Results
2013-23-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200 and -200PF series airplanes. This AD was prompted by reports indicating that a standard access door was located where an impact-resistant access door was required, and stencils were missing from some impact-resistant access doors. This AD requires an inspection of the left- and right-hand wing fuel tank access doors to determine that impact-resistant access doors are installed in the correct locations, and to replace any door with an impact-resistant access door if necessary. This AD also requires an inspection for stencils and index markers on impact-resistant access doors, and application of new stencils or index markers if necessary. This AD also requires revising the maintenance program to incorporate changes to the airworthiness limitations section. We are issuing this AD to prevent foreign object penetration of the fuel tank, which could cause a fuel leak near an ignition source (e.g., hot brakes or engine exhaust nozzle), consequently leading to a fuel-fed fire.
2010-13-07: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P airplanes. This AD requires you to replace specific spot-welded, V-band exhaust coupling with a riveted, V-band exhaust coupling. This AD results from reports that spot-welded, V-band exhaust couplings are failing. We are issuing this AD to prevent failure of the V-band exhaust coupling, which could cause the exhaust pipe to detach from the turbocharger. This failure could result in release of high-temperature gases inside the engine compartment and possibly cause an in-flight fire. An in-flight fire could lead to loss of control.
88-02-04: 88-02-04 MARVEL SCHEBLER (FACET AEROSPACE PRODUCTS COMPANY): Amendment 39-5830. Applies to Marvel Schebler (Facet) Model MA-3PA carburetors, Part Numbers A10-5220, A10-5257, and A10-5267 manufactured since June 30, 1985, and having serial numbers as listed herein: Carburetors Serial Number Model: MA-3PA DD-4-1583 through DD-4-1610 P/N: A10-5220 DD-4-1613, DD-4-1614, DD-4-1617, (Lycoming P/N: LW-16072) DD-4-1619 through DD-4-1622 Lycoming Engine Models: DD-4-1624 through DD-4-1627 O-235-C1C, O-235-L2A, and O-235-L2C DD-4-1629, DD-4-1632, and DD-4-1633 Model: MA-3PA DM-3-1818 through DM-3-1826, P/N: A10-5257 DM-3-1828 and DM-3-1829 (Lycoming P/N: LW-16677) Lycoming Engine Models: O-235-L2C and O-235-H2C Model: MA-3PA DT-3-1911 through DT-3-1913, P/N: A10-5267 DT-3-1916, DT-3-1917 (Lycoming P/N: LW-16677) DT-3-1920, DT-3-1921, and Lycoming Engine Models: DT-3-1923 through DT-3-1981 O-235-L2C, O-235-N2C, and O-235-P1Compliance is required within the next 25 hours time in service or 30 days, whichever occurs first, after the effective date of this AD, for all applicable carburetors, unless already accomplished. To prevent possible loss of engine power due to a loose metering sleeve, accomplish the following: (a) Check all Textron Lycoming Model O-235-C1C, O-235-L2A, O-235-L2C, O-235-H2C, O-235-N2C, and O-235-P1 engines incorporating Marvel Schebler (Facet) Model MA-3PA carburetors, Part Numbers A10-5220, A10-5257, and A10-5267 manufactured since June 30, 1985, to determine the carburetor serial number. This serial number can be found on the carburetor nameplate located on the throttle body. (b) If the serial number is one of those listed, remove the carburetor, tag it as unairworthy, and replace it with a serviceable one prior to further flight. If the serial number is not one of those listed above, no further corrective action is required. (c) Make an engine logbook entry that this AD has been complied with. NOTE (1): Facet Service Bulletin (SB) A1-87, dated October 1987, pertains to this subject and gives instructions for returning the affected carburetors directly to the factory for corrective action. If being returned to the factory, the owner should package the carburetor to prevent enroute damage and ship directly to Facet Aerospace Products Company, 1048 Industrial Park Road, Bristol, Virginia 24201, USA, Attention: William Smith. NOTE (2): To indicate carburetor corrective action has been taken, Facet will have stamped the lower portion of the carburetor nameplate with the number "87", in which case no further action is required. NOTE (3): Persons authorized by FAR 43.3(g) may perform the check of paragraph (a) and engine logbook entry of paragraph (c) of this AD if the carburetor serial number is not one of those listed above. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 toa base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, ANE-170, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (f) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, New York Aircraft Certification Office, Valley Stream, New York, may adjust the compliance time specified in this AD. This amendment 39-5830 becomes effective on February 1, 1988.
99-18-02: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 205A-1 and 205B helicopters, that requires inspecting the vertical fin spar cap (spar cap) for cracking, corrosion, or disbonding; modifying the vertical fin; and replacing the left-hand spar cap. This amendment is prompted by five accidents involving helicopters of similar type design. The actions specified by this AD are intended to detect fatigue cracking or corrosion on the spar cap, which could lead to failure of the vertical fin spar, loss of the tail rotor, and subsequent loss of control of the helicopter.
2013-23-19: We are adopting a new airworthiness directive (AD) for XtremeAir GmbH Model XA42 airplanes. 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 cracks in a weld seam between the lower left landing gear attachment bearing and the lower engine mount to the firewall attachment plate, which could reduce the structural integrity of the airplane and could result in engine separation. We are issuing this AD to require actions to address the unsafe condition on these products.
99-14-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires inspections to verify correct installation of certain fasteners located on the trailing edges of the horizontal and vertical stabilizer; replacement of the existing fasteners with new fasteners installed with wet sealant; and follow-on actions, if necessary. This amendment is prompted by reports indicating that, during manufacture of the horizontal and vertical stabilizers, certain fasteners attaching the aluminum ribs and brackets to the trailing edges on the empennage were not correctly installed with wet sealant. The actions specified by this AD are intended to prevent corrosion and possible cracking of those aluminum parts, which could result in loss of the attachment of the elevator and rudder to the empennage and consequent reduced controllability of the airplane.
82-08-01: 82-08-01 DOWTY ROTOL: Amendment 39-4356. Applies to Dowty Rotol Propellers (c)R.209/4-40.5/2, installed on Nihon YS-11 airplanes; (c)R.245/4-40.5/13, installed on Convair Models 600(240D) and 640(340D); and (c)R.259/4-40-4.5/17, installed on Convair Model 640(440D) airplanes, not modified by Dowty Rotol Modification (c)VP2693 in accordance with Dowty Rotol SB No. 61-728, Revision 3, dated July 17, 1981. Compliance required as indicated unless already accomplished. To detect and prevent loosening of the propeller blade groups, accomplish the following: (a) Unless already accomplished, within the next 50 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 300 hours' time in service from the last inspection, inspect the locking of the blade groups in the hub group, in accordance with Dowty Rotol Service Bulletin 61-581, Revision 3, dated July 17, 1981, or an FAA-approved equivalent. (b) If, during the inspections required by paragraph (a), it is found that the red line position markings across the bearing center race and the hub have separated by more than 0.100 of an inch, before further flight, replace the propeller with a serviceable propeller of the same model number. (c) If, during the inspections required by paragraph (a), it is found that the lockpieces on the rear of the cylinder are damaged or they are not engaging with and locking the serrations of the bearing center race of the blade group; or that the set bolts securing the lockpieces are not secure or they are bent; or that the shims under the distance blocks on which the lockpieces are mounted have extruded, before further flight, replace the defective parts with serviceable parts of the same part number. This AD supersedes AD 67-32-02. This amendment becomes effective April 12, 1982.
2022-14-09: The FAA is adopting a new airworthiness directive (AD) for certain Saab AB, Support and Services Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by a report that there is no evidence that post-machining stress relief or de-embrittlement post- cadmium plating treatments were performed on certain torque arm center pins. This AD requires replacing each affected torque arm center pin on the main landing gear (MLG), as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2013-23-09: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with sliding doors, except those with modification AL.4262. This AD requires removing from service certain part-numbered nuts and washers from the lower ball-joint bolt. This AD was prompted by a report of a sliding door detaching from the helicopter in flight. These actions are intended to prevent loss of the lower ball-joint nut, which could lead to loss of the sliding door and damage to the helicopter.
59-22-01: 59-22-01 PIAGGIO: Applies to All Model P.136-L2 Aircraft. Compliance required by November 30, 1959. In order to preclude the possibility of condensed water vapor from freezing and obstructing the oil tank breather lines, these lines for both the right and left engines should be rerouted to provide an increased slope in accordance with Piaggio & Co. Change Order No. 36- 52 which covers this same subject.
2013-23-02: We are adopting a new airworthiness directive (AD) for all EADS CASA (Type Certificate previously held by Construcciones Aeronauticas, S.A.) Model CN-235, CN-235-100, CN-235-200, CN-235-300, and C-295 airplanes. This AD requires inspection of the feeder cables of certain fuel booster pumps for damage (including, but not limited to, signs of electrical arcing and fuel leaks), and replacement if necessary. This AD was prompted by a report of an in-flight problem with the fuel transfer system. We are issuing this AD to detect and correct damage to certain fuel booster pumps, which could create an ignition source in the fuel tank vapor space, and result in a fuel tank explosion and consequent loss of the airplane.
99-14-01: This amendment supersedes Airworthiness Directive (AD) 98-04-27, which currently requires incorporating certain icing information into the FAA-approved airplane flight manual (AFM) of The New Piper Aircraft, Inc. (Piper) PA-23, PA-30, PA-31, PA-34, PA-39, PA-40, and PA-42 series airplanes. The Federal Aviation Administration (FAA) inadvertently omitted Piper Models PA-31P, PA-31T, PA-31T1, PA-31T2, and PA-31P-350 airplanes from the Applicability section of AD 98-04-27. This AD retains the requirement of incorporating the icing information into the AFM for all airplanes affected by AD 98-04-27, and adds Piper Models PA-31P, PA-31T, PA-31T1, PA-31T2, and PA-31P-350 airplanes to the Applicability section of the AD. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
99-14-02: This amendment adopts a new airworthiness directive (AD) that applies to certain LET Aeronautical Works (LET) Model L33 SOLO sailplanes. This AD requires replacing the main wing attachment and wing spar root pins and modifying the corresponding area. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. The actions specified by this AD are intended to prevent structural failure of the wing attachments caused by the current design configuration, which could result in the wing separating from the sailplane with consequent loss of control.
2013-22-23: We are adopting a new airworthiness directive (AD) for Aermacchi S.p.A. Models F.260, F.260B, F.260C, F.260D, F.260E, F.260F, S.208, and S.208A airplanes equipped with a Lycoming O-540 wide cylinder flange engine with a front crankcase mounted propeller governor. 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 the set screw that fixes the setting of the propeller governor idler gear shaft was not in the proper position. We are issuing this AD to require actions to address the unsafe condition on these products. [[Page 68358]]
2010-15-02: 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: Several cases of corrosion and damage on the Down Drive Shafts (DDS), between the Down Drive Gear Box (DDGB) and the Input Gear Box (IPGB), on all 10 Flap Tracks (5 per wing), have been reported by AIRBUS Long Range Operators. Investigations have revealed that corrosion and wear due to absence of grease in the spline interfaces could cause [DDS] disconnection which could result in a free movable flap surface, potentially leading to aircraft asymmetry or even flap detachment. * * * * * The unsafe condition could reduce the ability of the flightcrew to maintain the safe flight and landing of the airplane. We are issuing this AD to require actionsto correct the unsafe condition on these products.
99-14-03: This amendment supersedes Airworthiness Directive (AD) 98-13-08, which currently requires replacing and re-routing the power return cables on the starter generator and the generator 2 on certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 98-13-08 also requires inserting a temporary revision to the pilot operating handbook (POH), and installing a placard near the standby magnetic compass. This AD retains the actions currently required by AD 98-13-08 on all airplanes affected by that AD, and requires replacing the temporary revision to the POH and the placard near the standby magnetic compass with an improved procedural POH revision and placard. This AD also requires the placard and the temporary revision to the POH for additional manufacturer serial number Models PC-12 and PC-12/45 airplanes; and requires accomplishing improved Standby Magnetic Compass Swing procedures and incorporating a temporary revision to the maintenance manual on all of theaffected airplanes. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent directional deviation on the standby magnetic compass caused by modifications made to the airplane since manufacture, which could result in flight-path deviation during critical phases of flight. The incorporation by reference of Pilatus PC-12 Maintenance Manual Temporary Revision No. 34-03, dated July 16, 1998, as specified in Pilatus Service Bulletin No. 34-006, dated September 3, 1998, as listed in the regulations is approved by the Director of the Federal Register as of August 17, 1999. The incorporation by reference of Pilatus PC XII Service Bulletin No. 24-002, Rev. No. 1, dated September 20, 1996, as listed in the regulations was previously approved by the Director of Federal Register as of July 31, 1998 (63 FR 32975, July 17, 1998).
99-13-11: This amendment adopts a new airworthiness directive (AD), applicable to Robinson Model R44 helicopters, that requires installing a shutoff clamp on the auxiliary fuel tank sump drain tube (drain tube) and a placard decal to alert operators as to the proper use of the auxiliary fuel tank drain. This amendment is prompted by a report of fuel leaking from a drain tube opening in the area of the horizontal and vertical firewalls. The actions specified by this AD are intended to prevent fuel leaks from the drain tube that could cause a fire and subsequent loss of control of the helicopter.
2013-19-14: We are superseding Airworthiness Directives (ADs) 2009-04-07 and 2011-02-09 for certain [[Page 68348]] Airbus Model A330-200, A330-200 Freighter, A300-300, A340-200, A340- 300, A340-500, and A340-600 series airplanes. AD 2009-04-07 required revising the airplane flight manual (AFM) to include appropriate operational procedures to prevent the air data inertial reference unit (ADIRU) from providing erroneous data to other airplane systems. AD 2011-02-09 required revising the AFM to provide appropriate operational procedures to prevent the airplane flight directors (FDs), autopilot (AP), and auto-thrust re-engagement in the event of airspeed sources providing similar but erroneous data. This new AD requires that operators modify or replace all three flight control primary computers (FCPCs) with new software standards. Since we issued ADs 2009-04-07 and 2011-02-09, we have determined that new software standards for the FCPCs are necessary to inhibit autopilot re-engagementunder unreliable airspeed conditions. This new AD also removes certain airplanes from the applicability. We are issuing this AD to prevent autopilot engagement under unreliable airspeed conditions, which could result in reduced controllability of the airplane.
99-13-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires inspections to detect cracking and other discrepancies of certain web-to-cap fasteners of the rear spar between inner wing stations 310 and 343, and of the web area around those fasteners; and various follow-on actions. That AD also provides for an optional modification, which, if accomplished, would defer the initiation of the inspections for a certain period of time. This amendment requires accomplishment of the previously optional modification. This amendment is prompted by an FAA determination that the optional terminating modification specified in the existing AD must be accomplished within a specified period of time to ensure an acceptable level of safety of the affected fleet. The actions specified by this AD are intended to prevent fatigue cracking in the web of the rear spar of the wing, which could result in failure of the rear spar of the wing and consequent fuel spillage.
2013-22-10: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model Fan Jet Falcon; Model Mystere-Falcon 200 airplanes; and Model Mystere-Falcon 20-C5, 20-D5, 20-E5, and 20-F5 airplanes. This AD was prompted by reports of defective fire extinguisher bottle cartridges. This AD requires checking manufacturing references of pyrotechnical cartridges for batch number and date, repetitive checking of cartridges for electrical continuity, and replacing defective pyrotechnical cartridges if necessary. We are issuing this AD to detect and correct defective fire bottle cartridges, which could impact the capability to extinguish a fire in an engine, auxiliary power unit, or rear compartment, which could result in damage to the airplane and injury to the occupants.
99-13-07: This amendment adopts a new airworthiness directive (AD); applicable to certain McDonnell Douglas Model DC-9-80 series airplanes, Model MD-88 airplanes, and Model MD-90-30 airplanes; that requires repetitive inspections to detect cracking of the main landing gear (MLG) shock strut pistons, and replacement of a cracked piston with a new or serviceable part. This amendment is prompted by reports indicating that, while an airplane was positioned on the taxiway, the right MLG shock strut piston failed due to fatigue cracking. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in failure of the piston, and consequent damage to the airplane structure or injury to the passengers and flightcrew.
92-07-01: 92-07-01 SAAB-SCANIA: Amendment 39-8197. Docket No. 91-NM-53-AD. Applicability: Model SF-340 series airplanes, Serial Numbers 003 through 138, certificated in any category. Compliance: Required within one year after the effective date of this AD, unless previously accomplished. To prevent unexpected loss of nose wheel steering and brakes during taxi, accomplish the following: (a) Remove main/emergency dual pressure indicator 3DB, Part Number (P/N) 522796 and install main/emergency dual pressure indicator 3DB, P/N 523250, in accordance with SAAB Service Bulletin SF340-29-004, Revision 1, dated November 9, 1990. (b) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplanes to a location where the requirements of this AD can be accomplished. (d) The installation shall be done in accordance with SAAB-Scania Service Bulletin SF340- 29-004, Revision 1, dated November 9, 1990, which includes the following list of effective pages: Page Number Revision Level Date 1, 2, 4, 5 1 November 9, 1990 3 (Original) September 15, 1988 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 SAAB-Scania AB, Product Support, S- 581.88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) Thisamendment becomes effective on April 28, 1992.
2013-22-12: We are adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Models DG-800A, DG-800B, DG-500MB gliders. 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 a defective starter motor control unit, which could activate the starter motor without pressing the starter button. We are issuing this AD to require actions to address the unsafe condition on these products. [[Page 67014]]
99-12-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T99-12-52 that was sent previously to all known U.S. owners and operators of all Boeing Model 727 series airplanes by individual telegrams. This AD requires a boost pump dry bay inspection to detect leakage of fuel through an arced-through conduit, and corrective action, as necessary. This AD also requires repetitive detailed visual inspections of the in-tank fuel boost pump wiring to detect chafing of the wire insulation, evidence of electrical arcing, or arc-through of the conduit wall on Model 727 series airplanes, and applicable corrective action; and installation of sleeving over the in- tank fuel boost pump wires as a method to protect the wiring from chafing. This action is prompted by reports of severe wear of in-tank fuel boost pump wiring, and arc-through of the surrounding conduit on two Model 727 series airplanes. The actions specified by this AD are intended toprevent fuel tank explosion resulting from arc-through of the fuel boost pump wiring conduits.
99-13-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777 series airplanes. This action requires repetitive inspections to detect cracking of the upper cutout and lower flange of the outboard support assembly of the flaperons on the wings; and corrective actions, if necessary. This amendment also provides an optional terminating action for the repetitive inspections. This amendment is prompted by results of flight testing conducted by the manufacturer indicating that high engine thrust conditions during takeoff cause excessive cyclic loads and could lead to fatigue cracking of the outboard support of the flaperon. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in fracture of the flaperon support structure, loss of the flaperon, and consequent reduced controllability of the airplane.