Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 75831 

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/ibr-locations.html. 

Issued in Renton, Washington, on 

December 5, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30305 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–2012–1198; Directorate 

Identifier 2012–NE–35–AD; Amendment 39– 

17289; AD 2012–25–08] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

serial numbers (S/Ns) of Rolls-Royce plc 

(RR) RB211-Trent 768–60, 772–60, and 

772B–60 turbofan engines. This AD 

requires initial and repetitive on-wing 

or in-shop inspections of the high 

pressure/intermediate pressure (HP/IP) 

turbine bearing support oil feed tube 

outer heat shield. This AD also requires 

installation of a revised HP/IP turbine 

bearing support structure as terminating 

action to the repetitive inspections of 

the HP/IP turbine bearing support oil 

feed tube outer heat shield. This AD was 

prompted by a report of high oil 

consumption due to an oil leak from the 

HP/IP turbine bearing support oil feed 

tube. We are issuing this AD to prevent 

failure of the HP turbine disc, 

uncontained engine failure, and damage 

to the airplane. 

DATES: This AD becomes effective 

January 10, 2013. 

We must receive comments on this 

AD by February 11, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication as of January 10, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications as of 

December 14, 2007 (72 FR 67568, 

November 29, 2007). 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

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. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803. 

For information on the availability of 

this material at the FAA, call 781–238– 

7125. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

800–647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2012– 

0201, dated September 26, 2012 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

In August 2011, a Trent 700 engine was 

removed for high oil consumption, which 

was found to have been caused by a small 

hole in the oil feed tube of the High Pressure/ 

Intermediate Pressure (HP/IP) Bearing 

Support. The hole was the result of frettage 

(chafing) with a fractured outer heat shield. 

This is a known problem and recognized 

unsafe condition that has re-emerged having 

been previously addressed by EASA AD 

2007–0260R1. 

Investigation by RR revealed a build error 

that, in contradiction to the build records, the 

previous configuration of outer heat shield 

(Pre-Service Bulletin (SB) 72–F117 standard) 

was fitted on the oil feed tube service pipe 

of the HP/IP structure. As the build error may 

have been reproduced several times, it is 

assumed that further post-SB 72–F117 

standard structures may be in service with 

pre-SB 72–F117 outer heat shields fitted to 

the oil feed tube. 

The frettage on the oil feed tube within the 

HP/IP turbine bearings support structure 

results from contact with the fracture edges 

of the tubes outermost heat shield, which has 

been found to fracture under thermal cycling 

and then to chafe against the oil tube with 

the potential to cause holes and consequent 

oil leaks. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

On November 20, 2007, we issued AD 

2007–24–09 (72 FR 67568, November 

29, 2007) which corresponds with 

EASA AD 2007–0260R1. Our AD has a 

mandatory terminating action date of 

May 31, 2010, however, there were, and 

currently are, no U.S. operators of the 

engines affected by those ADs. Those 

ADs are only applicable to engines that 

do not incorporate Modification 

Standard 72–F117. Since those ADs 

were issued, EASA has issued AD 2012– 

0201 that is applicable to a specific set 

of engines that may have had 

Modification Standard 72–F117 

incorporated incorrectly. EASA did not 

supersede EASA AD 2007–0260R1 with 

EASA AD 2012–0201 because EASA AD 

2012–0201 only affects a very specific 

population of engines that, having 

incorporated Modification Standard 72– 

F117, either correctly or incorrectly, are 

no longer affected by EASA AD 2007– 

0260R1. We are issuing our AD as a 

standalone document for the same 

reasons. This new AD also is applicable 

only to the engines specified in the 

MCAI, none of which are currently 

registered to U.S. operators. Also, this 

new AD lists certain service bulletins 

that were previously incorporated by 

reference in AD 2007–24–09. 

Relevant Service Information 

RR has issued Alert Service Bulletin 

No. RB.211–72–AG873, dated February 

27, 2012. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 


tkelley on DSK3SPTVN1PROD with 
75832 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the United Kingdom and is approved for 

operation in the United States. Pursuant 

to our bilateral agreement with the 

European Community, EASA has 

notified us of the unsafe condition 

described in the MCAI and service 

information referenced above. We are 

issuing this AD because we evaluated 

all information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. 

FAA’s Determination of the Effective 

Date 

No domestic operators use any of the 

RB211-Trent 768–60, 772–60, and 

772B–60 turbofan engines listed by S/N 

in this AD. Therefore, we find that 

notice and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2012–1198; 

Directorate Identifier 2012–NE–35–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 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); 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 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. 

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 adding 

the following new AD: 

2012–25–08 Rolls-Royce plc: Amendment 

39–17289; Docket No. FAA–2012–1198; 

Directorate Identifier 2012–NE–35–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 10, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211 Trent 768–60, 772–60, and 772B–60 

turbofan engines with serial numbers (S/Ns) 

listed in Table 1 to paragraph (c) of this AD. 

TABLE 1 TO PARAGRAPH (C)—AFFECTED ENGINE S/NS

41221 41435 41446 41459 41465 

41425 41437 41451 41460 41466 

41428 41438 41452 41461 41468 

41430 41440 41454 41462 41469 

41431 41442 41455 41463 41470 

41432 41445 41456 41464 41471 

(d) Reason 

This AD was prompted by a report of high 

oil consumption due to an oil leak from the 

high pressure/intermediate pressure (HP/IP) 

turbine bearing support oil feed tube. We are 

issuing this AD to prevent a failure of the HP 

turbine disc, uncontained engine failure, and 

damage to the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(f) Initial Inspection 

(1) Initially inspect the HP/IP turbine 

bearing support oil feed tube within the 

compliance times specified in paragraphs 

1.D.(1)(a) through 1.D.(1)(a)(ii) of RR Alert 

Service Bulletin (ASB) No. RB.211–72– 

AG873, dated February 27, 2012. Perform the 

initial inspection in accordance with 

paragraphs 3.A (1)(a) through 3.A (1)(j) of RR 

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

27, 2012. 


tkelley on DSK3SPTVN1PROD with 
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