30020 Federal Register / Vol. 74, No. 120 / Wednesday, June 24, 2009 / Proposed Rules 

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: 

Authority : 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing Amendment 39–15075 (72 FR 

30249, May 31, 2007), and by adding a 

new airworthiness directive, to read as 

follows: 

General Electric Company: Docket No. FAA– 

2006–24171; Directorate Identifier 2006– 

NE–08–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

August 24, 2009. 

Affected ADs 

(b) This AD revises AD 2007–11–18, 

Amendment 39–15075. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF6–50C, CF6–50C1, CF6– 

50C2, and CF6–50C2R turbofan engines, with 

a forward fan stator case, part number (P/N) 

9064M53G04, G05, G06, G07, G08, G09, G10, 

G12, or G13, or P/N 9173M37G01, G02, G03, 

G04, G05, or G06 installed. These engines are 

installed on, but not limited to, Airbus A300, 

McDonnell Douglas DC–10 series, and DC– 

10–30F (KC–10A, KDC–10) airplanes. 

Unsafe Condition 

(d) This AD revision results from a review 

that shows that only one of the service 

bulletins referenced in the original AD is 

applicable as a compliance method. We are 

issuing this AD to prevent uncontained fan 

blade failures, which can result in separation 

of airplane hydraulic lines, damage to critical 

airplane systems, and possible loss of 

airplane control. 

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. 

(f) At the next engine shop visit after the 

effective date of this AD, but no later than 

June 30, 2010, rework the forward fan stator 

case and install the fan module secondary 

containment shield. 

(1) For engines on Airbus 300 series 

airplanes, use paragraph 3, Accomplishment 

Instructions, of GE Service Bulletin (SB) No. 

CF6–50 S/B 72–0985, Revision 2, dated 

March 21, 2007, to do the rework and 

installation. 

(2) Deleted. 

(g) The rework and installation specified in 

paragraph (f)(1) of this AD can also be done 

on-wing. 

Previous Credit 

(h) Previous credit is allowed for fan stator 

cases reworked and containment shields 

installed using GE SB No. CF6–50 S/B 72– 

0985, dated December 2, 1991 or Revision 1, 

dated September 15, 1998 before the effective 

date of this AD. 

Alternative Methods of Compliance 

(i) 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 

(j) European Aviation Safety Agency 

airworthiness directive 2004–0007, dated 

December 15, 2004, also addresses the 

subject of this AD. 

(k) Contact James Rosa, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.rosa@faa.gov; telephone 

(781) 238–7152; fax (781) 238–7199, for more 

information about this AD. 

(l) Contact General Electric Company via 

Lockheed Martin Technology Services, 10525 

Chester Road, Suite C, Cincinnati, Ohio 

45215, telephone (513) 672–8400, fax (513) 

672–8422, for a copy of the service 

information referenced in this AD. 

Issued in Burlington, Massachusetts, on 

June 17, 2009. 

Carlos Pestana, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–14815 Filed 6–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0143; Directorate 

Identifier 2009–NE–05–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company GE90–110B1, GE90– 

113B, and GE90–115B Series 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 

General Electric Company (GE) GE90– 

110B1, GE90–113B, and GE90–115B 

series turbofan engines with stage 6 lowpressure turbine (LPT) blades, part 

number (P/N) 1765M37P03 or P/N 

1765M37P04, installed. This proposed 

AD would require initial and repetitive 

inspections for shroud interlock wear of 

the stage 6 LPT blades. This proposed 

AD would also require replacing those 

blades with stage 6 LPT blades eligible 

for installation at the next engine shop 

visit as terminating action to the 

repetitive blade inspections. This 

proposed AD results from eight reports 

of GE90–115B stage 6 LPT single-blade 

separation events. We are proposing this 

AD to prevent failure of stage 6 LPT 

blades, which could result in 

uncontained engine failure and damage 

to the airplane. 

DATES: We must receive any comments 

on this proposed AD by August 24, 

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 General Electric Company via 

GE—Aviation, Attn: Distributions, 111 

Merchant St., Room 230, Cincinnati, 

Ohio 45246; telephone (513) 552–3272; 

fax (513) 552–3329, for a copy of the 

service information identified in this 

proposed AD. 

FOR FURTHER INFORMATION CONTACT: 

Barbara Caufield, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: barbara.caufield@faa.gov; 

telephone (781) 238–7146; 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– 

2009–0143; Directorate Identifier 2009– 

NE–05–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 

Federal Register / Vol. 74, No. 120 / Wednesday, June 24, 2009 / Proposed Rules 30021 

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 

Since December of 2007, GE reported 

eight instances of stage 6 LPT singleblade failures in some GE90 series 

engines. GE’s investigation indicated 

that excessive wear at the shroud 

interlock of stage 6 LPT blades, P/N 

1765M37P03 or P/N 1765M37P04, 

caused the failures. The interlock 

surface wears during operation which 

results in a loss of axial preload (contact 

between two surfaces) between two 

adjacent stage 6 LPT blades. This wear 

leads to increased tip deflection and 

blade stress. This condition, if not 

corrected, could result in failure of stage 

6 LPT blades, which could result in 

uncontained engine failure and damage 

to the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of GE Service 

Bulletin No. GE90–100 SB 72–0260, 

Revision 6, dated May 1, 2009. That SB 

describes procedures for inspecting 

stage 6 LPT blades, P/N 1765M37P03, 

and P/N 1765M37P04, for shroud 

interlock wear. 

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 initial and 

repetitive inspections for shroud 

interlock wear of stage 6 LPT blades, P/ 

N 1765M37P03 and P/N 1765M37P04. 

This proposed AD would also require 

replacing those blades with stage 6 LPT 

blades eligible for installation, at the 

next engine shop visit, as terminating 

action to the repetitive blade 

inspections. 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 four GE GE90 series 

engines installed on airplanes of U.S. 

registry. We also estimate that it would 

take about 18 work-hours per engine to 

perform one inspection of the stage 6 

LPT blades, and that the average labor 

rate is $80 per work-hour. Replacement 

stage 6 LPT blades would cost $258,280 

per engine. We estimate that no 

additional labor costs would be incurred 

to perform the required blade 

replacements, because the replacements 

would be done at the time of the engine 

shop visit. Based on these figures, we 

estimate the total cost of the proposed 

AD for one inspection to U.S. operators 

to be $1,038,880. 

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: 

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: 

General Electric Company: Docket No. FAA– 

2009–0143; Directorate Identifier 2009– 

NE–05–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

August 24, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) GE90–110B1, GE90–113B, and 

GE90–115B series turbofan engines with 

stage 6 low-pressure turbine (LPT) blades, 

part number (P/N) 1765M37P03 or P/N 

1765M37P04, installed. These engines are 

installed on, but not limited to, Boeing 777– 

200LR, 777–300ER, and 777 Freighter series 

airplanes. 

30022 Federal Register / Vol. 74, No. 120 / Wednesday, June 24, 2009 / Proposed Rules 

Unsafe Condition 

(d) This AD results from eight reports of 

GE90–115B stage 6 LPT single-blade 

separation events. We are issuing this AD to 

prevent failure of stage 6 LPT blades, which 

could result in uncontained engine failure 

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. 

Inspections 

(f) Before accumulating 3,000 engine 

operating hours time-since-new, or 400 

engine cycles-since-new, whichever occurs 

first, inspect the stage 6 LPT blades, P/N 

1765M37P03 or P/N 1765M37P04 for shroud 

interlock wear. Thereafter, reinspect within 

every 1,000 engine operating hours, or within 

125 engine cycles-since-last inspection, 

whichever occurs first. Use paragraphs 3.A. 

through 3.A.(3)(g)(12) of the Accomplishment 

Instructions of GE Service Bulletin (SB) No. 

GE90–100 SB 72–0260, Revision 6, dated 

May 1, 2009, to do the inspections. 

Terminating Action 

(g) At the next engine shop visit, replace 

stage 6 LPT blades, P/N 1765M37P03 or 

P/N 1765M37P04, with stage 6 LPT blades 

eligible for installation as terminating action 

to the repetitive inspections required by this 

AD. 

Installation Prohibition of Affected Stage 6 

LPT Blades 

(h) After the effective date of this AD, do 

not install any stage 6 LPT blades, P/N 

1765M37P03 or P/N 1765M37P04, onto any 

engine. 

Previous Credit 

(i) An inspection performed before the 

effective date of this AD using GE SB No. 

GE90–100 SB 72–0260, Revision 4, dated 

October 8, 2008, or Revision 5, dated 

November 7, 2008, satisfies the initial 

inspection requirement of this AD. 

Definition 

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

shop visit is induction of the engine into the 

shop for any cause. 

Alternative Methods of Compliance 

(k) 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 

(l) Contact Barbara Caufield, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: barbara.caufield@faa.gov; 

telephone (781) 238–7146; fax (781) 238– 

7199, for more information about this AD. 

(m) Guidance on stage 6 LPT blades that 

are eligible for installation can be found in 

GE Service Bulletin No. 72–0279, Revision 1, 

dated December 11, 2008, and GE Service 

Bulletin No. 72–0313, dated March 18, 2009. 

(n) Contact General Electric Company via 

GE—Aviation, Attn: Distributions, 111 

Merchant St., Room 230, Cincinnati, Ohio 

45246; telephone (513) 552–3272; fax (513) 

552–3329, for a copy of the service 

information identified in this AD. 

Issued in Burlington, Massachusetts, on 

June 17, 2009. 

Carlos Pestana, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–14807 Filed 6–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2009–0362; Airspace 

Docket No. 09–ASW–10] 

Proposed Establishment of Class D 

Airspace; Arlington, TX 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

establish Class D airspace at Arlington, 

TX. Establishment of an air traffic 

control tower at Arlington Municipal 

Airport has made this action necessary 

for the safety and management of 

Instrument Flight Rules (IFR) aircraft 

operations at Arlington Municipal 

Airport. 

DATES: 0901 UTC. Comments must be 

received on or before August 10, 2009. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. You must 

identify the docket number FAA–2009– 

0362/Airspace Docket No. 09–ASW–10, 

at the beginning of your comments. You 

may also submit comments on the 

Internet at http://www.regulations.gov. 

You may review the public docket 

containing the proposal, any comments 

received, and any final disposition in 

person in the Dockets Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Office (telephone 1–800–647– 

5527), is on the ground floor of the 

building at the above address. 

FOR FURTHER INFORMATION CONTACT: 

Scott Enander, Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone: (817) 321– 

7716. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers and be submitted in 

triplicate to the address listed above. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

on this notice must submit with those 

comments a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket No. FAA–2009–0362/Airspace 

Docket No. 09–ASW–10.’’ The postcard 

will be date/time stamped and returned 

to the commenter. 

Availability of NPRMs 

An electronic copy of this document 

may be downloaded through the 

Internet at http://www.regulations.gov. 

Recently published rulemaking 

documents can also be accessed through 

the FAA’s Web page at http:// 

www.faa.gov/airports_airtraffic/ 

air_traffic/publications/ 

airspace_amendments/. 

Additionally, any person may obtain 

a copy of this notice by submitting a 

request to the Federal Aviation 

Administration (FAA), Office of Air 

Traffic Airspace Management, ATA– 

400, 800 Independence Avenue, SW., 

Washington, DC 20591, or by calling 

(202) 267–8783. Communications must 

identify both docket numbers for this 

notice. Persons interested in being 

placed on a mailing list for future 

NPRMs should contact the FAA’s Office 

of Rulemaking, (202) 267–9677, to 

request a copy of Advisory Circular No. 

11–2A, Notice of Proposed Rulemaking 

Distribution System, which describes 

the application procedure. 

The Proposal 

This action proposes to amend Title 

14, Code of Federal Regulations (14 

CFR), part 71 by establishing Class D 

airspace from the surface up to but not 

including 2,000 feet MSL for IFR 

operations at Arlington Municipal 

Airport, Arlington, TX. The area would 

be depicted on appropriate aeronautical 

charts.