Results
2024-06-51: The FAA is superseding airworthiness directive (AD) 2024-05- 51, which applied to certain General Electric Company (GE) Model CT7- 2E1, CT7-2F1, CT7-8A, CT7-8E, and CT7-8F5 engines, and various restricted category helicopters with GE Model T700-GE-700, -701A, - 701C, -701D/CC, -701D, -401, -401C, CT7-2D, or CT7-2D1 engines installed. AD 2024-05-51 required a phase array ultrasonic inspection of the torque reference tube magnetic insert braze joint of the power turbine (PT) drive shaft assembly for inadequate braze coverage, and repair or replacement of the PT drive shaft assembly if necessary. This AD was prompted by at least four reports of failures of the torque reference tube magnetic insert braze joint of the PT drive shaft assembly within the last several months. This AD retains the requirements of AD 2024-05-51 and expands the applicability to include a PT drive shaft assembly part number that was inadvertently omitted. The FAA previously sent an emergency AD to all known U.S. owners and operators of these engines and helicopters and is now issuing this AD to address the unsafe condition on these products.
98-12-28: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that requires repetitive inspections for cracking in the false spar of the wing, and repair, 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 cracking in the false spar, which could result in reduced structural integrity of the wing.
81-06-51 R1: 81-06-51 R1 BOEING: Amendment 39-4110 as amended by Amendment 39-4445. Applies to Boeing Model 707/720 series airplanes, certificated in all categories, prior to line number 885. To assure continued structural integrity of the outboard wing, accomplish the following within the next 75 hours time-in-service unless accomplished since January 1, 1980: \n\n\t1.\tPerform a one-time visual inspection and repeat visual inspections at intervals not exceeding one year, in accordance with Boeing Service Bulletin A3308, Revision 2, dated July 10, 1981, or later revision approved by the Manager, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. The first repetitive inspection shall be accomplished within a year of the last inspection (AD 81-06-51) or within 90 days after the effective date of this amendment, whichever occurs later. \n\n\t2.\tAfter inspection, spray the area with BMS 3-23 organic corrosion inhibitor or equivalent.\n \n\t3.\tParts found cracked must be repaired in accordance with Boeing Service Bulletin A3308 or replaced prior to further flight except that airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197 and 21.199 with prior approval of the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region.\n\n \t4.\tEquivalent inspections and repairs may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region.\n \n\tThe manufacturers specifications and procedures identified and described in this amendment are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received the service document 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\tAmendment 39-4110 became effective May 18, 1981, and was effective earlier to those recipients of telegraphic AD T81-06-51, dated March 6, 1981. \n\n\tThis Amendment 39-4445 becomes effective September 30, 1982.
2024-05-06: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a Model AW169 helicopters. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the airworthiness limitations section (ALS) of the existing helicopter maintenance manual or instructions for continued airworthiness (ICA) for your helicopter and the existing approved maintenance or inspection program for your helicopter, as applicable, 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.
2002-22-17: This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to repetitively inspect the inboard forward flap bellcranks for cracks or replace bellcranks depending on the amount of usage. This AD is the result of Cessna re-evaluating the bellcrank life limit analysis and determining that the original estimate is too high. The actions specified by this AD are intended to detect, correct, and prevent future cracks in the bellcrank, which could result in failure of this part. Such failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane.
2018-02-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-301, -321, -322 and -342 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 a report of cracking in the top skin of the horizontal stabilizer (HS) center box (CB) of an airplane in pre-modification 41330 configuration. We are issuing this AD to address the unsafe condition on these products.
2002-22-14: This amendment supersedes an existing airworthiness directive (AD) for specified Bell Helicopter Textron, Inc. (BHTI) model helicopters that requires reducing the retirement time for certain main rotor tension-torsion (TT) straps on those models and on the Model UH-1 series helicopters. This document contains the same requirements as the existing AD but removes the Model UH-1 series restricted category helicopters and adds the BHTI Model 205A and 205B helicopters to the applicability. This amendment is prompted by the issuance of a separate AD for the Model UH-1 series helicopters and the need to add the BHTI Model 205A and 205B helicopters to the applicability because the affected straps are eligible for installation on these model helicopters. The actions specified by this AD are intended to prevent failure of a TT strap, loss of a main rotor blade, and subsequent loss of control of the helicopter.
98-16-23: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235 series airplanes, that requires repetitive high frequency eddy current (HFEC) inspections of the flap transmission shafts to detect cracking, and repetitive functional tests (checks) to verify proper operation of the flap braking sub-system; and corrective actions, 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 cracking in the flap transmission shafts, and to correct a malfunctioning flap braking sub-system, which could result in the inability to move the flaps, or in an asymmetric flap condition, and consequent reduced controllability of the airplane.
95-26-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Textron Lycoming reciprocating engines installed on certain aircraft identified by registration numbers. This action supersedes priority letter AD 94-14-13 that currently requires engines certified to operate on 91 octane or higher aviation gasoline (avgas) to undergo a teardown and analytical inspection for detonation damage, and engines certified to operate on 80 octane avgas to undergo inspection for evidence of possible internal engine damage. This action revises incorrect engine model numbers and aircraft registration numbers listed in the priority letter AD. This amendment is prompted by the Federal Aviation Administration (FAA) receiving more accurate information concerning which aircraft were fueled with the contaminated mixture at the affected airports. The actions specified by this AD are intended to prevent detonation due to low octane, which can result in severe engine damage and subsequent failure.
2024-05-09: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. This AD was prompted by a report of a crack at fuselage station (STA) 1640 frame web common to the lower hinge intercostal tee clip center hole of the upper fastener row. This AD requires a maintenance records check for existing repairs at STA 1640, repetitive ultrasonic (UT) inspections for cracking of the frame web, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
95-26-14: This amendment adopts a new airworthiness directive (AD) that applies to Beech Aircraft Corporation (Beech) Model 1900D airplanes. This action will require inspecting the cabin partition to ensure that a right-hand forward partition bracket exists on certain airplanes, installing this bracket if it does not exist, and improving the right-hand forward partition installation on all affected airplanes. The actions specified by this AD are intended to prevent cabin partition failure because of a structural deficiency in the bracket or if the bracket is not installed, which, if not detected and corrected, could cause passenger injury if the partition could not withstand the load incurred with the baggage compartment loaded to its 250-pound limit.
96-01-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a visual inspection to detect cracks or discrepancies in the aft mount beam assembly of the engines; and replacement of the cracked or discrepant aft mount beam assembly with a new assembly, or a previously inspected and re-identified assembly. That amendment was prompted by reports of cracking in a certain aft mount beam assembly. This new amendment requires additional inspections to detect cracks or discrepancies in the subject area, and various follow-on actions. The actions specified by this amendment are intended to prevent cracks in the aft mount beam assembly of the engines, which could result in loss of the capability of the aft mount beam assembly to support engine loads, and possible separation of the engine from the airplane.
2002-20-07 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that currently requires installation of a new rudder control system and changes to the adjacent systems to accommodate that new rudder control system. That amendment would have superseded seven existing ADs; however, this new amendment removes any reference to superseding four of those seven ADs. This new amendment is prompted by an FAA determination that the requirements of those four ADs must remain in effect until installation of the new rudder control system and corresponding changes to the adjacent systems. The actions specified in this AD are intended to prevent an uncommanded rudder hardover event and consequent loss of control of the airplane due to inherent failure modes, including single-jam modes, and certain latent failures or jams combined with a second failure or jam.
2024-03-08: 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 reports that some overheat detection sensing elements of the bleed air leak detection system were manufactured with insufficient salt fill, which can result in an inability to detect hot bleed air leaks. This AD requires maintenance records verification, and if an affected part is installed, would prohibit the use of certain Master Minimum Equipment List (MMEL) items under certain conditions by requiring revising the operator's existing Minimum Equipment List (MEL). This AD also requires testing the overheat detection sensing elements, marking each serviceable sensing element with a witness mark, and replacing each nonserviceable part with a serviceable part. This AD also prohibits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
95-26-11: This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires visual inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers. That AD also currently requires replacement of cracked fittings, and repair of adjacent structure if found to be cracked. This amendment requires new repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, and corrective actions, if necessary. This amendment is prompted by the results of the visual inspections performed in accordance with the existing AD, which indicate that the visual inspection is inadequate to detect fatigue cracking. The actions specified in this AD are intended to prevent fatigue cracking of the aft pressure bulkhead, which could lead to failure of the end fittings and splice tabs, and subsequent rapid decompression of the airplane during flight.
2018-02-10: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines. This AD was prompted by the discovery of multiple cracked outer diffuser cases. This AD requires initial and repetitive inspections to detect cracks in the outer diffuser case and removal from service of cases that fail inspection. We are issuing this AD to address the unsafe condition on these products.
95-26-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires repetitive purging of the hydraulic system and installation of a spoiler actuator that has been previously certified. That AD was prompted by a report of damage to the locking mechanisms on some pistons of the spoiler actuators. The actions specified by the AD are intended to prevent uncommanded extension of the lift spoiler in the event of loss of hydraulic pressure in the spoiler actuator. This amendment establishes an increased life limit for certain spoiler actuators, and provides an optional terminating action for the requirements of that AD. This amendment also limits the applicability of the rule to fewer airplanes.
2018-02-09: We are superseding Airworthiness Directive (AD) 2008-06-20 R1, which applied to all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes, and certain Model F28 Mark 1000, 2000, 3000, and 4000 airplanes. AD 2008-06-20 R1 required revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness for certain airplanes, and the maintenance or inspection program, as applicable, for certain other airplanes, to incorporate new limitations for fuel tank systems. AD 2008-06-20 R1 also clarified the intended effect on spare and on-airplane fuel tank system components, regarding the use of maintenance manuals and instructions for continued airworthiness. This new AD was prompted by revised fuel airworthiness limitation items (ALI) tasks, and critical design configuration control limitations (CDCCL) items, and associated [[Page 2900]] thresholds, intervals, and instructions. 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. We are issuing this AD to address the unsafe condition on these products.
91-04-04: 91-04-04 AIRBUS INDUSTRIE: Amendment 39-6895. Docket No. 90-NM-224-AD. Applicability: Model A320-111, A320-211, and A320-231 series airplanes, equipped with twin wheel axles; Serial Numbers 002 through 044, 052 through 055, 059 through 073, 076 through 078, and 081; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect defects in the main landing gear (MLG) sliding tube assemblies, accomplish the following: A. Prior to the accumulation of 6,600 landings, or within 30 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with Airbus Industrie Service Bulletin A320-32-1031, Revision 1, dated March 19, 1990: 1. Perform an inspection of the MLG wheel axles, using "Stresscan 500C" test equipment. 2. Identify the part number of the MLG sliding tube assemblies. 3. Replace all sliding tube assemblies identified as suspect. NOTE: The Airbus Industrie service bulletin references Dowty Rotol Service Bulletin 200-32-70, Appendix A, dated December 7, 1989, for additional instructions. B. If defects are found as a result of the inspection required by paragraph A. of this AD, prior to further flight, replace all sliding tube assemblies, in accordance with Airbus Industrie Service Bulletin A320-32-1031, Revision 1, dated March 19, 1990. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6895, AD 91-04-04) becomes effective on March 19, 1991.
2024-04-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by damage found on two power- feeder harnesses on three airplanes due to chafing with wheel bins. An investigation found that the power-feeder harnesses were not adequately supported to protect from chafing due to vibration. This AD requires modifying the variable frequency generator (VFG) power-feeder harness routing, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-17-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-17-51, which was sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) helicopters by individual letters. This AD requires installing a placard in the helicopter and marking the airspeed indication at 140 knots indicated airspeed (KIAS) to indicate a reduction in the helicopter never-exceed speed (Vne) of 28 KIAS; visually checking the tail roter blades on both sides for a crack before each start of the helicopter engines; visually inspecting the tail rotor blades with a 5x or higher magnifying glass at certain time intervals and anytime an increase in vibration occurs, and conducting a dye-penetrant inspection if necessary; and replacing any cracked tail rotor blade with an airworthy tail roter blade. The actions specified by this AD are intended to prevent failure of the tail roter blade and subsequent loss of control of the helicopter.
2024-06-04: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G- 3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engines. This AD was prompted by an updated analysis of an event involving an International Aero Engines, LLC (IAE LLC) Model PW1127GA-JM engine, which experienced a high-pressure compressor (HPC) 7th-stage integrally bladed rotor (IBR-7) separation that resulted in an engine shutdown and aborted takeoff. This AD requires performing an angled ultrasonic inspection (AUSI) of certain high-pressure turbine (HPT) 1st-stage hubs, HPT 2nd-stage hubs, and HPC 8th-stage disks for cracks and, depending on the results of the inspections, replacing the HPT 1st-stage hubs, HPT 2nd-stage hubs, or HPC 8th-stage disks. This AD also requires accelerated replacement of certain HPC 7th-stage rotors, HPC 8th-stage disks, HPC rear hubs, HPT 1st-stage hubs, HPT 2nd-stage hubs, HPT 1st-stage air seals, HPT 2nd- stage air seals, HPT 1st-stage blade retaining plates, and HPT 2nd- stage blade retaining plates. The FAA is issuing this AD to address the unsafe condition on these products.
2011-03-03: 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: Tail rotor driveshaft hanger bearing bracket part number (P/N) 427-044-223-101 has been found cracked due to fatigue. It has been determined that the fatigue cracking was initiated by a tooling mark left during manufacture. The existence of tooling marks on the bracket could lead to bracket failure, loss of tail rotor drive and, consequently, loss of control of the helicopter. We are issuing this AD to require actions to correct the unsafe condition on these products.
98-20-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection of direct current (DC) power unit 1VE to determine whether electrical connections are correctly installed and stud nuts are correctly torqued, and corrective actions, if necessary. For certain airplanes, this amendment also requires replacement of the existing DC power unit 1VE with a modified DC power unit. 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 overheating of electrical connections, which could result in electrical arcing and consequent fire.
2002-22-09: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. This action requires, before further flight, inserting statements into the Limitations section of the Rotorcraft Flight Manual (RFM) prohibiting flight under certain atmospheric conditions. Also, this AD requires inspecting the bullet seal on the multi-purpose air intake (MPAI) to determine the pressure and, if the pressure is less than 3 bars on one or both of the sides, replacing the P2 pipe with an airworthy P2 pipe within a specified time interval. This amendment is prompted by the discovery of unairworthy P2 pipes, which might cause insufficient inflation of the bullet seal on the MPAI. This condition, if not detected, could restrict airflow into the engine inlet during flight in icing conditions, resulting in loss of engine power and subsequent loss of control of the helicopter.