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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55124 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 

issuing this AD to prevent the potential 

of ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors caused by latent failures, 

alterations, repairs, or maintenance 

actions, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: This AD is effective November 

12, 2009. 

On November 20, 2007 (72 FR 58499, 

October 16, 2007), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the AD. 

We must receive any comments on 

this AD by December 11, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 Office (telephone 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1622; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 5, 2007, we issued AD 

2007–21–14, amendment 39–15232 (72 

FR 58499, October 16, 2007). That AD 

applied to all Airbus Model A310 

airplanes. That AD required revising the 

Airworthiness Limitations Section of 

the Instructions for Continued 

Airworthiness to incorporate new 

limitations for fuel tank systems. 

Critical design configuration control 

limitations (CDCCLs) are limitation 

requirements to preserve a critical 

ignition source prevention feature of the 

fuel tank system design that is necessary 

to prevent the occurrence of an unsafe 

condition. The purpose of a CDCCL is 

to provide instruction to retain the 

critical ignition source prevention 

feature during configuration change that 

may be caused by alterations, repairs, or 

maintenance actions. A CDCCL is not a 

periodic inspection. 

Actions Since AD Was Issued 

Since we issued that AD, we have 

determined that it is necessary to clarify 

the AD’s intended effect on spare and 

on-airplane fuel tank system 

components, regarding the use of 

maintenance manuals and instructions 

for continued airworthiness. 

Section 91.403(c) of the Federal 

Aviation Regulations (14 CFR 91.403(c) 

specifies the following: 

No person may operate an aircraft for 

which a manufacturer’s maintenance manual 

or instructions for continued airworthiness 

has been issued that contains an 

airworthiness limitation section unless the 

mandatory * * * procedures * * * have 

been complied with. 

Some operators have questioned 

whether existing components affected 

by the new CDCCLs must be reworked. 

We did not intend for the AD to 

retroactively require rework of 

components that had been maintained 

using acceptable methods before the 

effective date of the AD. Owners and 

operators of the affected airplanes 

therefore are not required to rework 

affected components identified as 

airworthy or installed on the affected 

airplanes before the required revisions 

of the Airworthiness Limitations 

Section of the Instructions for 

Continued Airworthiness. But once the 

CDCCLs are incorporated into the 

Airworthiness Limitations Section of 

the Instructions for Continued 

Airworthiness, future maintenance 

actions on components must be done in 

accordance with those CDCCLs. 

FAA’s Determination and Requirements 

of This AD 

The affected product(s) have been 

approved by the aviation authority of 

another country, and are approved for 

operation in the United States. We are 

issuing this AD because we evaluated 

all pertinent information and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

new AD retains the requirements of the 

existing AD, and adds a new note to 

clarify the intended effect of the AD on 

spare and on-airplane fuel tank system 

components. 

Costs of Compliance 

This revision imposes no additional 

economic burden. The current costs for 

this AD are repeated for the 

convenience of affected operators, as 

follows: 

This AD affects about 69 airplanes of 

U.S. registry. The required actions take 

about 2 work hours per airplane, at an 

average labor rate of $80 per work hour. 

Based on these figures, the estimated 

cost of the AD for U.S. operators is 

$11,040, or $160 per airplane. 

FAA’s Justification and Determination 

of the Effective Date 

This revision merely clarifies the 

intended effect on spare and on-airplane 

fuel tank system components, and 

makes no substantive change to the 

AD’s requirements. For this reason, it is 

found that notice and opportunity for 

prior public comment for this action are 

unnecessary, and good cause exists for 

making this amendment effective in less 

than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2009–0996; Directorate Identifier 2009– 

NM–156–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 we receive 

about this AD. 


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Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 55125 

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 the 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 AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 part 39 of the Federal 

Aviation Regulations (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 39–15232 (72 FR 

58499, October 16, 2007) and adding the 

following new AD: 

2007–21–14 R1 Airbus: Amendment 39– 

16061. Docket No. FAA–2009–0996; 

Directorate Identifier 2009–NM–156–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective November 12, 2009. 

Affected ADs 

(b) This AD revises AD 2007–21–14. 

Applicability 

(c) This AD applies to all Airbus Model 

A310–203, –204, –221, –222, –304, –322, 

–324, and –325 airplanes, certificated in any 

category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections and critical design 

configuration control limitations (CDCCLs). 

Compliance with the operator maintenance 

documents is required by 14 CFR 91.403(c). 

For airplanes that have been previously 

modified, altered, or repaired in the areas 

addressed by these inspections and CDCCLs, 

the operator may not be able to accomplish 

the inspections and CDCCLs described in the 

revisions. In this situation, to comply with 14 

CFR 91.403(c), the operator must request 

approval for an alternative method of 

compliance according to paragraph (j) of this 

AD. The request should include a description 

of changes to the required inspections and 

CDCCLs that will preserve the critical 

ignition source prevention feature of the 

affected fuel system. 

Unsafe Condition 

(d) This AD results from fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent the potential 

of ignition sources inside fuel tanks, which, 

in combination with flammable fuel vapors 

caused by latent failures, alterations, repairs, 

or maintenance actions, could result in fuel 

tank explosions and consequent loss of 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. 

Restatement of AD 2007–21–14, With No 

Changes 

Revise Airworthiness Limitations Section 

(ALS) To Incorporate Fuel Maintenance and 

Inspection Tasks 

(f) Within 3 months after November 20, 

2007 (the effective date of AD 2007–21–14), 

revise the ALS of the Instructions for 

Continued Airworthiness to incorporate 

Airbus A310 ALS Part 5—Fuel Airworthiness 

Limitations, dated May 31, 2006, as defined 

in Airbus A310 Fuel Airworthiness 

Limitations, Document 95A.1930/05, Issue 2, 

dated May 11, 2007 (approved by the 

European Aviation Safety Agency (EASA) on 

July 6, 2007), Section 1, ‘‘Maintenance/ 

Inspection Tasks.’’ For all tasks identified in 

Section 1 of Document 95A.1930/05, the 

initial compliance times start from the later 

of the times specified in paragraphs (f)(1) and 

(f)(2) of this AD, and the repetitive 

inspections must be accomplished thereafter 

at the intervals specified in Section 1 of 

Document 95A.1930/05, except as provided 

by paragraph (g) of this AD. 

(1) November 20, 2007. 

(2) The date of issuance of the original 

French standard airworthiness certificate or 

the date of issuance of the original French 

export certificate of airworthiness. 

Note 2: Airbus Operator Information Telex 

SE 999.0079/07, Revision 01, dated August 

14, 2007, identifies the applicable sections of 

the Airbus A310 Airplane Maintenance 

Manual necessary for accomplishing the 

tasks specified in Section 1 of Document 

95A.1930/05. 

Initial Compliance Time for Task 28–18–00– 

03–1 

(g) For Task 28–18–00–03–1 identified in 

Section 1 of Document 95A.1930/05, 

‘‘Maintenance/Inspection Tasks,’’ of Airbus 

A310 Fuel Airworthiness Limitations, 

Document 95A.1930/05, Issue 2, dated May 

11, 2007 (approved by the EASA on July 6, 

2007): The initial compliance time is the later 

of the times specified in paragraphs (g)(1) 

and (g)(2) of this AD. Thereafter, Task 28–18– 

00–03–1 must be accomplished at the 

repetitive interval specified in Section 1 of 

Document 95A.1930/05. 

(1) Prior to the accumulation of 40,000 

total flight hours. 

(2) Within 72 months or 20,000 flight hours 

after November 20, 2007, whichever occurs 

first. 

Revise ALS To Incorporate CDCCLs 

(h) Within 12 months after November 20, 

2007, revise the ALS of the Instructions for 

Continued Airworthiness to incorporate 

Airbus A310 ALS Part 5—Fuel Airworthiness 

Limitations, dated May 31, 2006, as defined 

in Airbus A310 Fuel Airworthiness 

Limitations, Document 95A.1930/05, Issue 2, 

dated May 11, 2007 (approved by the EASA 

on July 6, 2007), Section 2, ‘‘Critical Design 

Configuration Control Limitations.’’ 

No Alternative Inspections, Inspection 

Intervals, or CDCCLs 

(i) Except as provided by paragraph (j) of 

this AD: After accomplishing the actions 

specified in paragraphs (f) and (h) of this AD, 

no alternative inspections, inspection 

intervals, or CDCCLs may be used. 

New Information 

Explanation of CDCCL Requirements 

Note 3: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 


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55126 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 

airworthy or installed on the affected 

airplanes before the revision of the ALS, as 

required by paragraph (f) of this AD, do not 

need to be reworked in accordance with the 

CDCCLs. However, once the ALS has been 

revised, future maintenance actions on these 

components must be done in accordance 

with the CDCCLs. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) 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 Stafford, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1622; 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. 

Related Information 

(k) EASA airworthiness directive 2007– 

0096 R1, dated May 2, 2007, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(l) You must use Airbus A310 ALS Part 5— 

Fuel Airworthiness Limitations, dated May 

31, 2006; and Airbus A310 Fuel 

Airworthiness Limitations, Document 

95A.1930/05, 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 A310 ALS Part 5—Fuel 

Airworthiness Limitations, dated May 31, 

2006; and Airbus A310 Fuel Airworthiness 

Limitations, Document 95A.1930/05, Issue 2, 

dated May 11, 2007; on November 20, 2007 

(72 FR 58499, October 16, 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. E9–25774 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–2009–0018; Directorate 

Identifier 2009–NE–01–AD; Amendment 39– 

16044; AD 2009–21–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF6–80C2 Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for General 

Electric Company (GE) CF6–80C2 series 

turbofan engines with certain thrust 

reverser ballscrew gearbox assembly 

adjustable-length end actuators 

installed. This AD requires initial visual 

inspections and repetitive replacements 

of the 3⁄8-inch rod-ends installed on the 

thrust reverser ballscrew gearbox 

assembly adjustable-length end 

actuators. This AD also allows an 

optional terminating action to those 

repetitive replacements. This AD also 

requires initial visual inspections and 

replacements, if necessary, of the other 

hardware connecting the thrust reverser 

transcowls to the engine. This AD 

results from reports of four failures of 

rod-ends on certain thrust reverser 

ballscrew gearbox assembly adjustablelength end actuators, leading to partial 

or complete separation of the transcowl 

from the engine and airplane during 

thrust reversal. We are issuing this AD 

to prevent loss of asymmetric thrust and 

thrust control. 

DATES: This AD becomes effective 

December 1, 2009. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of December 1, 2009. 

ADDRESSES: You can get the service 

information identified in this AD from 

Middle River Aircraft Systems, 103 

Chesapeake Park Plaza, MF 46, 

Baltimore, MD 21220; telephone (410) 

682–0080; fax (410) 682–0100; or e-mail: 

bulletins@mras-usa.com. 

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: 

Christopher J. Richards, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; e-mail: 

christopher.j.richards@faa.gov; 

telephone (781) 238–7133; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to GE CF6–80C2 series turbofan 

engines with certain thrust reverser 

ballscrew gearbox assembly adjustablelength end actuators installed. We 

published the proposed AD in the 

Federal Register on March 16, 2009 (74 

FR 11043). That action proposed to 

require initial visual inspections and 

repetitive replacements of the 3⁄8-inch 

rod-ends installed on the thrust reverser 

ballscrew gearbox assembly adjustablelength end actuators. That action also 

proposed to allow optional terminating 

action to those repetitive replacements. 

That action also proposed to require 

initial visual inspections and 

replacements, if necessary, of the other 

hardware connecting the thrust reverser 

transcowls to the engine. 

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 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. 

Continue Operating to Next C-Check 

Lufthansa Technik asks if the current 

risk assessment for the 3⁄8-inch rod-ends 

failure also takes into account mixed 

configurations, meaning lower or upper 

position with 7⁄16-inch or fixed 

configuration rod-ends. The commenter 

states that if so, then a mixed 

configuration should therefore allow the 

operator to continue operating until 

next C-Check without any higher risk. 


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