Federal Aviation Administration January 2008 – Federal Register Recent Federal Regulation Documents

Results 151 - 152 of 152
Airworthiness Directives; Lycoming Engines, Fuel Injected Reciprocating Engines
Document Number: E7-25456
Type: Proposed Rule
Date: 2008-01-02
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to supersede an existing airworthiness directive (AD) for certain fuel injected reciprocating engines manufactured by Lycoming Engines. That AD currently requires inspection, and replacement if necessary, of externally mounted fuel injector fuel lines. This proposed AD would require the same actions but would add additional engine models, would clarify certain compliance time wording, and would exempt engines that have a Maintenance and Overhaul Manual with an Airworthiness Limitations Section that requires inspection, and replacement if necessary, of externally mounted fuel injector lines. This proposed AD results from Lycoming Engines revising their Mandatory Service Bulletin (MSB) to add new engine models requiring inspection, and from the need to clarify a repetitive inspection compliance time. We are proposing this AD to prevent failure of the fuel injector fuel lines that would allow fuel to spray into the engine compartment, resulting in an engine fire.
Airworthiness Directives; Bell Helicopter Textron Canada Model 430 Helicopters
Document Number: E7-25389
Type: Rule
Date: 2008-01-02
Agency: Federal Aviation Administration, Department of Transportation
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires replacing a certain servo actuator-to-actuator support attachment bolt (bolt) with an airworthy bolt. This action also requires establishing a retirement life for certain bolts and recording the retirement life on a component history card or equivalent record. This amendment is prompted by further evaluation of certain fatigue- critical parts, resulting in establishing a life limit of 5,000 hours for the affected bolts. The actions specified by this AD are intended to prevent fatigue failure of the bolt and subsequent loss of control of the helicopter.
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