Results
2014-02-06: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 helicopters. This AD requires visually inspecting the main rotor swashplate outer ring (outer ring) for a crack and replacing that outer ring if a crack exists. This AD is prompted by two cases of cracks caused by fatigue on certain outer rings. These actions are intended to prevent the failure of the outer ring, which would lead to loss of main rotor blade pitch control and subsequently loss of helicopter control.
2018-07-16: We are adopting a new airworthiness directive (AD) for all Austro Engine GmbH model E4 and E4P diesel piston engines. This AD requires replacement of the waste gate controller and the control rod circlip. This AD was prompted by reports of broken or disconnected turbocharger waste gate control rods on some engines. We are issuing this AD to address the unsafe condition on these products.
2014-04-01: We are adopting a new airworthiness directive (AD) for all Slingsby Aviation Ltd. Model T67M260 airplanes. 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 cracked horizontal stabilizer attachment brackets. We are issuing this AD to require actions to address the unsafe condition on these products.
2014-03-21: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727-200 and 727-200F series airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires a one-time inspection for cracking of the pressure floor of both main wheel wells, and related investigative and corrective actions if necessary; and modifying the pressure floor of both main wheel wells. We are issuing this AD to prevent fatigue cracking in the pressure floor of the main wheel wells, which could lead to rapid loss of cabin pressurization.
2003-13-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires repetitive inspections for cracking of the upper skin of the outboard and center sections of the horizontal stabilizer and the rear spar structure, hinge fittings, terminal fittings, and splice plates; and repair if necessary. This action is necessary to find and fix such cracking, which could lead to reduced structural capability of the outboard and center sections of the horizontal stabilizer, and result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
91-10-07: 91-10-07 MCDONNELL DOUGLAS: Amendment 39-6991. Docket No. 91-NM-02-AD. \n\n\tApplicability: All McDonnell Douglas Model DC-10 series airplanes, manufacturer's fuselage numbers 1 through 379, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent inadvertent opening of a cargo door in flight, a condition which could result in loss of pressurization and reduced controllability of the aircraft, accomplish the following: \n\n\tA.\tWithin 16 months after performing the torque test required by AD 90-19-12, Amendment 39-6735, perform magnetic particle inspections on the H-11 cargo door latch spool fitting attach bolts or replace the H-11 cargo door latch spool fitting attach bolts with new bolts and associated hardware, in accordance with the Accomplishment Instructions for Phase 2 of McDonnell Douglas DC-10 Alert Service Bulletin A52-212, Revision 1, dated September 14, 1990 (hereafter referred to as the "Service Bulletin").1.\tIf a bolt does not pass the magnetic particle inspection, prior to further flight, replace it with a new bolt and seal in accordance with Figure 1 of the Service Bulletin. \n\n\t\t2.\tIf a bolt passes the magnetic particle inspection, prior to further flight, reinstall the bolt and seal in accordance with the Service Bulletin. \n\n\tB.\tWithin 16 months after accomplishment of the inspections required by paragraph A. of this AD, and at intervals not to exceed sixteen months, replace the H-11 cargo door latch spool fitting attach bolts with new bolts and associated hardware or perform either a magnetic particle or ultrasonic inspection on the H-11 cargo door latch spool fitting attach bolts in accordance with the Accomplishment Instructions for Phase 2 of the Service Bulletin. \n\n\t\t1.\tIf a bolt does not pass the magnetic particle/ultrasonic inspection, prior to further flight, replace it with a new bolt and seal in accordance with Figure 1 of the Service Bulletin. \n\n\t\t2.\tIf a bolt passes the magnetic particle/ultrasonic inspection, prior to further flight, reinstall the bolt and seal in accordance with the Service Bulletin. \n\n\tC.\tThe inspections required by paragraphs A. and B. of this AD are not required for Inconel bolts, part numbers RA21026-7, 77711-7, and 3D0031-7. \n\n\tD.\tWithin five years after the effective date of this AD, replace all H-11 cargo door latch spool fitting attach bolts with Inconel bolts, part numbers RA21026-7, 77711-7, and 3D0031-7 (grip lengths as applicable per location as specified in Figure 1 sheets 3 and 4 of the Service Bulletin) in accordance with the Accomplishment Instructions for Phase 3 of the Service Bulletin. Installation of Inconel bolts constitutes terminating action for the requirements of paragraphs A. and B. of this AD. \n\n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base for the accomplishment of the requirements of this AD. \n\n\tF.\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HDR (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6991, AD 91-10-07) becomes effective on June 11, 1991.
2014-03-14: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and -300 series airplanes, and Model A340-200, - 300, -500, and -600 series airplanes. This AD was prompted by results from fuel system reviews conducted by the airplane manufacturer. This AD requires removing bulb-type maintenance lights; installing a drain mast on certain airplanes; and installing muffs on connecting bleed elements on certain airplanes. We are issuing this AD to prevent ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2014-03-07: We are superseding Airworthiness Directive (AD) 2009-26-16 for certain The Boeing Company Model MD-11 and MD-11F airplanes. AD 2009- 26-16 required inspecting to determine if wires touch the upper surface of the center upper auxiliary fuel tank, and marking the location, as necessary; inspecting all wire bundles above the center upper auxiliary fuel tank for splices and damage; inspecting for damage to the fuel vapor barrier seal and upper surface of the center upper auxiliary fuel tank; and performing corrective actions, as necessary. AD 2009-26-16 also required installing nonmetallic barrier/shield sleeving, new clamps, new attaching hardware, and a new extruded channel. This new AD requires inspections of additional center upper auxiliary fuel tank locations and corrective actions as necessary. This AD was prompted by reports that identified additional locations where inspections and corrective actions of the center upper auxiliary fuel tank are needed. We are issuing thisAD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2014-03-09: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42 and Model ATR72 airplanes. This AD was prompted by reports of defective sealing between the nacelle lower fairing and the underwing box. This AD requires a one-time general visual inspection for damaged (worn, torn, or abraded) or missing seals between the nacelle lower fairing and the underwing box of both the left-hand and right-hand engine nacelles, and replacement of the seal and/or shims if necessary. We are issuing this AD to prevent the decrease of the fire extinguishing agent efficiency, which could delay fire extinction and allow fire propagation out of the nacelle fire protected area, resulting in damage to the airplane.
2014-03-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD requires repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and fastener replacement if necessary. This AD was prompted by two reports of fractured fastener heads found on the inboard flap hinge-box forward fitting. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane.
2014-01-05: We are adopting a new airworthiness directive (AD) for certain the Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of cracks in stringer splices at body station STA 360 and STA 908, between stringer (S) S-10L and S-10R; cracks in butt straps between S-5L and S-3L, and S-3R and S-5R; vertical chem-mill fuselage skin cracks at certain butt joints; and an instance of cracking that occurred in all those three structural elements on one airplane. This AD requires repetitive inspections for any cracking of stringer splices and butt straps, and related corrective and investigative actions if necessary. We are issuing this AD to detect and correct cracking in the three structural elements, which could result in the airplane not being able to sustain limit load requirements and possibly result in uncontrolled decompression.
2025-05-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series 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 new or more restrictive airworthiness limitations, 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.
2014-02-09: We are adopting a new airworthiness directive (AD) for Eurocopter Model EC225LP and AS332L1 helicopters with emergency floatation gear. The AD requires, before the next overwater flight, inspecting the strap installation on the hinged rods of the emergency flotation gear on both rear cradles for correct installation. If a strap is installed under the hinged rod median plate rather than over it, reinstalling the strap is required. The AD is prompted by incorrect routing of the straps on the hinged rods of the emergency flotation gear rear cradles. The actions are intended to detect incorrect strap installation and prevent failure of the rods or straps upon deployment of the emergency flotation gear, incorrect float position, and subsequent capsizing of the helicopter.
2025-05-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership (ACLP) Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a design review of aircraft structural and stress reports that resulted in a revision of operational loads for some aircraft flight phases. This AD requires using a certain version of the aircraft structural repair manual (ASRP) and a review and disposition of repairs based on previous versions, 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.
2013-24-04: We are superseding Airworthiness Directive (AD) 2003-19-11 for certain Learjet Inc. Model 60 airplanes. AD 2003-19-11 required determining if a certain fuel crossflow tube is installed; and follow- on/corrective actions, as applicable. This new AD requires retaining all actions in AD 2003-19-11, and it also requires determining if a certain fuel crossflow tube is installed, performing repetitive measurements of the fuel crossflow tube and surrounding valves and cables, and doing corrective actions if necessary. In addition, this new AD expands the applicability of AD 2003-19-11. This AD was prompted by a report that airplanes produced since 2003 might also be subject to the unsafe condition; and that the minimum allowable clearance is not established in the airplane maintenance information. We are issuing this AD to prevent chafing and consequent failure of the fuel crossflow tube due to inadequate clearance between the tube and the flight control cables, which could result inloss of fuel from one fuel tank during normal operating conditions or loss of fuel from both main fuel tanks during fuel cross-feeding operations.
67-28-04: 67-28-04 GENERAL ELECTRIC ENGINES: Amdt. 39-489 Part 39 Federal Register October 5, 1967. Applies to Type CJ805-3, 3A, 3B, 23, 23B and 23C Turbojet Engines. Compliance required as indicated. To prevent failure of the eighth stage compressor disc P/N 106R682P1 and 108R619P1 accomplish the following: (a) Remove from service eighth stage compressor discs with 12,000 or more cycles on the effective date of this AD within the next 50 cycles. (b) Remove from service eighth stage compressor discs with 11,000 or more cycles on the effective date of this AD within the next 250 cycles. (c) Remove from service eighth stage compressor discs with less than 11,000 cycles but more than 9500 cycles on the effective date of this AD within the next 600 cycles. (d) Remove from service eighth stage compressor discs with less than 9500 cycles on the effective date of this AD within the next 1250 cycles or at 8000 cycles, whichever occurs later. (e) Remove from serviceeighth stage compressor discs installed into engines on or after the effective date of this AD at or before 8000 cycles. (f) For the purpose of this AD, the number of cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, take off operation, landing, and engine shutdown. The number of cycles may be determined by actual count or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing each eighth stage compressor disc's time in service by the operator's fleet average time per flight (involving an engine operating sequence consisting of engine starting, take off operation, landing and engine shutdown). (General Electric Alert Service Bulletins A72-254 and A72-261 cover the same subject.) This amendment effective October 5, 1967.
2014-02-03: We are superseding Airworthiness Directive (AD) 2011-27-51 for certain Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. AD 2011-27-51 required inspecting the elevator bob-weight and attaching linkage for correct installation and for damage or deformation to the weight and/or weight bracket with corrective action as necessary. This AD requires installation of the secondary elevator bob-weight stop bolt. The elevator bob-weight (stabilizer weight) traveling past its stop bolt may allow the attaching linkage to move over-center and lead to reduced nose down elevator control. We are issuing this AD to correct the unsafe condition on these products.
2017-17-03: The FAA is superseding Airworthiness Directive (AD) 2017-12- 13, which applied to certain Airbus SAS Model A320-212, -214, -232, and -233 airplanes. AD 2017-12-13 required repetitive low frequency eddy current inspections or repetitive high frequency eddy current inspections of the pocket radius at certain areas of the fuselage frame, and repair if necessary. This AD requires new repetitive inspections at the left- (LH) and right-hand (RH) sides of the fuselage skin at certain frames for any cracking, and repair if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report of a crack found during an inspection of the pocket radius of the fuselage frame, and a determination that similar cracks may develop in nearby areas of the fuselage frame and that additional airplanes are subject to the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
2013-25-03: We are superseding Airworthiness Directives (ADs) AD 2000-17- 05 and AD 2001-04-09 for all the Boeing Company Model 767 airplanes. AD 2000-17-05 required a functional check of the shear rivets in all six elevator power control actuator (PCA) bellcrank assemblies to determine the condition of the shear rivets; and replacement or rework of the bellcrank assemblies, if necessary. AD 2001-04-09 required repetitive testing of the elevator control system to determine if an elevator PCA is rigged incorrectly due to yielded or failed shear rivets in a bellcrank assembly for the elevator PCA, and follow-on actions if necessary. Since we issued ADs 2000-17-05 and 2001-04-09, a terminating modification has been designed. This new AD requires an inspection to determine the part numbers and condition of the bellcrank assemblies; modification or replacement of the PCA bellcrank assembly, if necessary; and a repetitive functional test and mis-rig check, and corrective actions if necessary. We are issuing this AD to prevent continued operation with yielded or failed shear rivets in the elevator PCA bellcrank assemblies, and to prevent certain failures or jams in the elevator system from causing a hardover of the elevator surface, resulting in a significant pitch upset and possible loss of control of the airplane.
2013-26-11: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC225LP helicopters. This AD requires inspecting the swashplates for corrosion or a crack, and making the appropriate repairs or replacement of parts. This AD was prompted by the discovery of corrosion on the swashplates when the main rotor hub (MRH) assemblies were reconditioned. The actions of this AD are intended to detect corrosion or a crack in the swashplates, which could lead to failure of the swashplates and subsequent loss of helicopter control.
53-12-01: 53-12-01 HILLER: Applies to All UH-12, UH-12A, UH-12B, HTE-1, HTE-2, H-23A and H-23B Helicopters Incorporating Horizontal Stabilizers With Short Spar Inserts or Without Spar Inserts. Compliance required as indicated below. Replacement of the horizontal stabilizer assembly, P/N 37001 on the above helicopters has been found necessary to prevent fatigue failure of the stabilizer spar. (Hiller Service Bulletin No. 26 covers this procedure.) (a) Stabilizer assemblies P/N 37001-9 incorporating short spar inserts (5.75 inches) must be removed from service when they have accumulated 300 hours total time. The replacement stabilizer is identified as 37001-14 and incorporates a long spar insert. (b) Stabilizer assemblies P/N 37001-7 (without spar insert and identified as 37001) must be removed from service when they have accumulated 1,600 hours total time. The replacement stabilizer is identified as 37001-12 and incorporates a long spar insert. (c) Stabilizer assemblies P/N 37001-12 and -14 incorporate long spar inserts (10.29 inches). Attachment to the aft bulkhead socket is made by two AN 174-17 bolts. The total service life of these assemblies is not limited.
2013-26-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by reports of arcing and smoke at the left number 2 window in the flight deck. This AD requires inspecting the orientation of both sides of the coil cord connector keyways of the number 2 windows on the flight deck; re-clocking the connector keyways, if necessary; and replacing the coil cord assemblies on both number 2 windows on the flight deck. We are issuing this AD to prevent arcing, smoke, and fire in the flight deck, which could lead to injuries to or incapacitation of the flightcrew.
81-07-10: This amendment adopts a new Airworthiness Directive (AD) which imposes an inspection schedule on the overrunning clutch assembly P/N 369A5350-601 and -603 and a Retirement life on the P/N 369A5364 sprag assembly, which it contains, used in the Hughes Helicopter Model 369 Series Helicopters equipped with any cargo hook. This AD is needed to prevent an overrunning clutch assembly failure which will result in the loss of engine power to the main rotor resulting in a hazardous emergency landing.
2000-02-35: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800 and 1000 airplanes and Model DH.125, HS.125, BH.125, and BAe.125 series airplanes, that requires replacement of cadmium plated fittings and cone caps in the oxygen system plumbing with improved fittings and cone caps, a detailed visual inspection of the oxygen system plumbing in the area of the replaced parts, and corrective actions, if necessary. This amendment is prompted by reports indicating that a field survey of the affected parts revealed that a reaction process was occurring, which resulted in cadmium flaking. The actions specified by this AD are intended to prevent flaking of cadmium from certain oxygen system plumbing fittings and cone caps from blocking the valves and impairing the function of the oxygen system, which could deprive the crew and passengers of necessary oxygen during an emergency that requires oxygen.
69-08-12: 69-08-12 DEHAVILLAND: Amdt. 39-867. Amdt. 39-756 as amended by Amdt. 39-867. Applies to de Havilland DHC-6 type airplanes certificated in all categories except airplanes altered in accordance with de Havilland Service Bulletin 6/181. To prevent loss of the flight controls compliance is required prior to the next flight and at daily intervals thereafter as follows: (a) Visually inspect the elevator rudder pulley bracket assembly at F.S. 106 specifically at the forward flange on the top and bottom beams P/Ns C6FS1263-27 and -29 outboard of the outboard lightening hole for cracks or deformation. Replace cracked or deformed parts before further flight. (b) The 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 directive effective April 30, 1969 and was effective upon receipt by all recipients of the telegram dated February 14, 1969, which contained amendment 39-756. Revised November 15, 1969.