Federal Aviation Administration 2016 – Federal Register Recent Federal Regulation Documents

We are superseding Airworthiness Directive (AD) 2007-21-14 R1 for all Airbus Model A310 series airplanes. AD 2007-21-14 R1 required revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This new AD requires revising the maintenance program or inspection program to incorporate revised fuel maintenance and inspection tasks. This AD was prompted by the issuance of more restrictive maintenance requirements and/or airworthiness limitations by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane.

This notice announces a request for comments on the draft FAA Order 5500.1B, Passenger Facility Charge. When finalized, this Order will replace Order 5500.1, Passenger Facility Charge, issued on August 9, 2001. This revised Order clarifies and updates statutory and regulatory requirements, including those affected by changes to the PFC statute from multiple FAA reauthorizations.

We propose to supersede Airworthiness Directive (AD) 2003-18- 06, for certain Airbus Model A319-131 and -132 airplanes; Model A320- 231, -232, and -233 airplanes; and Model A321-131 and -231 airplanes. AD 2003-18-06 currently requires installing new anti-swivel plates and weights on the engine fan cowl door (FCD) latches and a new cowl door hold-open device. Since we issued AD 2003-18-06, we have received reports of additional engine FCD in-flight losses, and a new FCD front latch and keeper assembly has been developed to address this unsafe condition. This proposed AD would retain the current actions and require modifying the engine FCDs, installing placards, and re- identifying the FCDs with the new part numbers. This proposed AD would also revise the applicability to include all Model A319-131 and -132 airplanes; Model A320-231, -232, and -233 airplanes; and Model A321-131 and -231 airplanes. We are proposing this AD to prevent in-flight loss of an engine FCD and possible consequent damage to the airplane and hazards to persons or property on the ground.

We propose to supersede Airworthiness Directive (AD) 2012-08- 11 for certain Bombardier, Inc. Model DHC-8-400 series airplanes. AD 2012-08-11 currently requires repetitive detailed inspections for defects and damage of the retract port flexible hoses on the left and right Main Landing Gear (MLG) retraction actuator, and replacement of the flexible hoses if necessary. Since we issued AD 2012-08-11, we determined that the orientation of the retraction actuator ports must be revised to address the identified unsafe condition. This proposed AD would continue to require the actions required by AD 2012-08-11, and would require reorientation of the retraction actuator of the MLG, which would terminate the repetitive inspections. This proposed AD would also remove airplanes from the applicability. We are proposing this AD to prevent hydraulic fluid leakage in the event of a damaged retract port flexible hose failure; this condition could lead to an undamped extension of the MLG and could result in MLG structural failure, leading to an unsafe, asymmetric landing configuration.

This rule establishes, amends, suspends, or removes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures (ODPs) for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.

This rule amends, suspends, or removes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide for the safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.

We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Models FU24-954 and FU24A-954 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracked elevator torque tubes. We are issuing this AD to require actions to address the unsafe condition on these products.

We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-603, B4-605R, and B4-622R airplanes; and Model A310-304, -324, and -325 airplanes. This AD was prompted by a report of a crack found on door frame (FR) 73A between stringers 24 and 25. This AD requires inspections around the rivet heads of the seal retainer run-out holes at certain frames and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the door frame, which could result in reduced structural integrity of the airplane.

We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes. This AD was prompted by a design review that revealed insufficient measures were taken to ensure the correct locking of the attachments of the fuel quantity tank units (FQTUs) in each wing tank. When an FQTU becomes loose, this could lead to insufficient clearance between the FQTU and the adjacent tank structure or other metal parts, and under certain conditions, create an ignition source inside the wing fuel vapor space. This AD requires modifying the FQTUs by applying sealant to cover the nuts, washers, and stud ends at the FQTU attachments in each main wing tank. This AD also requires revising the maintenance or inspection program, as applicable, by incorporating a fuel airworthiness limitation item and a critical design configuration control limitation (CDCCL). We are issuing this AD to prevent an ignition source in the wing fuel tank vapor space, which could result in a wing fuel tank explosion and consequent loss of the airplane.

We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 900EX and FALCON 2000EX airplanes. This AD was prompted by a review that identified a nonconformity between the torque value applied to the screw-nuts of aileron servo actuators, and the torque value specified by the type design. This AD requires replacing certain aileron servo actuators with serviceable servo actuators. We are issuing this AD to prevent desynchronization between two servo actuator barrels, which could lead to reduced control of the airplane during roll maneuvers at low altitude.

These special conditions are issued for The Boeing Company (Boeing) Model 787-9 series airplane. This airplane, as modified by Boeing, will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport-category airplanes. These design features are single-occupant oblique (side-facing) seats with inflatable and 3-point restraint systems requiring dynamic testing. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

These special conditions are issued for the Embraer S.A. (Embraer) Model EMB-545 and EMB-550 airplanes. These airplanes will have a novel or unusual design feature associated with a vision system that displays video imagery on the head-up display. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

These special conditions are issued for the Boeing Model 747- 8 airplane. This airplane, as modified by Associated Air Center, will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport- category airplanes. This design feature is an airbag system to limit axial rotation of the upper leg, due to leg flail, of occupants in single-place side-facing seats. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, - 114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This proposed AD was prompted by reports of cracks on the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's thrust reverser (T/R). This proposed AD would require repetitive inspections for cracking and corrosion of the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's T/R, and corrective actions if necessary. We are proposing this AD to detect and correct such cracking and corrosion, which could lead to T/R malfunction and, in a case of rejected takeoff at V1 on a wet runway, a consequent runway excursion, possibly resulting in damage to the airplane and injury to occupants.

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.

The Federal Aviation Administration (FAA) is hosting a public meeting to conclude the Aircraft Access to System Wide Information Management (AAtS) Demonstration project. The meeting will inform flight operations stakeholders and information service providers on the demonstrated concept, prototype applications developed, and results collected throughout the project. This meeting is not a precursor to a request for proposal (RFP) or request for offer (RFO). The FAA is not seeking or accepting unsolicited proposals.

This action proposes to amend Class E en route airspace around the Iron Mountain VHF omnidirectional range/distance measuring equipment, Iron Mountain, MI. This action would add additional airspace to facilitate the vectoring of Instrument Flight Rules (IFR) aircraft under control of the Minneapolis Air Route Traffic Control Center (ARTCC) in the Great Lakes area located north and northwest of the Iron Mountain, MI, VHF Omnidirectional Range/Distance Measuring Equipment (VOR/DME) navigation aid. This proposed action would enhance the safety and management of aircraft operations within the National Airspace System (NAS).

We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200 and -200CB series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lap splices at stringer S-14R, lower fastener row, are subject to widespread fatigue damage (WFD). This AD requires external dual frequency eddy current (DFEC) or internal high frequency eddy current (HFEC) inspections of the lap splice, inner skin fasteners, at stringer S-14R, station (STA) 440 through STA 540, and corrective action if necessary. We are issuing this AD to detect and correct cracking of the fuselage skin lap splice. Such cracking could result in reduced structural integrity of the airplane.

These special conditions are issued for the Embraer S.A. (Embraer) Model EMB-545 and EMB-550 series airplanes. These airplanes will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport- category airplanes. This feature is an airbag system designed to limit the axial rotation of the upper leg on single-place and multiple-place side-facing seats. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

The FAA is issuing this notice to advise the public of a meeting of Eleventh Meeting Special Committee 231 TAWS.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747- 200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the nose wheel well is subject to widespread fatigue damage (WFD). This proposed AD would require modification of the nose wheel body structure; a detailed inspection of the nose wheel body structure for any cracking; a surface high frequency eddy current inspection (HFEC) or an open hole HFEC inspection of the vertical beam outer chord and web for any cracking; and all applicable related investigative actions including repetitive inspections, and other specified and corrective actions. We are proposing this AD to detect and correct fatigue cracking in the nose wheel well structure; such cracking could adversely affect the structural integrity of the airplane.

The FAA is issuing this notice to advise the public of a meeting of EUROCAE WG-99 PLENARY #8/RTCA SC-234 Plenary #5Calling Notice ``Portable Electronic Devices (PEDs)''.

The Federal Aviation Administration (FAA) is revising its repair station rules to remove the requirement that a repair station with an airframe rating provide suitable permanent housing to enclose the largest type and model aircraft listed on its operations specifications. The FAA is also revising its general housing and facilities regulation to provide that a repair station's housing for its facilities, equipment, materials, and personnel must be consistent not only with its ratings, but also with its limitations to those ratings. Finally, the FAA is adding an additional general purpose limited rating to cover maintenance work not covered by the existing 12 limited rating categories. These changes are necessary because the existing ratings and housing rules impose unnecessary housing requirements on certain repair stations that work only on component parts of an aircraft. These changes will enable some repair stations to obtain a limited rating that is tailored to their intended scope of work, and will relieve repair stations that have a limited airframe rating, but that work only on component parts of an aircraft, from having to provide large and expensive housing to enclose the entire aircraft when that type of housing is not needed for the limited scope of their work.

The FAA is correcting a final rule published in the Federal Register on June 24, 2016 (81 FR 41200). In that final rule, the FAA amended certain airworthiness regulations for transport category airplanes to require fuel tank designs that prevent a fuel tank explosion caused by the propagation of flames, from external fires, through the fuel tank vents. The final rule requires a delay of two minutes and thirty seconds between exposure of external fuel tank vents to ignition sources and explosions caused by propagation of flames into the fuel tank, thus increasing the time available for passenger evacuation and emergency response. The amendments apply to applications for new type certificates and certain applications for amended or supplemental type certificates. The amendments also require certain airplanes produced in the future and operated by air carriers to meet the new standards. However, in that document, the amendment numbers for the final rules were incorrect, and an airplane model number in a footnote was incorrect. This document now posts the correct amendment numbers and airplane model number in the footnote.

We propose to adopt a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211- Trent 892B-17, and RB211-Trent 895-17 turbofan engines that have not incorporated RR modification 72-J195 in production or RR Service Bulletin (SB) RB.211-72-J195. This proposed AD was prompted by inspection of RR Trent 800 engines returned from service that revealed flame erosion and axial cracking on the aft face of the stage 3 disk rim of the high-pressure compressor (HPC) stage 1-4 rotor disks shaft. This proposed AD would require machining the HPC stage 3 inner shroud, inspecting the HPC stage 1-4 rotor disks shaft, and replacing the HPC stage 1-4 rotor disks shaft if found defective. We are proposing this AD to prevent uncontained failure of the HPC stage 1-4 rotor disks shaft, damage to the engine, and damage to the airplane.