Results
2006-13-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400 and 747-400D series airplanes. This AD requires replacing specified tie rods of the center overhead stowage bins. This AD results from manufacturer analysis of the overhead storage bin support structure that demonstrated that the capability of certain existing tie rods does not meet emergency landing load requirements. We are issuing this AD to prevent detachment of the center overhead stowage bins during an extreme forward load event, which could cause injury to passengers and hinder emergency evacuation procedures.
2006-13-12: We are adopting a new airworthiness directive (AD) that supersedes AD 98-12-01, which applies to certain Pilatus Aircraft Ltd (Pilatus) Models PC-6, PC-6/A, PC-6/B, and PC-6/C series airplanes equipped with turbo-prop engines. Since we issued AD 98-12-01, the FAA determined the action should also apply to all the models of the PC-6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15 that were produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 98-12-01 was to apply to all the affected serial numbers of the airplane models listed in TC No. 7A15. This AD retains all the actions of AD 98-12-01, adds those Fairchild Republic Company airplanes to the applicability of this AD, and lists the individual specific airplane models. We are issuing this AD to prevent engine fuel starvation during maximum climb and descent caused by poor fuel tank venting with low fuel levels, which could result in a loss of engine power during critical phases of flight. DATES: This AD becomes effective on August 7, 2006. As of July 13, 1998 (63 FR 30370, June 4, 1998), the Director of the Federal Register previously approved the incorporation by reference of Pilatus Service Bulletin No. PC-6-SB-171, dated October 18, 1995, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
2006-13-07: The FAA is superseding an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD-11 and MD-11F airplanes. That AD currently requires replacement of the upper and lower reading lights in the forward crew rest area with a redesigned light fixture. This new AD adds airplanes to the applicability of the existing AD. This AD results from a report of the old reading lights being inadvertently sent to an additional ten airplanes. We are issuing this AD to prevent a possible flammable condition, which could result in smoke and fire in the forward crew rest area.
2006-12-18: The FAA is adopting a new airworthiness directive (AD) for all Short Brothers Model SD3 airplanes. This AD requires installing additional fuel tank bonding jumpers, performing an in-place resistance check of the float switches, inspecting certain internal components of the fuel tanks, and performing related corrective actions if necessary. This AD also requires revisions to the Airworthiness Limitations section of the Instructions for Continued Airworthiness, and to the airplane flight manual procedures for operation during icing conditions and fuel system failures. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent ignition sources inside the fuel tanks, which could lead to fire or explosion.
2006-12-25: The FAA adopts a new airworthiness directive (AD) for General Machine--Diecron, Inc. (GMD) actuator nut assembly, part number (P/N) GMD115-810029-17 and P/N GMD115-810029-23, that are installed on certain Raytheon Aircraft Company (Raytheon) (formerly Beech) airplanes that are not equipped with a hydraulic main landing gear (MLG) or modified to a hydraulic MLG. This AD requires you to determine by maintenance records check and/or inspection whether any actuator nut assembly, P/N GMD115-810029-17 or P/N GMD115-810029-23, is installed on the right main MLG actuator, and, if installed, requires you to replace it with a new actuator nut assembly, P/N GMD115-810029-23B or FAA- approved equivalent P/N. This AD results from several reports of failures of the actuator nut assembly, P/N GMD115-810029-17 and P/N GMD115-810029-23. We are issuing this AD to prevent failure of the actuator nut assembly for the right MLG actuator, which could result in failure of the MLG. This failure couldprevent the extension or retraction of the MLG.
2006-12-19: The FAA is adopting a new airworthiness directive (AD) for Hamilton Sundstrand model 14RF-19 propellers. This AD requires replacing certain actuator yokes with improved actuator yokes. This AD results from certain propeller system actuator yoke arms breaking during flight. We are issuing this AD to prevent actuator yoke arms breaking during flight, which could cause high propeller vibration and contribute to reduced controllability of the airplane.
2006-12-11: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires replacing the fuel shutoff valve wires and conduit assemblies in the left and right engine strut aft fairing areas. This AD results from a report that an operator discovered many small chafe marks and exposed shield braid on fuel shutoff wires routed through a conduit in the wing. We are issuing this AD to prevent exposed wires that could provide an ignition source in a flammable leakage zone and possibly lead to an uncontrolled fire or explosion.
2006-12-03: The FAA is adopting a new airworthiness directive (AD) for certain 747-100B, 747-200B, 747-200F, 747-300, 747-400, 747-400F, and 747SP series airplanes. This AD requires doing inspections of the midpivot bolt and midpivot bolt access door of the spring beam of the inboard side of the outboard struts for discrepancies, installing a placard on the midpivot bolt access door, and applicable corrective actions if necessary. This AD results from reports indicating that the midpivot bolt and midpivot bolt access door of the spring beam of the inboard side of the outboard struts were installed in the incorrect position. We are issuing this AD to ensure that the subject midpivot bolts and midpivot bolt access doors are installed in the correct position. If not installed in the correct position, a midpivot bolt could be overloaded and crack or fracture, which could result in the loss of the spring load path and consequent separation of the associated outboard strut and engine from the airplane.
2006-04-11 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Airbus Model A321-111, -112, and -131 airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner rear spar; and repair, if necessary. That AD also provides for optional terminating action for the repetitive inspections, adds inspections of three additional mounting holes, and revises the thresholds for the currently required inspections. We issued that AD to detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity of the airplane. This new AD retains the requirements and revises the applicability of that AD. This AD results from the discovery of a typographical error in the applicability of that AD, which could cause the unsafe condition on an affected airplane to remain uncorrected. We are issuing this AD to detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity of the airplane. DATES: Effective June 22, 2006. The incorporation by reference of the publications specified in the following table, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 8, 2006 (71 FR 8792, February 21, 2006). Material Incorporated by Reference Airbus service bulletin Revision level Date A320 57 1100, including Appendix 01 (1) July 28, 1997. A320 57 1100, including Appendices 01 and 02 03 January 16, 2003. A320 57 1101 03 July 30, 2003. A320 57 1101 04 November 22, 2004. 1 Original. The incorporation by reference of Airbus Service Bulletin A320-57- 1101, Revision 02, dated October 25, 2001, as listed in the regulations, was approved previously by the Director ofthe Federal Register as of April 21, 2004 (69 FR 17906, April 6, 2004). The incorporation by reference of Airbus Service Bulletin A320-57- 1101, dated July 24, 1997, as listed in the regulations, was approved previously by the Director of the Federal Register as of December 18, 1998 (63 FR 66753, December 3, 1998). We must receive comments on this AD by August 7, 2006.
2006-12-07: The FAA is superseding an existing airworthiness directive (AD) for Lycoming Engines (formerly Textron Lycoming) models 320, 360, and 540 series, "Parallel Valve" reciprocating engines, with certain Engine Components Inc. (ECi) cylinder assemblies, part number (P/N) AEL65102 series "Classic Cast", installed. That AD currently requires replacing these ECi cylinder assemblies. This AD requires the same actions, but replaces the "Engine Models" Table 1 and "Engines Installed On, But Not Limited To" Table 2 with corrected tables. Also, this AD corrects the casting part number. This AD results from reports of applicability errors found in AD 2005-26-10. We are issuing this AD to prevent loss of engine power due to cracks in the cylinder assemblies and possible engine failure caused by separation of a cylinder head.
2006-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes. This AD requires replacing the de-icing system ejector flow control valves with new, improved control valves having hermetically sealed switches; and rewiring applicable connectors. This AD results from a fuel system review conducted by the manufacturer. We are issuing this AD to prevent a potential source of ignition near a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2006-11-06: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-200 and -300 series airplanes. This AD requires replacing the placards on certain stowage bins with new placards, installing partial dividers in certain other stowage bins, and installing straps on stowage bins containing life rafts. For certain airplanes, this AD also requires related concurrent actions. This AD results from test data indicating that outboard overhead stowage bins are unable to withstand the 4.5g down-load standard intended to protect passengers during flight turbulence or a hard landing. We are issuing this AD to prevent the stowage bins from opening during flight turbulence or a hard landing, which could result in the contents of the stowage bins falling onto the passenger seats below and injuring passengers, or blocking the aisles, impeding the evacuation of passengers in an emergency.
2006-11-04: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Airbus Model A319, A320, and A321 airplanes. The existing AD currently requires a one-time ultrasonic inspection for certain airplanes, and repetitive detailed inspections for all airplanes, for cracking in the forward lug of the support rib 5 fitting of both main landing gear (MLG), and repair if necessary. The existing AD also provides for optional terminating actions. This AD removes the requirement for the one-time ultrasonic inspection and reduces the compliance time and repetitive interval for the detailed inspection of all airplanes. This AD also adds certain Airbus Model A318 airplanes to the applicability. This AD continues to provide optional terminating action for certain airplanes, as well as other optional methods of complying with the AD's requirements. This AD results from a new crack that was found in the forward lug of the MLG support rib 5 fitting. We are issuing this AD to detect and correct cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during takeoff or landing.
2006-10-07: The FAA is adopting a new airworthiness directive (AD) for Hamilton Sundstrand model 14RF-9 propellers. This AD requires visual, feeler gage, and tap test inspections of certain serial number (SN) propeller blades of the "+E'' repair configuration for blade delamination, and removing the blade from service if the blade fails inspection. This AD also requires removing those serial-numbered propeller blades from service by March 1, 2007. This AD results from reports of delaminated blade fiberglass repair patches that allowed corrosion to form on the aluminum blade spar under the patch. We are issuing this AD to prevent blade failure that could result in separation of a propeller blade and loss of control of the airplane.
2006-10-14: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires an inspection to determine the part number of the upper and lower stop pad support fittings of all the lower cargo doors, repetitive inspections of all early configuration stop pad support fittings, and corrective action if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from a report of cracks found in the area of the upper and lower stop pad support fittings of the cargo door pan on numerous airplanes. We are issuing this AD to prevent cracks in the cargo door pan, which could result in the inability to fully pressurize an airplane, possible pressure loss, or possible rapid decompression of the airplane.
2006-10-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310-200 and -300 series airplanes. This AD requires repetitive inspections for cracking of the flap transmission shafts, and replacing the transmission shafts if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of longitudinal cracks due to stress corrosion in the transmission shafts between the power control unit (PCU) and the torque limiters of the flap transmission system. We are issuing this AD to detect and correct cracking of the flap transmission shaft, which could compromise shaft structural integrity and lead to a disabled flap transmission shaft and reduced controllability of the airplane.
2006-10-09: The FAA is adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes in operation. This AD requires replacing the protective tubes and conduits of the wiring harnesses of the refueling vent and pilot valves with non-conductive hoses; modifying the harness wiring and supports; and rerouting the harnesses to prevent interference with adjacent strobe light connectors; as applicable. This AD results from a fuel system review conducted by the manufacturer. We are issuing this AD to prevent a potential source of ignition near a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion.
2006-10-06: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 440) airplanes. This AD requires an inspection of the manufacturer's date code on certain electrical relays to identify defective Leach TDH- series electrical relays and replacement of identified relays. This AD results from a report of defective electrical relays affecting emergency equipment. We are issuing this AD to prevent the malfunction of emergency equipment (the passenger oxygen system, the thrust reverse control system, and the auxiliary power unit fire detection, warning, and extinguishing system) during an emergency.
2006-09-13: The FAA is superseding an existing airworthiness directive (AD) for Honeywell International Inc. ALF502L series and ALF502R series turbofan engines. That AD currently establishes stress rupture retirement life limits for certain third stage turbine discs used in conjunction with certain third stage turbine nozzles. This AD brings requirements forward and unchanged, from the previous AD for ALF502R series turbofan engines. Also, this AD establishes new reduced stress rupture retirement life limits for certain part numbers (P/Ns) of third stage turbine disc and shaft assemblies installed in ALF502L series turbofan engines. This AD also requires removing those same parts from service using a drawdown schedule. This AD results from a report of failure of a third stage turbine disc and shaft assembly, leading to turbine blade release and separation of the exhaust nozzle. We are issuing this AD to prevent total loss of engine power, in-flight engine shutdown, release of turbine blades, separation of the exhaust nozzle, and possible damage to the airplane.
2006-10-02: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747 airplanes. This AD requires the following actions for the drive mechanism of the horizontal stabilizer: Repetitive detailed inspections for discrepancies and loose ball bearings; repetitive lubrication of the ballnut and ballscrew; repetitive measurements of the freeplay between the ballnut and the ballscrew; and corrective action if necessary. This AD results from a report of extensive corrosion of a ballscrew in the drive mechanism of the horizontal stabilizer on a similar airplane model. We are issuing this AD to prevent an undetected failure of the primary load path for the ballscrew in the horizontal stabilizer and subsequent wear and failure of the secondary load path, which could lead to loss of control of the horizontal stabilizer and consequent loss of control of the airplane.
2006-09-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310-200 and -300 series airplanes. This AD requires doing repetitive rotating probe inspections for any crack of the rear spar internal angle and the left and right sides of the tee fitting, and doing related investigative/corrective actions if necessary. This AD also requires modifying the holes in the internal angle and tee fitting by cold expansion. This AD results from full-scale fatigue tests, which revealed cracks in the lower rear spar internal angle, and tee fitting. We are issuing this AD to detect and correct fatigue cracks of the rear spar internal angle and tee fitting, which could lead to the rupture of the internal angle, tee fitting, and rear spar, and consequent reduced structural integrity of the wings.
2004-03-15 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 airplanes. That AD currently requires performing a one-time inspection to detect chafing of electrical wires in the cable trough below the cabin floor; repairing, if necessary; installing additional tie-mounts and tie-wraps; applying sealant to rivet heads; and modifying electrical wires in certain sections. We issued that AD to prevent chafing of electrical wires. This new AD, for certain airplanes, eliminates the requirement to modify electrical wires in certain sections. This AD results from a report indicating that the modification of electrical wires does not need to be done on certain airplanes subject to the existing AD. We are issuing this AD to prevent chafing of electrical wires, which could result in an uncommanded shutdown of an engine during flight. DATES: The effective date of this AD is March 19, 2004.On March 19, 2004 (69 FR 7111, February 13, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin 8-53-80, Revision "A", dated July 25, 2000. On October 27, 1998 (63 FR 50501, September 22, 1998) the Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin S.B. 8-53-66, dated March 27, 1998.
2006-09-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires modifying the wiring on an alternating current (AC) service bus contactor that is located in the avionics bay. This AD results from incidents of short circuit failures of certain AC contactors located in the avionics bay. We are issuing this AD to prevent short circuit failures of certain AC contactors, which could result in arcing and consequent smoke or fire.
2006-08-11: We are adopting a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 airplanes equipped with certain crew seat bucket assemblies with and without a backrest recline system. This AD requires you to replace the backrest tubes on these crew seat bucket assemblies at a specified time and adds a life limit for these backrest tubes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to prevent cracks in the backrest tubes of certain crew seat bucket assemblies, which could result in failure of the seat system. This failure could lead to the pilot and co-pilot's reduced ability to control the airplane. This failure could also affect the proper function of the seat restrain system in the case of an emergency landing.
2006-08-06: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model SA-360C, SA-365C, SA-365C1, and SA-365C2 helicopters. This action requires inspecting the main gearbox (MGB) base plate for a crack and replacing the MGB if a crack is found. This amendment is prompted by the discovery of a crack in a MGB base plate. The actions specified in this AD are intended to detect a crack in a MGB base plate and prevent failure of one of the MGB attachment points to the frame, which could result in severe vibration and subsequent loss of control of the helicopter.