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91-24-03: 91-24-03 PRATT & WHITNEY CANADA: Amendment 39-8088. Docket No. 91-ANE-36. Supersedes AD 90-24-05, Amendment 39-6812. Applicability: Pratt & Whitney Canada (PWC) PW123, PW124B, PW125B, and PW126A turboprop engines installed on but not limited to DeHavilland Dash 8 Series 300, Aerospatiale ATR72, Fokker 50, and British Aerospace ATP aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent a low pressure turbine (LPT) overspeed, that could result in uncontained disk failure, and subsequent damage to the aircraft, accomplish the following: (a) For PW123 and PW124B engines that have not been modified in accordance with any revision level of PWC Service Bulletin (SB) 21018, prior to the effective date of this AD, accomplish the following: (1) Within 5 days after the effective date of this AD, perform a turbomachinery magnetic chip detector (MCD) continuity check in accordance with PWC SB 20938, Revision 2, dated November 18, 1991. (2) Within 5 days after the effective date of this AD, perform a turbomachinery MCD functional check in accordance with PWC SB 20938, Revision 2, dated November 18, 1991. (3) Thereafter, at intervals not to exceed 25 flight hours since last inspection, perform the turbomachinery MCD continuity check specified in paragraph (a)(1) of this AD. (4) Thereafter, at intervals not to exceed 300 flight hours since last inspection, perform the turbomachinery MCD functional check specified in paragraph (a)(2) of this AD. (b) In addition to the requirements of paragraph (a) of this AD, for PW123 engines that have not been modified in accordance with any revision level of PWC SB 21018, prior to the effective date of this AD, accomplish the following: (1) Within 5 days after the effective date of this AD, perform a turbomachinery MCD airframe circuitry check in accordance with PWC SB 20938, Revision 2, dated November 18, 1991. (2) Thereafter, at intervals not to exceed 300 flight hourssince last inspection, perform the turbomachinery MCD airframe circuitry check specified in paragraph (b)(1) of this AD. (c) For PW125B and PW126A engines that have not been modified in accordance with any revision level of PWC SB 21018, prior to the effective date of this AD, accomplish the following: (1) Within the next 125 flight hours after the effective date of this AD, unless previously accomplished within the last 875 flight hours, perform a turbomachinery MCD operational check in accordance with the applicable engine maintenance manual. NOTE: Further information on the turbomachinery MCD operational check specified in paragraph (c)(1) can be found in PWC Maintenance Manual Part Number 3034932 for the PW125B, and PWC Maintenance Manual Part Number 3034922 for the PW126A. (2) Within the next 125 flight hours after the effective date of this AD, unless previously accomplished within the last 875 flight hours, perform an operational check of the turbomachinery MCD airframe circuitry and indicating system in accordance with the applicable aircraft maintenance manual. NOTE: Further information on the turbomachinery MCD airframe circuitry and indicating system specified in paragraph (c)(2) of this AD can be found in Fokker 50 Maintenance Manual, Chapter 77-33-00, for the PW125B, and BAe ATP Aircraft Maintenance Manual, Chapter 79-33-00, for the PW126A. (3) Thereafter, at intervals not to exceed 1,000 flight hours since last inspection, perform the turbomachinery MCD operational check specified in paragraph (c)(1) of this AD. (4) Thereafter, at intervals not to exceed 1,000 flight hours since last inspection, perform the operational check of the turbomachinery MCD airframe circuitry and indicating system in paragraph (c)(2) of this AD. (d) The initial inspections of paragraphs (a)(1), (a)(2), and (b)(1) of this AD need not be accomplished for those PW123 and PW124B engines previously inspected in accordance with AD 90-24-05. (e) Forengines that have not been modified in accordance with any revision level of PWC SB 21018, prior to the effective date of this AD, incorporate a new low pressure rotor balancing assembly in accordance with PWC SB 21018, Revision 2, dated November 25, 1991, at the next engine shop visit or by June 30, 1994, whichever occurs first. The incorporation of a new low pressure rotor balancing assembly in accordance with this paragraph constitutes a terminating action for paragraphs (a), (b), or (c), as applicable, of this AD. (f) For the purpose of this AD, an engine shop visit is defined as the induction of an engine into a maintenance facility for the conduct of any type of maintenance. (g) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Engine Certification Office. (h) 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. (i) The inspections and modifications shall be done in accordance with the following Pratt & Whitney Canada service documents: Document Number Page Number Issue/Rev Date PWC SB 21018R2 1-36 Revision 2 11/25/91 Total: 36 pages PWC SB 20938R2 1-8 Revision 2 11/18/91 Total: 8 pages 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 Pratt & Whitney Canada, Technical Publications Department, 1000 Marie Victorin, Longueuil, Quebec J4G 1A1. Copiesmay be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. (j) This amendment becomes effective on May 26, 1992.
78-03-01: 78-03-01\tBELL 47 SERIES AS MODIFIED BY STC SH357SW: Amendment 39- 3131. To preclude failure of the hopper upper support bracket, accomplish the following: \n\n\tWithin the next 25 hours flight time and at each 25 flight hours thereafter, inspect the hopper upper support bracket (P/N B630224) for cracks and/or deformation. If cracks and/or deformation are found, replace or repair. Inspections may be discontinued upon installation of Simplex Modification No. E201 (See Fig. 1), or equivalent modification or repair approved by an FAA Maintenance Inspector. \n\n\tThe manufacturer's repair, identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received the repair documents from the manufacturer, may obtain copies upon request to Simplex Manufacturing Company, 5224 N.E. 42nd Avenue, Portland, Oregon 97218. This repair document may also be examined at FAA Northwest Region, 9010 E. Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective March 6, 1978.
2013-19-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of chafing damage to a wire bundle that was arcing to hydraulic tubing and caused by insufficient separation between the wire bundle and the hydraulic tubing in the main landing gear (MLG) wheel well. This AD requires an inspection for damage of wire bundles and hydraulic tubing on the right side of the forward bulkhead of the MLG wheel well; installation of new clamps; and corrective actions, as applicable. We are issuing this AD to detect and correct possible damage caused by insufficient separation between the wire bundles and hydraulic \n\n((Page 59799)) \n\ntubing to prevent electrical arcing in a flammable fluid leakage zone, which could lead to a wheel well fire.
90-09-10: 90-09-10 TEXAS INSTRUMENTS: Amendment 39-6565. Docket No. 89-ANE-38. Applicability: To circuit breaker Models 6TC6-7.5 and -10 and 6TC20-7.5 and -10, all with date codes 8150 and earlier. Compliance is required no later than November 1, 1990, unless already accomplished. (a) To prevent potential overheating of the applicable circuit breakers, replace Texas Instruments circuit breaker Models 6TC6-7.5 and -10 and Models 6TC20-7.5 and -10, all with date codes 8150 and earlier. These circuit breakers may be replaced with the same model numbers with the manufacturing date codes of 8151 and later. NOTE: The circuit breakers are installed in, but not limited to, aircraft manufactured by Boeing Commercial Airplanes and Lockheed Corporation. Service bulletins published to date, which may be helpful in identifying replacement circuit breakers, are as follows: (1) The Boeing Commercial Airplanes' service bulletins 757-24-0054, 747-24-2135, and 767-24-0060, all dated August 31, 1989. Their part numbers BACC18AC7 and BACC18AC10 are used to identify Texas Instruments Model 6TC6-7.5 and 6TC6-10, respectively. (2) The Lockheed Corporation service bulletin 093-24-134, dated August 12, 1987. Their part numbers LS10159-7 and LS10159-10 are used to identify Texas Instruments Model 6TC20-7.5 and 6TC20-10, respectively. (b) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment (39-6565, AD 90-09-10) becomes effective on May 30, 1990.
57-12-02: 57-12-02 BELL: Applies to Model 47H1 Helicopters Serial Numbers 1349, 1351 Through 1360, 1362, 1363, 1365 Through 1371. Compliance required as soon as possible but not later than August 1, 1957. In order to prevent possible failure of the tail boom attach bolts the following inspection and rework should be accomplished. 1. Visually inspect the four (4) tail boom attach fittings 47-265-026-1 and -2 on the forward bulkhead to determine if all eight (8) bolt hole locations (2 in each fitting) have been spot faced. It is necessary to remove the baggage compartment floor section in order to make this inspection. 2. If it is found that any or all the bolt hole locations have not been spot faced, it is required that they be spot faced in accordance with the instructions given in Bell Mandatory Service Bulletin No. 116, dated November 9, 1956.
2013-19-02: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes. This AD was prompted by a report that a certain wire harness located in the tail cone has wiring of a narrower gauge than design requires. This AD requires replacing the affected wire harness. We are issuing this AD to prevent damage to the affected wiring, which could create an ignition source in an area that might contain fuel vapors, possibly resulting in an uncontrolled fire and subsequent loss of the airplane.
2013-16-03: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350 and AS355 helicopters, to require inspecting for a crack in the control lever attachment yokes, and if needed, replacing the tail rotor gearbox (TGB). This AD is prompted by improper casting of TGB casing assemblies, which may lead to cracking. A crack in the control lever attachment yokes could cause a loss of tail rotor pitch control, and consequently, loss of control of the helicopter.
2012-12-13: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD was prompted by reports of baggage bay fire bottles that can be misassembled such that two squib electrical connectors can be cross- connected. This AD requires a general visual inspection of certain baggage bay fire bottles for correct connection and for the length of the wiring loom, modification of the wiring loom to certain squib connectors, and corrective actions if necessary. We are issuing this AD to detect and correct excessive wiring loom length and improper connection of the squib connecters, which in conjunction with a fire in one of the baggage bays, could result in the fire extinguishing agent being discharged into a wrong compartment and consequent damage to the airplane.
78-07-02: 78-07-02 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-3168. Applies to Model HS-125 Series 700A airplanes, S/N NA0201 through NA0210, certificated in all categories. Compliance is required as indicated. To detect cracking and possible failure of the attaching lugs of the tee pieces, P/N 25- 7PA41, that are mounted on the master refuel valve, accomplish the following: (a) Within 10 days after the effective date of this AD, unless already accomplished, inspect the attachment lugs for cracking and the area of attachment to the main refuel valve for evidence of fuel leakage in accordance with Part A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd. Alert Service Bulletin 28-A65, dated November 30, 1977 (service bulletin), or an FAA-approved equivalent. (b) If during the inspection required by paragraph (a) of this AD, evidence of lug cracking or fuel leakage is found, before further flight, except that the airplane may be flown in accordance with FARs 21.197 and 21.199 to a base where the repairs can be performed, remove and destroy both tee pieces and replace with the improved parts, P/N 25-7PA125A, in accordance with Part B of the section entitled "Accomplishment Instructions" of the service bulletin, or an FAA-approved equivalent. (c) If during the inspection required by paragraph (a) of this AD, no evidence of lug cracking or fuel leakage is found, continue to inspect the area in accordance with paragraph (a) of this AD, at intervals not to exceed three calendar months from the initial inspection, except that both tee pieces must be replaced in accordance with the installation instructions of paragraph (b) of this AD no later than August 1, 1978. Compliance with the repetitive inspection requirements of this paragraph may be terminated after the replacement required by this paragraph is accomplished. This amendment becomes effective April 14, 1978.
2013-18-05: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters with certain fire extinguishing systems installed. This AD requires modifying the fire extinguishing system injection tubes. This AD is prompted by a report that the injection tubes are deforming due to heat. The actions required by this AD are intended to prevent deformation of the fire extinguishing system injection tubes during a fire, which could result in impaired distribution of the fire extinguishing agent, failure of the fire extinguishing system to contain an engine fire, and subsequent loss of control of the helicopter.