Federal Aviation Administration July 31, 2006 – Federal Register Recent Federal Regulation Documents

Special Conditions: Gulfstream Aerospace Corporation Model G-1159 Gulfstream II Airplanes; High Intensity Radiated Fields (HIRF)
Document Number: E6-12139
Type: Rule
Date: 2006-07-31
Agency: Federal Aviation Administration, Department of Transportation
These special conditions are issued for the Gulfstream Aerospace Corporation Model G-1159 Gulfstream II airplanes modified by Gulfstream Aerospace Corporation, Dallas, Texas. 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 electronic attitude direction indicators (ADI) and dual horizontal situation indicators (HSI). 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 the Administrator considers necessary to establish a level of safety equivalent to that provided by the existing airworthiness standards.
Airworthiness Directives; Hamilton Sundstrand Model 14RF-19 Propellers
Document Number: E6-12109
Type: Rule
Date: 2006-07-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is superseding an existing airworthiness directive (AD) for Hamilton Sundstrand model 14RF-19 propellers. That AD currently requires replacing certain actuator yokes with improved actuator yokes. This AD requires the same actions. This AD results from the discovery of a part number (P/N) error in the applicability paragraph of AD 2006-12-19. We are issuing this AD to prevent actuator yoke arms breaking during flight, which could cause high propeller vibration and contribute to reduced controllability of the airplane.
Airworthiness Directives; Raytheon (Beech) Model 400 and 400A Series Airplanes
Document Number: E6-12107
Type: Rule
Date: 2006-07-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Raytheon (Beech) Model 400 and 400A series airplanes. This AD requires, among other actions, reviewing the airplane logbook to determine whether certain generator control unit (GCU) installation kits are installed, and replacing any incorrect GCU. This AD results from reports of over-voltage conditions of the direct current (DC) starter generator. We are issuing this AD to prevent such over-voltage conditions due to the incompatibility between certain GCUs, which could result in the loss of normal electrical power, damage to some electrical components, or blown fuses during flight, and consequent unrecoverable loss of some or all essential equipment.
Airworthiness Directives; Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and -900 Series Airplanes
Document Number: E6-12099
Type: Rule
Date: 2006-07-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and -900 series airplanes. This AD requires modifying the wiring for the master dim and test system. For certain airplanes, this AD also requires related concurrent actions as necessary. This AD results from a report that the master dim and test system circuit does not have wiring separation of the test ground signal for redundant equipment in the flight compartment. We are issuing this AD to prevent a single fault failure in flight from simulating a test condition and showing test patterns instead of the selected radio frequencies on the communications panels, which could inhibit communication between the flightcrew and the control tower, affecting the continued safe flight of the airplane.
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), and MD-88 Airplanes
Document Number: E6-12094
Type: Rule
Date: 2006-07-31
Agency: Federal Aviation Administration, Department of Transportation
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models, that requires a one-time inspection for chafing or signs of arcing of the wire bundle for the auxiliary hydraulic pump, and other specified and corrective actions, as applicable. This AD also requires that, for certain airplanes, installation of additional protective sleeving on the upper portion of the auxiliary hydraulic pump wire assembly. This AD results from reports of shorted wires and evidence of arcing on the power cables of the auxiliary hydraulic pump, as well a fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent shorted wires or arcing at the auxiliary hydraulic pump, which could result in loss of auxiliary hydraulic power, or a fire in the wheel well of the airplane. The actions specified by this AD are also intended to reduce the potential of an ignition source adjacent to the fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes
Document Number: E6-12092
Type: Rule
Date: 2006-07-31
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires modification of the wiring distribution of the alternating current bus transfer power system and the right-hand and left-hand windshield anti- icing system, as necessary. This AD results from a report of electrical sparks coming out of the flight deck from a panel behind the left seat. We are issuing this AD to prevent failure of the sliding window heating element(s), due to electrical overload, which could result in smoke and fire in the cockpit.
Airworthiness Directives; Raytheon Aircraft Company Models C90A, B200, B200C, B300, and B300C Airplanes
Document Number: 06-6590
Type: Proposed Rule
Date: 2006-07-31
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) (formerly Beech) Models C90A, B200, B200C, B300, and B300C airplanes. This proposed AD would require you to inspect the flight controls for improper assembly or damage, and if any improperly assembled or damaged flight controls are found, take corrective action. This proposed AD results from a report of inspections of several affected airplanes with improperly assembled or damaged flight controls. We are proposing this AD to detect and correct improperly assembled or damaged flight controls, which could result in an unsafe condition by reducing capabilities of the flight controls and lead to loss of control of the airplane.
Airworthiness Directives; Raytheon Aircraft Company Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) Airplanes
Document Number: 06-6581
Type: Proposed Rule
Date: 2006-07-31
Agency: Federal Aviation Administration, Department of Transportation
We propose to supersede Airworthiness Directive (AD) 62-24-01, which applies to all Raytheon Aircraft Company (Raytheon) Beech Models 45 (YT-34), A45 (T-34A, B45), and D45 (T-34B) airplanes. AD 62-24-01 currently requires you to repetitively inspect, using the dye penetrant method, the front and rear horizontal stabilizer spars for cracks and replace any cracked stabilizer. Since we issued AD 62-24-01, we determined that using dye penetrant inspection method may not detect cracks before failure of the horizontal stabilizer spars. Therefore, we are proposing to require the surface eddy current inspection method to detect cracks in the horizontal stabilizer spars. Consequently, this proposed AD would retain the actions required in AD 62-24-01 and change the required inspection method from dye penetrant to surface eddy current. We are proposing this AD to prevent failure of the front and rear horizontal stabilizer spars caused by fatigue cracks. This failure could result in stabilizer separation and loss of control of the airplane.
Notice of Availability of Draft Advisory Circulars, Other Policy Documents and Proposed Technical Standard Orders
Document Number: 06-6566
Type: Notice
Date: 2006-07-31
Agency: Department of Transportation, Federal Aviation Administration
The FAA's Aircraft Certification Service publishes proposed non-regulatory documents that are available for public comment on the Internet at http://www.faa.gov/aircraft/draftdocs/.