Results
2004-24-10: The FAA adopts a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-3 airplanes modified with A.M. Luton's Supplemental Type Certificate (STC) number SA3777NM. This AD requires you to inspect the wiring for the heating blankets on P3 and PY pneumatic lines and the push-to-test function lights to ensure that they are wired to the correct schematic; replace the circuit breaker switch as applicable; and replace the flight manual supplement currently in use with Revision G, dated March 28, 2001 (incorporates Revision I of Sheet 1 of Drawing 20075, "Electrical System Schematic," dated October 10, 2000). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Canada. We are issuing this AD to detect and correct wiring installed in accordance with an incorrect drawing, which shows the pneumatic heating blankets to the P3 and PY pneumatic lines wired in series with the indicator lights, rather than parallel. This can result in reduced current for the heating blankets and loss of pneumatic line heating, which can lead to loss of engine power or reverse propeller overspeed governing protection and ultimately loss of control of the airplane.
96-26-02: This amendment adopts a new airworthiness directive (AD) that applies to certain FLS Aerospace (Lovaux) Ltd. OA7 Optica series 300 airplanes equipped with a Hoffman fan, part number HO-E315/122EZ, and fan shaft extension. This AD requires replacing the fan shaft extension with one that incorporates Modification No. B2/MOD/047. The AD results from a quality control review that shows that the four counterbores on the fan shaft extension to engine attachment flange have excessive depths. The actions specified in this AD are intended to prevent cracks from forming in the fan shaft extension flange and subsequent structural failure of this area because of counterbores with excessive depth.
80-07-13: 80-07-13 PACIFIC INFLATABLES COMPANY: Amendment 39-3731. P/N 4000 and P/N 4000E Series floatation devices. Compliance is required as indicated. To prevent the possible failure of the floatation device due to excessive age, accomplish the following: a. Within 10 days' time in service from the effective date of this AD, remove from service all Pacific Inflatables Company P/N 4000 and 4000E flotation devices. b. As of the effective date of this AD, Pacific Inflatables Company P/N 4000 or 4000E floatation devices are not eligible for installation in aircraft. This amendment becomes effective April 7, 1980.
2023-04-18: The FAA is superseding Airworthiness Directive (AD) 2021-03- 11, which applied to all Dassault Aviation Model FALCON 2000 airplanes. AD 2021-03-11 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2021-03-11, and also 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. The FAA is issuing this AD to address the unsafe condition on these products.
68-14-01: 68-14-01 BEECH: Amendment 39-618. Applies to Model D55, 56TC and E95 airplanes equipped with Beechcraft pneumatic deicer system and Beechcraft Model B5 Autopilot (manufactured as Brittain Model B-5P). Compliance required as indicated. An unsafe condition exists wherein the simultaneous operation of the Model B5 Autopilot and the pneumatic de-icer system might cause the airplane to exceed the structural limits. Since a potential unsafe condition exists, the following operating limitations are prescribed for all affected aircraft: A. Aircraft must not be operated with Beechcraft Model B5 Autopilot and Beechcraft pneumatic de-icer system operating simultaneously. B. Within the next ten hours time in service after receipt of the telegram a placard must be installed in clear view of the pilot near the autopilot controller stating as follows: "Autopilot must be turned OFF whenever the de-icer system is ON." C. Placard is to remain installed in aircraft until such time as Brittain Industries, Inc., Service Bulletin No. 68-1, Revision A, or a satisfactory equivalent modification approved by the Chief, Aircraft Engineering Division, FAA, Western Region, has been accomplished and incorporated into the autopilot system. This amendment becomes effective on July 10, 1968, for all persons except those to whom it was made effective immediately by telegram dated May 29, 1968.
85-18-03: 85-18-03 GENERAL ELECTRIC COMPANY: Amendment 39-5130. Applies to General Electric Model CJ610-8A, -9, and CF700-2D, -2D-2 turbine engines. Compliance is required as indicated unless already accomplished. To prevent failure of the stage 1 turbine disk, P/N 5011T75P01, with serial numbers beginning with the letters GATSRM, accomplish the following: Remove the disk from service in accordance with General Electric Alert SBs (CJ610) A72-142 or (CF700) A72-145, dated August 30, 1983, at or prior to accumulating 5,000 total cycles. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an alternative means of compliance may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The General Electric Alert SBs (CJ610) A72-142 and (CF700) A72-145, dated August 30, 1983, described in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the SBs from the manufacturer may obtain copies upon request to Project Manager, CJ610/CF700, General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, Rules Docket No. 83-ANE-24, 12 New England Executive Park, Burlington, Massachusetts 01803, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on November 15, 1985.
2004-24-09: The FAA is adopting a new airworthiness directive (AD) for certain RRC 250-B and 250-C series turboshaft and turboprop engines. This AD requires a onetime inspection of the fuel nozzle screen for contamination, and if contamination is found, inspection and cleaning of the entire aircraft fuel system before further flight. This AD also requires replacing the fuel nozzle with a new design fuel nozzle, at the next fuel nozzle overhaul or by June 30, 2006, whichever occurs first. This AD results from 10 reports of engine power loss with accompanying collapse of the fuel nozzle screen, due to fuel contamination. We are issuing this AD to minimize the risk of sudden loss of engine power and uncommanded shutdown of the engine due to fuel contamination and collapse of the screen in the fuel nozzle.
2000-05-16: This amendment adopts a new airworthiness directive (AD) applicable to Sikorsky Model S-61 helicopters. This action requires inspecting certain pylon upper and lower hinge web fittings (web fittings) for corrosion or a crack and either repairing certain web fittings or replacing any unairworthy web fittings with airworthy web fittings. The AD also requires creating a log card or equivalent record and implementing a recurring inspection of the web fittings. This amendment is prompted by the discovery of extensive cracking in the area of the web fittings. The actions specified in this AD are intended to prevent structural failure of the tail boom due to a crack or corrosion of certain web fittings and subsequent loss of control of the helicopter.
2023-02-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A321-251NX, A321-252NX, A321-253NX, A321-271NX and A321-272NX airplanes. This AD was prompted by an emergency exit slide deployment test on an Airbus Cabin Flex (ACF) overwing emergency exit, the emergency exit slide did not deploy due to disconnected slide release cable junction. This AD requires a one-time detailed inspection of the installation of the ACF overwing emergency exit slide release mechanism for discrepancies, 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.
2000-23-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that currently requires opening the circuit breaker of the pneumatic sense line heater tape, installing an inoperative ring, and coiling and stowing the electrical wire to the circuit breaker of the pneumatic sense line heater tape. That AD also provides for an optional inspection, which, if accomplished, constitutes terminating action for deactivation of the pneumatic sense line heater tape. This amendment requires repetitive inspections of the subject area and corrective actions, if necessary, and provides for an optional terminating modification(s) for the repetitive inspection requirements. This amendment is prompted by the FAA's determination that the one-time optional terminating inspection in the existing AD does not adequately detect chafing, electrical arcing, or inadequate clearance of the subject area. The actionsspecified by this AD are intended to detect and correct such inadequate clearance, which could result in a hole in the fuel feed pipe caused by electrical arcing, and consequent fuel leakage and possible ignition of the fuel vapors.\n\n\tThe incorporation by reference of certain publications, as listed in the regulations, is approved by the Director of the Federal Register as of December 27, 2000.\n\n\tThe incorporation by reference of McDonnell Douglas Alert Service Bulletin MD11-36A030, dated April 2, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 28, 1998 (63 FR 20066, April 23, 1998).