50160 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Alternative Methods of Compliance (AMOCs) 

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

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) AMOCs approved previously according 

to AD 98–13–33 are not approved as AMOCs 

with this AD. 

Related Information 

(p) French airworthiness directive F–2004– 

092, issued June 23, 2004, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(q) You must use the service information 

listed in Table 3 of this AD to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

TABLE 3.—MATERIAL INCORPORATED BY REFERENCE

Airbus service bulletin Revision level Date 

A300–27–0188 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A300–27–0188, including Appendix 01 and Reporting Sheet ................................................ 05 ........................................... April 16, 2004. 

A300–27–6036 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A300–27–6036, including Appendix 01 and Reporting Sheet ................................................ 08 ........................................... April 16, 2004. 

A300–55–0044 ......................................................................................................................... Original ................................... October 22, 1996. 

A300–55–6023 ......................................................................................................................... Original ................................... October 22, 1996. 

A310–27–2082 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A310–27–2082, including Appendix 01 and Reporting Sheet ................................................ 05 ........................................... April 16, 2004. 

A310–55–2026 ......................................................................................................................... Original ................................... October 22, 1996. 

(1) The Director of the Federal Register 

approves th incorporatin by reference of the 

service information listed in Table 4 of this 

AD in accordance with 5 U.S.C. 552(a) and 

1 CFR part 51. 

TABLE 4.—NEW MATERIAL INCORPORATED BY REFERENCE

Airbus service bulletin Revision level Date 

A300–27–0188, including Appendix 01 and Reporting Sheet ................................................ 05 ........................................... April 16, 2004. 

A300–27–6036, including Appendix 01 and Reporting Sheet ................................................ 08 ........................................... April 16, 2004. 

A310–27–2082, including Appendix 01 and Reporting Sheet ................................................ 05 ........................................... April 16, 2004. 

(2) On July 30, 1998 (63 FR 34580, June 25, 

1998), the Director of the Federal Register 

previously approved the incorporation by 

reference of the service information listed in 

Table 5 of this AD. 

TABLE 5.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Airbus service bulletin Revision level Date 

A300–27–0188 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A300–27–6036 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A300–55–0044 ......................................................................................................................... Original ................................... October 22, 1996. 

A300–55–6023 ......................................................................................................................... Original ................................... October 22, 1996. 

A310–27–2082 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A310–55–2026 ......................................................................................................................... Original ................................... October 22, 1996. 

(3) To get copies of the service information, 

contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. To 

view the AD docket, go to the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC. To review copies of the service 

information, go to 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/federalregister/cfr/ibr-locations.html. 

Issued in Renton, Washington, on August 

12, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–16749 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–2005–22168; Directorate 

Identifier 2005–NM–146–AD; Amendment 

39–14234; AD 2005–17–13] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers Model SD3–60 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 50161 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Short Brothers Model SD3–60 airplanes. 

This AD requires an inspection of the 

rudder for damage, an inspection of the 

balance weight attachment for 

discrepancies, an inspection of the 

rudder horn spar and cleats for cracking 

and corrosion, and corrective action if 

necessary. This AD results from events 

in which fatigue cracking was found on 

the rudder horn spar. We are issuing 

this AD to detect and correct cracking 

and corrosion of the rudder horn spar, 

which could lead to detachment of the 

mass balance weight of the rudder. The 

detachment of the mass balance weight 

could jam or restrict the movement of 

the rudder, which could result in 

reduced controllability of the airplane. 

Loss of a mass balance weight could 

also damage other parts of the airplane, 

which could result in reduced 

controllability of the airplane, or could 

result in an injury to a person or damage 

to property on the ground. 

DATES: Effective September 12, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 12, 2005. 

We must receive comments on this 

AD by October 25, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments 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. 

• 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 Short Brothers, Airworthiness 

& Engineering Quality, P.O. Box 241, 

Airport Road, Belfast BT3 9DZ, 

Northern Ireland, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the United Kingdom, notified us that an 

unsafe condition may exist on all Short 

Brothers Model SD3–60 airplanes. The 

CAA advises that there have been 

reports of fatigue cracking found on the 

rudder horn spar. In one event, the 

rudder horn spar failed and the lower 

mass balance weights detached from the 

rudder horn spar, which caused 

structural damage to the rudder’s front 

spar, rib 14, and outer skin. Cracking of 

the rudder horn spar, if not corrected, 

could lead to detachment of the mass 

balance weight of the rudder. The 

detachment of the mass balance weight 

could jam or restrict the movement of 

the rudder, which could result in 

reduced controllability of the airplane. 

Loss of a mass balance weight could 

also damage other parts of the airplane, 

which could result in reduced 

controllability of the airplane, or could 

result in an injury to a person or damage 

to property on the ground. 

Relevant Service Information 

Short Brothers has issued Alert 

Service Bulletin SD360–55–A22, 

Revision 1, dated August 4, 2005. The 

service bulletin describes procedures for 

doing a visual inspection of the rudder 

for damage and an inspection of the 

balance weight attachment for 

discrepancies (discrepancies include 

potential rudder restriction and 

detachment of the balance weight). The 

service bulletin also describes 

procedures for a detailed visual 

inspection of the rudder horn spar for 

cracking and corrosion, a borescope 

inspection of the cleats for cracking and 

corrosion, and corrective action if 

necessary. The corrective action 

includes replacement of the rudder horn 

spar and cleats as specified in Part C of 

the service bulletin and an optional 

temporary repair to the rudder horn spar 

that includes replacement of the cleats. 

The CAA mandated the service 

bulletin and issued British 

airworthiness directive G–2005–0021, 

dated July 6, 2005, to ensure the 

continued airworthiness of these 

airplanes in the United Kingdom. 

The service bulletin refers to Short 

Brothers Repair Drawing SD3–03– 

6825XB, dated July 2005, as the 

appropriate source of service 

information for doing the temporary 

repair to the rudder horn spar including 

replacement of the cleats. 

FAA’s Determination and Requirements 

of This AD 

This airplane model is manufactured 

in the United Kingdom 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. Pursuant to this bilateral 

airworthiness agreement, the CAA has 

kept the FAA informed of the situation 

described above. We have examined the 

CAA’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

detect and correct cracking and 

corrosion of the rudder horn spar, 

which could lead to detachment of the 

mass balance weight of the rudder. The 

detachment of the mass balance weight 

could jam or restrict the movement of 

the rudder, which could result in 

reduced controllability of the airplane. 

Loss of a mass balance weight could 

also damage other parts of the airplane, 

which could result in reduced 

controllability of the airplane, or could 

result in an injury to a person or damage 

to property on the ground. This AD 

requires accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the AD and the Service Bulletin.’’ 

Differences Between the AD and the 

Service Bulletin 

When less than five cracks are 

detected in the rudder horn spar that are 

each 1 inch or less (and no cracks found 

on the cleats), Shorts Alert Service 

Bulletin SD360–55–A22 specifies to 

repetitively inspect every 25 flight 

cycles for up to 100 flight cycles. 

However, this AD does not permit 

further flight if any crack is detected in 

the rudder horn spar. We have 

determined that, because of the safety 

implications and consequences 

associated with that cracking, any crack 

found on the rudder horn spar must be 

repaired before further flight. In 

addition, the service bulletin does not 

specify what the corrective action is 

after 100 flight cycles. This AD requires 

either replacing the rudder horn spar 

with a new rudder horn spar and 

replacing the cleats, part number (P/N) 

SD3–33–6404XA and –6405XA, with 

new improved cleats; or doing the 

temporary repair and then replacing the 

rudder horn spar with a new rudder 

horn spar. 

50162 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 

Clarification of Inspection Terminology 

In this AD, the ‘‘visual inspection’’ 

specified in the service bulletin is 

referred to as a ‘‘general visual 

inspection.’’ We have included the 

definition for a general visual inspection 

in a note in the AD. 

In this AD, the ‘‘detailed visual 

inspection’’ specified in the service 

bulletin is referred to as a ‘‘detailed 

inspection.’’ We have included the 

definition for a detailed inspection in a 

note in the AD. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we may 

consider further rulemaking. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to the address listed under 

the ADDRESSES section. Include ‘‘Docket 

No. FAA–2005–22168; Directorate 

Identifier 2005–NM–146–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD 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 that 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 Docket 

You may examine the AD docket on 

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

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System 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 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 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–17–13 Short Brothers PLC: 

Amendment 39–14234. Docket No. 

FAA–2005–22168; Directorate Identifier 

2005–NM–146–AD. 

Effective Date 

(a) This AD becomes effective September 

12, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Shorts Model 

SD3–60 airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from events in which 

fatigue cracking was found on the rudder 

horn spar. The FAA is issuing this AD to 

detect and correct cracking and corrosion of 

the rudder horn spar, which could lead to 

detachment of the mass balance weight of the 

rudder. The detachment of the mass balance 

weight could jam or restrict the movement of 

the rudder, which could result in reduced 

controllability of the airplane. Loss of a mass 

balance weight could also damage other parts 

of the airplane, which could result in 

reduced controllability of the airplane, or 

could result in an injury to a person or 

damage to property on the ground. 

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. 

Service Bulletin 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of Shorts Alert Service Bulletin 

SD360–55–A22, Revision 1, dated August 4, 

2005. 

Inspections 

(g) Within 5 flight cycles after the effective 

date of this AD, do a general visual 

inspection of the rudder for damage and of 

the balance weight attachment for 

discrepancies in accordance with Part A of 

the service bulletin. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 50163 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

(1) If no damage and no discrepancy is 

found, no further action is necessary for this 

paragraph. 

(2) If any damage or discrepancy is found, 

before further flight, do a detailed inspection 

of the rudder horn spar and a borescope 

inspection of the cleats for cracking and 

corrosion in accordance with Part B of the 

service bulletin. 

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

(h) At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD, do a 

detailed inspection of the rudder horn spar 

and a borescope inspection of the cleats for 

cracking and corrosion in accordance with 

Part B of the service bulletin, unless the 

inspections have already been done as 

required by paragraph (g)(2) of this AD. 

(1) For airplanes on which a heavy landing 

has occurred before the effective date of this 

AD, do the inspections within 20 flight 

cycles or 7 days after the effective date of this 

AD, whichever occurs first. 

(2) For airplanes on which a heavy landing 

has not occurred before the effective date of 

this AD, do the inspections at the earlier of 

the times specified in paragraphs (h)(2)(i), 

(h)(2)(ii), and (h)(2)(iii) of this AD. 

(i) For airplanes on which a heavy landing 

occurs after the effective date of this AD, do 

the inspections within 20 flight cycles or 7 

days after the heavy landing occurred, 

whichever occurs first. 

(ii) For airplanes that have accumulated 

28,800 or more total flight hours, do the 

inspections within 20 flight cycles or 7 days 

after the effective date of this AD, whichever 

occurs first. 

(iii) At the applicable time specified in 

Table 1 of this AD. 

TABLE 1.—CERTAIN COMPLIANCE TIMES FOR PART B INSPECTIONS

For airplanes that— Do the inspections— 

Have accumulated 25,000 or less total flight cycles ................................ Within 80 flight cycles or 28 days after the effective date of this AD, 

whichever occurs first. 

Have accumulated more than 25,000 total flight cycles but less than 

50,000 total flight cycles.

Within 40 flight cycles or 14 days after the effective date of this AD, 

whichever occurs first. 

Have accumulated 50,000 or more total flight cycles .............................. Within 20 flight cycles or 7 days after the effective date of this AD, 

whichever occurs first. 

Corrective Actions 

(i) If, during any inspection required by 

paragraph (g)(2) or (h) of this AD, no crack 

is found and any corrosion found is within 

the limits specified in the service bulletin, no 

further action is required by this paragraph. 

(j) If any crack is found during any 

inspection required by paragraph (g)(2) or (h) 

of this AD, do the corrective action specified 

in paragraph (j)(1), (j)(2), or (j)(3) of this AD, 

as applicable, except as required by 

paragraph (k) of this AD. 

(1) If any crack is found on the rudder horn 

spar and there is no crack on any of the 

cleats, do the actions specified in paragraph 

(j)(1)(i) or (j)(1)(ii) of this AD. 

(i) Before further flight, replace the rudder 

horn spar with a new rudder horn spar and 

replace the cleats, part numbers (P/N) SD3– 

33–6404XA and –6405XA, with new cleats, 

in accordance with Part C of the service 

bulletin. 

(ii) Before further flight, do the temporary 

repair in accordance with Short Brothers 

Repair Drawing SD3–03–6825XB, dated July 

2005, and within 300 flight cycles, replace 

the rudder horn spar with a new rudder horn 

spar, in accordance with Part C of the service 

bulletin. 

(2) If any crack is found on the rudder horn 

spar and any crack is found on any cleat, do 

the actions specified in paragraph (j)(2)(i) or 

(j)(2)(ii) of this AD. 

(i) Before further flight, replace the rudder 

horn spar with a new rudder horn spar and 

replace all three cleats with new cleats, in 

accordance with Part C of the service 

bulletin. 

(ii) Before further flight, do the temporary 

repair in accordance with Short Brothers 

Repair Drawing SD3–03–6825XB, dated July 

2005, and within 300 flight cycles, replace 

the rudder horn spar with a new rudder horn 

spar, in accordance with Part C of the service 

bulletin. 

(3) If any crack is found on any of the 

cleats and no cracks are found on the rudder 

horn spar, before further flight, replace the 

cleats with new cleats in accordance with 

Part C of the service bulletin or in accordance 

with Short Brothers Repair Drawing SD3–03– 

6825XB, dated July 2005. 

(k) If, during any inspection required by 

paragraph (g)(2) or (h) of this AD, any 

corrosion is found that is outside the limits 

specified in the service bulletin, before 

further flight, replace the corroded part with 

a new part, in accordance with Part C of the 

service bulletin. 

Actions Accomplished in Accordance With 

Previous Issue of Service Information 

(l) Actions accomplished before the 

effective date of this AD in accordance with 

Shorts Alert Service Bulletin SD360–55–A22, 

dated July 6, 2005; and Short Brothers Repair 

Drawing SD3–03–6825XA, dated July 2005; 

are considered acceptable for compliance 

with the corresponding actions specified in 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m) The Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Related Information 

(n) British airworthiness directive G–2005– 

0021, dated July 6, 2005, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(o) You must use Shorts Alert Service 

Bulletin SD360–55–A22, Revision 1, dated 

August 4, 2005; and Short Brothers Repair 

Drawing SD3–03–6825XB, dated July 2005; 

as applicable, 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 this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Short Brothers, Airworthiness & 

Engineering Quality, PO Box 241, Airport 

Road, Belfast BT3 9DZ, Northern Ireland, 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. 

50164 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 

Issued in Renton, Washington, on August 

12, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–16750 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–2005–22039; Directorate 

Identifier 2005–NE–33–AD; Amendment 39– 

14238; AD 2005–17–17] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Arrius 2F Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Turbomeca S.A. Arrius 2F turboshaft 

engines. This AD requires replacing 

certain O-rings on the check valve 

piston in the lubrication unit. This AD 

results from a report of a forced landing 

of a Eurocopter EC120B helicopter. We 

are issuing this AD to prevent an 

uncommanded in-flight shutdown of the 

engine, which could result in a forced 

autorotation landing and damage to the 

helicopter. 

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 01803–2599, telephone 

(781) 238–7175; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 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 

Turbomeca S.A. Arrius 2F turboshaft 

engines. In addition, on May 13, 2005, 

an uncommanded in-flight engine 

shutdown (IFSD) of an Arrius 2F engine 

resulted in the forced landing of a 

Eurocopter EC120B helicopter in the 

Gulf of Mexico. Investigation of the 

engine found that an interruption of 

engine lubrication due to excessive 

swelling of the check valve O-ring in the 

lubrication unit caused the IFSD. The 

amount of swelling of the O-ring 

depends on the class of oil used, 

standard (STD) or high-thermal stability 

(HTS), and the engine operating time. 

This condition, if not corrected, could 

result in an uncommanded in-flight 

shutdown of the engine, which could 

result in a forced autorotation landing 

and damage to the helicopter. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of Turbomeca Alert 

Service Bulletin (ASB) No. A319 79 

4802, dated June 21, 2005, that 

describes procedures for replacing the 

O-ring on the check valve piston of the 

lubrication unit. The DGAC classified 

this alert service bulletin as mandatory 

and issued AD No. F–2005–122, dated 

July 20, 2005, in order to ensure the 

airworthiness of these Turbomeca S.A. 

Arrius 2F turboshaft engines in France. 

Bilateral Airworthiness Agreement 

This turboshaft 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 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 

prevent an uncommanded in-flight 

shutdown of the engine, which could 

result in a forced autorotation landing 

and damage to the helicopter. This AD 

requires replacing the O-ring on the 

check valve piston in the lubrication 

unit at the following intervals: 

• For engines that use HTS or an 

unknown class oil, within 300 hours 

time-since-new (TSN) or 50 hours after 

the effective date of this AD, whichever 

is later. 

• For engines that use STD class oil, 

within 450 hours TSN or 50 hours after 

the effective date of this AD, whichever 

is later. 

• Thereafter, replace the O-ring 

within 300 hours time-since-last 

replacement (TSR) on engines that use 

HTS class oil or 500 hours TSR on 

engines that use STD class oil. 

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. 

Interim Action 

These actions are interim actions and 

we may take further rulemaking actions 

in the future. 

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–2005–22039; Directorate Identifier 

2005–NE–33–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.