Results
2009-09-06: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive detailed and high frequency eddy current inspections to detect cracks of the backup intercostals and the upper sill of the forward airstair doorway, and applicable corrective actions. This AD also provides for an optional terminating action, which would eliminate the need for repetitive inspections. This AD results from a report indicating that cracks were found in the backup intercostals and upper sill web of the forward airstair doorway. We are issuing this AD to detect and correct fatigue cracking of the backup intercostals and upper sill web of the forward airstair doorway, which could result in a rapid loss of cabin pressure.
2009-09-08: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This AD requires repetitive external surface high frequency eddy current inspections to detect cracks in the radius detail of the upper lobe doubler on both sides of the airplane, and applicable corrective action. This AD results from reports of cracks in the radius detail of the upper lobe doublers. We are issuing this AD to detect and correct cracks in the upper lobe doublers. Such cracks could result in significant degradation of the fuselage structure and reduce its ability to carry flight loads from the vertical stabilizer, which could adversely affect the controllability of the airplane.
2009-06-22: 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 A320 aircraft experienced an event where it was not possible to open the reinforced cockpit door, even after power had been removed from the aircraft. Investigation has identified that the cockpit door latch/striker assembly may have overheated, causing permanent internal damage prior to being electrically isolated by the internal thermal fuse. This condition, in case of a rapid decompression in the cockpit, would prevent the necessary unlocking/ opening of the door, which may lead to failure of the airplane structure. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-09-05: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A318-100 and A319-100 series airplanes; A320-111 airplanes; A320-200 series airplanes; and A321-100 and A321-200 series airplanes. That AD currently requires a one-time inspection of the horizontal hinge pin of the 103VU electrical panel in the avionics compartment to determine if the hinge pin can move out of the hinge, and related investigative and corrective actions if necessary. This new AD instead requires installing a hinge pin stopper on the internal door of the 103VU electrical panel. This AD results from a report indicating that electrical wire damage was found in the 103VU electrical panel due to contact between the hinge pin and the adjacent electrical wire harness. We are issuing this AD to prevent contact between the horizontal hinge pin and the adjacent electrical wire harness, which could result in damage to electrical wires, and consequent arcing and/or failure of associated systems.
2009-09-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Several cases of Gas Generator Turbine (HP Turbine) blade rearward displacement have been detected during borescope inspection or in repair centre following engine disassembly. Two of them resulted in blade rubs between the rear face of the fir-tree roots and the rear bearing support cover. High HP blade rearward displacement can potentially result in blade release due to fatigue of the blade, which would cause an uncommanded in-flight engine shutdown. We are issuing this AD to prevent an uncommanded in-flight engine shutdown which could result in an emergency autorotation landing or, at worst, an accident.
2009-09-01: 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: During a routine inspection on an Airbus A321 aircraft, the operator discovered that a bearing of the flap track No. 1 pendulum assembly had migrated out of position. * * * This condition, if not corrected, could lead to separation of the bearing/flap track assembly, resulting in the detachment of the affected flap surface from the wing and consequent loss of control of the aircraft. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2009-07-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2009-07-52 and supersedes Emergency AD 2009-07-51, issued March 17, 2009, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada Limited (Bell) Model 206A series, 206B series, 206L series, 407, and 427 helicopters by individual letters. This AD requires, before further flight, inspecting each cyclic control lever assembly (lever assembly) that has less than 50 hours time-in-service (TIS) to determine if it is correctly installed and properly staked in the lever assembly. This amendment is prompted by a Transport Canada AD report of a bearing incorrectly installed in the copilot lever assembly. The actions specified by this AD are intended to prevent failure of a bearing, failure of the lever assembly, and subsequent loss of control of the helicopter. DATES: Effective May 1, 2009, to all persons except those persons to whom it was made immediately effective by Emergency AD 2009-07-52, issued on March 19, 2009, which contained the requirements of this amendment. Comments for inclusion in the Rules Docket must be received on or before June 15, 2009.
2009-08-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: A damaged wiring harness which caused the air conditioning system circuit breaker to trip and evidencing a local overheating has been found on an in-service aircraft. The investigation revealed that the damage (chafed wires) found on the wiring harness resulted from an interference with the under- floor attachment fittings of the cabin partition net which was due to an incorrect routing of the harness while on the production line. Such conditions could result in an electrical short and potential loss of several functions essential for the safety of flight. We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-08-06: The FAA is adopting a new airworthiness directive (AD) for GE CF6-80A series turbofan engines with certain stage 1 high-pressure turbine (HPT) rotor disks, installed. This AD requires removal from service of those stage 1 HPT rotor disks within 30 days after the effective date of the AD. This AD results from the FAA learning that those disks are susceptible to cracks developing at the aft chamfer of the blade dovetail slots. We are issuing this AD to prevent cracks developing at the aft chamfer of the blade dovetail slots that could propagate to a failure of the disk and cause an uncontained engine failure and damage to the airplane.
2009-08-07: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. ALF502L-2 and ALF502L-2C turbofan engines with certain high-pressure compressor (HPC) first stage discs installed. This AD requires performing a dimensional inspection to determine if excessive disc balance material was removed and a magnetic particle inspection if the disc passes the dimensional inspection. This AD results from reports of discs found with excessive material removed from the balancing locations of the disc. We are issuing this AD to prevent the discs from fracturing before reaching the currently published life limit. A disc fracture could result in an uncontained failure of the disc and damage to the airplane.