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52-04-08: 52-04-08 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required not later than May 1, 1952. Relocate the anti-icing heater controls to the main bus. (Trans World Airlines Engineering Order 5759 covers this same subject.)
93-07-08: 93-07-08 AEROSPATIALE: Amendment 39-8540. Docket 92-NM-128-AD. Applicability: Model ATR42-300 and -320 series airplanes and Model ATR72-100 and - 200 series airplanes, as listed in Aerospatiale Service Bulletins ATR42-55-0005, Revision 2, dated October 28, 1991, and ATR72-55-1001, Revision 2, dated October 28, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced controllability of the airplane, accomplish the following: (a) Within 30 days after the effective date of this AD, remove the cotter pins on the left and right elevator tab hinges; recheck the torque of the nuts; and install correct size cotter pins, in accordance with Aerospatiale Service Bulletin ATR42-55-0005, dated November 9, 1990, or Revision 1, dated May 28, 1991, or Revision 2, dated October 28, 1991 (for Model ATR42-300 and -320 series airplanes); or Aerospatiale Service Bulletin ATR72-55-1001, dated November 9, 1990, or Revision 1, dated April 10, 1991, or Revision 2, dated October 28, 1991 (for Model ATR72-100 and -200 series airplanes); as applicable. (b) 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. 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. (c) 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. (d) The removal and installation shall be done in accordance with the following Aerospatiale service bulletins, as applicable, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page ATR42-55-0005, November 9, 1990 1-7 Original November 9, 1990 ATR42-55-0005, Revision 1, May 28, 1991 1-3, 5, 7 4, 6 1 Original May 28, 1991 November 9, 1990 ATR42-55-0005, Revision 2, October 28, 1991 1-3, 4, 6 5, 7 2 Original 1 October 28, 1991 November 9, 1990 May 28, 1991 ATR72-55-1001, November 9, 1990 1-7 Original November 9, 1990 ATR72-55-1001, Revision 1, April 10, 1991 1-2, 5, 7 3-4, 6 1 Original April 10, 1991 November 9, 1990 ATR7-55-1001, Revision 2, October 28, 1991 1-2 3-4, 6 5, 7 2 Original 1 October 28, 1991 November 9, 1990 April 10, 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 Aerospatiale, 316 Routede Bayonne, 31060 Toulouse, Cedex 03, France. 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. (e) This amendment becomes effective on May 26, 1993.
2014-16-16: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 ECJ, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This AD requires, for certain airplanes, retorquing and replacing the pylon outboard and inboard lower link fittings. For all airplanes, this AD requires repetitive retorquing of the pylon outboard and inboard lower link fittings. This AD was prompted by a report of a loose lower link assembly on the left and right pylons. We are issuing this AD to prevent loss of a shear pin on the pylon outboard and inboard lower link fittings, which could result in failure of the fitting and consequent separation of the engine from the wing.
2000-02-09: This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta Model AB412 helicopters with certain rescue hoists installed. This action requires replacing the rescue hoist hook assembly retention pin (retention pin) and periodically inspecting the rescue hoist. This amendment is prompted by an incident in which a rescue hoist hook assembly separated from a helicopter due to a missing retention pin. The actions specified in this AD are intended to prevent separation of the rescue hoist hook assembly from the helicopter due to failure of the retention pin. Loss of the rescue hoist hook assembly could result in loss of the person on the rescue hoist. Also, with the loss of the weight of the hoist cable assembly, the rescue hoist cable could become entangled with a main rotor or tail rotor blade, and result in damage or separation of a rotor blade and subsequent loss of control of the helicopter.
70-15-18: 70-15-18 MITCHELL INDUSTRIES, INC., doing business as EDO-AIRE MITCHELL: Amendment 39-1046. Applies to the Mitchell Century II, Century III (Serial Numbers 624 and below) and Stabilizer, automatic pilot and automatic aileron stabilizer instruments, and to Piper AutoControl III, Altimatic III and AutoFlite automatic pilot and automatic aileron stabilizer instruments installed in various light aircraft in accordance with the following Supplemental Type Certificates: AIRCRAFT MAKE SUPPLEMENTAL TYPE CERTIFICATE NUMBERS Aero Commander SA680SW Beech SA617SW SA742SW SA755SW SA800SW SA638SW SA745SW SA761SW SA824SW SA651SW SA754SW SA767SW SA837SW Cessna SA603SW SA624SW SA668SW SA784SW (See also Wren) SA606SW SA637SW SA669SW SA789SW SA607SW SA658SW SA709SW SA795SW SA621SW SA667SW SA737SW SA829SW deHavilland (See Riley 400) Helio SA615SW Maule SA693SW Piper SA511SW SA540SW SA596SW SA757SW SA525SW SA566SWSA662SW SA822SW SA532SW SA576SW SA707SW SA862SW SA533SW SA581SW SA756SW SA921SW Riley 400 (deHavilland modified per STC's SA120SO, SE163SO and SA164SO) SA676SW Wren (Cessna modified per SA791SW STC No. SA485SW) Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent slippage of servo bridle cable clamps and resultant binding of the control system, accomplish the following: Remove Servo Bridle Cable Clamps, Mitchell P/N 42A173 or 42A184, as applicable, and replace with new Servo Bridle Cable Clamps, Mitchell P/N 42A173-1 or 42A184-1, as applicable, in accordance with the installation instructions in Mitchell Industries, Inc. Service Bulletin No. MB-1 dated 2-11-68, revised as Edo-Aire Mitchell Service Bulletin No. MB-1 dated 6-1-70, or later FAA approved revision, or in accordance with instructions approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. The revised bulletin may be obtained from Edo-Aire Mitchell, P.O. Box 610, Mineral Wells, Texas 76067. This Amendment becomes effective August 31, 1970.
2022-18-14: The FAA is superseding Airworthiness Directive (AD) 2017-19- 13, AD 2018-24-04, and AD 2019-23-02, which applied to certain Airbus SAS Model A330-200 series, A330-200 Freighter series, and A330-300 series airplanes. ADs 2017-19-13, 2018-24-04, and 2019-23-02 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by the FAA's determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2019-23-02, adds airplanes to the applicability, and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, 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.
2014-15-21: We are superseding Airworthiness Directive (AD) 2006-26-06 for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce engines. AD 2006-26-06 required repetitive inspections to detect cracks of the outer V-blades of the thrust reverser, and corrective action if necessary. AD \n\n((Page 48025)) \n\n2006-26-06 also provided for an optional terminating action for the repetitive inspections. This new AD adds, for airplanes on which the optional terminating action is done, repetitive inspections for cracking in the outer V-blade fittings of the hinge beam and latch beam ends of each thrust reverser half, and replacement of an affected thrust reverser half if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by reports of cracked outer V- blade fittings at the hinge beam end of Rolls-Royce engine thrust reversers, on airplanes on which the optional terminating action was done. We are issuing this AD to preventseparation of a thrust reverser from the airplane during normal reverse thrust or during a refused takeoff, which could result in unexpected thrust asymmetry and a possible runway excursion.
2000-01-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90 series airplanes, that requires a one-time detailed visual inspection to detect fatigue cracking of certain longerons and the attaching frames of the lower left nose; and repair, if necessary. This amendment also requires installation of a preventive modification. This amendment is prompted by several reports of fatigue cracking of certain longerons and the attaching frames. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the fuselage, and consequent loss of pressurization of the airplane.
2000-01-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. For certain airplanes, this action requires modification of the electrical power supply of the landing gear anti-skid unit. For certain airplanes, this action also requires a revision to the Airplane Flight Manual (AFM) to provide the flight crew with procedures for calculating the accelerate-stop distance for certain conditions, and installation of a new ground idle stop assembly and new placards on the top cover of the pedestal, which terminates the requirements for the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent interruption of the anti-skid system function, or inadvertent selection of reverse thrust during a rejected takeoff. Either of these conditions could result in reduced controllability of the airplane.
87-07-08: 87-07-08 LOCKHEED-GEORGIA COMPANY: Amendment 39-5592. Applies to Lockheed JetStar Model 1329 and JetStar Model 1329-25 series airplanes, equipped with an AiResearch Aviation Company Model GTCP 30-92 Auxiliary Power Unit (APU) in accordance with STC SA1043WE or STC SA3297WE, certificated in any category. Compliance required as indicated, unless previously accomplished. To minimize the potential for fuel fumes entering the passenger compartment, accomplish the following: A. Within the next 600 hours time-in-service or 12 months after the effective date of this AD, whichever occurs earlier: 1. Install an improved APU fuel supply shutoff valve, Valcor P/N V4700- 130, in accordance with AiResearch Aviation Company Service Bulletin No. 11.37, dated December 19, 1984, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. 2. Visually inspect the sealing joint of the fuel control governor cover for fuelleaks, seal (O-ring) extrusion, and cover distortion, and replace, if necessary, prior to further flight, in accordance with the AiResearch Aviation Company Service Bulletin mentioned above. B. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Lockheed-Georgia Company, 86 South Cobb Drive, JetStar Customer Support, Dept. 64-26, Zone 668, Marietta, Georgia, 30063; or AiResearch Aviation Company, Customer Support Department, 6201 West Imperial Highway, Los Angeles, California 90045. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California. This amendment becomes effective May 1, 1987.