Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 32057 

necessary to ensure a manufacturer’s 

compliance with the rules of this part, 

part 430, or part 431, a manufacturer 

must base its certification of a basic 

model under subpart B of this part on 

independent, third-party laboratory 

testing. 

(b) If DOE determines that a 

manufacturer has used an AEDM to 

certify compliance and either has 

willfully certified the product at an 

unsupported rating or has distributed 

multiple, non-compliant basic models 

in commerce as a result of a faulty 

AEDM, DOE may prohibit continued 

use of an AEDM and require the 

manufacturer to base its certifications of 

compliance on physical testing of each 

basic model. 

PART 430—ENERGY CONSERVATION 

PROGRAM FOR CONSUMER 

PRODUCTS 

15. The authority citation for part 430 

continues to read as follows: 

Authority: 42 U.S.C. 6291–6309; 28 U.S.C. 

2461 note. 

§ 430.2 [Amended] 

16. Section 430.2 is amended by 

removing the definition of ‘‘ARM/ 

simulation adjustment factor’’. 

PART 431—ENERGY EFFICIENCY 

PROGRAM FOR CERTAIN 

COMMERCIAL AND INDUSTRIAL 

EQUIPMENT 

17. The authority citation for part 431 

continues to read as follows: 

Authority: 42 U.S.C. 6291–6317. 

18. Section 431.2 is amended by 

revising the definition of ‘‘alternative 

efficiency determination method or 

AEDM’’ to read as follows: 

§ 431.2 Definitions. 

* * * * * 

Alternative Efficiency Determination 

Method or AEDM is a simulation, 

calculation or engineering algorithm for 

determining the efficiency or 

consumption of a basic model of 

consumer product or commercial 

equipment, in terms of the appropriate 

descriptor used in or under section 325 

or 342(a) of the Act to state the standard 

for that product. 

* * * * * 

19. Section 431.17 is amended by 

revising paragraph (a) to read as follows: 

§ 431.17 Determination of efficiency. 

* * * * * 

(a) Provisions applicable to all electric 

motors— (1) General requirements. The 

average full load efficiency of each basic 

model of electric motor must be 

determined either by testing in 

accordance with § 431.16 of this 

subpart, or by application of an 

alternative efficiency determination 

method (AEDM) that meets the 

requirements of § 429.70, provided, 

however, that an AEDM may be used to 

determine the average full load 

efficiency of one or more of a 

manufacturer’s basic models only if the 

average full load efficiency of at least 

five of its other basic models is 

determined through testing. 

(2) Alternative efficiency 

determination method. An AEDM 

applied to a basic model must comply 

with § 429.70. 

(3) Use of a certification program or 

accredited laboratory. (i) A 

manufacturer may have a certification 

program, that DOE has classified as 

nationally recognized under § 431.20, 

certify the nominal full load efficiency 

of a basic model of electric motor, and 

issue a certificate of conformity for the 

motor. 

(ii) For each basic model for which a 

certification program is not used as 

described in paragraph (a)(3)(i) of this 

section, any testing of the motor 

pursuant to paragraphs (a)(1) through (2) 

of this section to determine its energy 

efficiency must be carried out in 

accordance with paragraph (b) of this 

section, in an accredited laboratory that 

meets the requirements of § 431.18. 

(This includes testing of the basic 

model, pursuant to § 429.70, to 

substantiate an AEDM.) 

* * * * * 

§ 431.442 [Amended] 

20. Section 431.442 is revised by 

removing the definition of ‘‘Alternative 

efficiency determination method’’. 

* * * * * 

21. Section 431.445 is amended by: 

a. Revising paragraph (b); and 

b. Removing paragraph (c). 

§ 431.445 Determination of small electric 

motor efficiency. 

* * * * * 

(b) Provisions applicable to all small 

electric motors—(1) General 

requirements. The average full load 

efficiency of each basic model of electric 

motor must be determined either by 

testing in accordance with § 431.444 of 

this subpart, or by application of an 

alternative efficiency determination 

method (AEDM) that meets the 

requirements of § 429.70, provided, 

however, that an AEDM may be used to 

determine the average full load 

efficiency of one or more of a 

manufacturer’s basic models only if the 

average full load efficiency of at least 

five of its other basic models is 

determined through testing. 

(2) Alternative efficiency 

determination method. To use an AEDM 

to rate a basic model, the AEDM must 

comply with § 429.70. 

[FR Doc. 2012–13108 Filed 5–30–12; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0497; Directorate 

Identifier 2011–NM–140–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 777–200, –200LR, 

–300, and –300ER series airplanes. The 

existing AD currently requires 

inspecting for scribe lines in the skin 

along lap joints, butt joints, certain 

external doublers, and the large cargo 

door hinges, and related investigative 

and corrective actions if necessary. 

Since we issued that AD, we have 

determined that scribe lines could occur 

where external decals are installed or 

removed across lap joints, large cargo 

door hinges, or external doublers. This 

proposed AD would add inspecting for 

scribe lines where external decals have 

been applied or removed across lap 

joints, large cargo door hinges, and 

external doublers, and related 

investigative and corrective actions if 

necessary. We are proposing this AD to 

detect and correct scribe lines which 

can develop into fatigue cracks in the 

skin. Undetected fatigue cracks can 

grow and cause sudden decompression 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 16, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 

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32058 Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 

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 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; email: 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

Berhane.Alazar@faa.gov. 

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–2012–0497; Directorate Identifier 

2011–NM–140–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 because of 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 November 12, 2009, we issued AD 

2009–24–08, Amendment 39–16096 (74 

FR 62217, November 27, 2009), for 

certain Model 777–200, –200LR, –300, 

and –300ER series airplanes. That AD 

requires inspections for scribe lines in 

the skin along lap joints, butt joints, 

certain external doublers, and the large 

cargo door hinges, and related 

investigative and corrective actions if 

necessary. That AD resulted from 

reports of scribe lines found at lap joints 

and butt joints, around external 

doublers, and at locations where 

external decals had been removed. We 

issued that AD to detect and correct 

scribe lines, which can develop into 

fatigue cracks in the skin. Undetected 

fatigue cracks can grow and cause 

sudden decompression of the airplane. 

Actions Since Existing AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009) Was Issued 

Since we issued AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009), we have 

determined that scribe lines could occur 

where external decals are installed or 

removed across lap joints, large cargo 

door hinges, and external doublers. AD 

2009–24–08 had exempted those areas 

from the required inspections. Those 

areas need to be inspected in order to 

address the identified unsafe condition. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

777–53A0054, Revision 1, dated 

November 4, 2010. We referred to 

Boeing Alert Service Bulletin 777– 

53A0054, dated August 7, 2008, as the 

appropriate source of service 

information for accomplishing the 

required actions of AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009). Boeing Service 

Bulletin 777–53A0054, Revision 1, 

dated November 4, 2010, describes an 

additional inspection to determine 

where external decals have been applied 

or removed across lap joints, large cargo 

door hinges, and external doublers on 

airplanes and areas that were previously 

determined to not require inspections as 

specified by the original issue of this 

service information (because the 

airplane had never been stripped or 

repainted). Where external decals have 

been applied or removed, Boeing 

Service Bulletin 777–53A0054, Revision 

1, dated November 4, 2010, describes 

inspecting for scribe lines, and related 

investigative and corrective actions 

previously specified in the original 

issue of this service information. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009). This proposed AD 

would add an inspection to determine 

where external decals have been applied 

or removed across affected lap joints, 

large cargo door hinges, and external 

doublers. For locations where the 

inspections determine that external 

decals have been applied or removed, 

this proposed AD would require 

inspecting for scribe lines, and related 

investigative and corrective actions as 

described in AD 2009–24–08. 

Differences Between the Proposed AD 

and the Service Information 

Where Boeing Service Bulletin 777– 

53A0054, Revision 1, dated November 

4, 2010, specifies contacting the 

manufacturer for instructions on how to 

repair certain conditions, this proposed 

AD would require repairing those 

conditions in one of the following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by an 

Authorized Representative for The 

Boeing Commercial Airplanes 

Organization Designation Authorization 

(ODA) whom we have authorized to 

make those findings. 

Boeing Service Bulletin 777– 

53A0054, Revision 1, dated November 

4, 2010, does not specify a compliance 

time for doing the Part 11 actions of the 

Accomplishment Instructions. This 

proposed AD would require doing the 

Part 11 actions within 24 months after 

the effective date of the AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 163 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

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Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 32059 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Exploratory inspection [retained action from AD 2009– 

24–08, Amendment 39–16096 (74 FR 62217, November 27, 2009)].

Up to 1,234 work-hours × 

$85 per hour = $104,890.

$0 Up to $104,890 Up to $17,097,070. 

Inspection for decals [new proposed action] ................... Up to 4 work-hours × $85 

per hour = $340.

0 Up to $340 ....... Up to $55,420. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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 have 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 that the 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 

removing airworthiness directive (AD) 

2009–24–08, Amendment 39–16096 (74 

FR 62217, November 27, 2009), and 

adding the following new AD: 

The Boeing Company: 

Docket No. FAA–2012–0497; Directorate 

Identifier 2011–NM–140–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by July 16, 2012. 

(b) Affected ADs 

This AD supersedes AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, and –300ER 

series airplanes; certificated in any category; 

as identified in Boeing Service Bulletin 777– 

53A0054, Revision 1, dated November 4, 

2010. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of scribe 

lines found at lap joints and butt joints, 

around external doublers, at locations where 

external decals had been cut, and at locations 

where external decals have been installed or 

removed. We are issuing this AD to detect 

and correct scribe lines which can develop 

into fatigue cracks in the skin. Undetected 

fatigue cracks can grow and cause sudden 

decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection With New Service 

Information and Additional Reporting 

This paragraph restates the requirements of 

paragraph (g) of AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009), with new service 

information and additional reporting. At the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–53A0054, dated August 7, 2008, 

except as provided in paragraphs (h) and (j) 

of this AD: Do detailed exploratory 

inspections for scribe lines in the skin along 

lap joints, butt joints, certain external 

doublers, and the large cargo door hinges. Do 

all applicable related investigative and 

corrective actions at the times specified in 

Boeing Alert Service Bulletin 777–53A0054, 

dated August 7, 2008, by accomplishing all 

actions specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–53A0054, dated August 7, 2008; or 

Boeing Service Bulletin 777–53A0054, 

Revision 1, dated November 4, 2010; except 

as provided by paragraph (i) of this AD. As 

of the effective date of this AD, use only 

Boeing Service Bulletin 777–53A0054, 

Revision 1, dated November 4, 2010, to do 

the actions required by this paragraph. 

Note 1 to paragraph (g) of this AD: The 

inspection exceptions described in NOTES 

1.–5. in Paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0054, 

dated August 7, 2008, apply to paragraph (g) 

of this AD. 

(h) Retained Exception to Service Bulletin 

Specifications, Compliance Time 

This paragraph restates the requirements of 

paragraph (h) of AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009). Where Boeing Alert 

Service Bulletin 777–53A0054, dated August 

7, 2008, specifies a compliance time after the 

date on that service bulletin, paragraph (g) of 

this AD requires compliance within the 

specified compliance time after January 4, 

2010 (the effective date of AD 2009–24–08). 

(i) Retained Exception to Service Bulletin 

Specifications, Contact for Appropriate 

Action With New Service Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2009–24–08, Amendment 

39–16096 (74 FR 62217, November 27, 2009), 

with new service information. Where Boeing 

Alert Service Bulletin 777–53A0054, dated 

August 7, 2008; and Boeing Service Bulletin 

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32060 Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 

777–53A0054, Revision 1, dated November 4, 

2010; specify to contact Boeing for 

appropriate action, accomplish applicable 

actions using a method approved in 

accordance with the procedures specified in 

paragraph (q) of this AD. 

(j) Retained Exception to Service Bulletin 

Specifications, Contact for Inspection 

Requirements 

This paragraph restates the requirements of 

paragraph (j) of AD 2009–24–08, Amendment 

39–16096 (74 FR 62217, November 27, 2009). 

Where paragraph 1.E. ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0054, 

dated August 7, 2008, specifies to ‘‘contact 

Boeing for inspection requirements for 

operation beyond 60,000 total flight-cycles 

after first repaint,’’ for those airplanes, this 

AD requires contacting the Manager, Seattle 

Aircraft Certification Office (ACO), for all 

inspection requirements of this AD and doing 

the requirements. 

(k) Retained Reporting 

This paragraph restates the requirements of 

paragraph (k) of AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009). At the applicable time 

specified in paragraph (k)(1) or (k)(2) of this 

AD: Submit a report of positive findings of 

cracks found during the inspection required 

by paragraphs (g) and (m) of this AD to the 

Boeing Commercial Airplane Group, P.O. 

Box 3707, Seattle, Washington 98124–2207. 

Alternatively, operators may submit reports 

to their Boeing field service representatives. 

The report must contain, at a minimum, the 

inspection results, a description of any 

discrepancies found, the airplane serial 

number, and the number of flight cycles and 

flight hours on the airplane. Under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(l) New Inspection for External Decals 

Within 24 months after the effective date 

of this AD: Inspect to determine the locations 

where external decals have been applied or 

removed across affected lap joints, large 

cargo door hinges, and external doublers, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

53A0054, Revision 1, dated November 4, 

2010. 

(m) New Inspection for Scribe Lines and 

Related Investigative and Corrective Actions 

If, during the inspection required by 

paragraph (l) of this AD, any location is 

found where external decals have been 

applied or removed across lap joints, large 

cargo door hinges, or external doublers: 

Before further flight, do a detailed 

exploratory inspection for scribe lines at all 

affected locations, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–53A0054, Revision 1, 

dated November 4, 2010. Do all applicable 

related investigative and corrective actions at 

the times specified in Boeing Service Bulletin 

777–53A0054, Revision 1, dated November 4, 

2010, by accomplishing all actions specified 

in the Accomplishment Instructions of 

Boeing Service Bulletin 777–53A0054, 

Revision 1, dated November 4, 2010, except 

as provided by paragraph (i) of this AD. 

(n) Exceptions to Service Information 

(1) Where Boeing Service Bulletin 777– 

53A0054, Revision 1, dated November 4, 

2010, specifies a compliance time after the 

date on that service bulletin, paragraphs (l) 

and (m) of this AD require compliance within 

the specified compliance time after the 

effective date of this AD. 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 777–53A0054, 

Revision 1, dated November 4, 2010, 

specifies to ‘‘contact Boeing for inspection 

requirements for operation beyond 60,000 

total flight-cycles after first repaint,’’ for 

those airplanes, this AD requires contacting 

the Manager, Seattle ACO, for all inspection 

requirements of this AD and doing the 

requirements. 

(o) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (m) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 777–53A0054, dated August 

7, 2008. 

(p) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 emailed to: 9–ANM– 

Seattle–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) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009), are approved as AMOCs 

for the corresponding provisions of this AD, 

except that AMOCs approved for AD 2009– 

24–08 are not approved for fuselage areas 

where any decals may have been installed or 

removed on airplanes that have never been 

stripped or repainted since they left the 

factory. 

(r) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6577; fax: 425–917–6590; email: 

Berhane.Alazar@faa.gov. 

(2) 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; email: 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 May 21, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–13169 Filed 5–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0493; Directorate 

Identifier 2011–NM–180–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

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