Federal Register / Vol. 77, No. 127 / Monday, July 2, 2012 / Rules and Regulations 39157 

(d) Related Information 

For more information about this AD, 

contact Mark Riley, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7758; fax: 781–238–7199; 

email: mark.riley@faa.gov. 

(e) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

June 7, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–15961 Filed 6–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0748; Directorate 

Identifier 2010–NE–13–AD; Amendment 39– 

17082; AD 2012–12–03] 

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) models RB211– 

Trent 970–84, 970B–84, 972–84, 972B– 

84, 977–84, 977B–84, and 980–84 

turbofan engines. That AD currently 

requires inspecting the intermediatepressure (IP) shaft rigid coupling splines 

for wear resulting in rearward 

movement of the IP turbine. This AD 

requires the same inspections, and new 

inspections based on possible changes 

in wear rate. This AD was prompted by 

RR identifying wear beyond engine 

manual limits on the abutment faces of 

the splines. RR also determined that an 

additional IP shaft rigid coupling 

configuration requires inspection. We 

are issuing this AD to detect wear on the 

abutment faces of the splines, which 

could result in loss of disc integrity, an 

uncontained failure of the engine, and 

damage to the airplane. 

DATES: This AD is effective July 17, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 17, 2012. 

We must receive any comments on 

this AD by August 16, 2012. 

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, P.O. 

Box 31, Derby, DE24 8BJ, United 

Kingdom; phone: 011 44 1332 242424; 

fax: 011 44 1332 249936; email: http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp; or Web: https:// 

www.aeromanager.com. You may 

review copies of the referenced 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. 

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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: alan.strom@faa.gov; phone: 781– 

238–7143; fax: 781–238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 26, 2010, we issued AD 2010– 

16–07, Amendment 39–16384 (75 FR 

49368, August 13, 2010), for RR model 

RB211–Trent 970–84, 970B–84, 972–84, 

972B–84, 977–84, 977B–84, and 980–84 

turbofan engines. That AD requires 

inspecting the IP shaft rigid coupling 

splines for wear resulting in rearward 

movement of the IP turbine. That AD 

resulted from RR identifying wear 

beyond engine manual limits on the 

abutment faces of the splines on the 

Trent 900 IP shaft rigid coupling on 

several engines during engine 

disassembly. We issued that AD to 

detect wear on the abutment faces of the 

splines, which could result in loss of 

disc integrity, an uncontained failure of 

the engine, and damage to the airplane. 

Actions Since AD Was Issued 

Since we issued AD 2010–16–07 (75 

FR 49368, August 13, 2010), RR 

determined that engines that are moved 

from one position to another on the 

same airplane or to a different airplane, 

may exhibit a change in the rate of IP 

shaft rigid coupling spline wear. RR also 

determined that an additional IP shaft 

rigid coupling configuration requires 

inspection, because it also exhibits 

wear. 

Relevant Service Information 

We reviewed RR RB211 Trent 900 

Series Propulsion Systems Alert NonModification Service Bulletin (NMSB) 

No. RB.211–72–AG329, Revision 4, 

dated March 23, 2012. That Alert NMSB 

describes procedures for inspecting and 

replacing the IP shaft rigid coupling. 

We also reviewed RR RB211 Trent 

900 Series Propulsion Systems Alert 

NMSB No. RB.211–72–AG871, dated 

March 23, 2012. That Alert NMSB 

describes procedures for inspecting the 

IP shaft rigid coupling on engines that 

have incorporated RR RB211 Trent 900 

Series Propulsion Systems Service 

Bulletin (SB) No. RB.211–72–G585, 

Original Issue, or any revision. Service 

Bulletin No. RB.211–72–G585 is the SB 

that introduces the additional 

configuration that this AD adds. 

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 accomplishing the 

actions specified in the service 

information described previously. 

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. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 


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39158 Federal Register / Vol. 77, No. 127 / Monday, July 2, 2012 / Rules and Regulations 

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 the docket number 

FAA–2010–0748 and directorate 

identifier 2010–NE–13–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 affect 

no engines installed on airplanes of U.S. 

registry. We also estimate that it would 

take about 4 work-hours per engine to 

perform one borescope inspection 

required by the AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

AD on 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, 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) 

2010–16–07, Amendment 39–16384 and 

adding the following new AD: 

2012–12–03 Rolls-Royce plc: Amendment 

39–17082; Docket No. FAA–2010–0748; 

Directorate Identifier 2010–NE–13–AD. 

(a) Effective Date 

This AD is effective July 17, 2012. 

(b) Affected ADs 

This AD supersedes AD 2010–16–07, 

Amendment 39–16384 (75 FR 49368, August 

13, 2010). 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

models RB211–Trent 970–84, 970B–84, 972– 

84, 972B–84, 977–84, 977B–84, and 980–84 

turbofan engines. 

(d) Unsafe Condition 

This AD was prompted by RR identifying 

wear beyond engine manual limits on the 

abutment faces of the splines on the Trent 

900 intermediate pressure (IP) shaft rigid 

coupling on several engines during engine 

disassembly. RR also determined that engines 

that are moved from one position to another 

on the same airplane or to a different 

airplane, may exhibit a change in the rate of 

IP shaft rigid coupling spline wear. RR also 

determined that an additional IP shaft rigid 

coupling configuration requires inspection. 

We are issuing this AD to detect wear on the 

abutment faces of the splines, which could 

result in loss of disc integrity, an 

uncontained failure of the engine, and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Engines That Have Not Incorporated RR 

RB211 Trent 900 Series Propulsion Systems 

Service Bulletin (SB) No. RB.211–72–G585, 

Original Issue, or Any Revision 

(1) On-Wing Borescope Inspections 

(i) Initially borescope-inspect the IP shaft 

rigid coupling splines. Use paragraphs 

3.A.(2)(a) through 3.A.(2)(k) of RR RB211 

Trent 900 Series Propulsion Systems Alert 

Non-Modification Service Bulletin (NMSB) 

No. RB.211–72–AG329, Revision 4, dated 

March 23, 2012, to do the inspection. Inspect 

per the following: 

(A) If the IP shaft rigid coupling has 250 

or fewer flight cycles-since-new (FCSN) on 

the effective date of this AD, inspect before 

accumulating 400 FCSN; or 

(B) If the IP shaft rigid coupling has more 

than 250 FCSN on the effective date of this 

AD, inspect within 150 additional flight 

cycles. 

(ii) Repetitively borescope-inspect the IP 

shaft rigid coupling splines. Use paragraphs 

3.A.(2)(a) through 3.A.(2)(l) of RR RB211 

Trent 900 Series Propulsion Systems Alert 

NMSB No. RB.211–72–AG329, Revision 4, 

dated March 23, 2012, to determine the reinspection interval and to do the inspections. 

(iii) If during the initial or any repetitive 

inspection, the average spline crest length 

measured dimension is less than 0.5 

millimeters (mm), remove the engine from 

service before further flight. 

(2) In-Shop Inspections 

(i) At every shop visit after the effective 

date of this AD, where the IP shaft rigid 

coupling is exposed, visually inspect and 

magnetic particle inspect (MPI) the IP shaft 

rigid coupling splines. 

(ii) At every shop visit after the effective 

date of this AD, where the IP shaft rigid 

coupling is not exposed: 

(A) Inspect the IP shaft as specified in 

paragraph (f)(1) of this AD and determine the 

next inspection interval using Figure 10 of 

RR RB211 Trent 900 Series Propulsion 

Systems Alert NMSB No. RB.211–72–AG329, 

Revision 4, dated March 23, 2012; and 

(B) Reject any IP shaft with an average 

spline crest length measured dimension less 

than 1.0 mm. 

(3) After Any Shop Inspection 

After any shop inspection, where the IP 

shaft rigid coupling is exposed, perform a 

borescope inspection per paragraph (f)(1) of 

this AD within 400 cycles after the in-shop 

visual inspection and MPI. 

(4) Engine Installation 

(i) Before installing an engine in a new 

position on the same airplane, or before 

installing an engine on a different airplane in 

any position: 


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Federal Register / Vol. 77, No. 127 / Monday, July 2, 2012 / Rules and Regulations 39159 

(A) Inspect the IP shaft rigid coupling 

splines as specified in paragraphs (f)(1) or 

(f)(2) of this AD as applicable and determine 

the next inspection interval using Figure 10 

of RR RB211 Trent 900 Series Propulsion 

Systems Alert NMSB No. RB.211–72–AG329, 

Revision 4, dated March 23, 2012; and 

(B) Do not install an engine that has an IP 

shaft with an average spline crest length 

measured dimension of less than 0.5 mm. 

(ii) Before installing an engine in the same 

position on the airplane it was removed from: 

(A) Inspect the IP shaft rigid coupling 

splines using paragraph (f)(1) or (f)(2) of this 

AD as applicable and determine the next 

inspection interval; and 

(B) Do not install an engine that has an IP 

shaft with an average spline crest length 

measured dimension of less than 0.5 mm. 

(g) Engines That Have Incorporated RR 

RB211 Trent 900 Series Propulsion Systems 

SB No. RB.211–72–G585, Original Issue, or 

Any Revision 

(1) On-Wing Borescope Inspections 

(i) Initially borescope-inspect the IP shaft 

rigid coupling splines before accumulating 

400 FCSN or 400 cycles since the last 

inspection per paragraph (g)(2)(i) of this AD. 

Use paragraph 3.A.(2) of RR RB211 Trent 900 

Series Propulsion Systems Alert NMSB No. 

RB.211–72–AG871, dated March 23, 2012, to 

do the inspection. 

(ii) Repetitively borescope-inspect the IP 

shaft rigid coupling splines. Use paragraphs 

3.A.(2)(e), 3.A.(2)(f), and 3.A.(3) of RR RB211 

Trent 900 Series Propulsion Systems Alert 

NMSB No. RB.211–72–AG871, dated March 

23, 2012, to determine the re-inspection 

interval and to do the inspections. 

(2) In-Shop Inspections 

(i) At every shop visit after the effective 

date of this AD, where the IP shaft rigid 

coupling is exposed, visually inspect and 

MPI the IP shaft rigid coupling splines. 

(ii) At every shop visit after the effective 

date of this AD, where the IP shaft rigid 

coupling is not exposed, borescope-inspect 

using paragraphs 3.A.(2)(a) through 3.A.(2)(f) 

of RR RB211 Trent 900 Series Propulsion 

Systems Alert NMSB No. RB.211–72–AG871, 

dated March 23, 2012. 

(A) If at the time of initial inspection, the 

average value of length ‘‘B’’ is equal to, or 

less than, 6.00 mm, repeat the borescope 

inspection using paragraph (g)(1) or (g)(2) of 

this AD within 400 flight cycles. 

(B) If at the time of initial inspection the 

average value of length ‘‘B’’ is greater than 

6.00 mm, MPI the IP turbine shaft, and 

visually inspect and MPI the intermediate 

turbine shaft and IP rigid coupling. 

(3) After Any Shop Inspection 

After any shop inspection, where the rigid 

shaft coupling is exposed, perform a 

borescope inspection per paragraph (g)(1) of 

this AD within 400 cycles after the in-shop 

visual inspection and MPI. 

(h) Definition 

For the purpose of this AD, a 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 does not 

constitute an engine shop visit. 

(i) Credit for Previous Actions for Engines 

That Have Not Incorporated RR RB211 

Trent 900 Series Propulsion Systems SB No. 

RB.211–72–G585 

If you performed inspections and 

corrective actions that are required by 

paragraph (f) of this AD using RR RB211 

Trent 900 Series Propulsion Systems Alert 

NMSB No. RB.211–72–AG329, Original 

Issue, dated November 26, 2009; Revision 1, 

dated January 13, 2010; Revision 2, dated 

July 7, 2010; or Revision 3, dated November 

25, 2010, before the effective date of this AD, 

you have met the requirements of paragraph 

(f) of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(k) Related Information 

(1) For more information about this AD, 

contact Alan Strom, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7143; fax: 781–238–7199; 

email: alan.strom@faa.gov. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0057, dated April 3, 2012, 

and AD 2012–0057 (corrected), dated April 

20, 2012, for related information. 

(3) RB211–Trent 900 Engine Manual, tasks 

72–33–21–200–804 and 72–00–00–200–808, 

pertain to the visual inspections and MPIs 

required by this AD. 

(l) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information: 

(i) Rolls-Royce plc RB211 Trent 900 Series 

Propulsion Systems Alert Non-Modification 

Service Bulletin No. RB.211–72–AG329, 

Revision 4, dated March 23, 2012. 

(ii) Rolls-Royce plc RB211 Trent 900 Series 

Propulsion Systems Alert Non-Modification 

Service Bulletin No. RB.211–72–AG871, 

dated March 23, 2012. 

(2) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ, phone: 011–44–1332– 

242424; fax: 011–44–1332–245418, or email: 

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

civil_team.jsp. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

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

(4) You may also review copies of the 

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/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

June 5, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–15985 Filed 6–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0441; Directorate 

Identifier 2012–CE–011–AD; Amendment 

39–17106; AD 2012–13–04] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileria de Aerona ́utica S.A. 

(EMBRAER) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Empresa Brasileria de Aerona ́utica S.A. 

(EMBRAER) Model EMB–505 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 an inadequate 

amount of drain holes in the primary 

control surfaces (rudder, elevator, and 

aileron) and their tab surfaces, which 

may allow water to accumulate in the 

control surfaces. This condition could 

cause unbalanced flight control surfaces 

and reduced flutter margins, which 

could result in loss of control of the 

airplane. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective August 6, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 6, 2012. 

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. 


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