3146 Federal Register / Vol. 82, No. 7 / Wednesday, January 11, 2017 / Rules and Regulations 

searching for and locating Docket No. FAA– 

2016–9113. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD. 

(m) 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. 

(i) Airbus Defense and Space Alert 

Operators Transmission (AOT), AOT– 

CN235–53–0002, Revision 1, dated 

September 17, 2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; email 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 

(4) 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. 

(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 Renton, Washington, on 

December 27, 2016. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–31958 Filed 1–10–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1015; Directorate 

Identifier 2013–NE–37–AD; Amendment 39– 

18768; AD 2017–01–01] 

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 

airworthiness directive (AD) 2014–05– 

25 for all Rolls-Royce plc (RR) RB211- 

Trent 970–84, RB211-Trent 970B–84, 

RB211-Trent 972–84, RB211-Trent 

972B–84, RB211-Trent 977–84, RB211- 

Trent 977B–84, and RB211-Trent 980– 

84 turbofan engines. AD 2014–05–25 

required inspections of the low-pressure 

turbine (LPT) exhaust case and support 

assembly or tail bearing housing (TBH) 

to detect cracks or damage. This AD 

modifies the inspection schedule for the 

affected engines and adds an optional 

terminating action. This AD was 

prompted by RR performing additional 

analysis of inspection results and 

determining that the existing 

inspections need to be modified. We are 

issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective January 26, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 26, 2017. 

We must receive any comments on 

this AD by February 27, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 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, DE24 8BJ; 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, 1200 District 

Avenue, Burlington, MA 01803. 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–2013– 

1015. 

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–2013– 

1015; 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 mandatory 

continuing airworthiness information, 

regulatory evaluation, any comments 

received, and other information. The 

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, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7754; fax: 781–238–7199; 

email: robert.green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

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 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–1015; Directorate Identifier 2013– 

NE–37–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. 

Discussion 

On February 27, 2014, we issued AD 

2014–05–25, Amendment 39–17798 (79 

FR 15665, March 21, 2014), ‘‘AD 2014– 

05–25,’’ for all RR RB211-Trent 970–84, 

RB211-Trent 970B–84, RB211-Trent 

972–84, RB211-Trent 972B–84, RB211- 

Trent 977–84, RB211-Trent 977B–84, 

and RB211-Trent 980–84 turbofan 

engines. AD 2014–05–25 required 

inspections of the LPT exhaust case and 

support assembly or TBH to detect 

cracks or damage. AD 2014–05–25 

resulted from an RR structural reanalysis indicating that the TBH may 

not retain full limit load capability in all 

fail-safe conditions. We issued AD 

2014–05–25 to prevent failure of the 


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Federal Register / Vol. 82, No. 7 / Wednesday, January 11, 2017 / Rules and Regulations 3147 

TBH, resulting in damage to the engine 

and to the airplane. 

Actions Since AD 2014–05–25 Was 

Issued 

Since we issued AD 2014–05–25, RR 

has analyzed inspection results and 

determined that the existing inspections 

need to be modified. Also since we 

issued AD 2014–05–25, the European 

Aviation Safety Agency (EASA) has 

issued AD 2016–0193, dated September 

30, 2016, which modifies the inspection 

schedule for the affected engines and 

adds an optional terminating action. 

Related Service Information Under 1 

CFR Part 51 

RR has issued Alert Non-Modification 

Service Bulletin (NMSB) RB.211–72– 

AG971, Revision 2, dated May 5, 2016; 

Alert NMSB RB.211–72–AH154, 

Revision 5, dated May 5, 2016; Alert 

NMSB RB.211–72–AJ101, dated May 5, 

2016; and Service Bulletin (SB) RB.211– 

72–J055, dated March 22, 2016. RR Alert 

NMSB RB.211–72–AG971 describes 

procedures for on-wing or in-shop 

inspection of the TBH mount lug runouts. RR Alert NMSB RB.211–72– 

AH154 describes procedures for an onwing or in-shop inspection of a pre-mod 

72–J024 TBH. RR Alert NMSB RB.211– 

72–AJ101 describes procedures for onwing or in-shop inspection of a postmod 72–J024 TBH. RR SB RB.211–72– 

J055 describes procedures for modifying 

the engine by introducing a revised 

TBH. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Other Related Service Information 

RR has also issued Technical Variance 

(TV) No. 124801, Issue 2, dated July 4, 

2012; TV No. 124851, Issue 2, dated July 

4, 2012; Repeater TV No. 132043, Issue 

1, dated March 25, 2013; and Repeater 

TV No. 132217, Issue 5, dated May 23, 

2013. RR TV No. 124801 and RR TV No. 

124851 provide details on the 

fluorescent penetrant inspection of the 

TBH mount lug run-outs. RR Repeater 

TV No. 132043 includes details of the 

inspection of the mount lug forging LE 

areas. RR Repeater TV No. 132217 

makes the removal and installation of 

the exhaust nozzle and forward and aft 

exhaust plugs optional tasks. 

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 modifies the inspection 

schedule for the affected engines and 

adds an optional terminating action. 

FAA’s Justification and Determination 

of the Effective Date 

No domestic operators use this 

product. 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. 

Costs of Compliance 

We estimate that this AD affects 0 

engines installed on airplanes of U.S. 

registry. We estimate the following costs 

to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection of the TBH ............................ 8 work-hours × $85 per hour = $680 $0 $680 per inspection cycle .. $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) 

2014–05–25, Amendment 39–17798 (79 

FR 15665, March 21, 2014), and adding 

the following new AD: 

2017–01–01 Rolls-Royce plc: Amendment 

39–18768; Docket No. FAA–2013–1015; 

Directorate Identifier 2013–NE–37–AD. 

(a) Effective Date 

This AD is effective January 26, 2017. 

(b) Affected ADs 

This AD replaces AD 2014–05–25, 

Amendment 39–17798 (79 FR 15665, March 

21, 2014). 

(c) Applicability 

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

RB211-Trent 970–84, RB211-Trent 970B–84, 

RB211-Trent 972–84, RB211-Trent 972B–84, 


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3148 Federal Register / Vol. 82, No. 7 / Wednesday, January 11, 2017 / Rules and Regulations 

RB211-Trent 977–84, RB211-Trent 977B–84, 

and RB211-Trent 980–84 turbofan engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7200, Engine (Turbine/Turboprop). 

(e) Unsafe Condition 

This AD was prompted by RR performing 

additional analysis of inspection results and 

determining that the existing inspections 

need to be modified. We are issuing this AD 

to prevent failure of the tail bearing housing 

(TBH), resulting in damage to the engine and 

to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within the compliance times and using 

the service information specified in Table 1 

to paragraph (f) of this AD, accomplish onwing inspections of the TBH features using 

the following instructions, as applicable. 

(i) If during any on-wing inspection of the 

TBH mount lug run-outs done using the 

Accomplishment Instructions, paragraph 

3.A.(1), of RR Alert Non-Modification Service 

Bulletin (NMSB) RB.211–72–AG971, 

Revision 2, dated May 5, 2016, any cracks 

less than or equal to 2 mm in length are 

found, remove the engine from service within 

10 flight cycles (FCs). If any cracks greater 

than 2 mm are found, remove the engine 

from service before further flight. 

(ii) If during any on-wing inspection of the 

TBH mount lug run-outs done using the 

Accomplishment Instructions, paragraph 

3.A.(2), of RR Alert NMSB RB.211–72– 

AG971, Revision 2, dated May 5, 2016, any 

crack indications resulting in an inspection 

signal with an amplitude of 50% full screen 

height or more are found, remove the engine 

from service before further flight. 

(iii) If during any on-wing inspection of a 

pre-mod 72–J024 TBH, any crack or damage 

is found on the TBH mount lug forging 

leading edge (LE) areas, re-inspect the engine 

or remove the engine from service in 

accordance with the Accomplishment 

Instructions, paragraph 3.A.(3)(t), of RR Alert 

NMSB RB.211–72–AH154, Revision 5, dated 

May 5, 2016. 

(iv) If during any on-wing inspection of a 

post-mod 72–J024 TBH, any crack is found 

on the TBH mount lug forging LE or cutback 

areas, re-inspect the engine or remove the 

engine from service in accordance with the 

Accomplishment Instructions, paragraph 

3.A.(3)(t), of RR Alert NMSB RB.211–72– 

AJ101, dated May 5, 2016. 

(2) Within the compliance times and using 

the service information specified in Table 2 

to paragraph (f) of this AD, peform in-shop 

inspections of the TBH features using the 

following instructions, as applicable. 

(i) If during any in-shop inspection of the 

TBH, any crack is found on the TBH mount 

lug or central male catcher run-outs, replace 

the TBH with a TBH eligible for installation 

before the engine is returned to service. 

(ii) If during any in-shop inspection of the 

TBH, any crack is found on the top core 

vanes, reject as unserviceable or repair the 

TBH in accordance with the 

Accomplishment Instructions, paragraph 

3.C.(1)(f), of RR Alert NMSB RB.211–72– 

AG971 Revision 2, dated May 5, 2016, before 

the engine is returned to service. 

(iii) If during any in-shop inspection of a 

pre-mod 72–J024 TBH, any crack or damage 

is found on the TBH mount lug forging LE 

areas, reject as unserviceable or repair the 

TBH in accordance with the 

Accomplishment Instructions, paragraph 

3.B.(2)(u)(ii), of RR Alert NMSB RB.211–72– 

AH154, Revision 5, dated May 5, 2016, or the 

Accomplishment Instructions, paragraph 

3.C.(1)(f), of RR Alert NMSB RB.211–72– 

AG971, Revision 2, dated May 5, 2016, before 

the engine is returned to service. 

(iv) If during any in-shop inspection of a 

post-mod 72–J024 TBH, any crack is found 

on the TBH mount lug forging LE or cutback 

areas, repair the TBH in accordance with the 

Accomplishment Instructions, paragraph 

3.B.(2)(u)(ii), of RR Alert NMSB RB.211–72– 

AJ101, dated May 5, 2016, or the 

Accomplishment Instructions, paragraph 

3.C.(1)(f), of Alert NMSB RB.211–72–AG971, 

Revision 2, dated May 5, 2016, before the 

engine is returned to service. 

TABLE 1 TO PARAGRAPH (f)—TBH ON-WING INSPECTIONS

Affected TBH P/N and feature Applicable NMSB and 

paragragph 

Alternate NMSB instructions 

acceptable for prior compliance Initial inspection 

Repeat 

inspection 

interval 

(not to 

exceed) 

All—Mount Lug Run-outs ............... RB.211–72–AG971 Revision 2, Paragraph 3.A.In-shop: RB.211–72–AG971 Revision 2, Paragraph 3.B or 3.C.Before exceeding 2,200 

FCs since new.

2,200 FCs. 

Pre-mod 72–J024 TBH—Mount 

Lug Forging LE Areas—for a 

TBH that has not exceeded 900 

FCs since new on April 7, 2014.

RB.211–72–AH154, Revision 5, Paragraph 3.A.In-shop: RB.211–72–AH154, Revision 5, Paragraph 3.B., or 

RB.211-72–AG971 Revision 2, 

Paragraph 3.C.

Before exceeding 1,000 

FCs since new.

1,000 FCs. 

Pre-mod 72–J024 TBH—Mount 

Lug Forging LE Areas—for a 

TBH that has exceeded 900 FCs 

since new on April 7, 2014.

RB.211–72–AH154, Revision 5, Paragraph 3.A.In-shop: RB.211–72–AH154, Revision 5, Paragraph 3.B., or 

RB.211-72–AG971 Revision 2, 

Paragraph 3.C.

Within 100 FCs after April 

7, 2014.

1,000 FCs. 

Post-mod 72–J024 TBH—Mount 

Lug Forging LE and Cutback 

Areas.

RB.211–72–AJ101, Paragraph 3.A.In-shop: RB.211–72–AG971, 

Revison 2, Paragraph 3.C, or 

RB.211–72–AJ101, Paragraph 

3.B.

Before exceeding 1,000 

FCs since NMSB 

RB.211-72-J024 embodiment.

1,000 FCs. 

TABLE 2 TO PARAGRAPH (f)—TBH IN-SHOP INSPECTIONS

Affected TBH P/N and feature Applicable NMSB and 

paragraph 

Alternate NMSB instructions 

acceptable for prior compliance Initial inspection 

Repeat 

inspection 

interval 

(not to 

exceed) 

All—Mount Lug Run-outs ............... RB.211–72–AG971, Revision 2, Paragraph 3.On-wing: RB.211–72–AG971 Rev 

2, Paragraph 3.A., or In-shop: 

RB.211–72–AG971 Revision 2, 

Paragraph 3.C.

Before exceeding 2,200 

flight FCs since new.

2,200 FCs. 

All—Top Core Vanes and Central 

Male Catcher Run-outs.

RB.211–72–AG971, Revision 2, Paragraph 3.C.None .............................................. Before exceeding 3,800 

FCs since new.

3.800 FCs. 


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TABLE 2 TO PARAGRAPH (f)—TBH IN-SHOP INSPECTIONS—Continued 

Affected TBH P/N and feature Applicable NMSB and 

paragraph 

Alternate NMSB instructions 

acceptable for prior compliance Initial inspection 

Repeat 

inspection 

interval 

(not to 

exceed) 

Pre-mod 72–J024 TBH—Mount 

Lug Forging LE Areas—for a 

TBH which has not exceeded 

900 FCs since new on April 7, 

2014.

RB.211–72–AH154, Revision 5, Paragraph 3.B.On-wing: RB.211–72–AH154, Revision 5, Section 3.A, or Inshop: RB.211–72–AG971, Revision 2, Paragraph 3.C.Before exceeding 1,000 

FCs since new.

1,000 FCs. 

Pre-mod 72–J024 TBH—Mount 

Lug Forging LE Areas—for a 

TBH which has exceeded 900 

FCs since new on April 7, 2014.

RB.211–72–AJ101, Paragraph 3.B.On-wing: RB.211–72–AH154 Rev 

5, Section 3.A, or In-shop: 

RB.211–72–AG971, Revision 2, 

Paragraph 3.C.

Within 100 FCs after the 

effective date of this 

AD.

1,000 FCs. 

Post-mod 72–J024 TBH—Mount 

Lug Forging LE and Cutback 

Areas.

RB.211–72–AJ101, Paragraph 3.B.On-wing: RB.211–72–AJ101, Section 3.A, or In-shop: RB.211– 

72–AG971 Rev 2, Paragraph 

3.C.

Before exceeding 1,000 

FCs since NMSB 

RB.211-72–J024 embodiment.

1,000 FCs. 

(g) Credit For Previous Actions 

(1) If you performed inspections and 

corrective actions on an engine before the 

effective date of this AD, in accordance with 

earlier versions of RR Alert NMSB RB.211– 

72–AG971, Revision 2, dated May 5, 2016, or 

RR Alert NMSB RB.211–72–AH154, Revision 

5, dated May 5, 2016, you met the 

requirements of paragraph (f)(1) or (2) of this 

AD, as applicable. 

(2) If, on or before April 7, 2014, you 

performed the inspections and corrective 

actions required by paragraphs (f)(1) and (2) 

of this AD using RR Technical Variance (TV) 

No. 124801, Issue 2, dated July 4, 2012 or 

earlier versions; or RR TV No. 124851, Issue 

2, dated July 4, 2012 or earlier versions; you 

met the requirements for a mount lug run-out 

inspection. 

(3) If, on or before April 7, 2014, you 

performed the inspections and corrective 

actions required by paragraphs (f)(1) and (2) 

of this AD using RR Repeater TV No. 132043, 

Issue 1, dated March 25, 2013 or earlier 

versions; or using RR Repeater TV No. 

132217, Issue 5, dated May 23, 2013 or 

earlier versions; you met the requirements for 

the mount lug forging LE inspections of this 

AD. 

(h) Optional Terminating Action 

(1) Accomplishment of corrective actions 

required by paragraphs (f)(1) and (2) of this 

AD does not constitute terminating action for 

the repetitive inspections required by this 

AD. 

(2) Modification of an engine in accordance 

with the instructions of RR SB RB.211–72– 

J055, dated March 22, 2016, constitutes 

terminating action for the repetitive 

inspections required by paragraphs (f)(1) and 

(2) of this AD for that engine, provided that, 

following this modification, no affected TBH 

is installed on that engine. 

(i) 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. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(j) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2016–0193, dated 

September 30, 2016, for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2013–1015. 

(3) RR TV No. 124801, Issue 2, dated July 

4, 2012; RR TV No. 124851, Issue 2, dated 

July 4, 2012, Repeater TV No. 132043, Issue 

1, dated March 25, 2013, and Repeater TV 

No. 132217, Issue 5, dated May 23, 2013; 

which are not incorporated by reference in 

this AD, can be obtained from RR using the 

contact information in paragraph (k)(3) of 

this AD. 

(k) 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) Service Bulletin 

RB.211–72–J055, dated March 22, 2016. 

(ii) RR Alert Non-Modification Service 

Bulletin (NMSB) RB.211–72–AJ101, dated 

May 5, 2016; 

(iii) RR Alert NMSB RB.211–72–AG971, 

Revision 2, dated May 5, 2016; and 

(iv) RR Alert NMSB RB.211–72–AH154, 

Revision 5, dated May 5, 2016. 

(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: 011–44–1332–245418, or email: 

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

team.jsp. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) 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 22, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2017–00398 Filed 1–10–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Parts 61, 68, and 91 

[Docket No.: FAA–2016–9157; Amdt. Nos. 

61–140, 68–1, and 91–347] 

RIN 2120–AK96 

Alternative Pilot Physical Examination 

and Education Requirements 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: This final rule will allow 

airmen to exercise pilot in command 

privileges in certain aircraft without 

holding a current medical certificate. 

This rule, which conforms FAA 

regulations with legislation, is intended 

to ensure that pilots who complete a 

medical education course, meet certain 

medical requirements, and comply with 

aircraft and operating restrictions are 

allowed to act as pilot in command for 

most part 91 operations. 


sradovich on DSK3GMQ082PROD with RULES