Results
2009-24-19: 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 A320 operator experienced difficulties in extending the RAT [ram air turbine] during a deployment testing. During the trouble shooting, the Ejection Jack of the RAT was removed and investigated. The investigation identified excessive wear of the uplock segments against the inner cylinder of the Ejection Jack, due to an incorrect blend radius of the inner cylinder. * * * This Ejection Jack failure may prevent the effective deployment and use of the RAT in emergency conditions. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-26-06: The FAA is adopting a new airworthiness directive (AD) for certain Technify Motors GmbH TAE 125-02-99 and TAE 125-02-114 model reciprocating engines. This AD was prompted by a report of a defective turbocharger hose discovered on an airplane during a pre-flight inspection. This AD requires the removal and replacement of the affected turbocharger hose. The FAA is issuing this AD to address the unsafe condition on these products.
2003-25-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires modifying the fuel pipe couplings and installing bonding leads in specified locations within the fuel tank. This amendment continues to require the modification and installation, but adds new modifications of the bonding leads for certain airplanes. This amendment also changes the applicability of the existing AD. The actions specified by this AD are intended to prevent ignition sources and consequent fire/explosion in the fuel tank. This action is intended to address the identified unsafe condition.
2009-24-20: 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: Frost, snow, slush or ice on the wing leading edges and upper wing surfaces may change the stall speeds, stall characteristics and the protection provided by the stall protection system, which could result in reduced controllability of the aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
94-18-03: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls- Royce plc (R-R) RB211 series turbofan engines. This action requires removing from service intermediate pressure (IP) compressor stage 6-7 rotor shafts that exceed new, reduced cyclic life limits. This amendment is prompted by a report of an uncontained failure of an IP compressor stage 6-7 rotor shaft. The actions specified in this AD are intended to prevent an uncontained engine failure due to rupture of an IP compressor stage 6-7 rotor shaft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 26, 1994. Comments for inclusion in the Rules Docket must be received on or before November 8, 1994.
95-24-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires replacement of the check valves of the thrust reverser with modified valves on certain airplanes and the replacement of the manual control valves of the thrust reverser with modified valves on certain other airplanes. This amendment is prompted by recent engineering analysis, which revealed that, if the non-return valve installed on the hydraulic return line of the thrust reverser were to jam in the closed position, it could cause pressurization of the Hydraulic Control Unit (HCU). The actions specified by this AD are intended to prevent such pressurization of the HCU due to jamming of the non-return valve in the hydraulic return line, and consequent deployment of a thrust reverser during flight; this condition, if not corrected, could adversely affect the controllability of the airplane.
2020-24-04: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD requires revising the existing airplane flight manual (AFM) to incorporate procedures for conducting an approach with a localizer- based navigation aid, monitoring localizer raw data, calling out any significant deviations, and performing an immediate go around if the airplane has not intercepted the final approach course as shown by the localizer deviation. This AD was prompted by reports that the autopilot flight director system (AFDS) failed to transition to the instrument landing system localizer (LOC) beam after the consistent localizer capture function in the flight control modules initiated a transition to capture LOC during approach. The FAA is issuing this AD to address the unsafe condition on these products.
94-17-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, -300, and -400 series airplanes, that requires various modifications of certain evacuation ramp/slides. This amendment is prompted by reports of several evacuation ramp/slide malfunctions. The actions specified by this AD are intended to prevent delayed inflation of evacuation ramp/slides, which could delay or impede the evacuation of passengers during an emergency.
2008-11-02 R1: The FAA is revising an existing airworthiness directive (AD), which applies to all Lockheed Model L-1011 series airplanes. That AD currently requires revising the FAA-approved maintenance program by incorporating new airworthiness limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires the accomplishment of certain fuel system modifications, the initial inspections of certain repetitive fuel system limitations to phase in those inspections, and repair if necessary. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.DATES: This AD is effective December 18, 2009. On June 25, 2008 (73 FR 29410, May 21, 2008), the Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD. We must receive any comments on this AD by January 19, 2010.
2021-01-04: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 series airplanes, excluding Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracked or completely severed lugs in the upper aft corner stop fitting assembly of the forward entry door. This AD requires an inspection, a measurement, or a records check of that assembly to determine the part number, and replacement if a certain part is found. The FAA is issuing this AD to address the unsafe condition on these products.
2003-25-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-400, -401, and -402 airplanes, that requires a one-time inspection of the forward engine mount assemblies on the left and right engine nacelles for installation of pre-production engine mount assemblies, and follow-on corrective actions if necessary. This action is necessary to prevent failure of the forward engine mount, which could result in reduced structural integrity of the nacelle and engine support structure. This action is intended to address the identified unsafe condition.
95-10-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (BHTI)-manufactured restricted category Model UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, UH-1P, TH-1F, and TH-1L helicopters. This action requires verification that the tail rotor control system is rigged in accordance with the applicable maintenance manual; a fluorescent penetrant inspection for cracks at the roots of the gear teeth on the pinion and gear of affected 42-degree tail rotor drive gearbox assemblies (42-degree gearboxes), and replacement of the 42-degree gearbox pinion or gear if cracks are found; and, creation of a component history card to track numbers of torque events. A torque event is defined as a takeoff or a lift (internal or external). This amendment is prompted by 14 accidents reported since 1979 in the United States and Canada related to failure of the 42-degree gearbox. The actions specified in this AD are intended to prevent failure of the 42-degree gearbox, loss of tail rotor control, and subsequent loss of control of the helicopter.
94-17-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking in the upper row of fasteners in the lower lobe of the fuselage skin lap joints, and repair, if necessary. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their design life goal. The actions specified by this AD are intended to prevent separation of the fuselage skin and rapid loss of pressure in the airplane. This AD also relates to the recommendations of the Airworthiness Assurance Working Group assigned to review Model 747 series airplanes, which indicate that, to assure long term continued operational safety, various structural inspections should be accomplished.
95-10-04: This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Textron Lycoming and Avco Lycoming) Model T5313B and T5317 series turboshaft engines, that currently requires initial and repetitive dye penetrant inspections of the centrifugal compressor impeller for cracks, and if necessary, removal from service. This amendment requires the use of a new, more conservative minor cycle counting factors table, introduces a method for prorating past centrifugal compressor impeller usage based on the new cycle counting factors, provides an enhanced centrifugal compressor impeller inspection procedure, and eliminates flyback criteria based on crack size. For those centrifugal compressor impellers that exceed their published life limit, this amendment implements a schedule for safe removal of time- expired parts. This amendment is prompted by a report of an uncontained centrifugal compressor impeller failure and subsequent rotorcraft accident. The actions specified by this AD are intended to prevent centrifugal compressor impeller failure, which can result in an uncontained engine failure, inflight engine shutdown, or damage to the rotorcraft.
2020-25-12: The FAA is adopting a new airworthiness directive (AD) for all Superior Air Parts, Inc. (SAP) Model IO-360-series and O-360-series reciprocating engines and certain Lycoming Engines (Lycoming) Model AEIO-360-, IO-360-, and O-360-series reciprocating engines with a certain SAP crankshaft assembly installed. This SAP crankshaft assembly is installed as original equipment on the affected SAP engines and as a replacement part under parts manufacturer approval (PMA) on the affected Lycoming engines. This AD was prompted by three crankshaft assembly failures that resulted in the loss of engine power and immediate or emergency landings. This AD requires the removal from service of all affected crankshaft assemblies. The FAA is issuing this AD to address the unsafe condition on these products.
2008-09-23 R1: We are adopting a new airworthiness directive (AD) for the products listed above that would revise an existing AD. 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: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that it is necessary to introduce Critical Design Configuration Control Limitations (CDCCL), in order to preserve critical fuel tank system ignition source prevention features during configuration changes such as modifications and repairs, or during maintenance actions Failure to preserve critical fuel tank system ignition source prevention features could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective December 14, 2009. On June 6, 2008 (73 FR 24145, May 2, 2008), the Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD. We must receive comments on this AD by January 11, 2010.
2009-24-03: We are adopting a new airworthiness directive (AD) to supersede AD 85-08-04, which applies to certain Vulcanair S.p.A. Models P 68, P 68B, P 68C, P 68C-TC, and P 68 "OBSERVER'' airplanes. AD 85- 08-04 currently requires you to repetitively visually inspect the front and rear wing spars for cracks. If cracks are found, AD 85-08-04 requires you to modify the wing spars. The wing spar modification terminates the repetitive inspection AD action and may be installed before cracks develop. Since we issued AD 85-08-04, the manufacturer revised the modification kit and identified additional airplane serial numbers that require the inspection and/or modification. Consequently, this AD would retain the actions of AD 85-08-04, allow you to install the revised modification kit, and add additional serial numbers to the Applicability section. We are issuing this AD to detect and correct cracks in the front and rear wing spar, which could result in the wing separating from the airplane. Thisfailure could lead to loss of control.
2020-25-03: The FAA is superseding Airworthiness Directive (AD) 2020-01- 17, which applied to all Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2020-01-17 required repetitive checks of the pressure gauges on the inflation reservoir of each emergency escape slide/raft to determine the amount of pressure and, depending on findings, accomplishment of applicable corrective actions. This AD retains the requirements of AD 2020-01-17, expands the list of affected parts to be checked, and provides optional terminating action for the repetitive checks; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by the determination that certain parts that were not identified in AD 2020-01-17 are also subject to the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
2003-25-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 airplanes, that currently requires inspections to detect breakage in the struts of the rear mount strut assemblies on the left and right engine nacelles, and replacement of any broken struts. The existing AD also requires eventual replacement of all currently installed struts with new and/or reworked struts, as terminating action for the inspections. The amendment requires new repetitive inspections of the strut assemblies for cracking of struts replaced per the existing AD, and replacement of any cracked strut with a new, machined strut. The amendment also changes the applicability of the existing AD by adding certain airplanes and removing certain other airplanes, and includes an optional terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent failure of the engine rear mount struts, which could result in reduced structural integrity of the nacelle and engine support structure. This action is intended to address the identified unsafe conditions.
97-05-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that currently requires replacing the existing standby generator control unit (GCU) with a new improved standby GCU. That action was prompted by reports of improper functioning of the standby GCU. This amendment requires replacement of the GCU on additional affected airplanes. For some airplanes, it also will require that a wiring modification be accomplished prior to replacement of the GCU. The actions specified by this AD are intended to prevent such improper functioning of the GCU, which could result in the loss of the standby emergency generation system.
2009-24-10: 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: In-flight engine shutdown incidents were reported on aircraft equipped with TAE-125-01 engines. This was found to be mainly the result of operation over a long time period with broken piston cooling oil nozzles which caused thermal overload of the piston. We are issuing this AD to prevent engine in-flight shutdown, possibly resulting in reduced control of the aircraft.
69-20-03: 69-20-03 GRUMMAN: Amdt. 39-848, as amended by Amdt. 39-924, applies to all G-159 aircraft. Compliance required within the next 50 hours' time in service after the effective date of this airworthiness directive as amended. To prevent fuel filter blockage due to ice and possible engine flameout, accomplish the following or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Southern Region. (a) Install a fuel temperature indicator on each engine fuel system in accordance with Grumman Gulfstream Service Change 114, with Amendment 1 or later approved revision. (b) Mark gage with red radial lines at +5 degrees C and +54 degrees C and a green arc from +5 degrees C to +54 degrees C. (c) Install a placard adjacent to fuel temperature indicator which reads as follows: "Caution See AFM for use of fuel filter heater." The use of a fuel additive as outlined in Advisory Circular 20-29A along with an appropriate Airplane Flight Manual supplement or Revision 21 to the G-159 Airplane Flight Manual is considered an equivalent means for showing compliance with paragraphs (a), (b), and (c). Amendment 39-848 effective October 5, 1969. This amendment (39-924) becomes effective January 23, 1970.
2020-21-17: The FAA is superseding Airworthiness Directive (AD) 2018-16- 05, which applied to certain The Boeing Company Model 757 airplanes. AD 2018-16-05 required repetitive inspections for skin cracking and shim migration at the upper link drag fittings, diagonal brace cracking, and fastener looseness; and applicable on-condition actions. This AD retains the actions required by AD 2018-16-05, reduces the compliance times for certain inspections, and adds repetitive inspections at certain fastener hole locations and applicable on-condition actions. This AD was prompted by reports of bolt rotation in the engine drag fitting joint and fastener heads; an inspection of the fastener holes revealed that cracks were found in the skin. This AD was also prompted by a report of multiple cracks in the drag fitting at fastener holes found during an inspection required by AD 2018-16-05. The FAA is issuing this AD to address the unsafe condition on these products.
94-15-03: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 767 series airplanes. This action requires revising the Non-Normal Procedures Section of the FAA-approved Airplane Flight Manual (AFM) to include procedures that will enable the flight crew to identify fuel system leaks and to take appropriate action to prevent further fuel loss. This amendment is prompted by reports that flight crew procedures related to fuel system leaks are not defined adequately in the FAA-approved AFM for these airplanes. The actions specified in this AD are intended to ensure that the flight crew is advised of the potential hazard related to fuel exhaustion due to undetected leakage, and the procedures necessary to address it.
2008-09-25 R1: We are adopting a new airworthiness directive (AD) for the products listed above that would revise an existing AD. 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: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that it is necessary to introduce Critical Design Configuration Control Limitations (CDCCL), in order to preserve critical fuel tank system ignition source prevention features during configuration changes such as modifications and repairs, or during maintenance actions. Failure to preserve critical fuel tank system ignition source prevention features could result in a fuel tank explosion. * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective December 10, 2009. On June 6, 2008 (73 FR 24157, May 2, 2008), the Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD. We must receive comments on this AD by January 11, 2010.