Emergency Airworthiness Directive. 2008-19-51 This emergency airworthiness directive (AD) is sent to all owners and operators of Rolls-Royce AE 3007A series turbofan engines. These engines are installed on, but not limited to EMBRAER EMB-135 and EMB-145 aircraft. This emergency AD results from reports of cracked high-pressure turbine (HPT) stage 2 wheels. This condition, if not corrected, could result in a possible uncontained failure of the HPT stage 2 wheel, which could cause damage to the airplane. We have reviewed RRC Alert Service Bulletin (ASB) AE 3007A-A-72-367, dated September 5, 2008. The ASB describes procedures for eddy current inspection (ECI) of the HPT stage 2 wheel on AE 3007A series engines.

Aviation Rulemaking Advisory Committee Meeting on Transport Airplane and Engine Issues. Notice of Public Meeting. SUMMARY: This notice announces a public meeting of the FAA's ARAC to discuss transport airplane and engine (TAE) issues. The meeting is scheduled for Wednesday, October 1, 2008, starting at 9 a.m. Pacific Daylight Time. Arrange for oral presentations by September 16, 2008. ADDRESSES: FAA-Northwest Mountain Region Office, Transport Standards Staff Conference Room, 1601 Lind Ave. SW., Renton, WA 98507.

Airworthiness Standards; Engine Control System Requirements Final rule. SUMMARY:The FAA is amending type certification standards for aircraft engine control systems. These changes reflect current industry practices and harmonize FAA standards with those recently adopted by the European Aviation Safety Agency (EASA). These changes establish uniform standards for all engine control systems for aircraft engines certificated by both U.S. and European countries and will simplify airworthiness approvals for import and export.

Airworthiness Directive. EMBRAER Model ERJ 170 and ERJ 190. 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: It has been found cases where the pressure equalization valve was not installed in the left-hand bulkhead blowout panel, on the forward and/or aft cargo compartments, thus affecting the effectiveness of fire detection, containment and suppression.

Airworthiness Directive. Airbus A330-200, A330-300, and A340-300. 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 manufacturing of A330/A340 aircraft framework, cracks have been found on Frame (FR) 12, left (LH) and right (RH) sides. It has been confirmed that a defect of the FR12 forming tool press is the root cause of the cracks. If undetected such damage could affect, after propagation, the structural integrity of the aircraft.

Airworthiness Directive: Bombardier DHC-8-400. Final Rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Bombardier Model DHC-8-400 series airplanes. That AD currently requires inspecting all barrel nuts to determine if the barrel nuts have a certain marking, inspecting affected bolts to determine if the bolts are pre-loaded correctly, and replacing all hardware if the pre-load is incorrect. For airplanes on which the pre-load is correct, the existing AD requires doing repetitive visual inspections for cracking of the barrel nuts and cradles and replacing all hardware for all cracked barrel nuts. The existing AD also requires replacing all hardware for certain affected barrel nuts that do not have cracking, which would end the repetitive inspections for those airplanes. The existing AD also provides an optional replacement for all affected barrel nuts. This new AD requires replacing all affected barrel nuts and applying a certain compound to the affected barrel nuts and bolts. This AD results from reports of cracking in the barrel nuts at the four primary front spar wing-to-fuselage attachment joints. We are issuing this AD to detect and correct cracking of the barrel nuts at the wing front spar wing-to-fuselage joints, which could result in reduced structural integrity of the wing-to- fuselage attachments and consequent detachment of the wing.

Airworthiness Directive: McDonnell Douglas Model 717-200. Final Rule. SUMMARY: This AD requires inspecting the drive assembly of the aft elevator standby loop of the elevator standby cable system for interference between the clevis and bolt of the bellcrank assembly, correct orientation of the pull-pull cable clevis bolt, and excessive freeplay of the bellcrank assembly bearing, and corrective actions if necessary. This AD also requires modifying the pull-pull cable clevis in the drive assembly of the aft elevator standby loop for certain airplanes. This AD results from a report of an aborted takeoff due to a control column disconnect. We are issuing this AD to prevent binding of the bolt that connects the cable 264A clevis to the bellcrank assembly against the adjacent (upper) clevis of the pull-pull cable assembly. This binding condition could result in slow airplane rotation or a control column disconnect during takeoff and a runway excursion if takeoff must be aborted.

Airworthiness Directive: Rolls-Royce RB211 Trent 500, 700, and 800 Series Turbofan Engines. 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 action is necessary following the discovery of IP Compressor Rotor rear balance land cracking on an in-service Trent 800 engine. Stress analysis of the damaged rotor has shown a possible threat to the rotor integrity, the cracking therefore presents a potential unsafe condition. We are issuing this AD to detect cracking on the intermediate pressure (IP) compressor rotor rear balance land. IP compressor rotor rear balance land cracking can lead to uncontained failure of the rotor and damage to the airplane.

Airworthiness Directive: McDonnell Douglas MD-90-30. Final Rule; Request for Comments. SUMMARY: This AD requires a detailed inspection for certain defects of the upper fasteners of the aft mount support fitting of the left and right engines and corrective actions if necessary. This AD results from reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines. We are issuing this AD to detect and correct loose, cracked, or missing fasteners in the engine aft support mount fitting, which could lead to separation of the support fitting from the pylon, which could result in separation of the engine from the airplane.