30270 Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations 

Nomad Service Bulletin NMD–53–22, dated 

June 4, 2007, for related information. 

Material Incorporated by Reference 

(i) You must use Nomad Service Bulletin 

NMD–53–22, dated June 4, 2007, to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Gippsland Aeronautics Pty 

Ltd., Latrobe Regional Airport, P.O. Box 881, 

Morwell Victoria, 3840, Australia; phone: 

+61 3 5172 1200; fax: +61 3 5172 1201; 

Internet: www.gippsaero.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on May 

13, 2010. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–12176 Filed 5–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0219; Directorate 

Identifier 2010–NE–14–AD; Amendment 39– 

16315; AD 2010–11–10] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Astazou XIV B and XIV H Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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: 

Investigation of an uncommanded in-flight 

shutdown (IFSD) revealed that a third stage 

turbine wheel rupture was not contained by 

the turbine casings. The released portion 

consisted of a turbine blade together with the 

rim piece immediately below the blade. The 

rim piece was bounded by two adjacent axial 

slots and a fatigue crack that had developed 

between the holes in which the slots 

terminate. The slots and holes, which are 

closed by riveted plugs, were introduced by 

modification AB 173 in order to improve the 

vibration characteristics of the turbine wheel. 

Modification AB 208 brings an improvement 

to modification AB 173 by changing only the 

riveting detail. SN 283 72 0805 provides 

instructions for re-boring the holes at 

overhaul or repair in order to improve their 

surface condition. A manufacturing process 

modification has been introduced to improve 

the surface condition of these holes in third 

stage turbine wheels. Wheels subject to the 

improved manufacturing process have S/Ns 

outside the range specified in Table 1. 

Although there is only one known event, and 

although it resulted only in an 

uncommanded IFSD, with no damage to the 

aircraft, the possibility exists that additional 

events may occur, potentially involving 

damage to the aircraft. 

We are issuing this AD to prevent 

uncontained failures of the third stage 

turbine wheel, which could result in 

damage to the helicopter. 

DATES: This AD becomes effective July 

6, 2010. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in this AD as of July 6, 2010. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Kevin Dickert, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: kevin.dickert@faa.gov; 

telephone (781) 238–7117, fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on March 30, 2010 (75 FR 

15627). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

Investigation of an uncommanded IFSD 

revealed that a third stage turbine wheel 

rupture was not contained by the turbine 

casings. The released portion consisted of a 

turbine blade together with the rim piece 

immediately below the blade. The rim piece 

was bounded by two adjacent axial slots and 

a fatigue crack that had developed between 

the holes in which the slots terminate. The 

slots and holes, which are closed by riveted 

plugs, were introduced by modification AB 

173 in order to improve the vibration 

characteristics of the turbine wheel. 

Modification AB 208 brings an improvement 

to modification AB 173 by changing only the 

riveting detail. SB 283 72 0805 provides 

instructions for re-boring the holes at 

overhaul or repair in order to improve their 

surface condition. A manufacturing process 

modification has been introduced to improve 

the surface condition of these holes in third 

stage turbine wheels. Wheels subject to the 

improved manufacturing process have S/Ns 

outside the range specified in Table 1. 

Although there is only one known event, and 

although it resulted only in an 

uncommanded IFSD, with no damage to the 

aircraft, the possibility exists that additional 

events may occur, potentially involving 

damage to the aircraft. 

To address the unsafe condition, EASA 

issued AD 2009–0136, mandating inspection 

of certain third stage turbine wheels and 

removal of any damaged wheel. The wheels 

to be inspected were those whose cycles 

since new (CSN) would exceed 2,000 by 

February 1, 2011. Following additional 

research by Turbomeca on crack initiation 

and growth, this AD mandates inspections 

based on new criteria and removal of any 

damaged wheel. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

three Astazou engines installed on 

products of U.S. registry. We also 

estimate that it will take about 5 workhours per engine to comply with this 

AD. The average labor rate is $85 per 

work-hour. We anticipate no parts to be 

required. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $1,275. 

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. 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations 30271 

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 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 this 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. 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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 FAA amends § 39.13 by adding 

the following new AD: 

2010–11–10 Turbomeca: Amendment 39– 

16315. Docket No. FAA–2010–0219; 

Directorate Identifier 2010–NE–14–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective July 6, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Turbomeca Astazou 

XIV B and XIV H turboshaft engines with the 

following part number (P/N) third stage 

turbine wheels that incorporate modification 

AB 173 (Turbomeca Service Bulletin (SB) No. 

283 72 0091) or modification AB 208 

(Turbomeca SB No. 283 72 0117), but that do 

not incorporate Turbomeca SB No. 283 72 

805: 

(1) Third stage turbine wheels P/N 

0265257000, all serial numbers (S/Ns); 

(2) Third stage turbine wheels P/N 

0265257020, all S/Ns; 

(3) Third stage turbine wheels P/N 

0265257060, all S/Ns; 

(4) Third stage turbine wheels P/N 

0265257050, of the S/Ns listed in Appendix 

1 of Turbomeca Mandatory Service Bulletin 

(MSB) No. 283 72 0804, Version C, dated 

October 23, 2009. 

(5) These engines are installed on, but not 

limited to, single-engine Aerospatiale 

AS319B ‘‘Alouette III’’ and AS342J ‘‘Gazelle’’ 

helicopters. 

Reason 

(d) European Aviation Safety Agency 

(EASA) AD No. 2010–0004, dated January 5, 

2010, states: 

Investigation of an uncommanded in-flight 

shutdown (IFSD) revealed that a third stage 

turbine wheel rupture was not contained by 

the turbine casings. The released portion 

consisted of a turbine blade together with the 

rim piece immediately below the blade. The 

rim piece was bounded by two adjacent axial 

slots and a fatigue crack that had developed 

between the holes in which the slots 

terminate. The slots and holes, which are 

closed by riveted plugs, were introduced by 

modification AB 173 in order to improve the 

vibration characteristics of the turbine wheel. 

Modification AB 208 brings an improvement 

to modification AB 173 by changing only the 

riveting detail. SN 283 72 0805 provides 

instructions for re-boring the holes at 

overhaul or repair in order to improve their 

surface condition. A manufacturing process 

modification has been introduced to improve 

the surface condition of these holes in third 

stage turbine wheels. Wheels subject to the 

improved manufacturing process have S/Ns 

outside the range specified in Table 1. 

Although there is only one known event, and 

although it resulted only in an 

uncommanded IFSD, with no damage to the 

aircraft, the possibility exists that additional 

events may occur, potentially involving 

damage to the aircraft. 

To address the unsafe condition, EASA 

issued AD 2009–0136, mandating inspection 

of certain third stage turbine wheels and 

removal of any damaged wheel. The wheels 

to be inspected were those whose cycles 

since new (CSN) would exceed 2,000 by 

February 1, 2011. Following additional 

research by Turbomeca on crack initiation 

and growth, this AD mandates inspections 

based on new criteria and removal of any 

damaged wheel. 

We are issuing this AD to prevent 

uncontained failures of the third stage 

turbine wheel, which could result in damage 

to the helicopter. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) For any affected third stage turbine 

wheel that on the effective date of this AD 

has accumulated fewer than 500 cycles-sincelast-overhaul or repair, or since-new if the 

engine has never been overhauled or 

repaired: 

(i) Within 300 additional cycles, perform a 

dye penetrant inspection on the rear face of 

the third stage turbine wheel. 

(ii) Use Section 2, Instructions to Be 

Incorporated, of Turbomeca MSB No. 283 72 

0804, Version C, dated October 23, 2009, to 

do the inspection. 

(iii) Perform a second dye penetrant 

inspection when the engine has accumulated 

between 450 and 550 cycles from the first 

inspection. 

(2) For any affected third stage turbine 

wheel that on the effective date of this AD, 

has accumulated 500 or more but fewer than 

700 cycles-since-last-overhaul or repair, or 

since-new if the engine has never been 

overhauled or repaired: 

(i) Within 200 additional cycles, perform a 

dye penetrant inspection on the rear face of 

the third stage turbine wheel. 

(ii) Use Section 2, Instructions to Be 

Incorporated, of Turbomeca MSB No. 283 72 

0804, Version C, dated October 23, 2009, to 

do the inspection. 

(3) For any affected third stage turbine 

wheel that on the effective date of this AD, 

has accumulated 700 or more but fewer than 

1,200 cycles-since-last-overhaul or repair, or 

since-new if the engine has never been 

overhauled or repaired: 

(i) Within 150 additional cycles, perform a 

dye penetrant inspection on the rear face of 

the third stage turbine wheel. 

(ii) Use Section 2, Instructions to Be 

Incorporated, of Turbomeca MSB No. 283 72 

0804, Version C, dated October 23, 2009, to 

do the inspection. 

(4) If any crack indication is found, then 

before further flight, remove the third stage 

turbine wheel from service. 

(5) For any affected third stage turbine 

wheel that on the effective date of this AD 

has accumulated 1,200 or more cycles-sincelast-overhaul or repair, or since-new if the 

engine has never been overhauled or 

repaired, no action is required. 


srobinson on DSKHWCL6B1PROD with RULES
30272 Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations 

FAA AD Differences 

(f) This AD differs from the Mandatory 

Continuing Airworthiness Information 

(MCAI) and or service information as follows: 

(1) EASA AD 2010–0004, dated January 5, 

2010, requires removing the engine from 

service before further flight if a third stage 

turbine wheel is found cracked. 

(2) This AD requires removing the third 

stage turbine wheel from service before 

further flight if a third stage turbine wheel is 

found cracked. 

Alternative Methods of Compliance 

(g) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(h) Refer to MCAI EASA AD 2010–0004, 

dated January 5, 2010, for related 

information. 

(i) Contact Kevin Dickert, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: kevin.dickert@faa.gov; 

telephone (781) 238–7117, fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(j) You must use Turbomeca Mandatory 

Service Bulletin No. 283 72 0804, Version C, 

dated October 23, 2009, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Turbomeca, 40220 Tarnos, 

France; telephone (33) 05 59 74 40 00, fax 

(33) 05 59 74 45 15. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

May 19, 2010. 

Tracy Murphy, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–12539 Filed 5–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0286 Directorate 

Identifier 2010–CE–013–AD; Amendment 

39–16320; AD 2010–11–15] 

RIN 2120–AA64 

Airworthiness Directives; SOCATA 

Model TBM 700 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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: 

The Civil Aviation Authority of the United 

Kingdom (UK) has informed EASA that 

significant quantities of Halon 1211 gas, 

determined to be outside the required 

specification, have been supplied to the 

aviation industry for use in fire extinguishing 

equipment. Halon 1211 (BCF) is used in 

portable fire extinguishers, usually fitted or 

stowed in aircraft passenger cabins and flight 

decks. 

EASA published Safety Information 

Bulletin (SIB) 2009–39 on 23 October 2009 to 

make the aviation community aware of this 

safety concern. 

The results of the ongoing investigation 

have now established that LyonTech 

Engineering Ltd, a UK-based company, has 

supplied further consignments of Halon 1211 

(BCF) to L’Hotellier that do not meet the 

required specification. This Halon 1211 has 

subsequently been used to fill certain P/N 

863520–00 portable fire extinguishers that 

are now likely to be installed in or carried 

on certain TBM700 aeroplanes. 

The contaminated nature of this gas, when 

used against a fire, may provide reduced fire 

suppression, endangering the safety of the 

aeroplane and its occupants. In addition, 

extinguisher activation may lead to release of 

toxic fumes, possibly causing injury to 

aeroplane occupants. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective July 

6, 2010. 

On July 6, 2010, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on March 19, 2010 (75 FR 

13239). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

The Civil Aviation Authority of the United 

Kingdom (UK) has informed EASA that 

significant quantities of Halon 1211 gas, 

determined to be outside the required 

specification, have been supplied to the 

aviation industry for use in fire extinguishing 

equipment. Halon 1211 (BCF) is used in 

portable fire extinguishers, usually fitted or 

stowed in aircraft passenger cabins and flight 

decks. 

EASA published Safety Information 

Bulletin (SIB) 2009–39 on 23 October 2009 to 

make the aviation community aware of this 

safety concern. 

The results of the ongoing investigation 

have now established that LyonTech 

Engineering Ltd, a UK-based company, has 

supplied further consignments of Halon 1211 

(BCF) to L’Hotellier that do not meet the 

required specification. This Halon 1211 has 

subsequently been used to fill certain P/N 

863520–00 portable fire extinguishers that 

are now likely to be installed in or carried 

on certain TBM700 aeroplanes. 

The contaminated nature of this gas, when 

used against a fire, may provide reduced fire 

suppression, endangering the safety of the 

aeroplane and its occupants. In addition, 

extinguisher activation may lead to release of 

toxic fumes, possibly causing injury to 

aeroplane occupants. 

For the reason described above, this EASA 

AD requires the identification and removal 

from service of certain batches of fire 

extinguishers and replacement with 

serviceable units. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 


srobinson on DSKHWCL6B1PROD with RULES