Results
2001-09-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Models 206H and T206H airplanes. This AD requires you to visually inspect the horizontal stabilizer attachment reinforcement brackets for the existence of seam welds and replace any reinforcement bracket found without seam welds. This AD is the result of a report that these parts were manufactured without seam welds. The actions specified by this AD are intended to detect and replace structurally deficient horizontal stabilizer attachment brackets. Continued use of such brackets could result in structural failure of the horizontal stabilizer with reduced or loss of control of the airplane.
2007-22-02: This amendment supersedes an existing airworthiness directive (AD) for the specified Bell Helicopter Textron, Inc. (Bell) Helicopters. That AD currently requires inspecting each affected tail rotor blade (blade) forward tip weight retention block (tip block) and the aft tip closure (tip closure) for adhesive bond voids, and removing any blade with an excessive void from service. That AD also requires modifying certain blades by installing shear pins and tip closure rivets. This amendment contains the same requirements but expands the applicability to include other part and serial-numbered blades. This AD also clarifies the requirement to re-identify the modified blade by adding "FM" after the part number and also requires dynamically balancing the tail rotor. The existing AD was prompted by five occurrences of missing tip blocks or tip closures resulting in minor to substantial damage. This amendment was prompted by the determination that the AD should apply to other affected part and serial-numbered blades. The actions specified by this AD are intended to prevent loss of a tip block or tip closure, loss of a blade and subsequent loss of control of the helicopter.
52-04-03: 52-04-03 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required not later than May 1, 1952. Eliminate pressure gage or place in heater fuel control box. (Trans World Airlines Engineering Order No. 5794 covers the elimination of the pressure gage.)
2001-08-25: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330-301, -321, -322, and -342 series airplanes and certain Airbus Model A340 series airplanes. This action requires reinforcement of the wing structure at the inboard pylon rear pickup area. This action is necessary to prevent fatigue cracking of the bottom skin and reinforcing plate of the wing due to bending, which could lead to reduced structural integrity of the airplane wing. This action is intended to address the identified unsafe condition.
2019-23-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes; A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N and -271N airplanes; and A321 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. The FAA is issuing this AD to address the unsafe condition on these products.
2019-22-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by the results of a structural analysis, which identified that the upper frame fittings (UFFs) of the forward cargo door surrounding structure have a low fatigue life. This AD requires repetitive inspections of the forward cargo door UFFs and brackets for discrepancies and, depending on the findings, doing applicable corrective actions, 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.
2007-22-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane.
2001-08-21: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires a visual inspection of the fuel level control switch, the fuel level control switch wiring harness, and the wiring harness conduit for damage, wear or chafing, broken or missing O-rings, or indications of electrical arcing. This amendment also requires replacement of a certain conduit in the fuel level control switch wiring harness, installation of electrical sleeving over the fuel level control switch wiring harness, and installation of the fuel level control switch which has been so modified. The actions specified by this AD are intended to prevent chafing of the fuel level control switch wiring harness, which could cause arcing and result in a fire in the fuel tank.
2001-08-28: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires revising the Airworthiness Limitations Section of the maintenance manual (767 Airworthiness Limitations Instructions (ALI)). The revision will incorporate into the ALI certain inspections and compliance times to detect fatigue cracking of principal structural elements (PSE). This amendment is prompted by analysis of data that identified specific initial inspection thresholds and repetitive inspection intervals for certain PSE's to be added to the ALI. The actions specified by this AD are intended to ensure that fatigue cracking of various PSE's is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
2007-22-05: 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: At some locations, the new calculated fatigue life [for the wing to center box assembly] falls below the aircraft Design Service Goal. The aim of this Airworthiness Directive (AD) is * * * to ensure detection of cracks on the panels and stiffeners at rib No. 1. This situation, if left uncorrected, could affect the structural integrity of the area. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective November 28, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 28, 2007. The Director of the Federal Register approved the incorporation by reference of Airbus A300-600 Airworthiness Limitations Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006, as of October 31, 2007 (72 FR 54536, September 26, 2007).
94-06-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that requires modification of the leading edge slat access panel and internal structure at Front Spar Station (FSS) 250.663. This amendment is prompted by reports that fuel leaking from the fuel line at FSS 250.663 flowed through a drain hole in a slat access panel and leaked into the turbine exhaust area. The actions specified by this AD are intended to prevent drainage from such a fuel leak into the turbine exhaust area, which could cause an external fire under the wing.
2019-22-06: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-800 series airplanes. This AD was prompted by reports of inadequate clearance between a certain fuel quantity indicating system (FQIS) tank unit and a certain reinforcement angle added as a part of a certain split winglet modification. This AD requires a detailed inspection to measure the clearance between the FQIS tank unit and a certain reinforcement angle installed as a part of the split winglet modification, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2001-08-23: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200 series airplanes. This action requires repetitive inspections for cracking of the outboard pitch load fittings of the wing front spar, and corrective action, if necessary. This action also provides a terminating action for the repetitive inspections, which is optional for uncracked pitch load fittings. This action is necessary to find and fix cracking of the outboard pitch load fittings of the wing front spar, which could lead to loss of the upper link load path and result in separation of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
2007-22-06: 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: Over the years, several Fokker 100 (F28 Mark 0100) operators reported that a MLG (main landing gear) wheel fell off during regular operation of the aircraft. These incidents occurred due to a missing spacer, which had inadvertently not been installed during a previous wheel change. Omitting the installation of the wheel spacer allows the wheel to move sideways along the axle, which subsequently leads to bearing failure, followed by loss of the wheel. * * * This condition, if not corrected, * * * could conceivably result in loss of control of the aircraft during the take-off run, landing rollout or taxiing operations. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
94-05-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F-28 series airplanes, that requires the implementation of a corrosion prevention and control program either by accomplishing specific tasks or by revising the maintenance inspection program to include such a program. This amendment is prompted by reports of incidents involving corrosion and fatigue cracking in transport category airplanes that are approaching or have exceeded their economic design goal; these incidents have jeopardized the airworthiness of the affected airplanes. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the airplane due to the problems associated with corrosion.
2007-19-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This AD requires inspections to detect scribe lines and cracks of the fuselage skin, lap joints, circumferential butt splice strap, and external and internal approved repairs; and related investigative/ corrective actions if necessary. This AD results from reports of scribe lines adjacent to the skin lap joints. We are issuing this AD to detect and correct cracks, which could grow and cause rapid decompression of the airplane.
2001-08-27: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Lockheed Model L-1011 series airplanes. This action requires inspection of the windshield heat wire bundle for chafing or damage, and inspection of the harness clamps of the wire bundle for damage; and corrective actions, if necessary. For certain airplanes, this action also requires rerouting of the windshield heat wire bundle. This action is necessary to prevent chafing or damage of the windshield heat wire bundle, which could cause arcing and result in smoke and fire in the cockpit. This action is intended to address the identified unsafe condition.
2019-21-51: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-115B model turbofan engines. Emergency AD 2019-21-51 was sent previously to all known operators of the GE GE90-115B model turbofan engines with certain engine serial numbers. This AD requires the removal from service of the Interstage Seal, part number 2505M72P01, from the affected engines. This AD was prompted by a recent event involving an uncontained high-pressure turbine (HPT) failure, resulting in an aborted takeoff and debris penetrating the airplane's fuselage and the other engine. The FAA is issuing this AD to address the unsafe condition on these products.
94-05-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400A airplanes, that requires an inspection to detect fatigue-related cracking in certain cabin seat frames; measurement to determine gap size between the bearing shafts and certain seat frames; and repair, if necessary. This amendment is prompted by in-service inspection reports of fatigue-related cracking radiating outward from the bushings welded into the cabin seat frames. The actions specified by this AD are intended to prevent separation of the cabin seat frames from their bases during an emergency landing.
2007-21-07: 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 incident occurred on one A300-600 aircraft at parking brake application. Both engines were running, the aircraft started moving again despite parking brake application. Captain tried to stop the aircraft via the pedals but, as the parking brake selector valve was selected, the aircraft could not be stopped (as per design, activation of the parking brake inhibits the other braking modes, and consequently prevents the recovery of the normal braking through the pedals). As part of the investigation, the pressure limiter was removed and examined. The expertise revealed a metallic wire aimed at reducing the section of one port of this equipment was found broken. A part of this wire partially obstructed the hole receiving this wire, thus delaying the build up of parking brake pressure. We are issuing this AD to require actions to correct the unsafe condition on these products.
2004-21-02: The FAA adopts a new airworthiness directive (AD) for all Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa ``PZL-Bielsko'' (PZL-Bielsko) Model SZD-50-3 ``Puchacz'' sailplanes. This AD requires you to repetitively inspect the front and back of the fuselage front bulkhead attachment fitting for cracks and replace the attachment fitting if any cracks are found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Poland. We are issuing this AD to detect and correct cracks in the fuselage front bulkhead attachment fitting, which could result in structural failure of the bulkhead. This failure could lead to loss of control of the sailplane.
2001-08-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes, that requires replacement of the existing potable water fill line tube with a new hose. This action is necessary to prevent fracture of a clamshell coupling on the potable water fill line, which could cause water to flow into the aft cargo compartment. A large amount of water in the cargo compartment could cause large shifts in the airplane's center of gravity, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2011-10-04: 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: During manufacture of high-pressure (HP) compressor stage 1 discs, a small number of parts have been rejected due to a machining defect that was found during inspection. Analysis of the possibility of less severe examples having been undetected and passed into service has concluded that action is required to reduce the risk of failure. It was therefore necessary to reduce the life limit. The HP compressor stage 1 disc is part of the HP compressor stage 1-4 shaft, part number (P/N) FK32580. We are issuing this AD to prevent failure of the HP compressor stage 1 disc, uncontained engine failure, and damage to the airplane.
94-04-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of the bottom joint fittings and modification of these new bottom joint fittings, the main landing gear (MLG) rear spar fittings, and the rear spar webs by cold-expanding the bolt holes. This amendment is prompted by full-scale fatigue testing of a Fokker Model F28 Mark 0100 series airplane, which revealed cracks in the MLG rear spar fitting. The actions specified by this AD are intended to prevent loss of the structural integrity of the MLG attachments.
2007-21-11: We are adopting a new airworthiness directive (AD) for the products listed above that will supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: This Airworthiness Directive (AD) is prompted by occurrences where abrasive damage (chafing) has been found on oil pipe assemblies in the area of the torque oil pressure transducer on the engines of some PC-12 aircraft. Incorrect assembly after maintenance tasks can decrease distances between various pipe/hoses assemblies and adjacent components. Damaged pipes can cause oil leakages in the area of the engine. This AD requires actions that are intended to address the unsafe condition described in the MCAI.