Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Proposed Rules 16809 

Removing LPCR Discs from Service 

(f) For engines with a second and 

third stage LPCR disc that has a serial 

number (SN) listed in Table 5 of 

Honeywell International Inc. Alert 

Service Bulletins (ASBs) TFE731–72– 

A3748, dated August 21, 2008, or 

TFE731–72–A3749, dated August 21, 

2008, remove the second and third stage 

LPCR disc from service within 100 

cycles-in-service (CIS) after the effective 

date of this AD. 

(g) For engines with a second and 

third stage LPCR disc that has an SN 

listed in Table 6 of Honeywell 

International Inc. ASBs TFE731–72– 

A3748, dated August 21, 2008, or 

TFE731–72–A3749, dated August 21, 

2008, do the earlier of the following: 

(1) Remove the second and third stage 

LPCR disc from service within 2,000 CIS 

after the effective date of this AD, or 

(2) Remove the second and third stage 

LPCR disc from service the next time 

the intermediate case is removed from 

the LPC case. 

Installation Prohibition 

(h) After the effective date of this AD, 

don’t install any second and third stage 

LPCR disc removed as required in 

paragraphs (f) or (g) of this AD. 

Alternative Methods of Compliance 

(i) The Manager, Los Angeles Aircraft 

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) Contact Joseph Costa, Aerospace 

Engineer, Los Angeles Aircraft 

Certification Office, FAA, Transport 

Airplane Directorate, 3960 Paramount 

Blvd., Lakewood, CA 90712–4137; email: joseph.costa@faa.gov; telephone: 

(562) 627–5246; fax: (562) 627–5210, for 

more information about this AD. 

(k) Honeywell International Inc. ASBs 

TFE731–72–A3748, dated August 21, 

2008, and TFE731–72–A3749, dated 

August 21, 2008, pertain to the subject 

of this AD. Contact Honeywell Engines 

and Systems Technical Publications and 

Distribution, M/S 2101–201, P.O. Box 

52170, Phoenix, AZ 85072–2170, 

telephone: Global Customer Care toll 

free (800) 601–3099; International 

callers (602) 365–3099, for a copy of this 

service information. 

Issued in Burlington, Massachusetts, on 

April 6, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–8309 Filed 4–10–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0330; Directorate 

Identifier 2008–NE–43–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. ARRIUS 2F Turboshaft 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: Rubs between the pipe and 

the bulkhead may lead to premature 

wearing and finally rupture of the P3 air 

pipe. The loss of P3 air pressure would 

then force the fuel control system to idle 

which could have a detrimental effect in 

critical phases of flight. We are 

proposing this AD to prevent an 

uncommanded power loss, which could 

result in an emergency autorotation 

landing or accident. 

DATES: We must receive comments on 

this proposed AD by May 13, 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. 

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: 

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–2009–0330; Directorate Identifier 

2008–NE–43–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 2008–0134R1, 

dated February 17, 2009, (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

16810 Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Proposed Rules 

On several ARRIUS 2F engines, the 

clearance between the P3 air pipe P/N 

0319719180 and the rear right bulkhead P/N 

0319998240 has been found to be too small. 

Investigations have shown that both P3 air 

pipe and rear right bulkhead were compliant 

to the design. The Turbomeca Engineering 

Department concluded that the tolerance of 

assembly established during the design could 

result in some rubbing between parts. 

Rubs between the pipe and the bulkhead 

may lead to premature wearing and finally 

rupture of the P3 air pipe. The loss of P3 air 

pressure would then force the fuel control 

system to idle which could have a 

detrimental effect in critical phases of flight. 

For the reason stated above, this 

Airworthiness Directive (AD) requires the 

inspection of the P3 air pipe (first section) 

and RH rear half-wall and, in case it is found 

damaged or non-compliant (idem), the 

replacement or readjustment of parts. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Turbomeca S.A. has issued 

Mandatory Service Bulletin (MSB) No. 

319 75 4810, dated May 14, 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 Proposed AD 

This product has been approved by 

the aviation authority of France, and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, 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 France 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 94 engines installed on 

helicopters of U.S. registry. We also 

estimate that it would take about 1 

work-hour per engine to comply with 

this proposed AD. The average labor 

rate is $80 per work-hour. Required 

parts would cost about $705 per engine. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $73,790. Our cost 

estimate is exclusive of possible 

warranty coverage. 

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 

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: 

Turbomeca S.A.: Docket No. FAA–2009– 

0330; Directorate Identifier 2008–NE– 

43–AD. 

Comments Due Date 

(a) We must receive comments by May 13, 

2009. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Turbomeca S.A. 

ARRIUS 2F turboshaft engines with P3 air 

pipe, part number 0319719180, installed. 

These engines are installed on, but not 

limited to, Eurocopter EC120B helicopters. 

Reason 

(d) Rubs between the pipe and the 

bulkhead may lead to premature wearing and 

finally rupture of the P3 air pipe. The loss 

of P3 air pressure would then force the fuel 

control system to idle which could have a 

detrimental effect in critical phases of flight. 

We are issuing this AD to prevent an 

uncommanded power loss, which could 

result in an emergency autorotation landing 

or accident. 

Actions and Compliance 

(e) Unless already done, do the following 

actions within 100 operating hours after the 

effective date of this AD. Use paragraphs 

2.B.(1) through 2.C.(2) of Turbomeca 

Mandatory Service Bulletin No. 319 75 4810, 

dated May 14, 2008. 

(1) Visually inspect P3 air pipe (first 

section) and RH rear half-wall. 

(2) Inspect play between P3 air pipe (first 

section) and RH rear half-wall. 

(3) Replace P3 air pipe (first section) if any 

damage is found. 

(4) Readjust the first section of the P3 air 

pipe if the inspected clearance is found to be 

not compliant. 

(5) If the play after readjusting the first 

section of the P3 air pipe is still less than 0.5 

mm, repeat paragraphs (e)(1) through (e)(4) of 

this AD within intervals of 100 hours timesince-last inspection. 

(6) Replace RH rear half-wall if any damage 

is found. 

FAA AD Differences 

(f) None. 

Other FAA AD Provisions 

(g) 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 

(h) Refer to MCAI EASA Airworthiness 

Directive 2008–0134R1, dated February 17, 

2009, and Turbomeca S.A. Mandatory 

Service Bulletin No. 319 75 4810, dated May 

14, 2008, for related information. Contact 

Turbomeca, 40220 Tarnos, France; telephone 

33 (0)5 59 74 40 00; telex 570 042; fax 33 (0)5 

59 74 45 15, for a copy of this service 

information. 

(i) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Proposed Rules 16811 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 238– 

7199, for more information about this AD. 

Issued in Burlington, Massachusetts, on 

April 6, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–8310 Filed 4–10–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0247; Directorate 

Identifier 2009–NE–07–AD] 

RIN 2120–AA64 

Airworthiness Directives; Hamilton 

Sundstrand Power Systems T–62T– 

46C12 Auxiliary Power Units 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

Hamilton Sundstrand Power Systems 

T–62T–46C12 auxiliary power units 

(APUs). This proposed AD would 

require upgrading the software in the 

APU full-authority digital controller 

(FADEC), from software version 

02.01.000 to version 03.00.000. This 

proposed AD results from two reports of 

APU compartment explosions due to 

over-fueling of the APU at low rpm 

during the start sequence. We are 

proposing this AD to prevent overfueling of the APU during the start 

sequence, which could lead to fuel 

explosions, injury, and damage to the 

APU and the airplane. 

DATES: We must receive any comments 

on this proposed AD by June 12, 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. 

FOR FURTHER INFORMATION CONTACT: 

Roger Pesuit, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712; e-mail: roger.pesuit@faa.gov; 

telephone (562) 627–5251, fax (562) 

627–5210. 

Contact Hamilton Sundstrand 

Technical Publications, One Hamilton 

Road, Mail Stop: 1A–3–Z63, Windsor 

Locks, CT 06096–1010; telephone (860) 

654–3575, for a copy of the service 

information identified in this proposed 

AD. 

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– 

2009–0247; Directorate Identifier 2009– 

NE–07–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 

We received two reports of APU 

compartment explosions of Hamilton 

Sundstrand Power Systems T–62T– 

46C12 APUs, related to attempted start 

of the APU. In both events, the APU 

compartment was damaged, and the 

compartment doors were blown off the 

airplane. The APUs are ground 

operational only, and the airplanes were 

parked at the time of explosion. 

Investigation has revealed that the APU 

could receive an excessively rich fuel 

mixture at low rpm during the start 

sequence, due to the APU FADEC 

version 02.01.000 software, that can 

allow over-fueling of the APU during 

starting. This condition, if not corrected, 

could result in over-fueling of the APU 

during the start sequence, which could 

lead to fuel explosion, injury, and 

damage to the APU and the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of Hamilton 

Sundstrand Power Systems Service 

Bulletin No. 4503067–49–12, Revision 

1, dated December 23, 2008, that 

describes procedures for upgrading the 

APU FADEC software to version 

03.00.000. This upgrade eliminates the 

potential for over-fueling the APU 

during the start sequence. 

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 upgrading the 

APU FADEC software to version 

03.00.000. 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 59 Hamilton Sundstrand 

Power Systems T–62T–46C12 APUs 

installed on airplanes of U.S. registry. 

We also estimate that it would take 

about three work-hours per APU to 

perform the proposed actions, and that 

the average labor rate is $80 per workhour. There is no required part cost. 

Based on these figures, we estimate the 

total cost of the proposed AD to U.S. 

operators to be $14,160. 

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,