Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Proposed Rules 15867 

Special Attention Service Bulletin 737–78– 

1083, dated June 30, 2010. 

Repetitive Inspections and Corrective 

Actions 

(l) For Group 1 airplanes, as identified in 

Boeing Special Attention Service Bulletin 

737–78–1083, dated June 30, 2010: Within 

7,500 flight hours after accomplishing the 

requirements of paragraph (g) of this AD, do 

the actions specified in paragraphs (l)(1), 

(l)(2), (l)(3), and (l)(4) of this AD. Repeat the 

actions thereafter at intervals not to exceed 

7,500 flight hours. 

(1) Do a detailed inspection for tears, holes, 

and disbonds of the wear spacer, in 

accordance with Appendix A of Boeing 

Special Attention Service Bulletin 737–78– 

1083, dated June 30, 2010. If any tear, hole, 

or disbond is found, before further flight, 

replace the spacer with a new spacer, in 

accordance with Appendix A of Boeing 

Special Attention Service Bulletin 737–78– 

1083, dated June 30, 2010. 

(2) Measure the thickness of the wear 

spacer in accordance with Appendix A of 

Boeing Special Attention Service Bulletin 

737–78–1083, dated June 30, 2010. If the 

thickness is less than 0.020 inch, before 

further flight, replace the spacer with a new 

spacer, in accordance with Appendix A of 

Boeing Special Attention Service Bulletin 

737–78–1083, dated June 30, 2010. 

(3) Do a detailed inspection for surface 

damage of the attach fitting, in accordance 

with Appendix A of Boeing Special Attention 

Service Bulletin 737–78–1083, dated June 30, 

2010. 

(i) If the surface damage is less than 0.005 

inch depth, before further flight, repair the 

attach fitting, in accordance with Appendix 

A of Boeing Special Attention Service 

Bulletin 737–78–1083, dated June 30, 2010. 

(ii) If the surface damage is 0.005 inch or 

greater in depth, before further flight, replace 

the attach fitting with a new attach fitting, in 

accordance with Appendix B of Boeing 

Special Attention Service Bulletin 737–78– 

1083, dated June 30, 2010. 

(4) Do a general visual inspection for 

damage (i.e. wear, missing, cracked, or bent 

parts) of the rod end, attach bolt, and nut, in 

accordance with Appendix A of Boeing 

Special Attention Service Bulletin 737–78– 

1083, dated June 30, 2010. If any damage is 

found, before further flight, replace the 

affected part with a new part in accordance 

with a method approved by the Manager, 

Seattle Aircraft Certification Office (ACO), 

FAA. 

Group 2 Inspection and Repair 

(m) For Group 2 airplanes, as identified in 

Boeing Special Attention Service Bulletin 

737–78–1083, dated June 30, 2010: Within 12 

months after the effective date of this AD, 

perform the actions required in paragraph (l) 

of this AD. Repeat the actions thereafter at 

intervals not to exceed 7,500 flight hours. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Seattle Aircraft 

Certification Office, 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be e-mailed to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

Related Information 

(o) For more information about this AD, 

contact Chris R. Parker, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue, SW., Renton, Washington 

98057–3356; phone: 425–917–6496; fax: 425– 

917–6590; e-mail: Chris.R.Parker@faa.gov. 

(p) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; phone: 

206–544–5000, extension 1; fax: 206–766– 

5680;e-mail: me.boecom@boeing.com; 

Internet:https://www.myboeingfleet.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, the FAA, 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 March 

14, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–6613 Filed 3–21–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0224; Directorate 

Identifier 2010–NM–210–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

* * * * * 

The airworthiness limitations applicable to 

Damage Tolerant Airworthiness Limitation 

Items (DT ALI) are currently given in Airbus 

A330 ALI Document reference AI/SE–M4/ 

95A.0089/97, which is approved by the 

European Aviation Safety Agency (EASA) 

and referenced in Airbus Airworthiness 

Limitations Section (ALS) Part 2. 

The issue 17 of Airbus A330 ALI 

Document introduces more restrictive 

maintenance requirements/airworthiness 

limitations. Failure to comply with this issue 

constitutes an unsafe condition. 

This [EASA] AD supersedes EASA AD 

2009–0102 [and retains the requirements 

therein], and requires the implementation of 

the new or more restrictive maintenance 

requirements/airworthiness limitations as 

specified in Airbus A330 ALI Document 

issue 17. 

The unsafe condition is fatigue cracking, 

damage, and corrosion in certain 

structure, which could result in reduced 

structural integrity of the airplane. The 

proposed AD would require actions that 

are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 6, 2011. 

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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–40, 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— 

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, e-mail 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 


srobinson on DSKHWCL6B1PROD with PROPOSALS
15868 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Proposed Rules 

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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 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–2011–0224; Directorate Identifier 

2010–NM–210–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 April 20, 2006, we issued AD 

2006–09–07, Amendment 39–14577 (71 

FR 25919, May 3, 2006). That AD 

requires actions intended to address an 

unsafe condition on A330–200 and –300 

series airplanes, A340–200 and –300 

series airplanes, and A340–541 and 

–642 airplanes. 

Since we issued AD 2006–09–07, 

Airbus has revised certain A330 Damage 

tolerant airworthiness limitations items 

to include more restrictive maintenance 

requirements/airworthiness limitations. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0174, 

dated August 17, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

The airworthiness limitations are 

distributed in the Airbus A330 Airworthiness 

Limitations Section (ALS). 

The airworthiness limitations applicable to 

Damage Tolerant Airworthiness Limitation 

Items (DT ALI) are currently given in Airbus 

A330 ALI Document reference AI/SE–M4/ 

95A.0089/97, which is approved by the 

European Aviation Safety Agency (EASA) 

and referenced in Airbus Airworthiness 

Limitations Section (ALS) Part 2. 

The issue 17 of Airbus A330 ALI 

Document introduces more restrictive 

maintenance requirements/airworthiness 

limitations. Failure to comply with this issue 

constitutes an unsafe condition. 

This [EASA] AD supersedes EASA AD 

2009–0102 [and retains the requirements 

therein], and requires the implementation of 

the new or more restrictive maintenance 

requirements/airworthiness limitations as 

specified in Airbus A330 ALI Document 

issue 17. 

The unsafe condition is fatigue cracking, 

damage, and corrosion in certain 

structure, which could result in reduced 

structural integrity of the airplane. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Document AI/SE– 

M4/95A.0089/97, ‘‘A330 Airworthiness 

Limitation Items,’’ Issue 17, dated May 

28, 2010. This document provides each 

mandatory time for maintenance tasks, 

structural inspection interval, and 

related structural inspection procedures. 

Related Rulemaking 

On February 3, 2011, we issued AD 

2011–04–05, Amendment 39–16605 (76 

FR 8612, February 15, 2011), for Airbus 

Model A340–200, –300, –500, and –600 

series airplanes, to require revising the 

maintenance program. Doing this 

revision terminates the requirements of 

AD 2006–09–07 for the Model A340 

airplanes. 

We are also considering issuance of 

another NPRM related to this NPRM. 

The NPRM we are considering, 

Directorate Identifier 2010–NM–211– 

AD, would restate the requirements of 

paragraph (f)(2) of AD 2006–09–07 for 

Model A330 airplanes. 

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. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 54 products of U.S. registry. 

The actions that are required by AD 

2006–09–07, and retained in this 

proposed AD, take about 1 work-hour 

per product, at an average labor rate of 

$85 per work hour. Based on these 

figures, the estimated cost of the 

currently required actions is $85 per 

product. 

We estimate that it would take about 

1 work-hour per product to comply with 

the requirements of this proposed AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of the proposed AD on 

U.S. operators to be $4,590, 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 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. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Proposed Rules 15869 

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); and 

3. 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. 

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 

removing Amendment 39–14577 (71 FR 

25919, May 3, 2006) and adding the 

following new AD: 

Airbus: Docket No. FAA–2011–0224; 

Directorate Identifier 2010–NM–210–AD. 

Comments Due Date 

(a) We must receive comments by May 6, 

2011. 

Affected ADs 

(b) This AD supersedes AD 2006–09–07, 

Amendment 39–14577. 

Applicability 

(c) This AD applies to Airbus Model A330– 

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

–243F airplanes, and Model A330–301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

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

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 05. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * * * 

The airworthiness limitations applicable to 

Damage Tolerant Airworthiness Limitation 

Items (DT ALI) are currently given in Airbus 

A330 ALI Document reference AI/SE–M4/ 

95A.0089/97, which is approved by the 

European Aviation Safety Agency (EASA) 

and referenced in Airbus Airworthiness 

Limitations Section (ALS) Part 2. 

The issue 17 of Airbus A330 ALI 

Document introduces more restrictive 

maintenance requirements/airworthiness 

limitations. Failure to comply with this issue 

constitutes an unsafe condition. 

This [EASA] AD supersedes EASA AD 

2009–0102 [and retains the requirements 

therein], and requires the implementation of 

the new or more restrictive maintenance 

requirements/airworthiness limitations as 

specified in Airbus A330 ALI Document 

issue 17. 

The unsafe condition is fatigue cracking, 

damage, and corrosion in certain structure, 

which could result in reduced structural 

integrity of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of Paragraph 

(F)(2) of AD 2006–09–07 

Airworthiness Limitations Revision 

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

–243, –301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes: Within 3 

months after June 7, 2006 (the effective date 

of AD 2006–09–07), revise the ALS of the 

Instructions for Continued Airworthiness by 

incorporating Airbus Document AI/SE–M4/ 

95A.0089/97, ‘‘A330 Airworthiness 

Limitation Items,’’ Issue 12, dated November 

1, 2003, as specified in Section 9–2 of the 

Airbus A330 Maintenance Planning 

Document (MPD), into the ALS. 

New Requirements of This AD 

Revise the Maintenance Program 

(h) Within 3 months after the effective date 

of this AD: Revise the maintenance program 

by incorporating Airbus Document AI/SE– 

M4/95A.0089/97, ‘‘A330 Airworthiness 

Limitation Items,’’ Issue 17, dated May 28, 

2010. At the times specified in Airbus 

Document AI/SE–M4/95A.0089/97, ‘‘A330 

Airworthiness Limitation Items,’’ Issue 17, 

dated May 28, 2010, comply with all 

applicable maintenance requirements and 

associated airworthiness limitations included 

in Airbus Document AI/SE–M4/95A.0089/97, 

‘‘A330 Airworthiness Limitation Items,’’ Issue 

17, dated May 28, 2010. Accomplishing the 

revision in this paragraph ends the 

requirements in paragraph (g) of this AD. 

Alternative Intervals or Limits 

(i) Except as provided by paragraph (j)(1) 

of this AD, after accomplishing the actions 

specified in paragraph (h) of this AD, no 

alternatives to the maintenance tasks, 

intervals, or limitations specified in 

paragraph (h) of this AD may be used. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

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, Washington 98057– 

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

227–1149. Information may be e-mailed 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. 

Related Information 

(k) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2010–0174, dated 

August 17, 2010; Airbus Document AI/SE– 

M4/95A.0089/97, ‘‘A330 Airworthiness 

Limitation Items,’’ Issue 12, dated November 

1, 2003; and Airbus Document AI/SE–M4/ 

95A.0089/97, ‘‘A330 Airworthiness 

Limitation Items,’’ Issue 17, dated May 28, 

2010; for related information. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
15870 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Proposed Rules 

Issued in Renton, Washington, on March 

14, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–6643 Filed 3–21–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0255; Directorate 

Identifier 2010–NM–253–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes, and Airbus 

Model A300 B4–600, B4–600R, and F4– 

600R Series Airplanes, and Model C4– 

605R Variant F Airplanes (Collectively 

Called A300–600 Series Airplanes) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

An operator reported several cases of wire 

damages at the pylon/wing interface. 

Analysis revealed that wires damages are due 

to installation quality issue resulting from 

lack of information in installation drawings 

and job cards. 

Moreover detailed analysis has highlighted 

that the Low Pressure Valve (LPV) wires were 

not segregated by design. 

* * * * * 

If left uncorrected, the wire chafing could 

impact fire protection and detection system. 

It may also induce dormant failure on LPV 

preventing its closure leading to a permanent 

and uncontrolled fire (in case of fire ignited 

upstream the High Pressure Valve (HPV)). 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 6, 2011. 

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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–40, 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; e-mail 

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, Washington. 

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, 

Washington 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–2011–0255; Directorate Identifier 

2010–NM–253–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 2010–0178, 

dated August 23, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

An operator reported several cases of wire 

damages at the pylon/wing interface. 

Analysis revealed that wires damages are due 

to installation quality issue resulting from 

lack of information in installation drawings 

and job cards. 

Moreover detailed analysis has highlighted 

that the Low Pressure Valve (LPV) wires were 

not segregated by design. 

Due to design similarities, A310, A300–600 

and A300–600ST aeroplanes can be affected, 

depending on the wires installation in the 

concerned area. 

If left uncorrected, the wire chafing could 

impact fire protection and detection system. 

It may also induce dormant failure on LPV 

preventing its closure leading to a permanent 

and uncontrolled fire (in case of fire ignited 

upstream the High Pressure Valve (HPV)). 

For the reasons explained above, this AD 

requires the modification of the electrical 

installation in the pylon/wing interface to 

avoid wire damages. 

The modification includes a general 

visual inspection of wires for damage. 

and repair if necessary. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–24–6106, including 

Appendix 01, dated March 31, 2010; 

and Mandatory Service Bulletin A310– 

24–2106, including Appendix 01, dated 

May 27, 2010. 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 


srobinson on DSKHWCL6B1PROD with PROPOSALS