67320 Federal Register / Vol. 78, No. 218 / Tuesday, November 12, 2013 / Proposed Rules 

comments. ASRAC invites written 

comments from all interested parties. If 

you would like to file a written 

statement with the committee, you may 

do so either by submitting a hard or 

electronic copy before or after the 

meeting. Electronic copy of written 

statements should be emailed to asrac@

ee.doe.gov. 

Minutes: All notices, public 

comments, public meeting transcripts, 

and supporting documents associated 

with this working group are included in 

Docket No. EERE–2013–BT–NOC–0039. 

Issued in Washington, DC on November 1, 

2013. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2013–27034 Filed 11–8–13; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR part 25 

[Docket No. FAA–2013–0902; Notice No. 25– 

13–25–SC] 

Special Conditions: Airbus, Model 

A350–900 series Airplane; Pitch and 

Roll Limiting by Electronic Flight 

Control System 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed special 

conditions. 

SUMMARY: This action proposes special 

conditions for the Airbus Model A350– 

900 series airplanes. This airplane will 

have a novel or unusual design 

feature(s) associated with the Electronic 

Flight Control System that limits pitch 

and roll attitude functions. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

These proposed 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: We must receive your comments 

by December 27, 2013. 

ADDRESSES: Send comments identified 

by docket number FAA–2013–0902 

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) 227–1320. 

SUPPLEMENTARY INFORMATION: 

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 

proposed special conditions based on 

the comments we receive. 

Background 

On August 25, 2008, Airbus applied 

for a type certificate for their new Model 

A350–900 series airplane. Later, Airbus 

requested and the FAA approved an 

extension to the application for FAA 

type certification to June 28, 2009, The 

Model A350–900 series has a 

conventional layout with twin wingmounted Rolls-Royce Trent engines. It 

features a twin aisle 9-abreast economy 

class layout, and accommodates side-byside placement of LD–3 containers in 

the cargo compartment. The basic 

Model A350–900 series configuration 

will accommodate 315 passengers in a 

standard two-class arrangement. The 

design cruise speed is Mach 0.85 with 

a Maximum Take-Off Weight of 602,000 

lbs. Airbus proposes the Model A350– 

900 series to be certified for extended 

operations (ETOPS) beyond 180 minutes 

at entry into service for up to a 420- 

minute maximum diversion time. 

A special condition to supplement 

§ 25.143 concerning pitch and roll limits 

was developed for the Airbus A320, 

A330, A340, and A380 Models wherein 

performance of the limiting functions 

was monitored throughout the flight test 

program. The FAA expects similar 

monitoring to take place during the 

A350 flight test program in order to 

substantiate the pitch and roll attitude 

limiting functions and the 

appropriateness of the chosen limits. 

Type Certification Basis 

Under Title 14, Code of Federal 

Regulations (14 CFR) 21.17, Airbus must 

show that the Model A350–900 series 

meets the applicable provisions of 14 

CFR part 25, as amended by 

Amendments 25–1 through 25–128. 

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 A350–900 series because 

of a novel or unusual design feature, 

special conditions are prescribed under 

§ 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 proposed 

special conditions would also apply to 

the other model under § 21.101. 

In addition to the applicable 

airworthiness regulations and proposed 

special conditions, the Model A350–900 

series 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.’’ 

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Federal Register / Vol. 78, No. 218 / Tuesday, November 12, 2013 / Proposed Rules 67321 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, under § 11.38, 

and they become part of the typecertification basis under § 21.17(a)(2). 

Novel or Unusual Design Features 

The Airbus Model A350–900 series 

will incorporate the following novel or 

unusual design features: an Electronic 

Flight Control system (EFCS), that when 

operating in its normal mode, will 

prevent airplane pitch attitudes greater 

than +30 degrees and less than –15 

degrees, and roll angles greater than 

plus or minus 67 degrees. In addition, 

positive spiral stability is introduced for 

roll angles greater than 33 degrees at 

speeds below VMO/MMO. At speeds 

greater than VMO and up to VDF, 

maximum aileron control force is 

limited to only 45 degrees maximum 

bank angle. 

Discussion 

It is expected that high thrust-toweight ratios will provide the most 

critical cases for the positive pitch limit. 

A margin in pitch control must be 

available to enable speed control in 

maneuvers such as climb after takeoff, 

and balked landing climb. The pitch 

limit must not impede likely 

maneuvering made necessary by 

collision avoidance efforts. A negative 

pitch limit must similarly not interfere 

with collision avoidance capability or 

with attaining and maintaining speeds 

near VMO/MMO for emergency descent. 

Spiral stability, which is introduced 

above 33 degrees roll angle, and the roll 

limit must not restrict attaining roll 

angles up to 66 degrees (approximately 

2.5g level turn) with flaps up and 60 

degrees (approximately 2.0g level turn) 

with flaps down. The implementation of 

this spiral stability will require a steady 

aileron control force to maintain a 

constant bank angle above 33 degrees. 

This force must not require excessive 

pilot strength as stated in § 25.143(f). 

Applicability 

As discussed above, these proposed 

special conditions apply to Airbus 

Model A350–900 series airplanes. 

Should Airbus apply later for a change 

to the type certificate to include another 

model incorporating the same novel or 

unusual design feature, the proposed 

special conditions would apply to that 

model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on the Airbus 

Model A350–900 series airplanes. It is 

not a rule of general applicability. 

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 Proposed Special Conditions 

Accordingly, the Federal Aviation 

Administration (FAA) proposes the 

following special conditions as part of 

the type certification basis for Airbus 

Model A350–900 series airplanes. 

In addition to § 25.143, the following 

requirements apply: 

1. The pitch limiting function must 

not impede normal maneuvering for 

pitch angles up to the maximum 

required for normal maneuvering, 

including a normal all-engines operating 

takeoff, plus a suitable margin to allow 

for satisfactory speed control. 

2. The pitch and roll limiting 

functions must not restrict or prevent 

attaining pitch attitudes necessary for 

emergency maneuvering or roll angles 

up to 66 degrees with flaps up, or 60 

degrees with flaps down. Spiral 

stability, which is introduced above 33 

degrees roll angle, must not require 

excessive pilot strength to achieve these 

limit roll angles. Other protections, 

which further limit the roll capability 

under certain extreme angle of attack or 

attitude or high speed conditions, are 

acceptable, as long as they allow at least 

45 degrees of roll capability. 

Issued in Renton, Washington, on October 

22, 2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–26928 Filed 11–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No.FAA–2013–0942; Notice No. 25– 

13–30–SC] 

Special Conditions: Bombardier 

Aerospace Inc., Models BD–500–1A10 

and BD–500–1A11 Series Airplanes; 

Autobraking System Loads 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed special 

conditions. 

SUMMARY: This action proposes special 

conditions for the Bombardier 

Aerospace Inc. Models BD–500–1A10 

and BD–500–1A11 series airplanes. 

These airplanes will have novel or 

unusual design features associated with 

the autobraking system for use during 

landing. The applicable airworthiness 

regulations do not contain adequate or 

appropriate safety standards for this 

design feature. These proposed 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: Send your comments on or 

before December 27, 2013. 

ADDRESSES: Send comments identified 

by docket number FAA–2013–0942 

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: 

Mark Freisthler, FAA, Airframe and 

Cabin Safety Branch, ANM–115 

Transport Airplane Directorate, Aircraft 

mstockstill on DSK4VPTVN1PROD with PROPOSALS