Results
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.
2020-25-09: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW4164, PW4164-1D, PW4168, PW4168-1D, PW4168A, PW4168A-1D, and PW4170 model turbofan engines with a certain outer combustion chamber assembly and 3rd stage low-pressure turbine (LPT) duct segments installed. This AD was prompted by reports of damaged or failed 3rd stage LPT duct segments on PW engines with the Talon IIB outer combustion chamber assembly configuration installed. This AD requires removing and replacing certain 3rd stage LPT duct segments. The FAA is issuing this AD to address the unsafe condition on these products.