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minimum panel size: ‘‘It is not possible to cite a specific size that will apply in all installations; however, as a general rule, components with exposed-surface areas of 1 ft 2 or less may be considered small enough that they do not have to meet the new standards. Components with exposed surface areas greater than 2 ft 2 may be considered large enough that they do have to meet the new standards. Those with exposed-surface areas greater than 1 ft2 , but less than 2 ft 2 , must be considered in conjunction with the areas of the cabin in which they are installed before a determination could be made.’’

In the late 1990s, the FAA issued Policy Memorandum 97–112–39, Guidance for Flammability Testing of Seat/Console Installations, October 17, 1997. That memo was issued when it became clear that seat designs were evolving to include large, non-metallic panels with surface areas that would impact survivability during a cabin fire event, comparable to partitions or galleys. The memo noted that large surface area panels must comply with heat release and smoke emission requirements, even if they were attached
to a seat.

If the FAA had not issued such policy, seat designs could have been viewed as a loophole to the airworthiness standards that would result in an unacceptable decrease in survivability during a cabin fire event.

In October 2004, an issue was raised regarding the appropriate flammability standards for passenger seats thatincorporated non-traditional, large, nonmetallic panels in lieu of the traditional metal covered by fabric. The Seattle Aircraft Certification Office and Transport Standards Staff reviewed this design and determined that it represented the kind and quantity of material that should be required to pass the heat release and smoke emissions requirements. We have determined that special conditions would be promulgated to apply the standards defined in § 25.853(d) to seats with large, non-metallic panels in their design. Applicability

As discussed above, these special conditions are applicable to the Bombardier Models BD–500–1A10 and BD–500–1A11 series airplanes. Should Bombardier Inc. apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on two model series of airplanes. It is not a rule of general applicability.

The substance of these special conditions has been subjected to the notice and comment period in several prior instances and has been derived without substantive change from those previously issued. It is unlikely that prior public comment would result in a significant change from the substance contained herein. Therefore, because a delay would significantly affect the certification of the airplane, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon publication in the Federal Register. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25

Aircraft, Aviation safety, Reporting and recordkeeping requirements.

The authority citation for these special conditions is as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions

Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for the Bombardier Inc. Models BD–500–1A10 and BD– 500–1A11 series airplanes. Seats With Non-Traditional, Large, Non-Metallic Panels

1. Compliance with Title 14 CFR part 25, appendix F, parts IV and V, heat release and smoke emission, is requiredfor seats that incorporate nontraditional, large non-metallic panels that may either be a single component or multiple components in a concentrated area in their design.

2. The applicant may designate up to and including 1.5 ft 2 of non-traditional, non-metallic panel material per seat place that does not have to comply with No. 1. A triple seat assembly may have a total of 4.5 ft 2 excluded on any portion of the assembly (e.g., outboard seat place 1 ft2 , middle 1 ft 2 , and inboard 2.5 ft 2 ).

3. Seats need not meet the test requirements of 14 CFR part 25, appendix F, parts IV and V when installed in compartments that are not otherwise required to meet these requirements. Examples include:

a. Airplanes with passenger capacities of 19 or less;

b. Airplanes that do not have smoke and heat release in their certification basis and do not need to comply with the requirements of 14 CFR 121.312; and

c. Airplanes exempted from smoke and heat release requirements.

4. Only airplanes associated with new seat certification programs approved after the effective date of these special conditions will be affected by the requirements in these special conditions. Previously certificated interiors on the existing airplane fleet and follow-on deliveries of airplanes with previously certificated interiors are not affected.

Issued in Renton, Washington, on December 11, 2013. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–30234 Filed 12–18–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 25**

**[Docket No. FAA–2013–1054; Notice No. 25– 513–SC]** 

**Special Conditions: Bombardier Inc., Models BD–500–1A10 and BD–500–**  **1A11 Series Airplanes; Side Stick Controllers: Pilot Strength, Pilot**  **Control Authority, and Pilot Control**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final special conditions; request for comments.

**SUMMARY :**  These special conditions are issued for the Bombardier Inc. Models BD–500–1A10 and BD–500–1A11 series airplanes. These airplanes will have a novel or unusual design feature associated with side stick controllers for pitch and roll control instead of conventional wheels and columns. 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.

**DATES :**  The effective date of these special conditions is December 19,


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2013. We must receive your comments by February 3, 2014.

**ADDRESSES :**  Send comments identified by docket number FAA–2013–1054 using any of the following methods:

• Federal eRegulations Portal: Go to http://www.regulations.gov/ and follow the online instructions for sending your comments electronically.

• Mail: Send comments to Docket Operations, M–30, U.S. Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room W12–140, West Building Ground Floor, Washington, DC
20590–0001.

• Hand Delivery or Courier: Take comments to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except federal holidays.

• Fax: Fax comments to Docket Operations at 202–493–2251.

Privacy: The FAA will post all comments it receives, without change,
to http://www.regulations.gov/

, including any personal information the commenter provides. Using the search function of the docket Web site, anyone can find and read the electronic form of all comments received into any FAA docket, including the name of the individual sending the comment (or signing the comment for an association, business, labor union, etc.). DOT’s complete Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477–19478), as well as at http://DocketsInfo.dot. gov/.

Docket: Background documents or comments received may be read at http://www.regulations.gov/ at any time. Follow the online instructions for accessing the docket or go to the Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except federal holidays.

**FOR FURTHER INFORMATION CONTACT :**  Joe Jacobsen, FAA, Airplane and Flightcrew Interface Branch, ANM–111, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–2011; facsimile
425–227–1149.

**SUPPLEMENTARY INFORMATION :**  The substance of these special conditions has been subject to the public comment process in several prior instances with no substantive comments received. The FAA therefore finds that good cause exists for making these special conditions effective upon publication in the Federal Register

. Comments Invited
We invite interested people to take part in this rulemaking by sending written comments, data, or views. The most helpful comments reference a specific portion of the special conditions, explain the reason for any recommended change, and include supporting data.

We will consider all comments we receive on or before the closing date for comments. We may change these special conditions based on the comments we receive.
Background

On December 10, 2009, Bombardier Inc. applied for a type certificate for their new Models BD–500–1A10 and BD–500–1A11 series airplanes (hereafter collectively referred to as ‘‘C-series.’’ The C-series airplanes are swept-wing monoplanes with a pressurized cabin. They share an identical supplier base and significant common design elements. The fuselage is aluminum alloy material, blended double-bubble fuselage, sized for nominal 5-abreast seating. Each airplane’s powerplant consists of two under wing Pratt and Whitney PW1524G ultra-high bypass, geared turbofan engines. Flight controls are fly-by-wire flight with two passive/ uncoupled side sticks. Avionics includes five landscape primary cockpit displays. The dimension of the airplanes encompass a wingspan of 115 feet; a height of 37.75 feet; and a length of 114.75 feet for the Model BD–500– 1A10 and a length of 127 feet for the Model BD–500–1A11. Passenger capacity is designated as 110 for the Model BD–500–1A10 and 125 for the Model BD–500–1A11. Maximum takeoff weight is 131,000 pounds for the Model BD–500–1A10 and 144,000 pounds for the Model BD–500–1A11. Maximum takeoff thrust is 21,000 pounds for the Model BD–500–1A10 and 23,300 pounds for the Model BD–500–1A11. Range is 3,394 miles (5,463 kilometers) for both models of airplanes. Maximum operating altitude is 41,000 feet for both model airplanes.

The Bombardier C-series airplanes will use side stick controllers for pitch and roll control. Regulatory requirements pertaining to conventional wheel and column, such as pilot strength and controllability, are not directly applicable for the side stick. In addition, pilot control authority may be uncertain because the side sticks are not mechanically interconnected as with conventional wheel and column controls. Type Certification Basis Under the provisions of Title 14, Code of Federal Regulations (14 CFR) 21.17,Bombardier Inc. must show that the Cseries airplanes meet the applicable provisions of 14 CFR part 25 as amended by Amendments 25–1 through 25–129 thereto.

If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 25) do not contain adequate or appropriate safety standards for the C-series airplanes because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16.

Special conditions are initially applicable to the model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same or similar novel or unusual design feature, the special conditions would also apply to the other model under § 21.101.

In addition to the applicable airworthiness regulations and special conditions, the C-series airplanes must comply with the fuel vent and exhaust emission requirements of 14 CFR part 34 and the noise certification requirements of 14 CFR part 36, and the FAA must issue a finding of regulatory adequacy under § 611 of Public Law 92– 574, the ‘‘Noise Control Act of 1972.’’

The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type-certification basis under § 21.17(a)(2). Novel or Unusual Design Features

The C-series airplanes will incorporate the following novel or unusual design features: Side stick controllers for pitch and roll control, which are not mechanically interconnected as with conventional wheel and column controls. These airplanes also have a fly-by-wire electronic flight control system. This system provides an electronic interface between the pilot’s flight controls and the flight control surfaces for both normal and failure states, and it generates the actual surface commands that provide for stability augmentation and control about all three airplane axes. In addition, pilot control authority may be uncertain, because the side sticks are not mechanically interconnected as with conventional wheel and column controls.

Discussion

Current FAA regulations do not specifically address the use of side stick controllers for pitch and roll control.


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The unique features of the side stick must therefore be demonstrated through flight and simulator tests to have suitable handling and control characteristics when considering the following:

1. The handling qualities tasks/ requirements of the C-series airplanes special conditions and other part 25 stability, control, and maneuverability requirements, including the effects of turbulence.

2. General ergonomics: Arm rest comfort and support, local freedom of movement, displacement angle suitability, and axis harmony.

3. Inadvertent input in turbulence. 4. Inadvertent pitch-roll cross talk. These requirements are elaborated upon in these special conditions, which 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 Handling Qualities Rating Method (HQRM) in Appendix 5 of Advisory Circular 25–7C, Flight Test Guide for Certification of Transport Category Airplanes, may be used to show compliance. Applicability

As discussed above, these special conditions are applicable to the Bombardier Models BD–500–1A10 and BD–500–1A11 series airplanes. Should Bombardier Inc. apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply to that model as well.

Conclusion

This action affects only certain novel or unusual design features on two model series of airplanes. It is not a rule of general applicability.

The substance of these special conditions has been subjected to the notice and comment period in several prior instances and has been derived without substantive change from those previously issued. It is unlikely that prior public comment would result in a significant change from the substance contained herein. Therefore, the FAA has determined that prior public notice and comment are unnecessary, and good cause exists for adopting these special conditions upon publication in the Federal Register. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting and recordkeeping requirements.

The authority citation for these special conditions is as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704. The Special Conditions

Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for the Bombardier Inc. Models BD–500–1A10 and BD– 500–1A11 series airplanes.

In the absence of specific requirements for side stick controllers, the following apply:

1. Pilot strength: In lieu of the ‘‘strength of pilots’’ limits shown in § 25.143(c) for pitch and roll, and in lieu of specific pitch force requirement of §§ 25.145(b) and 25.175(d), it must be shown that the temporary and maximum prolonged force levels for the side stick controllers are suitable for all expected operating conditions andconfigurations, whether normal or nonnormal.

2. Pilot control authority: The electronic side stick controller coupling design must provide for corrective and/ or overriding control inputs by either pilot with no unsafe characteristics. Annunciation of the controller status must be provided and must not be confusing to the flightcrew.

3. Pilot control: It must be shown by flight tests that the use of side stick controllers does not produce unsuitable pilot-in-the-loop control characteristics when considering precision path control/tasks and turbulence. In addition, pitch and roll control force and displacement sensitivity must be compatible, so that normal inputs on one control axis will not cause significant unintentional inputs on the other.

Issued in Renton, Washington, on December 12, 2013. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–30230 Filed 12–18–13; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF COMMERCE** 

**Bureau of Industry and Security**

**15 CFR Parts 730, 732, 734, 736, 738, 740, 742, 743, 744, 745, 746, 747, 748,**  **750, 752, 754, 756, 758, 760, 762, 764, 766, 768, 770, 772, and 774** 

**[Docket No. 131114960–3960–01]**

**RIN 0694–AG01**

**Updated Statements of Legal Authority for the Export Administration**  **Regulations**

**AGENCY :**  Bureau of Industry and Security, Commerce.

**ACTION :**  Final rule.

**SUMMARY :**  This rule updates the Code of Federal Regulations (CFR) legal authority paragraphs in the Export Administration Regulations (EAR) to include the citations to five Presidential notices extending emergencies declared pursuant to the International Emergency Economic Powers Act. This is a procedural rule that only updates authority paragraphs of the EAR. It does not alter any right, obligation or prohibition that applies to any person under the EAR.

**DATES :**  The rule is effective December 19, 2013.

**FOR FURTHER INFORMATION CONTACT :**  William Arvin, Regulatory Policy Division, Bureau of Industry and Security, Telephone: (202) 482–2440.

**SUPPLEMENTARY INFORMATION :**  Background

Authority for some provisions of the EAR rests, in part, on executive orders in which the President, using his authority under the International Emergency Economic Powers Act, declares an emergency and on annual notices extending those emergencies. This rule updates the authority citation paragraphs in the Code of Federal Regulations parts that comprise the Export Administration Regulations to cite five such annual notices. The five notices, the executive orders to which they relate, and the EAR parts affected by each notice are set forth below.

The notice of January 17, 2013, 78 FR 4303 (January 22, 2013) extended the emergency declared in Executive Order 12947 of January 23, 1995—National Emergency With Respect to Terrorists Who Threaten to Disrupt the Middle East Process, 60 FR 5079, 3 CFR, 1995 Comp., p. 356. This rule revises the authority paragraphs of parts 730 and 744 to cite that notice.

The notice of May 7, 2013, 78 FR 27301 (May 9, 2013) extended the