Historic Preservation, Advisory Council July 24, 2015 – Federal Register Recent Federal Regulation Documents

This notice announces the existence of and requests comments on the proposed airworthiness design standards for acceptance of the AutoGyro Model Calidus gyroplane under the regulations for primary category aircraft.

The Federal Motor Carrier Safety Administration (FMCSA) requests public comment on an application for exemption from Volvo Trucks of North America (Volvo) to allow the placement of rain and ambient light detection sensors on Volvo commercial motor vehicles (CMV) lower in the windshield than is currently permitted by the Agency's regulations in order to utilize a mounting location that allows the sensor to function correctly. The Federal Motor Carrier Safety Regulations (FMCSRs) currently require antennas, transponders, and similar devices to be located not more than 6 inches below the upper edge of the windshield, outside the area swept by the windshield wipers, and outside the driver's sight lines to the road and highway signs and signals. Volvo believes that mounting the sensor lower in the windshield will allow it to function properly while maximizing the external view of the road and maintaining an adequate forward facing field of view for the driver.

FMCSA announces its decision to renew the exemptions from the vision requirement in the Federal Motor Carrier Safety Regulations for 13 individuals. FMCSA has statutory authority to exempt individuals from the vision requirement if the exemptions granted will not compromise safety. The Agency has concluded that granting these exemption renewals will provide a level of safety that is equivalent to or greater than the level of safety maintained without the exemptions for these commercial motor vehicle (CMV) drivers.

We propose to supersede Airworthiness Directive (AD) 2012-15- 13, which applies to certain The Boeing Company Model 747-100B SUD, 747-300, 747-400, and 747-400D series airplanes; and Model 747-200B series airplanes having a stretched upper deck. AD 2012-15-13 currently requires inspections for cracking and discrepancies of certain fasteners; modification of the frame-to-tension-tie joints; repetitive post-modification inspections; related investigative and corrective actions if necessary; and repetitive inspections for cracking in the tension tie channels, and repair if necessary. For certain airplanes, AD 2012-15-13 also requires an inspection to determine if the angle is installed correctly, and re-installation if necessary; and an inspection at the fastener locations where the tension tie previously attached to the frame prior to certain modifications, and repair if necessary. Since we issued AD 2012-15-13, an evaluation indicated that the upper deck is subject to widespread fatigue damage (WFD). This proposed AD would add a new inspection for cracking in the tension tie channels and post-modification inspections of the modified tension ties for cracking, and repair if necessary. We are proposing this AD to prevent fatigue cracking of the tension ties, shear webs, and frames of the upper deck, which could result in rapid decompression and reduced structural integrity of the airplane.

The Federal Aviation Administration (FAA) has revised its procedures for implementing the National Environmental Policy Act (NEPA) by issuing Order 1050.1F, Environmental Impacts: Policies and Procedures. Order 1050.1F cancels Order 1050.1E, Environmental Impacts: Policies and Procedures. The revisions in Order 1050.1F include reorganization of the Order to make it easier to use, clarification of requirements, additions to the list of Categorical Exclusions (CATEXs), updating of policies and procedures to be consistent with recent guidance, addition of provisions for emergency actions, and updating of terminology to incorporate the Next Generation Air Transportation System (NextGen). The FAA issued a notice and request for comment in the Federal Register on August 14, 2013 (78 FR 49596). All comments received were considered in the issuance of the final Order. This notice summarizes the changes made to Order 1050.1E and includes responses to substantive comments received.

We are superseding Airworthiness Directive (AD) 2004-13-02, which applied to certain The Boeing Company Model 747-100, -200B, and - 200F series airplanes. AD 2004-13-02 required repetitive inspections to find discrepancies in the upper and lower skins of the fuselage lap joints, and repair if necessary. This new AD adds post-repair inspections for cracking and corrosion, and repair if necessary; structural modification at the lap joints; and post-modification inspections for cracking and corrosion, and repair if necessary. This AD was prompted by an evaluation by the design approval holder (DAH) that indicates the longitudinal lap joints are subject to widespread fatigue damage (WFD). The actions mandated by this AD are necessary to reach the limit of validity (LOV). We are issuing this AD to detect and correct fatigue cracking in the upper and lower skins of the fuselage lap joints, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage.

We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of wear of the trimmable horizontal stabilizer actuator (THSA). This AD requires repetitive inspections of the THSA for damage, and replacement if necessary; and replacement of the THSA after reaching a certain life limit. We are issuing this AD to detect and correct wear on the THSA, which would reduce the remaining life of the THSA, possibly resulting in premature failure and consequent reduced control of the airplane.

We are superseding Airworthiness Directive (AD) 2012-13-06, for all Airbus Model A300 series airplanes and all Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2012-13-06 required a one-time detailed inspection to determine the length of the fire shut-off valve (FSOV) bonding leads and for contact or chafing of the wires, and corrective actions if necessary. This new AD requires a new one-time detailed inspection of the FSOV bonding leads to ensure that the correct bonding leads are inspected, and corrective action if necessary. This AD was prompted by a determination that the description of the inspection area specified in the service information was misleading; therefore, some operators might have inspected incorrect bonding leads. We are issuing this AD to detect and correct contact or chafing of wires and the bonding leads, which, if not detected, could be a source of sparks in the wing trailing edge, and could lead to an uncontrolled engine fire.

We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model 4101 airplanes. This AD requires a one-time inspection for damage of the stop arms of the stop plates, an adjustment of the electric trim limit switches, and replacement of the stop plates with newly manufactured stop plates if necessary. This AD was prompted by a report that the pitch trim jammed in the fully down position. We are issuing this AD to detect and correct broken stop arms of the stop plates, which could lead to the pitch trim jamming, loss of control of the elevator trim, and possible reduced control of the airplane.