2284 Federal Register / Vol. 76, No. 9 / Thursday, January 13, 2011 / Proposed Rules 

Inspection Service Bulletin ISB.53–167, 

including Appendix 2, Revision 4, dated June 

10, 2010: Within 4,600 flight cycles after the 

last inspection done in accordance with 

paragraph (g) of this AD. 

(l) If any cracking is found during any 

inspection required by paragraph (j) or (k) of 

this AD, before further flight, accomplish the 

repair in accordance with a method approved 

by the FAA or EASA (or its delegated agent). 

Repair of an airplane in accordance with the 

requirements of this paragraph of this AD 

does not constitute terminating action for the 

inspection requirements of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(m) Inspections done before the effective 

date of this AD in accordance with BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–167, including 

Appendix 2, Revision 2, dated November 17, 

2008; or Revision 3, dated June 17, 2009; are 

acceptable for compliance with the 

corresponding requirements of paragraphs (j) 

and (k) 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 

(n) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards 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. 

(3) Reporting Requirements: 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. 

Related Information 

(o) Refer to MCAI EASA Airworthiness 

Directive 2009–0070R1, dated July 2, 2010; 

and BAE Systems (Operations) Limited 

Modification Service Bulletin ISB.53–167, 

including Appendix 2, Revision 1, dated May 

18, 2004; and BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

167, including Appendix 2, Revision 4, dated 

June 10, 2010; for related information. 

Issued in Renton, Washington, on January 

5, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–585 Filed 1–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1309; Directorate 

Identifier 2010–NM–060–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–300, A340–200, and A340–300 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. 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: 

Surface defects were visually detected on 

the rudder of one Airbus A319 and one A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were the result of 

de-bonding between the skin and honeycomb 

core. Such reworks were also performed on 

some rudders fitted on A330–300 and A340– 

200/–300 aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability 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 February 28, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone + 33 5 61 93 

36 96; fax + 33 5 61 93 45 80, e-mail 

airworthiness.A330–A340@airbus.com; 

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

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 76, No. 9 / Thursday, January 13, 2011 / Proposed Rules 2285 

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–2010–1309; Directorate Identifier 

2010–NM–060–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 aviation authority 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0021, 

dated February 9, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Surface defects were visually detected on 

the rudder of one Airbus A319 and one A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were the result of 

de-bonding between the skin and honeycomb 

core. Such reworks were also performed on 

some rudders fitted on A330–300 and A340– 

200/–300 aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

EASA AD 2009–0156 required inspections 

of specific areas and, depending on findings, 

the application of corrective actions for those 

rudders where production reworks have been 

identified. 

This AD retains the requirements of EASA 

AD 2009–0156, which is superseded, and in 

addition requires for the vacuum loss hole 

restoration: 

—a local ultrasonic inspection for reinforced 

area instead of the local thermography 

inspection, which is maintained for nonreinforced areas, and 

— an additional work for aeroplanes on 

which this thermography inspection has 

been performed in the reinforced area. 

The inspections include vacuum loss 

inspections and repetitive elasticity 

laminate checker inspections for defects 

including de-bonding between the skin 

and honeycomb core of the rudder, and 

ultrasonic inspections for defects on 

rudders on which temporary restoration 

with resin or permanent vacuum loss 

hole restoration has been performed. 

The corrective action is repair, if 

necessary. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued All Operators 

Telexes (AOTs) A330–55A3040 and 

A340–55A4036, both Revision 02, both 

dated September 30, 2009. 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 

Currently, there are no affected 

airplanes on the U.S. Register. However, 

if an affected airplane is imported and 

placed on the U.S. Register in the future, 

the required actions would take about 

21 work hours, at an average labor rate 

of $85 per work hour. Based on these 

figures, we estimate the cost of this AD 

to be $1,785 per airplane. 

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 

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. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
2286 Federal Register / Vol. 76, No. 9 / Thursday, January 13, 2011 / Proposed Rules 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2010–1309; 

Directorate Identifier 2010–NM–060–AD. 

Comments Due Date 

(a) We must receive comments by February 

28, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes, Model A340–211, 

–212, and –213 airplanes; and Model A340– 

311, –312, and –313 airplanes; all 

manufacturer serial numbers; certificated in 

any category; equipped with carbon fiber 

reinforced plastic rudders having part 

numbers and serial numbers listed in Table 

1 of this AD. 

TABLE 1—AFFECTED RUDDERS

Rudder part 

number 

Rudder 

serial number 

F554–70000–000–00 ...... TS–2013 

F554–70000–000–00 ...... TS–2015 

F554–70000–000–00 ...... TS–2016 

F554–70000–000–00 ...... TS–2017 

F554–70000–000–00 ...... TS–2018 

F554–70000–000–00 ...... TS–2020 

F554–70000–000–00 ...... TS–2021 

F554–70000–000–00 ...... TS–2024 

F554–70000–000–00 ...... TS–2026 

F554–70000–000–00 ...... TS–2035 

F554–70000–000–00 ...... TS–2036 

F554–70000–000–00 ...... TS–2040 

F554–70000–000–00 ...... TS–2042 

F554–70000–000–00 ...... TS–2055 

F554–70000–000–00 ...... TS–2056 

F554–70000–000–00 ...... TS–2058 

F554–70000–000–00 ...... TS–2059 

F554–70000–000–00 ...... TS–2061 

F554–70000–000–00 ...... TS–2062 

F554–70000–000–00 ...... TS–2063 

F554–70000–000–00 ...... TS–2065 

F554–70000–002–00 ...... TS–2074 

F554–71000–000–00 ...... TS–3003 

F554–71000–000–00 ...... TS–3004 

F554–71000–000–00 ...... TS–3005 

F554–71000–000–00 ...... TS–3006 

F554–71000–000–00 ...... TS–3007 

F554–71000–000–00 ...... TS–3008 

F554–71000–000–00 ...... TS–3011 

F554–71000–000–00 ...... TS–3015 

F554–71000–000–00 ...... TS–3033 

F554–71000–000–00 ...... TS–3061 

F554–71000–000–00 ...... TS–3064 

F554–71000–000–00 ...... TS–3066 

F554–71000–000–00 ...... TS–3071 

F554–71000–000–00 ...... TS–3072 

F554–71000–000–00 ...... TS–3075 

F554–71000–000–00 ...... TS–3079 

F554–71000–000–00 ...... TS–3084 

F554–71000–000–00 ...... TS–3087 

F554–70005–000–00 ...... TS–3100 

F554–70005–000–00 ...... TS–3106 

F554–70005–000–00 ...... TS–3107 

F554–70005–000–00 ...... TS–3119 

F554–70005–000–00 ...... TS–3124 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Surface defects were visually detected on 

the rudder of one Airbus A319 and one A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were the result of 

de-bonding between the skin and honeycomb 

core. Such reworks were also performed on 

some rudders fitted on A330–300 and A340– 

200/–300 aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability 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) Do the actions required by paragraphs 

(g)(1) through (g)(8) of this AD, in accordance 

with the Instructions of Airbus All Operators 

Telex (AOT) A330–55A3040 or A340– 

55A4036, both Revision 02, both dated 

September 30, 2009, as applicable. 

(1) In the reinforced location of the rudder: 

Within 1,800 flight hours after the rudder has 

accumulated 13,000 total flight cycles since 

first installation, or within 1,800 flight hours 

after the effective date of this AD, whichever 

is later, do a vacuum loss inspection to detect 

defects, including de-bonding between the 

skin and honeycomb core of the rudder. 

(2) In the trailing edge location of the 

rudder: Within 21 months after the rudder 

has accumulated 13,000 total flight cycles 

since first installation, or within 21 months 

after the effective date of this AD, whichever 

is later, do an elasticity laminate checker 

inspection to detect defects, including debonding between the skin and honeycomb 

core of the rudder. If no defects are found, 

repeat the inspection two times at intervals 

not to exceed 4,500 flight cycles, but not 

fewer than 4,000 flight cycles from the most 

recent inspection. 

(3) In locations other than those identified 

in paragraphs (g)(1) and (g)(2) of this AD (e.g., 

lower rib, upper edge, leading edge, and 

other locations): Within 1,800 flight hours 

after the rudder has accumulated 13,000 total 

flight cycles since first installation, or within 

1,800 flight hours after the effective date of 

this AD, whichever is later, do an elasticity 

laminate checker inspection to detect defects, 

including de-bonding between the skin and 

honeycomb core of the rudder. Repeat the 

inspection thereafter at intervals not to 

exceed 1,800 flight hours. 

(4) If no defects are found during any 

inspection required by paragraph (g)(3) of 

this AD: Within 21 months after the rudder 

has accumulated 13,000 total flight cycles 

since first installation, or within 21 months 

after the effective date of this AD, whichever 

is later, do a vacuum loss inspection on the 

other locations (e.g., lower rib, upper edge, 

leading edge, and other locations) to detect 

defects, including de-bonding between the 

skin and honeycomb core of the rudder. 

(5) Accomplishment of the inspection 

required by paragraph (g)(4) of this AD 

terminates the initial and repetitive 

inspections required by paragraph (g)(3) of 

this AD. 

(6) If any defect is found during any 

inspection required by this AD, before further 

flight, repair using a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency Airworthiness (EASA) (or its 

delegated agent). 

(7) If no defects are found during any 

inspection required by paragraphs (g)(1) and 

(g)(4) of this AD, before further flight, restore 

the vacuum loss holes by doing a temporary 

restoration with self-adhesive patches, a 

temporary restoration with resin, or a 

permanent restoration. Do the applicable 

actions specified in paragraph (g)(7)(i) or 

(g)(7)(ii) of this AD. 

(i) For airplanes on which a temporary 

restoration with patch is done: Within 900 

flight hours after the restoration, do a 

detailed inspection for defects of the restored 

area and repeat the inspection thereafter at 

intervals not to exceed 900 flight hours until 

the permanent restoration is done. Do the 

permanent restoration within 21 months after 

the temporary restoration. 

(ii) For airplanes on which a temporary 

restoration with resin is done: Within 21 

months after doing the temporary restoration, 

do the permanent restoration. 

(8) If any defect is found during any initial 

inspection required by paragraphs (g)(1), 

(g)(3), and (g)(4) of this AD, at the applicable 

time in paragraph (g)(8)(i) or (g)(8)(ii) of this 

AD: Report the inspection results to Airbus 

SAS, SEER1/SEER2/SEER3, Customer 

Services, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; fax +33 (0) 5 

61 93 28 73; or e-mail to 

region1.StructureRepairSupport@airbus.com, 

region2.StructureRepairSupport@airbus.com, 

or 

region3.StructureRepairSupport@airbus.com. 

(i) Inspections done before the effective 

date of this AD: Within 30 days after the 

effective date of this AD. 

(ii) Inspections done on or after the 

effective date of this AD: Within 30 days after 

accomplishment of the inspection. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

the service information identified in Table 2 

of this AD, are considered acceptable for 

compliance with the corresponding actions 

specified in paragraphs (g)(1) through (g)(5) 

and paragraph (g)(7) of this AD for only the 

areas inspected. For all areas, the repetitive 

inspections required by this AD remain 

applicable. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 76, No. 9 / Thursday, January 13, 2011 / Proposed Rules 2287 

TABLE 2—CREDIT SERVICE INFORMATION

Document Revision Date 

Airbus AOT A330–55A3040 ....................................................................................... Original .................................................... May 27, 2009. 

Airbus AOT A330–55A3040 ....................................................................................... 01 ............................................................. July 8, 2009. 

Airbus AOT A340–55A4036 ....................................................................................... Original .................................................... May 27, 2009. 

Airbus AOT A340–55A4036 ....................................................................................... 01 ............................................................. July 8, 2009. 

(i) For rudders on which temporary 

vacuum loss hole restoration with resin or 

permanent vacuum loss hole restoration has 

been done, as required by paragraph (g)(7) of 

this AD, in accordance with the applicable 

AOT in Table 2 of this AD before the 

effective date of this AD: Within 21 months 

after the restoration date, or within 3 months 

after the effective date of this AD, whichever 

occurs later, do an ultrasonic inspection for 

defects, including debonding of the 

reinforced area, in accordance with the 

Accomplishment Instructions of Airbus AOT 

A330–55A3040 or A340–55A4036, both 

Revision 02, both dated September 30, 2009, 

as applicable. If any defect is found, before 

further flight, repair using a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA (or 

its delegated agent). 

(j) As of the effective date of this AD, no 

person may install any rudder identified in 

Table 1 of this AD on any airplane, unless 

the rudder has been inspected and all 

applicable corrective actions have been done 

in accordance with paragraph (g) or (i) of this 

AD, as applicable. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(k) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Vladimir 

Ulyanov, Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

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

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: 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. 

Related Information 

(l) Refer to MCAI EASA Airworthiness 

Directive 2010–0021, dated February 9, 2010; 

and Airbus AOTs A330–55A3040 and A340– 

55A4036, both Revision 02, both dated 

September 30, 2009; for related information. 

Issued in Renton, Washington, on January 

5, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–586 Filed 1–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

SECURITIES AND EXCHANGE 

COMMISSION 

17 CFR Parts 240 and 249 

[Release No. 34–63347; File No. S7–35–10] 

RIN 3235–AK79 

Security-Based Swap Data Repository 

Registration, Duties, and Core 

Principles; Correction 

Correction 

In proposed rule document C1–2010– 

29719 beginning on page 79320 in the 

issue of December 20, 2010, make the 

following correction: 

On page 79320, in the second column, 

in instruction 5, footnote 165 is 

corrected to read as follows: 

165See Public Law 111–203 (adding 

Exchange Act Section 13(n)(5)(D)(i)). 

[FR Doc. C2–2010–29719 Filed 1–12–11; 8:45 am] 

BILLING CODE 8011–01–P 

DEPARTMENT OF JUSTICE 

Drug Enforcement Administration 

21 CFR Part 1308 

[Docket No. DEA–345C] 

Schedules of Controlled Substances: 

Temporary Placement of Five 

Synthetic Cannabinoids Into Schedule 

I; Correction 

AGENCY: Drug Enforcement 

Administration (DEA), U.S. Department 

of Justice. 

ACTION: Notice of Intent; correction. 

SUMMARY: On November 24, 2010, the 

Drug Enforcement Administration 

(DEA) published a Notice of Intent 

announcing its intention to temporarily 

place five synthetic cannabinoids into 

Schedule I of the Controlled Substances 

Act. This notice corrects two 

administrative errors made in that 

document. 

FOR FURTHER INFORMATION CONTACT: 

Christine A. Sannerud, PhD, Chief, Drug 

and Chemical Evaluation Section, Office 

of Diversion Control, Drug Enforcement 

Administration, 8701 Morrissette Drive, 

Springfield, VA 22152, telephone (202) 

307–7183, fax (202) 353–1263, or e-mail 

ode@dea.usdoj.gov. 

SUPPLEMENTARY INFORMATION: In a 

November 24, 2010, Notice of Intent 

published in the Federal Register (75 

FR 71635), DEA announced its intention 

to temporarily place five synthetic 

cannabinoids into schedule I of the 

Controlled Substances Act (CSA) 

pursuant to 21 U.S.C. 811(h). Due to an 

administrative error, DEA included in 

that notice a paragraph addressing the 

Regulatory Flexibility Act (RFA) in the 

‘‘Regulatory Certifications’’ section of 

that document. The provisions of the 

RFA have no application to temporary 

scheduling orders issued under 21 

U.S.C. 811(h) or to notices of intention 

to issue such orders. Accordingly, DEA 

certification under the RFA is not 


srobinson on DSKHWCL6B1PROD with PROPOSALS