Results
2002-04-07: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS350BA and B2 helicopters modified with a Eurocopter Canada Limited (ECL) Left-side-Pilot Configuration kit in accordance with Canadian Supplemental Type Certificate (STC) SH96-32 or United States STC SR00429 NY. This action requires replacing the collective locking device with a newly-designed locking device. This amendment is prompted by a report of a locking device that engaged during flight. The actions specified in this AD are intended to prevent inadvertent engagement of a locking device, the collective pitch control locking in the full-down position, and subsequent loss of control of the helicopter.
2002-04-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4 series airplanes; certain Model A300 F4-605R airplanes and Model A300 B4-600 and A300 B4-600R series airplanes; and certain Model A310 series airplanes, that requires repetitive inspections to detect damage of the fillet seals and feeder cables, and of the wiring looms in the wing/pylon interface area; and corrective action, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent wire chafing and short circuits in the wing leading edge/pylon interface area, which could result in loss of the power supply generator and/or system functions. This action is intended to address the identified unsafe condition.
83-13-01: 83-13-01 CESSNA: Amendment 39-4672. Applies to Models 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q (all serial numbers except 66590 and on) and R182 (S/N R18200002 through R18200583) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To alert the pilot to the potential effects of improper fuel cap sealing: a) Within the next 12 calendar months after the effective date of this AD install a placard adjacent to the fuel quantity gauges which states: "CAUTION Leaking fuel caps can cause loss of fuel and erroneously high fuel quantity indications." This placard may be fabricated by the owner/operator of the airplane. The person accomplishing this must make the prescribed entry in the aircraft maintenance records reflecting compliance with paragraph a) of this AD. b) Within the next 12 calendar months after the effective date of this AD and each 12 calendar months thereafter: 1) Visually inspect, the surface of the wing aft of the fuel cap for evidence of leakage, the fuel cap seals for cracks, distortion and or any condition which may prevent sealing and the sealing surface of the adapter for scratches, corrosion, distortion or other conditions which may prevent sealing. If any of these conditions are noted inspect the fuel tank for wrinkles in the bottom and proper attachment of the retaining snaps to the compartment. Prior to further flight, correct any unsatisfactory conditions in accordance with the manufacturers maintenance manuals or service information which should include inspection of the fuel tank installation in accordance with Cessna Service Letter SE82-34A. Fuel cap repairs should be accomplished in accordance with Cessna Service Letter SE80-59 Supplement 1. 2) On airplanes having Cessna P/N C156001-0106 plastic cap installed, visually inspect the adapter for presence and legibility of the Cessna P/N 1205253-1 FuelCap Alignment Placard and prior to further flight install new placards if required. 3) Check the tension of the fuel cap locking mechanism by operating the tab. If necessary, prior to further flight adjust in accordance with the manufacturers service manuals/information to obtain proper sealing pressure between the cap and adapters. c) Airplane may be flown per FAR 21.197 to a location where this AD may be accomplished. d) An equivalent method of compliance with this AD may be used if it is approved by Manager, Wichita Aircraft Certification Office, Room 238, Terminal building 2299, Mid-Continent Airport, Wichita, Kansas 67209. Cessna Service Information Letter SE79-45, SE8O-59, Supplement 1 and SE82-34A and Owner Advisories SE80-59A and SE82-34A pertain to the subject matter of this AD. This amendment becomes effective on August 1, 1983.
90-06-10: 90-06-10 SCHWEIZER AIRCRAFT CORPORATION: Amendment 39-6529. Docket No. 88-ASW-37. Applicability: All Schweizer Model 269A, 269A-1, 269B, and 269C helicopters, certificated in any category, with Serial Numbers 0004 through 0819 and those subsequent to 0819, which have had throttle cables replaced. Compliance: Required as indicated, unless already accomplished. To prevent loss of throttle control, accomplish the following: (a) Within the next 25 hours' time in service or within 30 days, whichever occurs first after the effective date of this AD, identify, inspect, and replace as indicated, the throttle cable assembly as follows: (1) Determine if aluminum fittings are installed as follows: (i) Check both end fittings of the cable assembly with a magnet to determine whether they are magnetic. Cables which incorporate magnetic fittings (magnet adheres to fitting) do not require the hardness test specified by paragraph (a)(1)(ii) below. For these cableassemblies, omit step (a)(1)(ii), and continue inspection with step (a)(2) below. (ii) If the magnet does not adhere to the fitting, perform a hardness test on the fitting. If Rockwell hardness is less than B-85, remove and replace the cable assembly with a swaged steel cable assembly in accordance with paragraph (c) of this AD before further flight. Performance of the hardness test will require removal of the throttle cable assembly from the helicopter in accordance with standard maintenance instructions. (2) Visually check both ends of the cable to determine whether the cable incorporates swaged or threaded steel end fittings. NOTE: Throttle cables which incorporate swaged end fittings may be identified by six evenly spaced flat spots around the barrel of the fitting just behind the lug. Threaded end fittings incorporate a cylindrical barrel (no flat spots). (3) If the cable incorporates swaged steel end fittings (as determined from steps (a)(1) and (2) above), further compliance is not required except to record compliance in the helicopter log book as "THROTTLE CABLE WITH SWAGED STEEL END FITTINGS INSTALLED." (4) If cable incorporates a threaded steel end fitting (as determined from steps (a)(1) and (2) above), perform an inspection before further flight and perform repetitive daily inspections in accordance with paragraph (b) of this AD until the cable is replaced in accordance with paragraph (c) of this AD. (5) Record compliance with paragraph (a) of this AD in the compliance record of the helicopter log book. (b) Prior to the first flight of each day, conduct a visual check of throttle cable assemblies with threaded steel end fittings as follows: (1) Inspect cable end fittings for general condition and security of attachment. If any abnormality or damage is noted, replace cable assembly in accordance with paragraph (c) of this AD. (2) Using a flashlight, visually inspect cable push rod for exposed threads adjacent to end fitting (both ends of cable assembly). NOTE: The cable push rod is the moveable rod that is attached directly to the cable end fitting (lug). (3) If threads are visible, replace cable assembly before further flight in accordance with paragraph (c) of this AD. (4) Record compliance with paragraph (b) of this AD in the compliance record of the helicopter log book. (c) Within the next 400 hours' time in service from the effective date of this AD, or within 12 months, whichever occurs first, replace with swaged steel end fittings all threaded steel end fittings which were not replaced during the inspections and rework required by paragraphs (a) and (b) of this AD. Replacement parts applicability is as follows: Model Swaged Steel Cable Assembly Part Numbers (P/N) 269A 269A4683-9 269A-1 269A4683-9 269B 269A4683-7 269C 269A4683-7 (1) Remove throttle control cable (reference Basic Helicopter Maintenance Instructions (HMI), paragraph 4-11). Donot bend throttle cable support tubes more than 8 degrees from centerline of cable; doing so could cause deformation of the support tubes, premature failure of the cable, and loss of throttle control. NOTE: The cable support tube is the stationary cylinder on the end of the cable through which the cable push rod slides. (2) Install P/N 269A4683-7 or -9 throttle control cable assembly (reference Basic HMI, paragraph 4-11). (3) Rig throttle control (reference Basic HMI). (4) Check idle speed and idle mixture in accordance with appropriate maintenance instructions, and adjust as required. Installation of the upgraded cable assembly, P/N 269A4683-7 or -9, cancels the repetitive inspection required by paragraph (b) of this AD. (5) Record compliance with paragraph (c) of this AD in the compliance record and in the maintenance record of the helicopter log book. NOTE: The instructions in this AD are similar to those contained in Schweizer SIN N-210, dated April15, 1988. An alternate method of compliance which provides an equivalent level of safety with this AD may be used upon the submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. (e) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the requirements of this AD may be accomplished. This amendment (39-6529, AD 90-06-10) becomes effective on April 6, 1990.
2017-25-04: We are superseding Airworthiness Directive (AD) 2014-22-08, which applied to all Airbus Model A318 and A319 series airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2014-22-08 required revising the maintenance or inspection program to incorporate new or revised airworthiness limitation requirements. This new AD requires revising the maintenance or inspection program to incorporate new or revised airworthiness limitation requirements, and removes airplanes from the applicability. This AD was prompted by a determination that more restrictive maintenance instructions and airworthiness limitations are necessary. We are issuing this AD to address the unsafe condition on these products.
2007-23-12: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This AD requires accomplishing an airplane survey to define the configuration of certain system installations, and repair of any discrepancy found. This AD also requires modifying the fuel system by installing lightning protection for the fuel quantity indication system (FQIS), ground fault relays for the fuel boost pumps, and additional power relays for the center tank fuel pumps and uncommanded on- indication lights at the flight engineer's panel. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent certain failures of the fuel pumps or FQIS, which could result in a potential ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
93-06-06: 93-06-06 HAMILTON STANDARD: Amendment 39-8531. Docket No. 92-ANE-51. Applicability: Hamilton Standard Models 14RF-9, 14RF-19, and 14RF-21, and Models 14SF-5, 14SF-7, 14SF-11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23 propellers, and Hamilton Standard-British Aerospace Model 6/5500/F-1 propellers installed on but not limited to Embraer EMB-120 and EMB-120RT; SAAB-SCANIA AB SAAB 340B; Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72-101, ATR72-210; DeHavilland DHC-8-100, DHC-8-300, DHC-8-314; Construcciones Aeronauticas SA (CASA) CN-235 and CN-235-100; Canadair CL215T; and British Aerospace ATP airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent loss of control of the propeller blade pitch due to propeller control unit (PCU) ballscrew quill wear, accomplish the following: (a) Within 10 hours time in service (TIS) after the effective date of this AD, for propeller assemblies equipped with titanium nitrided transfer tubes (identifiable by gold-colored spline area), remove the titanium nitrided transfer tubes from service, replace the PCU ballscrew quill with a new quill or a quill that has never been mated with a titanium nitrided transfer tube, and install an A-1 nitrided transfer tube (identifiable by a grey-colored spline area) that has been marked in accordance with the applicable SB listed in paragraph (c) of this AD. (b) Within 30 hours TIS after the effective date of this AD, for propeller assemblies equipped with an A-1 nitrided transfer tube and a PCU ballscrew quill that either has been mated to a titanium nitrided transfer tube, or that have no records showing to which transfer tube type the PCU ballscrew quill was mated, replace the PCU ballscrew quill with a new quill or a quill that has never been mated with a titanium nitrided transfer tube. (c) Within 60 days after the effective date of this AD, mark all A-1 nitrided transfer tubes with a new part number in accordance with the following Hamilton Standard Alert Service Bulletins (ASB), all dated October 27, 1992: ASB No. 14RF-21-61-A39, applicable to Hamilton Standard Model 14RF-21 propellers; ASB No. 14RF-9-61-A57, applicable to Hamilton Standard Model 14RF-9 propellers; ASB No. 14RF-19-61-A26, applicable to Hamilton Standard Model 14RF-19 propellers; ASB No. 14SF-61-A61, applicable to Hamilton Standard 14SF series propellers; and ASB No. 6/5500/F-61-A12, applicable to Hamilton Standard-British Aerospace Model 6/5500/F-1 propellers. (d) 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, Boston Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (e) 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. (f) The replacement, and marking of transfer tubes shall be accomplished in accordance with the following service documents: Document No. Page Issue Date Hamilton Standard ASB No. 14RF-21-61-A39 1-7 Original October 27, 1992 Total pages: 7 Hamilton Standard ASB No. 14RF-9-61-A57 1-7 Original October 27, 1992 Total pages: 7 Hamilton Standard ASB No. 14RF-19-61-A26 1-6 Original October 27, 1992 Total pages: 6 Hamilton Standard ASB No. 14SF-61-A61 1-7 Original October 27, 1992 Total pages: 7 Hamilton Standard ASB No. 6/5500/F-61-A12 1-7 Original October 27, 1992 Total pages: 7 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 Hamilton Standard Division of United Technologies Corporation, One Hamilton Road, Windsor Locks, Connecticut 06096-1010. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment supersedes AD T91-11-51 issued on May 22, 1991. (h) This amendment becomes effective on July 6, 1993.
93-21-06: 93-21-06 ISRAEL AIRCRAFT INDUSTRIES, LTD.: Amendment 39-8720. Docket 93-NM-96-AD. Supersedes AD 92-12-07, Amendment 39-8268, which superseded AD 90-10-08, Amendment 39-6597. Applicability: Model 1125 Westwind Astra series airplanes on which horizontal stabilizer aft spar splice fitting, part number 453005-509, has not been installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the horizontal stabilizer assembly, accomplish the following: (a) Within the next 50 hours time-in-service after July 31, 1992 (the effective date of AD 92- 12-07, amendment 39-8268), unless previously accomplished within the last 150 hours time-in-service prior to July 31, 1992, perform a visual inspection of the horizontal stabilizer hinge fitting to detect cracks in the outer lug root radius and fore and aft surfaces, and around the hinge pin head and nut of the lugs, in accordance with Astra Service Bulletin 1125-55-017, Revision 1, dated April 24, 1991. (1) If no cracks are found during this inspection, repeat the inspection at intervals not to exceed 200 hours time-in-service until the inspection required by paragraph (b) is accomplished. (2) If any crack is found during this inspection, prior to further flight, replace the hinge fitting in accordance with Astra Service Bulletin 1125-55-017, Revision 1, dated April 24, 1991. After replacement, repeat the visual inspection required by this paragraph at intervals not to exceed 200 hours time-in-service until the inspection required by paragraph (b) is accomplished. (b) Within 25 hours time-in-service after the effective date of this AD, unless previously accomplished within the last 75 hours time-in-service, perform a visual inspection of the horizontal stabilizer hinge fitting, including the horizontal stabilizer aft spar splice fitting, part number 453005-503 (aluminum), to detect cracks in the outer lug root radius and fore and aft surfaces, and around the hinge pin head and nut of the lugs, in accordance with the Accomplishment Instructions of IAI Service Bulletin 1125- 55-017, Revision 1, dated April 24, 1991. Accomplishment of this inspection terminates the requirements of paragraph (a) of this AD. (1) If no crack is found during this inspection, repeat the inspection at intervals not to exceed 100 hours time-in-service. (2) If any crack is found during this inspection, prior to further flight, replace the splice fitting, part number 453005-503 (aluminum), with an improved splice fitting, part number 453005- 509 (titanium), in accordance with procedures in the IAI Model 1125 Westwind Astra maintenance manual. Such replacement constitutes terminating action for the inspection requirements of this AD. (c) Within one year after the effective date of this AD, replace the splice fitting, part number 453005-503 (aluminum), with an improved splice fitting, part number 453005-509 (titanium), in accordance with the IAI Model 1125 Westwind Astra maintenance manual. Such replacement constitutes terminating action for the inspection requirements of this AD. (d) 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) 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. (f) The inspections and replacements shall be done in accordance with Astra Service Bulletin 1125-55-017, Revision 1, dated April 24, 1991. 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 Astra Jet Corporation, Technical Publications, 77 McCullough Drive, Suite 11, New Castle, Delaware 19720. 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. (g) This amendment becomes effective on December 13, 1993.
2017-24-08: We are superseding airworthiness directive (AD) 2014-24-08 for all Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211- 535E4-C-37 turbofan engines with certain low-pressure (LP) fuel filter- to-high-pressure (HP) fuel pump tube assemblies, or HP fuel pump-to- fuel flow governor (FFG) or FFG-to-HP pump inlet overspill return tube assemblies and flanged adaptor, installed. AD 2014-24-08 required replacing certain LP fuel filter-to-HP fuel pump tube assemblies. This AD retains the requirement in AD 2014-24-08 to remove the LP fuel filter-to-HP fuel pump tube, adds new compliance thresholds, and requires installation of new HP fuel pump-to-FFG and FFG-to-HP pump inlet overspill return tube assemblies and flanged adaptor. This AD was prompted by fuel leaks that have occurred at the flanged joints of the HP fuel pump-to-FFG tube assembly and FFG-to-HP pump inlet overspill return tube assembly. We are issuing this AD to correct the unsafe condition on these products.
2002-04-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires repetitive inspections for cracking of the upper chord of the rear spar of the wing, and corrective action, if necessary. This action is necessary to find and fix such cracking, which could result in fuel leaking through the cracks, reduced structural integrity of the wing, and separation of the wing from the airplane. This action is intended to address the identified unsafe condition.