Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations 16655 

(1) Where Boeing Alert Service Bulletin 

747–53A2439, Revision 2, dated July 17, 

2008, specifies a compliance time relative to 

the date of issuance of that service bulletin, 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2439, Revision 2, dated July 17, 

2008, specifies contacting Boeing for repair 

data: Before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (o) of this 

AD. 

Optional New Modification for Areas 1, 2, 3, 

and 4 

(m) For areas 1, 2, 3, and 4 as defined in 

Boeing Alert Service Bulletin 747–53A2439, 

Revision 2, dated July 17, 2008: Doing the 

modification and post-modification actions 

specified in Boeing Alert Service Bulletin 

747–53A2696, dated October 16, 2008, 

terminates the repetitive inspection 

requirements of paragraphs (g) and (h) of this 

AD. Doing the modification and postmodification actions specified in Boeing 

Alert Service Bulletin 747–53A2696, dated 

October 16, 2008, terminates the repetitive 

inspection requirements of paragraph (l) of 

this AD, except at the upper deck floor beam 

at body station (BS) 460 and 480 and the 

upper deck floor beams aft of BS 520. 

No Reporting Requirement 

(n) Although Boeing Alert Service Bulletin 

747–53A2439, Revision 1, dated March 10, 

2005; and Boeing Alert Service Bulletin 747– 

53A2439, Revision 2, dated July 17, 2008; 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: Ivan 

Li, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6437; fax (425) 917–6590. Or, 

e-mail information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) AMOCs approved previously in 

accordance with AD 2006–08–02, are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(4) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(p) You must use Boeing Alert Service 

Bulletin 747–53A2439, Revision 2, dated July 

17, 2008, to do the actions required by this 

AD, unless the AD specifies otherwise. If you 

accomplish the new optional actions 

specified by this AD, you must use Boeing 

Alert Service Bulletin 747–53A2696, dated 

October 16, 2008, to perform those actions, 

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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1, fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(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 NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 

17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6546 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–19559; Directorate 

Identifier 2004–NE–03–AD; Amendment 39– 

16254; AD 2010–07–09] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–Trent 700 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Rolls-Royce plc RB211–Trent 700 series 

turbofan engines. That AD currently 

requires initial and repetitive borescope 

inspections of the high-pressure-andintermediate pressure (HP–IP) turbine 

internal and external oil vent tubes for 

coking and carbon buildup, and 

cleaning or replacing the vent tubes if 

necessary. This AD requires the same 

actions, but adds additional inspections 

of the vent flow restrictor. This AD 

results from further analysis that the 

cleaning of the vent tubes required by 

AD 2007–02–05 could lead to loosened 

carbon fragments, causing a blockage 

downstream in the vent flow restrictor. 

We are issuing this AD to prevent 

internal oil fires due to coking and 

carbon buildup that could cause 

uncontained engine failure and damage 

to the airplane. 

DATES: This AD becomes effective May 

7, 2010. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of May 7, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce plc, P.O. Box 31, Derby, 

England; telephone: 011–44–1332– 

249428; fax: 011–44–1332–249223. 

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: The FAA 

proposed to amend 14 CFR part 39 by 

superseding AD 2007–02–05, 

Amendment 39–14892 (72 FR 2603, 

January 22, 2007), with a proposed AD. 

The proposed AD applies to Rolls-Royce 

plc RB211–Trent 700 series turbofan 

engines. We published the proposed AD 

in the Federal Register on October 26, 

2009 (74 FR 54940). That action 

proposed to require initial and 

repetitive borescope inspections of the 

HP–IP turbine internal and external oil 

vent tubes for coking and carbon 

buildup, cleaning or replacing the vent 

tubes if necessary, and inspections of 

the vent flow restrictor. 

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, 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
16656 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations 

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. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request to Reference the Latest Service 

Bulletin 

One commenter, Rolls-Royce plc, 

requests that we incorporate by 

reference the latest alert service bulletin 

(ASB) in the AD, which is ASB No. 

RB.211–72–AE302, Revision 8, dated 

October 21, 2009. 

We agree. We changed the AD to 

incorporate by reference Revision 8 of 

that ASB. 

Request To Allow Previous Credit 

Rolls-Royce plc requests that we 

allow previous credit to operators that 

performed the initial inspections 

specified in paragraph (f) of the 

proposed AD before the AD effective 

date, using Revision 4, Revision 5, 

Revision 6, or Revision 7 of ASB No. 

RB.211–72–AE302. 

We agree and added a previous credit 

paragraph to the AD. 

Request to Change Initial Inspection 

Threshold 

Rolls-Royce plc requests that we 

change the initial inspection threshold 

from 3 months to 2 months, to agree 

with the ASB. 

We agree and changed the AD. 

Clarification of AD Compliance Section 

We clarified paragraphs (g) and (h) of 

the AD compliance section to better 

align with the Rolls-Royce plc ASB. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

33 engines 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 $68,640. 

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 have 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 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); 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

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 Federal Aviation Administration 

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 Amendment 39–14892 (72 FR 

2603, January 22, 2007), and by adding 

a new airworthiness directive, 

Amendment 39–16254, to read as 

follows: 

2010–07–09 Rolls-Royce plc: Amendment 

39–16254. Docket No. FAA–2005–19559; 

Directorate Identifier 2004–NE–03–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 7, 2010. 

Affected ADs 

(b) This AD supersedes AD 2007–02–05, 

Amendment 39–14892. 

Applicability 

(c) This AD applies to Rolls-Royce plc 

RB211–Trent 768–60, RB211–Trent 772–60, 

and RB211–Trent 772B–60 series turbofan 

engines. These engines are installed on, but 

not limited to, Airbus A330–243, –341, –342 

and –343 series airplanes. 

Unsafe Condition 

(d) This AD results from further analysis 

that the cleaning of the vent tubes required 

by AD 2007–02–05 could lead to loosened 

carbon fragments, causing a blockage 

downstream in the vent flow restrictor. We 

are issuing this AD to prevent internal oil 

fires due to coking and carbon buildup that 

could cause uncontained engine failure and 

damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Initial Inspections, Cleaning, and 

Replacements 

(f) Using the schedule in Table 1 of this 

AD, borescope-inspect and clean as 

necessary, the high-pressure-andintermediate pressure (HP–IP) turbine 

internal oil vent tubes, external oil vent 

tubes, and bearing chamber. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations 16657 

TABLE 1—INITIAL INSPECTION SCHEDULE

If the engine or the 05 Module Then initially inspect 

Has reached 10,000 hours time-since-new (TSN) or reached 2,500 cycles-since-new (CSN) on the effective date of this AD.Within 2 months after the effective date of this AD. 

Has fewer than 10,000 hours TSN and fewer than 2,500 CSN on the 

effective date of this AD.

Within 2 months after reaching 10,000 hours TSN or 2,500 CSN, 

whichever occurs first. 

Is returned for an engine shop visit ......................................................... Before returning to service. 

(1) If after cleaning, there is still carbon in 

the vent tube that prevents cleaning tool 

number HU80298 from passing through the 

tube, then replace the internal oil vent tube 

within 10 cycles-in-service (CIS). 

(2) If after cleaning, there is still carbon of 

visible thickness in either of the two external 

oil vent tubes, then replace the external oil 

vent tube before further flight. 

(3) Use paragraphs 3.A. through 3.A.(7) of 

the Accomplishment Instructions and 

Appendix A of Rolls-Royce plc Alert Service 

Bulletin (ASB) No. RB.211–72–AE302, 

Revision 8, dated October 21, 2009, to do the 

borescope inspections and cleaning of the oil 

vent tubes and bearing chamber. 

Initial Visual Inspection of the Vent Flow 

Restrictor 

(g) For engines that, on the effective date 

of this AD, have not accumulated 25 service 

cycles since the last cleaning and inspection 

specified in paragraphs (f) through (f)(3) of 

this AD, visually inspect the vent flow 

restrictor: 

(1) Either after a high-power ground run 

immediately following the cleaning and 

inspection; or 

(2) Within 25 service cycles of the last 

cleaning and inspection. 

(h) For engines that, on the effective date 

of this AD, have accumulated 25 or more 

service cycles since the last cleaning and 

inspection specified in paragraphs (f) through 

(f)(3) of this AD, visually inspect the vent 

flow restrictor within 25 service cycles after 

the effective date of this AD. 

(i) Use paragraph 3.A.(8) of the 

Accomplishment Instructions of Rolls-Royce 

plc ASB No. RB.211–72–AE302, Revision 8, 

dated October 21, 2009, to do the visual 

inspections. 

Repetitive Inspections, Cleaning, and 

Replacements 

(j) Within 6,400 hours time-in-service since 

last inspection and cleaning, or within 1,600 

cycles-since-last inspection and cleaning, or 

at the next engine shop visit, whichever 

occurs first, borescope-inspect the HP–IP 

turbine internal and external oil vent tubes 

and bearing chamber, and clean the oil vent 

tubes as necessary. 

(1) If after cleaning there is still carbon in 

the internal oil vent tube that prevents 

cleaning tool, number HU80298, from 

passing through the tube, then replace the 

internal oil vent tube within 10 CIS. 

(2) If after cleaning there is still carbon of 

visible thickness, in either of the two external 

oil vent tubes, then replace the external oil 

vent tube before further flight. 

(3) Use paragraphs 3.A. through 3.A.(7) of 

the Accomplishment Instructions and 

Appendix A of Rolls-Royce plc ASB No. 

RB.211–72–AE302, Revision 8, dated October 

21, 2009, to do the borescope inspections and 

cleaning of the oil vent tubes and bearing 

chamber. 

(k) Visually inspect the vent flow restrictor 

either after a high-power ground run or 

within 25 service cycles after performing the 

cleaning and inspection specified in 

paragraph (f) through (f)(3) of this AD. Use 

paragraph 3.A.(8) of the Accomplishment 

Instructions of Rolls-Royce plc ASB No. 

RB.211–72–AE302, Revision 8, dated October 

21, 2009, to do the visual inspection. 

Definition 

(l) For the purpose of this AD, an engine 

shop visit is induction of the engine into the 

engine shop for any cause. 

Previous Credit 

(m) Initial inspections specified in 

paragraph (f) of this AD and performed before 

the effective date of this AD using RollsRoyce plc ASB No. RB.211–72–AE302, 

Revision 4, dated April 30, 2007, or Revision 

5, dated May 22, 2007, or Revision 6, dated 

January 29, 2009, or Revision 7, dated April 

30, 2009, satisfy the initial inspection 

requirements in paragraph (f) of this AD. 

Alternative Methods of Compliance 

(n) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(o) European Aviation Safety Agency AD 

2007–0201, dated August 1, 2007, and AD 

2007–0202 (corrected August 8, 2007), also 

address the subject of this AD. 

(p) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & 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 

(q) You must use Rolls-Royce plc Alert 

Service Bulletin No. RB.211–72–AE302, 

Revision 8, dated October 21, 2009, including 

Appendix A, to perform the actions required 

by this AD. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Rolls-Royce plc, P.O. Box 31, 

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

249428; fax: 011–44–1332–249223 for a copy 

of this service information. 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 25, 2010. 

Robert J. Ganley, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–7283 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1166; Directorate 

Identifier 2009–NM–107–AD; Amendment 

39–16255; AD 2010–07–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2–1C, B2K–3C, B2–203, B4–2C, 

B4–103, and B4–203 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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) 

originated 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: 

One operator reported loss of both pitch 

trims following autopilot disengagement after 

take off. Subsequent shop findings revealed 

severe damage to the power gears. Malphasing between the hydraulic motors was 

suspected to have induced excessive loads 

into the gear train, leading to collapse of one 

bearing on a shaft of the main gear, causing 

severe tooth damage. The combination of 

tooth damage and gear tilting caused the 

disconnection of two of the three hydraulic 

motors, resulting in jamming of the THSA 

[trimmable horizontal stabilizer actuator] 

gearbox and consequent loss of THSA 

control. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1