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75-10-04: 75-10-04 HUGHES HELICOPTERS: Amendment 39-2196. Applies to Hughes model 369, 369A, 369H, 369HM, 369HS, and 369HE helicopters certificated in all categories including Military YOH-6A and OH-6A equipped with aluminum tail rotor blades, part number 369A1613 or 369A1613-3. To determine if cracks exist in the root fittings of the tail rotor blades and assure timely rework of the fittings accomplish the following: A. Perform a close visual check by the pilot in command, or inspection by a certificated mechanic on any day the helicopter is operated, in accordance with Part III of Hughes Service Information Notice No. HN-83, dated April 15, 1975 or later FAA approved revisions. Comply with Part II of the notice for those blades specified therein prior to the first daily check or inspection. Remove all cracked blades from service prior to further flight. Note: The person who performs the check or inspection shall record it in the appropriate aircraft records per FAR 91.173. B.Within the next 50 hours time in service, unless already accomplished, comply with Part I of Hughes Service Information Notice No. HN-83, dated April 15, 1975 or later FAA-approved revisions. Remove all cracked blades from service prior to further flight. Continue the checks or inspections specified in paragraph A. above. C. For blades in spares inventory, including blades on spare tail rotor assemblies, accomplish Parts I and II of the Hughes S.I.N. No. HN-83, dated April 15, 1975, or later FAA- approved revisions, at or before installation on helicopter. D. Equivalent checks, inspections and rework may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. E. Aircraft may be flown to a base for performance of that work required by paragraph B., above, of this AD, per FARs 21.197 and 21.199." This amendment is effective May 12, 1975, for all persons except those to whom it was made effective immediately by airmail letter dated April 17, 1975.
2022-03-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that during type certification activity, it was identified that certain monitoring software was incorrectly implemented in the braking control system (BCS) certification standard. This AD requires installing (updating) certain software for the braking and steering system, 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.
97-13-10: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Aircraft Engines CF700 series turbofan engines, that requires replacement of existing fan guards with new, improved fan guards. This amendment is prompted by a report of uncontained fan blades which separated from the engine during an overspeed. The actions specified by this AD are intended to prevent an overspeed of the aft fan disk from resulting in an uncontained engine failure and damage to the aircraft.
2011-26-10: We are adopting a new airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F-28C, F-28C-2, F-28F, 280C, 280F, 280FX TH-28, 480, and 480B helicopters with certain trim relays to require modifying and testing the lateral and longitudinal cyclic trim actuator assemblies. This AD was prompted by four failures in the cyclic trim system on certain Enstrom model helicopters that resulted in reduced controllability of the helicopter. These actions are intended to prevent failure of the cyclic trim system and subsequent loss of control of the helicopter.
97-13-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all de Havilland Model DHC-8-100 and -300 series airplanes, that currently requires an inspection to detect discrepancies and damage of the low fuel pressure switch adapter/snubber (located on each engine fuel heater), and replacement, if necessary. That AD also requires an inspection to detect gaps or openings in each nacelle and engine-mounted firewall area, and in certain weather seals in the nacelles; and correction of discrepancies. This amendment requires certain new modifications to the nacelles that will minimize the passage of flammable fluid through the zones of the nacelle of each engine. The actions specified by this AD are intended to prevent the spread of fire through these zones in the event of an explosion during flight, and consequent structural damage to the airplane.
97-13-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB 340B and SAAB 2000 series airplanes. This action requires an inspection of the fluorescent lamps in the cabin area to ensure correct installation, and correction, if necessary. This AD also requires an inspection of the lampholders to identify any discrepancies and to ensure the security of the back covers, and replacement of discrepant lampholders with new lampholders; installation of retaining clips on certain Page Aerospace lampholders; and reinspection of the lamps to ensure correct installation after replacement or reinstallation of the lamps or lampholders, and corrections, if necessary. This amendment is prompted by reports indicating that loose back covers on the lampholders and incorrect lamp installations have led to electrical arcing between fluorescent tube pins and lampholders and consequent charring or melting of the affected areas. The actions specified inthis AD are intended to prevent such electrical arcing, which could burn the surrounding area and lead to smoke and fumes in the passenger compartment or lavatory area.
68-07-09: 68-07-09 CESSNA: Amdt. 39-682. Applies to Model 177, Serial Numbers 177-00001 through 177-01152, aircraft. Compliance: Required as indicated, unless already accomplished. To prevent oscillation in the longitudinal control system, accomplish the following: (a) Within 10 hours' time in service after the effective date of this airworthiness directive, modify the flap system by the installation of Cessna P/N 170094-1, in accordance with the instructions contained in Cessna Service Letter No. SE68-13, dated March 30, 1968, or any other method approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region. (b) Cessna P/N 170094-1 referred to in paragraph (a) may be removed when Cessna P/N 1709007-1 is installed in accordance with Cessna Service Letter SE68-14, operation 23 and attachments, dated April 11, 1968, as revised April 22, 1968, or when any other modification is installed which has been approved by Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region. This amendment becomes effective November 16, 1968.
97-12-04: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) GE90 series turbofan engines. This action requires initial and repetitive borescope inspections of compressor discharge pressure (CDP) manifolds for cracks, and replacement, if necessary, with an improved design CDP manifold. In addition, this AD requires, as terminating action to the inspections, replacement with an improved design CDP manifold. This amendment is prompted by reports of CDP manifold cracking that has resulted in liberated material causing high pressure compressor (HPC) blade damage. The actions specified in this AD are intended to prevent inflight engine power loss or shutdown due to HPC blade damage caused by liberated material from the CDP manifold.
81-05-52 R1: 81-05-52 R1 ROBINSON HELICOPTER: Amendment 39-4082. Applies to Model R-22 Helicopters, certified in all categories, Serial Numbers 0002 through 0036, 0038 through 0061, 0064 through 0089, 0093 and 0095. Compliance required as indicated, unless already accomplished. To prevent coupling failure which would result in the loss of power to the main rotor accomplish the following: (a) Prior to further flight, after receipt of telegraphic AD T81-05-52 or the effective date of this AD, whichever comes first, conduct an inspection of the main gearbox input flex coupling yoke P/N A 194 on all R-22 helicopters, Serial Nos. 0002 through 0036, 0038 through 0061, 0064 through 0089, 0093 and 0095, in accordance with Robinson Helicopter Company Service Bulletin SB-9, dated March 4, 1981, unless previously accomplished in accordance with Robinson Helicopter Company SB-6 dated January 26, 1981, within the previous ten (10) hours time in service. (b) Replace defective main gearbox flex coupling yoke P/N A 194 with like serviceable couplings from any production lot 18 and subsequent or new inertia welded coupling P/N A 908-1. Replacement using either of these couplings is terminating action for this AD. (c) After the inspection in (a), at intervals not to exceed ten (10) hours additional time in service, inspect Robinson R-22 Model Helicopters Serial No. 0002 through 0036, 0038 through 0061, 0064 through 0089, 0093 and 0095 main gearbox input flex coupling yoke, P/N A 194, for cracks, in accordance with Robinson Helicopter Company Service Bulletin SB-9, dated March 4, 1981. Comply with (b) if cracks are found. (d) Do not install a yoke, P/N A 194, from production lot prior to 18 as a replacement part or as original installation. Special flight permits may be issued in accordance with FAR 21.197 and FAR 21.199 to operate helicopters to a base for the accomplishment of inspections or modifications required by this AD. Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. 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. 553(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Robinson Helicopter Company, 24747 Crenshaw Boulevard, Torrance, California 90505. These documents may also be examined at FAA Western Region Office, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its headquarters in Washington, D.C. and at FAA Western Region Office. This supersedes AD No. T81-03-52.This amendment 39-4082 becomes effective April 13, 1981 to all persons except those to whom it was made immediately effective by telegraphic AD T81-05-52, dated March 4, 1981.
97-12-05: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) GE90 series turbofan engines. This action supersedes Telegraphic AD T97-09-51 that currently requires visual checks of the engine Debris Monitoring System (DMS) sensor for bearing debris, and, if necessary, performing procedures for additional maintenance actions. In addition, that AD requires replacing Variable Speed Constant Frequency (VSCF) gearshaft flange ball bearings that may incorporate rivets that are manufactured of improper material with serviceable bearings. This action references a later revision of the applicable Service Bulletin (SB) that includes additional engine serial numbers; however, these changes do not affect the Applicability or compliance requirements of this AD. This amendment is prompted by the issuance of the new revision to the SB. The actions specified by this AD are intended to prevent a VSCF gearshaft flange ball bearing failure, which could result in an inflight engine shutdown.