76772 Federal Register / Vol. 78, No. 244 / Thursday, December 19, 2013 / Proposed Rules 

listed in paragraphs (j)(2)(i) through (iii) 

of this section. 

(k) Party. The term ‘‘party’’ with 

respect to a covered agreement means 

each NGEP and each insured depository 

institution or affiliate that entered into 

the agreement. 

(l) Relevant supervisory agency. The 

‘‘relevant supervisory agency’’ for a 

covered agreement means the 

appropriate Federal banking agency 

for— 

(1) Each insured depository 

institution (or subsidiary thereof) that is 

a party to the covered agreement; 

(2) Each insured depository 

institution (or subsidiary thereof) or 

CRA affiliate that makes payments or 

loans or provides services that are 

subject to the covered agreement; and 

(3) Any company (other than an 

insured depository institution or 

subsidiary thereof) that is a party to the 

covered agreement. 

(m) State savings association. ‘‘State 

savings association’’ has the same 

meaning as in section 3(b)(3) of the 

Federal Deposit Insurance Act (12 

U.S.C. 1813(b)(3)). 

(n) Term of agreement. An agreement 

that does not have a fixed termination 

date is considered to terminate on the 

last date on which any party to the 

agreement makes any payment or 

provides any loan or other resources 

under the agreement, unless the relevant 

supervisory agency for the agreement 

otherwise notifies each party in writing. 

PART 390—REGULATIONS 

TRANSFERRED FROM THE OFFICE OF 

THRIFT SUPERVISION 

Subpart H —Disclosure and Reporting 

of CRA-Related Agreements 

■ 4. The authority citation for part 390 

is revised to read as follows: 

Authority: 12 U.S.C. 1819. 

Subpart A also issued under 12 U.S.C. 

1820. 

Subpart B also issued under 12 U.S.C. 

1818. 

Subpart C also issued under 5 U.S.C. 504; 

554–557; 12 U.S.C. 1464; 1467; 1468; 1817; 

1818; 1820; 1829; 3349, 4717; 15 U.S.C. 78l; 

78o–5; 78u–2; 28 U.S.C. 2461 note; 31 U.S.C. 

5321; 42 U.S.C. 4012a. 

Subpart D also issued under 12 U.S.C. 

1817; 1818; 1820; 15 U.S.C. 78l. 

Subpart E also issued under 12 U.S.C. 

1813; 1831m; 15 U.S.C. 78. 

Subpart F also issued under 5 U.S.C. 552; 

559; 12 U.S.C. 2901 et seq. 

Subpart G also issued under 12 U.S.C. 2810 

et seq., 2901 et seq.; 15 U.S.C. 1691; 42 U.S.C. 

1981, 1982, 3601–3619. 

Subpart I also issued under 12 U.S.C. 

1831x. 

Subpart J also issued under 12 U.S.C. 

1831p–1. 

Subpart K also issued under 12 U.S.C. 

1817; 1818; 15 U.S.C. 78c; 78l. 

Subpart L also issued under 12 U.S.C. 

1831p–1. 

Subpart M also issued under 12 U.S.C. 

1818. 

Subpart N also issued under 12 U.S.C. 

1821. 

Subpart O also issued under 12 U.S.C. 

1828. 

Subpart P also issued under 12 U.S.C. 

1470; 1831e; 1831n; 1831p–1; 3339. 

Subpart Q also issued under 12 U.S.C. 

1462; 1462a; 1463; 1464. 

Subpart R also issued under 12 U.S.C. 

1463; 1464; 1831m; 1831n; 1831p–1. 

Subpart S also issued under 12 U.S.C. 

1462; 1462a; 1463; 1464; 1468a; 1817; 1820; 

1828; 1831e; 1831o; 1831p–1; 1881–1884; 

3207; 3339; 15 U.S.C. 78b; 78l; 78m; 78n; 

78p; 78q; 78w; 31 U.S.C. 5318; 42 U.S.C. 

4106. 

Subpart T also issued under 12 U.S.C. 

1462a; 1463; 1464; 15 U.S.C. 78c; 78l; 78m; 

78n; 78w. 

Subpart U also issued under 12 U.S.C. 

1462a; 1463; 1464; 15 U.S.C. 78c; 78l; 78m; 

78n; 78p; 78w; 78d–1; 7241; 7242; 7243; 

7244; 7261; 7264; 7265. 

Subpart V also issued under 12 U.S.C. 

3201–3208. 

Subpart W also issued under 12 U.S.C. 

1462a; 1463; 1464; 15 U.S.C. 78c; 78l; 78m; 

78n; 78p; 78w. 

Subpart X also issued under 12 U.S.C. 

1462; 1462a; 1463; 1464; 1828; 3331 et seq. 

Subpart Y also issued under 12 U.S.C. 

1831o. 

Subpart Z also issued under 12 U.S.C. 

1462; 1462a; 1463; 1464; 1828 (note). 

Subpart H—[Removed and Reserved] 

■ 5. Remove and reserve subpart H 

consisting of §§ 390.160 through 

390.170. 

Dated at Washington, DC, this 10th day of 

December, 2013. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2013–29787 Filed 12–18–13; 8:45 am] 

BILLING CODE 6741–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2013–0801; Notice No. 25– 

13–41–SC] 

Special Conditions: Airbus Model 

A350–900 Airplanes; Permanently 

Installed Rechargeable Lithium-Ion 

Batteries and Battery Systems 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed special 

conditions. 

SUMMARY: This action proposes special 

conditions for Airbus Model A350–900 

series airplanes. These airplanes will 

have a novel or unusual design feature 

associated with permanently installed 

rechargeable lithium-ion batteries and 

battery systems. These batteries have 

certain failure, operational, and 

maintenance characteristics that differ 

significantly from those of the nickelcadmium and lead-acid rechargeable 

batteries currently approved for 

installation on large transport-category 

airplanes. 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 January 21, 2014. 

ADDRESSES: Send comments, identified 

by docket number FAA–2013–0801, 

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 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://Dockets 

Info.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 


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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: 

Nazih Khaouly, FAA, Airplane and 

Flight Crew Interface Branch, ANM– 

111, Transport Airplane Directorate, 

Aircraft Certification Service, 1601 Lind 

Avenue SW., Renton, Washington, 

98057–3356; telephone 425–227–2432; 

facsimile 425–227–1149. 

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 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 XWB 

engines. It features a twin aisle, 9- 

abreast, economy-class layout, and 

accommodates side-by-side placement 

of LD–3 containers in the cargo 

compartment. The basic Model A350– 

900 series configuration accommodates 

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. 

Existing airworthiness regulations did 

not anticipate the use of lithium-ion 

batteries and battery systems on aircraft. 

Lithium-ion batteries and battery 

systems have new hazards that were not 

contemplated when the existing 

regulations were issued. In Title 14, 

Code of Federal Regulations (14 CFR) 

25.1353, the FAA provided an 

airworthiness standard for lead-acid 

batteries and nickel-cadmium batteries. 

These special conditions provide an 

equivalent level of safety as that of the 

existing regulation. The current 

regulations are not adequate for 

rechargeable lithium-battery and battery 

system installations. Additional 

lithium-battery and battery system 

special conditions are required to 

ensure the same level of safety as set 

forth by the existing regulation intended 

for other battery technology. 

Type Certification Basis 

Under the provisions of 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. 

The FAA has determined that Airbus 

Model A350–900 series airplanes must 

comply with the following sections: 

§ 25.863(a) through (d), Amendment 25– 

61 and Amendment 25–66. 

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 or series 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 Airbus Model A350–900 

airplane must comply with the fuel-vent 

and exhaust-emission requirements of 

14 CFR part 34, 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 § 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 airplane 

will incorporate the following novel or 

unusual design features: permanently 

installed rechargeable lithium batteries 

and lithium battery systems. 

Discussion 

The current regulations governing 

installation of batteries in large 

transport-category airplanes were 

derived from Civil Air Regulations 

(CAR) part 4b.625(d) as part of the recodification of CAR 4b that established 

14 CFR part 25 in February 1965. The 

new battery requirements, 

§ 25.1353(c)(1) through (c)(4), basically 

reworded the CAR requirements. 

Increased use of nickel-cadmium 

batteries in small airplanes resulted in 

increased incidents of battery fires and 

failures which led to additional 

rulemaking affecting large transportcategory airplanes as well as small 

airplanes. On September 1, 1977 and 

March 1, 1978, the FAA issued 

§ 25.1353(c)(5) and (c)(6), respectively, 

governing nickel-cadmium battery 

installations on large transport-category 

airplanes. 

The proposed use of lithium-ion 

batteries and battery systems for 

equipment and systems on Airbus 

Model A350 airplanes has prompted the 

FAA to review the adequacy of these 

existing regulations. Our review 

indicates that the existing regulations do 

not adequately address several failure, 

operational, and maintenance 

characteristics of lithium-ion batteries 

and battery systems that could affect the 

safety and reliability of the Airbus 

model A350–900 airplane rechargeable 

lithium batteries and rechargeable 

lithium-battery-system installations. 

At present, commercial aviation has 

limited experience with use of 

rechargeable lithium-ion batteries and 

battery systems in applications 

involving commercial aviation. 

However, other users of this technology, 

ranging from wireless telephone 

manufacturers to the electric-vehicle 

industry, have noted potential hazards 

with lithium-ion batteries and battery 

systems. These problems include 

overcharging, over-discharging, and 

flammability of cell components. 

1. Overcharging 

In general, lithium-ion batteries and 

battery systems are significantly more 

susceptible to internal failures that can 

result in self-sustaining increases in 

temperature and pressure (i.e., thermal 

runaway) than their nickel-cadmium or 

lead-acid counterparts. This condition is 

especially true for overcharging, which 

causes heating and destabilization of the 

components of the cell, leading to the 

formation (by plating) of highly unstable 

metallic lithium. The metallic lithium 

can ignite, resulting in a self-sustaining 

fire or explosion. Finally, the severity of 

thermal runaway, due to overcharging, 

increases with increasing battery 

capacity due to the higher amount of 

electrolyte in large batteries. 

2. Over-Discharging 

Discharge of some types of lithiumion batteries and battery systems, 

beyond a certain voltage (typically 2.4 

volts), can cause corrosion of the 


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electrodes of the cell, resulting in loss 

of battery capacity that cannot be 

reversed by recharging. This loss of 

capacity may not be detected by the 

simple voltage measurements 

commonly available to flightcrews as a 

means of checking battery status—a 

problem shared with nickel-cadmium 

batteries. 

3. Flammability of Cell Components 

Unlike nickel-cadmium and lead-acid 

batteries, some types of lithium-ion 

batteries and battery systems use liquid 

electrolytes that are flammable. The 

electrolyte can serve as a source of fuel 

for an external fire if there is a breach 

of the battery container. 

The problems lithium-ion battery and 

battery-system users experience raise 

concern about the use of these batteries 

in commercial aviation. The intent of 

the proposed special conditions is to 

establish appropriate airworthiness 

standards for lithium-ion battery 

installations in Airbus Model A350–900 

airplanes and to ensure, as required by 

§§ 25.1309 and 25.601, that these 

lithium-ion batteries and battery 

systems will not result in an unsafe 

condition. To address these concerns, 

these special conditions adopt the 

following requirements: 

• Those sections of 14 CFR 25.1353 

that are applicable to lithium ion 

batteries. 

• The flammable fluid fire protection 

requirements of 14 CFR 25.863. In the 

past, this rule was not applied to 

batteries of transport category airplanes, 

since the electrolytes used in lead-acid 

and nickel-cadmium batteries are not 

flammable. 

• New requirements to address the 

hazards of overcharging and overdischarging that are unique to lithium 

ion batteries. 

• New maintenance requirements to 

ensure that batteries used as spares are 

maintained in an appropriate state of 

charge. 

These special conditions are similar 

to lithium-ion batteries and battery 

systems special conditions adopted for 

the Boeing Model 787 (72 FR 57842; 

October 11, 2007). 

Applicability 

As discussed above, these special 

conditions are applicable to the 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 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 airplanes. 

These proposed special conditions 

require that (1) all characteristics of the 

rechargeable lithium-ion batteries and 

battery systems, and their installation, 

that could affect safe operation of 

Airbus Model A350–900 airplanes, are 

addressed, and (2) appropriate 

Instructions for Continued 

Airworthiness, which include 

maintenance requirements, are 

established to ensure the availability of 

electrical power, when needed, from the 

batteries. 

The FAA proposes that the following 

special conditions apply to all 

rechargeable lithium-ion batteries and 

battery systems on Airbus Model A350– 

900 airplanes, in lieu of the 

requirements of § 25.1353(b)(1) through 

(b)(4) at Amendment 25–113: 

Rechargeable lithium-ion batteries 

and battery systems on Airbus Model 

A350–900 airplanes must be designed 

and installed as follows: 

1. Safe cell temperatures and 

pressures must be maintained during 

any foreseeable charging or discharging 

condition, and during any failure of the 

charging or battery monitoring system 

not shown to be extremely remote. The 

rechargeable lithium-ion batteries and 

battery systems must preclude 

explosion in the event of those failures. 

2. Design of the rechargeable lithiumion batteries and battery systems must 

preclude the occurrence of selfsustaining, uncontrolled increases in 

temperature or pressure. 

3. No explosive or toxic gases emitted 

by any rechargeable lithium-ion 

batteries and battery systems in normal 

operation, or as the result of any failure 

of the battery charging system, 

monitoring system, or battery 

installation that is not shown to be 

extremely remote, may accumulate in 

hazardous quantities within the 

airplane. 

4. Installations of rechargeable 

lithium-ion batteries and battery 

systems must meet the requirements of 

§ 25.863(a) through (d). 

5. No corrosive fluids or gases that 

may escape from any lithium-ion 

batteries and battery systems may 

damage surrounding structure or any 

adjacent systems, equipment, or 

electrical wiring of the airplane in such 

a way as to cause a major or more severe 

failure condition, in accordance with 

§ 25.1309 (b) and applicable regulatory 

guidance. 

6. Each lithium-ion battery and 

battery system must have provisions to 

prevent any hazardous effect on 

structure or essential systems caused by 

the maximum amount of heat the 

battery can generate during a short 

circuit of the battery or of its individual 

cells. 

7. Rechargeable lithium-ion batteries 

and battery systems must have a system 

to automatically control the charging 

rate of the battery, so as to prevent 

battery overheating or overcharging, 

and: 

i. A battery-temperature sensing and 

over-temperature warning system with a 

means for automatically disconnecting 

the battery from its charging source in 

the event of an over-temperature 

condition, or, 

ii. A battery-failure sensing and 

warning system with a means for 

automatically disconnecting the battery 

from its charging source in the event of 

battery failure. 

8. Any rechargeable lithium-ion 

batteries and battery systems, the 

function of which are required for safe 

operation of the airplane, must 

incorporate a monitoring and warning 

feature that will provide an indication 

to the appropriate flight crewmembers 

whenever the state-of-charge of the 

batteries has fallen below levels 

considered acceptable for dispatch of 

the airplane. 

9. The Instructions for Continued 

Airworthiness required by § 25.1529 

must contain maintenance requirements 

to assure that the lithium-ion batteries 

are sufficiently charged at appropriate 

intervals specified by the battery 

manufacturer and the equipment 

manufacturer of the rechargeable 

lithium-ion battery or rechargeable 

lithium-ion battery system. This is 

required to ensure that rechargeable 

lithium-ion batteries and battery 

systems will not degrade below 

specified ampere-hour levels sufficient 

to power the aircraft system, for 

intended applications. The Instructions 

for Continued Airworthiness must also 

contain procedures for the maintenance 

of batteries in spares storage to prevent 


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the replacement of batteries with 

batteries that have experienced 

degraded charge-retention ability or 

other damage due to prolonged storage 

at a low state of charge. Replacement 

batteries must be of the same 

manufacturer and part number as 

approved by the FAA. Precautions 

should be included in the Instructions 

for Continued Airworthiness 

maintenance instructions to prevent 

mishandling of the rechargeable 

lithium-ion batteries and battery 

systems, which could result in shortcircuit or other unintentional impact 

damage caused by dropping or other 

destructive means. 

Note 1: The term ‘‘sufficiently charged’’ 

means that the battery will retain enough of 

a charge, expressed in ampere-hours, to 

ensure that the battery cells will not be 

damaged. A battery cell may be damaged by 

lowering the charge below a point where the 

battery experiences a reduction in the ability 

to charge and retain a full charge. This 

reduction would be greater than the 

reduction that may result from normal 

operational degradation. 

Note 2: These special conditions are not 

intended to replace § 25.1353(b) at 

Amendment 25–113 in the certification basis 

for Airbus Model A350–900 airplanes. These 

special conditions apply only to rechargeable 

lithium-ion batteries and battery systems and 

their installations. The requirements of 

§ 25.1353(b) at Amendment 25–113 remain in 

effect for batteries and battery installations 

on Airbus Model A350–900 airplanes that do 

not use rechargeable lithium-ion batteries. 

Issued in Renton, Washington, on 

December 10, 2013. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–30231 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–2013–1002; Notice No. 25– 

13–36–SC] 

Special Conditions: Airbus, Model 

A350–900 Series Airplane; Lightning 

Protection of Fuel Tank Structure To 

Prevent Fuel Tank Vapor Ignition 

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. These airplanes 

will have a novel or unusual design 

feature(s) that will incorporate a 

nitrogen generation system (NGS) for all 

fuel tanks that actively reduce 

flammability exposure within the fuel 

tanks significantly below that required 

by the fuel tank flammability 

regulations. Among other benefits, the 

NGS significantly reduces the potential 

for fuel vapor ignition caused by 

lightning strikes. 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 February 3, 2014. 

ADDRESSES: Send comments identified 

by docket number FAA–2013–1002 

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 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: 

Doug Bryant, Propulsion/Mechanical 

Systems, ANM–112, Transport Airplane 

Directorate, Aircraft Certification 

Service, 1601 Lind Avenue SW., 

Renton, Washington, 98057–3356; 

telephone (425) 227–2384; 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 special 

conditions based on the comments we 

receive. 

Background 

On August 25, 2008, Airbus applied 

for a type certificate for their new 

Airbus 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 wing-mounted Rolls-Royce Trent 

XWB engines. It features a twin aisle 9- 

abreast economy class layout, and 

accommodates side-by-side 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. 

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. 


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