Results
2000-02-32: This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model SA. 315B helicopters, that currently requires initial and repetitive visual inspections and modification, if necessary, of the horizontal stabilizer spar tube (spar tube). This amendment requires the same corrective actions as the existing AD and would require an additional dye-penetrant inspection of the half-shell attachment clamps (clamps). This amendment is prompted by an in-service report of fatigue cracks that initiated from corrosion pits. The actions specified by this AD are intended to prevent fatigue failure of the spar tube, separation of the horizontal stabilizer and impact with the main or tail rotor, and subsequent loss of control of the helicopter.
2023-02-02: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation (Gulfstream) Model GV and GV-SP airplanes. This AD was prompted by the omission of a life limit in the airworthiness limitations section (ALS) of the maintenance manual for a certain main landing gear (MLG) trunnion pin. This AD requires revising the ALS of the existing instructions for continued airworthiness (ICA) or inspection program for the airplane to establish a life limit for the affected MLG trunnion pin. The FAA is issuing this AD to address the unsafe condition on these products.
2000-02-30: This document adopts a new airworthiness directive (AD) that applies to all Twin Commander Aircraft Corporation (Twin Commander) 600 series airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2004-23-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 and A320 series airplanes, that requires a modification and replacement affecting all fuel tanks. All affected airplanes require the installation of fuses in the wiring of the fuel quantity indicating probes of all fuel tanks. Some affected airplanes also require replacement of the high-level sensors of the additional center tanks (ACTs) with new sensors. For all affected airplanes, these actions are necessary to prevent overheating of the fuel probes due to a short circuit. For some affected airplanes, these actions are necessary to prevent fuel leakage due to inadequate space for thermal expansion within the ACTs. Such conditions could result in fuel vapors or fuel contacting an ignition source and/or consequent fire/explosion in the center fuel tanks. These actions are intended to address the identified unsafe condition.
2004-23-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-700 and -800 series airplanes. This AD requires doing an initial inspection for pitting and cracks of the lower skin panel at the lap joint; trimming the inner skin; installing exterior doublers; replacing the fuselage skin assembly; doing repetitive supplemental inspections; and repairing if necessary; as applicable. This AD is prompted by a report indicating that localized pitting in the lower skin panels was found during production on a limited number of airplanes. We are issuing this AD to detect and correct premature fatigue cracking at certain lap splice locations and consequent rapid decompression of the airplane.
2023-01-11: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran) Makila 1A and Makila 1A1 model turboshaft engines. This AD was prompted by reports of false engine fire warnings. This AD requires replacing the affected fire detectors, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected fire detectors. The FAA is issuing this AD to address the unsafe condition on these products.
64-05-03: 64-05-03 GENERAL DYNAMICS: Amdt. 688 Part 507 Federal Register February 21, 1964. Applies to All Models 22, 22M, 30 and 30A Aircraft. Compliance required as indicated. To prevent slipping of the aileron trim tab dial assembly in relation to the cable drum within the aileron and rudder trim gearbox assembly; to insure that the gear teeth on the aileron trim tab dial gear are not damaged; and to ascertain that the inside rim of the aileron trim tab dial gear is not rubbing against the sides of the hub of the aileron and rudder trim gear box, accomplish the following: (a) Within 500 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 500 hours' time in service from the last check, perform an operational check (see Maintenance Manual) to determine that the aileron trim tab dial indicator and the aileron trim tab deflections correspond throughout the operational range and that the aileron trim tab control knob and dial workproperly without evidence of binding or slippage. If there is any evidence that the aileron trim tab dial indicator and the aileron trim tab deflections do not correspond throughout the operational range or if there is any evidence of binding or slippage in the operation of the aileron trim tab control knob and dial, rework the aircraft per (b)(1) and (b)(2) before further flight. After compliance with paragraph (b) the checks required by this paragraph may be discontinued. (b) Within 1,500 hours' time in service after the effective date of this AD unless the modification has already been accomplished: (1) Pin the aileron trim drum shaft to the shaft gear and the aileron trim tab dial to the aileron trim tab gear per General Dynamics/Convair 880 Service Bulletin No. 27-27, 880M Service Bulletin No. 27-34, or 990 Service Bulletin No. 27-52, as applicable, or an FAA Western Region Engineering and Manufacturing Branch approved equivalent. (2) Conduct a visual inspection of the aileron trim tab dial gear and hub of the support within the aileron and rudder trim gearbox assembly and if there is any evidence that the gear teeth on the aileron trim tab dial gear are damaged or there is any evidence that the inside of the rim of the aileron trim tab dial gear is rubbing the hub of the support, rework the hub of the support and replace any damaged aileron trim tab dial gear with a new gear in accordance with General Dynamics/Convair 880 Service Bulletin No. 27-70, 880M Service Bulletin No. 27-37 or 990 Service Bulletin No. 27-62, as applicable, or an FAA Western Region Engineering and Manufacturing Branch approved equivalent. (General Dynamics/Convair 880 Service Bulletin Nos. 27-27 and 27-70, 880M Service Bulletins Nos. 27-34 and 27-37 and 990 Service Bulletins Nos. 27-52 and 27-62 cover this same subject.) This directive effective March 23, 1964.
2000-02-34: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that requires revising the Airplane Flight Manual to provide the flightcrew with modified procedures and limitations for operating in icing conditions. This amendment is prompted by an accident report indicating that possible accretion of ice on the wings of the airplane, due to the wing anti- ice system not being activated by the flightcrew, could have contributed to the source of the accident. The actions specified by this AD are intended to prevent undetected accretion of ice on the wings, which could result in reduced controllability of the airplane during normal icing conditions.
2004-23-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that currently requires modification of certain fuselage support structure for the number 2 galley. This amendment requires modification of the same support structure using new methods based on new calculations. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent the galley from shifting, which could limit access to the galley door during emergencies, and result in injury to passengers and flightcrew. This action is intended to address the identified unsafe condition.
2023-01-07: The FAA is adopting a new airworthiness directive (AD) for all GE Aviation Czech s.r.o. (GEAC) H75-100, H75-200, H80, H80-100, H80- 200, H85-100, and H85-200 model turboprop engines. This AD is prompted by the manufacturer revising the airworthiness limitations section (ALS) of the existing engine maintenance manual (EMM) to introduce updated coefficients for the calculation of the cyclic life and safe life for the main shaft. This AD requires revising the ALS of the existing EMM and the operator's existing approved maintenance or inspection program, as applicable, to incorporate the updated coefficients and recalculate the cycles accumulated on critical parts. The FAA is issuing this AD to address the unsafe condition on these products.