27964 Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 

The unsafe condition is loss of braking 

capability and possible brake fires, which 

could reduce the ability of the flightcrew to 

safely land the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Do the following actions. 

(1) Within 6 months after the effective date 

of this AD, do a detailed inspection for wear 

of the brake QD couplings by measuring 

dimension ‘‘A,’’ in accordance with Part 1 of 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–156, Revision 1, 

dated June 29, 2009. Repeat the inspection 

thereafter at the applicable intervals specified 

in Table 1 of this AD, except as required by 

paragraph (g)(2) of this AD. 

TABLE 1—REPETITIVE INSPECTION INTERVALS

If dimension ‘‘A’’ is— 

Repeat the inspection 

at intervals not to 

exceed— 

Greater than or equal to 0.76 mm ......................................................................................................................................... 6 months. 

Less than 0.76 mm but greater than or equal to 0.72 mm ................................................................................................... 3 months. 

Less than 0.72 mm but greater than or equal to 0.68 mm ................................................................................................... 30 days. 

Less than 0.68 mm but greater than or equal to 0.61 mm ................................................................................................... 7 days. 

Less than 0.61 mm but greater than 0.53 mm ...................................................................................................................... 24 hours. 

(2) If, during any inspection required by 

paragraph (g)(1) of this AD, dimension ‘‘A’’ on 

any brake QD coupling is less than or equal 

to 0.53 mm, before further flight, replace the 

affected brake QD coupling with an improved 

unit having P/N AE73059E or P/N AE73091E, 

as applicable, in accordance with Part 2 of 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–156, Revision 1, 

dated June 29, 2009. 

(3) Within 24 months after the effective 

date of this AD, replace all remaining brake 

QD couplings having P/N AE70690E, P/N 

AE70691E, P/N AE99111E, and P/N 

AE99119E with improved units, in 

accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–156, Revision 1, 

dated June 29, 2009. 

(4) Installation of brake QD couplings with 

an improved unit having P/N AE73059E or 

P/N AE73091E at all locations terminates the 

repetitive inspections required by paragraph 

(g)(1) of this AD. 

(5) Replacing the brake QD couplings is 

also acceptable for compliance with the 

corresponding requirements of paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD if done 

before the effective date of this AD, in 

accordance with any of the service bulletins 

specified in Table 2 of this AD: 

TABLE 2—FOKKER CREDIT SERVICE BULLETINS

Fokker Service Bulletins Revision Date 

Fokker Service Bulletin SBF100–32–127 ............................................................... Original ................................................... July 20, 2001. 

Fokker Service Bulletin SBF100–32–127 ............................................................... 1 ............................................................. March 6, 2009. 

Fokker Service Bulletin SBF100–32–156 ............................................................... Original ................................................... March 6, 2009. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. 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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI EASA Airworthiness 

Directive 2009–0176, dated August 6, 2009; 

and Fokker Service Bulletin SBF100–32–156, 

Revision 1, dated June 29, 2009; for related 

information. 

Issued in Renton, Washington, on May 4, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11904 Filed 5–18–10; 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] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) RB211–22B and RB211–524 

Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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 


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Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 27965 

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 proposing 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: We must receive comments on 

this proposed AD by July 6, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

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

Derby, DE24 8BJ, United Kingdom: 

Telephone 011 44 1332 242424; fax 011 

44 1332 249936, for the service 

information identified in this proposed 

AD. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tara 

Chaidez, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: tara.chaidez@faa.gov; telephone 

(781) 238–7773; fax (781) 238–7199. 

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–2009–1157; Directorate Identifier 

2009–NE–26–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 with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2007–0310 R1, 

dated January 8, 2008 (referred to after 

this as ‘‘the MCAI’’), 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. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Rolls-Royce plc has issued Alert 

Service Bulletin RB.211–72–AF336, 

dated October 24, 2007. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of the United 

Kingdom, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the United 

Kingdom, they have notified us of the 

unsafe condition described in the MCAI 

and service information referenced 

above. We are proposing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 10 products of U.S. registry. 

We also estimate that it would take 

about 7 work-hours per product to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about 

$15,000 per product. Based on these 

figures, we estimate the cost of the 

proposed 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 

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 


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27966 Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 

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); 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 proposed 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. 

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 adding 

the following new AD: 

Rolls-Royce plc: Docket No. FAA–2009– 

1157; Directorate Identifier 2009–NE– 

26–AD. 

Comments Due Date 

(a) We must receive comments by July 6, 

2010. 

Affected Airworthiness Directives (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. 

Other FAA AD Provisions 

(f) 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. 

Related Information 

(g) Refer to MCAI EASA Airworthiness 

Directive 2007–0310 R1, dated January 8, 

2008, and Rolls-Royce plc Alert Service 

Bulletin RB.211–72–AF336, dated October 

24, 2007, for related information. Contact 

Rolls-Royce plc P.O. Box 31, Derby, DE24 

8BJ, United Kingdom; telephone 044 1332 

242424; fax 044 1332 249936, for a copy of 

this service information. 

(h) Contact Tara Chaidez, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: tara.chaidez@faa.gov; 

telephone (781) 238–7773; fax (781) 238– 

7199, for more information about this AD. 

Issued in Burlington, Massachusetts, on 

May 12, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–11998 Filed 5–18–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0480; Directorate 

Identifier 2010–NM–035–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–400 and 747– 

400D Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model 747–400 and 747–400D series 

airplanes. This proposed AD would 


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