Results
2002-21-05: This amendment adopts a new airworthiness directive (AD) that applies to certain REVO, Incorporated (REVO) Models Lake LA-4, Lake LA- 4A, Lake LA-4P, Lake LA-4-200, and Lake Model 250 airplanes. This AD requires you to inspect the upper and lower wing spar doublers and angles for cracks at a certain time after the incorporation of Modification Kit B-79 or FAA-approved equivalent, replace any cracked wing spar doubler or angle, and report the results of the inspection to the Federal Aviation Administration (FAA). The kit modification consists of installing a doubler kit to give the spar an adequate fatigue life. This AD is the result of an incident of a crack found at the most outboard wing attachment fitting hole on one of the affected airplanes with the modification incorporated. The actions specified by this AD are intended to prevent wing spar failure caused by cracks in the wing spar doublers or angles, which could result in the wing separating from the airplane with consequent loss of control.
2024-01-02: The FAA is adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, 382G, and 382J airplanes; and Model C-130A, HP- C-130A, EC-130Q, 282-44A-05 (C-130B), C-130B, and C-130H airplanes. This AD was prompted by the determination that certain aft fuselage sloping longerons may have been exposed to excessively hot forming temperatures for excessive amounts of time, which will reduce the mechanical properties of the longerons and affect their static strength. This AD requires, for certain airplanes, a records review to determine if a conductivity check has been performed on the longerons and to determine if the check was measured at least every four inches. This AD also requires, for certain airplanes, an inspection and applicable repairs. This AD also prohibits installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2002-21-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Cirrus Design Corporation (Cirrus) Model SR20 and SR22 airplanes. This AD requires you to replace the self-locking retaining nut on the roll and yaw trim cartridges with a new self- locking retaining nut with a higher axial load capability. This AD is the result of a report that, during a production flight test, the self- locking retaining nut on the yaw trim cartridge came off. The actions specified by this AD are intended to prevent loss of the self-locking retaining nut on the roll and yaw trim cartridges during flight, which could result in jamming of the corresponding flight control system. Such jamming could lead to loss of control of the airplane.
95-15-07: This amendment supersedes an existing airworthiness directive (AD), applicable to British Aerospace Model BAC 1-11 200 and 400 series airplanes, that currently requires structural inspections and repairs or replacements, as necessary. This amendment requires additional inspections of certain Structural Significant Items (SSI) and expansion of the inspection area for certain other SSI's. This amendment is prompted by the results of a structural integrity audit, which indicated that in order to maintain the structural integrity of these airplanes as they approach or exceed the manufacturer's original fatigue design life goal, certain SSI's need to be inspected. The actions specified by this AD are intended to ensure continuing structural integrity of these airplanes.
2023-26-03: The FAA is adopting a new airworthiness directive (AD) for certain WACO Classic Aircraft Corporation Model 2T-1A-2 airplanes. This AD was prompted by reports of multiple types of cracks at the leading edge former ribs and trailing edge former ribs in the upper wing center section. This AD requires installing maneuver restriction placards in the front and rear cockpits, inspecting the leading and trailing edge former ribs for cracking, replacing any cracked ribs, modifying the upper wing center section assembly, and removing the maneuver restriction placards after completing the modification. The FAA is issuing this AD to address the unsafe condition on these products.
2011-05-06: 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: Service experience has shown that fracture of the timing chain has occurred due to chain wear. This condition, if not corrected, could lead to in-flight cases of engine shutdown. We are issuing this AD to prevent engine in-flight shutdown leading to loss of control of the airplane by requiring life limits for the timing chain.
2002-21-04: This amendment supersedes an existing emergency airworthiness directive (EAD) for Agusta S.p.A. (Agusta) Model A119 helicopters. EAD 2002-17-52, which was issued on August 21, 2002, was sent to all known U.S. owners and operators of Agusta Model A119 helicopters by individual letters. That AD currently requires installing a placard in the helicopter and marking the airspeed indication at 132 knots indicated airspeed (KIAS) before further flight; visually checking the tail rotor blades on both sides for a crack before each start of the helicopter engine; visually inspecting the tail rotor blades with a 5x or higher magnifying glass and conducting a dye-penetrant inspection if you are unable to determine by the visual inspection whether or not there is a crack; replacing any cracked tail rotor blade; modifying the tail rotor hub and blade assembly, reidentifying the modified tail rotor hub and grips assembly and the modified tail rotor hub and blade assembly, which is a terminating action for the never-exceed speed (Vne) reduction; and establishing a retirement life for the tail rotor control rod. This amendment requires the same actions as that EAD, but corrects the airspeed indication marking, which should have been stated as 122 KIAS instead of 132 KIAS. This amendment is prompted by the failure of a tail rotor blade due to a fatigue crack. The actions specified by this AD are intended to prevent failure of the tail rotor blade and subsequent loss of control of the helicopter.
2023-26-04: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000-AE3, Trent 1000-CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000- P3, Trent 1000-Q3, and Trent 1000-R3 engines. This AD is prompted by a determination that certain intervals for visual inspection of the intermediate-pressure stage 8 (IP8) and high-pressure stage 3 (HP3) air transfer tubes and front bearing housing IP8 air feed tubes need to be reduced. This AD requires initial and repetitive visual inspections of the IP8 and HP3 air transfer tubes and front bearing housing IP8 air feed tubes for cracking, damage, or air leakage wear, and replacement, if necessary, 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.
95-14-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model BAC 1-11 200 and 400 airplanes, that currently requires incorporation of certain structural modifications. That AD was prompted by reports of fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design goal. The actions specified by that AD are intended to prevent reduced structural integrity of the airplane. This amendment requires incorporation of additional structural modifications.
2002-21-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires performing a one-time general visual inspection of the pilot's overhead circuit breaker panel wiring for discrepancies; rerouting the P45-12 wire; and repair, if necessary. This action is necessary to prevent circuit breaker wiring from becoming pinched or damaged, causing arcing between the wire and attaching bracket, which could result in smoke and/or fire in the pilot's circuit breaker panel. This action is intended to address the identified unsafe condition.
2023-25-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A321, A330-200, A330-200 Freighter, A330- 300, A330-800, A330-900, A340-200, and A340-300 series airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, -253N, - 271N, -272N, and -273N airplanes; and Model A340-541 and A340-642 airplanes. This AD was prompted by a report that a production deficiency of some SafeLav gaseous oxygen container (SLGOC) batches was identified during production testing of newly manufactured oxygen containers. This AD requires replacing affected SLGOCs and prohibiting the installation of affected SLGOCs, 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.
2002-19-51 R1: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-19-51 R1 that was sent previously to all known U.S. owners and operators of all Boeing Model 737 series airplanes by individual notices. This AD revises existing AD 2002-19-51 that currently requires, for certain airplanes, an inspection to determine the serial number of certain flight control modules (FCM), having P/N 65-44891-7, and corrective actions if necessary. That AD was prompted by reports of failed FCMs, which resulted in sluggish response of the aileron, elevator, and rudder surfaces. This AD revises the existing AD to provide operators with additional options for compliance, to specify the serial numbers of the affected compensator, and to make other editorial changes. The actions specified by this AD are intended to prevent operation with one failed FCM, which could result in reduced controllability of the airplane, or with two failed FCMs, which could result inloss of control of the airplane.
2023-25-01: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report of a passenger seat Y-belt (lap belt) re-installed in the wrong orientation, due to an incorrect maintenance manual. This AD requires inspecting certain Y-belts for correct installation and damage and corrective actions if necessary. This AD also prohibits the use of certain revisions of a maintenance task. The FAA is issuing this AD to address the unsafe condition on these products.
2011-04-10: The FAA is superseding an existing airworthiness directive (AD), which applies to all Model 737-300, -400, and -500 series airplanes. That AD currently requires inspecting to determine if certain carriage spindles are installed, repetitive inspections for corrosion and indications of corrosion on affected carriage spindles, and if necessary, related investigative and corrective actions. That AD also provides an optional terminating action. This new AD mandates the optional terminating action, which eliminates the need for the repetitive inspections. This AD results from reports of corrosion found on carriage spindles that are located on the outboard trailing edge flaps. We are issuing this AD to detect and correct corrosion of the carriage spindle, which could result in fracture. Fracture of both the inboard and outboard carriage spindles, in the forward ends through the large diameters, on a flap, could adversely affect the airplane's continued safe flight and landing.
2023-26-05: 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 determination that the titanium threaded bolts at the forward end of the short rudder trim tab actuating rods could be subject to unexpectedly high oscillating loads due to aerodynamic forces acting on the rudder trim tab. This AD requires periodic replacement of affected titanium threaded bolts, a one-time inspection of the rudder mass balance arm and other elements of the rudder trim tab installation for correct attachment, damage (gouges), cracks, deformation, surface finish, and corrosion on any surrounding parts and, depending on findings, accomplishment of applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) emergency AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
95-13-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires modification of the nacelle strut and wing structure, inspections and checks to detect discrepancies, and correction of discrepancies. This amendment is prompted by the development of a modification of the strut and wing structure that improves the damage tolerance capability and durability of the strut-to-wing attachments, and reduces reliance on inspections of those attachments. The actions specified by this AD are intended to prevent failure of the strut and subsequent loss of the engine.
2002-20-04: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe AEROSPATIALE (Socata) Model TB 21 airplanes. This AD requires you to modify the exhaust system. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent high levels of carbon monoxide from entering the cockpit during certain flight configurations, which could result in the pilot becoming incapacitated or impairing his/her judgement. Such a condition could lead to the pilot not being able to make critical flight safety decisions and result in loss of control of the airplane.
2002-20-05: This amendment adopts a new airworthiness directive (AD), that is applicable to certain Breeze Eastern Aerospace rescue hoists. This amendment requires a one-time inspection of the mounting brackets for cracks, and, if necessary, replacement with serviceable parts. This amendment is prompted by reports of cracked mounting brackets. The actions specified by this AD are intended to prevent mounting bracket cracks, which could result in mounting bracket failure and separation of the rescue hoist from the helicopter.
2018-01-08: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of fatigue cracking in the frame outboard chord and in the radius of the auxiliary chord at a certain area. This AD requires inspections to detect this cracking, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
95-11-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, and -320 series airplanes, that requires modification of the wiring in the elevator controls and the pitch trim dissymmetry monitoring equipment. This amendment is prompted by a report of loss of a propeller and engine gearbox, which resulted in damage to the fuselage. There has also been a report that a modification was implemented in the elevator control cables during manufacture, which reduced the maximum physical separation between the elevator controls and the monitoring equipment. The actions specified by this AD are intended to prevent reduced controllability of the airplane in the event that debris from an engine burst or propeller failure were to strike the fuselage and sever the elevator flight controls.
95-12-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain de Havilland Model DHC-8-102, -103, and -106 series airplanes. This action requires repetitive operational testing of the stall warning computers to ensure activation of the associated stick shakers, and replacement of non-operational stall warning computers with new or serviceable units. This action also provides an optional terminating action for the repetitive operational tests. This amendment is prompted by a report that, during a routine test, the stick shakers of the stall warning system did not activate, due to contamination of the weight-on-wheels contacts in the stall warning computer. The actions specified in this AD are intended to ensure that such contamination is detected. Contamination of the stall warning computers could lead to incorrect logic detection of the weight-on-wheels signal, and subsequent loss of the stick shaker function.
95-11-06: 95-11-06 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE and EUROCOPTER FRANCE: Amendment 39-9240. Docket No. 95-SW-10-AD. Applicability: Model AS-350B, BA, D, B1, and B2 helicopters, with main gearbox (MGB) oil pressure switch (switch) part number (P/N) 704A37-721-082 (S1130-021-082), modification number 350A07-7141, installed, certificated in any category. NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition describedin this AD. Such a request should include an assessment of the effect of the changed configuration of the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent an undetected loss of MGB oil pressure, loss of the MGB, loss of power to the main rotor system, and subsequent loss of control of the helicopter, accomplish the following: (a) Until the MGB switch installation required by paragraph (c) of this AD is accomplished, during each shutdown of the helicopter engine, check to ensure that the MGB oil pressure warning light illuminates. If it does not illuminate, before further flight, replace the MGB switch in accordance with paragraph (c) of this AD. (b) The operational check required by paragraph (a) of this AD may be performed by an owner/operator holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR sections 43.11 and 91.417(a)(2)(v). (c) Within 30 days after the effective date of this AD, remove the MGB switch, P/N 704A37-721-082 (S1130-021-082), modification number 350A07-7141, and replace with MGB switch, P/N 704A37-721-089 (S1130-021-089), modification number 350A07-7152, or Jaeger MGB switch, P/N 704A37-721-014 (068651.54/350A32-3134-00) in accordance with paragraph CC (1) of Eurocopter Service Bulletin AS-350, No. 01.43, Revision 1, dated April 21, 1994. NOTE 2: The MGB switch P/N is engraved on the MGB switch casing. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used when approved by the Manager, Rotorcraft Standards Staff, FAA, Rotorcraft Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur orcomment and then send it to the Manager, Rotorcraft Standards Staff. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (e) The check, removal, and replacement shall be done in accordance with Eurocopter Service Bulletin AS-350, No. 01.43, Revision 1, dated April 21, 1994. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on June 9, 1995.
2023-24-03: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440); CL-600-2C10 (Regional Jet Series 700, 701, & 702); CL-600-2C11 (Regional Jet Series 550); CL-600-2D15 (Regional Jet Series 705); CL- 600-2D24 (Regional Jet Series 900); and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that aircraft maintenance manual (AMM) tasks and certification maintenance requirement (CMR) tasks are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive AMM and CMR tasks. The FAA is issuing this AD to address the unsafe condition on these products.
2002-20-01: This amendment adopts a new airworthiness directive (AD) for the specified military surplus helicopters that requires updating the product identification, extending the application of the AD to other models, continuing the existing retirement time for certain main rotor tension-torsion (TT) straps, and adding the TT strap part numbers to the applicability. This amendment is prompted by the need to expand the applicability to additional military surplus helicopters and to add two part numbers to the applicability. 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.
2023-24-02: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model EMB-135BJ airplanes. This AD was prompted by reports of missing sealant on the rivets installed in the interface between rib 3 and the wing skin. This AD requires applying sealant on the rivets installed in the interface between rib 3 and wing skin, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.