66762 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 

manufacturer, the part number, and the serial 

number of the left-hand (LH) and right-hand 

(RH) windshields installed on the airplane, 

in accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information identified in paragraph (g)(1), 

(g)(2), or (g)(3) of this AD. A review of 

airplane delivery or maintenance records is 

acceptable in lieu of this inspection if the 

manufacturer, part number, and serial 

number of the installed windshields can be 

conclusively determined from that review. 

(1) For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes: 

Airbus Service Bulletin A330–56–3009, 

Revision 01, including Appendix 01, 

excluding Appendices 02 and 03, dated 

January 27, 2011. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–56–4008, including Appendix 

01, excluding Appendices 02 and 03, dated 

May 4, 2010. 

(3) For Model A340–541 and –642 

airplanes: Airbus Service Bulletin A340–56– 

5002, including Appendix 01, excluding 

Appendices 02 and 03, dated May 4, 2010. 

(h) Replacement 

If it is found during the inspection required 

by paragraph (g) of this AD that any installed 

LH or RH windshield was manufactured by 

Saint-Gobain Sully (SGS) and the part 

number and serial number are identified in 

the applicable Airbus service information 

identified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD: Within 9 months or 1,200 flight 

hours after the effective date of this AD, 

whichever occurs first, replace all affected 

LH and RH windshields, in accordance with 

the Accomplishment Instructions of the 

applicable Airbus service information 

identified in paragraph (h)(1), (h)(2), or (h)(3) 

of this AD. 

(1) For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes: 

Airbus Service Bulletin A330–56–3009, 

Revision 01, including Appendix 01, 

excluding Appendices 02 and 03, dated 

January 27, 2011. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–56–4008, including Appendix 

01, excluding Appendices 02 and 03, dated 

May 4, 2010. 

(3) For Model A340–541 and –642 

airplanes: Airbus Service Bulletin A340–56– 

5002, including Appendix 01, excluding 

Appendices 02 and 03, dated May 4, 2010. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD for Model A330–201, –202, –203, 

–223, –223F, –243, –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A330–56–3009, 

dated May 4, 2010, which is not incorporated 

by reference in this AD. 

(j) Parts Installation Limitation 

As of the effective date of this AD, do not 

install on an airplane any affected 

windshield from SGS and having a part 

number and serial number as identified in 

the applicable service information identified 

in paragraphs (j)(1), (j)(2), and (j)(3) of this 

AD, unless a suffix ‘‘U’’ is present at the end 

of the S/N. 

(1) For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes: 

Airbus Service Bulletin A330–56–3009, 

Revision 01, including Appendix 01, 

excluding Appendices 02 and 03, dated 

January 27, 2011. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–56–4008, including Appendix 

01, excluding Appendices 02 and 03, dated 

May 4, 2010. 

(3) For Model A340–541 and –642 

airplanes: Airbus Service Bulletin A340–56– 

5002, including Appendix 01, excluding 

Appendices 02 and 03, dated May 4, 2010. 

(k) 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 or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(l) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0242, dated December 19, 2011 (corrected 

February 15, 2012), and the service 

information identified in paragraphs (k)(1)(i) 

through (k)(1)(iii) of this AD, for related 

information. 

(i) Airbus Service Bulletin A330-56–3009, 

Revision 01, including Appendix 01, 

excluding Appendices 02 and 03, dated 

January 27, 2011. 

(ii) Airbus Service Bulletin A340–56–4008, 

including Appendix 01, excluding 

Appendices 02 and 03, dated May 4, 2010. 

(iii) Airbus Service Bulletin A340–56– 

5002, including Appendix 01, excluding 

Appendices 02 and 03, dated May 4, 2010. 

(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 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on October 

31, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27142 Filed 11–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1159; Directorate 

Identifier 2012–NM–028–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Airbus Model A310–203, –204, –222, 

–304, –322, and –324 airplanes. This 

proposed AD was prompted by a design 

review of the fuel tank access covers 

and analyses comparing compliance of 

the access covers to different tire burst 

models. ‘Type 21’ panels located within 

the debris zone revealed that they could 

not sustain the impact of the tire debris. 

This proposed AD would require 

modifying the wing manhole surrounds 

and replacing certain fuel access panels. 

We are proposing this AD to prevent a 

possibility of a fire due to tire debris 

impact on the fuel access panels. 

DATES: We must receive comments on 

this proposed AD by December 24, 

2012. 

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– 


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Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 66763 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, 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— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

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

may review copies of the 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; or in person at the 

Docket Operations office 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2125; 

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–2012–1159; Directorate Identifier 

2012–NM–028–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0016, 

dated January 26, 2012 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Following a design review of the fuel tank 

access covers and further analyses aiming at 

comparing compliance of the access covers to 

different tyre burst models, panels ‘Type 21’ 

revealed to be a matter of concern when 

located within the tyre debris zone. It has 

been demonstrated that ’‘Type 21’ Super 

Plastic Formed (SPF) panels for fuel access, 

installed on left hand (LH) and right hand 

(RH) wings at manhole positions No. 1 and 

No. 2 of A310 aeroplanes pre-MSN500 could 

not sustain in an acceptable manner the 

impact of tyre debris. 

This condition, if not corrected, could 

result, following tyre debris impact, in fuel 

leaking and consequently fire on that area of 

the aeroplane. 

For the reasons described above, this 

[EASA] AD requires the replacement of SPF 

‘Type 21’ access panels with [type 11 access 

panels with]‘Type 11A’ [associated clamp 

plates] or ‘Type 21R’ access panels and 

concurrent modification of the manhole 

surrounds at positions No.1 and No.2 to 

prevent re-installation of ‘’Type 21’ panels at 

those positions. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A310–57–2033, dated July 15, 1989, and 

Mandatory Service Bulletin A310–57– 

2097, Revision 01, dated September 29, 

2011. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

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 the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 56 products of U.S. registry. 

We also estimate that it would take 

about 40 work-hours 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 $6,340 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$545,440, or $9,740 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 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, 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
66764 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 adding 

the following new AD: 

Airbus: Docket No. FAA–2012–1159; 

Directorate Identifier 2012–NM–028–AD. 

(a) Comments Due Date 

We must receive comments by December 

24, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –204, –222, –304, –322, and –324 

airplanes, certificated in any category, 

manufacturer serial numbers 0378, 0392, 

0399, 0404, 0406, 0407, 0409, 0410, 0412, 

0413, 0416, 0418, 0419, 0421, 0422, 0424, 

0425, 0427, 0428, 0429, 0431, 0432, 0434 to 

0437 inclusive, 0439, 0440, 0441, 0443 to 

0449 inclusive, 0451 to 0454 inclusive, 0456, 

0457, 0458, 0467, 0472, 0473, 0475, 0476, 

0478, 0480 to 0485 inclusive, and 0487 to 

0499 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a design review 

of the fuel tank access covers and analyses 

comparing compliance of the access covers to 

different tire burst models. ‘Type 21’ panels 

located within the debris zone revealed that 

they could not sustain the impact of the tire 

debris. We are proposing this AD to prevent 

a possibility of a fire due to tire debris impact 

on the fuel access panels. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Actions 

Within 60 months after the effective date 

of this AD, do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(1) Modify the wing manhole surrounds 

and replace the super plastic formed (SPF) 

‘Type 21’ fuel access panels at positions 1 

and 2 on the left- and right-hand wings with 

‘Type 11’ fuel access panels with associated 

‘Type 11A’ clamp plates, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2097, 

Revision 01, dated September 29, 2011. 

(2) Modify the wing manhole surrounds 

and replace the SPF ‘Type 21’ fuel access 

panels at positions 1 and 2 on the left- and 

right-hand wings with ‘Type 21R’ fuel access 

panels, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2033, dated July 

15, 1989. 

(h) Parts Installation Prohibition 

After accomplishing the modification 

required by paragraph (g) of this AD, no 

person may install SPF ‘Type 21’ fuel access 

panels at positions 1 and 2 on the left- and 

right-hand wings, on any airplane. 

(i) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2125; 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 or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2012– 

0016, dated January 26, 2012, and the service 

information specified in paragraphs (j)(1)(i) 

and (j)(1)(ii) of this AD, for related 

information. 

(i) Airbus Service Bulletin A310–57–2033, 

dated July 15, 1989. 

(ii) Airbus Mandatory Service Bulletin 

A310–57–2097, Revision 01, dated 

September 29, 2011. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. You may review copies of 

the 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. 

Issued in Renton, Washington, on October 

30, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27124 Filed 11–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1160; Directorate 

Identifier 2012–NM–096–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Model A330–200, –300 and –200 

Freighter series airplanes; and all Model 

A340–200 and –300 series airplanes. 

This proposed AD was prompted by a 

determination that the bonding lead 

from a certain isolation valve to a frame 

was too close to an electrical harness, 

which might cause chafing between the 

electrical harness and the associated 

bonding lead. This chafing could lead to 

a short circuit of the isolation valve and 

consequent non-closure of the isolation 

valve, which would prevent the air-flow 

to be shut-off in case of fire. This 

proposed AD would require modifying 

the bonding lead installation of the 

isolation valve. We are proposing this 

AD to prevent such chafing, which 

could result in non-closure of the 

isolation valve in the event of a fire and 

consequent damage to the airplane and 

injury to its occupants. 

DATES: We must receive comments on 

this proposed AD by December 24, 

2012. 


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