77972 Federal Register / Vol. 79, No. 248 / Monday, December 29, 2014 / Proposed Rules 

The Boeing Company: Docket No. FAA– 

2014–0929; Directorate Identifier 2014– 

NM–118–AD. 

(a) Comments Due Date 

We must receive comments by February 

12, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200, –300, –300F, and –400ER 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

767–53A0251, dated August 7, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports that six 

fasteners may not have been installed in the 

left and right stringer 37 (S–37) between body 

station 428 and 431 lap splices on certain 

airplanes. We are issuing this AD to detect 

and correct missing fasteners, which could 

result in cracks in the fuselage skin that 

could adversely affect the structural integrity 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections, Related Investigative 

Actions, and Corrective Actions 

Except as provided by paragraph (h)(2) of 

this AD, at the applicable time specified in 

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

Alert Service Bulletin 767–53A0251, dated 

August 7, 2013: Do an external general visual 

inspection of the S–37 lap splice for missing 

fasteners, and do all applicable related 

investigative and corrective actions; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0251, dated August 7, 2013, except 

as provided by paragraph (h)(1) of this AD. 

Do all applicable related investigative and 

corrective actions before further flight. 

(h) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

767–53A0251, dated August 7, 2013, 

specifies to contact Boeing for repair 

instructions: Before further flight, do the 

repair using an FAA-approved method. 

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

Boeing Alert Service Bulletin 767–53A0251, 

dated August 7, 2013, specifies a compliance 

time ‘‘after the original issue date of this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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) Except as required by paragraph (h)(1) 

of this AD: If the service information contains 

steps that are labeled as RC, those steps must 

be done to comply with this AD; any steps 

that are not labeled as RC are recommended. 

Those steps that are not labeled as RC may 

be deviated from, done as part of other 

actions, or done using accepted methods 

different from those identified in the 

specified service information without 

obtaining approval of an AMOC, provided 

the steps labeled as RC can be done and the 

airplane can be put back in a serviceable 

condition. Any substitutions or changes to 

steps labeled as RC require approval of an 

AMOC. 

(j) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6590; 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, WA 98124–2207; telephone 20–544– 

5000, extension 1; fax 206–766–5680; 

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

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

December 17, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–30271 Filed 12–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0928; Directorate 

Identifier 2014–NM–040–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A330–200 Freighter, 

A330–200, A330–300, A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. This proposed AD was 

prompted by a report of skin disbonding 

on a composite side panel of a rudder 

installed on an A310 airplane. This 

proposed AD would require a review of 

the maintenance records of the rudder 

to determine if any composite side shell 

panel repair has been done; a 

thermography inspection limited to the 

repair areas or complete side shells, as 

applicable, to identify possible inservice rudder repairs, damages, or fluid 

ingress; and applicable related 

investigative and corrective actions. We 

are proposing this AD to detect and 

correct the rudder skin disbonding, 

which could affect the structural 

integrity of the rudder, and could result 

in reduced controllability of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by February 12, 2015. 

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 

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 

W12–140, 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, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 248 / Monday, December 29, 2014 / Proposed Rules 77973 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

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

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. 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 by searching for 

and locating Docket No. FAA–2014– 

0928; 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 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, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0928; Directorate Identifier 

2014–NM–040–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2014–0033, 

dated February 4, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A330–200 

Freighter, A330–200, A330–300, A340– 

200, A340–300, A340–500, and A340– 

600 series airplanes. The MCAI states: 

A case of skin disbonding was reported on 

a composite side panel of a rudder installed 

on an A310 aeroplane. 

The investigation results revealed that this 

disbonding started from a skin panel area 

previously repaired in-service in accordance 

with the Structural Repair Manual (SRM). 

The initial damage has been identified as 

a disbonding between the core and skin of 

the repaired area. This damage may not be 

visually detectable and likely propagates 

during normal operation due to the variation 

of pressure during ground-air-ground cycles. 

Composite rudder side shell panels are also 

installed on A330 and A340 aeroplanes, 

which may have been repaired in-service 

using a similar method. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the rudder, possibly resulting in reduced 

control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires a one-time 

thermography inspection of a repaired rudder 

or a rudder whose maintenance records are 

incomplete and, depending on findings, 

accomplishment of applicable corrective and 

follow-up actions [including repetitive 

inspections. 

The related investigative actions in 

this AD include, as applicable, an 

ultrasonic inspection, an elasticity 

laminate checker inspection, a tap test 

inspection, detailed inspections, 

thermography inspections, and 

ventilation of the core. The repetitive 

inspections include detailed inspections 

and thermography inspections. The 

corrective actions in this AD include 

repairs. 

The compliance time for the related 

investigative actions is before further 

flight after accomplishing the applicable 

inspection required by paragraph (g)(1) 

or (g)(2)(ii) of this AD. 

The intervals for the repetitive 

inspections are either 900 flight hours or 

1,000 flight cycles, depending on the 

applicable conditions identified in the 

service information. 

The compliance times for the 

corrective actions range, depending on 

the applicable conditions identified in 

the service information, from before 

further flight to within 4,500 flight 

cycles but not to exceed 24 months after 

accomplishing the applicable inspection 

required by paragraphs (g)(1) or (g)(2)(ii) 

of this AD. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0928. 

Relevant Service Information 

Airbus has issued the following 

service information: 

• Airbus Service Bulletin A330–55– 

3043, dated February 7, 2013. 

• Airbus Service Bulletin A340–55– 

4039, dated February 7, 2013. 

• Airbus Service Bulletin A340–55– 

5007, dated February 7, 2013. 

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 these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 55 airplanes of U.S. registry. 

We also estimate that it would take 

about 45 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $210,375, or $3,825 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to 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 control 

number for the collection of information 

required by this proposed AD is 2120– 

0056. The paperwork cost associated 

with this proposed AD has been 

detailed in the Costs of Compliance 

section of this document and includes 

time for reviewing instructions, as well 

as completing and reviewing the 

collection of information. Therefore, all 

reporting associated with this proposed 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
77974 Federal Register / Vol. 79, No. 248 / Monday, December 29, 2014 / Proposed Rules 

AD is 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. 

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. 

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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2014–0928; 

Directorate Identifier 2014–NM–040–AD. 

(a) Comments Due Date 

We must receive comments by February 

12, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) Airbus Model A330–201, –202, –203, 

–223, –223F, –243, –243F, –301, –302, –303, 

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

airplanes, all manufacturer serial numbers. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, –313, –541, and –642 airplanes, 

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Reason 

This AD was prompted by a report of skin 

disbonding on a composite side panel of a 

rudder installed on an A310 airplane. We are 

issuing this AD to detect and correct the 

rudder skin disbonding, which could affect 

the structural integrity of the rudder, and 

could result in reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Review the Maintenance Records 

Within 24 months after the effective date 

of this AD: Review the maintenance records 

of the rudder to determine if any composite 

side shell panel repair has been 

accomplished on the rudder since first 

installation on an airplane. 

(1) If, based on the maintenance record 

review, any repair identified in Figure A– 

GBBAA (Sheet 01 and 02) or Figure A– 

GBCAA (Sheet 02) of the service information 

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

(g)(1)(iii) of this AD is found: Within 24 

months after the effective date of this AD, do 

a thermography inspection for repair, 

damages, and fluid ingress, limited to the 

repaired areas, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraphs (g)(1)(i) through (g)(1)(iii) of this 

AD: 

(i) Airbus Service Bulletin A330–55–3043, 

dated February 7, 2013 (for Model A330–201, 

–202, –203, –223, –223F, –243, –243F, –301, 

–302, –303, –321, –322, –323, –341, –342, 

and –343 airplanes). 

(ii) Airbus Service Bulletin A340–55–4039, 

dated February 7, 2013 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes). 

(iii) Airbus Service Bulletin A340–55– 

5007, dated February 7, 2013 (for Model 

A340–541 and –642 airplanes). 

(2) For a rudder for which maintenance 

records are unavailable or incomplete, do the 

actions specified in paragraph (g)(2)(i) and 

(g)(2)(ii) of this AD: 

(i) No later than 3 months before 

accomplishment of the thermography 

inspection, as required by paragraph (g)(2)(ii) 

of this AD, contact Airbus to request related 

rudder manufacturing reworked data by 

submitting the serial number of the rudder to 

Airbus. 

(ii) Within 24 months after the effective 

date of this AD: Do a thermography 

inspection for any repair on complete side 

shells to identify and mark any repair, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD. 

(h) Related Investigative Actions, Corrective 

Actions, and Repetitive Inspections 

After the inspection as required by 

paragraph (g)(1) or (g)(2) of this AD: At the 

applicable compliance times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Tables 3, 

4A, 4B, 4C, 4D, and 5 of the applicable 

service information specified in paragraphs 

(g)(1)(i) through (g)(1)(iii) of this AD, 

accomplish all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD; except as 

provided by paragraphs (i)(1) and (i)(2) of 

this AD. Options provided in the service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD for 

accomplishing the actions are acceptable for 

the corresponding requirements of this 

paragraph provided that the related 

investigative and corrective actions are done 

at the applicable times specified in paragraph 

1.E., ‘‘Compliance,’’ of the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD, including 

applicable repetitive inspection intervals. 

Thereafter repeat the inspections of the 

restored and repaired areas at the applicable 

compliance time specified in paragraph 1.E., 

‘‘Compliance,’’ of Tables 3, 4A, 4B, 4C, 4D, 

and 5 of the applicable service information 

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

(g)(1)(iii) of this AD. 

(i) Exceptions to the Service Information 

(1) Where the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD specifies a 

compliance time relative to the date of the 

service information, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) If the service information in paragraphs 

(g)(1)(i) through (g)(1)(iii) of this AD specifies 

to contact Airbus: At the applicable 


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Federal Register / Vol. 79, No. 248 / Monday, December 29, 2014 / Proposed Rules 77975 

compliance times specified in paragraph 1.E., 

‘‘Compliance,’’ of the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(j) Provisions for Certain Airplanes 

Airplanes fitted with a rudder having a 

serial number (S/N) that is not in the range 

of S/N TS–1001 through S/N TS–1043 

inclusive, S/N TS–2001 through S/N TS– 

2074 inclusive, S/N TS–3000 through S/N 

TS–3525 inclusive, S/N TS–4001 through S/ 

N TS–4170 inclusive, S/N TS–6001 through 

S/N TS–6246 inclusive, or S/N TS–5001 

through S/N TS–5138 inclusive, are not 

affected by the requirements of paragraphs (g) 

and (h) of this AD provided that it is 

determined that no repair has been 

accomplished on the composite side shell 

panel of that rudder since first installation on 

the airplane. 

(k) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install, on any airplane, a rudder, 

unless the record review and thermography 

inspection specified in paragraph (g) of this 

AD has been done on that rudder and 

thereafter all applicable related investigative 

actions, repetitive inspections, and corrective 

actions are done as required by paragraph (h) 

of this AD, except as provided in paragraph 

(j) of this AD. 

(l) Repair Prohibition 

As of the effective date of this AD, no 

person may accomplish a side shell repair on 

any rudder using a structure repair manual 

procedure identified in Figure A–GBBAA 

(Sheet 01 and 02) or Figure A–GBCAA (Sheet 

02) of the service information specified in 

paragraphs (g)(1)(i) through (g)(1)(iii) of this 

AD, as applicable, on any airplane. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0033, dated 

February 4, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0928. 

(2) For service information identified in 

this 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; email 

airworthiness.A330-A340@airbus.com; 

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

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

December 17, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–30270 Filed 12–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

SECURITIES AND EXCHANGE 

COMMISSION 

17 CFR Chapter II 

[Release Nos. 33–9694, 34–73891, 39–2500, 

IC–31389; IA–3986; File No. S7–13–14] 

List of Rules To Be Reviewed Pursuant 

to the Regulatory Flexibility Act 

AGENCY: Securities and Exchange 

Commission. 

ACTION: Publication of list of rules 

scheduled for review. 

SUMMARY: The Securities and Exchange 

Commission is publishing a list of rules 

to be reviewed pursuant to Section 610 

of the Regulatory Flexibility Act. The 

list is published to provide the public 

with notice that these rules are 

scheduled for review by the agency and 

to invite public comment on whether 

the rules should be continued without 

change, or should be amended or 

rescinded to minimize any significant 

economic impact of the rules upon a 

substantial number of such small 

entities. 

DATES: Comments should be submitted 

by January 28, 2015. 

ADDRESSES: Comments may be 

submitted by any of the following 

methods: 

Electronic Comments 

• Use the Commission’s Internet 

comment form (http://www.sec.gov/

rules/other.shtml); or 

• Send an email to rule-comments@

sec.gov. Please include File Number S7– 

13–14 on the subject line; or 

• Use the Federal eRulemaking Portal 

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

instructions for submitting comments. 

Paper Comments 

• Send paper comments to Brent 

Fields, Secretary, Securities and 

Exchange Commission, 100 F Street NE., 

Washington, DC 20549–1090. 

All submissions should refer to File No. 

S7–13–14. This file number should be 

included on the subject line if email is 

used. To help us process and review 

your comments more efficiently, please 

use only one method. The Commission 

will post all comments on the 

Commission’s Internet Web site (http:// 

www.sec.gov/rules/other.shtml). 

Comments also are available for Web 

site viewing and printing in the 

Commission’s Public Reference Room, 

100 F Street NE., Washington, DC 20549 

on official business days between the 

hours of 10:00 a.m. and 3:00 p.m. All 

comments received will be posted 

without change; we do not edit personal 


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