Federal Aviation Administration October 3, 2014 – Federal Register Recent Federal Regulation Documents

Change of Controlling Agency for Restricted Areas; California
Document Number: 2014-23662
Type: Rule
Date: 2014-10-03
Agency: Federal Aviation Administration, Department of Transportation
This action updates the name of the controlling agency for restricted areas R-2502N Fort Irwin, CA; R-2505 China Lake, CA; R-2506 China Lake South, CA; R-2508 Complex, CA; R-2515 Muroc Lake, CA and R- 2524 Trona, CA to read ``FAA, Joshua Control Facility, Edwards AFB, CA.'' This is an administrative change only as there are no changes to the dimensions, time of designation or activities conducted within the affected restricted areas.
Airworthiness Directives; Kaman Aerospace Corporation (Kaman) Helicopters
Document Number: 2014-23588
Type: Proposed Rule
Date: 2014-10-03
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for Kaman Model K-1200 helicopters with certain main rotor blades (MRB) installed. This proposed AD would require inspecting each MRB for a crack or damage. This proposed AD is prompted by a report that a crack was found on an MRB during a tear-down inspection. The proposed actions are intended to detect a crack in the MRB, which could lead to failure of the MRB and subsequent loss of control of the helicopter.
Airworthiness Directives; Bell Helicopter Textron Canada Limited
Document Number: 2014-23582
Type: Proposed Rule
Date: 2014-10-03
Agency: Federal Aviation Administration, Department of Transportation
We are revising and reopening the comment period for an earlier notice of proposed rulemaking (NPRM) for certain Bell Helicopter Textron Canada Limited (Bell) Model 206L-3 and 206L-4 helicopters. The NPRM proposes to require installing a placard and revising the limitations section of the rotorcraft flight manual (RFM). The NPRM was prompted by several incidents of third stage engine turbine wheel failures caused by excessive vibrations at certain engine speeds during steady-state operations. This action proposes to revise the NPRM by adding certain Model 206L1 helicopters to the applicability, excluding certain Model 206L3 and 206L4 helicopters from the applicability, and changing the procedures for updating the RFM. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes.
Airworthiness Directives; Bombardier, Inc. Airplanes
Document Number: 2014-23429
Type: Rule
Date: 2014-10-03
Agency: Federal Aviation Administration, Department of Transportation
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of missing clamps that are required to provide positive separation between the alternating current (AC) feeder cables and the hydraulic line of the landing gear alternate extension. This AD requires an inspection for missing clamps that are required to provide positive separation between the AC feeder cables and the hydraulic line of the landing gear alternate extension, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct chafing of the AC feeder cable. A chafed and arcing AC feeder cable could puncture the adjacent hydraulic line, which, in combination with the use of the alternate extension system, could result in an in- flight fire.
Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Document Number: 2014-23378
Type: Rule
Date: 2014-10-03
Agency: Federal Aviation Administration, Department of Transportation
We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 series airplanes. This AD was prompted by reports of cracked rib cap castellations. This AD requires repetitive inspections for castellation and skin clips cracked or damaged between stringers and cracked stringer clips of the wing box pylon back-up structure, and front spar to rear spar; repetitive inspections for cracking, damage, or failure of the pylon back-up torque box structure; repetitive inspections for cracking or damage of the wing box external areas at the drag brace aft wing fitting; repetitive inspections of the outer surface of the wing upper and lower skins for cracks or damage along the rib attachment at the fastener holes and between the two rows of attachment; and corrective actions if necessary. We are issuing this AD to detect and correct cracked or damaged rib cap castellations, which could degrade the structural capabilities of the airplane.
Airworthiness Directives; the Boeing Company Airplanes
Document Number: 2014-23377
Type: Rule
Date: 2014-10-03
Agency: Federal Aviation Administration, Department of Transportation
We are superseding Airworthiness Directive (AD) 2010-03-05 for all the Boeing Company Model 747-200C and -200F series airplanes. AD 2010-03-05 required, for the upper chords of the upper deck floor beam of section 41, an inspection for cracking of certain fastener holes, and corrective action if necessary; and repetitive replacements of the upper chords, straps (or angles), and radius fillers of certain upper deck floor beams and, for any replacement that is done, inspections for cracking, and corrective actions if necessary. This new AD adds repetitive inspections of the upper chords of the upper deck floor beam of Section 42, repetitive replacements of the upper chords, post- replacement inspections, and corrective actions if necessary. This new AD also adds post-replacement inspections for section 41 and reduces certain compliance times. This AD was prompted by a determination that the upper deck floor beams are subject to widespread fatigue damage (WFD), the existing inspection program is not sufficient to maintain an acceptable level of safety, and the upper chords of the upper deck floor beam of section 42 are subject to the unsafe condition. We are issuing this AD to detect and correct cracking of the upper chords and straps (or angles) of the floor beams, which could lead to failure of the floor beams and consequent loss of controllability, rapid decompression, and loss of structural integrity of the airplane.
Airworthiness Directives; Bombardier, Inc. Airplanes
Document Number: 2014-23145
Type: Rule
Date: 2014-10-03
Agency: Federal Aviation Administration, Department of Transportation
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD requires repetitive inspections for any fuel leak in the right-hand landing lights compartment, and related investigative and corrective actions if necessary. This AD also provides for an optional replacement of the connector of the fuel boost pump canister of the auxiliary power unit (APU), which terminates the repetitive inspections. This AD was prompted by a report of fuel leaks in the connector cavity of the APU fuel boost pump canister and at the electrical conduit connection of the APU fuel boost pump in the right- hand landing lights compartment. We are issuing this AD to detect and correct fuel leaks in the right-hand landing lights compartment, which, in combination with the heat generated by the taxi lights and landing lights on the ground reaching the auto-ignition temperature of the fuel, could result in ignition of any fuel or fumes present in the right-hand landing lights compartment.
Airworthiness Directives; Airbus Airplanes
Document Number: 2014-23139
Type: Rule
Date: 2014-10-03
Agency: Federal Aviation Administration, Department of Transportation
We are superseding Airworthiness Directive (AD) 94-12-03 for certain Airbus Model A320 series airplanes. AD 94-12-03 required modification of the belly fairing structure. This new AD requires repetitive inspections for cracking of the four titanium angles between the belly fairing and the keel beam side panel, an inspection for cracking of the open holes if any cracking is found in the titanium angles, and repair or replacement if necessary; this new AD also expands the applicability of AD 94-12-03. This AD was prompted by reports of cracks at the lower riveting of the four titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage. We are issuing this AD to detect and correct cracking of the titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage, which could affect the structural integrity of the airplane.