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

The Federal Aviation Administration (FAA) announces that the Draft O'Hare Modernization Section 303/4(f) and Section 6(f) Evaluation for the O'Hare Modernization Environmental Impact Statement is available for public review and comment. The Section 303/4(f) and Section 6(f) Evaluation can be obtained on the Web at https:// www.agl.faa.gov/OMP/DEIS.htm or the locations noted below. The Section 303/4(f) and Section 6(f) Evaluation documents the consideration of impacts to Section 303/4(f) lands and DOT Section 6(f) lands that could be impacted by build alternatives proposed at Chicago O'Hare International Airport. The proposed build alternatives are intended to address the projected needs of the Chicago region by reducing delays at O'Hare, thereby enhancing capacity of the National Airspace System, and ensuring that terminal facilities and supporting infrastructure can efficiently accommodate airport users. The comment period is open as of the date of this Notice of Availability and closes July 5, 2005. Comments must be sent to Michael W. MacMullen of the FAA at the address shown below. Comments must be postmarked and emails must be sent no later than midnight, July 5, 2005.

The FAA proposes to adopt a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Models 525, 525A, and 525B airplanes. This proposed AD would require you to install identification sleeves on the wiring for both engine fire extinguisher bottles. This proposed AD results from reports of incorrectly connecting the wires to the engine fire extinguisher bottles. We are issuing this proposed AD to prevent incorrect installation of the wires to the engine fire extinguisher bottles, which could result in failure of the engine fire extinguisher bottles to discharge when activated. This failure could lead to the inability to control an engine fire.

The FAA proposes to revise Airworthiness Directive (AD) 95-19- 15, which applies to all Tiger Aircraft LLC (Type Certificate A16EH formerly held by American General Aircraft Corporation and Grumman American Aviation Corporation) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes. AD 95-19-15 currently requires you to inspect the wing attach shoulder bolts for fretting, scoring, wear, or enlarged or elongated mounting holes (known as damage from hereon); replace any damaged parts; repair any damaged areas; inspect the wing spar at the center spar clearance gap for excessive clearance; and shim the spar if excessive clearance is found. Since we issued AD 95-19-15, FAA has received and evaluated new service information that limits the serial numbers for the Model AG-5B airplanes of AD 95-19-15. Consequently, this proposed AD retains all the actions of AD 95-19-15 and includes the serial numbers for the Model AG-5B airplanes in the applicability section. We are issuing this proposed AD to prevent wing attach shoulder bolt failure, which, if not detected and corrected, could lead to structural damage of the wing/fuselage to the point of failure.

The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 airplanes. That AD currently requires inspections to detect cracks in the front spar pressure bulkhead chord, and repair if necessary. This new AD requires repetitive high frequency eddy current (HFEC) inspections of the body station (BS) 1000 bulkhead chord for cracks, repetitive detailed inspections of the bathtub fittings, if installed, for cracks, and corrective action if necessary. Initiation of the new inspections ends the inspections of the existing AD. This AD also revises the applicability of the existing AD to include additional airplanes. This AD is prompted by reports of cracks in the BS 1000 bulkhead chord. We are issuing this AD to detect and correct fatigue cracks in the BS 1000 bulkhead chord, which, if not repaired before they reach critical length, could result in the failure of the adjacent structure and skin and lead to in-flight depressurization of the airplane.

This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 and -300 series airplanes, that requires modification of the bolt holes of the lower side of the body splice t-chord common to the paddle fittings of the lower wing panel. The modification includes performing a high frequency eddy current inspection of the fastener holes for cracks, repairing the hole if necessary, and replacing the fasteners with new inconel bolts. This action is necessary to prevent fatigue cracks in the lower t-chord at the bolt holes common to the paddle fittings that could result in fractures of one or more of the t-chord segments, which could lead to detachment of the lower wing panel and consequent loss of the wing. This action is intended to address the identified unsafe condition.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 series airplanes. This AD requires replacing the pressure switches on the override/jettison fuel pumps with new pressure switches, and replacing the ship side electrical connectors for the pressure switches on override/jettison fuel pumps with new connectors. This AD is prompted by reports that the ``FUEL LOW CENTER'' message does not activate when the fuel level in the center tank is low. We are issuing this AD to prevent the fuel pumps in the center fuel tank from running dry and becoming a potential ignition source, which could result in a fuel tank explosion.

On September 24, 2004, the Federal Aviation Administration (FAA) published a final rule, with request for comments, to amend the regulations implementing airport noise compatibility planning. The amendment included revisions stemming from changes to the authorizing legislation that had not been incorporated into the implementing regulations. In addition, the final rule contained several minor, technical changes. This action is a summary and disposition of the comments received in response to that final rule.

The Federal Aviation Administration (FAA) is issuing this notice to advise the public that a Draft Air Quality General Conformity Determination (DGCD) for the O'Hare Modernization Environmental Impact Statement at Chicago O'Hare International Airport has been prepared and is available for public review and comment. In accordance with section 176(c) of the Federal Clean Air Act, FAA has assessed whether the air emissions that would result from FAA's action in approving the proposed projects conform with the Illinois State Implementation Plan (SIP). This assessment is contained in the DGCD. The comment period is open as of the date of this Notice of Availability and closes June 20, 2005. Comments must be sent to Michael W. MacMullen of the FAA at the address shown below, and written comments must be postmarked and emails must be sent by not later than midnight, June 20, 2005.

the Federal Aviation Administration (FAA) has prepared and is making available the Draft Environmental Assessment (DEA) for the following proposed action at the St. Louis Downtown Airport: The construction of a new Air Traffic Control Tower, associated support building, parking lot, and access road. The Draft EA is being prepared in accordance with the National Environmental Policy Act (NEPA) of 1969, as amended, FAA Order 1050.1E ``Environmental Impacts: Policies and Procedures'', and FAA Order 5050.4A, ``Airport Environmental Handbook.'' The proposed development action is consistent with the National Airspace System Plan prepared by the U.S. Department of Transportation, Federal Aviation Administration (FAA). A Draft Environmental Assessment will be available for public review and comment at the following locations:

The FAA is revising an earlier NPRM for an airworthiness directive (AD) that applies to certain Airbus airplane models, as specified above. The original NPRM would have required modifying the thermal insulation system of certain fuselage frames, and modifying the fuselage drainage system. The original NPRM would also have required revising the FAA-approved maintenance inspection program to include inspections for corrosion or cracking in the subject areas. The original NPRM was prompted by reports of corrosion in the lower part of the pressure bulkhead at certain fuselage frames. This action revises the original NPRM by expanding the applicability to include additional airplanes. We are proposing this supplemental NPRM to prevent accumulation of condensation in the insulation blankets of certain fuselage frames, which could cause corrosion that could result in reduced structural integrity of the fuselage and consequent rapid decompression of the airplane.

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. On January 13, 2005, a notice was published of a petition seeking relief from the requirements of 14 CFR 25.841(a)(2)(ii). By a letter dated March 4, 2005, the petitioner submitted additional information that indicated that it would also be necessary to obtain exemption from the related requirements of Sec. 25.841(a)(2)(i). 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 amendment adopts a new airworthiness directive (AD) for the Schweizer Aircraft Corporation (Schweizer) Model 269C, C-1, and D helicopters. This action requires inspecting, modifying, and testing the lateral control trim actuator assembly on certain serial-numbered helicopters. This amendment is prompted by three reported incidents of the inner spring tube separating from the lateral trim control housing resulting in a lateral cyclic control restriction. The actions specified in this AD are intended to prevent separation of the inner spring tube from the lateral trim control housing and the associated loss of trim control, increased local resistance to right cyclic stick movement, and an emergency landing or subsequent loss of control of the helicopter.

The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 737-300, -400, and -500 series airplanes. That AD currently requires repetitive inspections of certain connectors located in the main wheel well to detect discrepancies, and corrective action if necessary. This new AD instead mandates a modification. This AD is prompted by the development of a modification intended to address the unsafe condition. We are issuing this AD to prevent discrepancies of certain connectors located in the main wheel well. Those discrepancies could result in electrical arcing of the connectors, uncommanded closure of the engine fuel shut-off valves, and consequent in-flight loss of thrust or engine shutdown from lack of fuel.

This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. That AD currently requires replacing certain main or combiner gearboxes with airworthy gearboxes. Further investigation has shown that the main gearbox is not affected, and this amendment requires replacing a certain combiner gearbox with a modified airworthy gearbox. This amendment is prompted by a report of a freewheel unit slipping resulting in an engine overspeed and shutdown. Also, this amendment is prompted by the conclusion of the investigation, which finds the freewheel slippage is due to the surface treatment applied to certain freewheel rollers in the combiner gearbox. The actions specified by this AD are intended to prevent an engine overspeed, an engine shutdown, and subsequent loss of control of the helicopter.

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 revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness of the Canadair Regional Jet Maintenance Requirements Manual by incorporating new repetitive detailed inspections of the secondary load path indicator for the horizontal stabilizer trim actuator (HSTA). This AD is prompted by a report of a potential failure of the horizontal stabilizer trim actuator (HSTA) secondary nut in conjunction with a latent failure of the HSTA primary load path discovered during sampling program activities. We are issuing this AD to detect and correct latent failure of the primary load path of the HSTA, which, in conjunction with a failure of the HSTA secondary nut, could result in loss of horizontal trim control and consequent reduced controllability of the airplane.

The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes. This AD requires operators to install torque tube catchers on the control columns of the flight controls. This AD is prompted by the discovery that a single malfunction of the torque tube could result in both flight control columns being supported by only one self-aligning bearing. We are issuing this AD to prevent the torque tube from fouling against the underfloor control cables, which could result in reduced controllability of the airplane.

On January 24, 2003, the FAA adopted eligibility standards that disqualify a person from holding an airman certificate, rating, or authorization when the Transportation Security Administration has advised the FAA in writing that the person poses a security threat. The rule was adopted to prevent a possible imminent hazard to aircraft, persons, and property within the United States. This action is a summary and disposition of comments received on the final rule.

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, dispositions of certain petitions previously received, and corrections. 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 availability of and requests comments on a proposed advisory circular that sets forth an acceptable means, but not the only means of showing compliance with Title 14 Code of Federal Regulations (14 CFR), part 23, for two new concepts in small airplanes. The two concepts are: (1) Synthetic Vision (SV), and (2) pathway depictions displaying the navigation course on the primary flight display. This AC covers airplanes in the normal, utility, acrobatic, and commuter categories approved to fly under Instrument Flight Rules (IFR). This notice is necessary to give all interested persons an opportunity to present their views on the proposed AC.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This proposed AD would require modification of the electrical bonding of all structures and systems installed inside the center fuel tank. This proposed AD is prompted by results of fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent electrical arcing in the center fuel tank due to inadequate bonding, which could result in an explosion of the center fuel tank and consequent loss of the airplane.

This rule establishes a Class E surface area at Valentine, NE. It also modifies the Class E airspace area extending upward from 700 feet above the surface at Valentine, NE. The effect of this rule is to provide appropriate controlled Class E airspace for aircraft departing from and executing instrument approach procedures to Miller Field, Valentine, NE and to segregate aircraft using instrument approach procedures in instrument conditions from aircraft operating in visual conditions.

The FAA is adopting a new airworthiness directive (AD) for certain Dornier Model 328-300 series airplanes. This AD requires installing a drain hole in the lower skin of the left- and right-hand elevator horns. This AD is prompted by reports of water found in the elevator assembly. We are issuing this AD to prevent water or ice accumulating in the elevator assembly, which could result in possible corrosion that reduces the structural integrity of the flight control surface, or in an unbalanced flight control surface. These conditions could result in reduced controllability of the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for all airplanes equipped with Aero Advantage ADV200 series (part numbers ADVPL211CC and ADVPL212CW) vacuum pumps installed under supplemental type certificate number SA10126SC, through field approval, or other methods. This proposed AD would require you to remove any affected vacuum pump and related monitor system, remove the applicable airplane flight manual supplement (AFMS) and placard, and install an FAA-approved vacuum pump other than the affected part numbers. This proposed AD results from several reports of pump chamber failure. We are issuing this proposed AD to correct problems with the vacuum pump before failure or malfunction during instrument flight rules (IFR) flight that can lead to loss of flight instruments critical for flight. The loss of flight instruments could cause pilot disorientation and loss of control of the aircraft.

The FAA is adopting a new airworthiness directive (AD) for all Dornier Model 328-300 series airplanes. This AD requires installing an additional mounting angle for the respective de-icing pipes at rib 9 in the leading edge area of the left- and right-hand wings. This AD is prompted by chafed de-icing lines in the wing leading edge area. We are issuing this AD to prevent chafing of the de-icing lines, which could result in a reduction in functionality of the anti-ice system, and possibly reduced controllability and performance of the airplane in icing conditions.