Results
51-19-04: 51-19-04 MARTIN: Applies to All Models 202 and 202A Airplanes Except as Noted. Compliance required as specified. In order to comply with the recommendations of the Martin 202 Modification Board, the following items must be accomplished. In all cases, modifications which are demonstrated to provide a level of safety equivalent to that provided by the modifications listed herein will be acceptable in lieu of the listed modifications. A. Canceled December 22, 1952. B. Compliance required by October 15, 1952. 1. Provide system independent of wing heat for windshield anti-icing, deicing defogging and birdproofing. Glenn L. Martin Service Bulletins Numbers 176 and 183 together with GLM Drawings Numbers 202A5051026, 202A5051027, 202A5051036, and 202A5051037 cover this same subject. (Applies to Model 202 airplanes only.) C. Compliance required by January 1, 1952. 1. Redesign heater fuel control box to make leak tight and provide adequate draining. 2. Relocate emergency high seat switches to eliminate lag. (Applies to Model 202 airplanes only.) 3. Redesign fire-detection circuit to eliminate stepping relay. (Applies to Model 202 airplanes only.) D. Compliance required by April 1, 1952. 1. Improve the landing gear position indicating system so as to reduce the possibility of obtaining a "safe" indication when gears is in an unsafe condition. (Martin Service Bulletins Numbers 163A (for Model 202A) and 168 (for Model 202) cover this same subject.) E. Compliance required prior to reactivation of the autopilot. 1. Accomplishment of the reduced gear ratio and installation of field rheostat in rudder servo motor circuit to reduce stall torque. Prototype installation to be approved by a Regional Office of FAA (Aircraft Engineering). (Martin Service Bulletins Numbers 104A and 114 cover this same subject.) (Applies to Model 202 airplanes only.) F. Compliance required before accumulation of 8,000 hours total operating time. 1. Accomplish reinforcement of the nacelle structure. (Martin Service Bulletins Numbers 144 (for Model 202) and 145 (for Model 202A) cover this same subject.) This supersedes AD 51-12-02.
2012-01-03: We are adopting an airworthiness directive (AD) for the Eurocopter France (ECF) Model AS332L2 helicopter and superseding an AD for the Model EC225LP helicopter. This AD is prompted by the manufacturer issuing additional corrective action to prevent failure of the main gearbox (MGB) due to the degradation of the epicyclic module of the MGB and expands the applicability to include the ECF Model AS332L2 helicopter because an investigation showed a failure within the epicyclic reduction gear module resulted in the rupture of the MGB case and separation of the main rotor head of a model AS332L2 helicopter in 2009. These actions are intended to prevent failure of the MGB and subsequent loss of control of the helicopter.
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.