Results
2006-06-01: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires inspecting an electrical cable bundle for wear. If wear is present, the AD requires installing an airworthy cable bundle and modifying the routing of the electrical cable bundles. This amendment is prompted by reports of a short circuit in the wiring, which led to failure of the normal and emergency landing gear operation modes. The actions specified by this AD are intended to prevent interference of the wiring with the structure resulting in an electrical short circuit, failure of the landing gear to extend, and an emergency landing.
79-04-02: 79-04-02 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39-3407 as amended by Amendment 39-3434. Applies to Model A109A helicopters, certificated in all categories, serial numbers 7135 and below. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible failure of the tailboom attachment provisions, remove and discard the nuts MS 21042-L6, the bolts NAS 626-20, and washers MS 20002-C6 and AN 960-616, and install in their place new nuts 42-FLW-624, bolts NAS 626-20, washers MS 20002-C6 and, as needed, one or more washers AN 960-616 and AN 960-616L, torque bolts, inspect bolts for torque, and if necessary retorque and re-inspect torque, all in accordance with Agusta Bollettino Tecnico No. 109-8, dated February 6, 1978, or an FAA-approved equivalent approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667. Amendment 39-3407 became effective March 5, 1979. This amendment 39-3434 became effective March 5, 1979.
2006-05-11: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the aircraft maintenance manual (AMM) by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units. This AD requires new repetitive functional tests of the pilot input lever of the PFS unit, and corrective actions if necessary. After initiating the new tests, this AD also requires removal of the existing procedures for the repetitive functional tests from the AMM. This AD results from a report that the shear pin located in the input lever of two PFS units failed due to fatigue. We are issuing this AD to prevent undetected failure of the shear pin of both PFS units simultaneously, which could result in loss of pitch feel forcesand consequent reduced control of the airplane. DATES: This AD becomes effective March 27, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 27, 2006. On February 13, 2004 (69 FR 4234, January 29, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Temporary Revision 2B-1784, dated October 24, 2003, to the CL-600-2B19 Canadair Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, "Airworthiness Limitations.'' We must receive any comments on this AD by May 9, 2006.
99-14-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-300 and -400 series airplanes. This action requires repetitive inspections of the E-42 satellite communications (SATCOM) rack and fuselage (supporting) structure to detect cracking in the area surrounding the fastener holes, and to detect broken and missing fasteners; and corrective actions, if necessary. This amendment is prompted by reports indicating that cracking and broken and/or missing fasteners were found on the E-42 SATCOM equipment rack structure that attaches to the fuselage structure. The actions specified in this AD are intended to detect and repair cracking of the E-42 SATCOM rack and its supporting structure, which could result in the SATCOM equipment falling from the rack, loss of SATCOM capabilities, injury to passengers, and reduced controllability of the airplane.
2020-02-21: The FAA is superseding Airworthiness Directive (AD) 2018-19-25 and AD 2014-03-12, which applied to all Dassault Aviation Model FALCON 2000 airplanes. Those ADs required revising the existing maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. Since the FAA issued AD 2018-19-25, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require those maintenance or inspection program revisions, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2001-24-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Fokker Model F.28 Mark 0100 series airplanes. This action requires repetitive inspections of certain main landing gear (MLG) main fittings to detect forging defects, and rework of the main fittings if necessary. This action is necessary to detect forging defects of the MLG main fittings, which could lead to cracking and result in significant structural damage to the airplane and possible injury to the occupants.
2020-02-16: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lower skin of the fuselage skin lap splices along the lower fastener row of a certain stringer lap splice on certain body station skin panels may be subject to widespread fatigue damage (WFD). This AD requires inspections of the lower skin of the fuselage skin lap splices along the lower fastener row of a certain stringer lap splice on certain body station skin panels and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2020-03-11: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This AD was prompted by the FAA's analysis of the Model 707 and 720 fuel system reviews conducted by the manufacturer. This AD requires modifying the fuel quantity indicating system (FQIS) to prevent development of an ignition source inside the center fuel tank due to electrical fault conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2020-02-11: The FAA is superseding Airworthiness Directive (AD) 2015-04-04 for Bell Helicopter Textron Inc. (Bell) Model 412 and 412EP helicopters. AD 2015-04-04 required revising the Rotorcraft Flight Manual (RFM) for your helicopter and installing a placard to limit flights to visual flight rules (VFR) and prohibit night operations because of failing inverters. This AD requires replacing the affected inverter with a new inverter. This AD was prompted by numerous failures of inverters. The FAA is issuing this AD to address the unsafe condition on these products.
2001-24-07: This amendment supersedes an existing airworthiness directive (AD) that applies to Agusta S.p.A. (Agusta) Model A109C, A109E, and A109K2 helicopters and currently requires inspecting the main rotor blade (blade) tip cap for bonding separation and a crack. This amendment contains the same requirements as the existing AD but also requires a tap inspection of the tip cap for bonding separation in the blade bond area and a dye penetrant inspection of the tip cap leading edge along the welded joint line of the upper and lower tip cap skin shells for a crack. This amendment is prompted by three occurrences in which the blade tip cap leading edge opened in flight due to cracks, resulting in excessive helicopter vibration. The actions specified by this AD are intended to prevent failure of a blade tip cap, excessive vibration, and subsequent loss of control of the helicopter.