Federal Aviation Administration May 8, 2006 – Federal Register Recent Federal Regulation Documents
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Petitions for Exemption; Summary of Petitions Received
Pursuant to FAA's rulemaking provisions governing the application, processing, and disposition of petitions for exemption part 11 of Title 14, Code of Federal Regulations (14 CFR), this notice contains a summary of certain petitions seeking relief from specified requirements of 14 CFR. The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of FAA's regulatory activities. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of any petition or its final disposition.
Airworthiness Directives; Cirrus Design Corporation Model SR20 and SR22 Airplanes
The FAA proposes to adopt a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Model SR20 and SR22 airplanes. This proposed AD would require you to check the maintenance records to determine whether the brake caliper piston O-ring seals were replaced at the last annual or 100-hour inspection. If the O-rings were not replaced, this proposed AD would require you to replace the O-ring seals with new seals or replace brake calipers. This proposed AD would also require you to modify the main landing gear wheel fairings to add temperature indicator sticker inspection holes, trim the wheel fairings to prevent them from holding fluids, install temperature indicator stickers on the brake calipers, and insert Revision A6 (with revised preflight walk-around and taxi procedures) into the Pilot's Operating Handbook (POH). This proposed AD results from several reports of airplanes experiencing brake fires and two airplanes losing directional control. We are issuing this proposed AD to detect, correct, and prevent overheating damage to the brake caliper piston O-ring seals, which could result in leakage of brake hydraulic fluid. Consequently, this could lead to the loss of braking with loss of airplane directional control or brake fire.
Airworthiness Directives; Airbus Model A319-100 and A320-200 Series Airplanes; and Model A320-111 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-100 and A320-200 series airplanes, and Model A320-111 airplanes. This AD requires modifying the wiring to the fuel pump control of the center fuel tank. This AD results from reports that the low-pressure warning for the fuel pumps of the center fuel tank has come on in flight. We are issuing this AD to ensure that the fuel pumps do not run while dry, which could result in a potential ignition source inside the center fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that currently requires installation of protective tape on the fire and overheat control unit located in the flight compartment. This amendment requires the installation of protective tape and adds repetitive inspections of the condition of the protective tape and related corrective action. This amendment also mandates eventual replacement of the existing fire and overheat control unit with a modified unit, which ends the repetitive inspections. Additionally, this amendment adds airplanes to the applicability in the existing AD. The actions specified by this AD are intended to prevent fluid contamination inside the fire and overheat control unit, which could result in a false fire alarm and consequent emergency landing. This action is intended to address the identified unsafe condition.
Airworthiness Directives; Boeing Model 747 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747 airplanes. This AD requires the following actions for the drive mechanism of the horizontal stabilizer: Repetitive detailed inspections for discrepancies and loose ball bearings; repetitive lubrication of the ballnut and ballscrew; repetitive measurements of the freeplay between the ballnut and the ballscrew; and corrective action if necessary. This AD results from a report of extensive corrosion of a ballscrew in the drive mechanism of the horizontal stabilizer on a similar airplane model. We are issuing this AD to prevent an undetected failure of the primary load path for the ballscrew in the horizontal stabilizer and subsequent wear and failure of the secondary load path, which could lead to loss of control of the horizontal stabilizer and consequent loss of control of the airplane.
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