This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

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new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

15321 

Vol. 75, No. 59 

Monday, March 29, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1004; Directorate 

Identifier 2009–NE–36–AD; Amendment 39– 

16239; AD 2010–06–14] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–Trent 800 Series Turbofan 

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 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: 

During 2004, an incident was reported 

involving uncontained multiple 

intermediate-pressure (IP) turbine blade 

release on a Trent 700 engine. The blade 

release was the result of an overspeed of the 

IP turbine rotor that was initiated by an 

internal fire in the high-pressure/ 

intermediate-pressure (HP/IP) bearing 

chamber. Post-incident analysis and 

investigation has established that blockage of 

the HP/IP turbine bearing oil vent tube due 

to carbon deposits was a significant factor in 

the failure sequence. The Trent 800 has a 

similar type design standard to that of the 

Trent 700 and has also been found in service 

to be susceptible to carbon deposits in the oil 

vent tube. 

We are issuing this AD to prevent 

internal oil fires due to coking and 

carbon buildup in the HP/IP turbine 

bearing oil vent tube that could cause 

uncontained engine failure and damage 

to the airplane. 

DATES: This AD becomes effective May 

3, 2010. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in this AD as of May 3, 2010. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 

238–7199. 

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 was published in the Federal 

Register on January 5, 2010 (75 FR 264). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During 2004, an incident was reported 

involving uncontained multiple IP turbine 

blade release on a Trent 700 engine. The 

blade release was the result of an overspeed 

of the IP turbine rotor that was initiated by 

an internal fire in the HP/IP bearing chamber. 

Post-incident analysis and investigation has 

established that blockage of the HP/IP turbine 

bearing oil vent tube due to carbon deposits 

was a significant factor in the failure 

sequence. The Trent 800 has a similar type 

design standard to that of the Trent 700 and 

has also been found in service to be 

susceptible to carbon deposits in the oil vent 

tube. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supports the NPRM. 

Conclusion 

We reviewed the available data, 

including the comment received, 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 will affect about 

138 RB211 Trent 800 series turbofan 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about one work-hour per engine to 

comply with this AD. The average labor 

rate is $80 per work-hour. Required 

parts will cost about $2,000 per engine. 

Based on these figures, we estimate the 

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

$287,040. 

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 

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. 


PWALKER on DSK8KYBLC1PROD with RULES
15322 Federal Register / Vol. 75, No. 59 / Monday, March 29, 2010 / Rules and Regulations 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 (telephone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

2010–06–14 Rolls-Royce plc: Amendment 

39–16239. Docket No. FAA–2009–1004; 

Directorate Identifier 2009–NE–36–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 3, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce plc 

models RB211–Trent 875–17, Trent 877–17, 

Trent 884–17, Trent 884B–17, Trent 892–17, 

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

engines. These engines are installed on, but 

not limited to, Boeing 777 series airplanes. 

Reason 

(d) During 2004, an incident was reported 

involving uncontained multiple 

intermediate-pressure (IP) turbine blade 

release on a Trent 700 engine. The blade 

release was the result of an overspeed of the 

IP turbine rotor that was initiated by an 

internal fire in the high-pressure/ 

intermediate-pressure (HP/IP) bearing 

chamber. Post-incident analysis and 

investigation has established that blockage of 

the HP/IP turbine bearing oil vent tube due 

to carbon deposits was a significant factor in 

the failure sequence. The Trent 800 has a 

similar type design standard to that of the 

Trent 700 and has also been found in service 

to be susceptible to carbon deposits in the oil 

vent tube. 

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. We are 

issuing this AD to prevent internal oil fires 

due to coking and carbon buildup in the HP/ 

IP turbine bearing oil vent tube that could 

cause uncontained engine failure and damage 

to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) At the next engine shop visit after the 

effective date of this AD and thereafter at 

each engine shop visit, using the 

Accomplishment Instructions of Rolls-Royce 

plc Alert Service Bulletin No. RB.211–72– 

AE362, Revision 1, dated April 3, 2009: 

(i) Inspect the HP/IP turbine bearing 

internal and external oil vent tubes and 

bearing chamber for carbon buildup. 

(ii) Clean and flush the tubes and bearing 

chamber as required. 

(iii) Reject any oil vent tubes that do not 

meet inspection requirements after cleaning. 

(2) This AD does not require reporting of 

inspection results, as does paragraphs 

3.B.(4)(g) and 3.C.(9) of Rolls-Royce plc Alert 

Service Bulletin No. RB.211–72–AE362, 

Revision 1, dated April 3, 2009. 

FAA AD Differences 

(f) None. 

Alternative Methods of Compliance 

(AMOCs) 

(g) 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. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency AD 2009–0071 (corrected 

April 14, 2009), for related information. 

(i) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(j) You must use Rolls-Royce plc Alert 

Service Bulletin No. RB.211–72–AE362, 

Revision 1, dated April 3, 2009, to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Rolls-Royce plc, PO Box 31, 

Derby, England; telephone: 011–44–1332– 

249428; fax: 011–44–1332–249223. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; or 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 

March 9, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5788 Filed 3–26–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0978; Directorate 

Identifier 2008–NM–014–AD; Amendment 

39–16234; AD 2010–06–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767–200, –300, and 

–300F Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 767–200, –300, and –300F series 

airplanes. For certain airplanes, this AD 

requires installing support hardware 

and modifying the interfacing wiring of 

the fuel quantity indicating system 

(FQIS) densitometer. For certain other 

airplanes, this AD requires replacing the 

existing hot short protector (HSP) on the 

FQIS densitometer with a new HSP. 

This AD also requires revising the 

Airworthiness Limitations (AWL) 

section of the Instructions for Continued 

Airworthiness to incorporate AWL No. 

28–AWL–22. This AD results from fuel 

system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent the center tank fuel 

densitometer from overheating and 

becoming a potential ignition source 

inside the center fuel tank, which, in 

combination with flammable fuel 

vapors, could result in a center fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: This AD is effective May 3, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 3, 2010. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 


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