Federal Aviation Administration 2005 – Federal Register Recent Federal Regulation Documents

The FAA is amending the procedural regulations governing the assessment of civil penalties against persons other than individuals acting as pilots, flight engineers, mechanics or repairmen. The rules establish a clear separation of functions between those agency employees who prosecute civil penalty actions and those who advise the Administrator, acting as FAA decisionmaker, about appeals of decisions by Department of Transportation (DOT) administrative law judges (ALJs). Recent organizational changes in the Office of the Chief Counsel necessitate updating these regulations so they accurately reflect the Office's current structure and division of functions. We are also amending the rules to provide the FAA Civil Penalty Hearing Docket's new address, new instructions on filing of documents, and information about the availability of documents and FAA decisions via the Internet. We are amending the procedural rule governing appeals from initial decisions regarding applications for fees under the Equal Access to Justice Act (EAJA) to reinsert language that was inadvertently omitted during a previous revision.

The Federal Aviation Administration (FAA) announces that it is reviewing a proposed amendment (second) for the noise compatibility program that was submitted for Austin-Bergstrom International Airport under the provisions of Title 49, U.S.C. Chapter 475 (hereinafter referred to as ``Title 49'') and 14 CFR part 150 by the city of Austin. This program was submitted subsequent to a determination by the FAA that associated noise exposure maps submitted under 14 CFR part 150 for Austin-Bergstrom International Airport were in compliance with applicable requirements effective on April 29, 2000. The original noise compatibility program was approved on November 7, 2000, and subseqently amended on February 11, 2004. The proposed update to the noise compatibility program will be approved or disapproved on or before August 10, 2005.

The FAA is adopting a new airworthiness directive (AD) for all Dassault Model Falcon 10 series airplanes. This AD requires a temporary change to the airplane flight manual (AFM) to provide procedures to the flightcrew for touchdown using the main landing gear to avoid a three- point landing. This AD also requires repetitive inspections of the piston rod of the drag strut actuator of the nose landing gear (NLG) for cracks, which would terminate the AFM revision, and corrective actions if necessary. In addition, this AD provides for a terminating modification, which would end the repetitive inspections. This AD is prompted by reports of failure of the piston rod of the drag strut actuator of the NLG. The cause of such failure has been attributed to fatigue cracking caused by corrosion in the piston rod of the drag strut actuator. We are issuing this AD to prevent cracking and/or fracture of the piston rod of the drag strut actuator of the NLG, which could result in a gear-up landing, structural damage, and possible injury to passengers and crew.

This amendment supersedes an existing airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters that currently requires certain checks and inspections of the tail rotor blades. If a crack is found, the existing AD requires replacing the tail rotor blade (blade) with an airworthy blade before further flight. This amendment requires the same checks and inspections as the existing AD, but expands the applicability with the addition of two BHTC Model 430 helicopter serial numbers. This amendment is prompted by the manufacturer issuing revised service information that includes the additional two serial numbers. The actions specified by this AD are intended to detect a crack in the blade, and to prevent loss of a blade and subsequent loss of control of the helicopter.

In compliance with the Paperwork Reduction Act (44 U.S.C. 3501 et seq.) the FAA invites public comment on seven currently approved public information collections which will be submitted to OMB for renewal.

The FAA is adopting a new airworthiness directive (AD) for all Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes and Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This AD requires revising the airplane flight manuals to include a new cold weather operations limitation. This AD is prompted by a report that even small amounts of frost, ice, snow, or slush on the wing leading edges or forward upper wing surfaces can cause an adverse change in the stall speeds, stall characteristics, and the protection provided by the stall protection system. We are issuing this AD to prevent possible loss of control on take-off resulting from even small amounts of frost, ice, snow, or slush on the wing leading edges or forward upper wing surfaces.

The FAA is adopting a new airworthiness directive (AD) for all Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires a one-time inspection to determine the part and serial numbers of certain engine vibration isolators (mounts) and the cure dates of certain molded assemblies incorporated in those engine mounts; and related corrective actions if necessary. This AD is prompted by a report that disbonding of the elastomer from the inner metal core and shim of certain engine vibration mounts has occurred within a few hundred hours of operation, causing heavy chafing of the engine support system and chafing of the fire sensor loop. We are issuing this AD to prevent reduced integrity of the fire-shielding capacity of the nacelle structure and a possible fire detector fault.

The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Model GV-SP series airplanes. This AD requires repetitive inspections of the avionics standard communication bus (ASCB) for any noise interference and repair of the ASCB if noise interference is found. This AD also requires revisions of the airplane flight manual (AFM) to prohibit dispatch of any flight with the integrated standby flight display (SFD) inoperative; to add procedures to facilitate recovery of the cockpit display units in the event that the cockpit displays go blank; and to add flightcrew briefings on the use of standby instruments in case the cockpit display units go blank and do not recover. This AD also requires installing an avionics software update and a hardware upgrade to the Honeywell Primus Epic system to correct a display blanking problem; installing the update will allow removal of certain AFM revisions and will end the repetitive inspections of the ASCB. This AD is prompted by a report indicating that all four cockpit flight panel displays went blank simultaneously. We are issuing this AD to prevent a software error from blanking the cockpit display units, which will result in a reduction of the flightcrew's situational awareness, and possible loss of control of the airplane. We are also issuing this AD to address noise interference in the ASCB, which can interfere with the display recovery after a blanking event and consequently extend the time that the displays remain blank. In addition, we are issuing this AD to ensure that the flightcrew is advised of the procedures necessary to address blank cockpit display units.

The FAA has issued an order to show cause, which solicits the views of interested persons on the FAA's tentative determination to extend until October 31 an August 18, 2004, order limiting the number of scheduled aircraft arrivals at O'Hare International Airport during peak operating hours. The order to show cause also invites written views on whether the FAA should allocate any unused capacity while the extended order is in effect and, if so, how the FAA should allocate any such unused capacity. The text of the order to show cause is set forth in this notice.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This proposed AD would require installing additional shielding of the hydraulic lines in the wing box area. This proposed AD is prompted by the determination that the additional hydraulic line shields will protect the lines from possible impact by tire debris if the tire tread fails. We are proposing this AD to prevent damage to the hydraulic lines and subsequent leakage from the two hydraulic systems, which could result in loss of braking capability on the affected side of the airplane, asymmetrical braking, and reduced directional controlparticularly during a rejected takeoff.

The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 767 series airplanes. This proposed AD would require an inspection of each main tank fuel boost pump for the presence of a pump shaft flame arrestor, and if the flame arrestor is missing, replacement of that pump with a pump having a pump shaft flame arrestor. This proposed AD would also require repetitive measurements of the flame arrestor's position in the pump, and corrective actions if necessary. This proposed AD is prompted by reports that certain fuel boost pumps may not have flame arrestors installed in the pump shaft. We have also received reports that the pin that holds the flame arrestor in place can break due to metal fatigue. We are proposing this AD to prevent the possible migration of a flame from a main tank fuel boost pump inlet to the vapor space of that fuel tank, and consequent ignition of fuel vapors, which could result in a fire or explosion should the pump inlets become uncovered.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD-11 and -11F airplanes. The existing AD currently requires a one-time inspection to detect loose preload-indicating (PLI) washers or cracked or corroded nuts of the lower bolts of the inboard flap outboard hinge, and replacement with new parts if necessary. This proposed AD would require replacement with new, improved parts of the inboard flap, outboard hinge, forward attach bracket, and lower attach bolt assemblies. This proposed AD also would add certain other McDonnell Douglas transport category airplanes and require an inspection for certain parts, and related investigative and corrective actions if necessary. This proposed AD is prompted by a report indicating that the left-hand inboard flap outboard hinge pulled away from the wing structure. We are proposing this AD to prevent loose PLI washers or cracked or corroded nuts of the lower bolts of the inboard flap outboard hinge, which could result in separation of the inboard flap outboard hinge from the wing structure and consequent reduced controllability of the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for Boeing Model 727 airplanes equipped with an auxiliary fuel tank having a fuel pump installed. This proposed AD would require revising the airplane flight manual to include limitations on operating the fuel pumps for the auxiliary fuel tank. This proposed AD is prompted by a design review of the fuel pump installation, which revealed a potential unsafe condition related to the auxiliary fuel tank(s). We are proposing this AD to prevent dry operation of the fuel pumps for the auxiliary fuel tank, which could create a potential ignition source inside the auxiliary fuel tank that could result in a fire or explosion of the auxiliary fuel tank.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 767 series airplanes. This proposed AD would require replacing hinge assemblies with new hinge assemblies in the outboard overhead stowage bins and reworking hinge assemblies in the outboard overhead stowage bins that are adjacent to curtain tracks. This proposed AD is prompted by reports of hinge assemblies of outboard overhead stowage bins breaking or the stowage bin doors not latching properly. We are proposing this AD to prevent the outboard overhead stowage bins opening during flight and releasing baggage, and consequently cause passenger injury and blockage of the aisles during emergency egress.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, -500, -600, -700, -700C, -800 and -900 series airplanes. This proposed AD would require installing an updated version of the operational program software (OPS) in the flight management computers (FMCs), and doing other specified actions. This proposed AD would also require reinstalling software, if necessary. This proposed AD is prompted by one operator reporting FMC map shifts on several Model 737-400 series airplanes with dual FMCs, using OPS version U10.4A. We are proposing this AD to prevent the FMC from displaying the incorrect actual navigation performance value to the flightcrew, which could prevent adequate alerting of a potential navigation error. This condition could result in a near miss with other airplanes or terrain, or collision if other warning systems also fail.

These special conditions are issued for the Boeing Model 747- 100/200B/200F/200C/SR/SP/100B/300/100B SUD/400/400D/400F series airplanes. These airplanes, as modified by Boeing Commercial Airplanes, include a new flammability reduction means that uses a nitrogen generation system to reduce the oxygen content in the center wing fuel tank so that exposure to a combustible mixture of fuel and air is substantially minimized. This system is intended to reduce the average flammability exposure of the fleet of airplanes with the system installed to a level equivalent to 3 percent of the airplane operating time. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for the design and installation of this system. These special conditions contain the additional safety standards the Administrator considers necessary to ensure an acceptable level of safety for the installation of the system and to define performance objectives the system must achieve to be considered an acceptable means for minimizing development of flammable vapors in the fuel tank installation.

This notice announces the issuance of Advisory Circular (AC) 23-22. This advisory circular (AC) sets guidelines for using the Approved Model List (AML) Supplemental Type Certificate (STC) process for the installation approval of avionics for 14 CFR, part 23 airplanes. It also applies to airplanes certified under a prior certification basis, such as CAR 3 or bulletin 7-A. Guidance provided in this AC applies only to avionics installations using the AML STC process. For other types of modifications to part 23 airplanes seeking to use the AML STC process, the Aircraft Certification Office (ACO) should coordinate with the Small Airplane Directorate. Avionics AML STC guidance provided in this AC addresses the following: (1) Avionics eligible for the AML STC process, (2) Model Qualification Process used by the STC holder and the FAA to either create or edit the AML, and (3) Level of Detail required for the installation instructions for an AML STC, including a list of acceptable equipment that can be integrated under the STC. Material in this AC is neither mandatory nor regulatory in nature and does not constitute a regulation. In addition, this material is not to be construed as having any legal status and should be treated accordingly. However, it is designed to provide standardization guidelines for AML STC approvals. The AML STC process may be used whenever the ACO and the applicant agree that it is suitable. This AC is not applicable to any products certified under part 25, 27, or 29. The draft advisory circular was issued for Public Comment on October 8, 2004 (69 FR 60452). When possible, comments received were used to modify the draft advisory circular.

This notice announces glider towing as a restricted category special purpose operation under Title 14 of the Code of Federal Regulations (14 CFR) Sec. 21.25(B)(7), for aircraft type certificated under 14 CFR 21.25(a)(1).

The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This proposed AD would require repetitive inspections of the dual side braces (DSBs), underwing midspar fittings, and associated parts; other specified actions; and corrective actions if necessary. This proposed AD also provides an optional terminating action for the inspections and other specified actions. This proposed AD is prompted by reports of corroded, migrated, and rotated bearings for the DSBs in the inboard and outboard struts, a report of a fractured retainer for the eccentric bushing for one of the side links of a DSB, and reports of wear and damage to the underwing midspar fitting on the outboard strut. We are proposing this AD to prevent the loss of a DSB or underwing midspar fitting load path, which could result in the transfer of loads and motion to other areas of a strut, and possible separation of a strut and engine from the airplane during flight.

This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 helicopters that requires removing and modifying the fuel bleed lever. This amendment is prompted by some cases of loss of the fuel bleed lever in flight. If the tension of the control cable is too low, the cable may vibrate out of its notch, resulting in the fuel bleed lever separating from the hinge. The actions specified by this AD are intended to prevent a fuel bleed lever from separating and striking the tail rotor blade (blade), resulting in damage to or loss of a blade, and subsequent vibration and loss of control of the helicopter.

This amendment supersedes an existing airworthiness directive (AD) that applies to all Airbus Model A300 B2 and B4 series airplanes. The existing AD currently requires determining the part and amendment number of the variable lever arm (VLA) of the rudder control system to verify the parts were installed using the correct standard, and corrective actions if necessary. For certain VLAs, this new AD requires repetitive inspections of the VLA and corrective action if necessary. This new AD also provides a terminating action for the repetitive inspections. Furthermore, this new AD reduces the applicability of affected airplanes. The actions specified by this AD are intended to prevent failure of both spring boxes of certain VLAs due to corrosion damage, which could result in loss of rudder control and consequent 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 Raytheon Model DH.125, HS.125, and BH.125 series airplanes; BAe.125 series 800A (C-29A and U-125) and 800B airplanes; and Hawker 800 (including variant U-125A) and 800XP airplanes. This AD requires installing insulating blankets on the engine compartment firewall and the wire harness passing through the firewall fairlead. This AD is prompted by a report indicating that insulation on the wire harness passing through the firewall fairlead ignited on the fuselage side of the firewall. We are issuing this AD to prevent a fire in the engine compartment from causing possible ignition of outgassing wire insulation on the fuselage side of the firewall, which could lead to an uncontrollable fire in the fuselage.

The FAA proposes to adopt a new airworthiness directive (AD) for all Pilatus Aircraft Limited (Pilatus) Models B4-PC11, B4-PC11A, and B4-PC11AF sailplanes. This proposed AD would require you to repetitively inspect the control-column support for cracks and, if any cracks are found, replace the control-column support with a new support. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this proposed AD to detect and correct cracks in the control-column support, which could result in failure of the support. This failure could lead to loss of the primary flight control system.

This final rule updates the designated mountainous areas in the State of Alaska. Regulations currently designating mountainous areas in Alaska were established in 1956. Since that time, we have concluded that areas previously considered non-mountainous should be expanded, and two areas previously designated mountainous should be considered non-mountainous. This final rule will allow aircraft operating in certain non-mountainous areas to fly at altitudes acceptable for the actual topography of the area.

This document proposes superseding an existing airworthiness directive (AD) for the MD Helicopters, Inc. (MDHI) Model 600N helicopters. That AD currently requires certain inspections of both upper tailboom attachments, nutplates, and angles for a crack or thread damage, and repairing or replacing any cracked or damaged part. Also, that AD requires replacing certain tailboom attachment bolts, adding a washer to each bolt, and modifying both upper access covers. This action would require installing six additional inspection holes in the aft fuselage skin panels and inspecting the upper and lower tailboom attachment fittings, the upper longerons, and the angles and nutplates for cracks. Also, the AD would provide a terminating action of modifying the fuselage aft section to strengthen the tailboom attachments and longerons. This proposal is prompted by an analysis that shows that certain tailboom attachments and longerons may develop cracks. The actions specified by the proposed AD are intended to prevent failure of a tailboom attachment, loss of the tailboom, and subsequent loss of control of the helicopter.