33674 Federal Register / Vol. 79, No. 113 / Thursday, June 12, 2014 / Rules and Regulations 

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 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 Airbus Model 

A350–900 series airplanes in lieu of 

§ 25.397(c), which are identical to A320, 

A340, and A380 special conditions on 

the same subject: 

For the Airbus Model A350–900 

series airplane equipped with stick 

controls designed for forces to be 

applied by one wrist and not arms, the 

limit pilot forces are as follows: 

1. For all components between and 

including the handle and its control 

stops. 

Pitch Roll 

Nose up 200 lbf. ....... Nose left 100 lbf. 

2. For all other components of the 

side stick control assembly, but 

excluding the internal components of 

the electrical sensor assemblies, to avoid 

damage as a result of an in-flight jam. 

Pitch Roll 

Nose up 125 lbf. ....... Nose left 50 lbf. 

Nose down 125 lbf. ... Nose right 50 lbf. 

Issued in Renton, Washington, on: April 

22, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–13666 Filed 6–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2013–0890; Special 

Conditions No. 25–524–SC] 

Special Conditions: Airbus Model 

A350–900 Series Airplane; Ground 

Pivoting Loads 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for Airbus Model A350–900 

Series airplanes. These airplanes will 

have a novel or unusual design 

feature(s) associated with a braking 

system that affects the airplane’s 

pivoting behavior. 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: Effective July 14, 2014. 

FOR FURTHER INFORMATION CONTACT: 

Todd Martin, FAA, Airframe/Cabin 

Safety, ANM–115, Transport Airplane 

Directorate, Aircraft Certification 

Service, 1601 Lind Avenue SW., 

Renton, Washington, 98057–3356; 

telephone (425) 227–1178; facsimile 

(425) 227–1320. 

SUPPLEMENTARY INFORMATION: 

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 airplane 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 airplane to be certified for 

extended operations (ETOPS) beyond 

180 minutes at entry into service for up 

to a 420-minute maximum diversion 

time. 

The Airbus Model A350–900 series 

airplane is equipped with a braking 

system that affects the airplane’s 

pivoting behavior. During pivoting the 

braking system inhibits braking on some 

wheels. Title 14 Code of Federal 

Regulations (14 CFR) 25.503 and 

European Aviation Safety Agency 

(EASA) Certification Specification (CS) 

section 25.503, each specify limit loads 

due to pivoting, however, system effects 

are not taken into account. 

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 25–129. 

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 special 

conditions would also apply to the other 

model under § 21.101. 

In addition to the applicable 

airworthiness regulations and 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.’’ 

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 

airplane will incorporate the following 

novel or unusual design features: a 

braking system that affects the airplane’s 

pivoting behavior. 

Discussion 

Within the Aviation Rulemaking 

Advisory Committee, the Loads and 

Dynamics Harmonization Working 

Group developed criteria for 

determining pivoting loads. The group 

recommended, for airplanes with more 

than two main landing gear units, a 

rational pivoting maneuver that takes 

into account the effects of the braking 

system and tire characteristics, in lieu of 

the current requirement. Although the 


rmajette on DSK2TPTVN1PROD with RULES
Federal Register / Vol. 79, No. 113 / Thursday, June 12, 2014 / Rules and Regulations 33675 

Airbus Model A350–900 series airplane 

has two main landing gear units, EASA 

and the FAA propose to apply the same 

criteria on this airplane. 

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. 

Discussion of Comments 

Notice of proposed special conditions 

No. 25–13–10–SC for Airbus Model 

A350–900 series airplanes was 

published in the Federal Register on 

October 29, 2013 (78FR64415). The 

Boeing Company submitted one 

comment, which stated that ‘‘there is 

not a specific requirement to consider 

failure modes. Failure modes of the 

brake system that would cause brakes to 

be applied during pivoting should be 

investigated in accordance with the 

requirements relating to systems and 

structures interaction. We suggest that 

the FAA consider revising the proposal 

to include this specific requirement.’’ 

Failure modes of the braking system 

are addressed by a separate specialconditions document titled Interaction 

of Systems and Structures, published in 

the Federal Register on December 20, 

2013 (78FR76980). The Interaction of 

Systems and Structures special 

conditions requires that the effects of 

system failures be taken into account, 

and specifically addresses the pivoting 

requirement, § 25.503, and any special 

condition used in lieu of § 25.503. 

This (i.e., current) special conditions 

document addresses loads associated 

with structural design not specific to a 

failure condition. 

Applicability 

As discussed above, these 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 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 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 Airbus Model A350–900 series 

airplanes in lieu of § 25.503: 

1. The main landing gear and 

supporting structure must be designed 

for the loads induced by pivoting during 

ground maneuvers. 

a. The following rational pivoting 

maneuvers must be considered: 

i. Towing at the nose gear at the 

critical towing angle with no brakes 

applied, including cases with torque 

links disconnected; and separately, 

ii. Application of symmetrical or 

unsymmetrical forward thrust to aid 

pivoting, with or without braking by 

pilot action on the pedals. 

b. The airplane is assumed to be in 

static equilibrium, with the loads being 

applied at the ground contact points. 

c. The limit vertical load factor must 

be 1.0, and: 

i. For wheels with brakes applied, the 

coefficient of friction must be 0.8, 

ii. For wheels with brakes not 

applied, the ground tire reactions must 

be based on reliable tire data. 

Issued in Renton, Washington, on: April 

25, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–13667 Filed 6–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2014–0244; Special 

Conditions No. 25–552–SC] 

Special Conditions: Boeing Model 787– 

9, Side-Facing Seats 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special condition; request 

for comments. 

SUMMARY: These special conditions are 

issued for the Boeing Model 787–9 

airplane. This airplane has a novel or 

unusual design feature associated with 

side-facing seats. The applicable 

airworthiness regulations do not contain 

adequate or appropriate safety standards 

for occupants of seats installed at an 

angle of 49 degrees to the centerline of 

the airplane, nor for inflatable restraint 

systems. 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 June 12, 2014. We 

must receive your comments by July 28, 

2014. 

ADDRESSES: Send comments identified 

by docket number FAA–2014–0244 

using any of the following methods: 

Federal eRegulations Portal: Go to 

http://www.regulations.gov/ andfollow 

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: Jeff 

Gardlin, Airframe and Cabin Safety, 

ANM–115, Transport Airplane 

Directorate, Aircraft Certification 

Service, 1601 Lind Avenue SW., 

Renton, Washington 98057–3356; 

telephone 425–227–2136; facsimile 

425–227–1149. 

SUPPLEMENTARY INFORMATION: The FAA 

has determined that notice of, and 

opportunity for prior public comment 


rmajette on DSK2TPTVN1PROD with RULES