Document ID: FAA-2013-0776-0001
Agency: faa
Document Type: Rule
Title: Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Sidestick Controllers
Posted Date: 2013-10-25T04:00Z

[Federal Register Volume 78, Number 207 (Friday, October 25, 2013)]
[Rules and Regulations]
[Pages 63848-63850]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25206]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2013-0776; Special Conditions No. 25-498-SC]

Special Conditions: Embraer S.A., Model EMB-550 Airplanes; 
Sidestick Controllers

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special condition; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued for the Embraer S.A. Model 
EMB-550 airplane. This airplane will have a novel or unusual design 
feature associated with sidestick controllers. 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 October 25, 
2013. We must receive your comments by December 9, 2013.

ADDRESSES: Send comments identified by docket number FAA-2013-0776 
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

[[Page 63849]]

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 8 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: Loran Haworth, FAA, Airplane and 
Flight Crew Interface Branch, ANM-111, Transport Airplane Directorate, 
Aircraft Certification Service, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone 425-227-1133; facsimile 425-227-1149.

SUPPLEMENTARY INFORMATION: The FAA has determined that notice of, and 
opportunity for prior public comment on, these special conditions are 
unnecessary because 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.

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 by the closing date for 
comments. We may change these special conditions based on the comments 
we receive.

Background

    On May 14, 2009, Embraer S.A. applied for a type certificate for 
their new Model EMB-550 airplane. The Model EMB-550 airplane is the 
first of a new family of jet airplanes designed for corporate flight, 
fractional, charter, and private owner operations. The aircraft has a 
conventional configuration with low wing and T-tail empennage. The 
primary structure is metal with composite empennage and control 
surfaces. The Model EMB-550 airplane is designed for 8 passengers, with 
a maximum of 12 passengers. It is equipped with two Honeywell HTF7500-E 
medium bypass ratio turbofan engines mounted on aft fuselage pylons. 
Each engine produces approximately 6,540 pounds of thrust for normal 
takeoff. The primary flight controls consist of hydraulically powered 
fly-by-wire elevators, ailerons and rudder, controlled by the pilot or 
copilot sidestick.
    The Model EMB-550 airplane will use passive sidestick controllers 
for pitch and roll control instead of a conventional control column and 
wheel. The main characteristics of a sidestick controller are:
     Passive inceptor (i.e., the hand grip returns to the null 
position after in/out movements),
     Artificial tactile feedback,
     Located on the side of the pilot, and
     No mechanical interconnection.

Type Certification Basis

    Under the provisions of Title 14, Code of Federal Regulations (14 
CFR) 21.17, Embraer, S.A. must show that the Model EMB-550 airplane 
meets the applicable provisions of part 25, as amended by Amendment 25-
1 through 25-127 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 Model EMB-550 airplane 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 novel or 
unusual design feature, the special conditions would also apply to the 
other model.
    In addition to the applicable airworthiness regulations and special 
conditions, the Model EMB-550 airplane 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 Model EMB-550 airplane will incorporate the following novel or 
unusual design features: The Model EMB-550 airplane has a sidestick 
controller for pitch and roll control.

Discussion

    Regulatory requirements for conventional wheel and column 
controllers, such as requirements pertaining to pilot strength and 
controllability, are not directly applicable to sidestick controllers. 
Certain ergonomic considerations such as armrest support, freedom of 
arm movement, controller displacement, handgrip size and accommodations 
for a range of pilot sizes are not addressed in the regulations. In 
addition, pilot control authority may be uncertain, because the 
sidestick controllers are not mechanically interconnected as with 
conventional wheel and column controls. Pitch and roll control force 
and displacement sensitivity must be compatible so that normal inputs 
on one control axis do not cause significant unintentional inputs on 
the other. As a result, a special condition is issued to require that 
the unique features of the sidesstick controller must be demonstrated 
through flight and simulator tests to have suitable handing and control 
characteristics.

Applicability

    As discussed above, these special conditions are applicable to the 
Model EMB-550 airplane. Should Embraer S.A. 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 one model of airplanes. It is not a rule of general applicability.

[[Page 63850]]

    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 issuance. 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 Embraer S.A. Model EMB-550 airplanes.
    In the absence of specific requirements for sidestick controllers, 
the following Special Conditions apply:
    1. Pilot strength: In lieu of the control force limits shown in 
Sec.  25.143(d) for pitch and roll and in lieu of the specific pitch 
force requirements of Sec. Sec.  25.143(i)(2), 25.145(b), and 
25.175(d), it must be shown that the temporary and maximum prolonged 
force levels for the sidestick controllers are suitable for all 
expected operating conditions and configurations, whether normal or 
non-normal.
    2. Pilot control authority: The electronic sidestick 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 
sidestick 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 September 6, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-25206 Filed 10-24-13; 8:45 am]
BILLING CODE 4910-13-P