Federal Aviation Administration January 2006 – Federal Register Recent Federal Regulation Documents

This document corrects a docket number in an NPRM that was published in the Federal Register on October 17, 2005 (70 FR 60244). The NPRM applies to Eurocopter France Model EC155B and B1 helicopters. The NPRM proposed to require inspecting an electrical cable bundle for wear and, if necessary, installing an airworthy cable bundle and modifying the routing of the electrical cable bundles.

The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model Hawker 800XP airplanes. This AD requires inspecting to determine if the correct fuse is installed on the hydraulic over-temperature switch on panel ZK in the rear equipment bay, and replacing the existing fuse if necessary. This AD results from a report of the installation of an incorrect fuse on the over- temperature switch on panel ZK in the rear equipment bay during airplane maintenance. We are issuing this AD to prevent a short circuit in the fuse and consequent heat damage to associated wiring and surrounding equipment, which could result in smoke or fire on the airplane.

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 replacing the Camloc fasteners on the sidewall of the center pedestal. This AD results from reports of the Camloc fasteners on the sidewall of the center pedestal disengaging and interfering with an inboard rudder pedal. We are issuing this AD to prevent these fasteners from disengaging and interfering with an inboard rudder pedal, which could reduce directional controllability of the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Aerospatiale Model ATR42 airplanes and Model ATR72 airplanes. This proposed AD would require installing protective ramps on trim panel 110VU; and inspecting the protective guard of the standby pitch trim switch to determine if it is missing, damaged, or ineffective, and doing the corrective action if necessary. This proposed AD results from a finding that the protective guard of the standby pitch trim switch, which is installed on the center pedestal, could be damaged or missing. We are proposing this AD to prevent inadvertent activation of the standby pitch trim, which could result in pitch trim runaway and consequent reduced controllability of the airplane.

This amendment adopts miscellaneous 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. This regulatory action is needed because of changes occurring in the National Airspace System. These changes are designed to provide for the safe and efficient use of the navigable airspace under instrument conditions in the affected areas.

The Federal Aviation Administration (FAA), Central Terminal Service Area, is issuing this notice to advise the public of the availability of the Final Environmental Assessment Final (EA) and FONSI/ROD for the MASE project.

The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and -300 series airplanes, Model A340-200 and - 300 series airplanes, and Model A340-541 and A340-642 airplanes. This AD requires revising the airplane flight manual by incorporating new procedures to follow in the event of a fuel leak. This AD results from a determination that, once a fuel leak is detected, fuel management procedures are a critical factor in limiting the consequences of the leak. We are issuing this AD to ensure that the flightcrew, in the event of a fuel leak, is advised of appropriate procedures to follow, such as isolating the fuel tanks, stopping any fuel transfers, and landing as soon as possible. Failure to follow these procedures could result in excessive fuel loss that could cause the engines to shut down during flight.

This notice announces the issuance of Advisory Circular (AC) 23-13A, Fatigue, Fail-Safe, and Damage Tolerance Evaluation of Metallic Structure for Normal, Utility, Acrobatic, and Commuter Category Airplanes. The AC sets forth an acceptable means, but not the only means, to show compliance with applicable fatigue, fail-safe, and damage tolerance evaluations required for metallic structure in normal, utility, acrobatic, and commuter category airplanes. The AC provides information on approval of continued operational flight with known cracks in the structure of small airplanes, regardless of certification basis. The AC also clarifies the use of AC 20-128A in the evaluation of rotorburst structural hazards in small airplanes. Finally, the AC consolidates existing policy documents and certain technical reports into one document.

The required information will be used to determine if applicant proposals for conducting commercial space launches can be accomplished in a safe manner according to regulations and license orders issued by the Office of the Associate Administrator for Commercial Space Transportation. Respondents are applying for licenses to authorized licensed launch activities.

The Federal Aviation Administration (FAA) announces that it is reviewing a proposed second revision to the approved noise compatibility program that was submitted for Scottsdale Airport under the provisions of 49 U.S.C. 47501 et seq. (the Aviation Safety and Noise Abatement Act, hereinafter referred to as ``the Act'') and 14 CFR part 150 by the City of Scottsdale. This program was submitted subsequent to a determination by FAA that associated noise exposure maps submitted under 14 CFR part 150 for Scottsdale Airport were in compliance with applicable requirements, effective February 14, 1986. The Noise Compatibility Program for Scottsdale Airport was approved by the FAA on December 19, 1986. The proposed Revision No. 2 to the noise compatibility program will be approved or disapproved on or before May 31, 2006.

The FAA is extending the public scoping comment period for an additional 90 days to allow further participation in the scoping process. For additional information, the original announcement regarding the notice of intent to prepare an Environmental Impact Statement and to conduct scoping meetings was published in the Federal Register on October 13, 2005 (Volume 70, Number 197), Page 59800-59801. As a result of the meeting held on November 15, 2005, the FAA decided to extend the comment period to accommodate comments from potentially affected parties. Written comments on the scope of the EIS must be received no later than 5 p.m. Pacific Standard Time, March 15, 2006.

This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas transport category airplanes, that requires an inspection of the upper lock link assembly of the nose landing gear (NLG) to determine the manufacturer, repetitive eddy current inspections for cracking, and modification or replacement if necessary. This AD also provides for optional terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent fracture of the upper lock link assembly of the NLG, which could result in failure of the NLG to extend following a gear-down selection, and consequent gear-up landing, structural damage, and possible injury to passengers and crew. This action is intended to address the identified unsafe condition.

This notice revises an earlier proposed airworthiness directive (AD) that applies to certain IAE V2522-A5, V2524-A5, V2527- A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines. That proposal would have required initial and repetitive inspections of the master magnetic chip detector (MCD) or the No. 1, 2, 3 bearing chamber MCD. That proposal would also have required replacing certain No. 3 bearings and replacing or recoating certain high pressure compressor (HPC) stubshaft assemblies as mandatory terminating actions to the repetitive MCD inspections. That proposal resulted from IAE developing a terminating action to the repetitive inspections of the chip detectors. This action revises the proposed rule by expanding its applicability to include additional serial-numbered engines with certain No. 3 bearings installed. We are proposing this AD to prevent failure of the No. 3 bearing, which could result in an in-flight shutdown (IFSD) and smoke in the cockpit and cabin.

The FAA is adopting a new airworthiness directive (AD) for all Pacific Aerospace Corporation (PAC) Ltd. Model 750XL airplanes. This AD contains the same information as emergency AD 2005-26-53 and publishes the action in the Federal Register. This AD requires you to insert text into the Limitations Section of the Airplane Flight Manual (AFM) that reduces the maximum takeoff weight from 7,500 pounds to 7,125 pounds. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand. We are issuing this AD to reduce the maximum takeoff weight that will allow wing ultimate load requirements to be met. If wing ultimate load requirements are not met, wing failure could result and subsequent loss of control of the airplane.

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 208, Aeronautical Mobile Satellite Services.

The FAA proposes to rule and invites public comment on the application to impose and use the revenue from a PFC at Savannah/Hilton Head 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 withdraws the direct final rule published in the Federal Register on November 14, 2005, (70 FR 69077). In that action, the FAA proposed to establish a Class E enroute domestic airspace west of San Luis Obispo, CA, to replace existing Class G uncontrolled airspace. The FAA has determined that the boundaries of this airspace will be revised and another direct final rule resubmitted for publication.

This advisory circular (AC) 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 addresses the two concepts in a head down display format only. This AC covers airplanes in the normal, utility, acrobatic, and commuter categories approved to fly under Instrument Flight Rules (IFR). Material in this AC is neither mandatory nor regulatory in nature and does not constitute a regulation. The draft advisory circular was issued for Public Comment on May 16, 2005 (70 FR 25873). When possible, comments received were used to modify the draft advisory circular.

The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream 100 airplanes; and Model Astra SPX, and 1125 Westwind Astra airplanes. This AD requires a one-time inspection for discrepancies of the nose wheel steering assembly of the landing gear, installing a warning placard on each nose landing gear door, and corrective action if necessary. This AD results from reports of failure of the steering brackets of the nose wheel steering assembly, and in one incident, loss of steering control. We are issuing this AD to find and fix these discrepancies, which could result in loss of steering control and consequent reduced controllability of the airplane.

The FAA published a document in the Federal Register on August 30, 2002 (Volume 67, Number 169) regarding Special Condition 23-127-SC for Chelton Flight Systems, Various Airplane Models; Protection of Systems for High Intensity Radiated Fields (HIRF). This amendment is being published to add several airplane models to the existing special condition to cover current and future amendments to the Approved Model List (AML) STC. These special conditions address HIRF certification requirements for digital systems not addressed by the current regulations. See the attached AML for the airplanes that are added by this amendment. These airplanes, as modified by Chelton Flight Systems, will have a novel or unusual design feature(s) associated with the installation of an electronic flight instrument system. These special conditions address the protection of these systems from the effects of high intensity radiated field (HIRF) environments. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146-100A and -200A series airplanes. This AD requires inspecting the nose landing gear (NLG) assembly to determine the part number of the NLG main fitting subassembly. For subject NLG main fitting subassemblies, this AD also requires determining the total number of accumulated landings on a subject NLG main fitting subassembly, and eventually replacing the NLG assembly. This AD results from a report indicating that the airplane maintenance manual contains incorrect safe-life limit information for certain NLG assemblies. We are issuing this AD to ensure that affected NLG fitting subassemblies are removed from service before they reach their approved safe-life limit. Operating with an NLG fitting subassembly that is beyond its approved safe-life limit could result in failure of the NLG and consequent loss of directional control on the ground and major structural damage to the airplane.

The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplanes, listed above. This AD requires installing two-stage relays in the electronics rack (90VU), and performing related corrective and investigative actions. This AD results from reports of inadvertent rudder trim activation when the autopilot is on. We are issuing this AD to prevent inadvertent trim activation when the autopilot is on and the slats are extended, which could result in rudder activation when the autopilot is turned off.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. The existing AD currently requires repetitive detailed and ultrasonic inspections of the thrust links of the rear engine mounts for any crack or fracture and corrective actions if necessary. This proposed AD would require repetitive replacement of the thrust links with new or overhauled thrust links, which ends the repetitive detailed and ultrasonic inspections. This proposed AD results from the finding of fractured and cracked forward lugs of the rear engine mount thrust link on the number one strut on two airplanes. We are proposing this AD to prevent cracked or fractured thrust links that could lead to the loss of the load path for the rear engine mount bulkhead and damage to other primary engine mount structure, which could result in the in-flight separation of the engine from the airplane and consequent loss of control of the airplane.

On November 10, 2005, the Federal Aviation Administration (FAA) published a direct final rule to amend its regulation on the use of pilot supplemental oxygen with an effective date of January 9, 2006. The FAA received an adverse comment from the National Transportation Safety Board stating that the FAA relied on time of useful consciousness data that did not represent actual pilot performance under realistic decompression conditions. In accordance with Sec. 11.31, which states if the FAA receives an adverse comment it will notify the public by publishing a document in the Federal Register, the FAA is using this notice to withdraw this direct final rule in whole.

This final rule amends FAA regulations dealing with how the FAA notifies petitioners of its decisions on petitions for exemption. This rule change eliminates the requirement for the FAA to publish dispositions of petitions for exemption in the Federal Register. This change is intended to streamline our process and will save the agency the cost of publication. Publishing dispositions in the Federal Register is unnecessary because petitioners are notified in writing of FAA's decision and the decision is placed in the public docket, which is internet accessible and searchable.