the existing AD. The actions specified by this AD are intended to prevent the leakage of fuel into the forward cargo bay, as a result of fatigue cracking in the front spar web, which could result in a potential fire hazard.
92-21-03: 92-21-03 FOKKER: Amendment 39-8383. Docket No. 92-NM-83-AD. Applicability: Model F28 series airplanes; serial numbers 11003 through 11161, inclusive, 11991, and 11992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent potential failure of the wing-to-fuselage connection, accomplish the following: (a) Prior to the accumulation of 30,000 landings, or prior to June 1, 1997, whichever occurs later, install improved connection angles with reinforcement angles, in accordance with Fokker Service Bulletin F28/53-101, dated May 31, 1991. (b) Accomplishment of the installation required by paragraph (a) of this AD constitutes terminating action for the inspection identified as item 53-10-14 in the Fokker F28 Structural Integrity Program (SIP), which is required by AD 89-07-16 R1, Amendment 39-6444. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) 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. (e) The installation shall be done in accordance with Fokker Service Bulletin F28/53-101, dated May 31, 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 inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on November 24, 1992.
2000-03-18: This document adopts a new airworthiness directive (AD) that applies to all Partenavia Costruzioni Aeronauticas S.p.A. (Partenavia) Models AP68TP 300 "Spartacus" and AP68TP 600 "Viator" airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
50-17-02: 50-17-02 STINSON: Applies to All Model 108 Series Aircraft. Compliance required as indicated. A number of cases have been reported of broken core strands in the rudder cables where they pass over the pulley at fuselage Station 18.75 (first pulley aft of rudded pedals). To preclude failures, the following is therefore required: 1. Within the next 25 hours and at every 100 hours thereafter the following should be accomplished. Remove the rudder cables from the pulleys, bend the cables in a tight "U" where they pass over the pulley, being careful that permanent kinks are not formed, and inspect either visually or by touch. Replace all cables showing signs of breakage. 2. The above inspection may be discontinued and the normal inspections resumed if the following is done: Remove the AN 210-3A pulleys at fuselage Station 18.75; modify the pulley brackets and install larger pulleys, P/N 41001-2, and two cable guards, P/N SK253-2, in accordance with detailed instructions in PiperService Bulletin No. 114 or an equivalent modification.
2015-12-01: We are adopting a new airworthiness directive (AD) for Airbus Helicopters (previously Eurocopter France) Model AS355E, AS355F, AS355F1, and AS355F2 helicopters with a Fueltron flowmeter installed. This AD requires removing each flowmeter, replacing the fuel system hoses, and disabling the electrical connections for the flowmeter installation. This AD was prompted by a report of particle contamination creating an obstruction in a flowmeter which resulted in an uncontrolled flame-out of the engine. The actions of this AD are intended to prevent obstruction of the fuel supply to the flowmeter, which could result in engine flame-out and subsequent loss of control of the helicopter.
2000-11-04: This amendment adopts a new airworthiness directive (AD) that applies to certain Commander Aircraft Company (Commander) Model 114TC airplanes. This AD requires you to replace the existing Aeroquip V-band exhaust clamp with a new clamp of improved design. This AD is the result of reports of this clamp failing on 4 of the affected airplanes. This clamp attaches the exhaust stack to the turbocharger. The actions specified in this AD are intended to prevent the exhaust stack from detaching from the turbocharger due to failure of the V-band exhaust clamp. This could result in the release of high temperature gases inside the engine compartment with a consequent airplane cabin fire.
92-18-05: 92-18-05 AEROSPATIALE: Amendment 39-8349. Docket 91-NM-165-AD. Applicability: Model ATR42-300 and ATR42-320 series airplanes; as listed in Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the collapse of the main landing gear, accomplish the following: (a) Prior to the accumulation of 10,000 landings since new, or within 30 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991: (1) Install a new machined reinforcement fitting (Modification 1281) on the left and right sides of the main landing gear (MLG) in accordance with the service bulletin. (2) Perform a one-time eddy current inspection of the fastener holes on the left and right sides of the MLG to detect fatigue cracks in accordance with the service bulletin. If any cracks are found, prior to further flight, repair in accordance with the service bulletin. (3) Install doublers on Stringer 15 at Frame 25 on the reinforcement plate in accordance with the service bulletin. NOTE: Previous editions of this service bulletin erroneously referred to Stringer 15 as Stringer 14. The doubler can only be installed at Stringer 15. (4) Perform cold working procedures of two fastener holes on the left and right sides of the MLG in accordance with the service bulletin. (b) Airplanes modified prior to the effective date of this AD in accordance with earlier versions of Aerospatiale Service Bulletin ATR42-53-0043 issued prior to Revision 4 need not be inspected or modified further. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport AirplaneDirectorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (d) 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. (e) The installation, inspection, and cold working shall be done in accordance with Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1-2, 29 4 April 30, 1991 3-6, 10-28, 30-32 3 October 30, 1990 7-9 Original April 21, 1989 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC. (f) This amendment becomes effective on October 13, 1992.