Results
2020-20-08: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires, depending on helicopter configuration, installing skived polytetrafluoroethylene tape (PTFE tape) or removing PTFE tape and replacing window seals. This AD also prohibits the installation of a jettisonable cabin window unless the applicable requirements are accomplished. This AD was prompted by a report of excessive friction between the window seal and the helicopter airframe. The actions of this AD are intended to address an unsafe condition on these products.
59-06-01: 59-06-01 AERO COMMANDER: Applies to Model 500, Serial Numbers 618 Through 724 Except 700 and 718. Compliance required as indicated. I. Inspection. Within the next five hours of flight unless previously accomplished, inspect each elevator front spar in the area of the outboard hinge brackets for cracks. The elevator outboard hinge brackets must be removed for this inspection. If no cracks are found, the horizontal stabilizer must be modified as outlined in Item II. If any cracks are found in the elevator front spar, the spar must be reworked as outlined in Item III and the horizontal stabilizer must be modified as outlined in Item II. II. Modification. The horizontal stabilizer will be modified by installation of lead weights on the horizontal stabilizer front spars by incorporating Aero Design Company Kit No. Service Bulletin 57 or an equivalent approved modification. Modification of aircraft without elevator spar cracks will be accomplished within 25 flight hours, but not later than May 1, 1959. Modification of aircraft with elevator spar cracks will be accomplished immediately. III. Rework. If cracks are present, contact the Service Department, Aero Design and Engineering Company, Post Office Box 118, Bethany, Oklahoma, for rework of the elevator front spars. (Modification instructions are contained in Aero Design Service Bulletin No. 57. Rework of the elevator front spars is covered by Aero Design Salvage E.O. No. 5440000.) This Airworthiness Directive supersedes the FAA telegraphic instruction of March 12, 1959.
72-07-08: 72-07-08 GRUMMAN: Amdt. 39-1419. Applies to all Model G-159 Airplanes certificated in all categories. Compliance required as indicated unless already accomplished. To prevent jamming of the main landing gear drag brace assembly, P/N 159L10003, accomplish the following: (a) For airplanes having been inspected and modified, if necessary, in accordance with Grumman Customer Bulletin Number 99 or 217 within the last 50 hours time in service, comply with paragraph (e) below within the next 50 hours time in service after the effective date of this AD. (b) For all airplanes incorporating a new drag brace lower bearing, P/N 159LM10011-3 or -5, within the last 100 hours time in service, comply with paragraph (e) below within the next 15 hours time in service after the effective date of this AD. (c) Airplanes having been inspected and modified, if necessary, in accordance with Grumman Customer Bulletin 217A have met the requirements of this AD. (d) All airplanes that do not meet the requirements set forth in paragraphs (a), (b), or (c) above, must comply with paragraph (e) below within the next 15 hours time in service after the effective date of this AD. (e) (1) Inspect the following areas of the main landing gear drag brace assembly in accordance with Grumman Customer Bulletin 217A dated February 18, 1972 or later FAA approved revision: (a) Inner cylinder, P/N 159LM10001, for wear and galling; (b) The lower bearing, P/N 159LM10011, for wear and proper wall thickness; (c) The down lock, P/N 159LM10007, for the presence of a .030 + 010 inch radius on the 2.735 inch major diameter. (2) If bearing wear or improper wall thickness is found, before further flight, replace with a P/N 159LM10011-7 bearing. (3) If the down lock radius is absent, or if wear or galling of the inner cylinder is noted, before further flight, rework in accordance with Grumman Customer Bulletin 217A. (f) Airplanes requiring any action under sub-paragraph (e)(2) or (e)(3) above, may be flown with the landing gear in the down and locked position in accordance with FAR 21.197 to a base where the repair or modification can be accomplished. This amendment becomes effective March 30, 1972.
2020-22-12: The FAA is adopting a new airworthiness directive (AD) for certain Polskie Zaklady Lotnicze Sp. z o.o. Model PZL M28 05 airplanes. 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 defective thermo-shrinkable tubes installed on the electrical harnesses located in the fuel tanks. This AD requires a one-time inspection of the electrical harnesses located in the fuel tanks and, depending on findings, replacement of the affected harness. The FAA is issuing this AD to address the unsafe condition on these products.
2006-12-06: The FAA is adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires inspecting to determine if certain galleys and closets are installed, and replacing the spiral wire wrapping of the electrical cables of the galleys and closets with new spiral wire wrapping if necessary. This AD results from testing and reports from the manufacturer indicating unacceptable flammability properties of wire wrapping installed in certain galleys and closets. We are issuing this AD to prevent fire propagation or smoke in the cabin area due to electrical arcing or sparking and ignition of the spiral wire wrapping.
2006-11-17: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, B3, C, D, and D1 helicopters that have a Geneva Aviation, Inc. (Geneva) P132 console (console) installed. This AD requires installing right and left side Geneva cyclic control sticks and modifying the cyclic grips and the co- pilot cyclic stand (receptacle). This amendment is prompted by reports that pilots had restricted cyclic stick travel when using Eurocopter factory-installed cyclic sticks in a helicopter modified under a certain Supplemental Type Certificate (STC) for the installation of a Geneva P132 console. The actions specified by this AD are intended to prevent restricting full lateral movement of the cyclic control during high lateral center of gravity (CG) load operations in high cross winds and during slope takeoffs or landings and subsequent loss of control of the helicopter.
73-13-06: 73-13-06 HAWKER SIDDELEY: Amdt. 39-1671. Applies to Hawker Siddeley deHavilland Model DH-114 "Heron" Airplanes, having Modifications 496 installed. Compliance is required as indicated. To prevent possible inadvertent actuation of aileron and rudder trim in a direction other than that desired and to prevent possible interference by the aileron trim jack with the aileron when in its full down position, accomplish the following: Prior to September 21, 1973, unless already accomplished, incorporate Hawker Siddeley Modifications Nos. 1006 and 1053, or FAA-approved equivalents. This amendment becomes effective June 23, 1973.
2006-11-16: The FAA is superseding an existing airworthiness directive (AD) for AlliedSignal, Inc. T5317A-1 turboshaft engines. That AD currently requires repetitive engine fuel pump pressure tests of certain fuel control regulator assemblies to determine if both fuel pumps in the fuel control regulator assemblies are producing fuel pressure. That AD also requires replacing the fuel control regulator assembly, if necessary. This AD requires initial and repetitive visual and dimensional inspections of fuel control regulator assembly main and secondary drive shaft and pump gear splines, installed in certain fuel control regulator assemblies. This AD also expands the engine applicability, and includes certain engines installed on helicopters certified under Sec. 21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 or 14 CFR 21.27). This AD results from several reports of loss of fuel flow from the engine fuel control regulator assembly due to failure of both main and secondary drive shaft and pump gear splines. We are issuing this AD to prevent in-flight engine failure and forced autorotation landing.
95-19-13: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146-100A, -200A, and -300A airplanes, that requires repetitive inspections for cracking of fuselage frame 29, and repair, if necessary. This amendment is prompted by testing that revealed fatigue cracking in the web and inboard flange of frame 29. The actions specified by this AD are intended to prevent reduced structural integrity of the fuselage due to fatigue cracking in frame 29.
2018-11-10: We are superseding Airworthiness Directive (AD) 2017-01-07, which applied to all Dassault Aviation Model FAN JET FALCON airplanes; Model FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE- FALCON 200 airplanes; Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20- F5 airplanes; and Model MYSTERE-FALCON 50 airplanes. AD 2017-01-07 required a functional test or check of the main entry door closure and warning system, and applicable door closing inspections, adjustments, operational tests, and corrective actions if necessary. This AD requires repetitive door closing inspections, adjustments, operational tests, and corrective actions if necessary. This AD was prompted by a report indicating that during approach for landing, the main entry door detached from an airplane. We are issuing this AD to address the unsafe condition on these products.