Results
98-11-19: This document corrects a typographical error that appeared in airworthiness directive (AD) 98-11-19 that was published in the Federal Register on May 28, 1998 (63 FR 29096). The typographical error in the applicability statement of the AD resulted in a reference to an engine model that does not exist. This AD is applicable to certain Airbus Model A310 and A300-600 series airplanes. This AD requires a visual inspection to detect cracks in the aft mount beam assembly of the engine; and replacement of any cracked beam with a new beam or beam assembly; and a fluorescent penetrant inspection to detect cracks in the aft mount beam assembly of the engine, and various follow-on actions.
2015-11-10: We are adopting a new airworthiness directive (AD) for Sikorsky Model S-92A helicopters. This AD requires installing a main gearbox (MGB) failed pump sensor and vacuum switch wiring, installing an MGB oil auto bypass system, activating Aircraft Management System (AMS) 7.1 software to show a new visual warning, and installing updated enhanced ground proximity warning system (EGPWS) software that includes an aural [[Page 32462]] annunciation of a complete oil pressure loss condition. This AD also requires inserting a Rotorcraft Flight Manual (RFM) Supplement into the applicable RFM. This AD was prompted by investigation results of in- service oil leakage incidents. The actions are intended to alert and prevent MGB oil loss, which could lead to failure of the MGB and subsequent loss of control of the helicopter.
98-20-31: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect cracking in the pressurized floor pick-up angles on the rear spar of the wing, and replacement of any cracked pick-up angle and its associated diaphragms with improved parts. Such replacement terminates the repetitive inspections for that angle. 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 detect and correct cracking in the pressurized floor pick-up angles at the rear spar of the wing, which could result in reduced structural integrity of the airframe.
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.