55232 Federal Register / Vol. 80, No. 178 / Tuesday, September 15, 2015 / Rules and Regulations 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1013, Revision 1, dated September 29, 

1992. 

(i) New Requirement of This AD: Repetitive 

Inspections 

Within the applicable compliance times 

specified in paragraphs (i)(1) and (i)(2) of this 

AD, do a high frequency eddy current (HFEC) 

inspection for cracking of the radius of the 

rib flanges and vertical stiffener at frame 36, 

and do a rototest inspection for cracking of 

the fastener holes of the rib flanges and 

vertical stiffener, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1175, Revision 01, 

including Appendix 01, dated May 28, 2014. 

During each inspection, remove the shims 

and fasteners on the rib flange on the front 

spar side and do an HFEC inspection for 

cracking of the radius of the rib flanges and 

a rototest inspection for cracking of the 

fastener holes. If no cracking is found, 

oversize the holes of the rib flange and the 

holes of the shims, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1175, Revision 01, 

including Appendix 01, dated May 28, 2014. 

Repeat the inspections thereafter at intervals 

not to exceed 32,500 flight cycles or 65,000 

flight hours, whichever occurs first. 

(1) For airplanes having Airbus 

Modification 20976 embodied: At the later of 

the times specified in paragraphs (i)(1)(i) or 

(i)(1)(ii) of this AD. 

(i) Before exceeding 47,800 flight cycles or 

95,600 flight hours, whichever occurs first, 

since the airplane’s first flight. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(2) For airplanes on which the 

modification of the front spar of the wing 

center section was accomplished using 

Airbus Service Bulletin A320–57–1013, 

Revision 1, dated September 29, 1992: At the 

later of the times specified in paragraphs 

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

(i) Before exceeding 10,700 flight cycles or 

21,500 flight hours, whichever occurs first, 

after the modification of the rib flange on the 

front spar of the wing center section was 

done using Airbus Service Bulletin A320– 

57–1013, Revision 1, dated September 29, 

1992. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(j) Repair 

If, during any inspection required by 

paragraph (i) of this AD, any cracking is 

found, before further flight, 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). 

(k) Credit for Previous Actions 

This paragraph restates the requirements of 

Note 2 of paragraph (g) of AD 97–07–14, 

Amendment 39–9988 (62 FR 16473, April 7, 

1997): This paragraph provides credit for the 

modification of the rib flange required by 

paragraph (g) of this AD, if those actions were 

performed before May 12, 1997 (the effective 

date of AD 97–07–14), using Airbus Service 

Bulletin A320–57–1013, dated April 12, 

1989, which is not incorporated by reference 

in this AD. 

(l) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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: As of the 

effective date of this AD, 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (j) of this AD, if the 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures and tests that 

are not identified as RC are recommended. 

Those procedures and tests that are not 

identified as RC may be deviated from using 

accepted methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of an 

AMOC, provided the procedures and tests 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to procedures 

or tests identified as RC require approval of 

an AMOC. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0053, dated 

March 7, 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– 

2015–0926. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(5) and (n)(6) of this AD. 

(n) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 20, 2015. 

(i) Airbus Service Bulletin A320–57–1175, 

Revision 01, including Appendix 01, dated 

May 28, 2014. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 12, 1997 (62 FR 

16473, April 7, 1997). 

(i) Airbus Service Bulletin A320–57–1013, 

Revision 1, dated September 29, 1992. 

Note 1 to paragraph (n)(4)(i): Airbus 

Service Bulletin A320–57–1013, Revision 1, 

dated September 29, 1992, contains the 

following list of effective pages: Pages 1 

through 3 show revision level 1, dated 

September 29, 1992; pages 4 through 11 are 

from the original issue, dated April 12, 1989. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 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.airworth-eas@

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

(6) 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. 

(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 

September 2, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–22924 Filed 9–14–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0363; Directorate 

Identifier 2014–NE–08–AD; Amendment 39– 

18252; AD 2015–17–19] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

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Federal Register / Vol. 80, No. 178 / Tuesday, September 15, 2015 / Rules and Regulations 55233 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce plc (RR) RB211 Trent 768– 

60, 772–60, and 772B–60 turbofan 

engines. This AD was prompted by fuel 

leaks caused by damage to the fan case 

low-pressure (LP) fuel tube. This AD 

requires inspection of the fan case LP 

fuel tubes and associated clips and the 

fuel oil heat exchanger (FOHE) mounts 

and associated hardware. We are issuing 

this AD to prevent failure of the fan case 

LP fuel tube, which could lead to an inflight engine shutdown, loss of thrust 

control, and damage to the airplane. 

DATES: This AD is effective October 20, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 20, 2015. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, Corporate Communications, 

P.O. Box 31, Derby, England, DE248BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–249936; email: http://

www.rolls-royce.com/contact/civil_

team.jsp; Web site: https://

www.aeromanager.com. 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. It is also available on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0363. 

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– 

0363; 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 address for the 

Docket Office (phone: 800–647–5527) is 

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 FURTHER INFORMATION CONTACT: 

Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7134; fax: 781–238– 

7199; email: wego.wang@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to all RR RB211 Trent 

768–60, 772–60, and 772B–60 turbofan 

engines. The SNPRM published in the 

Federal Register on April 21, 2015 (80 

FR 22137). We preceded the SNPRM 

with a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on July 3, 2014 (79 FR 37965). 

The NPRM proposed to require 

inspection of the fan case LP fuel tubes 

and associated clips and the FOHE 

mounts and associated hardware. The 

NPRM was prompted by fuel leaks 

caused by damage to the fan case LP 

fuel tube. We are issuing this AD to 

prevent failure of the fan case LP fuel 

tube, which could lead to an in-flight 

engine shutdown, loss of thrust control, 

and damage to the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed RR Alert NonModification Service Bulletin (NMSB) 

No. RB.211–73–AH522, Revision 2, 

dated July 18, 2014; and RR Alert NMSB 

No. RB.211–73–AH837, dated 

September 9, 2014. This service 

information describes procedures for 

inspecting, and replacing if required, 

the fan case LP fuel tube and clips and 

the FOHE mounts and hardware. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or see ADDRESSES for 

other ways to access this service 

information. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(80 FR 22137, April 21, 2015). 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects about 

50 engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 6 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. We also estimate that 25 

of the engines will fail the inspection 

required by this AD. Required parts cost 

about $4,031 per engine. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $126,275. 

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 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. 

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55234 Federal Register / Vol. 80, No. 178 / Tuesday, September 15, 2015 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–17–19 Rolls-Royce plc: Amendment 

39–18252; Docket No. FAA–2014–0363; 

Directorate Identifier 2014–NE–08–AD. 

(a) Effective Date 

This AD is effective October 20, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce plc (RR) 

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

turbofan engines, if fitted with fuel tube, part 

number (P/N) FW53576, which was 

incorporated through RR production 

modification 73–F343 or which were 

modified in service in accordance with RR 

Service Bulletin (SB) No. RB.211–73–F343, 

Revision 4, dated May 26, 2011. 

(d) Reason 

This AD was prompted by fuel leaks 

caused by damage to the fan case lowpressure (LP) fuel tube. We are issuing this 

AD to prevent failure of the fan case LP fuel 

tube, which could lead to an in-flight engine 

shutdown, loss of thrust control, and damage 

to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 800 flight hours (FH) after the 

effective date of this AD, and thereafter at 

intervals not to exceed 800 FH, inspect the 

clip at the uppermost fan case LP fuel tube 

clip position, CP4881, and support bracket, 

P/N FW26692. Use Accomplishment 

Instructions, paragraph 3.A, of RR Alert NonModification Service Bulletin (NMSB) No. 

RB.211–73–AH837, dated September 9, 2014, 

or paragraph 3.A. or 3.B. of RR Alert NMSB 

No. RB.211–73–AH522, Revision 2, dated 

July 18, 2014, to do the inspection. 

(i) If the clip at the uppermost clip 

position, CP4881, fails inspection, replace 

the clip with a part eligible for installation 

and, before further flight, inspect the fan case 

LP fuel tube, P/N FW53576, for fretting, and 

clips for cracks or failure, according to 

Accomplishment Instructions, paragraph 3.A. 

of RR Alert NMSB No. RB.211–73–AH837, 

dated September 9, 2014, or paragraph 3.A. 

or 3.B. of RR Alert NMSB No. RB.211–73– 

AH522, Revision 2, dated July 18, 2014. 

(ii) If the support bracket, P/N FW26692, 

fails inspection, replace the bracket before 

further flight with a part eligible for 

installation and inspect the fan case LP fuel 

tube, P/N FW53576, and clips for cracks or 

failure. 

(2) Within 4,000 FH since new or 800 FH, 

whichever occurs later, after the effective 

date of this AD, and thereafter at intervals not 

to exceed 4,000 FH, inspect the fan case LP 

fuel tube, P/N FW53576, and clips, and the 

fuel oil heat exchanger (FOHE) mounts and 

hardware, for damage, wear, or fretting. Use 

paragraph 3.A. or 3.B., Accomplishment 

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

73–AH522, Revision 2, dated July 18, 2014, 

to do the inspection. 

(i) If the fan case LP fuel tube, P/N 

FW53576, fails inspection, before further 

flight, replace the fuel tube and clips with 

parts eligible for installation. 

(ii) If any FOHE mount or hardware shows 

signs of damage, wear, or fretting, replace the 

damaged part before further flight with a part 

eligible for installation. 

(3) At each shop visit after the effective 

date of this AD, inspect the fan case LP fuel 

tubes, P/Ns FW26589, FW36335, FW26587, 

FW53577, and FW53576, and clips, and the 

FOHE mounts and hardware, for damage, 

wear, or fretting. Use paragraphs 3.B.(1) and 

3.B.(2) of RR Alert NMSB No. RB.211–73– 

AH522, Revision 2, dated July 18, 2014, to do 

the inspection. 

(i) If any fan case LP fuel tube fails 

inspection, replace the fuel tube and clips 

before further flight with parts eligible for 

installation. 

(ii) If any FOHE mount or hardware shows 

signs of damage, wear, or fretting, replace the 

damaged part before further flight with a part 

eligible for installation. 

(4) If you replace any fan case LP fuel tube, 

clip, or FOHE mount or hardware as a result 

of the inspections in paragraphs (e)(1), (e)(2), 

or (e)(3) of this AD, you must still continue 

to perform the repetitive inspections in 

paragraphs (e)(1), (e)(2), and (e)(3) of this AD. 

(5) Any reports requested in the Alert 

NMSB accomplishment instructions 

referenced in paragraphs (e)(1), (e)(2), and 

(e)(3) of this AD are not required by this AD. 

(f) Credit for Previous Actions 

If, before the effective date of this AD, you 

performed the inspections and corrective 

actions required by paragraph (e) of this AD 

using RR NMSB No. RB.211–73–G848, 

Revision 3, dated June 12, 2014; or RR Alert 

NMSB No. RB.211–73–AH837, dated 

September 9, 2014; or paragraph 3.A. or 3.B. 

of RR Alert NMSB No. RB.211–73–AH522, 

Revision 2, dated July 18, 2014; or earlier 

versions, you met the inspection 

requirements in paragraph (e) of this AD. 

(g) Definitions 

For the purposes of this AD: 

(1) An ‘‘engine shop visit’’ is the induction 

of an engine into the shop for maintenance 

involving the separation of pairs of major 

mating engine flanges, except that the 

separation of engine flanges solely for the 

purposes of transportation without 

subsequent engine maintenance is not an 

engine shop visit. 

(2) The fan case LP fuel tubes and clips, 

and the FOHE mounts and hardware, are 

eligible for installation if they have passed 

the inspection requirements of paragraphs 

(e)(1), (e)(2), and (e)(3) of this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE–AD–AMOC@faa.gov. 

(i) Related Information 

(1) For more information about this AD, 

contact Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7134; fax: 781–238–7199; 

email: wego.wang@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0243R1, dated 

December 10, 2014 for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0363-0004. 

(3) RR NMSB No. RB.211–73–G848, 

Revision 3, dated June 12, 2014; RR Alert 

NMSB No. RB.211–73–AH837, dated 

September 9, 2014; and RR Alert NMSB No. 

RB.211–73–AH522, Revision 2, dated July 18, 

2014, or earlier versions, which are not 

incorporated by reference in this AD, can be 

obtained from RR, using the contact 

information in paragraph (j)(3) of this AD. 

(4) 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. 

(j) 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 (RR) Alert NonModification Service Bulletin (NMSB) No. 

RB.211–73–AH522, Revision 2, dated July 18, 

2014. 

(ii) RR NMSB No. RB.211–73–AH837, 

dated September 9, 2014. 

(3) For RR service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE24 8BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–249936; email: 

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

team.jsp; Internet: https://

www.aeromanager.com. 

(4) 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. 

(5) 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 Burlington, Massachusetts, on 

August 20, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21458 Filed 9–14–15; 8:45 am] 

BILLING CODE 4910–13–P 

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