Federal Aviation Administration April 11, 2006 – Federal Register Recent Federal Regulation Documents

The FAA withdraws a notice of proposed rulemaking (NPRM) that proposed a new airworthiness directive (AD) for certain Gulfstream Model GV-SP series airplanes. The proposed AD would have required an inspection to determine the serial number of the anti-skid control unit (ACU) in the right electronics equipment rack, and replacement of the ACU with a new or serviceable ACU if necessary. Since the proposed AD was issued, we have received new data that indicate the identified unsafe condition has been corrected on all airplanes that would have been affected by the NPRM, and on all ACUs in the affected range of serial numbers. Accordingly, the proposed AD is withdrawn.

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 a reinforced flightdeck bulkhead. These proposed special conditions contain the additional safety standards that the Administrator considers necessary to establish an appropriate level of safety for a reinforced flightdeck bulkhead and are equivalent to the standards established by existing airworthiness regulations for the flightdeck door. Additional special conditions will be issued for other novel or unusual design features of the Airbus Model A380-800 airplane.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Boeing Model 737-600, -700, - 700C, and -800 series airplanes. The existing AD currently requires replacing the point ``D'' splice fitting between windows number 1 and 2 with a new splice fitting; performing an eddy current inspection for cracking of the holes in the structure common to the new splice fitting, including doing any related investigative actions; and performing corrective actions if necessary. This proposed AD would add repetitive inspections for cracking of the skin just below each splice fitting, and related corrective actions if necessary. This proposed AD results from full-scale fuselage fatigue testing on the splice fitting that failed prior to the design objective on Boeing Model 737-800 series airplanes, and a report of a cracked splice fitting on an operational airplane. We are proposing this AD to prevent cracking of the existing fitting, which may result in cracking through the skin and consequent decompression of the flight cabin.

The FAA proposes to adopt a new airworthiness directive (AD) for certain EMBRAER Model EMB-135BJ airplanes. This proposed AD would require inspecting for missing fire blocking material on the left- and right-hand partitions of the forward baggage compartment door; replacing the seal on both partitions; and performing corrective action if necessary. This proposed AD results from a report indicating that certain airplanes were delivered with the fire blocking material missing and the seal improperly installed on the partitions of the forward baggage compartment door. We are proposing this AD to detect and correct such discrepancies on the partitions of the forward baggage compartment door, which, in the event of a fire in the baggage compartment, could result in smoke propagating into the main cabin.

This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2005-05-20 that was sent previously to all known affected U.S. operators of certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200F, 747-300, 747-400, 747-400D, 747SP, 747SR, 767-200, 767-300, 777- 200, 777-300, and 777-300ER series airplanes by individual notices. This AD requires modification of certain flight deck door electronic equipment. This AD results from a report indicating that this equipment is defective. We are issuing this AD to prevent failure of this equipment, which could jeopardize flight safety.

The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 747 airplanes. This proposed AD would require repetitive inspections for cracking of the web of the station (STA) 2360 aft pressure bulkhead around the fastener heads in the critical fastener rows in the web lap joints, from the Y-chord to the inner ring; and repair if necessary. This proposed AD also would require a modification, which would terminate the repetitive inspections. This proposed AD results from analysis by the manufacturer that the radial lap splices of the STA 2360 aft pressure bulkhead are subject to widespread fatigue damage. We are proposing this AD to detect and correct cracking of the bulkhead web at multiple sites along the radial lap splice, which could join together to form cracks of critical length, and result in rapid decompression and loss of control of the airplane.

This document proposes to modify Class E airspace at Fremont, MI. Standard Instrument Approach Procedures have been developed for Fremont Municipal Airport, Fremont, MI. Controlled airspace extending upward from 700 feet or more above the surface of the earth is needed to contain aircraft executing these approaches. This action would increase the area of the existing controlled airspace for Fremont, MI.

These special conditions are issued for McDonnell Douglas DC- 8-72F airplanes modified by Avionics and Systems Integration Group, LLC. 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 Universal Avionics Systems Corporation EFI-600 Electronic Flight Instruments 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.

The FAA is adopting a new airworthiness directive (AD) for all Aerospatiale Model ATR42 airplanes. This AD requires one-time inspections to detect discrepancies (e.g., cracking, loose/sheared fasteners, distortion) of the upper skin and rib feet of the outer wing boxes, and repair if necessary. This AD results from a report of cracking on the upper skin and ribs of the outer wing box on an in- service airplane. We are issuing this AD to detect and correct these discrepancies, which could result in reduced structural integrity of the airplane.

The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas airplanes, as listed above. That AD currently requires an initial general visual or dye penetrant inspection, repetitive dye penetrant inspections, and replacement, as necessary, of the rudder pedal bracket. This new AD also requires, for certain airplanes, replacing the rudder pedal bracket assemblies with new, improved parts, which terminates the repetitive inspections. This AD results from a report of numerous cracked rudder pedal brackets found during inspections of certain affected airplanes. We are issuing this AD to prevent failure of the rudder pedal bracket assembly, which could result in the loss of rudder and braking control at either the captain's or first officer's position.

The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 757 airplanes. This AD requires repetitive measurements of the freeplay of each of the three power control units (PCUs) that move the rudder; repetitive lubrication of rudder components; and corrective actions if necessary. This AD results from a report of freeplay-induced vibration of the rudder. The potential for vibration of the control surface should be avoided because the point of transition from vibration to divergent flutter is unknown. We are issuing this AD to prevent excessive vibration of the airframe during flight, which could result in divergent flutter and loss of control of the airplane.

These Special Conditions are issued 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. These design features include side stick controllers, a body landing gear in addition to conventional wing and nose landing gears, electronic flight control systems, and flight envelope protection. These Special Conditions also pertain to the effects of such novel or unusual design features, such as their effects on the structural performance of the airplane. Finally, the Special Conditions pertain to the effects of certain conditions on these novel or unusual design features, such as the effects of high intensity radiated fields (HIRF) or of operation without normal electrical power. Additional Special Conditions will be issued for other novel or unusual design features of the Airbus A380- 800 airplanes. A list is provided in the section of this document entitled ``Discussion of Novel or Unusual Design Features.''