Results
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.
2013-20-13: We are adopting a new airworthiness directive (AD) for certain Bell Model 206B and 206L helicopters. This AD requires installing a placard beneath the engine power dual tachometer and revising the operating limitations section of the rotorcraft flight manual (RFM). This AD was prompted by several incidents of third stage engine turbine wheel failures, which were caused by excessive vibrations at certain engine speeds during steady-state operations. These actions are intended to alert pilots to avoid certain engine speeds during steady- state operations, prevent failure of the third stage engine turbine, engine power loss, and subsequent loss of control of the helicopter.