Federal Aviation Administration March 23, 2007 – Federal Register Recent Federal Regulation Documents

We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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:

The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, and -106 airplanes and Model DHC-8-200 and DHC-8-300 series airplanes. This AD requires modifying the main landing gear (MLG) and nose landing gear (NLG) handle assemblies for alternate release and the MLG retaining plate. This AD also requires doing a related investigative action and corrective action if necessary. This AD results from reports of broken or damaged MLG and NLG alternate release cables caused by rubbing and fraying at the cable-to-handle interface. We are issuing this AD to prevent breakage of the MLG and NLG alternate release cables, which, if the normal gear extension fails, could result in the inability to extend the MLG or NLG and consequent collapse of the landing gear during ground maneuvers or upon landing.

This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2006-26-51, which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 C-2 helicopters by individual letters. This AD requires, before further flight, marking the position of the tail rotor control lever dynamic weights (weights), removing the split pins and the weights, and visually inspecting and replacing, if necessary, the tail rotor control lever before further flight. This AD also requires, within 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 25 hours TIS, repeating the visual inspection of the tail rotor control lever and replacing any unairworthy tail rotor control lever with an airworthy tail rotor control lever before further flight. Also required is reassembling the tail rotor control lever by following the appropriate maintenance instruction. This amendment is prompted by an in-flight incident in which the threaded portion of the tail rotor control lever containing a dynamic weight broke off leading to severe vibrations. The actions specified by this AD are intended to prevent separation of the weights in flight, severe vibration, and subsequent loss of control of the helicopter.

The FAA invites public comments about our intention to request the Office of Management and Budget (OMB) to approve a current information collection. Title 49 U.S.C. Section 44936(f) mandates that airlines must obtain safety records of prospective employees from the FAA and from previous air carrier employers, and the National Driver Register, before an offer of employment is made.