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67-31-04: 67-31-04 CESSNA: Amdt. 39-516, Part 39, Federal Register November 29, 1967. Applies to Models 150G and 150H Airplanes, Serial Numbers 15064533 through 15067891. To prevent loss of longitudinal control, unless already accomplished, prior to further flight, remove the glove compartment from the aircraft. If after it is removed the glove compartment is modified, the modification must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region, before it is reinstalled in the aircraft and the aircraft returned to service. This amendment effective November 29, 1967, for all persons except those to whom it was made effective by air mail letter dated November 17, 1967.
2021-11-04: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by a report of main landing gear (MLG) retractions after striking an obstacle or severe wheel imbalance after a tire failure. This AD requires inspections for correct height of the lock link over-center stop pin and for correct gaps of the left-hand and right-hand MLG downlock proximity sensors, replacement of the shim if necessary, corrective actions, and installation of a new, improved proximity sensor electronic unit (PSEU) with software changes. The FAA is issuing this AD to address the unsafe condition on these products.
2020-23-01: The FAA is adopting a new airworthiness directive (AD) for all GE Aviation Czech s.r.o. (GEAC) M601D-11, M601E-11, M601E-11A, M601E- 11AS, M601E-11S, M601F, H75-200, H80-100, H80-200, and H85-200 model turboprop engines. This AD was prompted by reports of engine power fluctuations occurring during ground tests. This AD requires the removal and replacement of the fuel control unit (FCU). The FAA is issuing this AD to address the unsafe condition on these products.
2003-22-11: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) Model AS350B, B1, B2, B3, BA, D, and AS355E helicopters, that currently requires removing certain serial-numbered main servocontrols before further flight. This amendment contains the same requirements but also requires removing certain other main and tail servocontrols on or before 550 hours time- in-service (TIS) or 24 months, whichever occurs first. Also, this amendment adds the Eurocopter Model AS350C, D1, and AS355F, F1, F2, and N helicopters to the applicability. This amendment is prompted by the discovery of a manufacturing defect in another set of servocontrols. The actions specified by this AD are intended to prevent failure of a main or tail servocontrol in the flight control system and subsequent loss of control of the helicopter.
2021-09-19: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-171N airplanes, Model A320-271N, -272N, and -273N airplanes, and Model A321-271N, -272N, -271NX, and -272NX airplanes. This AD was prompted by a report indicating that during a full scale fatigue test of the forward engine mounts, premature wear was identified on the forward engine mount shackle assemblies; in addition, during bearing replacement, the bearing lock washer was found broken. This AD requires replacing any forward engine mount shackle assemblies having a certain part number with a serviceable part, and re- identifying the engine mount, or replacing any forward engine mount assemblies having a certain part number, 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.
2007-21-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: * * * * * * * * the FAA set-up in January 1999 an Ageing Transport Systems Rulemaking Advisory Committee (ATSRAC) to investigate the potential safety issues in aging aircraft as a result of wear and degradation in their operating systems. Under this plan, all Holders of type Certificates aircraft are required to conduct a design review, to preclude the occurrence of potential unsafe conditions as the aircraft aged. * * * * * The unsafe condition is degradation of the fuel system, which could result in loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
95-02-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires modification of certain fuselage support structure for the number 2 galley. This amendment is prompted by results of engineering tests and analyses which revealed that certain fuselage support structure for the number 2 galley is unable to support certain loads that may occur during emergency landing conditions. If the fuselage support structure breaks, the galley may shift and cause blockage of the forward service door (galley door). The actions specified by this AD are intended to prevent inability of passengers and crew to exit the airplane through this door after an emergency landing.
96-02-06: 96-02-06 BOEING; MCDONNELL DOUGLAS; LOCKHEED; FOKKER; AND BRITISH AEROSPACE REGIONAL AIRCRAFT LIMITED, AVRO INTERNATIONAL AEROSPACE DIVISION (Formerly British Aerospace, plc; British Aerospace Commercial Aircraft, Limited): Amendment 39-9494. Docket 95-NM-55-AD. Supersedes AD 95-04-01, Amendment 39-9153; and AD 95-09-05, Amendment 39-9208. \n\n\tApplicability: The following models and series of airplanes, certificated in any category, equipped with Honeywell Standard Windshear Detection Systems (WSS): \n\n\nManufacturer and \nModel of Airplane\n\nType of Computer\n\nPart Numbers \nBoeing 727-100 and -200\nStandard Windshear\n(Honeywell STC)\n4061048-902, -903, and-904 \n4068054-901 \n4068060-901 \nBoeing 737-100 and -200\nStandard Windshear\n\n4061048-903, -904, and -905 4068058-903\nBoeing 737-200\t\nPerformance\nManagement\n(Honeywell STC)\n4050730-904 through -911 \n4051819-906 \nBoeing 737-300\nStandard Windshear\n(Honeywell STC) \n4068060-901 \nBoeing 747-100 and -200\nStandard Windshear\n(Honeywell STC) \n4061048-904 \nMcDonnell Douglas\nDC-8-50, -60, and -70\nStandard Windshear\n(Honeywell STC) \n4068046-903 \nMcDonnell Douglas\nDC-9-10, -21, -31\n-41, and -51 \nStandard Windshear\n(Honeywell STC)\n4068046-901, -902\n4068048-901, -902 \nMcDonnell Douglas\nDC-9-80 and MD-88 \nWindshear (OEM TC)\n4059845-902\nMcDonnell Douglas\nMD-90-30 \nWindshear (OEM TC)\n4059845-910 \nMcDonnell Douglas\nMD-11\nFlight Control\n(OEM TC)\n4059001-901 \nthrough -905 \n(with windshear \n\toption selected) \nLockheed L-1011-385-1,\n-385-1-14, -385-1-15,\nand -385-3 \nStandard Windshear\n(OEM TC) \n4068044-901\nFokker F28\nMark 1000, 2000,\n3000, and 4000 \nStandard Windshear\n(Honeywell STC) \n4068052-901\nFokker F28 Mark 0100\nFlight Management\n(OEM TC)\n4052502-951 \n(with windshear \n\toption selected) \nBritish Aerospace Avro\n146-RJ70A, -RJ85A,\nand -RJ100A \nFlight Control\n(OEM TC)\n4068300-902\n \n\tNOTE 1: This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been 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 use the authority provided in paragraph (d) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent significant delays in the Honeywell Standard Windshear Detection Systems(WSS) detecting hazardous windshear, which could lead to the loss of flight path control, accomplish the following: \n\n\t(a)\tRevise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement, at the time specified in either paragraph (a)(1) or (a)(2) of this AD, as applicable. This may be accomplished by inserting a copy of this AD in the AFM. \n\n\n"During sustained banks of greater than 15 degrees or during flap configuration changes, the Honeywell Windshear Detection and Recovery Guidance System (WSS) is desensitized and alerts resulting from encountering windshear conditions will be delayed." \n\n\t\t(1)\tFor all Boeing, McDonnell Douglas, Lockheed, and Fokker airplanes specified in the applicability statement of this AD: Within 14 days after March 8, 1995 (the effective date of AD 95-04-01, amendment 39-9153). \n\n\t\t(2)\tFor British Aerospace Model Avro airplanes specified in the applicability statement of this AD: Within 14 days after May 15, 1995 (the effective date of AD 95-09-05, amendment 39-9208). \n\n\t(b)\tWithin 36 months after the effective date of this AD, replace the currently-installed line replaceable unit (LRU) with a modified LRU having new software that eliminates delays in the WSS detecting windshear when the flaps of the airplane are in transition, in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Accomplishment of this replacement constitutes terminating action for the requirements of paragraph (a) of this AD; after the replacement has been accomplished, the AFM limitation required by paragraph (a) of this AD may be revised to read as follows: \n\n"During sustained banks of greater than 15 degrees, the Honeywell Windshear Detection and Recovery Guidance System (WSS) is desensitized and alerts resulting from encountering windshear conditions will be delayed." \n\n\t(c)\tAs of 18 months after the effective dateof this AD, no person shall install on any airplane an LRU that has not been modified in accordance with paragraph (b) of this AD. An unmodified LRU may be installed up to 18 months after the effective date of this AD, provided that, during that time, the AFM limitation required by paragraph (a) of this AD remains in effect. \n\n\t(d)\tAn 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, Los Angeles ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. \n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. \n\n\t(e)\tSpecial 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 can be accomplished. \n\n\t(f)\tThis amendment becomes effective on February 26, 1996.
2003-22-03: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211 Trent 768-60 and Trent 772-60 turbofan engines. This AD requires reworking the low pressure (LP) turbine nozzle vane case, the LP turbine bearing support exhaust case, and the support arm bracket assemblies. This AD is prompted by a report of an LP stage 4 blade failure at the blade shank, resulting in severe radial distortion of the rear flange of the LP turbine case and failure of a number of attaching bolts, resulting in enough flange separation to allow the release of high energy debris. We are issuing this AD to prevent possible uncontained LP turbine case failure and damage to the airplane.
2020-22-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-251N and -271N airplanes; Model A321- 251N, -271N, -272N, -252NX, and -271NX airplanes; Model A330-243, -343, and -941 airplanes; and Model A350-941 and -1041 airplanes. This AD was prompted by reports of removable \n\n((Page 70052)) \n\ndisplay units (RDUs) found undocked from the hosting display docking stations (DDSs). This AD requires removal of the RDUs or implementation of an operational restriction, and a one-time inspection of the RDU installation onto the DDS and, depending on findings, accomplishment of applicable corrective actions, 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.