Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Rules and Regulations 6669 

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 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. 

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: 

2012–02–04 Rolls-Royce plc: Amendment 

39–16927; Docket No. FAA–2012–0004; 

Directorate Identifier 2012–NE–01–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective February 24, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc RB211– 

Trent 553–61, RB211–Trent 553A2–61, 

RB211–Trent 556–61, RB211–Trent 556A2– 

61, RB211–Trent 556B–61, RB211–Trent 

556B2–61, RB211–Trent 560–61, and RB211– 

Trent 560A2–61 turbofan engines that have 

not complied with Rolls-Royce plc Service 

Bulletin No. RB.211–73–G723, and that have 

any of the following fuel tube part numbers 

installed: 

(1) FW57605. 

(2) FW17689. 

(3) FW57604. 

(4) FK30710. 

(5) FW57578. 

(6) FK30713. 

(d) Reason 

This AD was prompted by reports of wear 

found between the securing clips and the 

low-pressure (LP) fuel tube outer surface, 

which reduces the fuel tube wall thickness, 

leading to fracture of the fuel tube and 

consequent fuel leak. We are issuing this AD 

to prevent engine fuel leaks, which could 

result in risk to the airplane. 

(e) Actions and Compliance 

Unless already done, do the following onetime actions within 1,600 flight hours after 

the effective date of this AD. 

(1) Visually inspect the fuel tube clips 

holding the LP fuel tube run from the LP fuel 

pump to the fuel-oil-heat exchanger, and the 

clips holding the LP fuel tube run from the 

LP filter to the high-pressure (HP) fuel pump, 

for evidence of damage or wear and replace 

as necessary. Do this in accordance with 

paragraphs 3.A(4)(a) through 3.A(4)(c) of 

Rolls-Royce plc Alert Service Bulletin No. 

RB.211–73–AG797, dated October 26, 2011. 

(2) Clean and dry the LP fuel tube run from 

the LP fuel pump to the fuel-oil-heat 

exchanger, and the LP fuel tube run from the 

LP filter to the HP fuel pump. 

(i) Visually inspect for evidence of damage, 

wear near the clip locations, and for fuel 

leakage. 

(ii) Reject the tube and replace it if 

evidence of fuel leakage or contact frettage to 

a depth of greater than 0.1 mm (0.004 in.) on 

the outer surface of a bend, or 0.2 mm (0.008 

in.) in any other area, is evident. 

(f) 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. 

(g) 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; 

email: alan.strom@faa.gov; phone: (781) 238– 

7143; fax: (781) 238–7199. 

(2) Refer to European Aviation Safety 

Agency AD 2011–0243, dated December 20, 

2011, for related information. 

(h) 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 of the following 

service information under 5 U.S.C. 552(a) 

and 1 CFR part 51: 

(2) Rolls-Royce plc Alert Service Bulletin 

No. RB.211–73–AG797, dated October 26, 

2011. 

(3) 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. 

(4) You may review copies of the 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. 

(5) You may also review copies of the 

service information 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 Burlington, Massachusetts, on 

January 19, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–2895 Filed 2–8–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0789; Directorate 

Identifier 2011–NE–04–AD; Amendment 39– 

16929; AD 2012–02–06] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. TPE331–10 and 

TPE331–11 Series Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD was 

prompted by a report of an uncontained 

failure of a first stage turbine disk that 

had a metallurgical defect. This AD 

requires inspecting certain serial 

number (S/N) first stage turbine disks, 

part number (P/N) 3101520–1 and P/N 


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6670 Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Rules and Regulations 

3107079–1. We are issuing this AD to 

prevent uncontained failure of the first 

stage turbine disk and damage to the 

airplane. 

DATES: This AD is effective March 15, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 15, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Honeywell 

International Inc., 111 S. 34th Street, 

Phoenix, AZ 85034–2802; phone: (800) 

601–3099 (toll free in U.S. or Canada) or 

(602) 365–3099 (International direct); 

Web site: http://portal.honeywell.com. 

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. 

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: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; phone: 562–627–5246; fax: 

562–627–5210; email: 

joseph.costa@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 August 9, 2011 (76 FR 

48749). That NPRM proposed to require 

inspecting certain S/N first stage turbine 

disks, P/N 3101520–1 and P/N 

3107079–1. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 90 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 20 work-hours per engine to 

perform these actions, and that the 

average labor rate is $85 per work-hour. 

Required parts cost about $19,000 per 

engine. We estimate that one disk will 

fail the initial inspection and that 

repetitive inspections will be performed 

on 89 engines. We estimate that one 

engine will fail the repetitive 

inspections and that further repetitive 

inspections will be performed on 88 

engines. We estimate that an additional 

one disk will fail those repetitive 

inspections before retirement. Based on 

these figures, we estimate the total cost 

of the AD to U.S. operators to be 

$511,155. 

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 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): 

2012–02–06 Honeywell International Inc. 

(formerly AlliedSignal Inc., Garrett 

Engine Division; Garrett Turbine Engine 

Company; and AiResearch 

Manufacturing Company of Arizona): 

Amendment 39–16929; Docket No. 

FAA–2011–0789; Directorate Identifier 

2011–NE–04–AD. 

(a) Effective Date 

This AD is effective March 15, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

Honeywell International Inc. TPE331–10, 

–10AV, –10GP, –10GT, –10N, –10P, –10R, 

–10T, –10U, –10UA, –10UF, –10UG, 

–10UGR, –10UR, and TPE331–11U model 

turboprop engines with a first stage turbine 

disk, part number (P/N) 3101520–1 or 

3107079–1, with a serial number (S/N) listed 

in Table 2 of Honeywell International Inc. 

Alert Service Bulletin (ASB) TPE331–72– 

A2156, dated December 2, 2008, installed. 

(d) Unsafe Condition 

This AD was prompted by a report of an 

uncontained failure of a first stage turbine 

disk that had a metallurgical defect. We are 

issuing this AD to prevent uncontained 

failure of the first stage turbine disk and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 


emcdonald on DSK29S0YB1PROD with RULES
Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Rules and Regulations 6671 

(f) Initial Inspection 

(1) For first stage turbine disks, P/N 

3101520–1 or 3107079–1, that have an S/N 

listed in Table 2 of Honeywell International 

Inc. ASB TPE331–72–A2156, dated 

December 2, 2008, inspect the disks as 

follows: 

(i) For turbine disks with 4,100 or fewer 

cycles-since-new (CSN) on the effective date 

of this AD, perform an initial fluorescent 

penetrant inspection (FPI) by using 

paragraph 3.B.(2) through 3.B.(5) of 

Honeywell International Inc. ASB TPE331– 

72–A2156, dated December 2, 2008, within 

4,500 CSN or at the next access, whichever 

occurs first. 

(ii) For turbine disks with more than 4,100 

CSN on the effective date of this AD, perform 

an initial FPI by using paragraph 3.B.(2) 

through 3.B.(5) of Honeywell International 

Inc. ASB TPE331–72–A2156, dated 

December 2, 2008, within 400 cycles-inservice (CIS) after the effective date of this 

AD or at the next access, whichever occurs 

first. 

(iii) If the disk passes the FPI inspection, 

perform a special eddy current inspection 

(ECI) by using paragraph 3.B.(6) of 

Honeywell International Inc. ASB TPE331– 

72–A2156, dated December 2, 2008, before 

returning the disk to service. 

(2) If you find a crack in the disk, remove 

the disk from service. 

(g) Repetitive Inspection 

(1) Thereafter, for first stage turbine disks, 

P/N 3101520–1 or 3107079–1, that have an 

S/N listed in Table 2 of Honeywell 

International Inc. ASB TPE331–72–A2156, 

dated December 2, 2008, inspect the disks as 

follows: 

(i) Perform a repetitive inspection at each 

scheduled hot section inspection, but not to 

exceed 3,600 hours-since-last inspection. Use 

paragraph 3.B.(2) through 3.B.(5) of 

Honeywell International Inc. ASB TPE331– 

72–A2156, dated December 2, 2008. 

(ii) If the disk passes the FPI inspection, 

perform a special ECI by using paragraph 

3.B.(6) of Honeywell International Inc. ASB 

TPE331–72–A2156, dated December 2, 2008, 

before returning the disk to service. 

(2) If you find a crack in the disk, remove 

the disk from service. 

(h) Definition 

For the purpose of this AD, ‘‘next access 

to the first stage turbine disk’’ is defined as 

the removal of the second stage turbine 

nozzle from the turbine stator housing. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(j) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: (562) 627–5246; fax: (562) 627– 

5210; email: joseph.costa@faa.gov. 

(2) Contact Honeywell International Inc., 

111 S. 34th Street, Phoenix, AZ 85034–2802; 

phone: (800) 601–3099 (toll free in U.S. or 

Canada) or (602) 365–3099 (International 

direct); Web site: http:// 

portal.honeywell.com; for a copy of the 

service information referenced in this AD. 

(k) 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) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Honeywell International Inc., Alert 

Service Bulletin TPE331–72–A2156, 

December 2, 2008. 

(2) For service information identified in 

this AD, contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034– 

2802; Web site: http://portal.honeywell.com; 

or call Honeywell toll free at (800) 601–3099 

(U.S./Canada) or (602) 365–3099 

(International Direct). 

(3) You may review copies of the 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. 

(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 an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

January 12, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–2894 Filed 2–8–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0547; Directorate 

Identifier 2011–NE–13–AD; Amendment 39– 

16947; AD 2012–03–06] 

RIN 2120–AA64 

Airworthiness Directives; Superior Air 

Parts, Lycoming Engines (Formerly 

Textron Lycoming), and Continental 

Motors, Inc., Fuel-Injected 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

Superior Air Parts and Lycoming 

Engines fuel-injected reciprocating 

engines. That AD currently requires 

removing AVStar Fuel Systems, Inc. 

(AFS) fuel servos installed after May 20, 

2010, if the servo contained an AFS 

diaphragm, part number (P/N) 

AV2541801 or P/N AV2541803, from 

certain production lots. This AD 

expands the applicability, and changes 

the compliance interval for all affected 

Superior Air Parts, Lycoming Engines, 

and Continental Motors, Inc., fuelinjected reciprocating engines. This AD 

was prompted by an accident involving 

a Piper PA32R–301 airplane, and by the 

discovery of additional engines being 

affected by the unsafe condition since 

we issued the existing AD. We are 

issuing this AD to prevent an in-flight 

engine shutdown due to a failed fuel 

servo diaphragm, and damage to the 

airplane. 

DATES: This AD is effective February 24, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 16, 2011 (76 FR 45655, 

August 1, 2011). 

We must receive any comments on 

this AD by March 26, 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 AVStar Fuel Systems, 

Inc., 1365 Park Lane South, Jupiter, FL 

33458; phone: (561) 575–1560; Web site: 

www.avstardirect.com. 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. 

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 


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