66772 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 

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 

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: 

Rolls-Royce Deutschland Ltd & Co KG 

(Formerly Rolls-Royce Deutschland 

GmbH, and BMW Rolls-Royce plc): 

Docket No. FAA–2012–1100; Directorate 

Identifier 2012–NE–29–AD. 

(a) Comments Due Date 

We must receive comments by January 7, 

2013. 

(b) Affected Airworthiness Directives (ADs) 

None. 

(c) Applicability 

This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG (RRD) BR700– 

710A1–10 and BR700–710A2–20 turbofan 

engines, all serial numbers, and BR700– 

710C4–11 turbofan engines that have either 

of the following hardware configuration 

standards engraved on the engine data plate: 

(1) standard 710C4–11, RRD Alert NonModification Service Bulletin (NMSB) SB– 

BR700–72–101466 standard not 

incorporated, or 

(2) standard 710C4–11/10, RRD Alert 

NMSB SB–BR700–72–101466 standard 

incorporated. 

(d) Reason 

This AD was prompted by service 

experience that demonstrated premature 

wear of the splined coupling on the fuel 

pump. We are issuing this AD to prevent 

failure of the engine and loss of the airplane. 

(e) Actions and Compliance 

Unless already done, do the following. 

(1) After the effective date of this AD, 

replace the fuel pump splined coupling as 

follows and every 4,000 hours time in service 

(TIS) thereafter: 

(i) If the engine has 3,750 hours TIS or 

more, within 250 hours TIS. 

(ii) If the engine has less than 3,750 hours 

TIS, before reaching 4,000 hours TIS. 

(2) If you replaced the engine fuel pump 

splined coupling before the effective date of 

this AD, replace the fuel pump splined 

coupling before reaching 4,000 hours TIS 

since last replacement, or before further 

flight, whichever comes later. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

approve for return to service any engine with 

a fuel pump with an affected splined 

coupling that has accumulated 4,000 hours 

TIS, or any airplane with an engine with an 

affected fuel pump splined coupling installed 

that has accumulated 4,000 hours TIS. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(h) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: frederick.zink@faa.gov; phone: 781– 

238–7779; fax: 781–238–7199. 

(2) Refer to MCAI Airworthiness Directive 

No. 2012–0161, dated August 24, 2012, and 

RRD Alert NMSB SB–BR700–72–A900509, 

Revision 3, dated August 2, 2012, for related 

information. 

(3) For service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11, Dahlewitz, 15827 

Blankenfelde-Mahlow, Germany; telephone: 

49 0 33–7086–1883; fax: 49 0 33–7086–3276. 

You may review copies of the referenced 

service information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

October 26, 2012. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–27108 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–2012–1158; Directorate 

Identifier 2011–NM–232–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Airbus Model A300 

and A310 series airplanes; and Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and Model A300 C4– 

605R Variant F airplanes (collectively 

called A300–600 series airplanes). The 

existing AD currently requires revising 

the Airworthiness Limitations section of 

the Instructions for Continued 

Airworthiness to incorporate new and 

revised structural inspections and 

inspection intervals. Since we issued 

that AD, Airbus has revised certain ALI 

documents, which require more 

restrictive maintenance requirements 

and airworthiness limitations. This 

proposed AD would revise the 

maintenance program to incorporate the 

limitations section. We are proposing 

this AD to prevent fatigue cracking, 

damage, or corrosion in principal 

structural elements, which could result 

in reduced structural integrity of the 

airplane. 

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– 

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– 


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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, 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–2012–1158; Directorate Identifier 

2011–NM–232–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 May 2, 2011, we issued AD 2011– 

10–17, Amendment 39–16698 (76 FR 

27875, May 13, 2011). That AD required 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, 

May 13, 2011), Airbus has revised 

certain ALI documents, which require 

more restrictive maintenance 

requirements and 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 2011– 

0198, dated October 19, 2011 (referred 

to after this as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

The airworthiness limitations applicable to 

the Damage Tolerant Airworthiness 

Limitation Items (DT ALIs) are currently 

listed in Airbus ALI Documents, which are 

referenced in the A300, A310 and A300–600 

Airworthiness Limitations Section (ALS) Part 

2. 

Airbus have recently revised the A300–600 

and A310 ALI Documents, and these issues 

have been approved by EASA. The Airbus 

A300–600 ALI Document issue 13 and 

temporary revision (TR) 13.1 and the A310 

ALI document issue 08 introduce more 

restrictive maintenance requirements and 

airworthiness limitations, which have been 

identified as mandatory actions for continued 

airworthiness. 

EASA AD 2009–0155 [which corresponds 

to FAA AD 2011–10–17, Amendment 39– 

16698 (76 FR 27875, May 13, 2011)] required 

compliance with the maintenance 

requirements and associated airworthiness 

limitations defined in the following 

documents: 

—AIRBUS A300 ALI Document issue 04, 

—AIRBUS A310 ALI Document issue 07, 

and 

—AIRBUS A300–600 ALI Document issue 

12. 

For the reasons described, this EASA AD 

retains the requirements of EASA AD 2009– 

0155, which is superseded, and requires 

compliance with the airworthiness 

limitations defined in the Airbus A300–600 

ALI Document issue 13 and TR13.1, and the 

A310 ALI document issue 08. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued the following 

service information. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

• Airbus A310 Airworthiness 

Limitation Items Document, AI/SE–M2/ 

95A.1309/07, Issue 8, dated October 

2010 (for Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 

airplanes). 

• Airbus A300–600 Airworthiness 

Limitation Items Document, AI/SE–M2/ 

95A.1310/07, Issue 13, dated October 

2010 (Model A300 B4–601, B4–603, B4– 

620, B4–622, B4–605R, B4–622R, F4– 

605R, F4–622R, and C4–605R Variant F 

airplanes). 

• Airbus Temporary Revision 13.1, 

dated February 2011, to the Airbus 

A300–600 Airworthiness Limitation 

Items Document, AI/SE–M2/95A.1310/ 

07, Issue 13, dated October 2010 (for 

Model A300 B4–601, B4–603, B4–620, 

B4–622, B4–605R, B4–622R, F4–605R, 

F4–622R, and C4–605R Variant F 

airplanes). 

FAA’s Determination and Requirements 

of This Proposed AD 

These products have been approved 

by the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

This proposed AD requires revisions 

to certain operator maintenance 

documents to include new actions (e.g., 

inspections). Compliance with these 

actions is required by section 91.403(c) 

of the Federal Aviation Regulations (14 

CFR 91.403(c)). For airplanes that have 

been previously modified, altered, or 

repaired in the areas addressed by these 

inspections, an operator might not be 

able to accomplish the actions described 

in the revisions. In this situation, to 

comply with 14 CFR 91.403(c), the 

operator must request approval of an 

alternative method of compliance 

(AMOC) in accordance with the 

provisions of paragraph (u)(1) of this 

proposed AD. The request should 

include a description of changes to the 

required actions that will ensure the 

continued damage tolerance of the 

affected structure. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 170 products of U.S. 

registry. 

The actions that are required by AD 

2011–10–17, Amendment 39–16698 (76 

FR 27875, May 13, 2011), and retained 

in this proposed AD take about 1 workhour per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 


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currently required actions is $85 per 

product. 

We estimate that it would take about 

1 work-hour per product to comply with 

the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$14,450, 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. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

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 airworthiness directive (AD) 

2011–10–17, Amendment 39–16698 (76 

FR 27875, May 13, 2011), and adding 

the following new AD: 

Airbus: Docket No. FAA–2012–1158; 

Directorate Identifier 2011–NM–232–AD. 

(a) Comments Due Date 

We must receive comments by December 

24, 2012. 

(b) Affected ADs 

This AD supersedes AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 13, 

2011), which superseded AD 2007–04–11, 

Amendment 39–14943 (72 FR 8604, February 

27, 2007); AD 2007–20–03, Amendment 39– 

15213 (72 FR 54536, September 26, 2007); 

and AD 2007–25–02, Amendment 39–15283 

(72 FR 69612, December 10, 2007). AD 2007– 

04–11 superseded AD 96–13–11, 

Amendment 39–9679 (61 FR 35122, July 5, 

1996). 

(c) Applicability 

This AD applies to all Airbus model 

airplanes identified in paragraphs (c)(1), 

(c)(2), and (c)(3) of this AD, certificated in 

any category. 

(1) Model A300 B2–1A, B2–1C, B4–2C, 

B2K–3C, B4–103, B2–203, and B4–203 

airplanes. 

(2) Model A310–203, –204, –221, –222, 

–304, –322, –324, and –325 airplanes. 

(3) Model A300 B4–601, B4–603, B4–620, 

B4–622, B4–605R, B4–622R, F4–605R, F4– 

622R, and C4–605R Variant F airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by revisions of 

certain Airbus Airworthiness Limitation 

Items (ALI) documents, which require more 

restrictive maintenance requirements and 

airworthiness limitations. We are issuing this 

AD to prevent fatigue cracking, damage, or 

corrosion in principal structural elements, 

which could result in reduced structural 

integrity of the airplane. 

(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) Retained Maintenance Program Revision 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 13, 

2011). Within one year after August 9, 1996 

(the effective date of AD 96–13–11, 

Amendment 39–9679 (61 FR 35122, July 5, 

1996)), replace the revision of the 

maintenance program with the inspections, 

inspection intervals, repairs, and 

replacements defined in Airbus Industrie 

A300 Supplemental Structural Inspection 

Document, Revision 2, dated June 1994. 

Accomplish the actions specified in the 

service bulletins identified in Section 6, ‘‘SB 

Reference List,’’ in Airbus Industrie A300 

Supplemental Structural Inspection 

Document, Revision 2, dated June 1994, at 

the times specified in those service bulletins. 

The actions are to be accomplished in 

accordance with those service bulletins. 

Accomplishing the initial ALI tasks required 

by paragraph (r) of this AD terminates the 

actions required by this paragraph. 

(1) For airplanes that have exceeded the 

threshold specified in any of the service 

bulletins identified in Section 6, ‘‘SB 

Reference List,’’ in Airbus Industrie A300 

Supplemental Structural Inspection 

Document, Revision 2, dated June 1994: 

Accomplish the actions specified in those 

service bulletins within the grace period 

specified in those service bulletins. The grace 

period is to be measured from August 9, 1996 

(the effective date of AD 96–13–11, 

Amendment 39–9679 (61 FR 35122, July 5, 

1996)). 

(2) For airplanes that have exceeded the 

threshold specified in any of the service 

bulletins identified in Section 6, ‘‘SB 

Reference List,’’ in Airbus Industrie A300 

Supplemental Structural Inspection 

Document, Revision 2, dated June 1994, and 

a grace period is not specified in that service 

bulletin: Accomplish the actions specified in 

that service bulletin within 1,500 flight 

cycles after August 9, 1996 (the effective date 

of AD 96–13–11, Amendment 39–9679 (61 

FR 35122, July 5, 1996)). 

(h) Retained Revision of the Maintenance 

Inspection Program 

This paragraph restates the requirements of 

paragraphs (h) and (i) of AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 13, 

2011). 

(1) For airplanes identified in paragraph 

(c)(1) of this AD: Within 12 months after 

April 3, 2007 (the effective date of AD 2007– 

04–11, Amendment 39–14943 (72 FR 8604, 

February 27, 2007), replace the revision of 

the maintenance program required by 

paragraph (g) of this AD with the 

supplemental structural inspections, 

inspection intervals, and repairs defined in 

Airbus A300 Airworthiness Limitation Items 

Document SEM2/95A.1090/05, Issue 3, dated 

September 2005, as revised by Airbus A300 

Temporary Revision (TR) 3.1, dated April 

2006. Accomplish the actions specified in 


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Airbus A300 Airworthiness Limitation Items 

Document SEM2/95A.1090/05, Issue 3, dated 

September 2005, as revised by Airbus A300 

TR 3.1, dated April 2006, at the times 

specified in that ALI, except as provided by 

paragraph (h)(2) of this AD. The actions must 

be accomplished in accordance with Airbus 

A300 Airworthiness Limitation Items 

Document SEM2/95A.1090/05, Issue 3, dated 

September 2005, as revised by Airbus A300 

TR 3.1, dated April 2006. Accomplishing the 

initial ALI tasks required by paragraph (r) of 

this AD terminates the actions required by 

this paragraph. 

(2) For airplanes identified in paragraph 

(c)(1) of this AD that have exceeded the 

threshold or intervals specified in the Airbus 

A300 Airworthiness Limitation Items 

Document SEM2/95A.1090/05, Issue 3, dated 

September 2005, for the application tolerance 

on the first interval for new and revised 

requirements and have exceeded 50 percent 

of the intervals specified in sections D and 

E of Airbus A300 Airworthiness Limitation 

Items Document SEM2/95A.1090/05, Issue 3, 

dated September 2005: Do the actions within 

6 months after April 3, 2007 (the effective 

date of AD 2007–04–11, Amendment 39– 

14943 (72 FR 8604, February 27, 2007)). 

(i) Retained Corrective Actions 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–10–17, Amendment 

39–16698 (76 FR 27875, May 13, 2011). 

Damaged, cracked, or corroded structure 

detected during any inspection done in 

accordance with the Airbus A300 

Airworthiness Limitation Items Document 

SEM2/95A.1090/05, Issue 3, dated September 

2005, must be repaired, before further flight, 

in accordance with Airbus A300 

Airworthiness Limitation Items Document 

SEM2/95A.1090/05, Issue 3, dated September 

2005, as revised by Airbus A300 TR 3.1, 

dated April 2006, except as provided by 

paragraph (j) of this AD; or other data 

meeting the certification basis of the airplane 

which is approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or by the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(j) Retained Exception 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 13, 

2011). Where the Airbus A300 Airworthiness 

Limitation Items Document SEM2/95A.1090/ 

05, Issue 3, dated September 2005, specifies 

contacting Airbus for appropriate action: 

Before further flight, repair the damaged, 

cracked, or corroded structure using a 

method approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). 

(k) Retained No Fleet Sampling 

This paragraph restates the requirements of 

paragraph (l) of AD 2011–10–17, Amendment 

39–16698 (76 FR 27875, May 13, 2011). 

Although Airbus A300 Airworthiness 

Limitation Items Document SEM2/95A.1090/ 

05, Issue 3, dated September 2005, specifies 

to do a ‘‘Sampling Concept’’ in section B, this 

AD prohibits the use of such a sampling 

program and requires all affected airplanes of 

the fleet to be inspected. 

(l) Retained No Reporting 

This paragraph restates the exception 

specified in paragraph (m) of AD 2011–10– 

17, Amendment 39–16698 (76 FR 27875, May 

13, 2011). Although Airbus A300 

Airworthiness Limitation Items Document 

SEM2/95A.1090/05, Issue 3, dated September 

2005, specifies to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 

(m) Retained Actions and Compliance 

This paragraph restates the requirements of 

paragraph (n) of AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 13, 

2011). For airplanes identified in paragraph 

(c)(3) of this AD: Within 3 months after 

October 31, 2007 (the effective date AD 

2007–20–03, Amendment 39–15213 (72 FR 

54536, September 26, 2007)), revise the 

Airworthiness Limitations Section (ALS) of 

the Instructions for Continued Airworthiness 

(ICA) to incorporate Airbus A300–600 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.0502/06, Issue 11, dated 

April 2006. The tolerance (grace period) for 

compliance (specified in paragraph 2 of 

Section B—Program Rules) with Airbus 

A300–600 Airworthiness Limitation Items 

Document AI/SE–M2/95A.0502/06, Issue 11, 

dated April 2006, is within 2,000 flight 

cycles after October 31, 2007 (the effective 

date AD 2007–20–03), provided that none of 

the following is exceeded. Accomplishing the 

initial ALI tasks required by paragraph (r) of 

this AD terminates the actions required by 

this paragraph. 

(1) Thresholds or intervals in the operator’s 

current approved maintenance schedule that 

are taken from a previous ALI issue, if 

existing, and are higher than or equal to those 

given in Airbus A300–600 Airworthiness 

Limitation Items Document AI/SE–M2/ 

95A.0502/06, Issue 11, dated April 2006. 

(2) 8 months after October 31, 2007 (the 

effective date AD 2007–20–03, Amendment 

39–15213 (72 FR 54536, September 26, 

2007)). 

(3) 50 percent of the intervals given in 

Airbus A300–600 Airworthiness Limitation 

Items Document AI/SE–M2/95A.0502/06, 

Issue 11, dated April 2006. 

(4) Any application tolerance given in the 

task description of Airbus A300–600 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.0502/06, Issue 11, dated 

April 2006. 

(n) Retained Revision of the ALS of the ICA 

This paragraph restates the requirements of 

paragraph (o) of AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 13, 

2011). For airplanes identified in paragraph 

(c)(2) of this AD: Within 3 months after 

January 14, 2008 (the effective date of AD 

2007–25–02, Amendment 39–15283 (72 FR 

69612, December 10, 2007)), do the actions 

specified in paragraphs (n)(1) and (n)(2) of 

this AD. Accomplishing the initial ALI tasks 

required by paragraph (r) of this AD 

terminates the actions required by this 

paragraph. 

(1) Revise the ALS of the ICA to 

incorporate the structural inspections and 

inspection intervals defined in Airbus A310 

Airworthiness Limitations Items Document, 

AI/SE–M2/95A.0263/06, Issue 6, dated April 

2006 (approved by the EASA on May 31, 

2006). Accomplish the actions specified in 

Airbus A310 Airworthiness Limitations Items 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006, at the times specified in 

Airbus A310 Airworthiness Limitations Items 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006, except as provided by 

paragraph (o) of this AD. Thereafter, except 

as provided by paragraphs (n)(2) and (s) of 

this AD, no alternative structural inspection 

intervals may be approved. The actions 

specified in Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

95A.0263/06, Issue 6, dated April 2006, must 

be accomplished in accordance with Airbus 

A310 Airworthiness Limitations Items 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006. 

(2) Revise the ALS of the ICA to 

incorporate the new and revised structural 

inspections and inspection intervals defined 

in Airbus TR 6.1, dated November 2006 

(approved by the EASA on December 12, 

2006), to Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

95A.0263/06, Issue 6, dated April 2006. 

Thereafter, except as provided by paragraph 

(s) of this AD, no alternative structural 

inspection intervals may be approved. 

(o) Retained Exception to Issue 6 of the A310 

ALI Document 

This paragraph restates the requirements of 

paragraph (p) of AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 13, 

2011). The tolerance (grace period) for 

compliance with Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

95A.0263/06, Issue 6, dated April 2006, is 

within 1,500 flight cycles after January 14, 

2008 (the effective date of AD 2007–25–02, 

Amendment 39–15283 (72 FR 69612, 

December 10, 2007)), provided that none of 

the following is exceeded. 

(1) Thresholds or intervals in the operator’s 

current approved maintenance schedule that 

are taken from a previous ALI issue, if 

existing, and are higher than or equal to those 

given in Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

95A.0263/06, Issue 6, dated April 2006. 

(2) 18 months after January 14, 2008 (the 

effective date of AD 2007–25–02, 

Amendment 39–15283 (72 FR 69612, 

December 10, 2007)). 

(3) 50 percent of the intervals given in 

Airbus A310 Airworthiness Limitations Items 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006. 

(4) Any application tolerance specified in 

Section D of Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

95A.0263/06, Issue 6, dated April 2006. 

(p) Retained Corrective Actions 

This paragraph restates certain 

requirements of paragraph (q) of AD 2011– 

10–17, Amendment 39–16698 (76 FR 27875, 

May 13, 2011). Damaged, cracked, or 

corroded structure detected during any 

inspection done in accordance with Airbus 

A310 Airworthiness Limitations Items 


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66776 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006, must be repaired, before 

further flight, in accordance with Airbus 

A310 Airworthiness Limitations Items 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006; or in accordance with other 

data meeting the certification basis of the 

airplane that has been approved by either the 

Manager, International Branch, ANM–116, or 

the EASA (or its delegated agent). Where 

Airbus A310 Airworthiness Limitations Items 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006, specifies to contact Airbus 

for appropriate action: Before further flight, 

repair the damaged, cracked, or corroded 

structure using a method approved by either 

the Manager, International Branch, ANM– 

116; or the EASA (or its delegated agent). 

(q) Retained Reporting Requirement 

This paragraph restates the requirements of 

paragraph (r) of AD 2011–10–17, Amendment 

39–16698 (76 FR 27875, May 13, 2011). If any 

damage that exceeds the allowable limits 

specified in Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

95A.0263/06, Issue 6, dated April 2006, is 

detected during any inspection required by 

this AD: At the applicable time specified in 

paragraph (q)(1) or (q)(2) of this AD, submit 

a report of the finding to Airbus, Customer 

Service Directorate, Attn: Department 

Manager Maintenance Engineering, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; email: 

sched.maint@airbus.com. The report must 

include the ALI task reference, airplane serial 

number, the number of flight cycles and 

flight hours on the airplane, identification of 

the affected structure, location and 

description of the finding including its size 

and orientation, and the circumstance of 

detection and inspection method used. 

(1) If the inspection was done after January 

14, 2008 (the effective date of AD 2007–25– 

02, Amendment 39–15283 (72 FR 69612, 

December 10, 2007)): Submit the report 

within 30 days after the inspection. 

(2) If the inspection was accomplished 

prior to January 14, 2008 (the effective date 

of AD 2007–25–02, Amendment 39–15283 

(72 FR 69612, December 10, 2007)): Submit 

the report within 30 days after January 14, 

2008 (the effective date of AD 2007–25–02). 

(r) Retained Revision of the ALS of the ICA 

This paragraph restates the requirements of 

paragraph (s) of AD 2011–10–17, 

Amendment 39–16698 (76 FR 27875, May 13, 

2011). Within 3 months after June 17, 2011 

(the effective date of AD 2011–10–17): Revise 

the maintenance program to incorporate the 

structural inspections and inspection 

intervals defined in the applicable ALI 

document listed in table 1 to paragraph (r) of 

this AD. Thereafter, except as provided by 

paragraphs (u) and (s) of this AD, no 

alternative structural inspections and 

inspection intervals may be approved. The 

actions must be accomplished in accordance 

with the applicable issue of the ALI. The 

initial ALI tasks must be done at the times 

specified in the applicable ALI document 

listed in table 1 to paragraph (r) of this AD. 

Accomplishing the applicable initial ALI 

tasks constitutes terminating action for the 

requirements of paragraphs (g) through (q) of 

this AD for that airplane only. Doing the 

actions required by paragraph (s) of this AD 

terminates the requirements of this 

paragraph. 

TABLE 1 TO PARAGRAPH (R) OF THIS AD—AIRWORTHINESS LIMITATIONS ITEMS DOCUMENT

Model Document Issue Date 

A300 ................................... Airbus A300 Airworthiness Limitation Items Document AI/SE–M2/95A.1308/07 ..... 4 June 2008. 

A310 ................................... Airbus A310 Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07 ...... 7 June 2008. 

A300–600 ........................... Airbus A300–600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/ 

07.

12 June 2008. 

(s) New Maintenance Program Revision 

Within 3 months after the effective date of 

this AD, do the applicable revision specified 

in paragraph (s)(1) or (s)(2) of this AD. The 

initial compliance times for the actions 

specified in the documents specified in 

paragraphs (s)(3), (s)(4), and (s)(5) of this AD 

are at the applicable compliance time 

specified in the document specified in 

paragraphs (s)(3), (s)(4), and (s)(5) of this AD, 

or within 3 months after the effective date of 

this AD, whichever occurs later; except for 

actions identified in both documents for the 

Model A300–600 series airplanes, use the 

applicable compliance time specified in 

Airbus TR 13.1, dated February 2011, to the 

Airbus A300–600 Airworthiness Limitation 

Items Document AI/SE–M2/95A.1310/07, 

Issue 13, dated October 2010. Accomplishing 

the applicable initial actions constitutes 

terminating action for the requirements of 

paragraph (r) of this AD for that airplane 

only. 

(1) For Model A310 series airplanes: 

Within 3 months after the effective date of 

this AD, revise the maintenance program to 

incorporate the actions (e.g., modifications 

and structural inspections) and compliance 

times defined in Airbus A310 Airworthiness 

Limitation Items Document AI/SE–M2/ 

95A.1309/07, Issue 8, dated October 2010. 

(2) For Model A300–600 series airplanes: 

Within 3 months after the effective date of 

this AD, revise the maintenance program to 

incorporate the structural inspections and 

inspection intervals defined in Airbus A300– 

600 Airworthiness Limitation Items 

Document AI/SE–M2/95A.1310/07, Issue 

13.1, dated February 2011. 

(3) For Model A310 series airplanes: 

Airbus A310 Airworthiness Limitation Items 

Document AI/SE–M2/95A.1309/07, Issue 8, 

dated October 2010. 

(4) For Model A300–600 series airplanes: 

Airbus A300–600 Airworthiness Limitation 

Items Document AI/SE–M2/95A.1310/07, 

Issue 13, dated October 2010. 

(5) TR 13.1, dated February 2011, to the 

Airbus A300–600 Airworthiness Limitation 

Items Document AI/SE–M2/95A.1310/07, 

Issue 13, dated October 2010. 

(t) New Alternative Inspections and 

Inspection Intervals Limitation 

After accomplishing the revision required 

by paragraph (s) of this AD, no alternative 

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

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (u) of this 

AD. 

(u) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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, Washington 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. 

(v) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0198, dated October 19, 2011, 

and the service information specified in 

paragraphs (v)(1) through (v)(12) of this AD, 

for related information. 

(1) Airbus A300 Airworthiness Limitation 

Items Document AI/SE–M2/95A.1308/07, 

Issue 4, dated June 2008. 

(2) Airbus A300 Airworthiness Limitation 

Items Document SEM2/95A.1090/05, 

Revision 3, dated September 2005. 


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Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 66777 

(3) Airbus A300–600 Airworthiness 

Limitation Items Document AI/SE–M2/ 

95A.0502/06, Revision 11, dated April 2006. 

(4) Airbus A300–600 Airworthiness 

Limitation Items Document AI/SE–M2/ 

95A.1310/07, Issue 13, dated October 2010. 

(5) Airbus A300–600 Airworthiness 

Limitation Items Document AI/SE–M2/ 

95A.1310/07, Revision 12, dated June 2008. 

(6) Airbus A310 Airworthiness Limitation 

Items Document AI/SE–M2/95A.1309/07, 

Issue 8, dated October 2010. 

(7) Airbus A310 Airworthiness Limitation 

Items Document AI/SE–M2/95A.1309/07, 

Revision 7, dated June 2008. 

(8) Airbus A310 Airworthiness Limitations 

Items Document AI/SE–M2/95A.0263/06, 

Revision 6, dated April 2006. 

(9) Airbus Industrie A300 Structural 

Inspection Document, Revision 2, dated June 

1994. 

(10) Airbus Temporary Revision 13.1, 

dated February 2011, to Airbus A300–600 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.1310/07, Revision 13, dated 

October 2010. 

(11) Airbus Temporary Revision 3.1, dated 

April 2006, including attachment, dated 

April 2006, and including attachments dated 

September 2005, to Airbus A300 

Airworthiness Limitation Items, Document 

SEM2/95A.1090/05, Issue 3, dated September 

2005. 

(12) Airbus Temporary Revision 6.1, 

including pages 1 and 2 of Section D and 

page 1 of Section E, dated November 2006, 

to Airbus A310 Airworthiness Limitations 

Items Document, AI/SE–M2/95A.0263/06, 

Issue 6, dated April 2006. 

Issued in Renton, Washington, on October 

30, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27126 Filed 11–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Parts 764 and 766 

[Docket No. 120207107–2565–01] 

RIN 0694–AF59 

Time Limit for Completion of Voluntary 

Self-Disclosures and Revised Notice of 

the Institution of Administrative 

Enforcement Proceedings 

AGENCY: Bureau of Industry and 

Security, Commerce. 

ACTION: Proposed rule. 

SUMMARY: This proposed rule would 

require that the final, comprehensive 

narrative account required in voluntary 

self-disclosures (VSDs) of violations of 

the Export Administration Regulations 

(EAR) be submitted to the Office of 

Export Enforcement within 180 days of 

the initial VSD notification. This 

proposed rule also would authorize the 

use of delivery services other than 

registered or certified mail for providing 

notice of the issuance of a charging 

letter instituting an administrative 

enforcement proceeding under the EAR. 

It also would remove the phrase ‘‘if 

delivery is refused’’ from a provision 

relating to determining the date of 

service of notice of a charging letter’s 

issuance based on an attempted delivery 

to the respondent’s last known address. 

The Bureau of Industry and Security is 

proposing these changes to be better 

able to resolve administrative 

enforcement proceedings in a timely 

manner and provide more efficient 

notice of administrative charging letters. 

DATES: Comments must be received no 

later than January 7, 2013. 

ADDRESSES: You may submit comments 

by any of the following methods: 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. The identification 

number for this rulemaking is BIS– 

2012–0043. 

• By email directly to 

publiccomments@bis.doc.gov. Include 

RIN 0694–AF59 in the subject line. 

• By mail or delivery to Regulatory 

Policy Division, Bureau of Industry and 

Security, U.S. Department of Commerce, 

Room 2099B, 14th Street and 

Pennsylvania Avenue NW., Washington, 

DC 20230. Refer to RIN 0694–AF59. 

FOR FURTHER INFORMATION CONTACT: 

Special Agent Kirk Flashner, Office of 

Export Enforcement, Bureau of Industry 

and Security, U.S. Department of 

Commerce, Room H4514, 14th Street 

and Pennsylvania Avenue NW., 

Washington, DC 20230. Tel: (202) 482– 

1208. Facsimile: (202) 482–5889. 

SUPPLEMENTARY INFORMATION: 

Background 

The Bureau of Industry and Security 

(BIS), Office of Export Enforcement 

(OEE), investigates possible violations of 

the Export Administration Regulations 

(EAR) and orders, licenses, and 

authorizations issued thereunder. These 

investigations may result in allegations 

of violations that may be settled, 

adjudicated in an administrative 

enforcement proceeding, or referred to 

the Department of Justice for possible 

criminal prosecution. This rule 

proposes three changes to the EAR. One 

change addresses voluntary selfdisclosures in connection with OEE’s 

conduct of investigations. The other two 

changes address service of notice in 

administrative enforcement 

proceedings. 

Proposed Change Regarding Voluntary 

Self-Disclosures 

Section 764.5 of the EAR provides a 

procedure whereby parties that believe 

that they may have committed a 

violation of the EAR can voluntarily 

disclose the facts of the potential 

violations to OEE. Such disclosures that 

meet the requirements of § 764.5 

typically are afforded ‘‘great weight’’ by 

BIS, relative to other mitigating factors, 

in determining what administrative 

sanctions, if any, to seek. Section 764.5 

requires an initial notification, which is 

to include a description of the general 

nature and extent of the suspected 

violations, and is followed at a later date 

by a thorough review and narrative 

account of the suspected violations, 

including all relevant supporting 

documentation. If the person making the 

initial notification subsequently 

completes the narrative account, the 

disclosure is deemed to have been 

submitted to OEE on the date of the 

initial notification. The date of the 

initial notification may be significant 

because information provided to OEE 

may only be considered a voluntary 

disclosure if the information ‘‘is 

received by OEE for review prior to the 

time that OEE or another United States 

Government agency has learned of the 

same or substantially similar 

information from another source and 

has commenced an investigation or 

inquiry in connection with that 

information.’’ 15 CFR 764.5(b)(3). 

Currently, § 764.5 of the EAR does not 

include a specific time limit within 

which a narrative account must be 

submitted to OEE. Too often, initial 

notifications are not promptly followed 

by comprehensive narrative accounts, 

and as a result, OEE must maintain open 

files on voluntary disclosures for 

extended periods of time without 

making sufficient progress towards 

resolving the matter disclosed. To 

address these situations and promote 

expeditious resolution of self-disclosed 

violations, BIS proposes to set a 180-day 

deadline for persons who have 

submitted an initial notification to 

complete and submit the final narrative 

report to OEE. The Director of OEE 

could extend this 180-day time 

deadline, at his or her discretion, if U.S. 

Government interests would be served 

by an extension or upon a showing by 

the party making the disclosure that 

more time is reasonably necessary to 

complete the narrative account. Some 

illustrative examples of circumstances 

that might warrant additional time 

include the following. 

• Records or information from 

multiple entities and/or jurisdictions are 


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