Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / Rules and Regulations 10355 

39–1917 (39 FR 28229, August 6, 1974)), and 

thereafter at intervals not to exceed 1,000 

hours’ time-in-service from the last 

inspections, accomplish the following: 

(1) Inspect all lavatory paper and linen 

waste receptacle enclosure access doors and 

disposal doors for proper operation, fit, 

sealing, and latching for the containment of 

possible trash fires. 

(2) Correct all defects found during the 

inspections required by paragraph (k)(1) of 

this AD. 

(l) Restatement of Requirements of AD 74– 

08–09 R2, Amendment 39–9680 (61 FR 

32318, June 24, 1996): Adjustments to 

Inspection Intervals 

Upon the request of an operator, the FAA 

Principal Maintenance Inspector (PMI) may 

adjust the 1,000-hour repetitive inspection 

interval specified in paragraph (k) of this AD 

to permit compliance at an established 

inspection period of the operator if the 

request contains data to justify the requested 

change in the inspection interval. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Airframe/Cabin Safety 

Branch, 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 manager of the ACO, send it 

to the attention of the person identified in the 

Related Information section of this AD. 

(2) 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. 

(n) Related Information 

For more information about this AD, 

contact Alan Sinclair, Aerospace Engineer, 

Airframe/Cabin Safety Branch, ANM–115, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; phone: 425–227–2195; fax: 425– 

227–1232; email: alan.sinclair@faa.gov. 

(o) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on January 

27, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–3973 Filed 2–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0755; Directorate 

Identifier 2010–NE–12–AD; Amendment 39– 

16956; AD 2012–04–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) RB211–Trent 800 Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all RR RB211–Trent 800 series turbofan 

engines. That AD currently requires 

removal from service of certain critical 

engine parts based on reduced life 

limits. This new AD reduces the life 

limits of additional critical engine parts. 

This AD was prompted by RR reducing 

the life limits of additional critical 

engine parts. We are issuing this AD to 

prevent the failure of critical rotating 

parts, which could result in 

uncontained failure of the engine and 

damage to the airplane. 

DATES: This AD is effective March 28, 

2012. 

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– 

44–1332–245418 or email from http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp, or download the 

publication from 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 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to supersede 

airworthiness directive (AD) 2003–16– 

18, amendment 39–13271 (68 FR 49344, 

August 18, 2003). That AD applies to 

the specified products. That SNPRM 

published in the Federal Register on 

November 7, 2011 (76 FR 68663). The 

original NPRM (75 FR 45560, August 3, 

2010) proposed to revise the Trent 800 

Time limits Manual (TLM) of the Trent 

800 engine maintenance manuals 

(EMMs). The SNPRM proposed to 

prohibit installation of one certain 

critical part and to increase the life of 

another critical part whose lives were 

previously reduced by that existing AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(76 FR 68663, November 7, 2011). 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects about 16 

RB211–Trent 800 series turbofan 

engines of U.S. registry. The average 

labor rate is $85 per work-hour, but no 

labor cost is associated with this AD 

because discs are replaced at scheduled 

maintenance intervals. Prorated cost of 

parts cost about $45,000 per engine. 

Based on these figures, we estimate the 

cost of the AD on U.S. operators to be 

$720,000. 

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: 


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10356 Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / Rules and Regulations 

‘‘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 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) 

2003–16–18, Amendment 39–13271 (68 

FR 49344, August 18, 2003) and adding 

the following new AD: 

2012–04–01 Rolls-Royce plc: Amendment 

39–16956; Docket No. FAA–2010–0755; 

Directorate Identifier 2010–NE–12–AD. 

(a) Effective Date 

This AD is effective March 28, 2012. 

(b) Affected ADs 

This AD supersedes AD 2003–16–18, 

Amendment 39–13271 (68 FR 49344, August 

18, 2003). 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211–Trent 895–17, 892–17, 892B–17, 884– 

17, 884B–17, 877–17, and 875–17 turbofan 

engines. 

(d) Unsafe Condition 

This AD was prompted by RR reporting 

changes to the lives of certain life-limited 

rotating parts. We are issuing this AD to 

prevent the failure of critical rotating parts, 

which could result in uncontained failure of 

the engine and damage to the airplane. 

(e) Actions and Compliance 

Compliance is required within 30 days 

after the effective date of this AD, unless 

already done. 

(1) After the effective date of this AD, 

remove from service the parts listed in Table 

1 of this AD before exceeding the new life 

limit indicated: 

TABLE 1—REDUCED PART LIVES

Part nomenclature Part No. 

(P/N) 

Life in standard 

duty cycles 

Life in cycles 

using the 

HEAVY profile 

(i) Intermediate-pressure (IP) Compressor Rotor Shaft ........................................................ FK24100 8,140 8,140 

(ii) IP Compressor Rotor Shaft .............................................................................................. FK24496 8,860 8,180 

(iii) High-pressure (HP) Compressor Stage 1 to 4 Rotor Discs Shaft .................................. FK24009 4,560 4,460 

(iv) HP Compressor Stage 1 to 4 Rotor Discs Shaft ............................................................ FK26167 6,340 6,000 

(v) HP Compressor Stage 1 to 4 Rotor Discs Shaft ............................................................. FK32580 8,550 6,850 

(vi) HP Compressor Stage 1 to 4 Rotor Discs Shaft ............................................................ FW11590 8,550 6,850 

(vii) HP Compressor Stage 1 to 4 Rotor Discs Shaft ........................................................... FW61622 8,550 6,850 

(viii) HP Compressor Stage 5 and 6 Discs and Cone .......................................................... FK25230 5,000 5,000 

(ix) HP Compressor Stage 5 and 6 Discs and Cone ............................................................ FK27899 5,000 5,000 

(x) IP Turbine Rotor Disc ....................................................................................................... FK21117 11,610 10,400 

(xi) IP Turbine Rotor Disc ...................................................................................................... FK33083 0 0 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any IP turbine rotor discs, P/N 

FK33083, into any engine. 

(g) 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. 

(h) Related Information 

(1) You may find additional information on 

calculating Standard Duty Cycles and/or 

using HEAVY Profile Cycles, in RR Time 

Limits Manual 05–00–01–800–801, 

Recording and Control of the Lives of Parts. 

(2) 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. 

(3) Refer to European Aviation Safety 

Agency Airworthiness Directive 2007– 

0003R1, dated January 15, 2009, and RR Alert 

Service Bulletin No. RB.211–72–AE935, 

Revision 7, dated January 19, 2009, for 

related information. 

(4) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, DE24 

8BJ, United Kingdom; phone: 011–44–1332– 

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

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

civil_team.jsp; or Web: https://www.

aeromanager.com. 

(i) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

February 10, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–3863 Filed 2–21–12; 8:45 am] 

BILLING CODE 4910–13–P 


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