Results
2023-02-03: The FAA is superseding Airworthiness Directive (AD) 2022-01-09 for certain Stemme AG Model Stemme S 10-VT and Model Stemme S 12 gliders. AD 2022-01-09 required removing the affected freewheel clutch from service and prohibited the installation of affected parts. Since the FAA issued AD 2022-01-09, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to amend the definition of an affected part. This AD retains the requirements of AD 2022-01-09 for removing the affected freewheel clutch from service and continues to prohibit the installation of an affected part, and amends the definition of an affected part and clarifies the part installation prohibition. The FAA is issuing this AD to address the unsafe condition on these products.
83-05-05: 83-05-05 BRITISH AEROSPACE: Amendment 39-4578. Applies to BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect cracking of the windshield glazing frame and prevent possible failure of the adjacent fuselage frame, accomplish the following: A. For airplanes that have accumulated less than 25,000 total landings on the effective date of this AD, comply with the following: 1. Prior to the accumulation of 15,000 landings or within the next 500 landings after the effective date of this AD, whichever occurs later, unless accomplished within the previous 2,000 landings, visually inspect the windshield glazing frame for cracks internally and externally in accordance with the instructions contained in paragraph 4 entitled "Guidance to Operators" of British Aerospace Alert Service Bulletin 53-A-PM5425, Issue 3, dated February 20, 1978 (hereinafter referred to as the service bulletin).2. Repeat the inspection specified in paragraph A.1. of this AD at intervals not to exceed 2,500 landings from the last inspection until 25,000 landings are accumulated and thereafter comply with the inspection interval specified in paragraph B. of this AD. B. For airplanes that have accumulated 25,000 landings or more on the effective date of this AD, inspect the area in accordance with paragraph 4 entitled "Guidance to Operators" of the service bulletin within the next 400 landings after the effective date of this AD, unless accomplished within the last 800 landings, and thereafter continue to inspect the area at intervals not to exceed 1,200 landings from the last inspection. C. If cracks are found during any inspection required by this AD that do not extend forward of the cutouts for the windshield wiper shafts, accomplish the repair modification specified in BAC Modification PM2857, Part (a). 1. Within the next 750 landings after discovery of the cracks onairplanes with less than 25,000 landings at the time of the inspection. 2. Within the next 250 landings after discovery of the cracks on airplanes with 25,000 or more landings at the time of the inspection. D. If cracks are found during any inspection required by this AD that extend forward of the cutouts for the windshield wiper shafts (refer to Figure 1 of the service bulletin), accomplish the repair modification specified in BAC Modification PM2857, part (a), prior to further flight. E. Incorporation of BAC Modification PM2857, Part (a), or PM3346 or PM5525 eliminates the repetitive inspection requirement of this AD and constitutes terminating action. F. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. G. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. H. For the purpose of complying with this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's time in service by the operator's fleet average from takeoff to landing for the airplane type. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective April 4, 1983.
2001-18-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-18-51, which was sent previously to all known U.S. owners and operators of Eurocopter France (ECF) Model SA.315B, SA.316C, SA 3180, SA 318B, SA 318C, SA.319B, SE.3160, and SA.316B helicopters by individual letters. This AD requires, within 10 hours time-in-service (TIS), inspecting the magnetic drain plug and the main gear box (MGB) filter for a rust-colored deposit, inspecting the MGB to determine the angular displacement on the MGB output flange, and periodically examining oil samples. If a rust-colored deposit is found on the drain plug or filter, if the oil is rust-colored, or if the angular displacement is 1 millimeter (0.039 inch) or more, this AD requires replacing the MGB with an airworthy MGB before further flight. Repairing or overhauling the gearbox, or re-identifying certain gearboxes that have already been appropriately overhauled, is terminating action forthe requirements of this AD. This AD is prompted by an accident of an ECF Model SA.315B helicopter that lost power to the tail rotor. The loss of power to the tail rotor was due to wear of the splines of the output bevel drive pinion in the MGB. The actions specified by this AD are intended to prevent a loose splined coupling, spline wear, loss of power to the tail rotor, and subsequent loss of control of the helicopter.
2025-11-12: The FAA is superseding Airworthiness Directive (AD) 2020-03- 14, which applied to all Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-03-14 required an inspection of affected crew oxygen cylinder assemblies for any discrepancy and replacement of discrepant crew oxygen cylinder assemblies with serviceable parts, and allowed installation of affected parts under certain conditions. Since the FAA issued AD 2020-03-14, the supplier introduced an improved crew oxygen cylinder assembly, that will ensure the correct function of the system. This AD continues to require the actions in AD 2020-03-14, requires replacement of all affected parts with redesigned parts, and also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2005-14-10: The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas transport category airplanes. That AD currently requires implementation of a program of structural inspections to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This new AD requires implementation of a program of structural inspections of baseline structure to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This AD is prompted by a significant number of these airplanes approaching or exceeding the design service goal on which the initial type certification approval was predicated. We are issuing this AD to detect and correct fatigue cracking that could compromise the structural integrity of these airplanes.
2017-06-01: We are superseding Airworthiness Directive (AD) 2017-03-04, which applied to all The Boeing Company Model 737-500 series airplanes. AD 2017-03-04 required inspections to detect cracks in the fuselage skin panels, permanent repairs of time-limited repairs, skin panel replacement, and related investigative and corrective actions if necessary. This AD reduces the applicability of AD 2017-03-04. This AD was prompted by a determination that airplanes were inadvertently included in the applicability of AD 2017-03-04. We are \n\n((Page 14430)) \n\nissuing this AD to address the unsafe condition on these products.
2025-11-11: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701, and 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that new or more restrictive aircraft maintenance manual (AMM) tasks are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive AMM tasks, as specified in a Transport Canada, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2001-20-14: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 and SA227 series airplanes. This AD requires you to replace the brake shuttle valves with parts of improved design and install a shield over the hydraulic lines. This AD also requires replacing the rubber fuel hose with a metal device for certain SA226 series airplanes. This AD is the result of a report of a wheel brake system malfunction caused by a faulty brake shuttle valve. The actions specified by this AD are intended to correct potential brake shuttle valve problems, which could cause the brake assembly to drag and overheat. Hydraulic or fuel line damage could then occur if the overheated brake assembly is retracted into the main wheel well, with a consequent fire if the hydraulic or fuel lines ruptured.
51-04-01: 51-04-01 MARTIN: Applies to All Model 202 Aircraft. Compliance required not later than April 1, 1951. In order to eliminate a fire hazard due to the possibility of flow from the tank to the engine compartment in case of the failure of the carburetor vapor vent return line, install a swing type check valve at each fuel tank where the vapor vent line attaches to the tank so that flow can take place only toward the fuel tank. (Martin Service Bulletin No. 138, dated November 30, 1950, covers this same subject.)
80-12-02 R1: 80-12-02 R1 MCDONNELL DOUGLAS: Amendment 39-3785 as amended by Amendment 39-5499. Applies to McDonnell Douglas Model DC-6, -6A, -6B, R6D, and C-118 (Military) series airplanes, certificated in any category, with 30,000 hours or more total time-in-service. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent loss in strength capability of the wing due to lower wing fitting, stringer and skin cracks, accomplish the following: \n\n\t(a)\tWithin the next ten hours' time in service after the effective date of this AD, or within 25 hours' time in service from the last inspection conducted in accordance with this paragraph and thereafter at intervals not to exceed 25 hours' time in service, until inspected in accordance with paragraph (c), inspect by dye penetrant or equivalent the left and right hand wing lower surface six inches inboard and outboard of wing stations 96, 127, 138 and 179 from the front spar to the center spar. \n\n\t(b)\tIf cracks are found, before further flight, \n\n\t\t(1)\tAccomplish the inspection required by paragraph (c), and \n\n\t\t(2)\tRepair cracks in accordance with Douglas Structural Repair Manual or other repair data approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\t(3)\tAt intervals not to exceed 500 hours' time in service from the last inspection in accordance with paragraph (c) repeat the inspections required by paragraph (c). \n\n\t(c)\tWithin 100 hours' time in service after the effective date of this AD, unless previously accomplished within the last 400 hours' time in service and thereafter at intervals not to exceed 500 hours' time in service from the last inspection required by this paragraph, using procedures approved by FAA Principal Maintenance Inspector, \n\n\t\t(1)\tInspect by X-ray the left and right wing lower skin, stringers, and fittings between wing station 60 to 130 and 167 to 185, from the front spar to the center spar; and inspect by X-ray the wing skin that lies beneath the skate angle at wing station 130 at the inboard edge of the inboard nacelle, both left and right wing, in accordance with Douglas Aircraft Company Report MDC-J1946, "NDI Inspection Techniques for DC-6 Lower Wing Skin at Station 130," Revision "A", dated July 26, 1985, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\t(2)\tClean and visually inspect with a 4X magnification in the nacelle area internally between wing stations 130 and 167, from the front spar to the center spar, and \n\n\t\t(3)\tClean and inspect by dye penetrant or equivalent external skin surface six inches inboard and outboard of wing station 96, from the front spar to the center spar. \n\n\t\t(4)\tThe interval for conducting the X-ray inspection in paragraph (c)(1), above, may be extended from 500 to 1000 hours time-in-service from the last X-ray inspection, provided that the visual inspection specified in paragraph (c)(2),above, is extended to cover wing stations 60 to 185 from the front spar to the center spar, when the X-ray inspection is not accomplished. \n\n\t\t(5)\tRepair cracks prior to further flight in accordance with Douglas Structural Repair Manual or other repair data approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t(d)\tAlternate 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, Cl-750 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, orthe Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tAmendment 39-3785 superseded emergency telegraphic AD T80WE-18. \n\n\tAmendment 39-3785 became effective June 9, 1980. \n\n\tAmendment 39-5499 became effective January 28, 1987. \n\n\tThis action corrects Amendment 39-5499 (51 FR 46602; December 24, 1986). \n\n\tThis correction becomes effective April 21, 1987.