50168 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 

(2) Perform a complete electrical shutdown 

of the airplane. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

Related Information 

(h) French emergency airworthiness 

directive UF–2005–150, dated August 10, 

2005, also addresses the subject of this AD. 

Material Incorporated by Reference 

(i) You must use the documents listed in 

Table 2 of this AD to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of these documents in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France, for a copy of this service information. 

You may review copies at the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

Room PL–401, Nassif Building, Washington, 

DC; on the Internet at http://dms.dot.gov; or 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 2.—MATERIAL INCORPORATED

BY REFERENCE

Airbus all operators telex Date 

A330–31A3092 .................. August 1, 2005. 

A340–31A4102 .................. August 1, 2005. 

A340–31A5023 .................. August 1, 2005. 

Issued in Renton, Washington, on August 

18, 2005. 

Michael Zielinski, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–16896 Filed 8–25–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21924; Directorate 

Identifier 2005–NE–30–AD; Amendment 39– 

14236; AD 2005–17–15] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arrius 2F Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Turbomeca Arrius 2F turboshaft 

engines. This AD requires a one-time 

removal and inspection of the fuel filterholder assembly to determine that the 

fuel control unit (FCU) filter is 

dimensionally correct. The AD also 

requires updating the Engine 

Maintenance Manuals to include a 

dimensional check of the fuel filterholder assembly every time the FCU 

filter element is removed from the fuel 

filter-holder assembly. This AD results 

from reports of restricted fuel flow 

caused by a dimensionally incorrect 

FCU filter. Ground run testing may not 

detect the fuel flow limitation. We are 

issuing this AD to detect a 

dimensionally incorrect FCU filter that 

could lead to an undetected limitation 

of fuel flow, limiting the maximum 

power available in-flight, which could 

result in the inability to continue safe 

flight, avoid obstacles or land safely. 

DATES: Effective September 12, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the 

regulations as of September 12, 2005. 

We must receive any comments on 

this AD by October 25, 2005. 

ADDRESSES: Use one of the following 

addresses to comment on this AD: 

• DOT Docket Web site: Go to http:// 

dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590– 

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Turbomeca S.A., 40220 

Tarnos, France; telephone 33 05 59 74 

40 00, fax 33 05 59 74 45 15, for the 

service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Spinney, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803–5299; telephone 

(781) 238–7175; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The 

Direction Generale de L’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, notified us that an 

unsafe condition might exist on 

Turbomeca S.A. Arrius 2F turboshaft 

engines. The DGAC advised us of 

reports of restricted fuel flow caused by 

a dimensionally incorrect FCU filters. 

Ground run testing may not detect the 

fuel flow limitation and, therefore, it 

could go undetected until maximum 

power is needed for certain flight 

conditions. We are issuing this AD to 

detect a dimensionally incorrect FCU 

filter that could lead to an undetected 

limitation of fuel flow, limiting the 

maximum power available in-flight, 

which could result in the inability to 

continue safe flight, avoid obstacles or 

land safely. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of Turbomeca 

Mandatory Alert Service Bulletin No. 

A319 73 4823, dated May 11, 2005, that 

describes procedures for checking the 

correct position of the FCU fuel filter. 

The DGAC classified this service 

bulletin as mandatory and issued AD 

No. F–2005–088, in order to ensure the 

airworthiness of these engines in 

France. 

Bilateral Airworthiness Agreement 

This engine model is manufactured in 

France and is type certificated for 

operation in the United States under the 

provisions of section 21.29 of the 

Federal Aviation Regulations (14 CFR 

21.29) and the applicable bilateral 

airworthiness agreement. Under this 

bilateral airworthiness agreement, the 

Direction General De L’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, recently notified us 

that an unsafe condition might exist on 

certain Turbomeca S.A. Arrius 2F 

turboshaft engines. Under this bilateral 

airworthiness agreement, the DGAC 

kept the FAA informed of the situation 

described above. We have examined the 

findings of the DGAC, reviewed all 

available information, and determined 

that AD action is necessary for products 

of this type design that are certificated 

for operation in the United States. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other Turbomeca S.A. Arrius 2F 

turboshaft engines of the same type 

design. We are issuing this AD to detect 

incorrect positioning of the FCU filter 

that could lead to an undetected 

limitation of fuel flow, limiting the 

Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 50169 

maximum power available in-flight, 

which could result in the inability to 

continue safe flight, avoid obstacles or 

land safely. This AD requires a one-time 

removal and inspection of the fuel filterholder assembly to determine that the 

fuel control unit (FCU) filter is in the 

correct position. The AD also requires 

that the Engine Maintenance Manuals 

be updated to include this inspection 

every time the FCU filter is removed 

from the fuel filter-holder assembly. 

You must use the service information 

described previously to perform the 

actions required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that 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 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2005–21924; Directorate Identifier 

2005–NE–30–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.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 DMS web site, 

anyone can find and read the comments 

in any of our dockets, including 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) or you may visit 

http://dms.dot.gov. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the DMS Docket Offices 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone (800) 647– 

5227) is located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘AD Docket No. 2005–NE–30– 

AD’’ in your request. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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 adding 

the following new airworthiness 

directive: 

2005–17–15 Turbomeca S.A: Amendment 

39–14236. Docket No. FAA–2005–21924; 

Directorate Identifier 2005–NE–30–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 12, 2005. 

Affected ADs 

(b) None. 

Applicability 

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

Arrius 2F turboshaft engines. These engines 

are installed on, but not limited to, 

Eurocopter EC120 helicopters. 

Unsafe Condition 

(d) This AD results from incorrect 

positioning of the FCU filter that could limit 

the fuel flow downstream of the filter. We are 

issuing this AD to detect incorrect 

positioning of the FCU filter that could lead 

to an undetected limitation of fuel flow, 

limiting the maximum power available inflight, which could result in the inability to 

continue safe flight, avoid obstacles or land 

safely. 

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. 

Check Position of Fuel Control Unit (FCU) 

Fuel Filter 

(f) Within 25 engine-operating-hours after 

the effective date of this AD, remove the fuel 

filter-holder assembly and check that the 

FCU fuel filter is in the correct position using 

Paragraph 2 of Turbomeca Mandatory Alert 

Service Bulletin No. A319 73 4823, dated 

May 11, 2005. 

(g) Within 30 days, revise your engine 

maintenance manual to include a 

dimensional check to ensure the correct 

position of the FCU filter after every 

installation of the fuel filter element into the 

fuel filter-holder assembly. The latest 

revision of the Arrius 2F maintenance 

manual includes the dimensional check in 

Sub-Task 73–23–06–901–002 paragraph 

(2)(e). 

50170 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 

Alternative Methods of Compliance 

(AMOCs) 

(h) 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 

(i) DGAC airworthiness directive No. F– 

2005–088, dated June 8, 2005, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(j) You must use Turbomeca Mandatory 

Alert Service Bulletin No. A319 73 4823, 

dated May 11, 2005, to perform the check 

required by this AD. The Director of the 

Federal Register approved the incorporation 

by reference of this service bulletin in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Turbomeca S.A., 40220 

Tarnos, France; telephone 33 05 59 74 40 00, 

fax 33 05 59 74 45 15, for a copy of this 

service information. You may review copies 

at the Docket Management Facility; U.S. 

Department of Transportation, 400 Seventh 

Street, SW., Nassif Building, Room PL–401, 

Washington, DC 20590–0001, on the internet 

at http://dms.dot.gov; 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/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

August 17, 2005. 

Richard Noll, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–16902 Filed 8–25–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19929; Directorate 

Identifier 2004–NE–15–AD; Amendment 39– 

14237; AD 2005–17–16] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney JT8D–1, –1A, –1B, –7, –7A, 

–7B, –9, –9A, –11, –15, –15A, –17, 

–17A, –17R, –17AR, –209, –217, –217A, 

–217C, and –219 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney (PW) JT8D–1, –1A, –1B, –7, 

–7A, –7B, –9, –9A, –11, –15, –15A, –17, 

–17A, –17R, –17AR, –209, –217, –217A, 

–217C, and –219 turbofan engines. This 

AD requires removing affected rotating 

parts overhauled by a certain repair 

vendor, and inspecting the parts as 

applicable. This AD results from reports 

that certain JT8D critical life-limited 

rotating parts have been returned to 

service with cracks, corrosion pitting, or 

dimensions outside of manual limits. 

We are issuing this AD to prevent 

failure of critical life-limited rotating 

engine parts which could result in an 

uncontained engine failure and damage 

to the airplane. 

DATES: This AD becomes effective 

September 30, 2005. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of September 30, 2005. 

ADDRESSES: You can get the service 

information identified in this AD from 

Pratt & Whitney, 400 Main St., East 

Hartford, CT 06108; telephone (860) 

565–7700; fax (860) 565–1605. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Keith Lardie, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803–5299; telephone (781) 238–7189; 

fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed airworthiness directive (AD). 

The proposed AD applies to Pratt & 

Whitney (PW) JT8D–1, –1A, –1B, –7, 

–7A, –7B, –9, –9A, –11, –15, –15A, –17, 

–17A, –17R, –17AR, –209, –217, –217A, 

–217C, and –219 turbofan engines. We 

published the proposed AD in the 

Federal Register on December 30, 2004 

(69 FR 78359). That action proposed to 

require removing affected rotating parts 

overhauled by a certain repair vendor, 

and inspecting or replacing the parts as 

applicable. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the DMS Docket Offices 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone (800) 647– 

5227) is located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request To Remove Rear Compressor 

Rear Hub From List of Affected Parts 

One commenter requests that we 

remove the rear compressor rear hub 

from the list of affected parts. The 

commenter states that the part is a 

nickel alloy similar to the 13th stage 

disk and there is no cracking or 

corrosion associated with it. In addition, 

the rear compressor rear hub is not a 

life-limited part, and the serial numbers 

are not readily available. As a result, the 

commenter feels the proposed AD 

would force operators to inspect all 

parts, not just the listed serial number 

parts. 

We agree. We have removed it from 

this AD. 

Include All Parts Improperly Processed 

by the Repair Vendor 

One commenter asks that this AD 

include all parts improperly processed 

by a certain repair vendor, not just the 

high-pressure compressor. 

We do not agree. The proposed AD 

addresses those parts that pose a safety 

threat. All other parts either present no 

known safety threat, or are already 

addressed through other applicable ADs 

and field notifications. If we decide that 

further AD action is necessary to 

address other parts, we may issue a 

separate AD at that time. 

Request To Clarify ‘‘Shop Visit’’ 

One commenter asks that we clarify 

the definition of ‘‘shop visit’’ contained 

in the AD. The commenter feels that an 

operator could interpret a shop visit as 

when an airplane upon which an 

affected engine is installed, goes into a 

hangar. 

We agree. We included the following 

definition in the AD: ‘‘A shop visit is 

defined as an engine removal where 

engine maintenance entails separation 

of pairs of major engine flanges or the 

removal of a disk, hub or spool at a 

maintenance facility, regardless of the 

scheduled maintenance action or the 

reason for engine removal.’’ 

Request To Inspect Rear Compressor 

Front and Rear Compressor Rear Hubs 

When They Are Accessible 

One commenter asks that we not 

place time restrictions on operators to 

inspect rear compressor front and rear 

compressor rear hubs and instead 

inspect them when they are accessible. 

Because they aren’t life-limited parts, 

the hubs are not tracked by serial