Results
2007-09-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as Several recent inspections have revealed that some spar wooden centre blocks have shown cracks. Investigation revealed that cracks are generated by the wood drying. Actions specified in this AD are intended to detect and correct any defects on the central wing spar block. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2000-26-11: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters. This action requires replacing certain tail rotor blades with airworthy tail rotor blades. This amendment is prompted by a tail rotor blade (blade) failure that caused a high vibration level in the helicopter. Investigation revealed that the failure was due to a change in the manufacturing process for an identified production lot of blades. This condition, if not corrected, could result in a failure of a blade and subsequent loss of control of the helicopter.
2000-25-53: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-25-53, which was sent previously to all known U.S. owners and operators of Airbus Model A330 series airplanes by individual notices. This AD requires either repetitive detailed visual inspections or repetitive borescopic inspections to detect cracking or other damage of the barrel nuts of the engine aft mount; and replacement of any cracked nut and its associated bolt with a new nut and bolt, or replacement of all 4 nuts and their associated bolts if two or more nuts on the same engine mount are found cracked. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the aft engine mount nut, which could result in reduced structural integrity of the engine-to-pylon aft mount assembly, or, in the case of multiple cracked nuts, possible loss of an engine.
2013-25-08: We are superseding airworthiness directive (AD) 2009-24-09 for all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2009-24-09 required a repetitive inspection program on certain check valves in the hydraulic systems that includes, among other things, inspections for lock wire presence and integrity, traces of seepage or black deposits, proper torque, alignment of the check valve and manifold, installing new lock wire, and corrective actions if needed. This new AD expands the applicability, reduces the compliance time, changes torque values of the check valve tightening, and requires a repetitive inspection program for certain check valves in the [[Page 78695]] hydraulic systems on airplanes that have had a certain modification embodied during production or in-service. This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to detect and correct such check valve loosening, which could result in hydraulic leaks, possibly leading to the loss of all three hydraulic systems and consequent loss of control of the airplane.
2007-09-01: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 182 series airplanes that are equipped with Air Plains Services Corporation Supplemental Type Certificate (STC) SA00152WI. This AD requires you to disconnect or remove the electrical cable between the forward ground power relay and the starter relay, install a placard, inspect the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump for chafing, and replace the fuel line if chafing is found. This AD results from a report of an in-flight and post-landing engine compartment fire. We are issuing this AD to detect and correct interference between the ground power electrical cable, the fuel strainer cable, and the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump. This condition could lead to a fire in the engine compartment.
2021-26-24: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. (type certificate previously held by Agusta S.p.A.) Model A109A and A109A II helicopters. This AD was prompted by a report of internal corrosion on a main rotor (M/R) blade. This AD requires repetitively inspecting affected M/R blades and accomplishing film analysis and repair in accordance with certain approved methods. The FAA is issuing this AD to address the unsafe condition on these products.
75-20-06: 75-20-06 BELLANCA: Amendment 39-2372. Applies to Model 17-30, 17-30A (S/N 30263 through S/N 76-30811), 17-31, 17-31TC, 17-31ATC (S/N 30004, S/N 31004 through S/N 76-31124), 14-19-3A, and 17-31A (S/N 32-15 through S/N 76-32-163) airplanes certificated in all categories. Compliance required upon accumulation of 300 hours time in service or within the next 25 hours time in service from the effective date of this Airworthiness Directive (whichever occurs later) unless already accomplished, and thereafter at intervals not to exceed 100 hours time in service from the last inspection until Bellanca Kit SK1234789-0004 is accomplished. To detect cracks in either vertical side fuselage tube (F. S. 7), which is adjacent to the horizontal stabilizer carry-through, in the area near the upper fuselage longeron, accomplish the following: A. Inspect the vertical tube for circumferential cracks at the upper weld, and between the upper weld and the horizontal stabilizer carry-throughtube, all around the tube. B. If cracks are found, repair and modify in accordance with Bellanca Kit SK1234789-0004 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region, before further flight, except that the airplane may be flown, in accordance with FAR 21.197, to a base where the repair can be performed. C. If no cracks are found, no further action is required until the next inspection. Bellanca Service Letter No. 85 or 85A pertains to this same subject. This amendment becomes effective September 26, 1975.
2007-08-09: We are adopting a new airworthiness directive (AD) for the products listed above. 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: An analysis of the cable operated control system installed on the SD3 aircraft types that use MS 21260 type end fittings has identified a number of potentially unsafe conditions due to a combination of failures * * *. The failure of certain control cables could result in the loss of certain critical systems. For example, the loss of the low pressure (LP) fuel control cable in combination with a single failure of a fuel condition control cable on the same engine can cause the loss of the capability to shut down the engine in the event of an engine fire. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
97-10-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires repetitively inspecting the main landing gear (MLG) pintle to cylinder interface area for cracks, and replacing any MLG cylinder where a crack of any length is found in the MLG pintle to cylinder interface area. This AD results from reports of MLG cracks in the area of the pintle to cylinder interface on three of the affected airplanes. The actions specified by this AD are intended to prevent failure of the MLG caused by cracks in the pintle to cylinder interface area, which could result in loss of control of the airplane during landing operations.
2007-05-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007-05-51, which was sent previously to all known U.S. owners and operators of MDHI Model MD600N helicopters by individual letters. This AD requires, before further flight, a visual and eddy current inspection of each lateral mixer output link assembly (mixer link) and replacing any cracked mixer link. This AD also requires performing an eddy current inspection on each mixer link before installing it on any helicopter. This amendment is prompted by the discovery of 3 cracked mixer links. The actions specified by this AD are intended to detect a crack in the mixer link, which could result in failure of the mixer link and subsequent loss of control of the helicopter. \n\nDATES: Effective May 7, 2007, to all persons except those persons to whom it was made immediately effective by Emergency AD 2007-05-51, issued on February 17, 2007, which contained the requirements of this amendment. \n\n\tComments for inclusion in the Rules Docket must be received on or before June 19, 2007.