51654 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Rules and Regulations 

inspection for corrosion and rejection 

criteria. 

Previous Credit 

(f) Initial inspections done before the 

effective date of this AD on LP turbine disks 

stage 2 and stage 3 listed in Table 1 and 

Table 2 of this AD using RRD ASB No. TAY– 

72–A1524, Revision 1, dated September 1, 

2006, or Revision 2, dated June 13, 2008, 

comply with the initial inspection 

requirements specified in this AD. 

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 EASA AD 2010–060R1, dated 

April 14, 2010, for related information. 

Contact Rolls-Royce Deutschland Ltd & Co 

KG, Eschenweg 11, Dahlwitz, 15827 

Blankenfelde-Mahlow, Germany; phone: 011 

49 (0) 33–7086–1883; fax: 011 49 (0) 33– 

7086–3276, for a copy of the service 

information referenced in this AD. 

(i) Contact Mark Riley, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: mark.riley@faa.gov; phone: 

(781) 238–7758; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(j) You must use RRD Alert Service 

Bulletin No. TAY–72–A1524, Revision 3, 

dated March 24, 2010, to do the inspections 

required by this AD. 

(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 Deutschland Ltd 

& Co KG, Eschenweg 11, Dahlwitz, 15827 

Blankenfelde-Mahlow, Germany; phone: 011 

49 (0) 33–7086–1883; fax: 011 49 (0) 33– 

7086–3276. 

(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 

August 6, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–20657 Filed 8–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1157; Directorate 

Identifier 2009–NE–26–AD; Amendment 39– 

16402; AD 2010–17–10] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) RB211–22B and RB211–524 

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: 

Several low pressure turbine (LPT) shafts 

have been found with cracks originating from 

the rear cooling air holes. The cracks were 

found at normal component overhaul, by the 

standard Magnetic Particle Inspection (MPI) 

technique defined in the associated engine 

manual. The cracks have been found to 

initiate from corrosion pits. Propagation of a 

crack from the rear cooling air holes may 

result in shaft failure and subsequently in an 

uncontained Low Pressure Turbine failure. 

For the reasons stated above, this AD requires 

the inspection of the affected engines’ LPT 

shafts and replacement of the shaft, as 

necessary. 

We are issuing this AD to detect 

cracks, initiated by corrosion pits, 

originating from the rear cooling air 

holes, which could result in shaft failure 

and subsequently in an uncontained 

failure of the LPT and damage to the 

airplane. 

DATES: This AD becomes effective 

September 27, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

September 27, 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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: alan.strom@faa.gov; telephone 

(781) 238–7143; 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 May 19, 2010 (75 FR 27964). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Several low pressure turbine (LPT) shafts 

have been found with cracks originating from 

the rear cooling air holes. The cracks were 

found at normal component overhaul, by the 

standard Magnetic Particle Inspection (MPI) 

technique defined in the associated engine 

manual. The cracks have been found to 

initiate from corrosion pits. Propagation of a 

crack from the rear cooling air holes may 

result in shaft failure and subsequently in an 

uncontained Low Pressure Turbine failure. 

For the reasons stated above, this AD requires 

the inspection of the affected engines’ LPT 

shafts and replacement of the shaft, as 

necessary. 

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 

10 products of U.S. registry. We also 

estimate that it will take about 7 workhours per product to comply with this 

AD. The average labor rate is $85 per 

work-hour. Required parts will cost 

about $15,000 per product. Based on 

these figures, we estimate the cost of the 

AD on U.S. operators to be $155,950. 

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 


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Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Rules and Regulations 51655 

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. 

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 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: 

2010–17–10 Rolls-Royce plc: Amendment 

39–16402. Docket No. FAA–2009–1157; 

Directorate Identifier 2009–NE–26–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 27, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce plc 

RB211–22B series and RB211–524B4–D–02, 

RB211–524D4–19, RB211–524D4–39, 

RB211–524D4–B–19, RB211–524D4–B–39, 

RB211–524D4X–19, and RB211–524D4X–B– 

19 model turbofan engines. These engines are 

installed on, but not limited to, Boeing 747 

series and Lockheed L–1011 series airplanes. 

Reason 

(d) This AD results from: 

Several low pressure turbine (LPT) shafts 

have been found with cracks originating from 

the rear cooling air holes. The cracks were 

found at normal component overhaul, by the 

standard Magnetic Particle Inspection (MPI) 

technique defined in the associated engine 

manual. The cracks have been found to 

initiate from corrosion pits. Propagation of a 

crack from the rear cooling air holes may 

result in shaft failure and subsequently in an 

uncontained Low Pressure Turbine failure. 

For the reasons stated above, this AD requires 

the inspection of the affected engines’ LPT 

shafts and replacement of the shaft, as 

necessary. 

We are issuing this AD to detect cracks, 

initiated by corrosion pits, originating from 

the rear cooling air holes, which could result 

in shaft failure and subsequently in an 

uncontained failure of the LPT and damage 

to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

Initial Inspection Requirements 

(1) At the next engine shop visit after the 

effective date of this AD when the LPT shaft 

is completely disassembled to piece-part 

level, inspect the LPT shaft using paragraphs 

3.A.(1)(a) through 3.A.(4)(l) of the 

accomplishment instructions of Rolls-Royce 

Service Bulletin RB.211–72–AF336, dated 

October 24, 2007. 

Repetitive Inspection Requirements 

(2) Thereafter, reinspect the LPT shaft 

using paragraphs 3.A.(1)(a) through 3.A.(4)(l) 

of the accomplishment instructions of RollsRoyce Service Bulletin RB.211–72–AF336, 

dated October 24, 2007 and the following 

schedule in Table 1 of this AD: 

TABLE 1—REPETITIVE INSPECTION INTERVAL BY ENGINE MODEL

Engine model Maximum time between inspections 

(engine cycles) 

(i) RB211–22B Series, all models ....................................................................................................... 3,500. 

(ii) RB211–524B4–D–02 ...................................................................................................................... 4,000. 

(iii) RB211–524D4–19, RB211–524D4–39, RB211–524D4–B–19, RB211–524D4–B–39, RB211– 

524D4X–19 and RB211–524D4X–B–19.

At the next engine shop visit after the last 

inspection. 

Remove Parts With Cracks 

(3) Remove cracked LPT shafts, found 

using paragraphs (e)(1) or (e)(2) of this AD, 

from service before further flight. 

Definitions 

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

shop visit is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges. The separation of engine flanges 

solely for the purposes of transportation 

without subsequent engine maintenance does 

not constitute an engine shop visit. 

Alternative Methods of Compliance 

(AMOCs) 

(f) 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 

(g) Refer to MCAI EASA Airworthiness 

Directive 2007–0310 R1, dated January 8, 

2008, for related information. 

(h) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: alan.strom@faa.gov; telephone 

(781) 238–7143; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(i) You must use Rolls-Royce Service 

Bulletin RB.211–72–AF336, dated October 

24, 2007, 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. 


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51656 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Rules and Regulations 

(2) For service information identified in 

this AD, contact Rolls-Royce plc, P.O. Box 

31, Derby, DE24 8BJ, United Kingdom; 

telephone 044 1332 242424; fax 044 1332 

249936. 

(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 

August 5, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–20705 Filed 8–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0776; Directorate 

Identifier 2009–NE–32–AD; Amendment 39– 

16403; AD 2010–17–11] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers R408/6–123–F/17 Model 

Propellers 

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: 

Friction or contact between a propeller deice bus bar and the backplate assembly can 

cause failure of the bus bar and a consequent 

intermittent short circuit. Such a short circuit 

can cause a dual AC generator shutdown 

that, particularly in conjunction with an 

engine failure in icing conditions, could 

result in reduced controllability of the 

airplane. 

We are issuing this AD to prevent an inflight double generator failure, which 

could result in reduced controllability 

of the airplane. 

DATES: This AD becomes effective 

September 27, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

September 27, 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: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

michael.schwetz@faa.gov; telephone 

(781) 238–7761; fax (781) 238–7170. 

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 September 25, 2009 (74 FR 

48870). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

Friction or contact between a propeller deice bus bar and the backplate assembly can 

cause failure of the bus bar and a consequent 

intermittent short circuit. Such a short circuit 

can cause a dual AC generator shutdown 

that, particularly in conjunction with an 

engine failure in icing conditions, could 

result in reduced controllability of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

One commenter, a private citizen, 

requests that the AD allow propellers 

modified under earlier revisions of the 

service bulletin to meet the 

requirements of the AD, as the 

modification instructions are the same. 

We agree. We added a paragraph that 

allows for previous credit for initial 

sealant application done before the 

effective date of the AD using earlier 

versions of the service bulletin. We also 

reference using Dowty Propellers Alert 

Service Bulletin No. D8400–61–A66, 

Revision 5, dated June 16, 2010 in the 

compliance section, which is the latest 

version. Since Revision 5 of the ASB 

requires repetitive applications of 

sealant, we eliminated the AD 

differences that appeared in the 

proposed AD. 

Conclusion 

We 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 determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

104 propellers installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 2 work-hours per 

propeller to comply with this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $20 per 

propeller. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $18,720. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 


sroberts on DSKD5P82C1PROD with RULES