Results
2007-19-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from Mandatory Continuing Airworthiness Information (MCAI) provided by the aviation authority of France to identify and correct an unsafe condition on SICMA Aero Seat 50XXX Passenger Seats. The MCAI states the following: \n\n\tA release of smoke was experienced in the passenger compartment during flight after an overheating of a reading lights power box of a PN 5039201-4T SICMA seat. An analysis put into evidence that this overheating was caused by a short-circuit produced by the rupture of an electrical power supply component (PN 78147-B). It has been noticed that this power supply is not in compliance with DO 160 environmental standard. \n\n\tThe short-circuiting could result in arcing and consequent smoke or fire. We are proposing this AD to prevent a short-circuit in the power box, which could result in smoke or fire in the airplane cabin.
2004-20-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD requires revising the airplane flight manual to provide procedures for the flightcrew to follow in the event of the loss of all liquid crystal display (LCD) units on airplanes equipped with a certain EIS2 standard of electronic instrument system. This AD is prompted by reports of the brief but total loss of all LCD units during cruise on airplanes equipped with that standard of electronic instrument system. We are issuing this AD to provide procedures to the flightcrew to restore operation of these LCD units and prevent prolonged loss of critical flight information to the flightcrew and the consequent reduced ability of the flightcrew to control the airplane during adverse flight conditions.
84-10-06 R1: 84-10-06 R1 GARRETT TURBINE ENGINE COMPANY (GTEC, formerly AIRESEARCH MANUFACTURING COMPANY OF ARIZONA): Amendment 39-4867 as amended by Amendment 39-4964. Applicable to all series of engine models TPE331-25, -43, -47, -55, -1, -2, -3, -5, -6, -10 (except -10A), and -11 equipped with the following fuel pump assemblies: P/N S/N 868531-7/-8 All. 869151-1/-3/-4/-5 All. 893573-1 through -7 All. 895413-1/-9 All. 897380-1/-2/-3 Series 1 & 2. 897380-4/-5 Series 1, 2, & 3. 897390-1/-2/-3/-4 Series 1 & 2. 897400-1/-2 Series 1 & 2. 897400-4 Series 1. Compliance is required as indicated unless already accomplished. To prevent possible engine failure, accomplish the following: (a) Inspect low-time engine fuel control/pump assembly to determine drive shaft running torque as specified in Section 2.A.(2), "Accomplishment Instructions," of GTEC SB TPE331-73-0121, Revision 2 dated April 18, 1984, or equivalent approved by the Manager, Western Aircraft Certification Office, in accordance with the schedule below: Fuel pump assembly time: since new or since last assembled; or engine total time: since new or since last overhauled; whichever is known to be least, Hours Inspect not later than Less than 200 the next 100 hours in service 200 or more, and less than 1,000 the next 200 hours in service 1,000 or more next fuel pump disassembly NOTE: Engine Logbook Records should indicate if a new or reassembled fuel pump assembly has been installed on the engine since new or returned from overhaul. Remove from further service fuel pump assemblies having unsatisfactory running torque inspection results unless modified as specified in Section 2, "Accomplishment Instructions," in SB TPE331-73-0121, Revision 2, or equivalent approved by the Manager, Western Aircraft Certification Office. Fuel control/pump assemblies having satisfactory inspection results may be continued in service until fuel pump disassembly per Paragraph (b) below. (b) Upon disassembly of fuel pump for any reason, reassemble to an approved parts configuration as specified in Section 2, "Accomplishment Instructions," in SB TPE331-73-0121, Revision 2, or equivalent approved by the Manager, Western Aircraft Certification Office. (c) Special flight permits may be issued in accordance with Federal Aviation Regulation FAR 21.197 and FAR 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. (d) Alternative means of compliance providing an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. (e) Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the compliance schedule specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the adjustment for that operator. (f) The Manager, Western Aircraft Certification Office has found GTEC SB TPE331-73-0121 Revision 3, dated November 5, 1984, to be equivalent to GTEC SB TPE331-73-0121 Revision 2 dated April 18, 1984. This revision only adds the fuel pump assembly P/N. There are no changes in inspections or accomplishment instructions. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Garrett Turbine Engine Company, 111 South 34th St., P.O. Box 5217, Phoenix, Arizona 85010; telephone (602) 231-1000. This document also may be examined at FAA Rules Docket 83-ANE-29, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment supersedes Amendment 39-4840 (49 FR 13487), AD 84-07-08. Amendment 39-4867 became effective May 30, 1984. This Amendment 39-4964 becomes effective on December 26, 1984.
2007-19-15: The FAA is superseding an existing airworthiness directive (AD), which applies to all McDonnell Douglas Model MD-10-10F and MD-10- 30F airplanes, Model MD-11 and MD-11F airplanes, and Model 717-200 airplanes. That AD currently requires a revision to the Limitations section of the airplane flight manual (AFM) to prohibit use of the flight management system (FMS) profile (PROF) mode for descent and/or approach operations unless certain conditions are met. This new AD requires, for certain Model 717-200 airplanes, upgrading the versatile integrated avionics (VIA) digital computer with new system software, which would end the need for the AFM revision. This AD results from a report of two violations of the selected flight control panel (FCP) altitude during FMS PROF descents. We are issuing this AD to prevent, under certain conditions during the FMS PROF descent, the uncommanded descent of an airplane below the selected level-off altitude, which could result in an unacceptable reduction in the separation between the airplane and nearby air traffic or terrain.
2001-07-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, Model MD-88 airplanes, and Model MD-90-30 series airplanes. This action requires a revision to the applicable Airplane Flight Manual (AFM) to provide the flightcrew with the appropriate landing distance and flap positions, if applicable, for wet or icy runways. This AD also provides for an optional terminating action for the applicable AFM revision. This action is necessary to prevent the flightcrew from performing a scheduled landing on a runway of potentially insufficient length due to failure of the weight-on-wheels spoiler lockout mechanism system and possible inactivation of the autospoiler actuator, which could result in the airplane overrunning the end of the runway during landing on a wet or icy runway. This action is intended to address the identified unsafe condition.
2019-20-01: The FAA is superseding Airworthiness Directive (AD) 2018-26- 07, which applied to all Airbus SAS Model A350-941 and -1041 airplanes. AD 2018-26-07 required repetitive greasing of the thrust reverser actuators (TRAs), dispatch restrictions, and maintenance procedure revisions. This AD requires actions specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by the FAA's determination to add a requirement to replace the TRAs, which AD 2018-26-07 specified was not required at the time to provide the opportunity for the public to comment on the merits of that action. The FAA is issuing this AD to address the unsafe condition on these products.
2007-19-06: The FAA is adopting a new airworthiness directive (AD) for GEAE CF6-45A, -45A2, -50A, -50C, -50CA, -50C1, -50C2, -50C2B, -50C2D, - 50C2F, -50C2R, -50E, -50E1, - 50E2, and -50E2B turbofan engines. This AD requires replacing the compressor discharge pressure (CDP) restoring spring assembly on certain main engine controls (MECs) or re-marking MECs that already incorporate GEAE Service Bulletin (SB) No. CF6-50 S/B 73-0119, dated March 21, 2005. This AD results from reports of five events involving fractured CDP restoring spring assemblies. We are issuing this AD to prevent loss of engine thrust control that could lead to loss of control of the airplane.
2007-19-05: The FAA is adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Model 400, 400A, and 400T series airplanes. This AD requires modifying the attachment fasteners on the engine cowling panels. This AD results from several reports of loose attachment fasteners found on the engine cowling panels, and subsequently the panels either peeling back or separating from the airplane during flight. We are issuing this AD to prevent failure of the attachment fasteners on the engine cowling panels, which could result in separation of a panel from the airplane, and consequent damage to airplane structure. These conditions could adversely affect continued safe flight and landing of the airplane, or cause injury to people or damage to property on the ground.
2019-20-07: The FAA is adopting an airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD requires repetitive operational checks of the leading edge (LE) outboard (OB) slats and applicable on-condition actions. This AD also requires revising the airplane flight manual (AFM) to prohibit flap retraction under icing conditions and revising the existing maintenance or inspection program, as applicable, to incorporate a new operation check. This AD was prompted by a determination that the LE OB slat system could be out of position without flight deck annunciation. The FAA is issuing this AD to address the unsafe condition on these products.
2018-09-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes; Model A340-200 series airplanes; and Model A340-300 series airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by reports of cracks on both left-hand (LH) and right-hand (RH) sides on certain frame (FR) locations. We are issuing this AD to address the unsafe condition on these products.