Federal Aviation Administration March 2006 โ€“ Federal Register Recent Federal Regulation Documents

Petitions for Exemption; Summary of Petitions Received
Document Number: E6-4724
Type: Notice
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
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. 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.
Executive Committee of the Aviation Rulemaking Advisory Committee; Meeting
Document Number: E6-4714
Type: Notice
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is issuing this notice to advise the public of a meeting of the Executive Committee of the Aviation Rulemaking Advisory Committee.
Airworthiness Directives; General Electric Company CF6-45 and CF6-50 Series Turbofan Engines
Document Number: E6-4702
Type: Proposed Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to adopt a new airworthiness directive (AD) for certain General Electric Company (GE) CF6-45 and CF6-50 series turbofan engines. This proposed AD would require inspecting and reworking certain forward and aft center bodies of the long fixed core exhaust nozzle (LFCEN) assembly. This proposed AD results from reports of separation of LFCEN assembly forward and aft center bodies, due to high imbalance engine conditions during flight. We are proposing this AD to prevent the forward and aft center body of the LFCEN assembly from separating, leading to additional damage to the engine and airplane, possible damage to other airplanes, and to objects on the ground.
Airworthiness Directives; General Electric Company CT7-5, -7, and -9 Series Turboprop Engines
Document Number: E6-4700
Type: Proposed Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to supersede an existing airworthiness directive (AD) for General Electric Company (GE) CT7-5A2, -5A3, -7A, - 7A1, -9B, -9B1, and -9B2 turboprop engines, with certain part number (P/N) and serial number stage 2 turbine aft cooling plates installed. That AD currently requires a onetime eddy current inspection (ECI) of boltholes in certain P/N stage 2 turbine aft cooling plates. This proposed AD would expand the population of affected CT7 turboprop engine models, but would reduce the number of cooling plates affected. It would also require a onetime ECI of boltholes in certain P/N stage 2 turbine aft cooling plates. This proposed AD results from the manufacturer identifying the affected stage 2 turbine aft cooling plates by serial number. We are proposing this AD to prevent separation of the stage 2 turbine aft cooling plate, resulting in uncontained engine failure and damage to the airplane.
Notice Before Waiver With Respect to Land at Raleigh County Memorial Airport, Beckley, WV
Document Number: 06-3139
Type: Notice
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is publishing notice of proposed release of 23.945 acres of land at Raleigh County Memorial Airport, Beckley, West Virginia to the Raleigh County Airport Authority and the Raleigh County Commission for the development of an industrial park. There are no impacts to the Airport and the land is not needed for airport development as shown on the Airport Layout Plan. Fair Market Value of the land will be paid to the Raleigh County Airport and the Raleigh County Commission, and used for Airport purposes.
RTCA Special Committee 147: Minimum Operational Performance Standards for Traffic Alert and Collision Avoidance Systems Airborne Equipment
Document Number: 06-3138
Type: Notice
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 147: Minimum Operational Performance Standards for Traffic Alert and Collision Avoidance Systems Airborne Equipment.
Experimental Permits for Reusable Suborbital Rockets
Document Number: 06-3137
Type: Proposed Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The Federal Aviation Administration (FAA) proposes to amend its commercial space transportation regulations under the Commercial Space Launch Amendments Act of 2004. The FAA proposes application requirements for an operator of a reusable suborbital rocket to obtain an experimental permit. The FAA also proposes operating requirements and restrictions on launch and reentry of reusable suborbital rockets operated under a permit.
Reservation System for Unscheduled Arrivals at Chicago's O'Hare International Airport
Document Number: 06-3114
Type: Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
This action extends the expiration date of Special Federal Aviation Regulation (SFAR) No. 105 through October 28, 2006. This action is necessary to maintain the reservation system established for unscheduled arrivals at O'Hare International Airport while the FAA completes rulemaking associated with scheduled arrivals at the airport.
Operating Limitations at Chicago O'Hare International Airport
Document Number: 06-3113
Type: Notice
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
On March 13, 2006, the Federal Aviation Administration (FAA) issued an order to show cause, soliciting written views on extending through October 28, 2006, the August 2004 order limiting scheduled operations at O'Hare International Airport (O'Hare). The August 2004 order made effective a series of schedule adjustments that air carriers individually agreed to during a scheduling reduction meeting convened under 49 U.S.C. 41722. The FAA previously extended the order twice, most recently through April 1, 2006. After careful reflection on the written views submitted in this matter, the FAA is now extending the August 2004 order through October 28, 2006, but reserves the right to terminate the August 2004 order before that date if a final rule on congestion and delay reduction at O'Hare earlier takes effect.
Proposed Amendment to Class E Airspace; Kalispell, MT
Document Number: 06-3111
Type: Proposed Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
This action proposes to revise Class E surface airspace at Kalispell, MT. This action is necessary for the safety of Instrument Flight Rules (FR) aircraft executing Instrument Landing System (ILS) approach procedures to the newly extended runway at Kalispell/Glacier Park International Airport, Kalispell, MT.
RTCA Special Committee 205/EUROCAE Working Group 71: Software Considerations in Aeronautical Systems Second Joint Plenary Meeting
Document Number: 06-3110
Type: Notice
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 205/EUROCAE Working Group 71: Software Considerations in Aeronautical Systems.
Notice Before Waiver With Respect To Land at Lynchburg Regional Airport, Lynchburg, VA
Document Number: 06-3109
Type: Notice
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The Federal Aviation Administration (FAA) proposes to rule and invites public comment on the release of approximately thirty (30) acres of land at the Lynchburg Regional Airport, Lynchburg, Virginia from all Federal obligations, since the land is no longer needed for airport purposes. Reuse of the land for commercial/light industrial purposes represents a compatible land use. There are no impacts to the Airport and the land is not needed for airport development as shown on the Airport Layout Plan. The proceeds from the disposal of land acquired with Federal grants will be used for land acquisition and construction costs associated with the southerly extension to Runway 4- 22. The proceeds from the disposal of land acquired without Federal grants will be used for Airport operating and capital costs.
Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
Document Number: 06-3066
Type: Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires a one-time inspection for scribe lines and cracks in the fuselage skin at certain lap joints, butt joints, external repair doublers, and other areas; and related investigative/ corrective actions if necessary. This AD results from reports of fuselage skin cracks adjacent to the skin lap joints on airplanes that had scribe lines. Scribe line damage can also occur at many other locations, including butt joints, external doublers, door scuff plates, the wing-to-body fairing, and areas of the fuselage where decals have been applied or removed. We are issuing this AD to prevent rapid decompression of the airplane due to fatigue cracks resulting from scribe lines on pressurized fuselage structure.
Airworthiness Directives; McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 Airplanes
Document Number: 06-3064
Type: Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas airplanes identified above. This AD requires a one- time inspection of the aft attach fitting assembly of the spoiler link to determine the part number, and further investigative action and replacement of the assembly with a new or serviceable assembly, if necessary. This AD results from a determination that the holes of certain aft attach fitting assemblies of the spoiler link were not cold-worked during production. We are issuing this AD to prevent fatigue cracking of the aft attach fitting of the spoiler link and consequent failure of the fitting. Failure of the fitting could result in an asymmetrical lift condition and consequent reduced controllability of the airplane.
Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
Document Number: 06-3063
Type: Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300-600 series airplanes. This AD requires modifying nine bolt holes in the vertical flange to prevent cracking before the inspection threshold of AD 98-18-02. This AD results from reports of cracking in the vertical web of the center spar sealing angles of the wing earlier than the inspection interval specified in the existing AD. We are issuing this AD to prevent crack formation in the sealing angles; such cracks could rupture the sealing angle and lead to subsequent crack formation in the bottom skin of the wing, and resultant reduced structural integrity of the center spar section of the wing.
Airworthiness Directives; Airbus Model A318-100 and A319-100 Series Airplanes; Model A320-111 Airplanes; and Model A320-200, A321-100, and A321-200 Series Airplanes
Document Number: 06-3062
Type: Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318-100 and A319-100 series airplanes; Model A320-111 airplanes; and Model A320-200, A321-100, and A321-200 series airplanes. This AD requires repetitive detailed inspections of the trimmable horizontal stabilizer actuator (THSA) attachments for proper clearances, and any crack, damage, or metallic particles; related corrective actions if necessary; and a report of the inspection results to the manufacturer. This AD results from a report that during lab testing to verify the performance of the THSA's secondary load path with a simulated failure of the THSA's primary load path, the secondary load path's nut did not jam (as it was supposed to do). We are issuing this AD to ensure the integrity of the THSA's primary load path, which if failed, could result in latent (undetected) loading and eventual failure of the THSA's secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane.
Airworthiness Directives; McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes
Document Number: 06-3061
Type: Rule
Date: 2006-03-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This AD requires repetitive inspections for stress corrosion cracks of the main fuselage frame, and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from several reports of cracking of the main fuselage frame. We are issuing this AD to detect and correct stress corrosion cracking of the main fuselage frame, which could result in extensive damage to adjacent structure and reduced structural integrity of the airplane.
Airworthiness Directives; Gulfstream Model GV and GV-SP Series Airplanes
Document Number: E6-4621
Type: Proposed Rule
Date: 2006-03-30
Agency: Federal Aviation Administration, Department of Transportation
The FAA is revising an earlier proposed airworthiness directive (AD) for all Gulfstream Model GV and certain Model GV-SP series airplanes. The original NPRM would have required a one-time inspection of the left and right aileron and elevator actuators to determine the part and serial numbers of each actuator, repetitive inspections of suspect actuators to detect broken damper shafts, and replacement of any actuator having a broken damper shaft. The original NPRM would also have required that operators report any broken damper shaft they find to the FAA. The original NPRM would also have provided an optional terminating action for the repetitive inspection requirements of the proposed AD. The original NPRM resulted from reports of broken or cracked damper shafts within the aileron and elevator actuator assemblies. This action revises the original NPRM by proposing to mandate the previously optional terminating action. We are proposing this supplemental NPRM to prevent broken damper shafts, which could result in locking of an aileron or elevator actuator (hard-over condition), which would activate the hard-over protection system (HOPS), resulting in increased pilot workload and consequent reduced controllability of the airplane.
Airworthiness Directives; Boeing Model 737-200C Series Airplanes
Document Number: E6-4620
Type: Proposed Rule
Date: 2006-03-30
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Boeing Model 737-200C series airplanes. The existing AD currently requires a one-time external detailed inspection for cracking of the fuselage skin in the lower lobe cargo compartment; repetitive internal detailed inspections for cracking of the frames in the lower lobe cargo compartment; repair of cracked parts; and terminating action for the repetitive internal detailed inspections. This proposed AD restates the requirements of the existing AD and adds a requirement to perform repetitive detailed inspections of the body station (BS) 360 and BS 500 fuselage frames, after accomplishing the terminating action, and repair if necessary. This proposed AD results from multiple reports that the existing AD is not fully effective in preventing cracks in the BS 360 and BS 500 fuselage frames. We are proposing this AD to detect and correct cracking of the fuselage frames from BS 360 to BS 500B, which, if not detected, could lead to loss of the cargo door during flight and consequent rapid decompression of the airplane.
Airworthiness Directives; Boeing Model 777 Airplanes
Document Number: E6-4619
Type: Proposed Rule
Date: 2006-03-30
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 777 airplanes. This proposed AD would require, for the drive mechanism of the horizontal stabilizer, repetitive detailed inspections for discrepancies; repetitive lubrication of the ballnut and ballscrew; repetitive measurements of the freeplay between the ballnut and the ballscrew; and corrective action if necessary. This proposed AD results from a report of extensive corrosion of a ballscrew in the drive mechanism of the horizontal stabilizer on a Boeing Model 757 airplane, which is similar in design to the ballscrew on certain Model 777 airplanes. We are proposing this AD to prevent an undetected failure of the primary load path for the ballscrew in the horizontal stabilizer and subsequent wear and failure of the secondary load path, which could lead to loss of control of the horizontal stabilizer and consequent loss of control of the airplane.
Airworthiness Directives; Airbus Model A310 Airplanes, Model A300 B4-600 Series Airplanes, Model A300 B4-600R Series Airplanes, Model A300 F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes
Document Number: 06-3119
Type: Rule
Date: 2006-03-30
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310 airplanes, Model A300 B4-600 series airplanes, Model A300 B4-600R series airplanes, Model A300 F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes. This AD requires inspections of the rudder for discrepancies and corrective action if necessary. This AD also requires reporting all inspection results to the airplane manufacturer and the FAA. This AD results from two separate findings of inner skin disbonding discovered while undergoing unrelated repair and maintenance procedures. We are issuing this AD to detect discrepancies of the rudder, which could result in reduced structural integrity of the rudder.
Airworthiness Directives; Cirrus Design Corporation Models SR20 and SR22 Airplanes
Document Number: 06-2982
Type: Rule
Date: 2006-03-30
Agency: Federal Aviation Administration, Department of Transportation
The FAA adopts a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to inspect the fuel line and wire bundles for any chafing damage; replace any damaged fuel line and repair any damaged wires or sheathing of the wire harness if any chafing damage is found; and install (to prevent any chafing damage to the fuel line and wire bundles) the forward loop clamp, fuel line shield, aft loop clamp, and anti-chafe tubing. This AD results from reports of fuel line leaks resulting from wire chafing on the fuel lines. We are issuing this AD to detect, correct, and prevent damage to the fuel line and wire bundles, which could result in fuel leaks. This failure could lead to unsafe fuel vapor within the cockpit and possible fire.
Airworthiness Directives; Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131, -231, and -232 Airplanes
Document Number: 06-2961
Type: Rule
Date: 2006-03-30
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131, -231, and -232 airplanes. This AD requires inspecting for cracks or failure of the primary load path components of the engine forward mount, and corrective action if necessary. This AD also requires removing, re-installing, and re-torquing the attachment bolts for the secondary load path. This AD results from a report that, during modification of certain engine forward mount assemblies of the left and right engines done at an engine shop visit, an incorrect torque was applied to the attachment bolts. We are issuing this AD to prevent structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from the airplane.
Airworthiness Directives; Bombardier Model DHC-8-301, -311, and -315 Airplanes
Document Number: 06-2960
Type: Rule
Date: 2006-03-30
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-301, -311, and -315 airplanes. This AD requires replacing the pressure control valve of the Type 1 emergency door. This AD results from reports that the pressure control valve of the Type 1 emergency door is susceptible to freezing. We are issuing this AD to ensure that the pressure control valve does not freeze and prevent the door seal from deflating, which could result in the inability to open the door in an emergency.
Airworthiness Directives; Airbus Model A321-100 and -200 Series Airplanes
Document Number: 06-2959
Type: Rule
Date: 2006-03-30
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A321-100 and -200 series airplanes. This AD requires replacing the crashworthiness pins on the side-stay of the main landing gear (MLG) with new pins having an increased internal notch diameter. This AD results from testing on the side-stay crashworthiness pins on the MLG, which revealed that, in the case of an emergency landing, the crashworthiness pins installed will not ensure a correct MLG collapse. We are issuing this AD to prevent a punctured fuel tank, which could cause damage to the airplane or injury to passengers.
Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
Document Number: 06-2958
Type: Rule
Date: 2006-03-30
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive general visual inspections for dirt, debris, and drain blockage and cleaning of the aft fairing cavities of the engine struts; and modification of the aft fairings, which terminates the repetitive general visual inspections. This AD results from a report indicating that water had accumulated in the cavities of the engine strut aft fairings. We are issuing this AD to prevent drain blockage by debris that, when combined with leaking, flammable fluid lines passing through the engine strut aft fairing, could allow flammable fluids to build up in the cavity of the aft fairing, and consequently could be ignited by the engine exhaust nozzle located below the engine strut, resulting in an explosion or uncontrolled fire.
Airworthiness Directives; DORNIER LUFTFAHRT GmbH Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 Airplanes
Document Number: E6-4556
Type: Proposed Rule
Date: 2006-03-29
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for all DORNIER LUFTFAHRT GmbH (DORNIER) Models 228-100, 228-101, 228-200, 228- 201, 228-202, and 228-212 airplanes. This proposed AD would require you to repetitively inspect the wiring in the flight deck overhead panels (locations 5VE and 6VE) for chafing and damage and repair any chafed or damaged wires. Regardless of the results of each inspection, this proposed AD would require you to assure correct installation of the wiring in the flight deck overhead panels by reattaching or replacing the wire tie attachment holders and securing any loose wires to the wire tie attachment holders with plastic wire ties. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are proposing this AD to detect, correct, and prevent chafed or damaged wires in the flight deck overhead panels, which could result in short-circuiting of related wiring. This condition could lead to electrical failure of affected systems and potential fire in the flight deck.
Special Conditions: Airbus Model A380-800 Airplane, Extendable Length Escape System
Document Number: E6-4511
Type: Proposed Rule
Date: 2006-03-29
Agency: Federal Aviation Administration, Department of Transportation
This notice proposes special conditions for the Airbus A380- 800 airplane. This airplane will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. Many of these novel or unusual design features are associated with the complex systems and the configuration of the airplane, including its full- length double deck. For these design features, the applicable airworthiness regulations do not contain adequate or appropriate safety standards regarding extendable length escape slides. These proposed 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. Additional special conditions will be issued for other novel or unusual design features of the Airbus Model A380-800 airplane.
Special Conditions: Airbus Model A380-800 Airplane, Design Roll Maneuver
Document Number: E6-4509
Type: Proposed Rule
Date: 2006-03-29
Agency: Federal Aviation Administration, Department of Transportation
This notice proposes special conditions for the Airbus A380- 800 airplane. This airplane will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. Many of these novel or unusual design features are associated with the complex systems and the configuration of the airplane, including its full- length double deck. For these design features, the applicable airworthiness regulations do not contain adequate or appropriate safety standards for design roll maneuvers. These proposed 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. Additional special conditions will be issued for other novel or unusual design features of the Airbus Model A380-800 airplane.
Special Condition: Robinson R44 Helicopters, ยง 27.1309, Installation of an Autopilot (AP) Stabilization Augmentation System (SAS) That Has Potential Failure Modes With Criticality Categories Higher Than Those Envisioned by the Applicable Airworthiness Regulations
Document Number: 06-3013
Type: Rule
Date: 2006-03-29
Agency: Federal Aviation Administration, Department of Transportation
This special condition is issued for the modification of the Robinson Model R44 helicopter. This modification will have novel or unusual design features associated with installing a complex Autopilot/ Stabilization Augmentation System (AP/SAS) that has potential failure modes with more severe adverse consequences than those envisioned by the existing applicable airworthiness regulations. This proposal contains the additional safety standards that the Administrator considers necessary to ensure that the failures and their effects are sufficiently analyzed and contained.
Airworthiness Directives; GROB-WERKE Model G120A Airplanes
Document Number: 06-2983
Type: Rule
Date: 2006-03-29
Agency: Federal Aviation Administration, Department of Transportation
This document makes a correction to Airworthiness Directive (AD) 2005-13-09, which published in the Federal Register on August 23, 2005 (70 FR 49184), and applies to certain GROB-WERKE Model G120A airplanes. AD 2005-13-09 requires replacement of the main landing gear (MLG) up-lock hook assembly. Current language in paragraph (e)(2) of AD 2005-13-09 incorrectly references the MLG up-lock assembly as ``elevator and aileron hinge pins.'' This AD corrects that paragraph to reference the appropriate part number MLG up-lock hook assembly.
Special Conditions: Airbus Model A380-800 Airplane, Airplane Jacking Loads
Document Number: E6-4494
Type: Proposed Rule
Date: 2006-03-28
Agency: Federal Aviation Administration, Department of Transportation
This notice proposes special conditions for the Airbus A380- 800 airplane. This airplane will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. Many of these novel or unusual design features are associated with the complex systems and the configuration of the airplane, including its full- length double deck. For these design features, the applicable airworthiness regulations do not contain adequate or appropriate safety standards regarding airplane jacking loads. These proposed 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. Additional special conditions will be issued for other novel or unusual design features of the Airbus Model A380-800 airplane.
Airworthiness Directives; McDonnell Douglas Model 717-200 Airplanes
Document Number: E6-4443
Type: Proposed Rule
Date: 2006-03-28
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to adopt a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This proposed AD would require replacing the lightning critical clamp bases of the fuel tank vent system with improved clamp bases; and checking the electrical bond of the modified self-bonding mounting clamps. This proposed AD results from an investigation that revealed the aluminum foil strip on the nylon base of the ground clamps can fracture or separate from the base. We are proposing this AD to ensure that the fuel pipes are properly bonded to the airplane structure. Improper bonding could prevent electrical energy from a lightning strike from dissipating to the airplane structure, which could result in a fuel tank explosion.
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes; and Model A340-541 and A340-642 Airplanes
Document Number: E6-4442
Type: Proposed Rule
Date: 2006-03-28
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 and A340-642 airplanes. This proposed AD would require an inspection for anti-fretting material contamination of the Halon filters and plumbing parts of the flow metering system (FMS) and flow metering compact unit (FMCU) in the lower deck cargo compartment (LDCC) and bulk crew rest compartment (BCRC), as applicable; other specified actions; and corrective actions if necessary. This proposed AD results from a report that the FMS and FMCU of the fire extinguishing system may be blocked by anti-fretting material contamination. We are proposing this AD to prevent such anti- fretting material contamination, which could reduce the effectiveness of the fire extinguisher system to discharge fire extinguishing agents and to lower the concentration of Halon gas in the LDCC or BCRC in a timely manner. An ineffective fire extinguisher system in the event of a fire could result in an uncontrollable fire in the LDCC or BCRC.
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
Document Number: 06-2981
Type: Rule
Date: 2006-03-28
Agency: Federal Aviation Administration, Department of Transportation
The FAA is revising an existing airworthiness directive (AD), which applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the maintenance requirements manual (MRM) by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units. That AD also requires new repetitive functional tests of the pilot input lever of the PFS unit, and corrective actions if necessary; and after initiating the new tests, requires removal of the existing procedures for the repetitive functional tests from the MRM. This AD retains the requirements of the existing AD and further clarifies the requirements of the AD. This AD results from a report that the shear pin located in the input lever of two PFS units failed due to fatigue. We are issuing this AD to prevent undetected failure of the shear pin of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane.
Air Traffic Procedures Advisory Committee
Document Number: 06-2974
Type: Notice
Date: 2006-03-28
Agency: Federal Aviation Administration, Department of Transportation
The FAA is issuing this notice to advise the public that a meeting of the Federal Aviation Air Traffic Procedures Advisory Committee (ATPAC) will be held to review present air traffic control procedures and practices for standardization, clarification, and upgrading of terminology and procedures.
Special Conditions: Airbus Model A380-800 Airplane, Loading Conditions for Multi-Leg Landing Gear
Document Number: 06-2973
Type: Proposed Rule
Date: 2006-03-28
Agency: Federal Aviation Administration, Department of Transportation
This notice proposes special conditions for the Airbus A380- 800 airplane. This airplane will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. Many of these novel or unusual design features are associated with the complex systems and the configuration of the airplane, including its full-length double deck. For these design features, the applicable airworthiness regulations do not contain adequate or appropriate safety standards regarding loading conditions for multi-leg landing gear. These proposed 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. Additional special conditions will be issued for other novel or unusual design features of the Airbus Model A380-800 airplane.
Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Airplanes
Document Number: E6-4411
Type: Proposed Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. The existing AD currently requires a one-time inspection to detect corrosion of the flap structure and machined ribs, corrective actions if necessary, and reprotection of the rib boss bores. This proposed AD would require a records review of the results of that inspection, and an additional inspection and related investigative/corrective action if necessary. This proposed AD results from the development of an improved inspection for corrosion in the subject area. We are proposing this AD to detect and correct corrosion in the flap structure and machined ribs, which could result in reduced structural integrity of the airplane.
Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes
Document Number: E6-4409
Type: Proposed Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 airplanes. This proposed AD would require revising the Limitations section of the airplane flight manual (AFM); performing a one-time hardness test of certain ribs of the left- and right-hand engine pylons, as applicable, which would terminate the AFM limitations; and performing related corrective actions if necessary. This proposed AD results from a report that certain stainless steel ribs installed in the engine pylon may not have been heat-treated during manufacture, which could result in significantly reduced structural integrity of the pylon. We are proposing this AD to detect and correct reduced structural integrity of the engine pylon, which could lead to separation of the engine from the airplane.
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes, and Model A340-541 and A340-642 Airplanes
Document Number: E6-4408
Type: Proposed Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The FAA is revising an earlier NPRM for an airworthiness directive (AD) that would have applied to certain Airbus Model A330- 200, A330-300, A340-200, and A340-300 series airplanes, and A340-541 and A340-642 airplanes. The original NPRM would have required inspecting to determine if certain emergency escape slides/slide rafts (referred to as slide/rafts) are installed in certain crew/ passenger doors; and, if so, performing a one-time inspection to determine if the electrical harnesses of the slide/rafts are properly routed, and rerouting the harnesses if necessary. The original NPRM resulted from a report that a slide/raft failed to deploy properly during a deployment test. This action revises the original NPRM by expanding the applicability of the proposed AD. We are proposing this AD to detect and correct improper routing of the electrical harnesses of certain slide/rafts, which could prevent proper deployment of the slide/rafts and delay evacuation of passengers and flightcrew during an emergency.
Airworthiness Directives; Airbus Model A300 B4 Series Airplanes; Model A300 B4-600 Series Airplanes; Model A300 C4-605R Variant F Airplanes; Model A310-200 Series Airplanes; and Model A310-300 Series Airplanes
Document Number: E6-4407
Type: Proposed Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A300 B4-600 and A300 C4-600 series airplanes. The existing AD currently requires a one- time inspection to detect damage of the pump diffuser guide slots (bayonet) of the center tank fuel pumps, the pump diffuser housings, and the pump canisters; repetitive inspections to detect damage of the fuel pumps and the fuel pump canisters; and corrective action, if necessary. This proposed AD would add, for new airplanes, repetitive inspections of the pump bodies for cracking, damage, and missing and broken fasteners; repetitive inspections of the fuel pump canisters for a cracked flange web; and corrective actions if necessary. For all airplanes, this proposed AD would also add replacement of the fuel pump canisters with new reinforced fuel pump canisters, which ends the repetitive inspections. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to detect and correct damage of the center tank fuel pumps and fuel pump canisters, which could result in separation of a pump from its electrical motor housing, loss of flame trap capability, and a possible fuel ignition source in the center fuel tank.
Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
Document Number: E6-4406
Type: Proposed Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The FAA is revising an earlier supplemental NPRM for an airworthiness directive (AD) that applies to certain Airbus airplanes as listed above. The first supplemental NPRM would have required repetitively inspecting for cracking in the web of nose rib 7 of the inner flap on the wings, and performing related investigative/ corrective actions if necessary. The original NPRM resulted from reports of cracking in the web of nose rib 7 of the inner flap. This action revises the first supplemental NPRM by requiring eventual replacement of nose rib 7 with a new, improved rib, which would terminate the proposed inspections. This action also removes from the applicability airplanes on which the improved nose rib 7 was installed during production. We are proposing this supplemental NPRM to prevent cracking in the web of nose rib 7, which could result in rupture of the attachment fitting between the inner flap and flap track 2, and consequent reduced structural integrity of the flap.
Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes; and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
Document Number: E6-4402
Type: Proposed Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The FAA is revising an earlier NPRM for an airworthiness directive (AD) that applies to certain Airbus Model A300 B2 and A300 B4 series airplanes, and A300-600 series airplanes. The original NPRM would have superseded an existing AD that currently requires repetitive inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary. That AD also requires modification of Gear Rib 5 of the MLG attachment fittings, which constitutes terminating action for the repetitive inspections. The original NPRM proposed to reduce the compliance times for all inspections, and require doing the inspections in accordance with new revisions of the service bulletins. The original NPRM resulted from new service information that was issued by the manufacturer and mandated by the French airworthiness authority. This new action revises the original NPRM by proposing new repetitive inspections of certain areas of the attachment fittings that were repaired in accordance with the actions specified in both the existing AD and the original NPRM. We are proposing this supplemental NPRM to prevent fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane.
Airworthiness Directives; Bombardier Model DHC-7 Airplanes
Document Number: E6-4400
Type: Proposed Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The FAA is revising an earlier NPRM for an airworthiness directive (AD) that applies to all Bombardier Model DHC-7 airplanes. The original NPRM would have required implementing a corrosion prevention and control program (CPCP) either by accomplishing specific tasks or by revising the maintenance inspection program to include a CPCP. The original NPRM resulted from a determination that, as airplanes age, they are more likely to exhibit indications of corrosion. This action revises the original NPRM by clarifying certain compliance aspects of the proposed AD that were not adequately defined in the original NPRM. We are proposing this supplemental NPRM to prevent structural failure of the airplane due to corrosion.
Airworthiness Directives; Pacific Aerospace Corporation Ltd. Model 750XL Airplanes
Document Number: E6-4386
Type: Proposed Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for certain Pacific Aerospace Corporation Ltd. Model 750XL airplanes. This proposed AD would require you to inspect the condition of the insulation of the wiring adjacent to the electrical plugs mounted in the left-hand (LH) and right-hand (RH) sides of the forward end of the cockpit center console for signs of abrasion and arcing. If you find evidence of abrasion or arcing, this proposed AD would require you to replace the affected wire(s) and secure the wires away from the back shells of the electrical plugs. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand. We are proposing this AD to detect and correct damaged wires on the LH and RH sides of the forward end of the cockpit center console, which could result in short-circuiting of the related wiring. This could lead to electrical failure of affected systems and potential fire in the cockpit.
Environmental Impacts: Policies and Procedures
Document Number: E6-4375
Type: Notice
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The Federal Aviation Administration (FAA) has revised its procedures for implementing the National Environmental Policy Act by revising Order 1050.1E, Environmental Impacts: Policies and Procedures, with Order 1050.1E, Change 1. The revisions include: changes for clarification, consistency, and addition of information; corrections; and editorial changes. This notice informs the public of the availability of the Final Order. This notice also provides the public with information on how to access Order 1050.1E, Change 1 on FAA's Office of Environment and Energy Web site.
Programmatic Environmental Impact Statement: Launches and Reentries Under an Experimental Permit
Document Number: E6-4373
Type: Notice
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The Commercial Space Launch Amendments Act of 2004 (CSLAA), enacted on December 23, 2004, directs the Secretary of Transportation and, through delegations, the Federal Aviation Administration (FAA) Office of Commercial Space Transportation, to establish an experimental permit regime for developmental reusable suborbital rockets. The intent of Congress for the experimental permit regime is to reduce the regulatory burden on developers of reusable suborbital rockets. Congress intended that, ``[a]t a minimum, permits should be granted more quickly and with fewer requirements than licenses.'' (H. Rep. 108.429 Sec. VII) To address the intent of Congress and meet a reduced timeline for issuing permits, a congressionally mandated 120 day timeline, the FAA is preparing a Programmatic Environmental Impact Statement (PEIS) to evaluate the impacts of launches and reentries conducted under an experimental permit. The intent of the PEIS is to facilitate the development of a permit application package and the subsequent environmental review by FAA, and to ensure that the issuance of an experimental permit is consistent with the FAA's mission of protecting public health and safety, safety of property, and the national security and foreign policy interests of the United States. The proposed action for this PEIS is to issue experimental permits for the launch and reentry of reusable suborbital rockets. Suborbital rocket means a vehicle, rocket-propelled in whole or in part, intended for flight on a suborbital trajectory, the thrust of which is greater than its lift for the majority of the rocket-powered portion of its ascent. Suborbital trajectory means the intentional flight path of a launch vehicle, reentry vehicle, or any portion thereof, whose vacuum instantaneous impact point does not leave the surface of the Earth. The FAA will prepare the PEIS in accordance with the National Environmental Policy Act (NEPA), the Council on Environmental Quality (CEQ) NEPA regulations (40 Code of Federal Regulations [CFR] Parts 1500-1508), and the FAA procedures for implementing NEPA in FAA Order 1050.1E.
Establishment of Area Navigation Instrument Flight Rules Terminal Transition Route (RITTR) T-210; Jacksonville, FL
Document Number: 06-2920
Type: Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
This action establishes a RITTR, designated T-210, in the Jacksonville, FL, terminal area. The purpose of this route is to expedite the handling of Instrument Flight Rules (IFR) overflight aircraft transitioning through busy terminal airspace. The FAA is taking this action to enhance the safe and efficient use of the navigable airspace in the Jacksonville, FL, terminal area.
Notice of Intent to Rule on Request to Release Airport Property at Ontario Municipal Airport, Ontario, OR
Document Number: 06-2916
Type: Notice
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to rule and invite public comment on the release of land at Ontario Municipal Airport under the provisions of Section 125 of the Wendell H. Ford Aviation Investment Reform Act for the 21st Century (AIR 21), now 49 U.S.C. 47107(h)(2).
Exemptions for Passenger Carrying Operations Conducted for Compensation and Hire in Other Than Standard Category Aircraft
Document Number: 06-2915
Type: Proposed Rule
Date: 2006-03-27
Agency: Federal Aviation Administration, Department of Transportation
This document identifies and provides guidance on the current FAA policies regarding requests for an exemption from the rules governing the operation of aircraft for the purpose of carrying passengers on living history flights in return for compensation. Specifically, this document clarifies which aircraft are potentially eligible for an exemption and what type of information petitioners should submit to the FAA for proper consideration of relief from the applicable regulations. This policy does not apply to flight crew training or commercial space transportation issues.