Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Rules and Regulations 32007 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0418; Directorate 

Identifier 2012–NE–12–AD; Amendment 39– 

17064; AD 2012–11–01] 

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 adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce plc (RR) RB211–Trent 800 

series turbofan engines. This AD 

requires removal from service of certain 

critical engine parts based on reduced 

life limits. This AD was prompted by RR 

adding a new flight profile and an 

associated set of life limits. 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 becomes effective June 

15, 2012. 

We must receive comments on this 

AD by July 16, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

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 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 

Operations office 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 Operations office (phone: 

800–647–5527) is the same as the Mail 

address provided 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; 

phone: 781–238–7143; fax: 781–238– 

7199; email: alan.strom@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2012– 

0051, dated March 26, 2012 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Flight Profiles (FP) define the limits of 

engine operation within which the engine 

will qualify for use of an associated set of 

Critical Parts life limits. The Rolls-Royce 

RB211–Trent 800 engine previously had 

seven such FPs and associated sets of life 

limits published in the RR Time Limits 

Manual. 

However, the results of a recent review of 

operational flight data determined that the 

existing FPs do not encompass the full range 

of Trent 800 operations. To account for the 

consequent increased rate of fatigue life 

usage on the life limited Critical Parts, a new 

FP and associated set of reduced life limits 

for Critical Parts has been developed, defined 

as FP ‘‘MAX’’, that defines a new level of 

operation which is outside the ‘‘HEAVY’’ FP, 

previously the most arduous. 

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. 

You may obtain further information by 

examining the MCAI in the AD docket. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the United Kingdom and is approved for 

operation in the United States. Pursuant 

to our bilateral agreement with the 

European Community, EASA has 

notified us of the unsafe condition 

described in the MCAI and service 

information referenced above. We are 

issuing this AD because we evaluated 

all information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because some parts may require 

immediate removal upon recalculation 

of the part lives in accordance with the 

AD. Therefore, we determined that 

notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2012–0418; 

Directorate Identifier 2012–NE–12–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 with FAA 

personnel concerning this AD. Using the 

search function of the Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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. 

mstockstill on DSK4VPTVN1PROD with RULES1

32008 Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / 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); and 

3. 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. 

4. We prepared a regulatory 

evaluation of the estimated costs to 

comply with this AD and placed it in 

the AD docket. 

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 AD: 

2012–11–01 Rolls-Royce plc: Amendment 

39–17064; Docket No. FAA–2012–0418; 

Directorate Identifier 2012–NE–12–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 15, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211–Trent 875–17, 877–17, 884–17, 884B– 

17, 892–17, 892B–17, and 895–17 turbofan 

engines. 

(d) Reason 

This AD was prompted by RR adding a 

new flight profile and an associated set of life 

limits. 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. 

(f) After the effective date of this AD, 

remove from service the parts listed by part 

number (P/N) in Table 1 of this AD before 

exceeding the new life limit indicated. 

TABLE 1—REDUCED PART LIVES—LIFE IN CYCLES USING THE MAX PROFILE

Part nomenclature P/N New life limit in 

MAX profile cycles 

(1) Low-pressure (LP) Compressor Rotor Disc ................................................................................ FK14399, FK30901 ..... 10,080. 

(2) LP Compressor Rotor Shaft ........................................................................................................ FK20840 ...................... 7,950. 

(3) Intermediate-pressure (IP) Compressor Rotor Shaft .................................................................. FK24100, FK24496 ..... 8,140. 

(4) IP Rear Shaft .............................................................................................................................. FK23564, FW18545 .... 15,000. 

(5) High-pressure (HP) Compressor Stage 1 to 4 Rotor Discs Shaft .............................................. FK24009 ...................... MAX profile cycles 

prohibited. 

(6) HP Compressor Stage 1 to 4 Rotor Discs Shaft ........................................................................ FK26167, FK32580, 

FW88724.

4,500. 

(7) HP Compressor Stage 1 to 4 Rotor Discs Shaft ........................................................................ FW11590, FW61622, 

FW88723, FW88725.

6,000. 

(8) HP Compressor Stage 5 and 6 Discs and Cone ....................................................................... FK25230, FK27899 ..... 4,500. 

(9) HP Compressor Stage 5 and 6 Discs and Cone ....................................................................... FW24633 ..................... 5,800. 

(10) HP Compressor Stage 5 and 6 Discs and Cone ..................................................................... FW24634 ..................... 5,060. 

(11) HP Turbine Rotor Disc .............................................................................................................. FK24651, FK24790 ..... 4,500. 

(12) HP Turbine Rotor Disc .............................................................................................................. FK26893 ...................... 5,540. 

(13) IP Turbine Rotor Disc ............................................................................................................... FK21117, FK33049 ..... 8,400. 

(14) IP Turbine Rotor Disc ............................................................................................................... FK33083 ...................... MAX profile cycles 

prohibited. 

(15) IP Turbine Rotor Shaft .............................................................................................................. FK23295, FK25180, 

FW18550, FW19626.

10,380. 

(16) LP Turbine Stage 1 Rotor Disc ................................................................................................. FK24971 ...................... 15,000. 

(17) LP Turbine Stage 2 Rotor Disc ................................................................................................. FK23208, FK26625 ..... 15,000. 

(18) LP Turbine Stage 3 Rotor Disc ................................................................................................. FK24199, FK26626 ..... 15,000. 

(19) LP Turbine Stage 4 Rotor Disc ................................................................................................. FK23210 ...................... 15,000. 

(20) LP Turbine Stage 5 Rotor Disc ................................................................................................. FK24200 ...................... 15,000. 

(21) LP Turbine Rotor Shaft ............................................................................................................. FK20817 ...................... 7,360. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install any IP turbine rotor discs, P/N 

FK33083, into any engine. 

(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. 

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Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Rules and Regulations 32009 

(i) Related Information 

(1) You may find additional information on 

calculating MAX Profile Cycles, in RB211 

Trent 800 Propulsion Systems Alert Service 

Bulletin (ASB) No. RB.211–72–AG801 and 

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 2012–0051, 

dated March 26, 2012, and RB211 Trent 800 

Propulsion Systems ASB No. RB.211–72– 

AG801, dated December 8, 2011, for related 

information. 

(4) 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 

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

civil_team.jsp. 

(i) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

May 16, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–13081 Filed 5–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0195; Directorate 

Identifier 2012–NE–08–AD; Amendment 39– 

17070; AD 2012–11–07] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International, Inc. Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Honeywell International, Inc. ALF502L– 

2C; ALF502R–3; ALF502R–3A; 

ALF502R–5; LF507–1F; and LF507–1H 

turbofan engines. This AD was 

prompted by two reports of engines 

experiencing uncontained release of 

low-pressure (LP) turbine blades. This 

AD requires operational checks of the 

engine overspeed trip system. We are 

issuing this AD to prevent LP turbine 

overspeed leading to uncontained 

release of the LP turbine blades and 

damage to the airplane. 

DATES: This AD is effective July 5, 2012. 

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: 

Robert Baitoo, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, 3960 Paramount Blvd., Lakewood, 

CA 90712; phone: 562–627–5245; fax: 

562–627–5210; email: 

robert.baitoo@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on March 9, 2012 (77 FR 

14312). That NPRM proposed to require 

operational checks of the engine 

overspeed trip system. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the one comment 

received. The National Transportation 

Safety Board supports the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed, except that we determined 

to not incorporate by reference the 

engine manuals for the procedures for 

operational checks of the engine 

overspeed trip system. Instead, we have 

included those procedures in the AD. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

14312, March 9, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 14312, 

March 9, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

188 Honeywell International, Inc. 

ALF502L–2C; ALF502R–3; ALF502R– 

3A; ALF502R–5; LF507–1F; and LF507– 

1H turbofan engines, installed on 

airplanes of U.S. registry. We also 

estimate that it will take about one 

work-hour to perform an operational 

check of the overspeed trip system on 

each engine. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the total cost of this 

AD for one operational check of the 

overspeed trip system to U.S. operators, 

to be $15,980. 

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. 

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