11976 Federal Register / Vol. 78, No. 35 / Thursday, February 21, 2013 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0624; Directorate 

Identifier 2010–NE–11–AD; Amendment 39– 

17358; AD 2013–04–01] 

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 superseding an 

existing airworthiness directive (AD) for 

all Rolls-Royce plc (RR) RB211–524 

series turbofan engines. That AD 

currently requires removal and repair of 

certain thrust reverser units (TRUs) 

prior to reinstallation. This AD requires 

the same actions for an expanded 

population of TRUs and extends the 

compliance time for repairing certain 

TRUs. This AD was prompted by 

additional engineering evaluation of 

TRUs, as a result of a translating cowl 

gearbox stubshaft failure and 

subsequent repair. We are issuing this 

AD to prevent failure of the attachment 

rivets, which may result in release of the 

TRU from the engine. 

DATES: This AD is effective March 8, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 8, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication as of 

August 12, 2011, (76 FR 40217, July 8, 

2011). 

We must receive any comments on 

this AD by April 8, 2013. 

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 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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– 

1332–249936, 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 Management Facility 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 Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7754; fax: 781–238– 

7199; email: Robert.Green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 8, 2011, we issued AD 2011– 

13–01, Amendment 39–16724 (76 FR 

40217, July 8, 2011), for all RR plc 

RB211–524 series turbofan engines. 

That AD required removal and repair of 

certain TRUs prior to reinstallation. 

That AD resulted from an investigation 

into the loss of a TRU during landing. 

The investigation revealed that the 

incident was preceded by the 

detachment of the TRU’s fixed structure 

front ring rivet lines on the rear flange. 

It was determined that the loss of rivet 

lines was directly associated with a 

previous translating cowl gearbox 

stubshaft fracture and the repair of the 

fixed structure to Engine Manual repair 

No. FRS5887. At the time, the repair 

instructed the replacement of the 

damaged section of the structure but did 

not require the rivets adjacent to the 

repair to be replaced. Subsequent 

analysis has shown that the rivets may 

have weakened as a result of the 

translating cowl gearbox stubshaft 

failure. 

Actions Since AD Was Issued 

Since we issued AD 2011–13–01, (76 

FR 40217, July 8, 2011), engineering 

evaluation by RR has concluded that the 

compliance time for repairing TRUs that 

had only Engine Manual repair No. 

FRS5887 incorporated as a result of a 

translating cowl gearbox stubshaft 

failure, can be extended. RR also 

concluded that TRUs previously 

repaired at the front ring with additional 

rivets using Engine Manual repair No. 

FRS5887 Part 2, and that have not had 

Engine Manual repair Nos. FRS4976 and 

FRS6669 applied to the rear ring at the 

No. 2 or No. 3 gearbox position, 

constitute a new population that must 

be removed and repaired during the 

next scheduled engine removal. The 

European Aviation Safety Agency 

(EASA) has notified us of this same 

unsafe condition, and corrective actions 

described in EASA AD 2012–0255, 

dated November 30, 2012. 

Relevant Service Information 

We reviewed RR Alert NonModification Service Bulletin (NMSB) 

No. RB.211–78–AG084, Revision 7, 

dated November 23, 2012. The NMSB 

describes procedures for removal, 

repair, and reinstallation of affected 

TRUs. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires removal and repair 

of TRUs that experienced a cowl 

gearbox stubshaft failure with 

subsequent repair of the fixed structure 

to Engine Manual repair No. FRS5887. 

This AD also requires removal and 

repair of TRUs previously repaired at 

the front ring with additional rivets 

using Engine Manual repair No. 

FRS5887 Part 2, and that have not had 

Engine Manual repair Nos. FRS4976 and 

FRS6669 applied to the rear ring at the 

No. 2 or No. 3 gearbox position. 

FAA’s Justification and Determination 

of the Effective Date 

The FAA has found that notice and 

comment prior to adoption of this rule 

is unnecessary because no engines are 

used on U.S. registered airplanes. 

Therefore, we find 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 provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 


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Federal Register / Vol. 78, No. 35 / Thursday, February 21, 2013 / Rules and Regulations 11977 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the Docket No. FAA– 

2011–0624 and Directorate Identifier 

2010–NE–11–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 we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD will not 

affect any engines installed on airplanes 

of U.S. registry. Therefore, we estimate 

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

be $0. 

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 

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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (14 CFR part 39) as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2011–13–01, Amendment 39–16724 (76 

FR 40217, July 8, 2011) and adding the 

following new AD: 

2013–04–01 Rolls-Royce plc: Amendment 

39–17358; Docket No. FAA–2011–0624; 

Directorate Identifier 2010–NE–11–AD. 

(a) Effective Date 

This AD is effective March 8, 2013. 

(b) Affected ADs 

This AD supersedes AD 2011–13–01, 

Amendment 39–16724 (76 FR 40217, July 8, 

2011). 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211–524D4–19, –524D4–B–19, –524D4– 

39, –524D4–B–39, –524D4X–19, –524D4X– 

B–19, –524H–36, –524H2–19, –524H–T–36, 

–524H2–T–19, –524G2–19, –524G3–19, 

–524G2–T–19, and –524G3–T–19 turbofan 

engines with thrust reverser units (TRUs) that 

have a part number (P/N) specified in 

paragraph 1.A. of RR Alert Non-Modification 

Service Bulletin (NMSB) No. RB.211–78– 

AG084, Revision 7, dated November 23, 

2012, installed. 

(d) Unsafe Condition 

This AD was prompted by additional 

engineering evaluation of TRUs, as a result of 

a translating cowl gearbox stubshaft failure 

and subsequent repair. We are issuing this 

AD to prevent failure of the attachment 

rivets, which may result in release of the 

TRU from the engine. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) If no repairs were performed as a result 

of a stubshaft failure, no further action is 

necessary. 

(2) If before December 14, 2009, the TRU 

has incorporated Engine Manual repair No. 

FRS5887 and incorporated either Engine 

Manual repair No. FRS4976 or No. FRS6669 

as a result of a translating cowl gearbox 

stubshaft failure, then repair the TRU before 

further flight. Use the procedures in Section 

3., Accomplishment Instructions, of RR Alert 

NMSB No. RB.211–78–AG084, Revision 5, 

dated February 4, 2011, to do the repair. 

(3) If before December 14, 2009, the TRU 

has incorporated Engine Manual repair No. 

FRS4976, or No. FRS6669 as a result of a 

translating cowl gearbox stubshaft failure, 

and it is not known whether Engine Manual 

repair No. FRS5887 was incorporated 

concurrently, then repair the TRU within 200 

engine flight cycles after the effective date of 

this AD. Use the procedures in Section 3., 

Accomplishment Instructions, of RR Alert 

NMSB No. RB.211–78–AG084, Revision 5, 

dated February 4, 2011, to do the repair. 

(4) If before December 14, 2009, the TRU 

has incorporated only Engine Manual repair 

No. FRS5887 as a result of a translating cowl 

gearbox stubshaft failure, then repair the TRU 

within 1,150 engine flight cycles after the 

effective date of this AD. Use the procedures 

in Section 3., Accomplishment Instructions, 

of RR Alert NMSB No. RB.211–78–AG084, 

Revision 7, dated November 23, 2012, to do 

the repair. 

(5) If the TRU has previously been repaired 

at the front ring with additional rivets using 

Engine Manual repair No. FRS5887 Part 2, 

and has not had Engine Manual repair Nos. 

FRS4976 and FRS6669 applied to the rear 

ring at the No. 2 or No. 3 gearbox position: 

(i) Remove the TRU from the engine during 

the next scheduled engine removal after the 

effective date of this AD; and 

(ii) Before returning the TRU to service, 

repair the TRU using the procedure in 

Section 3.A.(4), Accomplishment 

Instructions, of RR Alert NMSB No. RB.211– 

78–AG084, Revision 7, dated November 23, 

2012. 

(f) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(1) Actions performed before the effective 

date of this AD using RR Alert NMSB No. 

RB.211–78–AG084, Revision 4, dated 

December 22, 2009, or RR Alert NMSB No. 

RB.211–78–AG084, Revision 3, dated 

November 24, 2009, satisfy the requirements 

of paragraphs (e)(2) and (e)(3) of this AD. 

(2) Actions performed before the effective 

date of this AD using RR Alert NMSB No. 

RB.211–78–AG084, Revision 6, dated 

November 16, 2012, or Revision 5, dated 

February 4, 2011, or Revision 4, dated 

December 22, 2009, or Revision 3, dated 

November 24, 2009, satisfy the requirements 

of paragraph (e)(4) of this AD. 

(3) Actions performed before the effective 

date of this AD using RR Alert NMSB No. 

RB.211–78–AG084, Revision 6, dated 


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11978 Federal Register / Vol. 78, No. 35 / Thursday, February 21, 2013 / Rules and Regulations 

November 16, 2012, satisfy the requirements 

of paragraph (e)(5)(ii) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(h) Related Information 

(1) Refer to EASA Airworthiness Directive 

2012–0255, dated November 30, 2012, for 

related information. 

(2) Contact Robert Green, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7754; fax: 781–238– 

7199; email: Robert.Green@faa.gov, for more 

information about this AD. 

(i) 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 Non-Modification 

Service Bulletin No. RB.211–78–AG084, 

Revision 7, dated November 23, 2012. 

(ii) Reserved. 

(3) The following service information was 

approved for IBR on August 12, 2011, (76 FR 

40217, July 8, 2011). 

(i) Rolls-Royce plc Alert Non-Modification 

Service Bulletin No. RB.211–78–AG084, 

Revision 5, dated February 4, 2011. 

(ii) Reserved. 

(4) For Rolls-Royce plc 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: 011–44–1332–249936, 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 

February 7, 2013. 

Robert J. Ganley, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–03708 Filed 2–20–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1274; Directorate 

Identifier 2012–CE–042–AD; Amendment 

39–17359; AD 2013–04–02] 

RIN 2120–AA64 

Airworthiness Directives; Reims 

Aviation S.A. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Reims 

Aviation S.A. Model F406 airplanes. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued 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 improper 

material used in nose landing gear 

(NLG) attachment brackets could lead to 

failure of the NLG bracket with 

consequent damage to the airplane 

while landing. We are issuing this AD 

to require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective March 28, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 28, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

For service information identified in 

this AD, contact Reims Aviation 

Industries, Ae ́rodrome de Reims Prunay, 

51360 Prunay, France; telephone + 33 3 

26 48 46 65; fax + 33 3 26 49 18 57; 

email: stephan.lapagne@reimsaviation.fr; Internet: 

www.geciaviation.com/en/f406.html. 

You may review copies of the 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

FOR FURTHER INFORMATION CONTACT: 

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090; email: 

albert.mercado@faa.gov. 

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 December 5, 2012 (77 FR 

72252). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During the manufacturing process, RAI 

found that some of the nose landing gear 

(NLG) attachment brackets, Part Number 

(P/N) 6013119–1, were made of aluminum 

alloy, instead of steel. The results of the 

investigations showed that some of these 

aluminum alloy brackets are likely to be 

installed on aeroplanes currently in service. 

This condition, if not detected and 

corrected, could lead to failure of the NLG 

attachment bracket and jamming of the NLG 

extension/retraction mechanism, possibly 

resulting in a runway excursion and 

consequent damage to the aeroplane and 

injury to the occupants. 

For the reasons described above, this AD 

requires inspection of the NLG attachment 

bracket P/N 6013119–1 and, depending on 

findings, replacement with a serviceable 

bracket made of steel. 

In addition, as some aluminum alloy P/N 

6013119–1 NLG attachment brackets may 

have been supplied as spares, this AD also 

requires determination that the part is made 

of steel, prior to installation. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 72252, December 5, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

72252, December 5, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the (77 FR 72252, December 

5, 2012). 

Costs of Compliance 

We estimate that this AD will affect 7 

products of U.S. registry. We also 

estimate that it would take about .5 

work-hour per product to comply with 


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