36420 Federal Register / Vol. 74, No. 140 / Thursday, July 23, 2009 / Proposed Rules 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2500, dated December 21, 2004; or 

Revision 1, dated September 25, 2008; except 

as required by paragraph (h) or provided by 

paragraph (l) of this AD. After the effective 

date of this AD, Boeing Alert Service Bulletin 

747–53A2500, Revision 1, dated September 

25, 2008, must be used. Do the initial and 

repetitive inspections at the applicable times 

specified in paragraph (g)(1) or (g)(2) of this 

AD, except as required by paragraph (j) of 

this AD. Repair any crack before further flight 

after detection. 

(1) For Groups 1 through 7, 9, and 10 

identified in Boeing Alert Service Bulletin 

747–53A2500, Revision 1, dated September 

25, 2008: Do the initial and repetitive 

inspections at the times specified in 

paragraph 1.E. of Boeing Alert Service 

Bulletin 747–53A2500, dated December 21, 

2004, except as required by paragraph (i) of 

this AD. 

(2) For Group 8 airplanes identified in 

Boeing Alert Service Bulletin 747–53A2500, 

Revision 1, dated September 25, 2008: Do the 

initial and repetitive inspections at the 

applicable time specified in paragraph 1.E. of 

Boeing Alert Service Bulletin 747–53A2500, 

Revision 1, dated September 25, 2008, except 

as required by paragraph (k) of this AD. 

Exceptions to Service Bulletin Procedures 

(h) If any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2500, dated 

December 21, 2004, or Revision 1, dated 

September 25, 2008, specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (m) of this AD. 

(i) Where Boeing Alert Service Bulletin 

747–53A2500, dated December 21, 2004, or 

Revision 1, dated September 25, 2008, 

specifies a compliance time after the date on 

the original issue of the service bulletin, this 

AD requires compliance within the specified 

compliance time after April 6, 2006 (the 

effective date of AD 2006–05–02). 

New Requirements of This AD 

Actions for Additional Areas 

(j) For the additional inspection areas of 

Groups 1 through 7, 9, and 10 airplanes, 

identified in Boeing Alert Service Bulletin 

747–53A2500, Revision 1, dated September 

25, 2008: Do initial and repetitive inspections 

for cracking of the inspection areas, and, as 

applicable, repair cracking, by doing all the 

actions specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2500, Revision 1, dated September 

25, 2008; except as required by paragraph (h) 

of this AD. Do the initial and repetitive 

inspections at the times specified in 

paragraph 1.E. of Boeing Alert Service 

Bulletin 747–53A2500, Revision 1, dated 

September 25, 2008, except as required by 

paragraph (k) of this AD. Repair all cracking 

before further flight. 

(k) Where Boeing Alert Service Bulletin 

747–53A2500, Revision 1, dated September 

25, 2008, specifies a compliance time after 

the date on Revision 1 of the service bulletin, 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(l) For Group 8 airplanes, inspection of 

Areas 2 and 5 identified in Boeing Alert 

Service Bulletin 747–53A2500, dated 

December 21, 2004 as required by paragraph 

(g) of this AD is no longer required. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(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, email 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 2006–05–02, are 

approved as alternative methods of 

compliance with the corresponding 

requirements of this AD. 

(4) Accomplishment of the inspections 

specified in this AD is considered an AMOC 

for the applicable requirements of paragraphs 

(c) and (d) of AD 2004–07–22 R1, amendment 

39–15326, under the conditions specified in 

paragraphs (m)(4)(i) and (m)(4)(ii) of this AD. 

(i) The inspections specified in this AD 

must be done within the compliance times 

specified in AD 2004–07–22 R1. The initial 

inspection specified in this AD must be done 

at the times specified in paragraph (d) of AD 

2004–07–22 R1, and the inspections 

specified in this AD must be repeated within 

the intervals specified in paragraph (g) of this 

AD. 

(ii) The AMOC applies only to the areas of 

Supplemental Structural Inspection 

Document for Model 747 Airplanes, 

Document D6–35022, Revision G, dated 

December 2000, that are specified in Boeing 

Alert Service Bulletin 747–53A2500, dated 

December 21, 2004. 

(5) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who 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. 

Issued in Renton, Washington, on July 15, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–17448 Filed 7–22–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0606; Directorate 

Identifier 2009–NE–11–AD] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A Model CFM56–3B1 

and –3B2 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain CFM International Model 

CFM56–3B1 and -3B2 turbofan engines. 

This proposed AD would require initial 

and repetitive inspections for damage to 

the fan blades. This proposed AD results 

from a report of a failed fan blade with 

severe out-of-limit wear on the 

underside of the blade platform where 

it contacts the damper. We are 

proposing this AD to prevent failure of 

multiple fan blades, which could result 

in an uncontained failure of the engine 

and damage to the airplane. 

DATES: We must receive any comments 

on this proposed AD by September 21, 

2009. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• 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 CFM International, S. A., 

Technical Publication Department, 1 

Neumann Way, Cincinnati, OH 45215; 

telephone (513) 552–2800; fax (513) 

552–2816, for a copy of the service 

information identified in this proposed 

AD. 


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Federal Register / Vol. 74, No. 140 / Thursday, July 23, 2009 / Proposed Rules 36421 

FOR FURTHER INFORMATION CONTACT: 

Stephen K. Sheely, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: stephen.k.sheely@faa.gov; 

telephone (781) 238–7750; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2009–0606; Directorate Identifier 2009– 

NE–11–AD’’ in the subject line of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of 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). 

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. 

Discussion 

On February 13, 2006, we received a 

report of a failed fan blade with a 25 

degrees midspan shroud. The underside 

of the blade platform had severe out-oflimit wear at a contact point with the 

damper. We couldn’t determine the 

exact root cause for the wear. However, 

poor damping of the 25 degrees 

midspan shroud blade set due to severe 

wear on several dampers and the 

undersides of the fan blade platforms 

contributed to high dynamic stress 

levels seen on this set of blades. This 

condition, if not corrected, could result 

in failure of multiple fan blades, which 

could result in an uncontained failure of 

the engine and damage to the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of CFM International 

Service Bulletin (SB) CFM56–3/3B/3C 

S/B 72–1067, dated February 15, 2007, 

that describes procedures for performing 

on-wing and in-shop inspections for 

wear. 

Differences Between the Proposed AD 

and the Manufacturer’s Service 

Information 

CFM International SB CFM56–3/3B/ 

3C S/B 72–1067, dated February 15, 

2007, requires an initial inspection 

within 6 months. This proposed AD 

would require the initial inspection 

within 3,000 cycles-in-service (CIS) after 

the effective date of the proposed AD. 

CFM International SB CFM56–3/3B/3C 

S/B 72–1067, dated February 15, 2007, 

also requires a repetitive inspection 

within 1,500 to 3,000 cycles-since-last 

inspection (CSLI). This proposed AD 

would require the repetitive inspection 

within 3,000 CSLI. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. We are proposing this AD, 

which would require performing initial 

and repetitive inspections of the fan 

blade for wear. The proposed AD would 

require you to use the service 

information described previously to 

perform these actions. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 50 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 8 

work-hours per engine to perform the 

proposed actions, and that the average 

labor rate is $80 per work-hour. 

Required parts would cost about 

$38,000 per engine. Based on these 

figures, we estimate the total cost of the 

proposed AD to U.S. operators to be 

$1,932,000. 

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 

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 distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed 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. Would 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. 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. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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: 


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36422 Federal Register / Vol. 74, No. 140 / Thursday, July 23, 2009 / Proposed Rules 

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: 

CFM International S.A.: Docket No. FAA– 

2009–0606; Directorate Identifier 2009– 

NE–11–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

September 21, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to CFM International 

S.A. model CFM56–3B1 and -3B2 turbofan 

engines with 25 degrees midspan shroud fan 

blades, part numbers (P/Ns) 9527M99P08, 

9527M99P09, 9527M99P10, 9527M99P11, 

1285M39P01, or fan blade pairs, P/Ns 335– 

088–901–0, 335–088–902–0, 335–088–903–0, 

and 335–088–904–0 installed. These engines 

are installed on, but not limited to, Boeing 

737 series airplanes. 

Unsafe Condition 

(d) This AD results from a report of a failed 

fan blade with severe out-of-limit wear on the 

underside of the blade platform where it 

contacts the damper. We are issuing this AD 

to prevent failure of multiple fan blades, 

which could result in an uncontained failure 

of the engine 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. 

Inspection for Wear 

(f) Within 3,000 cycles-in-service after the 

effective date of this AD, perform an on-wing 

or in-shop inspection of the fan blade and 

damper for wear. Use paragraph 3. 

Accomplishment Instructions of CFM 

International Service Bulletin (SB) CFM56–3/ 

3B/3C S/B 72–1067, dated February 15, 2007. 

(g) If you find wear, perform additional 

inspections as specified in paragraph 3. 

Accomplishment Instructions of CFM 

International SB CFM56–3/3B/3C S/B 72– 

1067, dated February 15, 2007. 

(h) Thereafter, within intervals not to 

exceed 3,000 cycles-since-last inspection, 

perform an on-wing or in-shop inspection for 

wear. Use paragraph 3. Accomplishment 

Instructions of CFM International SB 

CFM56–3/3B/3C S/B 72–1067, dated 

February 15, 2007. 

(i) If you find wear, perform additional 

inspections as specified in paragraph 3. 

Accomplishment Instructions of CFM 

International SB CFM56–3/3B/3C S/B 72– 

1067, dated February 15, 2007. 

Installation Prohibition 

(j) After the effective date of this AD, don’t 

install any 25 degrees midspan shroud fan 

blades, P/Ns 9527M99P08, 9527M99P09, 

9527M99P10, 9527M99P11, 1285M39P01, or 

fan blade pairs, P/Ns 335–088–901–0, 335– 

088–902–0, 335–088–903–0, and 335–088– 

904–0, unless they have passed an inspection 

specified in paragraph 3. Accomplishment 

Instructions of CFM International SB 

CFM56–3/3B/3C S/B 72–1067, dated 

February 15, 2007. 

Optional Terminating Action 

(k) Replacing the 25 degrees midspan 

shroud fan blade set with a 37 degrees 

midspan shroud fan blade set terminates the 

repetitive inspection requirements specified 

in paragraph (h) of this AD. 

Alternative Methods of Compliance 

(l) 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 

(m) Contact Stephen K. Sheely, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: stephen.k.sheely@faa.gov; 

telephone (781) 238–7750; fax (781) 238– 

7199, for more information about this AD. 

(n) CFM International SB CFM56–3/3B/3C 

S/B 72–1067, dated February 15, 2007, 

pertains to the subject of this AD. Contact 

CFM International, S. A., Technical 

Publication Department, 1 Neumann Way, 

Cincinnati, OH 45215; telephone (513) 552– 

2800; fax (513) 552–2816, for a copy of this 

service information. 

(o) EASA airworthiness directive 2009– 

0036, dated February 20, 2009, also addresses 

the subject of this AD. 

Issued in Burlington, Massachusetts, on 

July 16, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–17473 Filed 7–22–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0674; Directorate 

Identifier 2009–NE–25–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211 Trent 800 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: Under certain ambient 

conditions, ice can accumulate on the 

walls of the fuel pipes within the 

aircraft fuel system, which can then be 

released downstream when fuel flow 

demand is increased. This released ice 

can then collect on the fuel-to-oil heat 

exchanger (FOHE) front face and limit 

fuel flow through the FOHE. 

We are proposing this AD to prevent 

ice from blocking the FOHE, which 

could result in an unacceptable engine 

power loss, and loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by August 24, 2009. 

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, UK; telephone 44 (0) 

1332 242424; fax 44 (0) 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: 

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: 


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