Federal Aviation Administration January 20, 2006 – Federal Register Recent Federal Regulation Documents
Results 1 - 6 of 6
Airworthiness Directives; Eurocopter France Model EC155B and B1 Helicopters; Correction
This document corrects a docket number in an NPRM that was published in the Federal Register on October 17, 2005 (70 FR 60244). The NPRM applies to Eurocopter France Model EC155B and B1 helicopters. The NPRM proposed to require inspecting an electrical cable bundle for wear and, if necessary, installing an airworthy cable bundle and modifying the routing of the electrical cable bundles.
Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes. This AD requires installing a rivet and washer in the hole of the upper frame of the auxiliary power unit (APU) firewall. This AD results from a report indicating that, during production, a pinhole was left open at the upper frame of the APU firewall. We are issuing this AD to ensure that the APU compartment is isolated from the rest of the airplane in the event of an APU fire.
Airworthiness Directives; Raytheon Model Hawker 800XP Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model Hawker 800XP airplanes. This AD requires inspecting to determine if the correct fuse is installed on the hydraulic over-temperature switch on panel ZK in the rear equipment bay, and replacing the existing fuse if necessary. This AD results from a report of the installation of an incorrect fuse on the over- temperature switch on panel ZK in the rear equipment bay during airplane maintenance. We are issuing this AD to prevent a short circuit in the fuse and consequent heat damage to associated wiring and surrounding equipment, which could result in smoke or fire on the airplane.
Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, & CL-604) airplanes. This AD requires modifying the rudder balance spring assembly by installing a new adjustable balance spring, and rigging the assembly to suit the rudder of each airplane. This AD results from production inspections that showed that the spring assembly that controls rudder balance may not have the correct pre-load on some airplanes. We are issuing this AD to prevent uncommanded yaw movements and consequent reduced controllability of the airplane.
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires replacing the Camloc fasteners on the sidewall of the center pedestal. This AD results from reports of the Camloc fasteners on the sidewall of the center pedestal disengaging and interfering with an inboard rudder pedal. We are issuing this AD to prevent these fasteners from disengaging and interfering with an inboard rudder pedal, which could reduce directional controllability of the airplane.
Airworthiness Directives; Airbus Model A310-203, -204, and -222 Airplanes, and Model A310-300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310-203, -204, and -222 airplanes, and Model A310-300 series airplanes. This AD requires a one-time rototest inspection for cracking of the frame foot and adjacent frames and skin in the area surrounding the frame foot run-outs from fuselage frames (FR) 43 through FR 46, and repair if necessary. This AD also requires modification of certain fastener holes. This AD results from a structural evaluation of Model A310 airplanes for widespread fatigue damage of the frame foot run-outs from FR 43 through FR 46. The evaluation revealed that, on in-service airplanes, undetected cracking in this area can lead to the rupture of the frame foot and subsequent cracking of the adjacent frames and fuselage skin. We are issuing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and result in reduced structural integrity of the fuselage.
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