[Federal Register Volume 78, Number 244 (Thursday, December 19, 2013)]
[Rules and Regulations]
[Pages 76736-76738]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-30230]


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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.

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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,

[[Page 76737]]

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/ 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 C-series 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 Sec.  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 Sec.  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 Sec.  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 Sec.  11.38, and they become part of the type-
certification basis under Sec.  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.

[[Page 76738]]

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 Sec.  25.143(c) for pitch and roll, and in lieu of specific 
pitch force requirement of Sec. Sec.  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 and configurations, whether normal or non-normal.
    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