Department of Transportation March 30, 2005 – Federal Register Recent Federal Regulation Documents
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Special Conditions: Bombardier Aerospace Models BD-700-1A10 and BD-700-1A11 Global Express Airplanes; Enhanced Flight Visibility System (EFVS)
This notice proposes special conditions for the Bombardier Aerospace Models BD-700-1A10 and BD-700-1A11 Global Express airplanes. These airplanes, as modified by Bombardier Aerospace Corporation, will have an Enhanced Flight Visibility System (EFVS). The EFVS is a novel or unusual design feature which consists of a head up display (HUD) system modified to display forward-looking infrared (FLIR) imagery. The regulations applicable to pilot compartment view do not contain adequate or appropriate safety standards for this design feature. These proposed special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that provided by the existing airworthiness standards.
Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ Series Airplanes
The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ series airplanes. The existing AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This proposed AD would also require revising the ALS of the Instructions for Continued Airworthiness to incorporate new and more restrictive life limits for certain items and new and more restrictive inspections to detect fatigue cracking in certain structures. This proposed AD is prompted by issuance of a later revision to the airworthiness limitations of the BAe/Avro 146 Aircraft Maintenance Manual, which specifies new inspections and compliance times for inspection and replacement actions. We are proposing this AD to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Series Airplanes
The FAA proposes to adopt a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes. This proposed AD would require modifying the auxiliary power unit (APU) exhaust duct in the environmental control system (ECS) bay; installing new, improved insulation on this APU exhaust duct; and replacing the existing drain pipe with a new exhaust drain pipe blank. This proposed AD is prompted by a determination that the temperature of the skin of the APU exhaust duct in the ECS bay is higher than the certificated maximum temperature for this area. We are proposing this AD to prevent the potential for ignition of fuel or hydraulic fluid, which could leak from pipes running through the ECS bay. Ignition of these flammable fluids could result in a fire in the ECS bay.
Airworthiness Directives; Bombardier Model DHC-8-102, -03, -106, -201, -202, -301, -311, and -315 Airplanes
The FAA proposes to adopt a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, - 311 and -315 airplanes. This proposed AD would require installation of check valves in Numbers 1 and 2 hydraulic systems, removal of the filters from the brake shuttle valves, and removal of the internal garter spring from the brake shuttle valves. This proposed AD results from two instances of brake failure due to the loss of hydraulic fluid from both Numbers 1 and 2 hydraulic systems and one incident of brake failure due to filter blockage in the shuttle valve. We are proposing this AD to prevent the loss of hydraulic power from both hydraulic systems which could lead to reduced controllability of the airplane; and to prevent brake failure which could result in the loss of directional control on the ground and consequent departure from the runway during landing.
Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 and -135 Series Airplanes
The FAA proposes to adopt a new airworthiness directive (AD) for certain EMBRAER Model EMB-145 and -135 series airplanes. This proposed AD would require replacing the horizontal stabilizer control unit (HSCU) with a modified and reidentified or new, improved HSCU. For certain airplanes, this proposed AD would also require related concurrent actions as necessary. This proposed AD is prompted by reports of loss of the pitch trim system due to a simultaneous failure of both channels of the HSCU. We are proposing this AD to prevent loss of pitch trim and reduced controllability of the airplane.
Airworthiness Directives; Boeing Model 707-300B, -300C, and -400 Series Airplanes
The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 707-300B, -300C, and -400 series airplanes. This proposed AD would require repetitive inspections to detect cracked or broken hinge fitting assemblies of the inboard leading edge slats, and corrective action if necessary. This proposed AD would provide as an option a preventive modification, which would defer the repetitive inspections. This proposed AD also would provide an option of replacing all hinge fitting assemblies with new, improved parts, which would terminate the repetitive inspection requirements. This proposed AD is prompted by results of a review to identify and implement procedures to ensure the continued structural airworthiness of aging transport category airplanes. We are proposing this AD to detect and correct fatigue cracking of the hinge fitting assembly of the inboard leading edge slats, which could result in reduced structural integrity of the slat system. This condition could result in loss of the inboard leading edge slat and could cause the flightcrew to lose control of the airplane.
Airworthiness Directives; Boeing Model 757-200, -200CB, and -200PF Series Airplanes
The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 757-200, -200CB, and -200PF series airplanes. This proposed AD would require an inspection of each trailing edge flap transmission assembly to determine the part number and serial number, and related investigative and corrective actions and part marking if necessary. This proposed AD is prompted by a report indicating that cracked flap transmission output gears have been discovered during routine overhaul of the trailing edge flap transmission assemblies. We are proposing this AD to prevent an undetected flap skew, which could result in a flap loss, damage to adjacent airplane systems, and consequent reduced controllability of the airplane.
Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 Series Airplanes
The FAA proposes to adopt a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 series airplanes. This proposed AD would require repetitive inspections for cracks of the fuselage pressure skin above the left and right main landing gear (MLG) bay. This proposed AD also would require corrective action, including related investigative actions, if leaks are found. This proposed AD is prompted by reports of cracks in the fuselage pressure skin above the left and right MLG bay. We are proposing this AD to detect and correct fatigue cracking in the fuselage pressure skin above the left and right MLG bay; such fatigue cracking could adversely affect the structural integrity of the fuselage and its ability to maintain pressure differential.
Airworthiness Directives; Bombardier Model DHC-8-400, -401, and -402 Airplanes
The FAA proposes to adopt a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400, -401, and -402 airplanes. This proposed AD would require repetitive inspections to detect discrepancies of the attachment fittings of the outboard flap front spar at flap track Number 4 and Number 5 locations, and corrective actions if necessary. This proposed AD also would require eventual replacement of the attachment fittings as terminating action for the repetitive inspections. This proposed AD is prompted by the discovery of several airplanes that have loose flap front spar attachment fittings at flap track Number 4 and Number 5 locations. We are proposing this AD to prevent the attachment fittings from becoming detached, and consequent loss of control of the airplane.
Airworthiness Directives; Airbus Model A321 Series Airplanes
The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A321 series airplanes. The existing AD currently requires revising the Limitations section of the airplane flight manual to include an instruction to use Flap 3 for landing when performing an approach in conditions of moderate to severe icing, significant crosswind (i.e., crosswinds greater than 20 knots, gust included), or moderate to severe turbulence. This proposed AD would require replacing existing elevator and aileron computers (ELAC) with ELACs having either L83 or L91 software, as applicable, which would terminate the requirements of the existing AD. This proposed AD would also require a related concurrent action. In addition, this proposed AD would revise the applicability by removing airplanes with these ELAC software standards incorporated in production. This proposed AD is prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority. We are proposing this AD to prevent roll oscillations during approach and landing in certain icing, crosswind, and turbulent conditions, which could result in reduced controllability of the airplane.
Airworthiness Directives; Bombardier Model DHC-8-101, -102, -103, -106, -201, -202, -301, -311, and -315 Airplanes
The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Bombardier Model DHC-8-101, -102, - 103, -106, -201, -202, -301, -311, and -315 airplanes. The existing AD currently requires installation of a placard on the instrument panel of the cockpit to advise the flightcrew that positioning of the power levers below the flight idle stop during flight is prohibited. Additionally, the existing AD requires eventual installation of an FAA- approved system that would prevent such positioning of the power levers during flight. Installation of that system terminates the requirement for installation of a placard. This proposed AD would require operators who have incorporated a certain Bombardier service bulletin to perform repetitive operational checks of the beta lockout system and to revise the Airworthiness Limitations document. This proposed AD is prompted by in-service issues reported by operators who incorporated Bombardier Service Bulletin 8-76-24 as an alternative method of compliance to the existing AD. We are proposing this AD to prevent the inadvertent activation of ground beta mode during flight, which could lead to engine overspeed, engine damage or failure, and consequent reduced controllability of the airplane.
Notice of Request for the Extension of Currently Approved Information Collection
In accordance with the Paperwork Reduction Act of 1995, this notice announces the intention of the Federal Transit Administration (FTA) to request the Office of Management and Budget (OMB) to extend the following currently approved annual information collection and approve the addition of the collection of some monthly data requested by Congress: 49 U.S.C. Sec. 5335(a) and (b) National Transit Database.
Membership in the Grand Canyon Working Group of the National Parks Overflights Advisory Group Aviation Rulemaking Committee
The Federal Aviation Administration (FAA) and the National Park Service (NPS) are establishing a Grand Canyon Working Group within the National Parks Overflights Advisory Group (NPOAG) to provide advice and recommendations regarding the implementation of the National Parks Overflights Act of 1987 with respect to the Grand Canyon. To the extent that recommendations involve aviation rulemaking, the Working Group will also participate in the development of the rule(s). This notice informs the public of the establishment of the Grand Canyon Working Group, describes its structure and qualifications for membership, and provides for nominations for membership in the Working Group.
Advanced Qualification Program
The FAA is proposing to codify the requirements of the Advanced Qualification Program (AQP). The AQP would continue as a regulatory alternative program to the traditional training program. AQP would continue to be an alternative for airlines that seek more flexibility in training than the traditional training program allows. Currently, the AQP requirements are in a Special Federal Aviation Regulation that expires on October 2, 2005. The intended effect of this proposal is to make AQP a permanent, alternative method of complying with FAA's training requirements for carriers.
Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to the airplane models listed above. That AD currently requires repetitive inspections to detect discrepancies of the transfer tubes and the collar of the ball nut of the trimmable horizontal stabilizer actuator (THSA), and corrective action if necessary. This amendment expands the applicability of the existing AD; and requires new repetitive inspections for discrepancies of the ball screw assembly; corrective action if necessary; repetitive greasing of the THSA ball nut, and replacement of the THSA if necessary; and a modification or replacement (as applicable) of the ball nut assembly, which would end certain repetitive inspections. The actions specified by this AD are intended to prevent degraded operation of the THSA due to the entrance of water into the ball nut. Degraded operation could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
Airworthiness Directives; Boeing Model 777-200 and -300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 777-200 and -300 series airplanes. This AD requires inspection of the outer cylinder of the main landing gear (MLG) to determine the serial number; an ultrasonic inspection of the outer cylinder of the MLG for cracks if necessary; and applicable specified and corrective actions if necessary. This AD is prompted by reports indicating that two outer cylinders were found fractured in the weld area. We are issuing this AD to detect and correct cracks or defects that could result in a fracture of the outer cylinder of the MLG, which could lead to collapse of the MLG during landing.
Airworthiness Directives; McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; and Model DC-9-81 (MD-81) and DC-9-82 (MD-82) Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; and Model DC-9-81 (MD-81) and DC-9-82 (MD-82) airplanes. This AD requires repetitive detailed inspections of the upper and lower caps of the rear spar of the left and right wings, and corrective action if necessary. This AD also provides an optional modification that would end the repetitive inspections. This AD is prompted by reports of fatigue cracks in the upper and lower caps of the wing spar. We are issuing this AD to detect and correct fatigue cracking in the upper and lower caps of the rear spar of the left and right wings, which could result in structural failure of the wings.
Airworthiness Directives; General Electric Company CF6-45A, CF6-50A, CF6-50C, and CF6-50E Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-45A, CF6-50A, CF6-50C, and CF6-50E series turbofan engines that have not incorporated GE Service Bulletin (SB) No. CF6-50 S/B 72-1239, Revision 1, dated September 24, 2003, or that have not incorporated paragraph 3.B. of GE SB No. CF6-50 S/B 72- 1239, original issue, dated May 29, 2003. This AD requires inspecting the stage 1 low pressure turbine (LPT) blades for damage and replacement of the LPT module if necessary. This AD results from a report of a stud that separated from a turbine mid frame (TMF) strut and from an updated analysis of strut stud failures. We are issuing this AD to prevent uncontained failure of the engine and possible damage to the airplane caused by failure of TMF strut studs.
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