Results
2005-01-15: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan engines with certain part number (P/N) low pressure compressor (LPC) fan blades installed. That AD currently requires initial and repetitive ultrasonic inspections of the fan blade dovetail roots. This AD requires the same actions except at reduced compliance times for certain blades, defines a specific terminating action to the repetitive blade inspection requirements, and adds the 884B series to the applicability. This AD results from a report of a cracked fan blade found before the blade reached the initial inspection threshold of AD 2002-11-08. This AD also results from the need to reduce a repetitive inspection compliance time due to potential breakdown of blade coating and lubrication on certain blades. We are issuing this AD to prevent multiple LPC fan blade failures due to cracks, which could result in uncontained enginefailure and possible damage to the airplane.
80-19-03: 80-19-03 PRATT & WHITNEY AIRCRAFT: Amendment 39-3911. Applies to all Pratt & Whitney Aircraft JT3D-1-MC7 turbofan engine models. Compliance required not later than December 31, 1980. To preclude high cycle fatigue cracking of fifth stage compressor disks which could result in disk fracture, retire from service all fifth stage compressor disks, P/N 426505, and replace with either disk P/N 697105 or P/N 749605. Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch, New England Region, may adjust the compliance date. A historical file on this AD is maintained in full by the FAA at its headquarters in Washington, D.C., and at the New England Region. This amendment becomes effective October 7, 1980.
2023-12-08: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 series airplanes. This AD was prompted by a report of stress corrosion cracking in certain stringers and end stringer splice assemblies. This AD requires repetitive inspections of the stringers and end stringer splice assemblies for any crack, shim, or gap, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2000-10-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-10-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 767 series airplanes by individual notices. This AD requires a one-time inspection to determine whether certain bolts are installed in the side load underwing fittings on both struts, and various follow-on actions, if necessary. This action is prompted by a report that two fractured bolts and one cracked bolt were found in the side load underwing fittings. The actions specified by this AD are intended to detect and correct cracking or fracturing of the tension bolts on the side load underwing fittings on the strut, which would eventually result in loss of the strut.
83-11-02: 83-11-02 BOEING: Amendment 39-4659. Applies to those Model 747 series airplanes certificated in all categories listed in Service Bulletin 747-53-2224, Revision 3, or later FAA approved revisions. To prevent failure of the floor beams and webs, accomplish the following: \n\n\tA.\tVisually inspect, or as an alternate, inspect using eddy current inspection techniques, the longitudinal floor beams in the areas noted in the appropriate table of Section III of Boeing Service Bulletin 747-53-2224, Revision 3, or later FAA approved revisions, unless previously accomplished. The inspections are to commence prior to the accumulation of one-half the number of cycles specified in the "Repeat Inspection Interval Cycles" column in the appropriate table in Section III of the service bulletin after the effective date of this AD for airplanes which have accumulated more than the number of cycles listed in the "Inspection Threshold Cycles" column of the table, or prior to accumulating the inspectionthreshold number of cycles, whichever is later. Inspections are to be repeated at intervals not to exceed those specified in the table. \n\n\tB.\tWebs or chords found cracked are to be repaired or replaced prior to further flight in accordance with the instructions of Section III of Boeing Service Bulletin 747-53-2224, Revision 3, or later FAA approved revisions, or repair of damaged structure may be deferred as noted therein. \n\n\tC.\tComplete modification of the floor beam webs and chords in accordance with the terminating action procedures described in Boeing Service Bulletins 747-53-2224, Revision 3; 747-53-2176, Revision 4; and 747-53-2183, Revision 2; or later FAA approved revisions, constitutes terminating action for this AD. \n\n\tD.\tAfter accomplishing each inspection, repairs, or the terminating modification, apply organic corrosion inhibitor (BMS 3-23) or equal to all exposed floor beams and pressure web structures as required. \n\n\tE.\tFor purposes of complying with this AD, subject to acceptance by the assigned FAA Principal Maintenance Inspector, the number of landings may be determined by dividing each airplane's hours time in service by the operator's fleet average from takeoff to landing for the airplane type. Only pressurized flights need be considered when establishing number of landings on the airplane. \n\n\tF.\tUpon request of the operator, a FAA Principal Maintenance Inspector, subject to prior approval by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the inspection interval, if the request contains substantiating data to justify the increase for that operator. \n\n\tG.\tSpecial flight permits may be issued in accordance with Section 21.197 and 21.199 of the Federal Aviation Regulations to operate airplanes to a base for the accomplishment of the inspections and/or modifications required by the AD. \n\n\tH.\tAlternate means of compliance or other actions which provide an equivalent level of safety may beused when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tI.\tThis amendment supersedes Airworthiness Directive (AD) 81-13-03, Amendment 39-4138 (46 FR 31873), as amended by Amendment 39-4485 (47 FR 49957). \n\n\tAll persons affected by this directive who have not already received the appropriate service bulletins from the manufacturer may obtain copies upon request to The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. These documents also may be examined at FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective June 20, 1983.
2000-11-26: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes, that requires repetitive ultrasonic inspections to detect corrosion of the retraction links of the main landing gear (MLG), and replacement of the retraction link with a new retraction link, if necessary. 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 detect and correct corrosion of the retraction link of the MLG, which could result in reduced structural integrity and possible collapse of the MLG.
2023-13-07: The FAA is adopting a new airworthiness directive (AD) for certain Saab AB, Support and Services Model SAAB 340B airplanes. This AD was prompted by a determination that the affected airplanes must not be operated at a maximum take-off weight (MTOW) above 29,000 pounds. This AD requires amending the applicable airplane flight manual (AFM) by incorporating a temporary revision (TR) to reduce the MTOW, 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.
2000-11-27: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319, A320, and A321 series airplanes. This action requires a one-time ultrasonic inspection to detect disbonding of the skin attachments at the stringers and spars of the vertical stabilizer, and repair, if necessary. This action is necessary to detect and correct disbonding of the vertical stabilizer structure, which could result in reduced structural integrity of the spar boxes of the vertical stabilizer.
2005-01-14: The FAA is superseding an existing airworthiness directive (AD) for Bombardier-Rotax GmbH Type 912 F, 912 S, and 914 F series reciprocating engines. That AD currently requires venting of the lubrication system and inspection of the valve train on all engines. That AD also requires venting of the lubrication system of all engines on which the lubrication system has been opened, and any engine on which the propeller has been rotated one full turn in the wrong direction. This AD requires similar actions, and also requires removing the existing part number oil dipstick from service and installing a new oil dipstick. This AD results from the need to clarify the mandated procedures for inspections and venting. This AD also results from the manufacturer discovering that under certain circumstances, the oil level in the oil tank can fall below the minimum level required to sustain proper engine lubrication. We are issuing this AD to prevent damage to the engine valve train due to inadequate venting of the lubrication system, which can result in an in-flight engine failure and forced landing.
2005-01-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200, -200PF, and -200CB series airplanes, that requires an inspection of certain ballscrews of the trailing edge flap system to find their part numbers, and replacement of the ballscrews with new, serviceable, or modified ballscrews if necessary. This action is necessary to prevent a flap skew due to insufficient secondary load path of the ballscrew of the trailing edge flaps in the event that the primary load path fails, which could result in possible loss of a flap and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2014-17-10: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD requires repetitive on-ground power cycles (resets) of the Transponder, Terrain and Traffic Collision Avoidance System (T3CAS). This AD was prompted by reports of spurious terrain ahead warning system (TAWS) alerts during approach and takeoff. We are issuing this AD to prevent spurious TAWS alerts, which could increase flightcrew workload during critical landing or takeoff phases, and result in reduced control of the airplane.
97-03-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that currently requires, among other things, repetitive visual inspections to detect discrepancies of the fuel pipe of the fuel transfer system of the tail tank and associated mounting bracket located in the aft fuselage compartment. That AD was prompted by reports of cracking or bending of the fuel pipe mounting support and/or attaching bracket in the aft fuselage compartment due to a fuel pressure surge that caused repetitive loading of this area. This amendment adds a requirement to install a restraint on the tail tank fuel pipe, which would terminate the repetitive visual inspections. The actions specified by this AD are intended to prevent such cracking/bending, which could expose the fuel pipe coupling O-ring. An exposed O-ring could lose its sealing effect and could allow a fuel leak in the aft fuselage compartment, which would present a fire hazard.
63-22-04: 63-22-04 PIAGGIO: Amdt. 635 Part 507 Federal Register October 30, 1963. Applies to All Model P.166 Aircraft. Compliance required within 50 hours' time in service after the effective date of this AD. As a result of failures of the main landing gear shock absorber the following modifications must be accomplished in the manner specified in Piaggio Service Bulletin 166- 25A. (a) Install Teflon sealing gasket P/N 4/22015.52 on inner ring nut of shock absorber casing. (b) Replace light alloy piston bottom with steel P/N 4/22015.55. (c) Replace the present ring nut with P/N 4/22015.56. (d) Shock absorbers modified as specified herein shall have a letter "D" placed on the nameplate. (e) Shock absorbers modified as specified herein shall be overhauled every 1,200 hours' time in service or every 2 years, whichever occurs first. This directive effective December 2, 1963
2005-01-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 series airplanes. This AD requires a one-time inspection for discrepancies of the frame web and inner chords on the forward edge frame of the number 5 main entry door cutout, and related corrective action. This AD is prompted by a report of cracking of the frame web and inner chords on the forward edge frame of the number 5 main entry door. We are issuing this AD to find and fix discrepancies of the frame web and inner chords, which could result in cracking, subsequent severing of the frame, and consequent rapid depressurization of the airplane.
80-17-07: 80-17-07 SIKORSKY AIRCRAFT: Amendment 39-3877. Applies to S-61 series helicopters certificated in all categories, including military counterparts. Compliance required as indicated. To prevent fatigue failures of the horizontal hinge pins: Replace the Rotary Wing Horizontal Hinge Pin P/N S6110-23020 and S6110-23320 prior to 4000 and 5300 hours time in service, respectively, or within 25 hours time in service after the effective date of this AD, whichever occurs later. This amendment is effective August 15, 1980.
97-03-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300 series airplanes, that requires an inspection to detect fatigue cracking, base trim, and upper flange over-trim of the pulley brackets of the aileron control cables. This amendment also requires, if necessary, replacement of the pulley brackets with new pulley brackets, and replacement of the two button-head rivets with flush-head rivets. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent fatigue cracking or fracturing of the pulley brackets, which could result in slack in the cables and consequent reduced ability of the flightcrew to control the aileron.
62-03-01: 62-03-01 HILLER: Amdt. 395 Part 507 Federal Register January 30, 1962. Applies to All UH-12A and UH-12B Helicopters. Compliance required within the next 150 hours' time in service after the effective date of this AD. To preclude additional failures of the tail rotor drive slip joints which can result in loss of power to the tail rotor, replace CR-10 or CR-10T type rollers of both fore and aft slip joints UH-12A Assembly Nos. 24500-9 and -10 and UH-12B Assembly Nos. 24565 and 24544, with the improved Torrington CR-10U type rollers. (Hiller Service Bulletin No. 44, Revision A covers this same subject.) This supersedes AD 55-08-03. This directive effective January 30, 1962.
83-14-01: 83-14-01 SHORT BROTHERS LTD.: Amendment 39-4681. Applies to SC7 Skyvan Series 3 airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the flaps, accomplish the following: (a) For all affected aircraft, except SNs SH1845 and SH1883, within the next 50 flights after the effective date of this AD or upon accumulating 7,000 flights, whichever occurs later, and thereafter at each subsequent 7,000 flights: (1) Inspect the inboard flap outer hinge arm and operating arm attachment ribs and replace the outer hinge arm in accordance with Part 1 of the Accomplishment Instructions Section of Short Brothers Service Bulletin No. 57-A61, Rev. 5, dated October 28, 1980, or an FAA approved equivalent. (b) Within the next 250 flights after the effective date of this AD or upon accumulating 7,000 flights, whichever occurs later: (1) Modify the outboard flap attachment ribs at the inboard hinge arm and operating arm in accordance with Part 1 of the Accomplishment Instructions Section of Short Brothers Service Bulletin No. 57-62, Rev. 1, dated September 9, 1980, or an FAA approved equivalent. (c) For S/Ns SH1845 and SH1883 only: (1) Accomplish the initial inspection and outer hinge arm replacement described in paragraph (a) (1) of this AD within the next 250 flights after the effective date of this AD. (2) Accomplish the modification described in paragraph (b)(1) of this AD within the next 250 flights after the effective date of this AD. (d) For all affected aircraft, including S/Ns SH1845 and SH1883, replace the outboard flap inner hinge arm, P/N SC7-25-39, operating arm, P/N SC7-25-107/8, inboard flap inner hinge arm, P/N SC7-25-39, operating arm P/N SC7-25-109/110, and their associated attachment ribs at 20,000 flights or 18,000 flights, as defined by Short Brothers Life Extension Service Bulletin No. 51-51, Rev. 1, dated October 19, 1978, in accordance with Short Brothers ServiceBulletin No. 57-A61, Rev. 5, dated October 28, 1980, or an FAA approved equivalent. (e) For purposes of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of flights may be determined by multiplying each airplane's hours time-in-service by 2. (f) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on August 19, 1983.
2005-01-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100 and -200B series airplanes. This AD requires installing bonding clips and bonding jumpers from the housing of each fuel pump to airplane structure outside the fuel tanks. This AD is prompted by the results of fuel system reviews conducted by the manufacturer. We are issuing this AD to ensure adequate electrical bonding between the housing of each fuel pump and airplane structure outside the fuel tanks. Inadequate electrical bonding, in the event of a lightning strike or pump electrical fault, could cause electrical arcing and ignition of fuel vapor in the wing fuel tank, which could result in a fuel tank explosion.
2000-11-22: This amendment adopts a new airworthiness directive (AD), applicable to Allison Engine Company AE 3007A and AE 3007C series turbofan engines. This AD requires revisions to the Airworthiness Limitations Section of the Allison Engine Company AE 3007A and AE 3007C Engine Manuals to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD also requires an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. Air carriers with an approved continuous airworthiness maintenance program will be allowed to either maintain the records showing the current status of the inspections using the record keeping system specified in the air carrier's maintenance manual or establish an acceptable alternate method of record keeping. This amendment is prompted by an FAA study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that, if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2023-12-04: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. This AD was prompted by a report that an incorrect wiring arrangement was detected around the weather radar system. This AD requires modifying the weather radar redundant wiring, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2023-12-02: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
97-02-13: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JFTD12A series and T73 series turboshaft engines, that requires initial and repetitive fluorescent penetrant inspections (FPI) of compressor hubs, disks, spacers, and bolted on (rotating) airseals for cracks, and replacement, if necessary, with serviceable parts. This amendment is prompted by reports of extensive compressor rotor part cracking. The actions specified by this AD are intended to prevent disk rupture, an uncontained engine failure, and possible damage to the aircraft.
80-02-05: 80-02-05 ROLLS ROYCE LIMITED: Amendment 39-3655. Applies to Viper MK 601-22 model engine as installed in, but not limited to, Hawker Siddeley HS 125 series 600A and Beechcraft Hawker Siddeley BH 125 series 600A aircraft. Compliance is required as indicated unless already accomplished. To prevent possible failure of the flexible fuel hose, accomplish the following: (a) Within 250 hours engine time in service after the effective date of this AD, remove the flexible fuel hose assembly, Rolls Royce P/N DX 33-180-300 and install a new flexible fuel hose assembly, Rolls Royce P/N V 103813, in accordance with paragraph 2.A., "Accomplishment Instructions," of Rolls Royce Service Bulletin No. 73-A17, dated June 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Region, Brussels, Belgium. (b) Upon request of an operator, an FAA Maintenance Inspector may adjust the compliance time specified in paragraph (a) of this ADto be compatible with that operator's maintenance schedule. This amendment becomes effective January 24, 1980.
2005-01-11: The FAA adopts a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to check the airplane logbook to determine whether any main landing gear (MLG) actuator (part number (P/N) 960.30.01.103) with serial numbers (SNs) 830E through 881E is installed. If any MLG actuator with one of these SNs is installed, you are required to replace the MLG actuator with a P/N 960.30.01.103 actuator that has a SN other than 830E through 881E. The pilot is allowed to do the logbook check. If the pilot can positively determine that no MLG actuator with one of these SNs is installed, then no further action is required. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to prevent failure of the MLG actuator caused by an incorrect heat treating process, which could result in loss of hydraulic extension/retraction of the MLG. This failure could lead to loss of control during ground operations.