Federal Aviation Administration October 9, 2015 – Federal Register Recent Federal Regulation Documents

Airworthiness Directives; The Boeing Company Airplanes
Document Number: 2015-25709
Type: Proposed Rule
Date: 2015-10-09
Agency: Federal Aviation Administration, Department of Transportation
We propose to supersede Airworthiness Directive (AD) 2008-13- 12 R1, which applies to certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-13-12 R1 currently requires various repetitive inspections for cracking of the upper frame to side frame splice of the fuselage, and other specified and corrective actions if necessary; and also provides for an optional preventive modification, which terminates the repetitive inspections. Since we issued AD 2008-13-12 R1, we have received reports of additional fatigue cracking of the upper frame to side frame splice of the fuselage, and two reports of severed frames. This proposed AD would add, for certain airplanes, an inspection to determine if the existing frame repair meets all specified requirements; for certain other airplanes, a new modification of the upper frame to side frame splice, which would terminate the repetitive inspections; and reduce certain inspection thresholds and repetitive intervals. We are proposing this AD to detect and correct fatigue cracking of the upper frame to side frame splice of the fuselage, which could result in reduced structural integrity of the frame and adjacent lap joint, causing increased loading in the fuselage skin, which will accelerate skin crack growth and result in decompression of the airplane.
Airworthiness Directives; Rolls-Royce plc Turbojet Engines
Document Number: 2015-25607
Type: Proposed Rule
Date: 2015-10-09
Agency: Federal Aviation Administration, Department of Transportation
We propose to supersede airworthiness directive (AD) 2013-11- 13 that applies to all Rolls-Royce plc (RR) Viper Mk. 601-22 turbojet engines. Since we issued AD 2013-11-13, RR determined that additional parts for the RR Viper Mk. 601-22 as well as additional engine models are affected. This proposed AD would add two new engine models and additional engine parts to the applicability. We are proposing this AD to prevent failure of life-limited parts, which could lead to an uncontained part release, damage to the engine, and damage to the airplane.
Airworthiness Directives; Honeywell International Inc. Turboprop Engines (Type Certificate Previously Held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona)
Document Number: 2015-25606
Type: Rule
Date: 2015-10-09
Agency: Federal Aviation Administration, Department of Transportation
We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. TPE331-5, -5A, -5AB, -5B, -10, -10R, -10U, -10UF, -10UG, -10UGR, and -10UR model turboprop engines. This AD was prompted by engine propeller shaft coupling failures, leading to unexpected propeller pitch changes causing increased aerodynamic and asymmetric drag on the airplanes using these engines. This AD requires removing certain part number (P/N) engine propeller shaft couplings from service. This AD also requires inserting a copy of certain airplane operating procedures into applicable flight manuals. We are issuing this AD to prevent loss of airplane control, leading to an accident.
Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes
Document Number: 2015-25495
Type: Rule
Date: 2015-10-09
Agency: Federal Aviation Administration, Department of Transportation
We are adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation Model GVI airplanes. This AD was prompted by reports of corrosion on in-service air non-return valves. This AD requires a revision to the Emergency Procedures section of the airplane flight manual (AFM). This AD also requires a revision to the maintenance or inspection program, as applicable, to incorporate airworthiness limitations for the high pressure (HP) Stage 5 air non- return valves. We are issuing this AD to ensure the flightcrew is provided with procedures to mitigate the risks associated with failure of the HP Stage 5 air non-return valve. Failure of the HP Stage 5 air non-return valve in the open position could result in engine instability and uncommanded in-flight shutdown.
Airworthiness Directives; The Boeing Company Airplanes
Document Number: 2015-25490
Type: Rule
Date: 2015-10-09
Agency: Federal Aviation Administration, Department of Transportation
We are superseding Airworthiness Directive (AD) 2003-13-01 for certain The Boeing Company Model 767 airplanes. AD 2003-13-01 required an inspection to detect cracks and fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, and follow-on and corrective actions if necessary. For certain airplanes, AD 2003-13-01 required an inspection to determine if a tool runout option has been performed in the area. This new AD reduces certain compliance times, adds airplanes to the applicability, and provides optional terminating action for certain inspections. This AD was prompted by reports of hinge assembly fractures found before certain required compliance times in AD 2003-13-01. We are issuing this AD to prevent the inboard aft flap from separating from the wing and potentially striking the airplane, which could result in damage to the surrounding structure and potential personal injury.
Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Document Number: 2015-24465
Type: Rule
Date: 2015-10-09
Agency: Federal Aviation Administration, Department of Transportation
We are adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating the left and right lower surface panels of the wings are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking at these panels, and repair if necessary. The AD also requires a one-time bolt- hole eddy current inspection of all open holes for cracking, repair if necessary, and modification. We are issuing this AD to prevent fatigue cracking of the left and right lower surface panels of the wings, which could result in reduced structural integrity of the airplane.