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

The FAA proposes to supersede three existing airworthiness directives (ADs) that apply to certain Boeing Model 747 airplanes. The existing ADs currently require repetitive inspections of the body station (BS) 2598 bulkhead, and corrective action if necessary. This proposed AD would add a requirement to modify the bulkhead, including a one-time inspection and corrective action if necessary, which would terminate certain repetitive inspections. This proposed AD would also require a post-modification inspection of the modified area. This proposed AD results from new reports of cracking in all three areas that require inspection in accordance with the existing ADs. We are proposing this AD to prevent fatigue cracking of the BS 2598 bulkhead structure, which could result in inability of the structure to carry horizontal stabilizer flight loads, and reduced controllability of the airplane.

These special conditions are issued for the Gulfstream Aerospace Limited Partnership (GALP) Model G150 airplane. This airplane will have a novel or unusual design feature associated with use of a hydrophobic coating, rather than windshield wipers, as the means to maintain a clear portion of the windshield during precipitation conditions, as required by the airworthiness standards for transport category airplanes. 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.

This notice announces the availability of and requests comments on a proposed advisory circular (AC) that sets forth acceptable methods of compliance with 14 CFR part 25, Appendix H, section H25.5(a)(1). This proposed AC complements revisions to the airworthiness standards that are being proposed by a separate notice. This notice is necessary to give all interested persons an opportunity to present their views on the proposed AC.

The FAA proposes to supersede an existing airworthiness directive (AD) for certain RRC 250-B and 250-C series turboshaft and turboprop engines. That AD currently requires a onetime inspection of the fuel nozzle screen for contamination, and if contamination is found, inspection and cleaning of the entire aircraft fuel system before further flight. That AD also requires replacing the fuel nozzle with a new design fuel nozzle, at the next fuel nozzle overhaul or by June 30, 2006, whichever occurs first. This proposed AD would require the same actions, but would add additional part numbers (P/Ns) to the list of affected fuel nozzles. This proposed AD would also explain that the existing AD, as worded, allows certain part number (P/N) fuel nozzles back into service. Those fuel nozzles must not be allowed back into service. This proposed AD results from the discovery that several P/Ns of fuel nozzles were inadvertently left out of AD 2004-24-09. We are proposing this AD to minimize the risk of sudden loss of engine power and uncommanded shutdown of the engine due to fuel contamination and collapse of the screen in the fuel nozzle.

This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron (Bell) Model 47D1, 47G, 47G-2, 47G-2A, 47G-2A- 1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A and Coastal Helicopters, Inc. Model OH-13H (Tomcat Mark 5A, 6B, 6C) helicopters that have a certain scissors assembly or weld assembly scissors bracket installed. The AD requires, within 60 days, determining and recording the total hours time-in-service (TIS) for each Parts Manufacturer Approval (PMA)-produced scissors assembly and weld assembly scissors bracket and establishes a life limit for each affected part. This amendment is prompted by the need to establish a life limit on scissors assemblies and weld assembly scissors brackets produced under PMA No. PQ808SW or installed per Supplemental Type Certificate (STC) No. SH2772SW. The actions specified by this AD are intended to establish a life limit to prevent using a scissors assembly or weld assembly scissors bracket past it's life limit, which could result in failure of the part and subsequent loss of control of the helicopter.

This amendment supersedes an existing airworthiness directive (AD) for the MD Helicopters, Inc. (MDHI) Model 369A, H, HE, HM, HS, D, and E helicopters with a certain part-numbered main rotor blade (blade) and modified with a Helicopter Technology Company, LLC (HTC), Supplemental Type Certificate (STC) No. SR09172RC, SR09074RC, or SR09184RC. That AD currently requires recording on the component history card or equivalent record (record) each torque event (TE) on each blade, inspecting both surfaces of the blade, and replacing any cracked blade with an airworthy blade. Also, that AD establishes life limits for certain part-numbered blades. This amendment revises the model applicability, adds MDHI part-numbered blades, removes any reference to the life limits of the blades, changes the requirements for inspecting the blades, and revises the STC applicability. This amendment also provides that compliance with portions of certain documents constitutes alternative methods of compliance with portions of this AD, contains editorial changes for clarification, and makes some corrections. This amendment is prompted by additional reports of cracked blades and by the comments received in response to AD 2003-24- 01. The actions specified in this AD are intended to detect fatigue cracking of the blade to prevent blade failure and subsequent loss of control of the helicopter.

This amendment supersedes an existing airworthiness directive (AD) that applies to Pratt & Whitney (PW) JT8D-200 series turbofan engines. That AD currently requires installing and periodically inspecting individual or sets of certain part number (P/N) temperature indicators on the No. 4 and 5 bearing compartment scavenge oil tube and performance of any necessary corrective action. This AD requires installing and periodically inspecting two temperature indicators on all PW JT8D-200 series turbofan engines, including those incorporating high pressure turbine (HPT) containment hardware. This AD results from five uncontained HPT shaft failures. We are issuing this AD to prevent oil fires and the resulting fracture of the HPT shaft which can result in uncontained release of engine fragments; engine fire; in-flight engine shutdown; and possible airplane damage.

The FAA is notifying operators of a proposed advisory circular entitled ``Guidance on Aircraft Noise Certification Documents for International Flights.'' This advisory circular (AC) is in response to the International Civil Aviation Organization (ICAO) adoption of three acceptable options for managing noise certification documents. This AC offers guidance to affected operators on aircraft noise certification documentation they may choose to carry on board the aircraft that fly to a foreign country. This AC is designed to assist operators in preparing noise certification documents that may be requested by foreign authorities or airports. A suggested document format for operators to present noise certification documentation is provided.

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 135: Environmental Conditions and Test Procedures for Airborne Equipment.

This action establishes two colored Federal airways, Amber-5 (A-5) and Blue 1 (B-1), in Alaska. This action adds to the instrument flight rules (IFR) airway and route structure in Alaska. The FAA is taking this action to enhance safety and the management of aircraft operations in Alaska.

This action corrects an error in the legal description of a direct final rule, request for comments that was published in the Federal Register on Friday, July 29, 2005 (70 FR 43744).

This final rule establishes the Organization Designation Authorization (ODA) program. The ODA program expands the scope of approved tasks available to organizational designees; increases the number of organizations eligible for organizational designee authorizations; and establishes a more comprehensive, systems-based approach to managing designated organizations. This final rule also sets phaseout dates for the current organizational designee programs, the participants in which will be transitioned into the ODA program. This program is needed as the framework for the FAA to standardize the operation and oversight of organizational designees. The effect of this program will be to increase the efficiency with which the FAA appoints and oversees designee organizations, and allow the FAA to concentrate its resources on the most safety-critical matters.

This action establishes a Class E3 airspace area at Riverside March Field, CA.

On July 18, 2005, the Federal Aviation Administration (FAA) issued an order to show cause, which solicited written views on extending for a second time the FAA's August 18, 2004, order limiting scheduled operations at O'Hare International Airport (O'Hare). The August 2004 order made effective a series of schedule adjustments that the air carriers individually agreed to during a scheduling reduction meeting. These agreements, in general, resulted in a voluntary peak- hour arrival rate at O'Hare of eighty-eight scheduled flights, with the exception of the 8 p.m. hourthe final peak hour of the daywhen the rate would not exceed ninety-eight scheduled arrivals. The FAA previously extended the effectiveness of the August 2004 order through October 29, 2005. This notice announces that the FAA Administrator has signed an order that further extends the August 2004 order through April 1, 2006. The text of the extension order is published below as supplementary information to this notice.

This action corrects errors in the legal description of Class D airspace in a direct final rule, request for comments that was published in the Federal Register on Friday July 29, 2005 (70 FR 43742).

These special conditions are issued for Learjet Model 35, 35A, 36, and 36A airplanes modified by Genesis 3 Engineering, Inc. These modified airplanes will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The modification incorporates the installation of dual Revue Thommen AG AD30 Air Data Display Units and dual J2, Inc. Air Data Computers that perform critical functions. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for the protection of these systems from the effects of high-intensity radiated fields (HIRF). 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.

These special conditions are issued for Boeing Model 767-200, -300, and -300F series airplanes modified by ABX Air, Inc. These modified airplanes will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The modification incorporates the installation of an Innovative Solutions and Support Flat Panel Display System that performs critical functions. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for the protection of these systems from the effects of high-intensity radiated fields (HIRF). 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.

This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron (Bell) model helicopters modified with Aeronautical Accessories, Inc. (AAI), Supplemental Type Certificate (STC) SH2820SO or that have the affected AAI Parts Manufacturer Approval (PMA) parts installed. This action requires inspecting a certain part-numbered reservoir assembly adapter (adapter) for the counter bore depth (dimension D). If the dimension D of the adapter exceeds .860 inch, before further flight, this AD requires replacing the reservoir assembly and adapter with airworthy parts. This amendment is prompted by a report of a rupture of an adapter during nitrogen charging because of inadequate wall thickness for the operating pressures. The actions specified in this AD are intended to prevent the rupture of an adapter, uncontrolled jetting of pressurized gas from the nitrogen bottle, and subsequent injury to occupants or damage to the helicopter.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -300 series airplanes, powered by Pratt & Whitney PW2000 series engines. This AD requires repetitive inspections for loose or damaged components of the support brackets and associated fasteners for the hydraulic lines located in the nacelle struts, and any related investigative and corrective actions. This AD results from reports of damage and subsequent failure of the support brackets and associated fasteners for the hydraulic lines located internal to the upper fairing cavity of the nacelle struts. We are issuing this AD to prevent such failure, which, in conjunction with sparking of electrical wires, failure of seals that would allow flammable fluids to migrate to compartments with ignition sources, or overheating of the pneumatic ducts beyond auto-ignition temperatures, could result in an uncontained fire.

The FAA is superseding an existing airworthiness directive (AD) for Type R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12, and R334/4- 82-F/13 propeller assemblies. That AD currently requires initial and repetitive ultrasonic inspections of propeller hubs, part number (P/N) 660709201. This AD requires the same initial and repetitive ultrasonic inspections, but reduces the initial and repetitive compliance times for Type R334/4-82-F/13 propeller assemblies when used on Construcciones Aeronauticas, S.A. (CASA) 212 airplanes. This AD results from a report of a hub separation on a CASA 212 airplane. We are issuing this AD to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane.

The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplane models, as specified above. This AD requires modifying the floor proximity emergency escape path marking system. This AD results from information that the existing system design for interconnection of the emergency power supply units of the floor proximity emergency escape path marking system does not provide adequate floor path lighting and marking for safe evacuation of the airplane in the event of an emergency. We are issuing this AD to prevent inadequate lighting and marking of the escape path, which could delay or impede the flightcrew and passengers when exiting the airplane during an emergency landing.

The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections to detect cracks in various areas of the fuselage internal structure, and repair if necessary. This new AD requires repetitive inspections of additional areas of the fuselage internal structure, and related investigative/ corrective actions if necessary. This new AD also removes certain requirements from the existing AD. This AD results from fatigue testing of the fuselage structure of a Boeing Model 747SR series airplane. We are issuing this AD to prevent the loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane.

The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A320-111 airplanes. The existing AD currently requires repetitive inspections for cracking in the front and rear faces and at the crown fittings of the upper stringers of the center wing box and applicable repairs. This new AD requires continuing the repetitive inspections at revised thresholds and intervals, and applicable repairs. This AD results from a manufacturer survey of airplanes affected by the existing inspection program that led to the consequent revision of the thresholds and intervals of the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the upper stringers of the center wing box, which could lead to loss of structural integrity of the wing.

The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A320-111 airplanes; and Model A320-200, A321-100, and A321-200 series airplanes. This AD requires installing a bonding lead between the low pressure valve and the adjacent pipe assembly in each wing. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source for fuel vapor in the wing, which could result in fire or explosion in the adjacent wing fuel tank.

The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and -300 and A340-200 and -300 series airplanes. This AD requires inspecting to determine the part number and serial number of the left- and right-hand elevator assemblies, performing related investigative and corrective actions if necessary, and re- protecting the elevator assembly. This AD results from reports that areas on the top skin panel of the right-hand elevator have disbonded due to moisture penetration. We are issuing this AD to prevent disbonding of the elevator assembly, which could reduce the structural integrity of the elevator and result in reduced controllability of the airplane.