Airworthiness Directives; BAE Systems (Operations) Limited (Jetstream) Model 410. 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: A failure mode has been identified that can lead to loss of a nose wheel. Any combination of excessive wear and/or adverse tolerances on the axle inner cone, outer cone or wheel hub splined sleeve cones can result in the loss of the critical gap between the inner flange face of the wheel outer cone and the axle end face. If this gap is lost, it can result in the wheel having free play along the length of the axle. This condition, if not corrected, can result in breakage of the wheel nut lock plate leading to unscrewing of the wheel retention nut and subsequent separation of the nose wheel from the landing gear axle. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective September 9, 2009.

Airworthiness Directives; Pilatus Aircraft Limited Model PC-7. 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: This Airworthiness Directive (AD) is prompted due to reported corrosion on the bolts and in the bores of the attachment fittings for the engine mounting frame. The corrosion is caused by damaged cadmium plating of the bolts or damaged surface finish of the attachment fitting. Such a condition, if left uncorrected, could lead to crack initiation at the bolt and the fitting bore and subsequently to the failure of the engine attachment fitting. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective September 9, 2009.

Airworthiness Directives; Teledyne Continental Motors (TCM) IO-520, TSIO-520, and IO-550 Series Reciprocating Engines With Superior Air Parts, Inc. (SAP) Cylinder Assemblies Installed. Final rule. SUMMARY: This AD requires initial and repetitive inspections and compression tests to detect cracks in those cylinders with more than 750 flight hours (FH) time-in-service (TIS). This AD results from reports of cracks in the area of the exhaust valve and separation of cylinder heads from the barrels of SAP cylinder assemblies with certain part numbers. We are issuing this AD to prevent the separation of the cylinder head, which could result in immediate loss of engine power, possible structural damage to the engine, and possible fire in the engine compartment. DATES: This AD becomes effective September 9, 2009.

Airworthiness Directives; Fokker Model F.27 Mark 50. 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 walk around check on a Fokker 50 (F27 Mark 050) aeroplane, extensive damage was found on the left hand (LH) inner flap and nacelle. The damage had been caused by a broken fork of the inner flap outboard drive shaft. This resulted in asymmetric flap extension and interference between the flap and the nacelle. A metallurgical investigation showed that the fork end failed in a fatigue mode. Most probably the failure was caused by the ''cyclic load'' as a result of regularly reaching the mechanical end stop position. This condition, if not corrected, could lead to further cases of asymmetric flap extension, possibly resulting in loss of control of the aeroplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective August 20, 2009.

Airworthiness Directives; Boeing Model 767. Final rule. SUMMARY: This AD requires installing an automatic shutoff system for the auxiliary fuel tank override/jettison fuel pumps (also referred to as center tank fuel pumps in the airplane flight manual (AFM)), revising the AFM to advise the flightcrew of certain operating restrictions for airplanes equipped with an automatic auxiliary fuel tank pump shutoff control, and, for certain airplanes, installing a placard to alert the flightcrew of certain fuel usage restrictions. This AD provides optional terminating actions for certain requirements. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent an overheat condition outside the center tank fuel pump explosion-resistance area that is open to the pump inlet, which could cause an ignition source for the fuel vapors in the fuel tank and result in fuel tank explosions and consequent loss of the airplane. DATES: This AD is effective September 9, 2009.

Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500. Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. That AD currently requires repetitive inspections of the intercostal webs, attachment clips, and stringer splice channels for cracks; and corrective action if necessary. This new AD reduces the repetitive inspection intervals from 25,000 flight cycles to 6,000 flight cycles, and expands the inspection area for Model 737-200C series airplanes to include the area aft of the forward entry door. This AD results from additional reports of fatigue cracks. We are issuing this AD to detect and correct fatigue cracking of the intercostals on the forward and aft sides of the forward entry door, which could result in loss of the forward entry door and rapid decompression of the airplane. DATES: This AD becomes effective September 9, 2009.

Airworthiness Directives; Agusta Model AB139 and AW139 Helicopters. 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 aviation authority of Italy, with which we have a bilateral agreement, states in the MCAI that during the installation of a fire extinguisher bottle on a new helicopter, it was found that the electrical receptacle/connectors on the bottle which commands the firing of the extinguishing agent were swapped between engines No. 1 and No. 2. This condition could affect helicopters already in service and fire extinguisher bottles of the same part number in stock as spare parts. If not corrected, an improperly wired fire extinguishing bottle might cause the extinguishing agent to be discharged toward the unselected engine when the system is activated, rather than toward the engine with the fire. This AD requires determining if each engine has the proper outlet end on the electrical receptacle/connector that attaches the firing cartridge to the fire extinguisher bottle, and if not, replacing the fire extinguisher bottle. This AD is intended to prevent the fire extinguishing agent from not discharging toward the engine with the fire, which could result in loss of the helicopter due to an engine fire. DATES: This AD becomes effective on September 9, 2009.

Airworthiness Directives; SOCATA Model TBM 700. 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: This Airworthiness Directive (AD) was prompted by reports of loose rivets on frames C18 BIS and C19, which could result in a reduced structural integrity of the tail area. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective September 9, 2009.