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76-07-03: 76-07-03 FAIRCHILD: Amendment 39-2565. Applies to all FH-227 airplanes incorporating the outward opening large cargo door per STC SA2246WE. Compliance required within the next 300 hours time in service after the effective date of this AD, unless already accomplished. (a) To prevent inadvertent opening of the large cargo door in flight, accomplish the alteration in paragraph 2, Accomplishment Instructions, in Fairchild Service Bulletin FH-227-52-17, dated October 27, 1975, for FH-227 airplanes, or an equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective April 6, 1976.
77-05-05: 77-05-05 ADS SUPPLY COMPANY, AIR SPARES INTERNATIONAL, INC. AND SPENCER AIRCRAFT INDUSTRIES: Amendment 39-2849 as amended by Amendment 39-2868 and 39-2881 is further amended by Amendment 39-3199. Applies to various unapproved appliances, identified herein by the Boeing part number, sold by or procured through ADS Supply Company, Bellevue, Washington, Air Spares International, Inc., Seattle, Washington, or Spencer Aircraft Industries, Seattle, Washington, and installed in various Boeing model airplanes. Compliance required as indicated. Accomplish the following: A. Before further flight, except as provided in paragraph F, remove part number 65-52811 - Landing Gear Accessory Unit. B. Before further flight, except as provided in paragraph G, remove part number 65-52809 - Fire Detection Accessory Unit and part number 69-37307 - Engine and Fire Control Module. C. By March 18, 1977, remove the following appliances: (Additional dash numbers identify airline configurations.) Boeing Part No. Unit 65-52801- APU Accessory Unit 65-52807- Flap/Slat Position Switching Unit 69-37335- Fuel System Module Assembly 65-52804- Audio Accessory Unit 65-60211- Landing Gear Accessory Unit 69-37369- Ground Proximity System Test Accessory Module 69-37336- Ground Proximity Aural Warning Accessory Module 65-52805- Flight Instrument Accessory Unit 69-37346- Window and Pitot Heat Module 69-37338- Gyro Switching Panel D. By April 2, 1977, remove the following appliances: (Additional dash numbers identify airline configuration.) Boeing Part No. Unit 65-49808- Electrical Power Relay Module 65-52803- Window Heat Accessory Unit 65-52808- Compartment Overheat Accessory Unit 65-52810- Air Conditioning Accessory Unit 69-37314- AC System Generator and APU Module 69-37315- Generator Drive Standby Power Module 69-37317- Hydraulic Pump Module 69-37319- Air Conditioning Module 69-37320- Engine and Wing Anti-Ice Module 69-37324- Cabin Temperature Module 69-55179- Light Dimming Module 69-37344- VHF Navigation and Compass Switching Unit 65-52806- Miscellaneous Solid State Switching Module 69-37357- Thrust Reverser Override Module 69-37352- Door Warning Annunciator E. By April 8, 1977, remove the following appliances: (Additional dash numbers identify airline configuration.) Boeing Part No. Unit 65-37568- Landing Gear Accessory Unit 65-60209- Engine Fire Detection Control Unit Assembly 65-24917- Autopilot Accessory Unit 69-37313- Flight Control Module 65-24920- Fire Detector Module 69-37321- Electrical Module Assembly 65-60214- Flight Instrument Accessory Unit F. Operations with part number 65-52811 - Landing Gear Accessory Unit may continue until March 18, 1977, provided that before further flight a placard is installed adjacent to the speed brake handle stating "DO NOT ARM." Airplanes may be flown in accordance with FAR 21.197 to a maintenance base to accomplish the above. G. Operations with part number 65-52809 - Fire Detection Accessory Unit and part number 69- 37307 - Engine and APU Fire Control Module may continue until March 18, 1977, provided that before further flight, and daily thereafter, conduct tests in accordance with a procedure available from the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Airplanes may be flown in accordance with FAR 21.197 to a maintenance base to accomplish the above. H. By May 6, 1977, remove the following appliances: (Additional dash numbers identify airline configuration.) Boeing Part No. Unit 69-37339- Stall Warning Test Module 65-79479- Autobrake Accessory Unit 69-37334- Cabin Altimeter and Rate of Climb Module 65-73606- Engine Accessory Unit 65-52812- Autopilot Accessory Unit 65B-46136- Fire Detector Module I. By May 27, 1977, remove the following appliance: (Additional dash numbers identify airline configuration.) Boeing Part No. Unit 65-52802-1 Autopilot Switching Unit J. By May 26, 1978, (notwithstanding the dates of compliance listed in paragraphs A through I above) remove all appliances with Boeing part numbers listed in paragraphs A through I above which have been sold by or procured through Spencer Aircraft Industries (additional dash numbers identify airline configuration). K. Upon request of the operator, an FAA Principal Inspector, subject to the prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the compliance schedule in this AD for specific appliances if the request contains substantiating data to justify the increase for that operator. Amendment 39-2849 deleted Amendment 39-2837, AD 77-04-03. Amendment 39-2849 became effective March 10, 1977. Amendment 39-2868 became effective April 7, 1977. Amendment 39-2881 became effective April 28, 1977. This Amendment 39-3199 becomes effective May 9, 1978.
2002-12-15: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Pratt & Whitney PW4000 series turbofan engines. That AD requires operators to perform initial and repetitive inspections for cracking of high pressure compressor (HPC) front drum rotors based on cycle usage. That AD also requires the removal from service of any cracked HPC front drum rotors. This amendment clarifies inspection requirements for cracking of HPC front drum rotors that have fewer than 1,000 cycles-since-new (CSN). This amendment is prompted by comments from operators seeking more clarity about the inspection requirements of paragraph (a)(1) of that AD. The actions specified by this AD are intended to prevent HPC drum rotor failure from cracks that could result in an uncontained engine failure and damage to the airplane.
2025-01-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a full-scale fatigue test that found cracks on the main landing gear (MLG) bay rear skin panel at the stringer run-out at Frame 46 and Stringer 32 on the left-hand and right-hand sides. This AD requires repetitive special detailed inspections (SDIs) of the affected area for cracking and applicable corrective actions, 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.
2025-01-04: The FAA is adopting a new airworthiness directive (AD) for certain DAHER AEROSPACE (DAHER) Model TBM 700 airplanes. This AD was prompted by reports of wear of the inner flap actuator drive nut. This AD requires cleaning and lubricating the internal actuator rods, measuring the play between the drive nuts and the internal actuator rods, and if any play is found, replacing the drive nuts. This AD also allows replacing the drive nuts with certain other design drive nuts as terminating action for the requirements. The FAA is issuing this AD to address the unsafe condition on these products.
2002-12-14: This amendment supersedes an existing airworthiness directive (AD) for specified Eurocopter France (ECF) model helicopters that currently requires inserting statements into the Limitations section of the Rotorcraft Flight Manual (RFM) prohibiting flight under certain atmospheric conditions. This amendment contains the same requirements but corrects, expands, and updates the applicability. This amendment is prompted by an incident in which a Multi-Purpose Air Intake (MPAI) inlet seal deflated after the P2 air system line, which feeds the seal, clogged due to the formation of ice. The actions specified by this AD are intended to prevent clogging of the MPAI seal P2 air system line due to ice formation, which could result in deflation of the MPAI seal, loss of engine power, and subsequent loss of control of the helicopter.
67-31-03: 67-31-03 BRITISH AIRCRAFT: Amdt. 39-519, Part 39, Federal Register November 30, 1967. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated, unless already accomplished. To prevent reversal of the rudder feel function, within the next 500 hours' time in service after the effective date of this AD, accomplish the following: (a) Replace the paired links located in the rudder feel simulator linkage, Hobson P/N CH 504-071 or CH 504-280 with redesigned Hobson slotted links, P/N CH 504-446 in accordance with British Aircraft Corporation on BAC 1-11 Alert Service Bulletin PM 3290, or later ARB-approved issue, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region. (b) Attach Hobson slotted links P/N CH 504-446 with bolts P/N CH 127803-25 (NAS 1108-25) and CH-127803-22 (NAS 1108-22), or self-retained bolt P/N CH 127800 (NAS 1108-27-SR) and rivet P/N CH 524-129-3. If bolts P/N CH127803-25 (NAS 1108-25) and CH 127803-22 (NAS 1108-22) are used, replace these bolts with self-retained bolt P/N CH 127800 (NAS 1108-27-SR) and rivet P/N CH-524-129-3 during the next overhaul of the rudder feel simulator units. This amendment effective November 30, 1967.
52-25-01: 52-25-01 DOUGLAS: Applies to All Models DC3 Aircraft Equipped With Vacuum Systems. \n\n\tTo be accomplished not later than May 1, 1953. \n\n\tTo guard against the possibility of excessive air temperatures and associated fire hazards in the vacuum system discharge line, one of the following modifications must be accomplished: \n\n\t1.\tInstall a fusible plug in the side of the vacuum pump discharge port at right angles to the axis of the discharge port boss. Some pumps incorporate a plugged hole in the discharge port which may be enlarged to a 3/8-inch pipe tapped hole to accommodate the fusible plug. This plug should employ an AN 840-8D fitting with a binary eutectic mixture of 67.8 percent tin and 32.2 percent cadmium, which has a melting point of 351 degrees F. A drawing describing the design of such a plug is shown in Figure 2. The 3/8-inch plug fitting is intended for pumps such as the Model 3P-211 and 3P-485. For smaller pumps such as the 3P-207, an AN 840-6D fitting, incorporating the same modification as shown below, should be used. Brass fittings of the same design as the above dual fittings are acceptable. Incorporation of an overboard drain line clamped to the fusible plug is recommended but is not mandatory. On installations which do not use an overboard discharge line the possibility exists that the plug may damage other nacelle components if it can hit them upon being blown out of the adapter at high velocity. Therefore, if no overboard discharge line is provided, the installation must be made in such a manner that the plug will not be directed toward any vulnerable components when it issues from the adapter, or \n\n\t2.\tEmploy an oil separator equivalent in principle to the Genisco No. 40081 incorporating a pressure relief valve which can be disassembled for cleaning. \n\n\t(Douglas Service Letter A-129-T-1271/WB-11-Q-4 dated April 1, 1949, covers this type modification.)
2025-01-07: The FAA is superseding Airworthiness Directive (AD) 2022-11- 01, which applied to certain Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2022-11-01 required a detailed inspection (DET) of the main landing gear (MLG) support rib 5 lower flange, a fluorescent penetrant inspection (FPI) around the spot facing of certain fastener holes if necessary, and applicable corrective actions. This AD was prompted by the determination that additional airplanes are affected by the unsafe condition. This AD continues to require the actions in AD 2022-11-01 and adds airplanes to the applicability, 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.
2015-21-10: We are superseding Airworthiness Directive (AD) 2015-19-03 for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and - 900ER series airplanes. AD 2015-19-03 required revising the maintenance or inspection program to include new airworthiness limitations. This AD continues to require a maintenance or inspection program revision, but with revised language. This AD was prompted by a determination that certain language in the airworthiness limitation was not accurate in AD 2015-19-03. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine, which could result in the inability to shut off fuel to the engine and, in case of certain engine fires, an uncontrollable fire that could lead to wing failure.