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2013-13-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-112, -113, and -132 airplanes; Model A320-211, -212, -214, -231, and -232 airplanes; and Model A321-111 and -131 airplanes. This AD was prompted by a report of two fatigue cracks on the left-hand and right-hand sides of the continuity fittings at the front windshield lower framing on a Model A319 series airplane. This AD requires a high frequency eddy current (HFEC) inspection for any cracking on the left- hand and right-hand sides of the windshield central lower node continuity fittings, and repair if necessary. We are issuing this AD to detect and correct cracking of the windshield central lower node continuity fittings, which could reduce the structural integrity of the airplane.
2013-13-10: We are adopting a new airworthiness directive (AD) for all PILATUS Aircraft Ltd. Model PC-7 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 need to incorporate new revisions into the Limitations section of the FAA-approved maintenance program (e.g., maintenance manual). The limitations were revised to include an emergency fuel control system adjustment test. We are issuing this AD to require actions to address the unsafe condition on these products.
98-25-11: This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model MD-11 series airplanes. This action requires a one-time inspection to detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors, and repair, if necessary. This amendment is prompted by a report indicating that damaged electrical wires were found above the forward passenger doors due to flapper panels moving inboard and chafing the electrical wire assemblies of this area. The actions specified in this AD are intended to prevent such chafing, which could result in an electrical fire in the passenger compartment.
81-17-06: 81-17-06 BRITISH AEROSPACE, AIRCRAFT GROUP (formerly British Aircraft Corporation): Amendment 39-4193. Applies to Model BAC 1-11 200 and 400 series airplanes, certificated in all categories, that incorporate a ground charging system as a part of the airplane oxygen system. Compliance is required as indicated unless already accomplished. To minimize the possibility of fire originating in the oxygen system during recharging, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, install a placard in clear view of the pilots and at the oxygen filler valve to read as follows: "REMOVE OXYGEN BOTTLES FROM AIRPLANE FOR CHARGING" (b) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished, replace the non-return valve, P/N WKA 30035 or WKA 30035/1, in accordance with British Aerospace, Aircraft Group, Alert Bulletin 35-A-PM 5541,Issue 2, dated August 31, 1978, (hereinafter referred to as the service bulletin) with a new valve, P/N WKA 30035/1, modified to WKA 37395 configuration in accordance with paragraph 2.4 of section 2, "Accomplishment Instructions" of the service bulletin, or an FAA-approved equivalent. (c) Prior to October 1, 1981, accomplish British Aerospace, Aircraft Group, Modification PM 5291, or an FAA-approved equivalent. (d) Prior to October 1, 1981, if equipped with self-sealing charging valve, accomplish British Aerospace, Aircraft Group, Modification PM 5413, or an FAA-approved equivalent. (e) As an alternative to complying with paragraphs (a), (b), (c), or (d) of this AD, deactivate the ground charging system in accordance with paragraph 2.3.2 of Section 2, "Accomplishment Instructions," of the service bulletin, or an FAA-approved equivalent. (f) For airplanes incorporating oxygen shut-off valves, Normalair P/N OP 6370 or Adams P/N 6D/2313 MK 10 A: (1) Withinthe next 300 hours time in service or within the next 60 days after the effective date of this AD, whichever occurs sooner, unless already accomplished within the last 2100 hours time in service or 10 months, whichever is the shorter, and thereafter at intervals not to exceed 2400 hours time in service, or 1 year, whichever occurs sooner, inspect ground charging and passenger and crew supply shut-off valves, in accordance with paragraph 2.2.3 of section 2, "Accomplishment Instructions" of the service bulletin, or an FAA-approved equivalent. Precautions regarding securing and operation of the shut-off valves are outlined in paragraph 2.2.1 of section 2, "Accomplishment Instructions" of the service bulletin. (2) If, during the inspections required by paragraph (f)(1) of this AD, a valve is determined to be unserviceable in accordance with the criteria established in paragraph 2.2.3 of section 2, "Accomplishment Instructions" of the service bulletin, before further flight, replace the valve with a serviceable part of the same part number, and continue to inspect the valve in accordance with paragraph (f)(1) of this AD, or replace with P/N WKA 30342 valve, in accordance with British Aerospace, Aircraft Group, Modification No. PM 5575, or an FAA-approved equivalent. (g) Upon satisfactory compliance with paragraphs (b), (c), (d), and (f) of this AD, the placard required by paragraph (a) may be removed. (h) In accordance with FAR Sections 21.197 and 21.199, the airplane may be flown to a location where the required modification can be made. (i) For purposes of complying with this AD, an FAA-approved equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to British Aerospace, Inc., Box 17414, Dulles International Airport, Washington, DC 20041. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, DC 20591. This amendment becomes effective August 31, 1981.
2006-14-03: The FAA is adopting a new airworthiness directive (AD) for certain Honeywell International Inc. TPE331 series turboprop, and TSE331-3U model turboshaft engines. This AD requires implementing a new flight cycle counting method for first, second, and third-stage turbine rotors used in aircraft that make multiple takeoffs and landings without an engine shutdown, and removing turbine rotors from service that have reached or exceeded their cycle life limits. This new flight cycle counting method requires determining total equivalent cycles accrued. This AD results from several reports of uncontained turbine rotor separation on engines used in special-use operations. We are issuing this AD to prevent uncontained failure of the turbine rotor due to low-cycle-fatigue (LCF), and damage to the aircraft.
98-25-10: This amendment adopts a new airworthiness directive (AD) that is applicable to Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems, installed on, but not limited to, Beech Aircraft Corp., Bell Helicopter Textron, Inc., Cessna Aircraft Co., Dassault Aviation, Eurocopter Deutschland, Eurocopter France, Gulfstream Aerospace, Learjet Corp., Lockheed Aircraft Corp., and Piper Aircraft Corp. aircraft. This action requires an inspection to ensure the locking mechanism is engaging properly, and replacing the buckle-half of the seat restraint system, if necessary. This amendment is prompted by the manufacturer reporting two failures of the seat restraint system in the field. The actions specified in this AD are intended to prevent failure of the seat restraint system due to the buckle assembly locking mechanism not engaging properly, which could result in the seat restraint system failing to properly secure the occupant during turbulence or landing.
67-02-03: 67-02-03 GENERAL DYNAMICS: Amdt. 39-331 Part 39 Federal Register December 29, 1966, as amended by Amendment 39-1284. Applies to Model 340 Airplanes That Have Not Been Modified to Incorporate the Provisions of Convair Service Bulletin 340-174A or Equivalent Approved by the Chief, Aircraft Engineering Division, FAA Western Region. Compliance required as indicated. As a result of a number of inflight openings of the rear service door on Model 340 aircraft, (one such occurrence resulting in a fatal accident to a crewmember) accomplish the following: (a) Within the next 25 hours' time in service after December 18, 1962, unless already accomplished: (1) Add a placard to the rear service door indicating the "Open", "Unsafe", and "Locked" position for the door handle in accordance with Convair Service Bulletin 340-213, dated October 15, 1956, or an FAA approved equivalent installation. (2) Add a placard in the cockpit which requires that a flight crewmember inspectthe rear service door to determine that it is properly latched prior to takeoff. (b) Within the next 50 hours' time in service after May 8, 1963, unless already accomplished, incorporate an FAA-approved revision to the FAA approved Airplane Flight Manual as follows: (1) In the "Limitations Section", add a note which requires that a flight crewmember inspect the rear service door to determine that it is properly latched immediately prior to each takeoff unless it is known to that flight crewmember that the door has not been operated since last inspected by the flight crew. (2) In the "Emergency Procedure Section", add a note which requires that the airplane be depressurized in accordance with the procedure prescribed in this Manual if there is evidence that a door latch has become disengaged or leakage around the door occurs. (3) When the FAA approved Airplane Flight Manual is revised as prescribed in (b)(1), the placard prescribed in (a)(2) may be removed.(c) Within the next 1,000 hours' time in service after December 18, 1962, unless already accomplished: (1) Install inspection holes and lights in the rear service door threshold for inspection of the lower door latches in accordance with Item 6 of Convair Newsletter No. 294 dated May 6, 1955, and Convair Service Bulletin 340-232 dated November 11, 1957, or an FAA Western Region Aircraft Engineering Division approved equivalent installation. (2) Install microswitches in the upper and lower forward latches of the rear service door in accordance with the portion of Convair Service Bulletin 340-126A dated June 1, 1954, and revised December 1, 1954, pertaining to the rear service door, or an FAA Western Region Aircraft Engineering Division approved equivalent installation. (3) Install proximity switches on the rear service door in accordance with the portion of Convair Service Bulletin 340-234 dated January 29, 1958, pertaining to the rear service door, or an FAA Western Region Aircraft Engineering Division approved equivalent installation. (d) Within the next 1,000 hours' time in service after December 18, 1962, unless already accomplished, install an irreversible clutch mechanism on the rear service door in accordance with Convair Service Bulletin 340-233 dated September 10, 1957, or an FAA Western Region Aircraft Engineering Division approved equivalent. (e) Within the next 7,000 hours' time in service after January 28, 1967, install a rear service door forward hinge in accordance with Convair Service Bulletin 340-174A dated February 1, 1957, or an FAA Western Region Aircraft Engineering Division approved equivalent installation. NOTE. - Many Model 340 aircraft incorporate the provisions of the Model 440 performance kit, Service Bulletin 340-144, and have incorrectly been redesignated as Model 440 aircraft. Such aircraft are still Model 340 and should be treated as such (see nameplate and manufacturing serial numbers). (General Dynamics/Convair Service Bulletins 340-126A, 340-213, 340-232, 340-233, 340-234, and Service Newsletter No. 294 pertain to this subject.) AD 67-02-03 Amendment 39-331 supersedes AD 62-27-06. Amendment 39-331 became effective January 28, 1967. This Amendment 39-1284 becomes effective September 8, 1971.
76-24-06 R2: 76-24-06 R2 BRITISH AIRCRAFT CORPORATION: Amendment 39-2779 as amended by Amendment 39-2800 is further amended by Amendment 39-4734. Applies to BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance is required as indicated. To detect oxygen leaks, due to fractures in the flexible oxygen hoses of the emergency oxygen system, and prevent possible in-flight fires, accomplish the following: (a) Within the next 250 hours time in service after the effective date of this AD, unless already accomplished in the last 1500 hours time in service, conduct a leak test of the emergency oxygen system in accordance with paragraph 2.3 of the section entitled "Accomplishment Instructions" of British Aircraft Corporation Alert Service Bulletin 35-A-PM 5394, issue 3, dated June 29, 1979, or an FAA-approved equivalent. (b) If, during the leak test required by paragraph (a) of this AD, a leak is found, before further flight, locate the source of the leak and replace the defective part with a new part of the same part number or with a serviceable FAA-approved part and then retest the emergency oxygen system in accordance with paragraph (a) of this AD. (c) Inspect and rework the flexible hoses of the emergency oxygen system within the next 1000 hours time in service or six months after the effective date of this AD, whichever occurs sooner, unless already accomplished within the proceeding 1500 hours time in service, and thereafter at intervals not to exceed one year, in accordance with paragraph 2.4, Figure 1 through 3, and Table 1 of the service bulletin. (d) If, during an inspection required by paragraph (c) of this AD, the flexible oxygen hoses are found fractured or embrittled, before further flight, replace the affected parts with new parts of the same part number or with serviceable FAA-approved parts and then retest the oxygen system for leaks in accordance with paragraph (a) of this AD. Amendment 39-2779 became effective December 14, 1976. Amendment 39-2800 became effective January 6, 1977. This Amendment 39-4734 becomes effective November 14, 1983.
2022-11-21: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by reports that the inflation valve safety pin has been found installed on the nitrogen bottle of a certain escape slide in-service and may be installed on the nitrogen bottles of certain other escape slides on other airplanes in-service. This AD requires inspecting the inflation valve of the nitrogen bottle of the escape slide for the presence of the safety pin, and if the safety pin is installed, removing the safety pin from the inflation valve and stowing it in the safety pin stowage pouch of the escape slide, as specified in a Transport Canada Civil Aviation (TCCA) Emergency AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2022-10-10: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a report of a wing stall (wing drop/un-commanded roll) during a landing flare. This AD requires revising the existing airplane flight manual (AFM) to incorporate a limitation and procedure for the wing anti-ice (WAI) system in order to mitigate the risk of ice accumulation on the wing leading edges. The FAA is issuing this AD to address the unsafe condition on these products.