Federal Aviation Administration 2005 – Federal Register Recent Federal Regulation Documents

This document confirms the effective date of the direct final rule which revises Class E airspace at Meade Municipal Airport, KS

This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100& 440) airplanes, that requires performing an inspection of the electrical harnesses of the spoiler and the brake pressure sensor unit on both sides of the wing root to detect any chafing or wire damage, and repairing or replacing any damaged or chafed harness or wire with a new harness, as applicable. This action also provides/requires a terminating modification for the one-time inspection. The actions specified by this AD are intended to detect and correct chafing of the electrical cables of the spoiler and brake pressure sensor unit on both sides of the wing root, which could result in loss of the flight control system and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.

The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas transport category airplanes. That AD currently requires repetitive inspections for cracking of the lower cargo doorjamb corners, and corrective action if necessary. That AD provides for optional terminating action for certain repetitive inspections for certain airplanes. For certain other airplanes, that AD requires modification of the lower cargo doorjamb corners. This new AD adds airplanes to the applicability. The existing AD was prompted by reports of fatigue cracks in the fuselage skin in the lower cargo doorjamb corners; this AD is prompted by the inadvertent omission of certain airplanes from the existing applicability. We are issuing this AD to ensure that the unsafe condition will be addressed on all affected airplanes so that cracking in the lower cargo doorjamb corners is detected and corrected before it can result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.

This action corrects errors in certain amendments to the required IFR (instrument flight rules) altitudes and changeover points for certain Federal airways, jet routes, or direct routes for which a minimum or maximum en route authorized IFR altitude is prescribed listed in a final rule published in the Federal Register on August 2, 2005 (70 FR 44278).

The FAA proposes to adopt a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 airplanes, and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This proposed AD would require modification of the upper frame of the firewall for the auxiliary power unit (APU). This proposed AD results from the discovery of a hole in the upper frame of the firewall for the APU. We are proposing this AD to prevent smoke from entering the passenger cabin in the event of a fire in the APU compartment.

The FAA proposes to supersede an existing airworthiness directive (AD) that was issued for General Electric Company (GE) CF34- 3A1 and -3B1 series turbofan engines with certain part numbers (P/Ns) and serial numbers (SNs) of stage 5 low pressure turbine (LPT) disks and stage 6 LPT disks. These engines are installed in Bombardier Canadair CL600-2B19 Regional Jet (RJ) airplanes. This proposed AD would add SNs to the affected disk population for RJ airplanes. This proposed AD would also add GE CF34-1 and -3 series turbofan engines with certain P/Ns and SNs of stage 5 LPT disks and stage 6 LPT disks, to the applicability section. These engines are installed in Bombardier Canadair models CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A), (CL-601- 3R), and (CL-604) Business Jet (BJ) airplanes. This proposed AD would require initial and repetitive visual and eddy current inspections (ECI) of the affected disk population. This proposed AD would also allow replacement of those disks as optional terminating action to the repetitive inspections. Also, this proposed AD would require eventual replacement of the affected disks as terminating action to the repetitive inspections. This proposed AD results from the discovery of additional suspect stage 5 LPT disks and stage 6 LPT disks. These disks could fail due to low-cycle fatigue cracking that may start at the site of an electrical arc-out on the disk. We are proposing this AD to prevent low-cycle-fatigue (LCF) failure of stage 5 LPT disks and stage 6 LPT disks, which could lead to uncontained engine failure.

This notice announces the availably of and requests comments on a proposed Advisory Circular (AC) 20-DATABUS, Aviation Databus Assurance. This proposed AC provides guidance for manufacturers of aircraft, aircraft engine, and avionics incorporating databuses and databus technology in the design of their aircraft, aircraft engine, or avionics systems. In the proposed AC, we recommend how you as the manufacturer, may get design and airworthiness approval for your databus.

The Federal Aviation Administration (FAA) announces its findings on the Noise Compatibility Program revision submitted by the city of Austin under the provisions of 49 U.S.C. (the Aviation Safety and Noise Abatement Act, hereinafter referred to as ``the Act'') and 14 CFR part 150. These findings are made in recognition of the description of Federal and nonfederal responsibilities in Senate Report No. 96-52 (1980). On April 5 and May 8, 2000, The FAA determined that the noise exposure maps submitted by the city of Austin under part 150 complied with applicable requirements. On August 5, 2005, the FAA approved a revision to the Austin-Bergstrom International Airport Noise Compatibility Program. The program measure in this revision was fully approved.

The FAA is superseding an existing airworthiness directive (AD), which applies to certain Bombardier Model CL-215-1A10 and CL-215- 6B11 series airplanes. That AD currently requires repetitive ultrasonic inspections to detect cracking of the lower caps of the wing front spar and rear spar, and corrective action if necessary. This new AD reduces the threshold to do the initial inspections and revises the repetitive inspection interval. This new AD also adds a repetitive ultrasonic inspection of the wing lower skin. This AD results from reports of cracks in the front and rear spar lower caps. We are issuing this AD to detect and correct cracking of the lower caps of the wing front spar and rear spar, which could result in reduced structural integrity of the airplane.

The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) PW2000 series turbofan engines. That AD currently requires revisions to the engine manufacturer's time limits section (TLS) to include enhanced inspection of selected critical life- limited parts at each piece-part opportunity. This AD requires modifying the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. This AD results from an FAA study of in-service events involving uncontained failures of critical rotating engine parts that indicates the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.

This action amends Title 14 Code of Federal Regulations (14 CFR) part 71 relating to airspace designations to reflect the approval by the Director of the Federal Register of the incorporation by reference of FAA Order 7400.9N, Airspace Designations and Reporting Points. This action also explains the procedures the FAA will use to amend the listings of Class A, B, C, D, and E airspace areas; air traffic service routes; and reporting points incorporated by reference.

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 the disposition of certain petitions previously received. 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.

This notice announces the bi-annual meeting of the Federal Aviation Administration (FAA) Aeronautical Charting Forum (ACF) to discuss informational content and design of aeronautical charts and related products, as well as instrument flight procedures policy and criteria.

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 203, Minimum Performance Standards for Unmanned Aircraft Systems and Unmanned Aircraft

The Federal Aviation Administration (FAA) announces its findings on the noise compatibility program submitted by the Department of Port Administration of the American Samoa Government under the provisions of Title I of the Aviation Safety and Noise Abatement Act, as amended, (Pub. L. 96-193) (hereinafter referred to as ``the Act'') and 14 CFR part 150. These findings are made in recognition of the description of Federal and nonfederal responsibilities in Senate Report No. 96-52 (1980). On January 28, 2005, the FAA determined that the noise exposure maps submitted by Department of Port Administration of the American Samoa Government under Part 150 were in compliance with applicable requirements.

The FAA proposes to adopt a new airworthiness directive (AD) for all GROB-WERKE Model G120A airplanes. This proposed AD would require you to inspect for signs of any chafing damage to the attachment cables of the switch panels below the left-hand instrument panel, any damaged switch below the switch panels of the left-hand instrument panel, any damaged (that is, sharp) edge of the support tray for the attachment cables of the switch panels below the left-hand instrument panel; correct any damage found during the inspection; and apply a layer of anti-rub (protective padding) strips to the edge of the support tray. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this proposed AD to detect, correct, and prevent chafing of the cables against the rear lip of the tray that holds the switch panels. Chafing of the electrical cables could result in smoke or fire in the cockpit.

The Federal Aviation Administration (FAA) announces its determination that the noise exposure maps submitted by the City of Fresno for Fresno Yosemite International Airport under the provisions of 49 U.S.C. 47501 et seq. (Aviation Safety and Noise Abatement Act) and 14 CFR part 150 are in compliance with applicable requirements.

The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arrius 2F turboshaft engines. This AD requires a one-time removal and inspection of the fuel filter-holder assembly to determine that the fuel control unit (FCU) filter is dimensionally correct. The AD also requires updating the Engine Maintenance Manuals to include a dimensional check of the fuel filter-holder assembly every time the FCU filter element is removed from the fuel filter-holder assembly. This AD results from reports of restricted fuel flow caused by a dimensionally incorrect FCU filter. Ground run testing may not detect the fuel flow limitation. We are issuing this AD to detect a dimensionally incorrect FCU filter that could lead to an undetected limitation of fuel flow, limiting the maximum power available in-flight, which could result in the inability to continue safe flight, avoid obstacles or land safely.

The FAA is adopting a new airworthiness directive (AD) for Turbomeca S.A. Arrius 2F turboshaft engines. This AD requires replacing certain O-rings on the check valve piston in the lubrication unit. This AD results from a report of a forced landing of a Eurocopter EC120B helicopter. We are issuing this AD to prevent an uncommanded in-flight shutdown of the engine, which could result in a forced autorotation landing and damage to the helicopter.

The Federal Aviation Administration (FAA) is amending its operating regulations to allow the use, on board aircraft, of Child Restraint Systems (CRSs) that are approved by the FAA through a Type Certificate, Supplemental Type Certificate, or Technical Standard Order. Current FAA regulations do not allow the use of CRSs other than those that meet specific standards for the automobile environment. The intended effect of this regulation is to reduce the regulatory burden to industry while maintaining or increasing safety.

The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B2 and B4 series airplanes; Model A300-600 series airplanes; and Model A310-200 and -300 series airplanes. That AD currently requires, among other actions, repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary. This new AD requires new repetitive tests/inspections/analyses of the rudder servo actuators, and related investigative/corrective actions if necessary. Accomplishment of the new actions ends the existing repetitive requirements. This AD is prompted by new reports of desynchronization of the rudder servo actuators. We are issuing this AD to prevent desynchronization of one of the three rudder servo actuators, which, if combined with an engine failure, could result in the loss of the related hydraulic system and could cause the loss of one of the two synchronized actuators. This condition could create additional fatigue loading and possible cracking on the attachment fittings and could result in the inability of the remaining synchronized actuator to maintain the commanded rudder deflection, which could result in reduced controllability of the airplane.

This action modifies the Class E airspace area at Santa Elena, TX to provide adequate controlled airspace for the Instrument Landing System (ILS) standard instrument approach procedure (SIAP) at the Sierra Blanca Regional Airport (SRR).

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 the disposition of certain petitions previously received. 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.

This notice contains the text of a memorandum from the Secretary of Transportation to the Administrator of the Federal Aviation Administration regarding the Provision of Aviation Insurance Coverage for U.S. Flag Commercial Air Carrier Service in Domestic and International Operations.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A320-111, -211, -212, and -231 airplanes. This proposed AD would require, for certain airplanes, modifying the cables and access holes to the inner tank fuel pumps; and, for certain other airplanes, inspecting the fuel pump access holes and modifying the access holes, if necessary. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent chafing of the fuel pump cables, which could result in electrical arcing and possible ignition of fuel vapors and consequent explosion of the fuel tank.