Results
2007-08-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: An analysis of the cable operated control system installed on the SD3 aircraft types that use MS 21260 type end fittings has identified a number of potentially unsafe conditions due to a combination of failures * * *. The failure of certain control cables could result in the loss of certain critical systems. For example, the loss of the low pressure (LP) fuel control cable in combination with a single failure of a fuel condition control cable on the same engine can cause the loss of the capability to shut down the engine in the event of an engine fire. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
97-10-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires repetitively inspecting the main landing gear (MLG) pintle to cylinder interface area for cracks, and replacing any MLG cylinder where a crack of any length is found in the MLG pintle to cylinder interface area. This AD results from reports of MLG cracks in the area of the pintle to cylinder interface on three of the affected airplanes. The actions specified by this AD are intended to prevent failure of the MLG caused by cracks in the pintle to cylinder interface area, which could result in loss of control of the airplane during landing operations.
2007-05-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007-05-51, which was sent previously to all known U.S. owners and operators of MDHI Model MD600N helicopters by individual letters. This AD requires, before further flight, a visual and eddy current inspection of each lateral mixer output link assembly (mixer link) and replacing any cracked mixer link. This AD also requires performing an eddy current inspection on each mixer link before installing it on any helicopter. This amendment is prompted by the discovery of 3 cracked mixer links. The actions specified by this AD are intended to detect a crack in the mixer link, which could result in failure of the mixer link and subsequent loss of control of the helicopter. \n\nDATES: Effective May 7, 2007, to all persons except those persons to whom it was made immediately effective by Emergency AD 2007-05-51, issued on February 17, 2007, which contained the requirements of this amendment. \n\n\tComments for inclusion in the Rules Docket must be received on or before June 19, 2007.
2019-08-03: 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 reports that frame web and frame integral inboard chord cracking is occurring on multiple airplanes in multiple locations below the passenger floor. This AD requires repetitive detailed, general visual, and high frequency eddy current (HFEC) inspections of the section 43 lower lobe frames at certain stations; an inspection to determine if certain repairs are installed; and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2000-26-02: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland Model EC135 P1 and T1 helicopters. That AD currently requires visual and dye-penetrant inspections for a cracked stator blade of the fenestron tail rotor (tail rotor). That AD also requires either stop drilling a cracked blade or, as necessary, replacing an unairworthy stator blade with an airworthy stator blade. This amendment requires replacing the existing stator blade assembly with a new stator blade assembly that incorporates a reinforced base and modified riveting and limits the applicability to certain serial numbered tail booms. This amendment is prompted by additional reports of cracked stator blades of the tail rotor. The actions specified by this AD are intended to prevent failure of the tail rotor and subsequent loss of control of the helicopter.
2006-11-05R1: The FAA is revising an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B series, RB211-524B, -524C2, -524D4, -524G2, -524G3, and -524H series, and RB211-535C and -535E series turbofan engines with high pressure compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 installed. That AD currently requires removing from service certain disc assemblies before they reach their full published life if not modified with anticorrosion protection. This AD requires the same actions but relaxes the removal compliance time for certain disc assemblies that have a record of detailed inspection. This AD results from the FAA allowing certain affected disc assemblies that entered into service before 1990 that have a record of detailed inspections, to remain in service for a longer period than the previous AD allowed. We are issuing this AD to relax the compliance time for certain disc assemblies and track the disc life based on a detailed inspection rather than by its entry into service date, while continuing to prevent corrosion-induced uncontained disc assembly failure, resulting in damage to the airplane. DATES: Effective May 1, 2007. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of February 24, 2004 (69 FR 2661, January 20, 2004). We must receive any comments on this AD by June 15, 2007.
2018-01-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model MD-11 and MD-11F airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires a one-time inspection of the wire assemblies of the tail fuel tank transfer pumps to determine if metallic transitions are installed at the wire harness breakouts, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2018-01-04: We are superseding Airworthiness Directive (AD) 2011-04-05, which applied to all Airbus Model A340-200, -300, -500, and -600 series airplanes. AD 2011-04-05 required revising the maintenance or inspection program to incorporate new airworthiness limitation items (ALIs). This new AD was prompted by the revision of certain ALIs, which specify more restrictive instructions or airworthiness limitations. 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.
2000-26-01: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model BO-105CB-5 and BO-105CBS-5 helicopters. That AD currently requires, before further flight, creating a component log card or equivalent record and determining the calendar age and number of flights on each tension-torsion (TT) strap. This amendment requires before further flight, establishing a life limit for certain main rotor TT straps. This amendment is prompted by a need to establish a life limit for certain TT straps because of an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The same part-numbered TT strap is used on the ECD Model BO-105 helicopters. The actions specified by this AD are intended to prevent fatigue failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
97-14-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A300-600 series airplanes, that requires repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at certain frames, and repair or reinforcement of the structure at the frames, if necessary. This amendment also requires eventual reinforcement of the structure at certain frames, which, when accomplished, terminates the repetitive inspections. This amendment is prompted by a report indicating that fatigue cracks were found in the area of certain frames. The actions specified by this AD are intended to prevent such fatigue cracking, which could reduce the structural integrity of the airframe and result in rapid decompression of the airplane.
2017-26-07: We are 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 fatigue cracking found in a certain fuselage frame web. This AD requires inspection of the fuselage frame for existing repairs, repetitive inspections of the frame, and applicable repairs. We are issuing this AD to address the unsafe condition on these products.
2007-08-07: 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 references Latinoamericana de Aviaci[oacute]n S.A. Service Bulletin No. 25/53/03, dated May 10, 2006, which describes the unsafe condition as: REAR AND FORWARD SUPPORTS OF BOTH HORIZONTAL STABILIZER MODIFICATION. It have been found on several of the affected airplanes some severe corrosion and cracks in both supports. The probable cause for those failures is the accumulation of steam or application products vapors. We are issuing this AD to require actions to correct the unsafe condition on these products.
2017-14-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-401 and DHC-8-402 airplanes. This AD was prompted by a report that a pilot was unable to move the rudder pedal due to an obstruction. This AD requires an inspection to determine if wiring shrouds are present, and modifying the wiring shrouds if necessary. We are issuing this AD to address the unsafe condition on these products.
2000-25-10: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 and B4 series airplanes, and Model A300-600 series airplanes, that requires verifying the correct location of the labels of the hydraulic pipes supplying the strut unlocking actuator of the left-hand main landing gear (MLG), and of the pipes of the left- and right-hand cross brace; reidentifying the pipes; and replacing any incorrectly located label with a new label. The actions specified by this AD are intended to prevent cross connection of the hydraulic hoses or pipes that supply the main strut unlocking actuator, and collapse of the MLG under lateral taxiing loads. This action is intended to address the identified unsafe condition.
95-09-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain British Aerospace Model Avro 146-RJ series airplanes. This action requires a revision to the FAA-approved Airplane Flight Manual (AFM) to alert the flightcrew of the potential for significant delays in the Honeywell Standard Windshear Detection and Recovery Guidance System (WSS) detecting windshear when the flaps of the airplane are in transition. This amendment is prompted by a report of an accident during which an airplane encountered severe windshear during a missed approach. The actions specified in this AD are intended to ensure that the flightcrew is aware that there may be significant delays in the WSS detecting windshear when the flaps of the airplane are in transition.
99-02-09: This amendment adopts a new airworthiness directive (AD), applicable to Agusta S.p.A. Model A109C and A109K2 helicopters. This amendment requires removing the main rotor pitch link assemblies, measuring the radial play of the upper and lower spherical bearings (bearings), and replacing any unairworthy bearings. This amendment is prompted by four reports of increased vibration of the helicopters caused by wear in the bearings of the main rotor pitch change link assembly. The actions specified by this AD are intended to detect unairworthy bearings on the pitch change link assembly and to prevent increased vibration and subsequent reduced controllability of the helicopter.
2007-08-03: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2006-17-04, which applies to certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H airplanes. AD 2006-17-04 currently requires you to inspect the two end fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values, and, if any incorrect torque values are found during the inspection, tighten the hose end fittings to the correct torque values. This AD results from four reports of loose fuel lines connected to the fuel servo or fuel flow transducer. Two reports were of in-flight engine failure on a Model T182T airplane. A third report was of in-flight engine failure on a Model 206H airplane. A fourth report was of a Model 172S airplane losing engine power on final approach. Consequently, this AD would require you to establish the correct torque values of the end fittings on fuel hoses for certain Cessna Models 172R, 172S, 182T,T182T, 206H, and T206H airplanes. This AD clarifies that the torque values need to be physically established and visual inspection only is not sufficient. We are issuing this AD to detect and correct potential loss of fuel flow, which may result in partial or complete loss of engine power and/or uncontrolled engine compartment fire due to fuel leakage forward of the firewall.
2000-25-01: This amendment supersedes Airworthiness Directive (AD) 80-26-05, which currently requires you to repetitively inspect the main landing gear (MLG) inboard door hinges and attachment angles for cracks on certain The New Piper Aircraft, Inc. (Piper) PA-31 series airplanes. AD 80-26-05 also requires you to replace any cracked MLG inboard door hinge or attachment angle with parts of improved design. This AD results from the Federal Aviation Administration's policy on aging commuter-class aircraft and the determination that an improved design MLG inboard door hinge and attachment assembly, when incorporated, will eliminate the need for the currently required repetitive short-interval inspections; however, we have received reports of cracks in the improved design MLG inboard door hinge assemblies on the affected airplanes. This AD retains the current repetitive inspections contained in AD 80-26-05, and requires inspections on the improved design parts. The actions specified by this AD are intended to detect and correct cracked MLG inboard door hinge assemblies. These cracked door hinge assemblies could result in the MLG becoming jammed, with consequent loss of control of the airplane during landing operations.
2018-01-03: We are adopting a new airworthiness directive (AD) for certain Airbus 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); and Airbus Model A310 series 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 reports of the portable oxygen cylinder assembly (POCA) slipping from its bracket inside a one- frame overhead stowage compartment. We are issuing this AD to address the unsafe condition on these products.
97-14-11: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 97-14-11 that was sent previously to all known U.S. owners and operators of certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) series airplanes by individual notices. This AD requires repetitive inspections to detect cracks of a certain bulkhead web of the fuselage at certain locations, and repair, if necessary. This action is prompted by a report of a pressurization problem during flight, which was caused by fatigue cracking in the underfloor pressure bulkhead of the fuselage. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage.
2007-08-02: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. model HC-E4A-3( )/E10950( ) propellers. This AD requires initial and repetitive inspections and rework of the propeller blade retention radius, and replacement of the propeller blade thrust bearing, for each blade. This AD results from reports of excessive propeller vibration and of damaged or broken propeller blade thrust bearings found during routine and investigative propeller disassembly. We are issuing this AD to prevent propeller blade separation, damage to the airplane, and possible loss of airplane control.
95-10-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes, that requires inspections to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, and repair, if necessary. This amendment is prompted by a report indicating that fatigue cracks have been found on the lower spar of the pylon. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the lower spar of the pylon.
2000-25-03: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Inc. (BHTI) Model 205A-1, 205B, 212, 412, and 412CF helicopters. This action requires inspecting the locking washer on each main rotor actuator (actuator) for twisting or damage to the tab and replacing any locking washer that has a twisted or damaged tab. Replacing certain locking washers, regardless of condition, is also required within a specified time period. Installing a certain airworthy locking device on each actuator constitutes terminating action for the requirements of this AD. This amendment is prompted by an incident in which a damaged locking washer allowed the rod end to detach from the collective actuator, causing loss of collective control of the main rotor. The current locking washer is subject to mechanical damage and failure, which allows the actuator piston to unthread itself from its rod end. This condition, if not corrected, could cause loss of control of the main rotor and subsequent loss of control of the helicopter.
2004-13-08: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 series airplanes. This AD requires inspection of the welded joints of the balance weight brackets for the left and right elevator trim tabs for cracking; repetitive inspections, as applicable; and corrective actions including the eventual replacement of all brackets, which constitutes terminating action for the repetitive inspections. This action is necessary to prevent the loss of the balance weight for the elevator trim tab, which could result in incorrect trim during takeoff and landing, and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2017-24-05: 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 cracking in the upper aft skin at the rear spar of the wings. This AD requires repetitive inspections for cracking of the upper aft skin of the wings, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.