Federal Aviation Administration July 12, 2016 – Federal Register Recent Federal Regulation Documents

This notice contains a summary of a petition seeking relief from specified requirements of Title 14 of the Code of Federal Regulations. The purpose of this notice is to improve the public's awareness of, and participation in, the FAA's exemption process. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of the petition or its final disposition.

This notice contains a summary of a petition seeking relief from specified requirements of Title 14 of the Code of Federal Regulations. The purpose of this notice is to improve the public's awareness of, and participation in, the FAA's exemption process. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of the petition or its final disposition.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, and -200C series airplanes. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would require repetitive detailed, high frequency eddy current (HFEC), and ultrasonic inspections of the center section rear spar upper clevis lugs and horizontal stabilizer rear spar upper lugs, as applicable, for any cracking, and related investigative and corrective actions if necessary. For certain airplanes, this proposed AD would require replacement of the center section rear spar upper chord with a new part and a serviceable center section assembly. This proposed AD would also require repetitive HFEC and fluorescent dye penetrant inspections of the center section for cracking of the front and rear spar upper clevis lugs or horizontal stabilizer front and rear spar upper lugs, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct cracking in the rear spar upper clevis lugs of the center section, and in the rear spar upper lugs of the horizontal stabilizer which could result in the loss of structural integrity and controllability of the airplane.

We are superseding Airworthiness Directive (AD) 2015-10-03 for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2015-10-03 required a detailed inspection for visible chrome of each affected main landing gear (MLG) sidestay upper cardan pin, associated nuts, and retainer assembly; pin replacement if needed; measurement of cardan pin clearance dimensions (gap check); corrective actions if necessary; and a report of all findings. This new AD requires a detailed inspection of the upper cardan pin and nut threads for any corrosion, pitting, or thread damage, and if necessary, replacement of the cardan pin and nut. This new AD also revises the applicability to include additional airplane models. This AD was prompted by a report that an MLG sidestay upper cardan pin migration event had been caused by corrosion due to lack of jointing compound and inadequate sealant application during the MLG installation. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants.

We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of improperly drilled bores, located on upper and lower stiffener joints to the Web at a certain frame. This AD requires a one- time inspection of the bores, and repair if necessary. We are issuing this AD to detect and correct an unsatisfactory bore that can adversely affect the structural integrity of the airplane.

We are revising an earlier proposed airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. The NPRM proposed to supersede AD 2012-24-06. AD 2012-24-06 currently requires replacing the stall warning computer (SWC) with a new SWC that provides an artificial stall warning in icing conditions, and modifying the airplane for the replacement of the SWC. The NPRM was prompted by a determination that airplanes with certain modifications were excluded from the applicability in AD 2012-24-06, and are affected by the identified unsafe condition; and the SWC required by AD 2012-24-06 contained erroneous logic. This action revises the NPRM by reducing the compliance time for replacing the SWCs. We are proposing this supplemental NPRM (SNPRM) to prevent natural stall events during operation in icing conditions, which could result in loss of control of the airplane. Since this compliance time reduction imposes an additional burden to operators, we are reopening the comment period to allow the public the chance to comment on these proposed changes.