19714 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 

Compliance Time for AWL No. 28–AWL–03 

(m) The initial compliance time for AWL 

No. 28–AWL–03 of Boeing TR 09–010, dated 

July 2010, to Section 9 of Boeing 757 MPD 

Document, D622N001–9, is within 120 

months since the date of issuance of the 

original standard airworthiness certificate or 

the date of issuance of the original export 

certificate of airworthiness, or within 24 

months after the effective date of this AD, 

whichever occurs later. Accomplishing the 

actions required by this paragraph terminates 

the requirements of paragraph (h)(2) of this 

AD. 

Initial Inspection Compliance Times for 

AWL No. 28–AWL–25 and 28–AWL–26 

(n) The initial inspection compliance time 

for AWL No. 28–AWL–25 of Boeing TR 09– 

010, dated July 2010, to Section 9 of Boeing 

757 MPD Document, D622N001–9, is within 

72 months after accomplishing Boeing 

Service Bulletin 757–28A0088. 

(o) The initial inspection compliance time 

for AWL No. 28–AWL–26 of Boeing TR 09– 

010, dated July 2010, to Section 9 of Boeing 

757 MPD Document, D622N001–9, is within 

12 months after accomplishing Boeing 

Service Bulletin 757–28A0105. 

No Alternative Inspections, Inspection 

Intervals, or CDCCLs 

(p) After accomplishing the actions 

specified in paragraph (l) of this AD, no 

alternative inspections, inspection intervals, 

or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (u) of 

this AD. 

Terminating Action for AD 2008–11–07, 

Amendment 39–15529 

(q) Incorporating AWLs No. 28–AWL–20 

and No. 28–AWL–26 into the maintenance 

program in accordance with paragraph (l)(3) 

of this AD terminates the actions required by 

paragraphs (j) and (m) of AD 2008–11–07. 

Terminating Action for AD 2009–06–20, 

Amendment 39–15857 

(r) Incorporating AWL No. 28–AWL–22 

into the maintenance program in accordance 

with paragraph (l)(3) of this AD terminates 

the actions required by paragraph (h) of AD 

2009–06–20. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(s) Actions done before the effective date 

of this AD in accordance with Section 9 of 

the Boeing 757 MPD Document, D622N001– 

9, Revision December 2008, is acceptable for 

compliance with the corresponding 

requirements of this AD. 

(t) Actions done before the effective date of 

this AD in accordance with Subsection G of 

Boeing TR 09–008, dated March 2008, to 

Section 9 of the Boeing 757 MPD Document, 

D622N001–9, is acceptable for compliance 

with the requirements of paragraphs (n) and 

(o) of this AD. 

Explanation of CDCCL Requirements 

Note 4: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the 

maintenance program, as required by 

paragraphs (g) and (l) of this AD, do not need 

to be reworked in accordance with the 

CDCCLs. However, once the maintenance 

program has been revised, future 

maintenance actions on these components 

must be done in accordance with the 

CDCCLs. 

Alternative Methods of Compliance 

(AMOCs) 

(u)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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. 

(3) AMOCs approved previously for AD 

2008–10–11 are approved as AMOCs for the 

corresponding provisions of this AD. 

Related Information 

(v) For more information about this AD, 

contact Tak Kobayashi, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6499; fax: 425–917–6590; e-mail: 

takahisa.kobayashi@faa.gov. 

(w) 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; telephone 

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, 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 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–8407 Filed 4–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0305; Directorate 

Identifier 2010–NM–186–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320–214, –232, and –233 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: 

* * * * * 

Results from a design review done by 

AIRBUS for documentation update have 

revealed that, on post-mod 38310 A320 

aeroplanes only, in case of emergency 

electrical configuration combined with a 

Green and Yellow hydraulic system loss, 

during landing phase (nose landing gear 

extended), the roll control would only be 

provided by the left aileron. 

This condition, if not corrected, could lead 

to an asymmetrical landing configuration, 

resulting in reduced control of the aeroplane. 

* * * * * 

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 23, 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, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

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Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 19715 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; 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–2011–0305; Directorate Identifier 

2010–NM–186–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 2010–0149, 

dated July 21, 2010 (referred to after this 

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

condition for the specified products. 

The MCAI states: 

In 2007, Airbus modification 38310 was 

introduced in production to simplify the 

ELAC2 [elevator aileron computer] and 

Trimmable Horizontal Stabiliser (THS) Motor 

1 stand by power supply logic. 

Results from a design review done by 

AIRBUS for documentation update have 

revealed that, on post-mod 38310 A320 

aeroplanes only, in case of emergency 

electrical configuration combined with a 

Green and Yellow hydraulic system loss, 

during landing phase (nose landing gear 

extended), the roll control would only be 

provided by the left aileron. 

This condition, if not corrected, could lead 

to an asymmetrical landing configuration, 

resulting in reduced control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires a modification of the 

electrical installation of ELAC2 and THS 

Motor 1 power supply, restoring the 

aeroplane to the pre-mod 38310 

configuration. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A320–27–1199, Revision 02, 

including Appendix 01, dated 

September 20, 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 

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 666 products of U.S. 

registry. We also estimate that it would 

take about 35 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 $3,370 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 costs. 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 

$4,225,770, or $6,345 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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

19716 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 

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–2011–0305; 

Directorate Identifier 2010–NM–186–AD. 

Comments Due Date 

(a) We must receive comments by May 23, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A320– 

214, -232, and -233 airplanes, all 

manufacturer serial numbers on which 

Airbus modification 38310 has been 

accomplished in production; certificated in 

any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * * * 

Results from a design review done by 

AIRBUS for documentation update have 

revealed that, on post-mod 38310 A320 

aeroplanes only, in case of emergency 

electrical configuration combined with a 

Green and Yellow hydraulic system loss, 

during landing phase (nose landing gear 

extended), the roll control would only be 

provided by the left aileron. 

This condition, if not corrected, could lead 

to an asymmetrical landing configuration, 

resulting in reduced control of the aeroplane. 

* * * * * 

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. 

Actions 

(g) Within 24 months after the effective 

date of this AD, modify the electrical 

installation of the elevator aileron computer 

and trimmable horizontal stabilizer motor 1 

power supply, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–27–1199, 

Revision 02, dated September 20, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Modifications done before the effective 

date of this AD in accordance with Airbus 

Service Bulletin A320–27–1199, Revision 01, 

dated March 4, 2010, are acceptable for 

compliance with the requirements of 

paragraph (g) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) 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, sent it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; 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 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. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2010–0149, dated July 21, 2010; and Airbus 

Mandatory Service Bulletin A320–27–1199, 

Revision 02, dated September 20, 2010; for 

related information. 

Issued in Renton, Washington, on March 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–8409 Filed 4–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0306; Directorate 

Identifier 2010–NM–176–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (Operations) Limited Model 

4101 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: 

* * * BAE Systems (Operations) Ltd has 

issued Revision 33 of the AMM [airplane 

maintenance manual] to amend Chapter 05– 

10–10 by adding one new Structurally 

Significant Item (SSI) and increasing the 

repeat inspection period on another SSI. 

Failure to comply with this revision 

constitutes an unsafe condition. 

The unsafe condition is failure of 

certain structurally significant items, 

including the main landing gear and the 

nose landing gear, which could result in 

reduced structural integrity of the 

airplane; and fuel vapor ignition 

sources, which could result in a fuel 

tank explosion and consequent loss 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 23, 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– 

mstockstill on DSKH9S0YB1PROD with PROPOSALS