Federal Register / Vol. 79, No. 39 / Thursday, February 27, 2014 / Proposed Rules 11019 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. AMOCs approved previously for AD 

2007–06–12, Amendment 39–14993 (72 FR 

12555, March 16, 2007), are approved as 

AMOCs for the corresponding provisions of 

paragraph (i) of this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval). You are required to ensure the 

product is airworthy before it is returned to 

service. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0016, dated 

January 16, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0061. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04259 Filed 2–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0060; Directorate 

Identifier 2012–NM–194–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directives (AD) 2006–21– 

08, AD 2007–14–01, AD 2008–25–02, 

AD 2010–04–09, AD 2011–01–02, and 

AD 2012–16–05, for certain Airbus 

Model A330 and 340 series airplanes. 

AD 2006–21–08, AD 2007–14–01, AD 

2008–25–02, AD 2010–04–09, AD 2011– 

01–02, and AD 2012–16–05 currently 

require revising the maintenance 

program or inspection program to 

incorporate certain maintenance 

requirements and airworthiness 

limitations for fuel tank systems. Since 

we issued AD 2006–21–08, AD 2007– 

14–01, AD 2008–25–02, AD 2010–04– 

09, AD 2011–01–02, and AD 2012–16– 

05, we have determined that more 

restrictive maintenance requirements 

and airworthiness limitations are 

necessary. This proposed AD would 

require a new maintenance or 

inspection program revision. We are 

proposing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 14, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0060; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0060; Directorate Identifier 

2012–NM–194–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On October 10, 2006, we issued AD 

2006–21–08, Amendment 39–14793 (71 

FR 61639, October 19, 2006), for certain 

Airbus Model A330–200, A340–200, 

and A340–300 airplanes. AD 2006–21– 

08 requires installation of heat shields 

in the belly fairing of the center 

fuselage. AD 2006–21–08 resulted from 

fuel system reviews conducted by the 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
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manufacturer. We issued AD 2006–21– 

08 to prevent exposing any fuel leaked 

from the center fuel tank to the hot 

temperature areas of the air 

conditioning packs, which could result 

in a fire and consequent fuel tank 

explosion. 

On June 25, 2007, we issued AD 

2007–14–01, Amendment 39–15123 (72 

FR 38006, July 12, 2007), for all Airbus 

Model A330 and A340 airplanes. AD 

2007–14–01 requires revising the 

Airworthiness Limitations Section 

(ALS) of the Instructions for Continued 

Airworthiness (ICA) to incorporate new 

limitations for fuel tank systems. AD 

2007–14–01 resulted from fuel system 

reviews conducted by the manufacturer. 

We issued AD 2007–14–01 to prevent 

the potential of ignition sources inside 

fuel tanks, which, in combination with 

flammable fuel vapors caused by latent 

failures, alterations, repairs, or 

maintenance actions, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

On November 26, 2008, we issued AD 

2008–25–02, Amendment 39–15760 (73 

FR 75307, December 11, 2008), for all 

Airbus Model A330 airplanes, and 

Model A340–200 and A340–300 

airplanes. AD 2008–25–02 requires 

inspecting P-clips in the wings, 

modifying the electrical bonding of the 

equipment installed in fuel tanks, and 

applying applicable corrective actions. 

AD 2008–25–02 resulted from fuel 

system reviews conducted by the 

manufacturer. We issued AD 2008–25– 

02 to prevent the potential of ignition 

sources inside fuel tanks, which, in 

combination with flammable fuel 

vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

On February 5, 2010, we issued AD 

2010–04–09, Amendment 39–16202 (75 

FR 7940, February 23, 2010; corrected 

March 3, 2010 (75 FR 9515)), for certain 

Airbus Model A330–200 series 

airplanes, and Model A340–200 and 

A340–300 series airplanes. AD 2010– 

04–09 requires the installation of plugs 

on the heat shield panels of the lefthand (LH) and right-hand (RH) air 

conditioning packs. AD 2010–04–09 

resulted from the development of a 

repair solution by the manufacturer. We 

issued AD 2010–04–09 to prevent fuel 

from the center tank leaking through 

holes in the heat shield panels, which 

could cause vapor to develop into a 

potential source of ignition, possibly 

resulting in a fuel tank explosion and 

consequent loss of the airplane. 

On December 17, 2010, we issued AD 

2011–01–02, Amendment 39–16555 (76 

FR 432, January 5, 2011), for certain 

Airbus Model A330–201, –202, –203, 

–223, and –243 airplanes; certain Airbus 

Model A330–300 series airplanes; and 

all Airbus Model A340–200 and –300 

series airplanes. AD 2011–01–02 

requires installing flight warning 

computer (FWC) software on both 

FWCs. AD 2011–01–02 resulted from 

fuel system reviews conducted by the 

manufacturer. We issued AD 2011–01– 

02 to prevent failure of the auxiliary 

power unit (APU) bleed leak detection 

system, which could result in overheat 

of the fuel tank located in the horizontal 

stabilizer and ignition of the fuel vapors 

in that tank and consequent loss of the 

airplane. 

On July 31, 2012, we issued AD 2012– 

16–05, Amendment 39–17152 (77 FR 

48425, August 14, 2012), for certain 

Airbus Model A330–200 and –200 

freighter series airplanes; and Model 

A340–200, A340–300, A340–500, and 

A340–600 series airplanes. AD 2012– 

16–05 requires modification of the 

control circuit for the fuel pumps for the 

center fuel tanks for certain airplanes, 

and center and rear fuel tanks for certain 

other airplanes. AD 2012–16–05 

resulted from fuel system reviews 

conducted by the manufacturer. We 

issued AD 2012–16–05 to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

Actions Since Previously Described 

ADs Were Issued 

Since we issued AD 2006–21–08, 

Amendment 39–14793 (71 FR 61639, 

October 19, 2006); AD 2007–14–01, 

Amendment 39–15123 (72 FR 38006, 

July 12, 2007); AD 2008–25–02, 

Amendment 39–15760 (73 FR 75307, 

December 11, 2008); AD 2010–04–09, 

Amendment 39–16202 (75 FR 7940, 

February 23, 2010; corrected March 3, 

2010 (75 FR 9515)); AD 2011–01–02, 

Amendment 39–16555 (76 FR 432, 

January 5, 2011); and AD 2012–16–05, 

Amendment 39–17152 (77 FR 48425, 

August 14, 2012); we have determined 

that more restrictive maintenance 

requirements and airworthiness 

limitations are necessary. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0168, 

dated August 31, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Prompted by an accident [involving a fuel 

tank system explosion in flight] * * * the 

FAA published Special Federal Aviation 

Regulation (SFAR) 88 (66 FR 23086, May 7, 

2001) and the Joint Aviation Authorities 

(JAA) published Interim Policy INT/POL/25/ 

12. The design review conducted Airbus to 

develop Fuel Airworthiness Limitations 

(FAL) for Airbus on A330 and A340 

aeroplanes in response to these regulations. 

The FAL * * * have been approved by the 

European Aviation Safety Agency (EASA) 

* * * ALS Part 5. 

Failure to comply with items as identified 

in Airbus A330 and A340 ALS Part 5 could 

result in a fuel tank explosion and 

consequent loss of the aeroplane. 

To address this condition, EASA issued: 

EASA AD 2007–0023, dated January 25, 

2007 (http://ad.easa.europa.eu/ad/2007- 

0023), which corresponds to FAA AD 2007– 

14–01, Amendment 39–15123 (72 FR 38006, 

July 12, 2007) to require compliance with 

FAL * * * (comprising maintenance/

inspection tasks and Critical Design 

Configuration Control Limitations (CDCCL)) 

for A330 aeroplanes, and 

EASA AD 2006–0205, dated July 11, 2006 

(http://ad.easa.europa.eu/ad/2006-0205), 

which also corresponds to FAA AD 2007–14– 

01, Amendment 39–15123 (72 FR 38006, July 

12, 2007) to require compliance with FAL 

* * * (comprising maintenance/inspection 

tasks and Critical Design Configuration 

Control Limitations (CDCCL)) for Airbus 

A340 aeroplanes. 

All other EASA ADs * * * required 

accomplishment of aeroplane modifications 

related to Fuel Tank Safety items, the 

requirements and compliance times of which 

are now integrated into ALS Part 5. 

For the reasons described above this 

[EASA] AD * * * requires the 

implementation of the new or more 

restrictive maintenance requirements and/or 

airworthiness limitations as specified in the 

revision 00 of Airbus A340 ALS Part 5. 

The unsafe condition is the potential of 

ignition sources inside fuel tanks. Such 

ignition sources, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov 

by searching for and locating it in 

Docket No. FAA–2014–0060. 

Relevant Service Information 

Airbus has issued A330 ALS Part 5— 

Fuel Airworthiness Limitations, dated 

November 16, 2011. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

Related Rulemaking 

We have issued AD 2013–26–03, 

Amendment 39–17712 (78 FR 79292, 

December 30, 2013), for Airbus Model 

A340 airplanes to require revising the 

maintenance or inspection program to 

incorporate certain maintenance 

requirements and airworthiness 

limitations. AD 2013–26–03 terminates 


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Federal Register / Vol. 79, No. 39 / Thursday, February 27, 2014 / Proposed Rules 11021 

the requirements of the following ADs 

for Model A340 airplanes only: 

• AD 2006–21–08, Amendment 39– 

14793 (71 FR 61639, October 19, 2006); 

• AD 2007–14–01, Amendment 39– 

15123 (72 FR 38006, July 12, 2007); 

• AD 2008–25–02, Amendment 39– 

15760 (73 FR 75307, December 11, 

2008); 

• AD 2010–04–09, Amendment 39– 

16202 (75 FR 7940, February 23, 2010; 

corrected March 3, 2010 (75 FR 9515)); 

• AD 2011–01–02, Amendment 39– 

16555 (76 FR 432, January 5, 2011); and 

• AD 2012–16–05, Amendment 39– 

17152 (77 FR 48425, August 14, 2012). 

Because AD 2013–26–03, Amendment 

39–17712 (78 FR 79292, December 30, 

2013), terminates the requirements of 

the preceding ADs and requires new 

airworthiness limitations for Airbus 

Model A340 series airplanes, we have 

not included Airbus Model A340 series 

airplanes in the applicability of this 

proposed AD. This proposed AD applies 

only to the Airbus Model A330 series 

airplanes specified in paragraph (c) of 

this proposed AD. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

This proposed AD would retain none 

of the requirements of the ADs listed 

below, because those requirements are 

now contained in Airbus A330 ALS Part 

5—Fuel Airworthiness Limitations, 

dated November 16, 2011: 

• AD 2006–21–08, Amendment 39– 

14793 (71 FR 61639, October 19, 2006). 

• AD 2007–14–01, Amendment 39– 

15123 (72 FR 38006, July 12, 2007). 

• AD 2008–25–02, Amendment 39– 

15760 (73 FR 75307, December 11, 

2008). 

• AD 2010–04–09, Amendment 39– 

16202 (75 FR 7940, February 23, 2010; 

corrected March 3, 2010 (75 FR 9515)). 

• AD 2011–01–02, Amendment 39– 

16555 (76 FR 432, January 5, 2011). 

• AD 2012–16–05, Amendment 39– 

17152 (77 FR 48425, August 14, 2012). 

This proposed AD would require 

implementation of certain maintenance 

requirements and airworthiness 

limitations. This proposed AD would 

also require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

this Proposed AD and the MCAI or 

Service Information.’’ 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections) and Critical 

Design Configuration Control 

Limitations (CDCCLs). Compliance with 

these actions and CDCCLs is required by 

14 CFR 91.403(c). For airplanes that 

have been previously modified, altered, 

or repaired in the areas addressed by 

these actions, the operator may not be 

able to accomplish the actions described 

in the revisions. In this situation, to 

comply with 14 CFR 91.403(c), the 

operator must request approval for an 

alternative method of compliance 

according to the procedures specified in 

paragraph (j)(1) of this AD. The request 

should include a description of changes 

to the required actions that will ensure 

the continued operational safety of the 

airplane. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

This NPRM proposes to incorporate 

Airbus A330 ALS Part 5—Fuel 

Airworthiness Limitations, dated 

November 16, 2011, including ‘‘the 

specified compliance times’’ for the 

actions. However, the compliance times 

in this proposed AD for certain initial 

actions is different from those specified 

in Airbus A330 ALS Part 5—Fuel 

Airworthiness Limitations, dated 

November 16, 2011, because the actions 

were required by the ADs identified in 

the paragraph titled ‘‘Related 

Rulemaking’’ in this AD. Therefore, the 

initial compliance time is relative to the 

effective date of the applicable 

superseded AD, as specified in 

paragraph (h) of this NPRM. 

Costs of Compliance 

We estimate that this proposed AD 

affects 80 airplanes of U.S. registry. 

We estimate that it would take about 

1 work-hour per product to comply with 

the basic requirements of this proposed 

AD. The average labor rate is $85 per 

work-hour. Required parts would cost 

about $0 per product. Based on these 

figures, we estimate the cost of this 

proposed AD on U.S. operators to be 

$6,800, or $85 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This proposed 

regulation is within the scope of that 

authority because it addresses an unsafe 

condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing AD 2006–21–08, 

Amendment 39–14793 (71 FR 61639, 

October 19, 2006); AD 2007–14–01, 

Amendment 39–15123 (72 FR 38006, 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
11022 Federal Register / Vol. 79, No. 39 / Thursday, February 27, 2014 / Proposed Rules 

July 12, 2007); AD 2008–25–02, 

Amendment 39–15760 (73 FR 75307, 

December 11, 2008); AD 2010–04–09, 

Amendment 39–16202 (75 FR 7940, 

February 23, 2010; corrected March 3, 

2010 (75 FR 9515)); AD 2011–01–02, 

Amendment 39–16555 (76 FR 432, 

January 5, 2011); AD 2012–16–05, 

Amendment 39–17152 (77 FR 48425, 

August 14, 2012); and 

■ b. Adding the following new AD: 

Airbus: Docket No. FAA–2014–0060; 

Directorate Identifier 2012–NM–194–AD. 

(a) Comments Due Date 

We must receive comments by April 14, 

2014. 

(b) Affected ADs 

This AD supersedes the ADs specified in 

paragraphs (b)(1) through (b)(6) of this AD. 

(1) AD 2006–21–08, Amendment 39–14793 

(71 FR 61639, October 19, 2006). 

(2) AD 2007–14–01, Amendment 39–15123 

(72 FR 38006, July 12, 2007). 

(3) AD 2008–25–02, Amendment 39–15760 

(73 FR 75307, December 11, 2008). 

(4) AD 2010–04–09, Amendment 39–16202 

(75 FR 7940, February 23, 2010; corrected 

March 3, 2010 (75 FR 9515)). 

(5) AD 2011–01–02, Amendment 39–16555 

(76 FR 432, January 5, 2011). 

(6) AD 2012–16–05, Amendment 39–17152 

(77 FR 48425, August 14, 2012). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –223F, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes, certificated in any 

category, all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by a determination 

that more restrictive maintenance 

requirements and airworthiness limitations 

are necessary. We are issuing this AD to 

prevent the potential of ignition sources 

inside fuel tanks, which, in combination with 

flammable fuel vapors, could result in fuel 

tank explosions and consequent loss of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance Program Revision and 

Airworthiness Limitations Compliance 

(1) Within 3 months after the effective date 

of this AD, revise the maintenance or 

inspection program, as applicable, by 

incorporating Airbus A330 Airworthiness 

Limitations Section (ALS) Part 5—Fuel 

Airworthiness Limitations, dated November 

16, 2011. 

(2) Comply with all applicable instructions 

and airworthiness limitations included in 

Airbus A330 ALS Part 5—Fuel Airworthiness 

Limitations, dated November 16, 2011. The 

initial compliance times for the actions 

specified in Airbus A330 ALS Part 5—Fuel 

Airworthiness Limitations, dated November 

16, 2011, are at the later of the times 

specified in paragraphs (g)(2)(i) and (g)(2)(ii) 

of this AD, except as required by paragraphs 

(h) and (i) of this AD. 

(i) Within the applicable compliance times 

specified in Airbus A330 ALS Part 5—Fuel 

Airworthiness Limitations, dated November 

16, 2011. 

(ii) Within 3 months after accomplishing 

the actions required by paragraph (g)(1) of 

this AD. 

(h) Exceptions to Compliance Times for 

Design Changes 

(1) For type design changes specified in 

‘‘Sub-part 5–2 Changes to Type Design,’’ of 

Airbus A330 ALS Part 5—Fuel Airworthiness 

Limitations, dated November 16, 2011, the 

compliance times are defined as 

‘‘Embodiment Limits,’’ except as defined in 

paragraph (h)(2) of this AD. 

(2) Where Airbus A330 ALS Part 5—Fuel 

Airworthiness Limitations, dated November 

16, 2011, specifies a compliance time based 

on a calendar date for modifying the control 

circuit for the fuel pump of the center fuel 

tank (installing ground fault interrupters to 

the center tank fuel pump control circuit), 

the compliance date is September 18, 2016 

(48 months after the effective date of AD 

2012–16–05, Amendment 39–17152 (77 FR 

48425, August 14, 2012)). 

(i) No Alternative Actions, Intervals, or 

Critical Design Configuration Control 

Limitations (CDCCLs) 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections), intervals, or 

CDCCLs may be used; except as specified in 

paragraphs (h) and (i) of this AD; or unless 

the actions, intervals, or CDCCLs are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j)(1) of 

this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval, as applicable). You are required to 

ensure the product is airworthy before it is 

returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0168, dated August 31, 2012; 

for related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0060. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager. Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04258 Filed 2–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0120; Directorate 

Identifier 2013–NM–056–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–215–6B11 

(CL–215T Variant), and CL–215–6B11 

(CL–415 Variant) airplanes. This 

proposed AD was prompted by several 

reports indicating that shorter nacelle 

strut bushings were inadvertently 

installed on certain airplanes. This 

proposed AD would require a general 

visual inspection of the left and right 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS