Results
2012-01-04: We are adopting a new airworthiness directive (AD) for certain Model CN-235-100, CN-235-200, and CN-235-300 airplanes. This AD was prompted by reports of failures of the engine condition control cable which led to an engine shut down. This AD requires an inspection to determine the part number of the engine condition control cable, repetitive inspections for excessive wear of the affected engine condition control cable, and replacement of the affected part. We are issuing this AD to detect and correct failure of the engine condition control cable which could cause a consequent runway excursion during take-off, or reduced control of the airplane during flight.
98-12-02: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA Groupe Aerospatiale (SOCATA) Model TBM 700 airplanes. This AD requires inspecting the elevator trim tab fittings for cracks, and replacing any elevator trim tab found to have cracks. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent cracks in the elevator trim tab fittings, which could result in separation of the elevator trim tab and loss of control of the airplane.
2012-02-08: We are adopting a new airworthiness directive (AD) for certain ACSS TCAS units installed on but not limited to various transport and small airplanes. This AD was prompted by reports of anomalies with TCAS units during a flight test over a high density airport. The TCAS units dropped several reduced surveillance aircraft tracks because of interference limiting. This AD requires upgrading software. We are issuing this AD to prevent TCAS units from dropping tracks, which could compromise separation of air traffic and lead to subsequent mid-air collisions.
98-12-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Models S10 and S10-V sailplanes. This AD requires replacing the fuel filter if it is contaminated, inserting a revision to the Limitations Section of the flight manual, and inspecting the engine valve shafts for brownish-black sticky residue. If a residue is found on the valve shafts, this action will require cleaning the engine. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent engine valve malfunction, which could cause engine failure during flight and loss of control of the sailplane.
71-13-01R1: We are rescinding an airworthiness directive (AD) for Lycoming Engines model TIO-540-A series reciprocating engines. The existing AD, AD 71-13-01, was prompted by a report of a failed fuel injector tube assembly. Since we issued AD 71-13-01, we became aware that Lycoming Engines no longer supports Service Bulletin (SB) No. 335A, which was incorporated by reference in AD 71-13-01. The intent of the requirements of that SB is now in Lycoming Engines Mandatory SB No. 342F, which we have incorporated by reference into AD 2008-14-07. The FAA determined, therefore, that this requirement is duplicated by another AD.
69-20-05: 69-20-05\tBOEING: Admt. 39-851. Applies to Models 707 and 720 Series Aircraft listed in Subpart 1, A, "Effectivity," of Weber Service Bulletin No. 30R, dated September 5, 1969, or later FAA approved revision. \n\tCompliance required as indicated, unless already accomplished. \n\tTo prevent occurrence of a hazardous fire condition in and around the lavatory electrical razor outlet terminals, accomplish the following: \n\t(a)\tWithin the next 25 hours' time in service after the effective date of this AD, deactivate the razor terminal outlets by pulling all applicable AC and DC circuit breakers. Secure circuit breakers in the open position with suitable collars and affix a placard worded, "Inoperative," adjacent to the breakers. Outlets may be reactivated upon accomplishment of paragraph (b) below. \n\t(b)\tInstall the shelf, fiberglass cover box, and fiberglass retainer in accordance with the instructions of Part 2, "Accomplishment Instructions," of Weber Service Bulletin No. 30R, Revisiondated September 5, 1969, or later FAA approved revision, or an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\tThis amendment becomes effective October 2, 1969.
2012-02-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD requires an inspection of a certain alternating current (AC) power wire bundle for damage, and repair if necessary. Additionally, this AD requires segregating the wire bundle into two wire bundles and installing Teflon tubing. This AD was prompted by multiple reports of the loss of certain AC systems caused by a burnt AC power wire bundle. We are issuing this AD to prevent the loss of ice protection systems for the angle of attack vanes, pitot probes, engine inlets, and windshields, and consequent loss of or misleading airspeed indication and increased workload for the flight crew, which could lead to loss of control of the airplane.
2003-06-01: This amendment supersedes Airworthiness Directive (AD) 2002- 13-02, which applies to all Air Tractor, Inc. (Air Tractor) Models AT- 300, AT-301, AT-302, and AT-400A airplanes that have aluminum spar caps; certain Air Tractor Models AT-400 airplanes that have aluminum spar caps; and all Models AT-300 and AT-301 airplanes that have aluminum spar caps and are or have been converted to turbine power. AD 2002-13-02 currently requires you to inspect (one-time) the wing centerline splice joint for cracks and, if any crack is found, replace the affected wing spar lower cap; requires you to report the results of the inspection to the Federal Aviation Administration (FAA); and requires you to replace the wing spar lower caps after a certain amount of usage. Based upon the inspection results from AD 2002-13-02, FAA has determined that the mandatory wing spar lower cap replacement times should be reduced. This AD maintains the wing spar lower cap replacement and reporting requirements from AD 2002-13-02 and reduces the compliance time of these replacements. The actions specified by this AD are intended to detect and correct cracks in the wing centerline splice joint. If not detected and corrected, these cracks could eventually result in the wing separating from the airplane during flight.
69-11-01: 69-11-01 SWEARINGEN : Amdt. 39-767. Applies to Model SA26-T, S/N T26-2 through S/N T26-99, and Model SA26-AT, S/N T26-100 through S/N T26-142. Compliance required as indicated. To prevent failures of cockpit side windows, P/N 26-21288-1 and P/N 26-21288-2, accomplish the following: (1) After the effective date of this AD: (a) Operate aircraft with cabin pressure differential not in excess of 5.0 psi. (b) Prior to the first flight, install placard in full view of pilot calling out maximum allowable cabin pressure differential of 5.0 psi. (c) Prior to each flight, inspect cockpit side windows for cracks, with particular attention to all edges and corners. (2) If any crack is found, airplanes may be operated unpressurized only. (3) Upon installation of new cockpit side windows, P/N 26-21383-5 and -6, in accordancewith Swearingen Aircraft Service Bulletin No. 26-68 dated April 28, 1969, or later FAA-approved revision or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA, the 5.0 psi limiting placard may be removed and the requirements of this AD discontinued. This amendment becomes effective May 26, 1969.
2012-02-05: We are adopting a new airworthiness directive (AD) for all Thielert Aircraft Engines GmbH (TAE) [[Page 4218]] TAE 125-02-99 and TAE 125-02-114 reciprocating engines. This AD was prompted by in-flight engine shutdown incidents reported on airplanes equipped with TAE 125 engines. We are issuing this AD to prevent in- flight engine shutdown, which could result in loss of control of the airplane.