Results
2005-01-17: The FAA adopts a new airworthiness directive (AD) to supersede AD 98-03-14, which applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Model EA-300 and EA-300/S airplanes. AD 98-03-14 currently requires you to inspect the upper longeron cutout-bridge for cracks, to repair any cracks found, and to modify this area. This AD retains the actions of AD 98-03-14 and incorporates new service information. For owner/ operators of the affected airplanes that were able to do the modification required in AD 98-03-14, no further action is required. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct cracks in the upper longeron cutout-bridge, which could cause the upper longeron cutout-bridge to fail resulting in structural damage to the fuselage. This condition could lead to loss of control of the airplane. DATES: This AD becomes effective on February 28, 2005. On March 16, 1998 (63 FR 5881, February 5, 1998), the Director of the Federal Register approved the incorporation by reference of EXTRA Flugzeugbau GmbH Service Bulletin EA-300 & EA-300/S Doc: SB-300-3-93, Issue: A, Date: January 12, 1994. As of February 28, 2005, the Director of the Federal Register approved the incorporation by reference of EXTRA Flugzeugbau GmbH Service Bulletin EA-300 & EA-300/S Doc: SB-300-3-93, Issue: B, Date: June 10, 1998.
2023-12-21: The FAA is superseding Airworthiness Directive (AD) 2021-26- 13, which applied to all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000- J2, Trent 1000-K2, and Trent 1000-L2 engines. AD 2021-26-13 required revision of the engine Time Limits Manual (TLM) life limits of certain critical rotating parts and direct accumulation counting (DAC) data files. Since the FAA issued AD 2021-26-13, RRD has revised the TLM with more restrictive airworthiness limitations, including updated life limits for certain critical parts and updated DAC data files. This AD was prompted by the manufacturer revising the engine TLM life limits of certain critical rotating parts, updating the DAC data files, and updating certain maintenance tasks. This AD requires revising the existing approved maintenance or inspection program, as applicable, to incorporate more restrictive airworthiness limitations, 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.
79-16-06: 79-16-06 DETROIT DIESEL ALLISON: Amendment 39-3527 is further amended by Amendment 39- 3650. Applies to all Model 250-C28 and 250-C30 series engines equipped with generator idler gearshaft P/N 6898980, or 6898591, or 77 tooth spur idler gearshaft P/N 6898652 installed in, but not limited to Bell 206L-1 and Sikorsky S-76 rotorcraft certificated in all categories. Compliance required as indicated unless previously accomplished. To preclude engine power loss as a result of an accessory drive gearbox failure, remove the referenced gearshafts from service prior to reaching 9000 cycles if installed in a 250-C28 series engine and prior to reaching 2000 cycles if installed in a 250-C30 engine. For those gearshafts that are within 50 cycles of the appropriate limit on the effective date of this AD, compliance is required within 100 cycles. For the purpose of this AD, a cycle is defined as an attempted or completed start, or a motoring of the engine using the starter. The start counter is activated and accumulates the count of cycles only when the ignition circuit is energized. Therefore, cycles due to motoring with the starter (ignition circuit not energized) must be added to the cycle count. (Detroit Diesel Allison Commercial Engine Bulletins CEB 72-2003 for the 250-C28B and CEB 72-3003 for the 250-C30 also pertain to this subject.) Amendment 39-3527 became effective August 15, 1979. This amendment 39-3650 becomes effective January 11, 1980.
97-03-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires modification and sealing of the firezone compartment of the nacelle of the left and right engines. This amendment is prompted by reports indicating that firezone compartments have not been completely sealed. The actions specified by this AD are intended to prevent flame, fuel, and vapor from entering compartments behind the firezone compartment. This condition, if not corrected, and if combined with a fire source in the firezone compartment, could result in an uncontrollable fire outside the firezone compartment.
2005-02-01: The FAA is adopting a new airworthiness directive (AD) for certain The Lancair Company (Lancair) Models LC40-550FG and LC42-550FG airplanes. This AD requires you to incorporate additional takeoff chart distance values information into the Performance Section of the FAA- approved Airplane Flight Manual (AFM). This AD results from flight testing that revealed that the takeoff distance values for the affected airplanes could not be duplicated. We are issuing this AD to prevent potential impact with terrain or obstruction during takeoff due to incorrect takeoff distance values.
2023-12-23: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-300F airplanes. This AD was prompted by a report indicating that the installation requirements were not followed for the first observer seat in the flight deck. This AD requires installing placards in various locations of the flight deck to indicate the proper position for the first observer seat during taxi, takeoff, and landing, and revising the existing airplane flight manual (AFM). The FAA is issuing this AD to address the unsafe condition on these products.
62-18-01: 62-18-01 GENERAL DYNAMICS/CONVAIR: Amdt. 475 Part 507 Federal Register August 18, 1962. Applies to All Models 22, 22M, and 30 Series Aircraft. Compliance required within 150 hours' time in service following the effective date of this AD, unless already accomplished. To prevent loose rudder flight tab balance weights, the following shall be accomplished: Inspect the rudder flight tab balance weight attachments for looseness of the balance weight, missing weights, missing attachment nuts and/or bolts, and for elongation of the attachment bolt holes in the balance weights and attachment arms in accordance with General Dynamics/Convair Alert Service Bulletins A27-60, A27-31, or A27-32, as appropriate. If any of the noted defects are found, they shall be corrected prior to the next flight, as specified in General Dynamics/Convair Alert Service Bulletins A27-60, A27-31, or A27-32, as appropriate, or by an FAA engineering approved equivalent method. (General Dynamics/Convair Alert Service Bulletins A27-60, A27-31, and A27-32 for the Models 22, 22M, and 30 respectively cover this same subject.) This directive effective August 18, 1962.
2023-13-14: The FAA is superseding Airworthiness Directive (AD) 2023-01- 12, which applied to all Safran Helicopter Engines, S.A. (Safran) Model Arriel 1C, Arriel 1C1, and Arriel 1C2 engines. AD 2023-01-12 required replacing affected fire detectors and prohibited installation of affected fire detectors. Since the FAA issued AD 2023-01-12, the FAA has determined that Model Arriel 1K1 engines are also affected by the unsafe condition. This AD is prompted by reports of false engine fire warnings. This AD requires replacing the affected fire detectors, prohibits installation of affected fire detectors, and adds Model Arriel 1K1 engines to the applicability, as specified in an 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.
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.