Results
2015-12-02: We are adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron Canada Limited (Bell) Model 206L-1, 206L-3, and 206L-4 helicopters. This AD requires installing a placard and revising the limitations section of the rotorcraft flight manual (RFM). This AD was prompted by several incidents of third stage engine turbine wheel failures caused by excessive vibrations at certain engine speeds during steady-state operations. The actions of this AD are intended to prevent turbine failure, engine power loss, and subsequent loss of control of the helicopter.
2017-22-03: We are superseding Airworthiness Directive (AD) 2015-05-02, which applied to all Airbus Model [[Page 49092]] 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. AD 2015-05-02 required revising the maintenance or inspection program to incorporate new, more restrictive airworthiness limitations. This new AD requires revising the maintenance or inspection program to incorporate new or revised structural inspection requirements and adds airplanes to the applicability. This AD was prompted by an evaluation by the design approval holder (DAH), which indicates that principal structural elements and certain life-limited parts are subject to widespread fatigue damage (WFD). We are issuing this AD to address the unsafe condition on these products.
2015-11-06: We are superseding Airworthiness Directive (AD) 2013-18-01 for Eurocopter France Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters. AD 2013-18-01 required inspecting the collective pitch lever for correct locking and unlocking conditions. As published, AD 2013-18-01 contained certain errors. This new AD retains the requirements of AD 2013-18-01, corrects the errors, and updates the type certificate holder's name. The actions in this AD are intended to detect an incorrectly adjusted collective pitch lever, which [[Page 32295]] could result in loss of control of the helicopter.
97-25-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42 series airplanes, that requires removal of certain landing gear attachment pins, and replacement of the pins with serviceable pins. 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 wear of the attachment pins, which could result in collapse of the main landing gear.
2015-11-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, 747-400D, 747-400F, 747-8F, and 747-8 series airplanes. This AD was prompted by reports of very high temperatures, near the floor in the aft lower lobe cargo compartment. This AD requires installing an additional zone temperature sensor (ZTS) assembly in the aft cargo compartment, and, for certain airplanes, installing tape and replacing the markers in the bulk cargo compartment. We are issuing this AD to prevent overheating of the aft lower lobe cargo compartment, where, if temperature sensitive cargo is present, the release of flammable vapors could result in a fire or explosion if exposed to an ignition source.
97-24-03: 97-24-03 DASSAULT AVIATION: Amendment 39-10210. Docket 97-NM-198-AD. Applicability: Model Falcon 2000 airplanes, serial numbers 2 through 31 inclusive; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplishedpreviously. To prevent injury to passengers as a result of inadequate breaking strength of the baggage net, accomplish the following: (a) Within 60 days after the effective date of this AD, revise the Limitations section of the FAA-approved Airplane Flight Manual (AFM) by inserting into the AFM a copy of Falcon 2000 AFM Temporary Change No. 31 (undated). NOTE 2: The revision of the AFM required by this paragraph may be accomplished by inserting a copy of Falcon 2000 AFM Temporary Change No. 31 in the AFM. When this temporary change has been incorporated into general revisions of the AFM, the general revisions may be inserted in the AFM, provided that the information contained in the general revisions is identical to that specified in Falcon 2000 AFM Temporary Change No. 31. (b) Within 6 months after the effective date of this AD, replace the center baggage net in the baggage compartment with a net having reinforced straps, in accordance with Dassault Service Bulletin F2000-76 (F2000-25-2), dated December 11, 1996. After this replacement is accomplished, the AFM revision required by paragraph (a) of this AD may be removed from the AFM. (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, International Branch, ANM-116, 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, International Branch, ANM-116. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD canbe accomplished. (e) The actions shall be done in accordance with Falcon 2000 Airplane Flight Manual Temporary Change No. 31 (undated), and Dassault Service Bulletin F2000-76 (F2000-25-2), dated December 11, 1996. 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 Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, New Jersey 07606. 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. NOTE 4: The subject of this AD is addressed French airworthiness directive 96-291-002(B), dated December 4, 1996. (f) This amendment becomes effective on December 26, 1997.
2016-20-12: We are superseding Airworthiness Directive (AD) 2012-20-07 for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2012-20-07 required revising the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate new limitations for fuel tank systems, and revising the maintenance program to incorporate revised fuel maintenance and inspection tasks. This new AD requires revising the maintenance or inspection program to incorporate revised fuel airworthiness limitations. This AD was prompted by Airbus issuing more restrictive maintenance requirements and/or airworthiness limitations. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2015-10-03: We are superseding Airworthiness Directive (AD) 2014-09-05, for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2014-09-05 required repetitive inspections of certain sidestay upper cardan pins of the main landing gear (MLG) and associated nuts and retainer assemblies, and pin replacement if necessary. This AD was prompted by a determination that a previously optional measurement is necessary to address the identified unsafe condition. This new AD continues to require a detailed inspection for visible chrome of each affected MLG sidestay upper cardan pin, associated nuts, and retainer assembly, and pin replacement if needed, and adds new requirements for measuring cardan pin clearance dimensions (gap check), doing corrective actions, and reporting all findings. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing [[Page 30609]] gear collapse and consequent damage to the airplane and injury to occupants.
97-20-10 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100, -200, and -300 series airplanes, that currently requires modification of the attitude and heading reference systems (AHRS). That action was prompted by a report of loss of power to both AHRS s during flight due to a faulty terminal block to which the signal ground for the AHRS s is connected. The actions specified by that AD are intended to prevent simultaneous power loss to both AHRS s, which could result in reduced controllability of the airplane. This amendment reduces the applicability of the existing AD.
98-07-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with procedures to prevent thrust loss during initial climb. This action also requires installing a new or modified electronic control unit on each engine, which, when accomplished, terminates the requirement for the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent significant thrust loss during initial climb, which could result in an increased risk of collision with obstacles in the initial climb path of the airplane.
2001-19-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-19-51, which was sent previously to all known U.S. owners and operators of Eurocopter France (ECF) Model SA341G, SA342J, and SA-360C helicopters by individual letters. This AD requires, before further flight, replacing a certain unairworthy main rotor head torsion tie bar (tie bar) with an airworthy tie bar. This AD also requires revising the limitations section of the maintenance manual by adding a life limit for certain tie bars. This AD is prompted by an accident involving an ECF Model SA341G helicopter due to the failure of a tie bar. The actions specified by this AD are intended to prevent failure of a tie bar, loss of a main rotor blade, and subsequent loss of control of the helicopter.
2015-10-07: We are superseding airworthiness directive (AD) 2014-01-01 for all Turbomeca S.A. Arrius 2F turboshaft engines. AD 2014-01-01 required a one-time inspection of the ejector assembly nozzle of certain serial number (S/N) lubricating devices and, if a discrepancy was found, removal and replacement of the affected ejector assembly nozzle with a part eligible for installation. This AD requires the same action as AD 2014-01-01 and expands the list of affected S/N lubricating devices. This AD was prompted by the determination that additional lubricating devices, identifiable by S/N, may have an incorrect bonding of the nozzle on the ejector assembly. We are issuing this AD to prevent failure of the ejector assembly nozzle, which could lead to an in- flight shutdown (IFSD) of the engine, damage to the engine, and damage to the helicopter.
98-06-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires modification to reinforce the joints of certain fuselage frames. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking of the fuselage frames, which could result in reduced structural integrity of the airplane.
97-15-12: This amendment adopts a new airworthiness directive (AD) that applies to certain Burkhart Grob, Luft-und Raumfahrt (Grob) Model G 109 sailplanes. This action requires installing a damper and new bell crank lever on the rudder, in addition to adjusting the weight and balance of the sailplane, to correct the tendency of flutter at specific excitation frequencies. For those Grob Model G 109 sailplanes that have previously accomplished this installation, a modification to the damper and bell crank lever, and adjustment to the weight and balance is required. These actions are prompted by the discovery of rudder vibration problems during testing of two Grob Model G 109 sailplanes. The actions specified by this AD are intended to prevent vibration of the rudder, which could result in structural damage and eventual loss of control of the sailplane.
2015-10-06: We are adopting a new airworthiness directive (AD) for certain Lycoming TIO-540-AJ1A reciprocating engines. This AD was prompted by several reports of cracked engine exhaust pipes. This AD requires inspection of the engine exhaust pipes for cracks and replacement of the turbocharger mounting bracket. We are issuing this AD to prevent failure of the exhaust system due to cracking, which could lead to uncontrolled engine fire, harmful exhaust gases entering the cabin resulting in crew incapacitation, and damage to the airplane.
2015-10-05: We are adopting a new airworthiness directive (AD) for Airbus Helicopters (previously Eurocopter France) Model AS365N3, EC155B, and EC155B1 helicopters with an external life raft in the footsteps with certain part-numbered junction units. This AD requires inspecting the junction units of the external life raft deployment system for corrosion, removing any corrosion, and performing certain measurements to determine whether the junction unit must be replaced. This AD is prompted by failure of a life raft deployment test and corrosion damage inside the left-hand junction unit. These actions are intended to prevent failure of an external life raft to deploy preventing evacuation of passengers during an emergency.
97-25-16: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires a one-time inspection of the tailplane (horizontal stabilizer) leading edges and surrounding area for discrepancies, and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent separation of the horizontal stabilizer from the fin, which could lead to reduced controllability of the airplane.
2015-08-51: We are publishing a new airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F-28A, 280, F-28C, F- 28C-2, F-28C-2R, 280C, F-28F, F-28F-R, 280F, 280FX, and 480 helicopters. This AD was sent previously to all known U.S. owners and operators of these helicopters and supersedes Emergency AD (EAD) 2015- 04-51, dated February 12, 2015. This AD requires inspecting certain main rotor spindles (spindles) for cracks and reporting the inspection results to the FAA. This AD is prompted by a fatal accident and reports of spindles with cracks. The actions specified in this AD are intended to detect a crack in a spindle and prevent loss of a main rotor blade and subsequent loss of control of the helicopter.
2015-09-06: We are superseding Airworthiness Directive (AD) 2014-26-04 for certain GROB-WERKE Models G115EG and G120A airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a defective starter solenoid. We are issuing this AD to require actions to address the unsafe condition on these products.
98-13-28: This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta S.p.A. (Agusta) Model A109C and A109K2 helicopters. This action requires a one-time inspection of each tail rotor blade (blade) for debonding, and if debonding exists which exceeds certain limits, replacement of the blade with an airworthy blade. This amendment is prompted by two incidents in which helicopters lost a blade tip fairing during ground run-up. The actions specified in this AD are intended to prevent loss of the tip fairing on a blade, which could result in increased vibrations, loss of the tail rotor assembly, and subsequent loss of control of the helicopter.
2015-08-07: We are adopting a new airworthiness directive (AD) for certain Zodiac Aerotechnics (formerly Intertechnique Aircraft Systems) oxygen [[Page 27082]] mask regulators. This AD was prompted by a report of a malfunctioning mask having an inflatable harness with a high premature rupture rate due to defective silicon. This AD requires inspecting and replacing defective harnesses with new or modified serviceable units. We are issuing this AD to detect and correct defective harnesses, which could lead, in case of a sudden depressurization event, to a harness rupture, thereby providing inadequate protection against hypoxia and possibly resulting in unconsciousness of the affected flightcrew member and consequent reduced control of the airplane.
2015-09-01: We are adopting a new airworthiness directive (AD) for Airbus Model EC225LP helicopters. This AD requires repetitive visual and tap test inspections of each main rotor blade (blade) leading edge stainless steel protective strip (strip) for a crack, cut, or blind or open debonding (debonding), and taking approved corrective measures. If there is a crack or if there is debonding that exceeds acceptable limits, this AD requires, before further flight, repairing or replacing the blade with an airworthy part. This AD was prompted by suspected water seepage through a crack in the blade strip resulting in significant debonding. The actions of this AD are intended to prevent loss of the blade strip, excessive vibrations induced by blade weight imbalance, and subsequent loss of control of the helicopter.
75-08-14: 75-08-14 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2166 as amended by Amendment 39-2201 is further amended by Amendment 39-2627. Applies to Lockheed- California Company Model L-1011-385-1 series airplanes certificated in all categories. To prevent possible failures of the C-1, C-2, and C-3 cargo door hooks due to cracks, accomplish the following: (a) Within 275 additional flight hours after the effective date of this AD, unless already accomplished, perform the following per Lockheed Alert Service Bulletin 093-52-A079, Revision 1, dated March 26, 1975 or later FAA-approved revision. (1) An inspection of the C-1, C-2 and C-3 cargo door hooks for identification configuration and affixing of appropriate part numbers; (2) A dye penetrant inspection of all hooks for cracks; (3) Replace all cracked hooks prior to further flight. (4) Scrap hooks identified as P/N's 1517205-103/-105. (5) Check rigging of hooks and doors for usage, and rerigg, as required.(b) Perform a dye penetrant inspection for cracks at intervals not to exceed 1500 hours time in service, of the C-1 and C-2 cargo door hooks identified as P/N's 1517205-107/-109 (per the inspection of (a)(1), above). Replace all cracked hooks prior to further flight. (c) Within 3000 flight hours after the initial inspections performed per (a)(1) and (2), above, replace all hooks identified as P/N's 1517205-107/-109 with hooks identified as P/N's 1517205-111/-113 on the C-1 and C-2 cargo doors. (d) The repetitive inspections required by paragraph (b) of this AD may be discontinued after accomplishment of modifications and checks in accordance with FAA-approved Lockheed-California Company Service Bulletin 093-52-087, dated March 11, 1976, or later FAA- approved revisions or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (Reference: Paragraph (f), AD 76-09-03). (e) Equivalent inspections and replacements may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. (f) Airplanes may be flown to a base for the accomplishment of the inspections and replacements required by this AD, per FAR's 21.197 and 21.199. Amendment 39-2166 became effective April 16, 1975. Amendment 39-2201 became effective May 19, 1975. This amendment 39-2627 becomes effective June 7, 1976.
2025-02-12: The FAA is superseding Airworthiness Directive (AD) 2023-20-03 for certain Austro Engine GmbH Model E4 and E4P engines. AD 2023-20-03 required repetitive engine oil analysis for aluminum content outside the acceptable limits and, if necessary, replacement of the pistons, piston rings, con-rods assembly, and crankcase or, as an alternative, replacement of the engine core. Since the FAA issued AD 2023-20-03, the manufacturer identified errors in the lists of affected engines and provided updated information, which prompted this AD. This AD retains the requirements of AD 2023-20-03, adds compliance times for additional affected engine serial numbers, and removes certain engine serial numbers from the applicability of the existing AD. The FAA is issuing this AD to address the unsafe condition on these products.
2025-02-14: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG Model Trent 1000-AE3, Trent 1000- CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3, Trent 1000-R3, Trent 7000-72, and Trent 7000-72C engines. This AD was prompted by reports of cracked intermediate pressure compressor (IPC) shaft assembly front air seals. This AD requires an inspection of the affected IPC shaft assembly for cracking and, depending on the results of the inspection, repetitive inspections or replacement of the IPC shaft assembly front air seals, 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.