Third Meeting--Special Committee 221--Aircraft Secondary Barriers & Alternative Flight Deck Security Procedures. Notice of RTCA Special Committee 221 meeting. SUMMARY: The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 221: Aircraft Secondary Barriers & Alternative Flight Deck Security Procedures. DATES: The meeting will be held June 23-24, 2009. From 12 p.m. to 5 p.m. on June 23 and 9 a.m. to 5 p.m. on June 24. ADDRESSES: The meeting will be held at RTCA, Inc., MacIntosh-NBAA and Hilton-ATA Rooms, 1828 L Street, NW., Suite 805, Washington, DC 20036. FOR FURTHER INFORMATION CONTACT: RTCA Secretariat, 1828 L Street, NW., Suite 805, Washington, DC 20036; telephone (202) 833-9339; fax (202) 833-9434; Web site http://www.rtca.org

Seventy-Ninth Meeting--Special Committee 159--Global Positioning System (GPS). Notice of RTCA Special Committee 159 meeting. SUMMARY: The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 159: Global Positioning System (GPS). DATES: The meeting will be held June 23-26, 2009, from 9 a.m. to 4:30 p.m. (unless stated otherwise). ADDRESSES: The meeting will be held at RTCA, Inc., 1828 L Street, NW., Suite 805, Washington, DC 20036. FOR FURTHER INFORMATION CONTACT: RTCA Secretariat, 1828 L Street, NW., Suite 805, Washington, DC 20036; telephone (202) 833-9339; fax (202) 833-9434; Web site http://www.rtca.org

Airworthiness Directives; Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1. Final rule; request for comments. SUMMARY: We are superseding an existing airworthiness directive (AD) for the specified ECD model helicopters that currently requires initial and repetitive inspections of the main rotor blade (blade) upper and lower surfaces for bulging. This AD results from mandatory continuing airworthiness information (MCAI) issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, based on reported incidents in which a balance weight migrated toward the tip of the blade. The MCAI states that new blades have become available that are not fitted with lead balance weights. The MCAI states that only blades equipped with a lead balance weight may result in the unsafe condition. This AD retains the requirements of the current AD but limits the applicability to those part-numbered blades that are fitted with lead balance weights. The actions are intended to limit the applicability to those blades fitted with lead balance weights that could detach, migrate, and cause severe vibrations leading to blade failure and subsequent loss of control of the helicopter. DATES: This AD becomes effective on June 12, 2009.

Airworthiness Directives; Air Tractor, Inc. Models AT-400, AT-400A, AT-402, AT-402A, AT-402B, AT-502, AT-502A, AT-502B, AT-503A, AT-602, AT-802, and AT-802A. Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) to supersede AD 2008-10-12, which applies to certain Air Tractor, Inc. AT-400, AT-500, AT-600, and AT-800 series airplanes. AD 2008-10-12 currently requires repetitively inspecting the engine mounts for cracks, repairing any crack damage found, and installing gussets as a terminating action for the repetitive inspections. This AD results from a report of a Model AT-602 airplane with a crack completely through the gusset that was installed as required in AD 2008-10-12. Consequently, this AD would require you to continue repetitively inspecting the engine mounts for cracks for all previously affected Air Tractor, Inc. AT-400, AT-500, AT-600, and AT-800 series airplanes with or without gussets installed, and repairing any crack damage found. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. This failure could lead to separation of the engine from the airplane. DATES: This AD becomes effective on June 1, 2009.

Airworthiness Directives; M7 Aerospace LP Models SA226-AT, SA226-T, SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, and SA227-DC (C-26B). Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) to supersede AD 2008-12-16,which applies to certain M7 Aerospace LP SA226 and SA227 series airplanes. AD 2008- 12-16 currently requires you to inspect wires and tube assemblies for chafing, arcing, or insufficient clearance between components. If chafing, arcing, or insufficient clearance between components is found, AD 2008-12-16 requires you to clear, repair, and/or replace all chafed wires, components, and tube assemblies. AD 2008-12-16 also requires you to cover the four-gauge wires leaving the battery box with firesleeving and secure them with a clamp. Since we issued AD 2008-12-16, M7 Aerospace LP has notified us that Model SA227- BC (C-26A) was inadvertently left out of the Applicability section of the AD, and they updated some of the service information due to parts availability. Operators have also identified issues with model applicability that needed clarification. Consequently, this AD retains the actions of AD 2008-12-16, adds Model SA227-BC (C-26A) to the Applicability section, and regroups the models for clarification. We are issuing this AD to detect and correct chafing of electrical wires, components, and tube assemblies. This condition could result in arcing of exposed wires with consequent burning of a hole in a hydraulic line or the bleed air line. This failure could lead to a hydraulic fluid leak and a possible fire in the engine nacelle compartment. DATES: This AD becomes effective on July 2, 2009.

Airworthiness Directives; British Aerospace 748. Final rule; request for comments. SUMMARY: 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: Resulting from the assessment of fuel tank wiring installations required by SFAR 88 (Special Federal Aviation Regulation) and equivalent JAA/EASA (Joint Aviation Authorities/European Aviation Safety Agency) policy, BAE Systems (Operations) Limited has revised the HS.748 Aircraft Maintenance Manual (AMM), now at Revision 19, to introduce Chapter 05-10-00 ''Critical Design Configuration Control Limitations (CDCCL)-Fuel System''. The CDCCLs provide instructions to retain critical ignition source prevention features during configuration changes that may be caused by modification, repair or maintenance actions. The CDCCLs have been identified as requirements for continued airworthiness to address the risk of fuel vapour ignition sources remaining undetected. This condition, if not corrected, could result in a fuel tank explosion and consequent loss of the aircraft. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective June 12, 2009.

Airworthiness Directives; Airbus Model A330-202, -223, -243, -301, -322, and -342. Final rule; request for comments. SUMMARY: 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: During the A330 and A340 aircraft fatigue test, cracks appeared on the right and left sides between the crossing area of the keel angle fitting and the front spar of the Centre Wing Box (CWB). Several modifications have been introduced in the fleet in the area of frame [FR] 40 keel angle assembly in order to prevent these cracks. However the new design has caused interference between one fastener and the keel angle which was corrected by further local reprofiling of the keel angle horizontal flange. Analysis shows that without an inspection of this reprofiled area, the structural integrity of the area is impacted, which constitutes an unsafe condition. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective June 12, 2009.

Airworthiness Directives; Airbus Model A310 Airplanes and Airbus Model A300-600. Final rule; request for comments. SUMMARY: ThisAD 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: An A300-600 operator reported a recent event which occurred during the take-off roll, where a SOGERMA co-pilot seat slid back uncommanded to the end position. The seat horizontal movement actuator was replaced on the affected co-pilot seat. At the following take-off roll the same event occurred, the co-pilot seat sliding back uncommanded again. An unwanted movement of pilot or co-pilot seat in the horizontal direction is considered as potentially unsafe, especially during the take-off phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction. Uncommanded movement of the pilot and co-pilot seats during takeoff or landing could interfere with the operation of the airplane and, as a result, could cause consequent loss of control of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective June 12, 2009.

Airworthiness Directives; Eurocopter Deutschland GmbH Model EC135. Final rule; request for comments. SUMMARY: This AD results from a report of abnormal main rotor blade vibrations on a Eurocopter Model EC135 helicopter. This AD also results from mandatory continuing airworthiness information (MCAI) issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI states that an operator reported unusual vibrations during the start phase of the main rotor blade on one helicopter. The vibrations stopped after the application of torque. Subsequent maintenance personnel found that six of the eight attachment screws of the lower hub-shaft bearing support were loose. This condition was discovered in two additional helicopters. Loose screws in the bearing support, if not detected and corrected, could result in abnormal main rotor blade vibrations and subsequent damage to the main transmission. DATES: This AD becomes effective on June 12, 2009.