Federal Aviation Administration February 14, 2005 – Federal Register Recent Federal Regulation Documents

This notice announces the issuance of Advisory Circular (AC) 23-22. This advisory circular (AC) sets guidelines for using the Approved Model List (AML) Supplemental Type Certificate (STC) process for the installation approval of avionics for 14 CFR, part 23 airplanes. It also applies to airplanes certified under a prior certification basis, such as CAR 3 or bulletin 7-A. Guidance provided in this AC applies only to avionics installations using the AML STC process. For other types of modifications to part 23 airplanes seeking to use the AML STC process, the Aircraft Certification Office (ACO) should coordinate with the Small Airplane Directorate. Avionics AML STC guidance provided in this AC addresses the following: (1) Avionics eligible for the AML STC process, (2) Model Qualification Process used by the STC holder and the FAA to either create or edit the AML, and (3) Level of Detail required for the installation instructions for an AML STC, including a list of acceptable equipment that can be integrated under the STC. Material in this AC is neither mandatory nor regulatory in nature and does not constitute a regulation. In addition, this material is not to be construed as having any legal status and should be treated accordingly. However, it is designed to provide standardization guidelines for AML STC approvals. The AML STC process may be used whenever the ACO and the applicant agree that it is suitable. This AC is not applicable to any products certified under part 25, 27, or 29. The draft advisory circular was issued for Public Comment on October 8, 2004 (69 FR 60452). When possible, comments received were used to modify the draft advisory circular.

This notice announces glider towing as a restricted category special purpose operation under Title 14 of the Code of Federal Regulations (14 CFR) Sec. 21.25(B)(7), for aircraft type certificated under 14 CFR 21.25(a)(1).

The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This proposed AD would require repetitive inspections of the dual side braces (DSBs), underwing midspar fittings, and associated parts; other specified actions; and corrective actions if necessary. This proposed AD also provides an optional terminating action for the inspections and other specified actions. This proposed AD is prompted by reports of corroded, migrated, and rotated bearings for the DSBs in the inboard and outboard struts, a report of a fractured retainer for the eccentric bushing for one of the side links of a DSB, and reports of wear and damage to the underwing midspar fitting on the outboard strut. We are proposing this AD to prevent the loss of a DSB or underwing midspar fitting load path, which could result in the transfer of loads and motion to other areas of a strut, and possible separation of a strut and engine from the airplane during flight.

This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 helicopters that requires removing and modifying the fuel bleed lever. This amendment is prompted by some cases of loss of the fuel bleed lever in flight. If the tension of the control cable is too low, the cable may vibrate out of its notch, resulting in the fuel bleed lever separating from the hinge. The actions specified by this AD are intended to prevent a fuel bleed lever from separating and striking the tail rotor blade (blade), resulting in damage to or loss of a blade, and subsequent vibration and loss of control of the helicopter.

This amendment supersedes an existing airworthiness directive (AD) that applies to all Airbus Model A300 B2 and B4 series airplanes. The existing AD currently requires determining the part and amendment number of the variable lever arm (VLA) of the rudder control system to verify the parts were installed using the correct standard, and corrective actions if necessary. For certain VLAs, this new AD requires repetitive inspections of the VLA and corrective action if necessary. This new AD also provides a terminating action for the repetitive inspections. Furthermore, this new AD reduces the applicability of affected airplanes. The actions specified by this AD are intended to prevent failure of both spring boxes of certain VLAs due to corrosion damage, which could result in loss of rudder control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.

The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model DH.125, HS.125, and BH.125 series airplanes; BAe.125 series 800A (C-29A and U-125) and 800B airplanes; and Hawker 800 (including variant U-125A) and 800XP airplanes. This AD requires installing insulating blankets on the engine compartment firewall and the wire harness passing through the firewall fairlead. This AD is prompted by a report indicating that insulation on the wire harness passing through the firewall fairlead ignited on the fuselage side of the firewall. We are issuing this AD to prevent a fire in the engine compartment from causing possible ignition of outgassing wire insulation on the fuselage side of the firewall, which could lead to an uncontrollable fire in the fuselage.