Results
85-05-01: 85-05-01 PIPER: Amendment 39-5011. Applies to Model PA-31P (Serial Numbers 31P-3 through 31P-7730012) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent the propagation of cracks in the fuselage bulkhead at station 332.0, and loss of stabilizer front spar structural support, accomplish paragraph (a) as follows: (a) Within the next 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not exceeding 200 hours time-in-service, inspect, using a dye-penetrant method, the fuselage station 332.0 bulkhead in accordance with Piper S/B No. 802 dated December 12, 1984. (1) If no cracks are found to exist, make appropriate maintenance record entry of compliance. (2) If cracks are found that do not exceed the acceptable limitations given in Piper S/B No. 802, prior to further flight stop drill the crack(s), and install Reinforcement Kit, Piper Part Number 764-983, orreinforced bulkhead assembly, Piper Part Number 45583-16. (3) If cracks are found that exceed the acceptable limitations given in Piper S/B No. 802, prior to further flight replace the bulkhead assembly with Reinforced Bulkhead Assembly, Piper Part Number 45583-16. (b) The repetitive inspections required by paragraph (a) of this AD may be discontinued when Reinforcement Kit Piper Part Number 764-983, or Replacement Bulkhead Piper Part No. 45583-16 is installed. (c) The intervals between repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (d) The airplanes may be flown, in accordance with FAR 21.197 to a location where the AD may be accomplished. (e) An equivalent method of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, Central Region, 1075 Inner Loop Road, College Park, Georgia 30337; Telephone (404) 763-7428. This amendment becomes effective on March 15, 1985.
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.
82-06-11 R1: 82-06-11 R1 PIPER AIRCRAFT CORPORATION: Amendment 39-4349 as amended by Amendment 39-4408. Applies to the following airplanes certificated in any category. Nose Landing Gear Inspection and Rigging (Part I of Service Bulletin) MODELS AFFECTED: SERIAL NUMBERS AFFECTED: PA-28R-201T Turbo Arrow III 28R-7703001 through 28R-7803373 PA-28RT-201T Turbo Arrow IV 28R-7931001 through 28R-8131193 Nose Landing Gear Inspection and Modification (Part II of Service Bulletin) MODELS AFFECTED: SERIAL NUMBERS AFFECTED: PA-28R-200 Arrow II 28R-7635522 through 28R-7635545 PA-28R-201 Arrow III 28R-7737001 through 28R-7837317 PA-28RT-201 Arrow IV 28R-7918001 through 28R-8118082 COMPLIANCE: Required as indicated, unless already accomplished. To prevent the inadvertent retraction of the nose landing gear, accomplish the following: A) Within the next 100 hours time-in-service after the effective date of this AD, inspect, rig and modify the nose landing gear in accordance with Piper Service Bulletin No. 724A, dated April 20, 1982, Parts I and II as applicable, except dye penetrant must be used for detection of cracks. B) Record compliance with this AD by an appropriate entry in the airplane maintenance records. This includes those airplanes where the provisions of this AD have already been accomplished. C) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. D) An equivalent method of compliance may be used when approved by the Chief, Aircraft Certification Field Office, FAA, 3400 Norman Berry Drive, East Point, Georgia 30344. Amendment 39-4349 became effective on March 25, 1982. This amendment 39-4408 becomes effective on June 16, 1982.
2007-19-02: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD-11, MD-11F, DC-10-30 and DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, and MD-10-30F airplanes. This AD requires measuring the electrical resistance of the bond between the No. 2 fuel transfer pump adapter surface of the fuel tank and the fuel transfer pump housing flange, and performing corrective and other specified actions as applicable. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent inadequate bonding between the No. 2 fuel transfer pump adapter surface of the fuel tank and the fuel transfer pump housing flange. Inadequate bonding could result in a potential ignition source inside the fuel tank if the fuel transfer pump and structure interface are not submerged in fuel, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2001-07-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Cessna Model 750 airplanes, that requires removal of a certain existing bulkhead web doubler, installation of left and right bulkhead web doublers, and enlargement of the lightening holes. This action is necessary to prevent jamming of the roll control system, due to inadequate clearance between the control cable and the web, which could result in reduced controllability of the airplane.
2013-07-03: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 airplanes and Model A340- 642 airplanes. This AD was prompted by reports of cracks in the bogie pivot pin caused by material heating due to friction between the bogie pivot pin and bush, leading to chrome detachment and chrome dragging on the bogie pivot pin. This AD requires repetitive detailed inspections for degradation of the bogie pivot pins and for any cracks and damage of the pivot pin bushes of the main and central landing gear; a magnetic particle inspection of the affected bogie pivot pins for corrosion and base metal cracks; and repairing or replacing bogie pivot pins and pivot pin bushes, if necessary. We are issuing this AD to detect and correct cracks and damage to the main and central landing gear, which could result in the collapse of the landing gear and adversely affect the airplane's continued safe flight and landing.
82-11-04: 82-11-04 PIPER: Amendment 39-4386. Applies to PA-31T Cheyenne/Cheyenne II (S/Ns 31T-8120036 through 31T-8120042, 31T-8120044 through 31T-8120050, 31T-8120055 and 31T-8120057), PA-31T1 Cheyenne I (S/Ns 31T-8104040 and 31T-8104041, 31T-8104043 through 31T-8104046, 31T-8104048, 31T-8104051, 31T-8104054, 31T-8104055, 31T-8104057 and 31T-8104058) and PA-31T2, Cheyenne II XL (S/Ns 31T-8166001, 31T-8166005 through 31T-8166017, 31T-8166019 through 31T-8166021, 31T-8166030 and 31T-8166031) airplanes certificated in any category. COMPLIANCE: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent possible sticking of the emergency exit window, accomplish the following: a) Modify the emergency exit window by installing Teflon tape on the emergency exit window frame in the seal area in accordance with Piper Aircraft Corporation Service Bulletin No. 733 dated January 25, 1982. b) Airplanes may be flownin accordance with FAR 21.197 to a location where this AD may be accomplished. c) An equivalent method of compliance may be used when approved by the Chief, New York Aircraft Certification Office, FAA, Federal Building, JFK International Airport, Jamaica, New York 11430. This amendment becomes effective on June 3, 1982.
2007-19-01: 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: To prevent the cockpit door windows separating from their frames, * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2019-19-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of cracks within the ring gears of a slat geared rotary actuator (SGRA) resulting from a change in the raw material manufacturing process. This AD requires replacement of affected parts with serviceable parts, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2001-07-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a modification involving nondestructive test inspections of the 34 fastener holes in each rear wing spar, corrective action, if necessary, and cold working of the holes to increase fatigue life of the rear spar web. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking, which could result in fuel leakage and reduced structural integrity of the wings.
82-10-01: 82-10-01 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4373. Applies to Model AS350 and AS355 Series helicopters certificated in all categories that are equipped with tail rotor blades P/N 350A.12.0030.01, 02, 04, or 05 (Airworthiness Docket No. 82-ASW-16). Compliance required before further flight after the effective date of this AD, and thereafter at intervals not to exceed 10 hours' time in service from the last inspection until the tail rotor blades attain 100 hours' or more total time in service since new or since replacement of the stainless steel leading edge strip. To detect bond failure between each tail rotor blade body and the steel leading protective strip, inspect by tapping along the span and over the surface of the leading edge strip with a coin or similar device. Remove the affected tail rotor blade before further flight if a change in sound tone is found that indicates bond failure exceeds 10 percent of the strip bond area. Equivalent means of compliance with this AD must be approved by the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Aerospatiale Telex Service No. 2366 for all Model AS350 and AS355 operations dated February 4, 1982, pertains to this subject.) This amendment becomes effective May 10, 1982.
2007-18-07: 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 aircraft, at the factory, presented some debris in the hydraulic fluid of the steering system. Investigations revealed that some components of the steering system can be responsible for the fluid contamination because of an initial pollution on their manufacturing. If not corrected, a contaminated fluid could cause malfunction and a possible jamming of the steering system. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-07-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time inspection for cracks on the attachment holes of the doorstop fitting on the aft passenger/crew doors; repair, if necessary; and modification of the attachment holes. This action is necessary to detect and prevent fatigue cracking of the attachment holes for doorstop fitting number 5, which could result in reduced structural integrity of the door frames. This action is intended to address the identified unsafe condition.
81-24-01: 81-24-01 PIPER: Amendment 39-4262. Applies to Piper airplane Models PA-36-285 and PA-36-300, S/N 36-7360001 thru 36-8160001, 36-8160003, 36-8160004 and 36-8160009 and PA-36-375, S/N 36-7802001 thru 36-8102004, certificated in all categories. To prevent failure of the rudder control system, and seat and harness cable assemblies, accomplish the following inspection or an approved equivalent. (a) Within the next 15 hours in service after the effective date of this AD, inspect for cracks, using a dye penetrant method, (1) Two Rudder Control Shackles, Piper P/N 486 566 (MS 20115-5), and (2) Two MS 20115-5 shackles on seat and harness cable assemblies, Piper P/N 98193-10 and 98193-9, respectively. (b) Replace all shackles found cracked prior to further flight with new shackles Piper P/N 486 566 or equivalent which have been previously inspected for cracks in accordance with paragraph (a). (c) Equivalent inspections or parts must be approved by the Chief,Engineering and Manufacturing Branch, FAA, Eastern Region. (d) Compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region upon receipt of substantiating data submitted through an FAA Maintenance Inspector. This amendment is effective November 19, 1981.
2018-10-01: We are adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A., Arriel 2E turboshaft engines. This AD was prompted by reports of ruptured front support pins on the accessory gearbox front support. This AD requires replacement of the accessory gearbox front support. We are issuing this AD to address the unsafe condition on these products.
2023-13-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports where the passenger door external handle mechanism was not retrieving its normal, flush position when the door was being closed. This AD requires a one-time cleaning and lubrication of the external door handle mechanism of each affected door, and limits the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.