Department of Transportation August 11, 2008 – Federal Register Recent Federal Regulation Documents

These special conditions are issued for the Embraer S.A. Model ERJ 190-100 ECJ airplane. This airplane will have novel or unusual design features associated with access during flight of the main deck Class C cargo compartment. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all AvCraft Dornier Model 328-300 airplanes. The existing AD currently requires modifying the electrical wiring of the fuel pumps; installing insulation at the flow control and shut-off valves, and other components of the environmental control system; installing markings at fuel wiring harnesses; replacing the wiring harness of the auxiliary fuel system with a new wiring harness; and installing insulated couplings in the fuel system; as applicable. The existing AD also requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new inspections of the fuel tank system. This proposed AD would replace the flight-hour-based threshold for conducting certain initial inspections, with a calendar-based threshold. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.

This action modifies Class E Airspace at Rome, New York to support the amendment of the current Terminal Visual Flight Rule (VFR) Radar Service Area (TRSA) and to allow for a lower vectoring altitude known as the Minimum Vectoring Altitude (MVA) for vectoring of both VFR and Instrument Flight Rule (IFR) aircraft around the Rome, NY area. This action will enhance the safety and airspace management around the Griffiss Airport area.

We are adopting a new airworthiness directive (AD) for BHTC Model 222, 222B, and 222U helicopters. 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 aviation authority of Canada, with which we have a bilateral agreement, states in the MCAI: ``It has been determined that the existing rigging procedures for the tail rotor pitch change mechanism have to be changed due to possibility of parts interference.'' The cumulative effect of individual part tolerances resulting in the total assemblage of those parts being out of tolerance could result in the tail rotor yoke striking another part other than the flapping stop (parts interference) cited in the MCAI. Also, the misalignment of the tail rotor counterweight bellcrank may result in higher tail rotor pedal forces and a higher pilot workload after failure of the No. 1 hydraulic system. Both parts interference and the misaligned counterweight bellcrank create an unsafe condition. We are issuing this AD to require actions that are intended to address these unsafe conditions.

The FAA is superseding two existing airworthiness directives (ADs), which apply to all Short Brothers Model SD3-60 airplanes. One of the ADs currently requires inspection of the welded joints of the balance weight brackets for the elevator trim tabs for cracking; repetitive inspections, as applicable; and corrective actions including the eventual replacement of all brackets. The other AD currently requires, for certain airplanes, repetitive inspections for cracking of the balance weight brackets and replacement of any cracked bracket, and provides for an optional terminating action for the repetitive inspections. This new AD requires an additional inspection to detect cracks of the balance weight brackets, applicable related investigative and corrective actions, and replacement of a certain balance weight bracket when it has reached its maximum life limit. This AD results from a report indicating that several reworked balance weight brackets have exhibited signs of premature failure. We are issuing this AD to prevent failure of the balance weight brackets of the elevator trim tabs, which could cause loss of the balance weight. This could result in incorrect trim during takeoff and landing, and reduced controllability of the airplane.