Forty-Ninth Meeting, RTCA Special Committee 186: Automatic Dependent Surveillance-Broadcast (ADS-B). The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 186: Automatic Dependent Surveillance-Broadcast (ADS-B). The meeting will be held October 5-9, 2009, at 8 a.m. on October 9th and 9 a.m. on the other days. The meeting will be held at the RTCA Conference Rooms at 1828 L Street, NW., Suite 805, Washington, DC 20036.

Air Traffic Procedures Advisory Committee. The FAA published a meeting notice on September 10, 2009 (74 FR 46655) advising the public that a meeting of the Federal Aviation Air Traffic Procedures Advisory Committee would be held on October 6, 2009. This notice adds an additional meeting date of Wednesday, October 7, 2009 from 8 a.m. to 5 p.m. The meeting will be held Tuesday, October 6th, 2009, from 8 a.m. to 5 p.m., and Wednesday, October 7th, 2009, from 8 a.m. to 5 p.m.

AW139 Tail Boom Subject of AD. FAA has issued an emergency airworthiness directive (AD) in reaction to an EASA mandatory continuing airworthiness information (MCAI) alert regarding the tail boom of the AgustaWestland AW139. According to EASA, the tail boom of an AW139 bent and collapsed while taxiing. In addition, the agency has discovered "evidence of debonding on some tail boom panels," on the AW139 and AB139. FAA is mandating more frequent inspections of the tail panels and measures designed to uncover potentially unsafe conditions. The latest EASA AD requires repetitive inspections of the tailboom panels at closer intervals. In case of debonding, the EASA AD requires you to mark the debonded areas for identification, contact the manufacturer for instructions, and follow their corrective actions.

BRAZILIAN AIRWORTHINESS DIRECTIVE. AD No.: 2009-09-01 Effective Date: 03 Sep. 2009 and issued by the Agencia Nacional de Aviacao Civil (ANAC) applies to all aircraft registered in the Registro Aeronautico Brasileiro. No person may operate an aircraft to which this AD applies, unless it has previously complied with the requirements established herein. AD No. 2009-09-01 - EMBRAER - Amendment 39-1286. This AD is applicable to Embraer Model EMB-500 airplanes. It has been found the possibility of elevator mass balance fasteners becoming slack under certain conditions. The loose of at least two fasteners may lead to an unbalance condition, which may induce flutter on airplane elevators. Since this condition may occur in other airplanes of the same type and affects flight safety, an immediate corrective action is required. Thus, sufficient reason exists to request compliance with this AD in the indicated time limit without prior notice. REQUIRED ACTION: Replacement of the nuts of the right and left elevators mass balance fasteners. COMPLIANCE: Required.

Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, -900 and -900ER. Final rule. SUMMARY: This AD requires repetitive testing of the rudder pedal forces or repetitive detailed inspections of the inner spring of the rudder feel and centering unit, and corrective actions if necessary. This AD also requires replacement of the spring assembly in the rudder feel and centering unit, which terminates the repetitive tests or inspections. This AD results from reports of low rudder pedal forces that were caused by a broken inner spring in the rudder feel and centering unit; a broken inner spring in conjunction with a broken outer spring would significantly reduce rudder pedal forces. We are issuing this AD to prevent reduced rudder pedal forces, which could result in increased potential for pilot-induced oscillations and reduce the ability of the flightcrew to maintain the safe flight and landing of the airplane. DATES: This AD is effective October 14, 2009.

Airworthiness Directives; Boeing 767. Final rule. SUMMARY: This AD requires sealing certain fasteners and stiffeners in the fuel tank, changing certain wire bundle clamp configurations on the fuel tank walls, inspecting certain fasteners in the fuel tanks and to determine the method of attachment of the vortex generators, and corrective action if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent possible ignition sources in the auxiliary fuel tank, main fuel tanks, and surge tanks caused by a wiring short or lightning strike, which could result in fuel tank explosions and consequent loss of the airplane. DATES: This AD becomes effective October 1, 2009.

Airworthiness Directives; Airbus Model A330-200 and -300, Model A340-200 and -300 Series Airplanes, and Model A340-541 and -642. Final rule; request for comments. SUMMARY: This AD requires replacing certain Thales Avionics pitot probes with certain other pitot probes. This AD results from reports of airspeed indication discrepancies while flying at high altitudes in inclement weather conditions. We are issuing this AD to prevent airspeed discrepancies, which could lead to disconnection of the autopilot and/or auto-thrust functions, and reversion to flight control alternate law and consequent increased pilot workload. Depending on the prevailing airplane altitude and weather, this condition, if not corrected, could result in reduced control of the airplane. DATES: This AD becomes effective September 8, 2009.

Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC- 6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2. Final rule. SUMMARY: This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Findings of corrosion, wear and cracks in the upper wing strut fittings on some PC-6 aircraft have been reported in the past. It is possible that the spherical bearing of the wing strut fittings installed in the underwing can be loose in the fitting or cannot rotate because of corrosion. In this condition, the joint cannot function as designed and fatigue cracks may then develop. Undetected cracks, wear and/or corrosion in this area could cause failure of the upper attachment fitting, leading to failure of the wing structure and subsequent loss of control of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 1, 2009.

Airworthiness Directives; CASA) Model CN-235, CN-235- 100, CN-235-200, and CN-235-300. Final rule. 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 operation in icing conditions, an asymmetric configuration of the de-icing boots was detected, occurring during the inflation and deflation check of the de-icing system. This was found to be due to an unexpected failure mode in the pneumatic and de-icing system's control electronic logic. This condition, if not corrected, could affect the deicing capabilities of the boots installed on the wing and horizontal stabilizers, potentially leading to loss of control of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 1, 2009.