Federal Aviation Administration March 2005 – Federal Register Recent Federal Regulation Documents

This notice is provided to inform the aviation community that effective immediately, the FAA's General Aviation And Commercial Division, AFS-800, will accept for approval new Flight Instructor Refresher Clinic (FIRC) training course outlines that meet the standards set forth in Advisory Circular (AC) 61-83E, Nationally Scheduled Federal Aviation Administration Approved Industry-Conducted Flight Instructor Refresher Clinics. This rescinds the Federal Register notice (FR Doc. 04-6149) issued March 11, 2004.

The FAA proposes to adopt a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 series airplanes. This proposed AD would require inspecting to determine the part number of the left and right engine fire handles; and replacing the engine fire handles with engine fire handles having different part numbers if necessary. This proposed AD is prompted by cases of the internal circuit of the engine fire handle failing. We are proposing this AD to prevent failure of the internal circuit of the engine fire handle that could disable the fuel shut-off valves and the discharge of the fire extinguishing agent, which, in the event of a fire, could result in the inability to extinguish a fire.

The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce (1971) Limited, Bristol Engine Division (RR) model Viper Mk.601-22 turbojet engines. That AD currently requires reducing the life of certain 1st stage turbine rotor blades from 7,000 hours time-in-service (TIS) to 4,600 hours TIS, and provides a drawdown schedule for blades that have already exceeded the new reduced life limit. This AD requires the same actions but changes certain compliance times to be in agreement with RR Alert Service Bulletin (ASB) No. 72- A184, dated January 2001. This AD results from comments received on AD 2004-13-03, that the AD is unnecessarily more restrictive than the requirements in the associated RR ASB No. 72-A184. We are issuing this AD to prevent multiple failures of 1st stage turbine rotor blades that could result in a dual-engine shutdown.

The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF34-8C1 series and CF34-8C5 series turbofan engines, with certain serial number (SN) master variable geometry (VG) actuators installed. That AD currently requires initial and repetitive reviews of the airplane Maintenance Data Computer (MDC) for master VG actuator fault messages, and if the MDC is inoperative, reviews of the Engine Indication and Crew Alerting System (EICAS) for fault messages. That AD also requires replacing actuators reported faulty by the Full Authority Digital Engine Control (FADEC). This ad requires those same actions, and expands the applicability to additional actuators by part number (P/N) and SN. This AD also prohibits installation of affected master VG actuators onto any CF34- 8C1 and CF34-8C5 engine after the effective date of this AD. This AD results from the need to add to the list of affected parts, master VG actuators made by parts manufacturer approval (PMA). We are issuing this AD to prevent dual-channel electrical signal faults in the VG master actuator, which will cause an uncommanded reduction of thrust to idle with a subsequent loss of the ability to advance thrust above idle, and which will result in a multiengine loss of thrust if dual- channel faults occur on more than one engine simultaneously.

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.

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.

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.

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.

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.

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.

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.

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.

The FAA proposes to adopt a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) (formerly Allison Engine Company) 501-D22A, 501-D22C, and 501-D22G turboprop engines. This proposed AD would require a onetime inspection for proper metal hardness of certain 1st stage, 2nd stage, 3rd stage, and 4th stage turbine wheels. This proposed AD results from a report of a turbine wheel found to be over dimensional limits, caused by improper metal hardness. We are proposing this AD to prevent uncontained turbine wheel failure, leading to damage of the airplane and total loss of engine power.

In issuing this notice, the FAA incorporates, on an interim basis; two new assurances to the standard grant assurances that are required of a sponsor before receiving a grant under the Airport Improvement Program (AIP). Also, the FAA is modifying another grant assurance. Pursuant to applicable law, the Secretary of Transportation is required to provide notice in the Federal Register of, and to provide an opportunity for public comment on, proposals to modify the assurances and on proposals for additional AIR assurances. A notice of modification of Airport Improvement Program grant assurances and of the opportunity to comment was published in the Federal Register/Vol. 69, No. 163/Tuesday, August 24, 2004 on page 52057. The existing AIP grant assurances are being amended here for two reasons: To add two new assurances as required by Vision 100Century of Aviation Reauthorization Act, (Pub. L. 108-176) and to modify an existing assurance. The August 24 notice proposed, in addition to these new assurances to restructure the grant assurances to better reflect existing law. FAA also invited comments on all of the assurances for proposed changes or for possible recommendations to propose changes to existing statute. FAA is committed to this larger project and wishes to give full considerations to the comments received. At the same time, FAA is obligated to implement changes to law as timely as possible. Therefore, this notice is issued to implement the law with respect to the new assurances and the modified assurance while the larger project is being considered.

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 202: Portable Electronic Devices.

In compliance with the Paperwork Reduction Act of 1995 (44 U.S.C. 3501 et seq.), this notice announces that the Information Collection Request (ICR) abstracted below has been forwarded to the Office of Management and Budget (OMB) for extension of the currently approved collection. The ICR describes the nature of the information collection and the expected burden. The Federal Register notice with a 60-day comment period soliciting comments on the following collection of information was published on December 24, 2004 on page 78520.

The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310 series airplanes; and Model A300 B4-600, B4- 600R, and F4-600R series airplanes, and Model C4 605R Variant F airplanes (collectively called A300-600). This AD requires one-time general visual, detailed, and tap test inspections for discrepancies in the structural integrity of the rudder and its attachments, and corrective actions if necessary. This AD is prompted by a report that, during cruise, a Model A310 series airplane lost most of its rudder, which was made from composite-fiber-reinforced plastic. Investigation revealed that most of the rudder, including the front spar portion above the three servo control actuators was missing. We are issuing this AD to prevent detachment of the rudder from the airplane, which could degrade airplane handling qualities and result in reduced controllability of the airplane.

This document confirms the effective date of the direct final rule which revises Class E airspace at Ozark, MO.

The FAA proposes to rule and invites public comment on the application to impose and use PFC revenue at Eugene Airport, Mahlon Sweet Field under the provisions of 49 U.S.C. 40117 and part 158 of the Federal Aviation Regulations (14 part CFR 158).

The FAA is delaying the effective date of the final rule requiring each repair station to have an approved training program. This action is necessary because applicable guidance material is not yet available to assist repair stations in developing their programs. The delayed date will give repair stations sufficient time to develop their programs and will give the FAA time to evaluate and approve them.

The FAA is adopting a new airworthiness directive (AD) for all The Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to incorporate information into the applicable section of the Airplane Flight Manual (AFM). This AD results from several accidents/incidents of problems with the affected airplanes during operations in icing conditions, including six accidents in the previous two icing seasons and nine events in the past few months. We are issuing this AD to assure that the pilot has enough information to prevent loss of control of the airplane while in-flight during icing conditions.

The FAA is proposing this rule to address persistent flight delays related to over-scheduling at O'Hare International Airport (O'Hare). This proposed rule is intended as an interim measure, because the FAA anticipates that the rule would yield to longer term solutions to traffic congestion at the airport. Such solutions include an application by the City of Chicago that, if approved, would modernize the airport and reduce levels of delay, both in the medium term and long term. For this reason, the proposed rule includes provisions allowing for the limits it imposes to be gradually relaxed and in any event would sunset in 2008.

The FAA proposes to rule and invites public comment on the application to use the revenue from a PFC at Minneapolis-St. Paul International Airport under the provisions of the 49 U.S.C. 40117 and part 158 of the Federal Aviation Regulations (14 CFR part 158).

This action amends Title 14 Code of Federal Regulations, part 71 (14 CFR part 71) by revising Class E airspace at Parsons, KS. The FAA is canceling three, modifying two and establishing three new standard instrument approach procedures (SIAPs) to serve Tri-City Airport, Parsons, KS. These actions require modification of the Class E airspace area extending upward from 700 feet above ground level (AGL) at Parsons, KS. The area is enlarged and two extensions are eliminated to conform to airspace criteria in FAA Orders. The intended effect of this rule is to provide controlled airspace of appropriate dimensions to protect aircraft departing from and executing SIAPs to Tri-City Airport.