Federal Register / Vol. 76, No. 215 / Monday, November 7, 2011 / Proposed Rules 68663 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2010–03–06, Amendment 39–16189 (75 

FR 5689, February 4, 2010), and adding 

the following new AD: 

Turbomeca S.A.: Docket No. FAA–2009– 

0889; Directorate Identifier 2009–NE– 

35–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by January 6, 2012. 

(b) Affected ADs 

This AD supersedes AD 2010–03–06, 

Amendment 39–16189 (75 FR 5689, February 

4, 2010). 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

Arriel 2B and 2B1 turboshaft engines. 

(d) Unsafe Condition 

This AD was prompted by three additional 

cases of uncoupling of the high-pressure/lowpressure (HP/LP) pump hydro-mechanical 

metering unit (HMU) LP fuel pump impeller 

and the HP fuel pump shaft, since AD 2010– 

03–06 (75 FR 5689, February 4, 2010) was 

issued. However, these failures were in 

HMUs that were modified to post-TU 147 

configuration HMUs. The investigation 

indicates that these HMUs may also need to 

be replaced. We are issuing this AD to 

prevent reduced engine power or, at worst, 

an uncommanded in-flight shutdown, which 

can result in a forced autorotation landing or 

accident. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Check the transmissible torque between 

the LP fuel pump impeller and the HP fuel 

pump shaft as follows: 

(i) For HMUs that do not incorporate 

Modification TU 147, check the torque before 

accumulating 500 engine flight hours (EFH) 

since March 11, 2010 (the effective date of 

AD 2010–03–06 (75 FR 5689, February 4, 

2010)). Use Paragraph 2 of Turbomeca Alert 

Mandatory Service Bulletin (MSB) No. A292 

73 2830, Version B, dated July 10, 2009, to 

do the check. 

(ii) For HMUs that incorporate 

Modification TU 147 and which Modification 

TU 147 was applied on or before March 31, 

2010, and the HMUs are not listed in Figures 

2 or 3 of Turbomeca Alert MSB No. A292 73 

2836, Version A, dated August 17, 2010, 

check the torque within 750 EFH from the 

effective date of this AD, but no later than 14 

months after the effective date of this AD. 

Use Paragraph 2 of Turbomeca Alert MSB 

No. A292 73 2836, Version A, dated August 

17, 2010, to do the check. 

(2) If the HMU does not pass the torque 

check, then replace the HMU with an HMU 

that is eligible for installation. 

(f) HMU Reinstallation 

Do not install any HMU removed from 

service by this AD until it has been checked 

in accordance with Paragraph 2 of 

Turbomeca Alert MSB No. A292 73 2836, 

Version A, dated August 17, 2010, or checked 

in accordance with Paragraph 2 of 

Turbomeca Alert MSB No. A292 73 2830, 

Version B, dated July 10, 2009, and found 

eligible for installation. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. 

(h) Related Information 

(1) For more information about this AD, 

contact James Rosa, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7152; fax: (781) 238–7199; 

email: james.rosa@faa.gov. 

(2) For service information identified in 

this AD, contact Turbomeca S.A., 40220 

Tarnos, France; phone: 33–05–59–74–40–00, 

fax: 33–05–59–74–45–15. You may review 

copies of the referenced service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA 01803. For information on the 

availability of this material at the FAA, call 

(781) 238–7125. 

Issued in Burlington, Massachusetts, on 

October 28, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–28677 Filed 11–4–11; 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] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) RB211–Trent 800 Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for RR RB211–Trent 800 series turbofan 

engines. That NPRM proposed to revise 

the Trent 800 Time Limits Manual 

(TLM) of the Trent 800 engine 

maintenance manuals (EMMs). That 

NPRM was prompted by RR reducing 

the life limits of certain critical engine 

parts. This action revises that NPRM by 

proposing to supersede an existing AD 

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. 

We are proposing this supplemental 

NPRM to prevent the failure of critical 

rotating parts, which could result in 

uncontained failure of the engine and 

damage to the airplane. Because of the 

extensive changes since the NPRM was 

issued, we are reopening the comment 

period to allow the public the chance to 

comment on these proposed changes. 

DATES: We must receive comments on 

this proposed AD by January 6, 2012. 

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, 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 proposed 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 


srobinson on DSK4SPTVN1PROD with PROPOSALS
68664 Federal Register / Vol. 76, No. 215 / Monday, November 7, 2011 / Proposed Rules 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0755; Directorate Identifier 

2010–NE–12–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

apply to RR RB211–Trent 800 series 

turbofan engines. That NPRM published 

in the Federal Register on August 3, 

2010 (75 FR 45560). That NPRM would 

have revised the TLM of the RB211– 

Trent 800 EMMs. That NPRM was 

prompted by RR reducing the life limits 

of certain critical engine parts. Revision 

of the critical part lives has been 

necessary due to actual operational 

flight profiles not conforming to those 

assumed at entry into service and is 

associated with a revised Flight Profile 

Monitoring methodology introduced by 

RR. The methodology was originally 

based on engine thrust rating but is now 

based on operating shaft speeds. 

Actions Since Previous NPRM Was 

Issued 

Since we issued the previous NPRM 

(75 FR 45560, August 3, 2010), RR 

requested that we supersede existing AD 

2003–16–18, Amendment 39–13271 (68 

FR 49344, August 18, 2003). That AD 

currently requires a life limit for 

intermediate-pressure (IP) turbine rotor 

disc, part number (P/N) FK21117, that is 

lower than the life limit proposed by 

this supplemental NPRM. Rolls-Royce 

plc substantiated their proposed 

increased life of P/N FK21117 by rig test 

and analysis. 

AD 2003–16–18 (68 FR 49344, August 

18, 2003) also reduced the life limit for 

IP turbine rotor discs, P/N FK33083, and 

all P/N FK33083 IP turbine rotor discs 

are no longer in service. RR has 

accordingly reduced the life for P/N 

FK33083 discs to zero, effectively 

removing them as a disc approved for 

installation in any engine. By revising 

the previous NPRM (75 FR 45560, 

August 3, 2010) to supersede AD 2003– 

16–18, as discussed previously, this 

proposed AD would make these changes 

to the life of RR IP turbine rotor disc, 

P/N FK21117, and RR IP turbine rotor 

disc, P/N FK33083, mandatory. We have 

also determined that it is unnecessary to 

incorporate by reference the TLM of the 

Trent 800 engine EMMs. We can 

address the unsafe condition identified 

in this supplemental NPRM by 

mandating the reduced lives of the 

affected parts. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM (75 FR 

45560, August 3, 2010). We have 

considered the comments received. 

Request To Change Compliance 

Paragraph (e)(1) 

American Airlines and Delta Airlines 

asked us to change paragraph (e)(1) in 

the proposed AD from ‘‘(1) Revise the 

airworthiness limitations section (ALS) 

* * * Time Limits manual (TLM) dated 

June 15, 2009’’ to ‘‘(1) Revise the 

airworthiness limitations section (ALS) 

* * * Time Limits manual (TLM) dated 

no earlier than June 15, 2009.’’ The 

commenters do not want to be forced to 

use a TLM dated earlier than the one 

currently in force. 

We partially agree. We agree that a 

more efficient method of revising the 

life exists, so we changed this proposed 

AD to specify the revised part lives in 

Table 1 in the Compliance section of 

this proposed AD. We do not agree to 

the requested wording as it leaves 

compliance with the AD open to future 

revisions that do not currently exist. We 

did not change the proposed AD further 

as a result of this comment. 

Request To Withdraw the NPRM 

Delta Airlines asked us to withdraw 

the NPRM (75 FR 45560, August 3, 

2010). Delta Airlines believed the NPRM 

is redundant because the current TLM 

already requires using the proposed 

tasks and life limits. 

We do not agree. Although the new 

life limits are included in the current 

TLM, the new life limits are reinforced 

when mandated by an AD. We changed 

this proposed AD to specify the revised 

part lives in Table 1 in the Compliance 

section of this proposed AD. 

Request To Supersede the Existing AD 

2003–16–18 (68 FR 49344, August 18, 

2003) 

Rolls-Royce plc asked us to change 

paragraph (b) of the proposed AD from 

‘‘None’’ to ‘‘AD 2003–16–18 is 

superseded by the current AD.’’ 

We agree. We changed paragraph (b) 

of this proposed AD to state that ‘‘This 

AD supersedes AD 2003–16–18, 

Amendment 39–13271 (68 FR 49344, 

August 18, 2003)’’. 

Relevant Service Information 

Rolls-Royce plc has issued Alert 

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

Revision 7, dated January 19, 2009. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in this 

supplemental NPRM. 

FAA’s Determination 

We are proposing this supplemental 

NPRM 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. Certain changes described above 

expand the scope of the previous NPRM 

(75 FR 45560, August 3, 2010). As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this 

supplemental NPRM. 

Proposed Requirements of the 

Supplemental NPRM 

This supplemental NPRM would 

reduce the life limits of certain critical 

engine parts and would supersede AD 

2003–16–18, Amendment 39–13271 (68 

FR 49344, August 18, 2003). 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect 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 

proposed AD because discs are replaced 

at scheduled maintenance intervals. 

Prorated cost of parts would cost about 

$45,000 per engine. Based on these 

figures, we estimate the cost of the 

proposed 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 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 215 / Monday, November 7, 2011 / Proposed Rules 68665 

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 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

(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 or; 

(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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Rolls-Royce plc: Docket No. FAA–2010– 

0755; Directorate Identifier 2010–NE– 

12–AD. 

(a) Comments Due Date 

We must receive comments by January 6, 

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 number (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 TLM 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 and 

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. 

Issued in Burlington, Massachusetts, on 

October 31, 2011. 

Peter A. White, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–28678 Filed 11–4–11; 8:45 am] 

BILLING CODE 4910–13–P 


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