Federal Aviation Administration March 24, 2015 – Federal Register Recent Federal Regulation Documents

Prohibition Against Certain Flights Within the Tripoli (HLLL) Flight Information Region (FIR); Extension of Expiration Date
Document Number: 2015-06697
Type: Rule
Date: 2015-03-24
Agency: Federal Aviation Administration, Department of Transportation
This action extends the prohibition of flight operations within the Tripoli (HLLL) Flight Information Region (FIR) by all: U.S. air carriers; U.S. commercial operators; persons exercising the privileges of an airman certificate issued by the FAA, except when such persons are operating a U.S.-registered aircraft for a foreign air carrier; and operators of U.S.-registered civil aircraft, except operators of such aircraft that are foreign air carriers. The extension of the expiration date is necessary to address a potential hazard to persons and aircraft engaged in such flight operations. Additionally, the FAA is amending the prohibition to make clear that operations by sub-contractors under a U.S. Government department, agency, or instrumentality's contract, grant, or cooperative agreement may be included in an approval request and to remove an obsolete reference to paragraph 8 of United Nations Security Council Resolution (UNSCR) 1973. The FAA is also revising the approval conditions that will apply to operations authorized by other U.S. Government departments, agencies, and instrumentalities that are approved by the FAA, and the information about requests for exemption, to reflect the termination of statutory authorization for the FAA premium war risk insurance program.
Airworthiness Directives; Bombardier, Inc. Airplanes
Document Number: 2015-06579
Type: Proposed Rule
Date: 2015-03-24
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This proposed AD was prompted by reports of inadvertent deployment of a single outboard spoiler during flight. This proposed AD would require replacement of the power control units (PCUs) for the outboard spoilers with upgraded PCUs. We are proposing this AD to prevent leakage of the piston head seal and piston rod seals of the outboard spoiler PCUs, which could result in inadvertent spoiler deployment and reduced controllability of the airplane.
Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Document Number: 2015-06576
Type: Proposed Rule
Date: 2015-03-24
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper and lower wing skin planks at the attachment of the main landing gear (MLG) ribs at certain wing-stations are subject to widespread fatigue damage (WFD). This proposed AD would require an inspection (for cracking) and modification of the chordwise fastener rows of the upper and lower wing planks at the attachments to the MLG ribs at certain wing-stations. We are proposing this AD to prevent fatigue cracking of the upper and lower wing skin planks at the attachment of the MLG ribs, which could result in failure of the wing.
Airworthiness Directives; The Boeing Company Airplanes
Document Number: 2015-06574
Type: Proposed Rule
Date: 2015-03-24
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This proposed AD was prompted by reports of cracking at certain fastener locations in the window corners of the window belt area. This proposed AD would require repetitive high frequency eddy current (HFEC) inspections for fatigue cracking in certain fastener locations in the window corners of the window belt area, and related investigative and corrective actions if necessary. This proposed AD would also provide an optional preventive modification that would terminate the repetitive inspections at the modified location. We are proposing this AD to detect and correct fatigue cracking around fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane.
Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) Helicopters
Document Number: 2015-06567
Type: Proposed Rule
Date: 2015-03-24
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (AHD) (previously Eurocopter Deutschland GmbH) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, C-1, and C- 2 helicopters. This proposed AD would require an initial and recurring inspection of the N2 control arm and, depending on the outcome of the inspection, repairing or replacing the N2 control arm. This proposed AD is prompted by a report of a heavily corroded and broken N2 control arm. The proposed actions are intended to detect corrosion, a crack, or a scratch in the N2 control arm, which could lead to failure of the N2 control arm, a drop in rotor speed, and subsequent loss of control of the helicopter.
Airworthiness Directives; Bombardier, Inc. Airplanes
Document Number: 2015-06563
Type: Proposed Rule
Date: 2015-03-24
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900) airplanes. This proposed AD was prompted by reports of a disconnect between the elevator lever and control rod. This proposed AD would require replacement of left and right fixed control rods and lever assemblies of the elevator control system. We are proposing this AD to prevent a disconnect between the elevator lever and control rod, which could lead to un-commanded elevator movement of the associated control surface, a large difference between the position of the left and the right elevator control surface, and consequent reduced controllability of the airplane and degradation of the structural integrity of the horizontal stabilizer.