Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations 65925 

(i) Boeing Special Attention Service 

Bulletin 737–57–1318, dated May 15, 2013. 

(ii) Reserved. 

(5) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. 

(6) You may view this service information 

at 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 October 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26993 Filed 10–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0593; Directorate 

Identifier 2015–NE–08–AD; Amendment 39– 

18254; AD 2015–17–21] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce plc (RR) RB211–535E4–37, 

RB211–535E4–B–37, and RB211– 

535E4–C–37 turbofan engines. This AD 

requires reducing the cyclic life limits 

for certain high-pressure turbine (HPT) 

disks, removing those disks that have 

exceeded the new life limit, and 

replacing them with serviceable parts. 

This AD was prompted by RR updating 

the life limits for certain HPT disks. We 

are issuing this AD to prevent failure of 

the HPT disk, which could result in 

uncontained disk release, damage to the 

engine, and damage to the airplane. 

DATES: This AD becomes effective 

December 2, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 2, 2015. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce 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. 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–2015–0593. 

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–2015– 

0593; 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 

(MCAI), 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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on April 29, 2015 (80 FR 

23737). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An engineering analysis, carried out by RR, 

of the lives of critical parts of the RB211– 

535E4–37 engine, has resulted in reduced 

cyclic life limits for certain high pressure 

(HP) turbine discs. The reduced limits are 

published in the RR RB211–535E4–37 Time 

Limits Manual (TLM): 05–10–01–800–000, 

current Revision dated July 2014. 

Operation of critical parts beyond these 

reduced cyclic life limits may result in part 

failure, possibly resulting in the release of 

high-energy debris, which may cause damage 

to the aeroplane and/or injury to the 

occupants. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 23737, April 29, 2015). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Task 05–00–01–800– 

000, ‘‘Recording and Control of the 

Lives of Parts’’, dated July 1, 2015, of 

the RR RB211–535E4–37/23 TLM, 

publication reference T–211(535)–6RR, 

Revision 49, dated July 1, 2015; and 

Task 05–10–01–800–000, ‘‘Group A 

Parts Lives—CONFIG–1’’, dated July 1, 

2014, of the RR RB211–535E4–37/23 

TLM, publication reference T–211(535)– 

6RR, Revision 49, dated July 1, 2015. 

This service information provides 

revised life limits for the affected HPT 

disks. 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. 

Related Service Information 

We reviewed RR Non-Modification 

Service Bulletin (NMSB) No. RB.211– 

72–G188, Revision No. 1, dated October 

30, 2013. The NMSB describes the 

updated lifing analysis of the affected 

HPT disks. 

Costs of Compliance 

We estimate that this AD affects 650 

engines installed on airplanes of U.S. 

registry. We also estimate that it would 

take about 0 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. The pro-rated cost of 

required parts would be about $12,213 

per engine. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $7,938,450. 

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. 


Lhorne on DSK5TPTVN1PROD with RULES
65926 Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations 

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), 

(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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–17–21 Rolls-Royce plc: Amendment 

39–18254; Docket No. FAA–2015–0593; 

Directorate Identifier 2015–NE–08–AD. 

(a) Effective Date 

This AD becomes effective December 2, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce plc 

(RR), RB211–535E4–37, RB211–535E4–B–37, 

and RB211–535E4–C–37 turbofan engines. 

(d) Reason 

This AD was prompted by RR updating the 

life limits for certain high-pressure turbine 

(HPT) disks. We are issuing this AD to 

prevent failure of the HPT disk, which could 

result in uncontained disk release, damage to 

the engine, and damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) After the effective date of this AD, use 

Task 05–00–01–800–000, ‘‘Recording and 

Control of the Lives of Parts’’, dated July 1, 

2015, of the Rolls-Royce (RR) RB211–535E4– 

37/23 Time Limits Manual (TLM), 

publication reference T–211(535)–6RR, 

Revision 49, dated July 1, 2015 to determine 

the new life limits for the affected engine 

models and configurations, with the 

exception of those engine models mentioned 

in paragraph (e)(2) of this AD. 

(2) For RR RB211–535E4–B–37 or RB211– 

535E4–C–37 engines with an affected HPT 

disk that was previously installed on an 

RB211–535E4–37 engine operated under 

Flight Plan A, use Task 05–10–01–800–000, 

‘‘Group A Parts Lives—CONFIG–1’’, dated 

July 1, 2014, of the RR RB211–535E4–37/23 

TLM, publication reference T–211(535)–6RR, 

Revision 49, dated July 1, 2015 to re-calculate 

equivalent cycles since new to obtain the 

new life limit. 

(3) If an affected engine model has an HPT 

disk installed with part number (P/N) 

UL27681 or UL39767, remove the affected 

HPT disk before the accumulated cyclic life 

exceeds either 19,500 flight cycles (FCs) 

under Flight Plan A, or 14,700 FCs under 

Flight Plan B, or within 25 FCs after the 

effective date of this AD, whichever occurs 

later. 

(4) For all affected engines, other than 

those specified in paragraph (e)(3) of this AD, 

remove each HPT disk before exceeding its 

applicable life limit as specified in Task 05– 

00–01–800–000, ‘‘Recording and Control of 

the Lives of Parts’’, dated July 1, 2015, of the 

RR RB211–535E4–37/23 TLM, publication 

reference T–211(535)–6RR, Revision 49, 

dated July 1, 2015; and Task 05–10–01–800– 

000, ‘‘Group A Parts Lives—CONFIG–1’’, 

dated July 1, 2014, of the RR RB211–535E4– 

37/23 TLM, publication reference T– 

211(535)–6RR, Revision 49, dated July 1, 

2015. 

(5) Install an HPT disk eligible for 

installation. 

(f) Definition 

For the purpose of this AD, a part eligible 

for installation is one with a P/N listed in 

Task 05–00–01–800–000, ‘‘Recording and 

Control of the Lives of Parts’’, dated July 1, 

2015, of the RR RB211–535E4–37/23 TLM, 

publication reference T–211(535)–6RR, 

Revision 49, dated July 1, 2015; and Task 05– 

10–01–800–000, ‘‘Group A Parts Lives— 

CONFIG–1’’, dated July 1, 2014, of the RR 

RB211–535E4–37/23 TLM, publication 

reference T–211(535)–6RR, Revision 49, 

dated July 1, 2015 with a total accumulated 

cyclic life that is less than the applicable life 

limit specified in those Tasks. 

(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. You may email your 

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

(h) 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 2014–0249R1, dated 

February 18, 2015, 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–2015–0593. 

(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) Task 05–00–01–800–000, ‘‘Recording 

and Control of the Lives of Parts’’, dated July 

1, 2015, of the Rolls-Royce (RR) RB211– 

535E4–37/23 Time Limits Manual (TLM), 

publication reference T–211(535)–6RR, 

Revision 49, dated July 1, 2015. 

(ii) Task 05–10–01–800–000, ‘‘Group A 

Parts Lives—CONFIG–1’’, dated July 1, 2014, 

of the RR RB211–535E4–37/23 TLM, 

publication reference T–211(535)–6RR, 

Revision 49, dated July 1, 2015. 

(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 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 

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. 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations 65927 

Issued in Burlington, Massachusetts, on 

August 21, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21729 Filed 10–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4207; Directorate 

Identifier 2015–NM–123–AD; Amendment 

39–18304; AD 2015–21–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–16– 

01 for certain The Boeing Company 

Model airplanes. AD 2015–16–01 

required incorporating design changes 

to improve the reliability of the cabin 

altitude warning system by installing a 

redundant cabin altitude pressure 

switch, replacing the aural warning 

module (AWM) with a new or reworked 

AWM, and changing certain wire 

bundles or connecting certain 

previously capped and stowed wires as 

necessary. For certain airplanes, AD 

2015–16–01 also required prior or 

concurrent incorporation of related 

design changes by modifying the 

instrument panels, installing light 

assemblies, modifying the wire bundles, 

and installing a new circuit breaker, as 

necessary. This AD retains all actions 

required by AD 2015–16–01. This AD 

was prompted by the discovery of a 

typographical error in AD 2015–16–01 

that referred to a nonexistent paragraph. 

We are issuing this AD to prevent the 

loss of cabin altitude warning, which 

could delay flightcrew recognition of a 

lack of cabin pressurization, and could 

result in incapacitation of the flightcrew 

due to hypoxia (a lack of oxygen in the 

body), and consequent loss of control of 

the airplane. 

DATES: This AD is effective November 

12, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 15, 2015 (80 FR 48013, 

August 11, 2015). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 7, 2012 (77 FR 

60296, October 3, 2012). 

We must receive any comments on 

this AD by December 14, 2015. 

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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https:// 

www.myboeingfleet.com. You may view 

this referenced 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. It is also available 

on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4207. 

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–2015– 

4207; 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: 

Francis Smith, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–917–6596; 

fax: 425–917–6590; email: 

Francis.Smith@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 22, 2015, we issued AD 2015– 

16–01, Amendment 39–18226 (80 FR 

48013, August 11, 2015), for certain The 

Boeing Company Model 737 airplanes. 

AD 2015–16–01 required incorporating 

design changes to improve the 

reliability of the cabin altitude warning 

system by installing a redundant cabin 

altitude pressure switch, replacing the 

AWM with a new or reworked AWM, 

and changing certain wire bundles or 

connecting certain previously capped 

and stowed wires as necessary. For 

certain airplanes, AD 2015–16–01 also 

required prior or concurrent 

incorporation of related design changes 

by modifying the instrument panels, 

installing light assemblies, modifying 

the wire bundles, and installing a new 

circuit breaker, as necessary. AD 2015– 

16–01 resulted from the report of a 

flightcrew not receiving an aural 

warning during a lack of cabin 

pressurization event. We issued AD 

2015–16–01 to prevent the loss of cabin 

altitude warning, which could delay 

flightcrew recognition of a lack of cabin 

pressurization, and could result in 

incapacitation of the flightcrew due to 

hypoxia (a lack of oxygen in the body), 

and consequent loss of control of the 

airplane. 

Actions Since AD 2015–16–01 Was 

Issued 

Since we issued AD 2015–16–01, 

Amendment 39–18226 (80 FR 48013, 

August 11, 2015), we have discovered a 

typographical error in paragraph 

(j)(1)(iii) of AD 2015–16–01. That error 

referred to paragraph (j)(4), which is a 

paragraph that does not exist in AD 

2015–16–01. The correct reference is 

paragraph (j)(1)(iv) of AD 2015–16–01. 

We have changed paragraph (j)(1)(iii) of 

this AD accordingly. 

We have also revised paragraph (g)(2) 

of this AD to remove a limitation to use 

only Boeing Special Attention Service 

Bulletin 737–21–1165, Revision 3, dated 

July 16, 2014, after the effective date of 

AD 2015–16–01, Amendment 39–18226 

(80 FR 48013, August 11, 2015). 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information: 

• Boeing Alert Service Bulletin 737– 

31A1325, Revision 2, dated June 5, 

2014. 

• Boeing Alert Service Bulletin 737– 

31A1332, Revision 4, dated October 31, 

2013. 


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