Results
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.