Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 75833 

(2) If the HP/IP turbine bearing support oil 

feed tube outer heat shield is not present, 

accept the module as compliant. No further 

action is required. 

(g) Repetitive Inspections 

If the HP/IP turbine bearing support oil 

feed tube outer heat shield is present, 

perform repetitive inspections of the HP/IP 

turbine bearing support oil feed tube, in 

accordance with paragraphs 3.A (2)(b) 

through 3.A (2)(f) of RR ASB No. RB.211–72– 

AG873, dated February 27, 2012. 

(h) Mandatory Terminating Action 

As mandatory terminating action to the 

repetitive inspections required by this AD, 

install a revised HP/IP turbine bearing 

support structure, at the next 05 Module 

overhaul after the effective date of this AD, 

in accordance with either: 

(1) Sections 3.B (1)(a) through 3.B (1)(f) of 

RR Service Bulletin (SB) No. RB.211–72– 

F117, Revision 2, dated September 25, 2006; 

or 

(2) Sections 3.B (1)(a) through 3.B (1)(e) 

and 3.B (2)(a) of RR SB No. RB.211–72–F227, 

Revision 1, dated October 8, 2007. 

(i) Definition 

For the purpose of this AD, ‘‘next 05 

Module overhaul’’ is any time that the HP/ 

IP turbine internal oil tubes have been 

exposed and the HP/IP turbine bearing 

support oil feed tube heat shields are 

subjected to visual inspection. 

(j) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(k) Related Information 

(1) For more information about this AD, 

contact Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238 7154; fax: 781–238 7199; 

email: robert.c.morlath@faa.gov. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0201, dated September 26, 

2012, for related information. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Rolls-Royce plc Alert Service Bulletin 

No. RB.211–72–AG873, dated February 27, 

2012, approved for IBR January 10, 2013. 

(ii) Reserved. 

(3) The following service information was 

approved for IBR on December 14, 2007 (72 

FR 67568, November 29, 2007). 

(i) Rolls-Royce plc Service Bulletin No. 

RB.211–72–F117, Revision 2, dated 

September 25, 2006. 

(ii) Rolls-Royce plc Service Bulletin No. 

RB.211–72–F227, Revision 1, dated October 

8, 2007. 

(4) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ, phone: 011–44–1332– 

242424; fax: 011–44–1332–245418; or email: 

http://www.rolls-royce.com/contact/ 

civil_team.jsp. 

(5) You may view this 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. 

(6) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

December 4, 2012. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30650 Filed 12–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0858; Directorate 

Identifier 2011–NM–183–AD; Amendment 

39–17287; AD 2012–25–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Airbus Model A300 B4–2C, B4– 

103, and B4–203 airplanes; and Model 

A300 B4–601, B4–603, B4–620, B4–622, 

B4–605R, and B4–622R airplanes. That 

AD currently requires performing a onetime detailed visual inspection of the 

forward fitting at frame (FR) 40 on both 

sides of the airplane for cracks, and 

repair if necessary. This new AD 

requires repetitive detailed inspections 

of the forward fitting at FR 40 without 

nut removal, and a one-time eddy 

current or liquid penetrant inspection of 

the forward fitting at FR 40 with nut 

removal, and repair if necessary. This 

AD was prompted by reports that new 

cracks were found in the FR 40 forward 

fitting. We are issuing this AD to detect 

and correct cracking of the FR 40 

forward fitting, which could result in a 

deterioration of the structural integrity 

of the frame. 

DATES: This AD becomes effective 

January 30, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 30, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 15, 2010 (75 FR 

11435, March 11, 2010). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on August 27, 2012 (77 FR 

51717), and proposed to supersede AD 

2010–06–05, Amendment 39–16229 (75 

FR 11435, March 11, 2010). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The 

Mandatory Continuing Airworthiness 

Information (MCAI) states: 

One A300–600 aeroplane operator reported 

that, during a routine inspection, a crack was 

found in the right hand frame (FR) 40 

forward fitting between stringer 32 and 

stringer 33. The subject aeroplane had 

previously been modified in accordance with 

Airbus SB A300–57–6053 (Mod. 10453). 

Therefore and pending completion of the 

full analysis using a refined Finite Element 

Model, EASA [European Aviation Safety 

Agency] issued AD 2009–0094 [which 

corresponds with FAA AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 

11, 2010)] to require a one-time Detailed 

Visual Inspection (DVI) of the post-SB A300– 

57–6053 A300–600 aeroplanes and post-SB 

A300–53–0297 A300 aeroplanes in order to 

ensure the structural integrity of frame 40. 

During a recent maintenance check, on two 

aeroplanes (one A300B4 and one A300–600), 

cracks were found in the FR 40 forward 

fitting. 

These new crack findings are considered as 

unexpected, since they were found after: 

—Application of modification SB A300–57– 

6053 or SB A300–53–0297 which cancels 

the inspection programme, and 

—Accomplishment of EASA AD 2009–0094. 


tkelley on DSK3SPTVN1PROD with 
75834 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 

For the reasons described above, this new 

[EASA] AD, which supersedes EASA AD 

2009–0094, requires repetitive DVI of the FR 

40 forward fitting (without nut removal), 

accomplishment of a one time Eddy Current 

(EC) inspection or liquid penetrant 

inspection of this area (with nut removal) 

and, depending on findings, the 

accomplishment of associated corrective 

action [repair if any cracking found]. Passing 

the EC or liquid penetrant inspection 

constitutes terminating action for the 

repetitive DVI. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 51717, August 27, 2012), or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

about 134 products of U.S. registry. 

The actions that are required by AD 

2010–06–05, Amendment 39–16229 (75 

FR 11435, March 11, 2010), and retained 

in this AD take about 3 work-hours per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the currently 

required actions is $255 per product. 

We estimate that it will take about 3 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $34,170, or $255 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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

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 AD and placed it in the AD docket. 

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 the NPRM (77 FR 

51717, August 27, 2012), 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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) 

2010–06–05, Amendment 39–16229 (75 

FR 11435, March 11, 2010), and adding 

the following new AD: 

2012–25–06 Airbus: Amendment 39–17287. 

Docket No. FAA–2012–0858; Directorate 

Identifier 2011–NM–183–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 30, 2013. 

(b) Affected ADs 

This AD supersedes AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 

11, 2010). 

(c) Applicability 

This AD applies to Airbus airplanes, 

certificated in any category, as identified in 

paragraphs (c)(1) and (c)(2) of this AD. For 

airplanes on which Airbus Service Bulletin 

A300–53–0297 or A300–57–6053 (Airbus 

Modification 10453), as applicable, has been 

incorporated as a corrective action (repair 

following crack finding), no action is 

required by this AD. 

(1) Model A300 B4–2C, B4–103, and B4– 

203 airplanes, all serial numbers, modified 

preventively in service (without any 

preliminary crack findings), as specified in 

Airbus Service Bulletin A300–53–0297 

(Airbus Modification 10453). 

(2) Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622, and B4–622R airplanes, all 

serial numbers, modified preventively in 

service (without any preliminary crack 

findings), as specified in Airbus Service 

Bulletin A300–57–6053 (Airbus Modification 

10453). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, 57: Fuselage, Wings. 

(e) Reason 

This AD was prompted by reports that 

cracks were found in the frame (FR) 40 

forward fitting. We are issuing this AD to 

detect and correct cracking of the FR 40 

forward fitting, which could result in a 

deterioration of the structural integrity of the 

frame. 

(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 Detailed Inspection 

This paragraph restates the actions 

required by paragraphs (f)(1), (f)(2), and (f)(3) 

of AD 2010–06–05, Amendment 39–16229 

(75 FR 11435, March 11, 2010). 

(1) At the applicable time specified in table 

1 to paragraph (g)(1) of this AD: Do a onetime detailed visual inspection of the forward 

fitting at FR 40 on both sides of the airplane, 

in accordance with Airbus Mandatory 

Service Bulletin A300–57A6108 (for Model 

A300 B4–601, B4–603, B4–605R, B4–620, 

B4–622, and B4–622R airplanes) or A300– 

53A0387 (for Model A300 B4–2C, B4–103, 

and B4–203 airplanes), both including 

Appendices 01 and 02, both dated September 

12, 2008. 


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Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 75835 

TABLE 1 TO PARAGRAPH (g)(1) OF THIS AD—COMPLIANCE TIMES

Airplane models/configuration Compliance time 

A300 B4–2C and B4–103 airplanes on which Airbus Service Bulletin 

A300–53–0297 was done prior to the accumulation of 9,000 total 

flight cycles.

Prior to the accumulation of 18,000 total flight cycles, or within 3 

months after April 15, 2010 (the effective date of AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever 

occurs later. 

A300 B4–2C and B4–103 airplanes on which Airbus Service Bulletin 

A300–53–0297 was done on or after the accumulation of 9,000 total 

flight cycles.

Within 5,500 flight cycles after accomplishment of Airbus Service Bulletin A300–53–0297, or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 

11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010–06– 

05), have accumulated 11,000 flight cycles or more since accomplishment of Airbus Service Bulletin A300–53–0297, within 3 months 

after April 15, 2010 (the effective date of AD 2010–06–05). 

A300 B4–203 airplanes on which Airbus Service Bulletin A300–53– 

0297 was done prior to the accumulation of 8,300 total flight cycles.

Prior to the accumulation of 15,000 total flight cycles, or within 3 

months after April 15, 2010 (the effective date of AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever 

occurs later. 

A300 B4–203 airplanes on which Airbus Service Bulletin A300–53– 

0297 was done on or after the accumulation of 8,300 total flight cycles.

Within 4,100 flight cycles after accomplishment of Airbus Service Bulletin A300–53–0297, or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 

11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010–06– 

05), have accumulated 8,200 flight cycles or more since accomplishment of Airbus Service Bulletin A300–53–0297, within 3 months after 

April 15, 2010 (the effective date of AD 2010–06–05). 

A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes on which Airbus Service Bulletin A300–57–6053 was done 

prior to the accumulation of 6,100 total flight cycles.

Prior to the accumulation of 11,500 total flight cycles, or within 3 

months after April 15, 2010 (the effective date of AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever 

occurs later. 

A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes on which Airbus Service Bulletin A300–57–6053 was done on 

or after the accumulation of 6,100 total flight cycles.

Within 3,300 flight cycles after accomplishment of Airbus Service Bulletin A300–57–6053, or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 

11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010–06– 

05), have accumulated 6,600 flight cycles or more since accomplishment of Airbus Service Bulletin A300–57–6053, within 3 months after 

April 15, 2010 (the effective date of AD 2010–06–05). 

(2) Except as required by paragraph (g)(3) 

of this AD: If any crack is found during the 

inspection required by paragraph (g)(1) of 

this AD, before further flight, do a temporary 

or definitive repair, as applicable, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–0268, Revision 06, dated January 7, 2002 

(for Model A300 B4–2C, B4–103, and B4–203 

airplanes); or A300–57–6052, Revision 03, 

dated May 27, 2002, including Airbus 

Drawings 15R53810394, Issue A, dated 

December 21, 1998, and 21R57110247, Issue 

A, dated June 20, 1997 (for Model A300 B4– 

601, B4–603, B4–605R, B4–620, B4–622, and 

B4–622R airplanes). 

(3) If any crack found during the inspection 

required by paragraph (g)(1) of this AD 

cannot be repaired in accordance with Airbus 

Service Bulletin A300–53–0268, Revision 06, 

dated January 7, 2002 (for Model A300 B4– 

2C, B4–103, and B4–203 airplanes); or A300– 

57–6052, Revision 03, dated May 27, 2002, 

including Airbus Drawings 15R53810394, 

Issue A, dated December 21, 1998, and 

21R57110247, Issue A, dated June 20, 1997 

(for Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622, and B4–622R airplanes): 

Contact Airbus for repair instructions and, 

before further flight, repair the crack using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(h) Retained Reporting Requirement 

This paragraph restates the requirements of 

paragraph (f)(4) of AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 

11, 2010). Submit an inspection report in 

accordance with Appendix 01 of Airbus 

Mandatory Service Bulletin A300–53A0387, 

including Appendices 01 and 02, dated 

September 12, 2008 (for Model A300 B4–2C, 

B4–103, and B4–203 airplanes); or Airbus 

Mandatory Service Bulletin A300–57A6108, 

including Appendices 01 and 02, dated 

September 12, 2008 (for Model A300 B4–601, 

B4–603, B4–605R, B4–620, B4–622, and B4– 

622R airplanes); to the address identified on 

the reporting sheet, at the applicable time 

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

AD. 

(1) If the inspection was done on or after 

April 15, 2010 (the effective date of AD 

2010–06–05, Amendment 39–16229 (75 FR 

11435, March 11, 2010)): Submit the report 

within 30 days after the inspection. 

(2) If the inspection was done before April 

15, 2010 (the effective date of AD 2010–06– 

05, Amendment 39–16229 (75 FR 11435, 

March 11, 2010)): Submit the report within 

30 days after April 15, 2010 (the effective 

date of AD 2010–06–05). 

(i) New Requirement: Repetitive Detailed 

Inspections 

Within 300 flight cycles after the effective 

date of this AD: Perform a detailed inspection 

for cracks of the forward fitting at FR 40 

without nut removal on both sides of the 

airplane, in accordance with Airbus All 

Operator Telex A300–53A0391, dated August 

9, 2011 (for Model A300 B4–2C, B4–103, and 

B4–203 airplanes); or Airbus All Operator 

Telex A300–57A6111, dated August 9, 2011 

(for Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622, and B4–622R airplanes). 

Thereafter, repeat the inspection at intervals 

not to exceed 300 flight cycles. 

(j) New Requirement: Eddy Current 

Inspection or Liquid Penetrant Inspection 

Within 36 months after the effective date 

of this AD: Perform an eddy current 

inspection or a liquid penetrant inspection 

for cracks of the forward fitting at FR 40 with 

nut removal on both sides of the airplane, in 

accordance with Airbus All Operator Telex 

A300–53A0391, dated August 9, 2011 (for 

Model A300 B4–2C, B4–103, and B4–203 

airplanes); or Airbus All Operator Telex 

A300–57A6111, dated August 9, 2011 (for 

Model A300 B4–601, B4–603, B4–605R, B4– 

620, B4–622, and B4–622R airplanes). 


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75836 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 

(k) New Requirement: Corrective Action 

If, during any inspection required by 

paragraph (i) or (j) of this AD, any crack is 

detected: Before further flight, repair the 

crack in accordance with a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA, or 

EASA (or its delegated agent). 

(l) New Requirement: Reporting 

Requirement 

Submit a one-time report of the findings 

(both positive and negative) of the 

inspections required by paragraphs (i) and (j) 

of this AD to Airbus, Sebastien Faure, SEES1, 

SAS—EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 31 68; 

fax +33 5 61 93 36 14; email 

sebastien.s.faure@airbus.com, at the 

applicable time specified in paragraph (l)(1) 

or (l)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(m) New Requirement: Terminating Action 

Accomplishment of the one-time eddy 

current inspection or a liquid penetrant 

inspection required by paragraph (j) of this 

AD, including doing all applicable repairs, 

constitutes terminating action for the 

inspections required by paragraph (i) of this 

AD. 

(n) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 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. AMOCs approved previously in 

accordance with AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 

11, 2010), are approved as AMOCs for the 

corresponding provisions of 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. 

(o) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0163, dated August 30, 2011, 

and the service information specified in 

paragraphs (o)(1) through (o)(6) of this AD, 

for related information. 

(1) Airbus All Operator Telex A300– 

53A0391, dated August 9, 2011. 

(2) Airbus All Operator Telex A300– 

57A6111, dated August 9, 2011. 

(3) Airbus Mandatory Service Bulletin 

A300–57A6108, including Appendices 01 

and 02, dated September 12, 2008. 

(4) Airbus Mandatory Service Bulletin 

A300–53A0387, including Appendices 01 

and 02, dated September 12, 2008. 

(5) Airbus Service Bulletin A300–53–0268, 

Revision 06, dated January 7, 2002. 

(6) Airbus Service Bulletin A300–57–6052, 

Revision 03, dated May 27, 2002, including 

Airbus Drawings 15R53810394, Issue A, 

dated December 21, 1998, and 21R57110247, 

Issue A, dated June 20, 1997. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on January 30, 2013. 

(i) Airbus All Operator Telex A300– 

53A0391, dated August 9, 2011. (The issue 

date and document number of this document 

are specified on only the first page of the 

document.) 

(ii) Airbus All Operator Telex A300– 

57A6111, dated August 9, 2011. (The issue 

date and document number of this document 

are specified on only the first page of the 

document.) 

(4) The following service information was 

approved for IBR on April 15, 2010 (75 FR 

11435, March 11, 2010). 

(i) Airbus Mandatory Service Bulletin 

A300–57A6108, including Appendices 01 

and 02, dated September 12, 2008. 

(ii) Airbus Mandatory Service Bulletin 

A300–53A0387, including Appendices 01 

and 02, dated September 12, 2008. 

(iii) Airbus Service Bulletin A300–53– 

0268, Revision 06, dated January 7, 2002. 

(Pages 1–6, 9, 10, and 25–27 of this document 

are identified as Revision 06, dated January 

7, 2002. Pages 7, 8, 11–24, and 28–84 of this 

AD document are identified as Revision 05, 

dated June 9, 2000). 

(iv) Airbus Service Bulletin A300–57– 

6052, Revision 03, dated May 27, 2002, 

which includes Airbus Drawing 

15R53810394, Issue A, dated December 21, 

1998 and Airbus Drawing 21R57110247, 

Issue A, dated June 20, 1997. Airbus Drawing 

21R57110247, Issue A, dated June 20, 1997 

has effective pages 1 and 2, dated May 28, 

1997 and pages 3 and 4, dated June 20, 1997. 

(5) For service information identified in 

this 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(6) You may review copies of the 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

December 4, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–29992 Filed 12–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–0660; Airspace 

Docket No. 12–ANM–20] 

Establishment of Class E Airspace; 

Walsenburg, CO 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes Class 

E airspace at Spanish Peaks Airfield, 

Walsenburg, CO, to accommodate 

aircraft using new Area Navigation 

(RNAV) Global Positioning System 

(GPS) standard instrument approach 


tkelley on DSK3SPTVN1PROD with