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2016-09-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by the discovery of a number of incorrectly calibrated angle of attack (AOA) transducers installed in the stall protection system. This AD requires replacement of incorrectly calibrated AOA transducers. We are issuing this AD to detect and replace incorrectly calibrated AOA transducers; incorrect calibration of the transducers could result in late activation of the stick pusher.
2011-03-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installing new fire handle shutoff system wiring. This AD was prompted by a possible latent failure in the fire handle shutoff relay circuit due to a lack of separation between engine wires. We are issuing this AD to minimize the possibility of a multiple engine shutdown due to single fire handle activation.
67-07-01: 67-07-01 BOEING: Amdt. 39-355 Part 39 Federal Register March 2, 1967. Applies to Model 727 Airplanes Equipped With the Sperry SP-50 Autopilot. \n\n\tCompliance required as indicated unless already accomplished. \n\n\tTo prevent an unsafe condition which may result when the autopilot does not disengage when the control wheel disconnect button is used, accomplish the following: \n\n\t(a)\tFor airplanes having Sperry SP-50 autopilot control panels with 1,500 or more hours' time in service on the effective date of this AD, comply with (d) prior to completing the next 50 hours' time in service. \n\n\t(b)\tFor airplanes having Sperry Sp-50 autopilot control panels with less than 1,500 hours' time in service on the effective date of this AD, comply with (d) prior to completing 1,550 hours' total time in service. \n\n\t(c)\tOperators who have not kept records of hours' time in service of individual Sperry SP-50 autopilot control panels shall substitute hours' time in service of the airplane or airplanes in which the individual autopilot control panel was installed. \n\n\t(d)\tInstall a placard in clear view of the pilot with the following information: \n\tAutopilot(s) must be turned off when operating below 3,000 feet above ground level in a terminal area. Verify by position of the control panel engage lever. \n\n\t(e)\tThe placard installed in accordance with (d) may be removed when the Sperry SP-50 autopilot control panel switches have been reworked to Sperry Service Bulletin TA-697-104. \n\n\tThis directive effective March 2, 1967.
83-06-05 R1: 83-06-05 R1 SIAI-MARCHETTI: Amendment 39-4591 as amended by Amendment 39-4830. Applies to Models F260, F260B, and F260C (including SF260), (Serial Numbers up to 774 inclusive) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To preclude failure of the nose-gear barrel joint weld, accomplish the following: (a) Within the next 100 hours time-in-service on those barrels having 400 or more hours time-in-service on the effective date of this AD or prior to the accumulation of 500 hours time-in-service on those barrels having less than 400 hours time-in-service on the effective date of this AD and thereafter at intervals not exceeding 100 hours time-in-service accomplish the following: (1) Using a dye-penetrant method, inspect the nose-gear barrel joint weld at the attachment plate for cracks. Perform the inspection in accordance with the "Instructions" section of SIAI-Marchetti SB No. 260B34A, dated October 1, 1983, or an FAA approved equivalent. (i) If a crack is found, prior to further flight replace the nose-gear barrel in accordance with the applicable paragraph of SB No. 260B34A. (b) Operators who have not kept records of hours time-in-service for the nose-gear barrel must substitute airplane hours time-in-service. (c) Replacement of the barrels in accordance with Table "A" of the SIAI-Marchetti SB No. 260B34A eliminates the requirement for the periodic inspections in paragraph (a). (d) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (f) An equivalent method of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle EastOffice, FAA, c/o American Embassy, 1000 Brussels, Belgium. Amendment 39-4591 became effective March 31, 1983. This Amendment 39-4830 becomes effective March 26, 1984.
2016-08-10: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6- 80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-80C2B1F1, CF6-80C2B1F2, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B3F, CF6-80C2B4, CF6- 80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6- 80C2B7F, CF6-80C2B8F, CF6-80C2D1F, CF6-80C2L1F, CF6-80C2K1F and CF6- 80E1A1, CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B turbofan engines. This AD was prompted by reports of a burn-through of the accessory heat shield during an engine fire, propagating the fire into the accessory compartment and igniting additional flammable fuel source. This AD requires replacing the accessory heat shield assembly. We are issuing this AD to prevent fires from propagating into the accessory compartment, resulting in an uncontrolled engine fire, and damage to the airplane.
83-24-01: 83-24-01 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-4770. Applies to Model HS 748 series 2A airplanes, certificated in all categories. To prevent failure of the wing structure, accomplish the following, unless already accomplished: A. Prior to accumulation of 10,000 landings, or within the next 750 landings after the effective date of this AD, whichever occurs later, visually inspect the wing structure in accordance with paragraph 2.B of the Accomplishment Instructions of British Aerospace HS 748 Aircraft Service Bulletin 57/34, Revision 3, dated March 3, 1980. B. Repeat the inspections as specified in Table No. 1 of the service bulletin. C. If any cracks are found, accomplish paragraph 2.D of the service bulletin. D. For the purpose of this AD, and when approved by an FAA maintenance inspector, the number of landings may be computed by dividing each airplane's time in service by the operator's fleet average time from takeoff to landing for the aircraft type. E. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective December 23, 1983.
79-11-04: 79-11-04 FAIRCHILD (HILLER): Amendment 39-3479. Applies to Model 1100 and FH-1100 type helicopters certificated in all categories. Compliance required as indicated unless already accomplished. In order to prevent cracking of the transmission lower housing gimbal ring support, accomplish the following: a. For P/N 24-23030-7 transmission lower housings (installed in P/N 24-23000-11, -31, and -41 transmission assemblies) which have accumulated 500 or more hours since new or overhauled, inspect and repair as necessary within 50 hours after the effective date of this AD, unless already accomplished within the last 500 hours, in accordance with Fairchild Service Bulletin No. FH-1100-23-10 dated September 25, 1974, revised April 24, 1979. This inspection shall be repeated at each 500-hour interval thereafter. b. For P/N 24-23030-7 transmission lower housings which have accumulated 1200 or more hours, unless already accomplished within the last 1100 hours, ream the gimbalring mounting holes to the next larger size in accordance with Fairchild Service Bulletin No. FH-1100-23-10 dated September 25, 1974, revised April 24, 1979, within 100 hours after the effective date of this AD and at each 1200-hour interval thereafter. c. As a result of the inspection and repair required under paragraphs a and b herein, if the gimbal ring mounting hole diameter exceeds 0.8755 inch or a total time of 3600 hours is attained on the P/N 24-23030-7 lower housing assembly the housing shall be retired from further service. d. Upon installation of transmission lower housing assembly P/N 24-23030-11, the requirements of this AD are no longer applicable. e. Equivalent inspections or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval specified in this airworthiness directive. f. Rotorcraft may be flown to a base where the maintenance required by this airworthiness directive is to be performed per FARs 21.197 and 21.199. This amendment is effective June 4, 1979.
2016-08-03: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports of fractured forward attach fittings of the inboard flap outboard aft flap track. The fractured fittings were determined to be the result of corrosion pits forming on the inside diameter of the fittings. This AD requires an inspection for the affected part number and serial number of the main flap; various additional repetitive inspections of the fitting, if necessary; and replacement of the fitting or nested bushing installation, if necessary, which would terminate the inspections. This AD also provides an optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct fracture of the fitting, which could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane.
2000-23-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires replacement of the flight control computers (FCC) with new, improved FCC's having updated software installed. This amendment also requires, for some airplanes, modification of the wiring of the FCC's. The actions specified by this AD are intended to prevent autopilot reversions in certain flight conditions, which could result in misunderstanding by the flight crew and consequent reduced ability to take appropriate action. This action is intended to address the identified unsafe condition.
2016-07-15: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a fuel leak that occurred in the baggage compartment during fuel system pressurization. This AD requires opening the fuel boxes and restoring the sealing. We are issuing this AD to prevent failure of a connector or coupling on a fuel line, which, in combination with a leak in the corresponding enclosure (i.e., fuel box), could result in a fire in the baggage compartment and affect the safe flight of the airplane.