Results
86-25-07 R1: We are rescinding an existing airworthiness directive (AD) for the products listed above. The existing AD resulted from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Since issuance of that AD, we have determined that the AD is not applicable because the Model LS6 is not type certificated in the United States. During flights at speeds between 250 to 270 km/h (135 to 145 kts) aileron flutter occurred resulting in damage of control stick attachment.
70-01-06: 70-01-06 HUGHES: Amdt. 39-921. Applies to Model 269A, 269A-1, 269A-2 and 269B helicopters certificated in all categories with P/N 269A7506 lateral pitch mixer idler bellcrank assembly installed. To insure continued airworthiness of Hughes Model 269A, 269A-1, 269A-2 and 269B helicopters, with P/N 269A7506 lateral pitch mixer idler bellcrank assembly installed, accomplish the following: (a) For helicopters equipped with P/N 269A7506 bellcrank assembly having less than 875 hours time in service on the effective date of this AD, remove from service P/N 269A7506 lateral pitch mixer idler bellcrank assembly prior to the accumulation of 900 hours time in service, and mark it permanently and conspicuously to prevent its inadvertent return to service. Replace it with a serviceable P/N 269A7506 or P/N 269A7508 lateral pitch mixer idler bellcrank assembly. (b) For helicopters equipped with P/N 269A7506 bellcrank assembly having 875 or more hours' time in service on the effective date of this AD, remove from service P/N 269A7506 lateral pitch mixer idler bellcrank assembly prior to the accumulation of 25 additional hours time in service, and mark it permanently and conspicuously to prevent its inadvertent return to service. Replace it with a serviceable P/N 269A7506 or P/N 269A7508 lateral pitch mixer idler bellcrank assembly. This amendment becomes effective January 17, 1970.
2001-13-18 R1: The FAA is revising Airworthiness Directive (AD) 2001-13-18, which applies to Raytheon Aircraft Corporation (Raytheon) Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) airplanes. AD 2001-13-18 currently requires you to repetitively inspect the wing spar assembly for cracks and replace any wing spar assembly found cracked (unless the spar assembly has a crack indication in the filler strip where the direction of the crack is toward the outside edge of the filler strip). AD 2001-13-18 also requires you to report the results of the initial inspection and maintain the flight and operating restrictions required by AD 99-12-02 until the initial inspection is done. We approved alternative methods of compliance (AMOCs) to AD 2001-13-18. We have since determined that those AMOCs do not address all critical areas in the wing spar assemblies and should no longer be valid. We are issuing this revision to AD 2001-13-18 for the purpose of eliminating the AMOCs to AD 2001-13-18. The actions of this AD are intended to prevent wing spar failure caused by fatigue cracks in the wing spar assemblies and ensure the operational safety of the above-referenced airplanes.
2010-26-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A manufacturing quality non-conformity has been identified that resulted in the under-crimping of ring tags on a batch of In-tank Fuel Harnesses. The affected ring tags are used to join individual electrical wires in the Wing Tank harness installations to in-tank equipment on QT [Tank Quantity] circuit. The failure of a one or more ring tag crimp connections may result in the disconnection of the electrical wire with a possibility that the loose wire ends can contact the tank structure. When combined with a loss of equipment surface protection this constitutes a potential source of ignition in a fuel tank and consequent danger of fire or explosion. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2021-09-13: The FAA is superseding Airworthiness Directives (AD) 2000-23- 04 R1 and AD 2018-20-14, which applied to certain ATR-GIE Avions de Transport Regional Model ATR42-500 airplanes. AD 2000-23-04 R1 and AD 2018-20-14 required revising the maintenance or inspection program, as applicable, to incorporate new and/or more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by the FAA's determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2021-10-03: The FAA is superseding Airworthiness Directive (AD) 2019-03-12 for certain Airbus Helicopters Model EC225LP helicopters. AD 2019-03-12 required repetitively inspecting, cleaning, and lubricating each life raft inflation cylinder percussion system bellcrank (bellcrank). This new AD continues to require the actions specified in AD 2019-03-12, and requires replacing any affected bellcrank with a serviceable bellcrank, which terminates the repetitive actions. This AD was prompted by reports of jammed bellcranks in the life raft jettison inflation cylinder percussion system. The actions of this AD are intended to address an unsafe condition on these products.
2004-04-09: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) JT15D-1, -1A, and -1B turbofan engines with certain impellers part number (P/N) 3020365. This AD requires a one-time borescope inspection of the rear face of certain impellers for evidence of a machined groove or step, and repair or replacement of the impeller if a groove or step is found. This AD results from three reports of uncontained failure of the impeller. We are issuing this AD to prevent uncontained failure of the impeller and possible damage to the airplane.
2010-26-09: This amendment supersedes an existing emergency airworthiness directive (EAD) for the specified Sikorsky model helicopters. The EAD requires inspecting the LITEF Attitude Heading and Reference System (AHRS) unit of the navigation system to determine if it is at a Mod Status "18.'' If either AHRS unit is at Mod Status "18,'' the EAD requires installing placards on the instrument panel to prohibit single pilot instrument flight rule (IFR) and single pilot night flight and reducing airspeeds to 120 knots indicated airspeed (KIAS) if both autopilots uncouple during instrument meteorological conditions (IMC) or night flight. The EAD also requires inserting minimum crew and airspeed limitations into the Limitations section of the applicable Rotorcraft Flight Manual (RFM) to limit the minimum flight crew to 2 pilots for night flight and IFR flight and to reduce airspeed to 120 KIAS if both autopilots uncouple during IMC or night flight. This amendment contains the same requirements but draws the appropriate distinctions between IFR and IMC as used in the intended operating limitations. Also, unlike the EAD, this AD states the airspeed must be reduced to 120 KIAS if both autopilots uncouple during IMC or night flight. Further, we are removing the limitation contained in the Active Temporary Revisions relating to pilots keeping their hands and feet near the flight controls. This AD was prompted by the need to supersede the EAD to state the distinction between IFR and IMC as used in the operating limitations and to reduce the airspeed to 120 KIAS if both autopilots uncouple during IMC or night flight. The actions specified by this AD are intended to implement operating limitations based on an anomaly in the AHRS related to the 26 volt AC inverter that could result in a decoupling of both autopilots and to prevent loss of control of the helicopter during IMC and during night flight.
97-11-05: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Textron Lycoming) ALF502 and LF507 series turbofan engines, that requires initial and repetitive on-wing eddy current or in-shop fluorescent penetrant inspections of fuel manifold assemblies for cracks, and replacement, if necessary, with serviceable parts. In addition, this AD presents an optional terminating action to the repetitive inspections by replacing the fuel manifold assembly with an assembly of a new, improved design. This amendment is prompted by reports of cracking of the fuel manifold assembly at the No. 5 scallop location. The actions specified by this AD are intended to prevent cracking of the fuel manifold assembly, which could result in an engine fire.
72-16-10: 72-16-10 BOEING-VERTOL: Amendment 39-1498. Applies to Model 107-II helicopters certificated in all categories. Compliance required as indicated below: To prevent failure of the aft transmission collector gear and to prevent separation of the aft transmission planetary carrier retention nut, either of which may cause dephasing of the main rotors, accomplish the following: a. Within the next 15 hours in service after the effective date of this AD, unless already accomplished, inspect for cracks and flat spline root radii and shot peen internal splines of serial number designated collector gears P/N 107D2066-10 or -12 or -14 and change part number identification in accordance with Accomplishment Instructions Parts I and II of Boeing-Vertol Service Bulletin No. A107-318R-1 dated 19 June 1972 or equivalent methods approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. All other serial numbered collector gears shall be inspected and shot peenedat the next transmission overhaul or within 800 hours, whichever comes first. b. Within 50 hours time in service after last retorquing of planet carrier retention nut, unless already accomplished, loosen, retorque, and install lock pins in the aft transmission planetary carrier retention nut (P/N 107D1276-7, VS10304-39 or BACN10-GR39) and mark transmission nameplate in accordance with Accomplishment Instructions Parts I and III of Boeing-Vertol Service Bulletin No. A107- 317 dated 12 January 1972 or equivalent methods approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective August 11, 1972.