Safety Rules & Regs

Airworthiness Directives; Airbus Model A300 Airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310. Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to the airplanes identified above. That AD currently requires revising the FAA-approved maintenance program to include a new airplane maintenance manual task that specifies a detailed inspection after each ram air turbine (RAT) retraction. That existing AD also currently requires, for certain airplanes, a one-time inspection to detect breaks in the bottom flange fitting of the RAT and corrective actions, if necessary; for certain airplanes, an adjustment of the ejection jack; and, for certain other airplanes, replacement of the aluminum part with an improved steel part. This AD also continues to require certain actions for additional airplanes and revising the FAA-approved maintenance program to include procedures for replacing the RAT swivel coupling fork fitting with a new steel part only. This AD results from a report that an additional swivel coupling of the RAT yoke fitting was found cracked during the accomplishment of the requirements of the existing AD. We are issuing this AD to prevent misrigging of the ejection jack of the RAT and to ensure removal of any RAT yoke fitting made from aluminum material. Such conditions could result in a broken or cracked swivel coupling and consequent failure of the RAT yoke fitting, which could result in the loss of RAT function and possible loss of critical flight control systems in the event of certain emergency situations. DATES: This AD becomes effective July 24, 2009.

Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ. Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD). That AD currently requires repetitive inspections for corrosion of frames 15, 18, 41, and 43 and applicable related investigative and corrective actions. The existing AD also provides an optional action that would extend the repetitive inspection interval. This new AD also requires a high frequency eddy current inspection for corrosion of the outer frame flanges and door hinge bosses of frames 15, 18, 41, and 43. This AD results from a report indicating that corrosion has been detected in the outer frame flanges and door hinge bosses during scheduled maintenance. We are issuing this AD to prevent reduced structural integrity of the airplane. DATES:This AD becomes effective July 24, 2009.

Airworthiness Directives; Airbus Model A340-541 and -642. 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: Following a refined Finite Element Model (FEM) analysis of the Nose Landing Gear (NLG) actuator fitting installed on the roof panel of the NLG box of all A340-500/- 600 aircraft, it has been demonstrated that potential fatigue cracks can be initiated on the NLG actuator fitting flanges. This situation, if not corrected, could lead to inadvertent extension of the NLG which could adversely affect the aircraft's continued safe flight or [could result in] failure to retract the NLG which, in combination with an engine failure, could adversely affect the aircraft's safe take off. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES:This AD becomes effective June 29, 2009.

Airworthiness Directives; ATR Model ATR42-500 and ATR72-212A. 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: Identification of an unsafe condition related to the loss of the fail-safe design criteria for the rudder trim, pitch trim and stick pusher control functions after a reported event led in April 2008 to the release of AD 2008-0062 to mandate the ATR modification No. 05780. It has appeared that some airplanes manufactured and delivered before April 1, 2008, may have received on the production-line a partial or incorrect implementation of the required ATR mod. No. 05780. The unsafe condition is loss of the rudder trim, pitch trim, and stick pusher control, which could result in 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 29, 2009.

Airworthiness Directives; Aeromot-Industria Mecanico Metalurgica ltda. Model AMT-200 and AMT-300 Series Gliders. 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: It has been found that the coolant liquid EVANS NPG + is a flammable fluid. The engine liquid cooling system of the affected Aeromot aircrafts is not designed to operate with flammable liquids. Therefore, there is an unacceptable engine fire risk associated with the use of Evans NPG + fluid. DATES:This AD becomes effective July 17, 2009.

Airworthiness Directives; Sikorsky Aircraft Corporation Model S-92A. Final rule; request for comments. SUMMARY: This amendment supersedes an existing airworthiness directive (AD) for Sikorsky Aircraft Model S-92A helicopters. That AD currently requires removing all main gearbox (MGB) filter bowl assembly mounting titanium studs (titanium studs) and replacing them with steel studs. This amendment requires the same actions as the existing AD as well as changes to the Rotorcraft Flight Manual (RFM). This amendment is prompted by an accident, by recent RFM changes made by the manufacturer that were not available when we issued the existing AD, and by our determination that certain MGB Normal and Emergency procedures in the RFM are unclear, may cause confusion, and may mislead the crew regarding MGB malfunctions, in particular the urgency to land immediately after warning indications of loss of MGB oil pressure and oil pressure below 5 pounds per square inch (psi). Replacing the titanium studs is intended to prevent their failure, which could result in rapid loss of oil, failure of the MGB, and subsequent loss of control of the helicopter. Changing the RFM procedures is intended to clarify and emphasize certain Normal and Emergency procedures to give the crew the best available information in the event of certain MGB malfunctions. DATES: Effective July 1, 2009.

Airworthiness Directives; Dornier Luftfahrt GmbH Models Dornier 228-100, Dornier 228-101, Dornier 228-200, Dornier 228-201, Dornier 228-202, and Dornier 228-212. 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: Excessive wear on a guide pin of a power lever has been detected during inspections. The total loss of the pin could cause loss of the flight idle stop and lead to inadvertent activation of the beta mode in flight. The inadvertent activation ofbeta mode in flight can result in loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES:This AD becomes effective July 24, 2009.

Airworthiness Directives; SOCATA Model TBM 700. Final rule; request for comments. SUMMARY:This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During a SOCATA flight test, it has been noted some difficulties for the pilot to release oxygen. After investigation it has been found that, due to the design of the oxygen generator release pin, one of the mask's lanyard linked to the pin can be jammed when it is pulled by a pilot or a passenger. This condition, if not corrected, would lead, in case of an emergency procedure due to decompression to a risk of generator fault with subsequent lack of oxygen on crew and/or passenger. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective July 9, 2009.

Airworthiness Directives; Piper Aircraft, Inc. PA-23, PA-31, and PA-42. Final rule. This AD establishes life limits for safety-critical nose baggage door components. This AD also requires you to replace those safety-critical nose baggage door components and repetitively inspect and lubricate the nose baggage door latching mechanism and lock assembly. This AD results from several incidents and accidents, including fatal accidents, where the nose baggage door opening in flight was listed as a causal factor. We are issuing this AD to detect and correct damaged, worn, corroded, or non-conforming nose baggage door components, which could result in the nose baggage door opening in flight. The door opening in flight could significantly affect the handling and performance of the aircraft. It could also allow baggage to be ejected from the nose baggage compartment and strike the propeller. This failure could lead to loss of control. DATES: This AD becomes effective on July 24, 2009.

Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343. 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 receipt of spare parts at the final assembly line, it was discovered that lugs of the assembly nut had been inverted (wrong orientation of the braking pin) during manufacturing process at the supplier. This lug inversion could give the illusion of correct torque whereas the affected parts are not properly connected. Loose connection could lead to loss of the fire extinguishing system integrity and therefore inability to ensure the adequate agent concentration. In combination with an engine fire event, it could result in a temporary uncontrolled engine fire, which constitutes an unsafe condition. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective July 24, 2009.