Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 55121 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, International Branch, 

ANM–116, 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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. 

(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. 

Related Information 

(k) European Aviation Safety Agency 

Airworthiness Directive 2007–0094 R1, dated 

May 2, 2007, also addresses the subject of 

this AD. 

Material Incorporated by Reference 

(l) You must use Airbus A300 Fuel 

Airworthiness Limitations, Document 

95A.1928/05, Issue 2, dated May 11, 2007, to 

do the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

previously approved the incorporation by 

reference of Airbus A300 Fuel Airworthiness 

Limitations, Document 95A.1928/05, Issue 2, 

dated May 11, 2007, on November 28, 2007 

(72 FR 60240, October 24, 2007). 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.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 or 425–227–1152. 

(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 October 

19, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–25772 Filed 10–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0037; Directorate 

Identifier 2007–NE–41–AD; Amendment 39– 

16052; AD 2009–22–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd. & Co. KG. (RRD) Tay 

650–15 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires initial and repetitive 

inspections of the low-pressure (LP) 

turbine discs stage 2 and stage 3 for 

corrosion, on certain serial number 

engines. This AD requires the same 

actions, but extends the applicability to 

additional engine serial numbers. 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: 

Strip results from some of the engines 

listed in the applicability section of this 

directive revealed excessively corroded lowpressure turbine disks stage 2 and stage 3. 

The corrosion is considered to be caused by 

the environment in which these engines are 

operated. Following a life assessment based 

on the strip findings it is concluded that 

inspections for corrosion attack are required. 

The action specified by this AD is intended 

to avoid a failure of a low-pressure turbine 

disk stage 2 or stage 3 due to potential 

corrosion problems which could result in 

uncontained engine failure and damage to 

the airplane. 

We are issuing this AD to detect 

corrosion that could cause the stage 2 or 

stage 3 disk of the LP turbine to fail and 

result in an uncontained failure of the 

engine. 

DATES: This AD becomes effective 

November 12, 2009. 

We must receive comments on this 

AD by November 27, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of Rolls-Royce Deutschland Alert 

Service Bulletin No. TAY–72–A1524, 

Revision 2, dated June 13, 2008, listed 

in the AD as of November 12, 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: 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. 

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 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: 

Jason Yang, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: jason.yang@faa.gov; telephone 

(781) 238–7747; fax (781) 238–7199. 

Contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11, Dahlwitz, 

15827 Blankenfelde-Mahlow, Germany; 

telephone 49 (0) 33–7086–1768; fax 49 

(0) 33–7086–3356, for the service 

information referenced in this AD. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 5, 2008, the FAA issued AD 

2008–10–14 (Amendment 39–15521 (73 

FR 29405, May 21, 2008). That AD 

requires initial and repetitive 

inspections of the LP turbine discs stage 

2 and stage 3 for corrosion on 45 

engines by serial number. That AD was 

the result of MCAI issued by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. That condition, if not 

corrected, could result in the stage 2 or 

stage 3 disk of the LP turbine to fail and 

result in an uncontained failure of the 

engine. 

Since AD 2008–10–14 was issued, 

RRD identified 34 additional engines by 

serial number that require the same 

inspections. The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2008– 

0122, dated July 1, 2008. That MCAI 


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55122 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 

extends the applicability to include the 

34 additional engine serial numbers for 

inspections. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Rolls-Royce Deutschland has issued 

Alert Service Bulletin No. TAY–72– 

A1524, Revision 2, dated June 13, 2008. 

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 AD 

Although no airplanes that are 

registered in the United States use these 

RRD Tay 650–15 engines, the possibility 

exists that the engines could be used on 

airplanes that are registered in the 

United States in the future. The unsafe 

condition described previously is likely 

to exist or develop on other RRD Tay 

650–15 engines of the same type design. 

We are issuing this AD to detect 

corrosion that could cause the stage 2 or 

stage 3 disk of the LP turbine to fail and 

result in an uncontained failure of the 

engine. This AD requires initial and 

repetitive inspections of the LP turbine 

discs stage 2 and stage 3 for corrosion 

on certain serial number engines. You 

must use the service information 

described previously to perform the 

actions required by this AD. 

FAA’s Determination of the Effective 

Date 

Since no domestic operators use this 

product, notice and opportunity for 

public comment before issuing this AD 

are unnecessary. Therefore, we are 

adopting this regulation immediately. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2007–0037; 

Directorate Identifier 2007–NE–41–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because 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 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). 

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. 

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 

removing Amendment 39–15521 (73 FR 

29405, May 21, 2008), and by adding a 

new airworthiness directive, 

Amendment 39–16052, to read as 

follows: 

2009–22–01 Rolls-Royce Deutschland Ltd & 

Co KG (RRD) (formerly Rolls-Royce plc, 

Derby, England): Amendment 39–16052. 

Docket No. FAA–2007–0037; Directorate 

Identifier 2007–NE–41–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 12, 2009. 

Affected ADs 

(b) This AD supersedes AD 2008–10–14, 

Amendment 39–15521. 

Applicability 

(c) This AD applies to RRD Tay 650–15 

turbofan engines that have a serial number 

listed in Table 1 or Table 2 of this AD, and 

low-pressure (LP) turbine module 

M05300AA installed. These engines are 

installed on, but not limited to, Fokker F28 

Mark 0100 airplanes. 

TABLE 1—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (CARRIED

FORWARD FROM AD 2008–10–14) 

Engine Serial Number 

17251 

17255 

17256 

17273 

17275 

17280 

17281 

17282 

17300 

17301 

17327 

17332 

17365 

17393 

17437 

17443 

17470 

17520 


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Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 55123 

TABLE 1—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (CARRIED

FORWARD FROM AD 2008–10– 

14)—Continued 

Engine Serial Number 

17521 

17523 

17539 

17542 

17556 

17561 

17562 

17563 

17580 

17581 

17612 

17618 

17635 

17637 

17645 

17661 

17686 

17699 

17701 

17702 

17736 

17737 

17738 

17739 

17741 

17742 

17808 

TABLE 2—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (ADDED

NEW IN THIS AD) 

Engine Serial Number 

17249 

17303 

17358 

17370 

17425 

17426 

17433 

17438 

17445 

17446 

17460 

17474 

17478 

17490 

17491 

17517 

17518 

17522 

17534 

17535 

17536 

17538 

17540 

17541 

17552 

17553 

17585 

17613 

17723 

17724 

17740 

17759 

TABLE 2—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (ADDED

NEW IN THIS AD)—Continued 

Engine Serial Number 

17760 

17807 

Reason 

(d) Strip results from some of the engines 

listed in the applicability section of this 

directive revealed excessively corroded lowpressure turbine disks stage 2 and stage 3. 

The corrosion is considered to be caused by 

the environment in which these engines are 

operated. Following a life assessment based 

on the strip findings it is concluded that 

inspections for corrosion attack are required. 

The action specified by this AD is intended 

to avoid a failure of a low-pressure turbine 

disk stage 2 or stage 3 due to potential 

corrosion problems which could result in 

uncontained engine failure and damage to 

the airplane. 

We are issuing this AD to detect corrosion 

that could cause the stage 2 or stage 3 disk 

of the LP turbine to fail and result in an 

uncontained failure of the engine. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Prior to accumulating 11,700 flight 

cycles (FC) since new, and thereafter at 

intervals not exceeding 11,700 FC of the 

engine, inspect the LP turbine disks stage 2 

and stage 3 for corrosion in accordance with 

RRD Alert Service Bulletin No. TAY–72– 

A1524, Revision 2, dated June 13, 2008. 

(2) For engines that already exceed 11,700 

FC on the effective date of this AD, perform 

the inspection within 90 days after the 

effective date of this AD. 

(3) When, during any of the inspections as 

required by paragraph (e)(1) of this directive, 

corrosion is found, replace the affected parts. 

The RRD TAY 650 Engine Manual—E–TAY– 

3RR, Tasks 72–52–23–200–000 and 72–52– 

24–200–000 contains guidance on performing 

the 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 of this 

AD using RRD Alert Service Bulletin No. 

TAY–72–A1524, Revision 1, dated 

September 1, 2006, 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 European Aviation Safety 

Agency AD 2008–0122, dated July 1, 2008, 

for related information. 

(i) Contact Jason Yang, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: jason.yang@faa.gov; telephone 

(781) 238–7747; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(j) You must use Rolls-Royce Deutschland 

Alert Service Bulletin No. TAY–72–A1524, 

Revision 2, dated June 13, 2008, to do the 

actions 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; telephone 

49 (0) 33–7086–1768; fax 49 (0) 33–7086– 

3356. 

(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 

October 8, 2009. 

Diane S. Romanosky, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–25031 Filed 10–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0996; Directorate 

Identifier 2009–NM–156–AD; Amendment 

39–16061; AD 2007–21–14 R1] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD), 

which applies to all Airbus Model A310 

airplanes. That AD currently requires 

revising the Airworthiness Limitations 

Section of the Instructions for 

Continued Airworthiness to incorporate 

new limitations for fuel tank systems. 

This AD clarifies the intended effect of 

the AD on spare and on-airplane fuel 

tank system components. This AD 

results from fuel system reviews 

conducted by the manufacturer. We are 


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