Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations 70357 

(a) Effective Date 

This AD is effective December 31, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

777F series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 777–24A0119, dated 

November 11, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2421; AC Generator-Alternator. 

(e) Unsafe Condition 

This AD was prompted by reports of failure 

of wire support clamps in the forward section 

of the aft pressure bulkhead. We are issuing 

this AD to prevent failure of the clamp, 

which could result in wire chafing and 

potential arcing and consequent fire in 

section 48 (a flammable fluid leakage zone) 

or heat damage to the auxiliary power unit 

(APU) power feeder cable, insulation 

blankets, or pressure bulkhead. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection of the Clamps 

Within 48 months after the effective date 

of this AD: Do a detailed inspection of the 

clamps on the APU power feeder cable to 

determine if TA027063 clamps are installed, 

and all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–24A0119, dated 

November 11, 2011, except as required by 

paragraphs (h) and (i) of this AD. Do all 

related investigative and corrective actions 

before further flight. 

(h) Exception to the Service Information 

If during any inspection of the fuselage 

structure required by paragraph (g) of this 

AD, no primer discoloration or structural 

deterioration is found, before further flight, 

repair the APU power feeder cable and 

insulation blanket and replace the existing 

clamps, in accordance with steps 3.B.7, 3.B.8, 

and 3.B.9 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–24A0119, dated November 11, 2011. 

(i) Repair Approval 

Where Boeing Alert Service Bulletin 777– 

24A0119, dated November 11, 2011, specifies 

to do the repair in accordance with the 

instruction from Boeing, before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any structural 

repair required by this AD if it is approved 

by the Boeing Commercial Airplanes 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Seattle ACO, to make those 

findings. For a structural repair method to be 

approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

For more information about this AD, 

contact Georgios Roussos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: (425) 917– 

6482; fax: (425) 917–6590; email: 

georgios.roussos@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 777– 

24A0119, dated November 11, 2011. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; fax 

206–766–5680; Internet https:// 

www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference 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 Renton, Washington, on 

November 8, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27908 Filed 11–23–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0591; Directorate 

Identifier 2012–NM–015–AD; Amendment 

39–17264; AD 2012–23–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

737–600, –700, –700C, –800, and –900 

series airplanes. That AD currently 

requires replacing the drain tube 

assemblies and support clamps on the 

aft fairing of the engine struts. This new 

AD requires replacing the drain tube 

assembly of the left and right engine 

strut aft fairings with a new one, which 

includes an integral support clamp 

made of nickel alloy 625. This AD also 

adds airplanes to the applicability. This 

AD was prompted by a report of a 

broken drain tube assembly on the left 

engine strut at the clamp support 

location under the aft fairing 

compartment, inside the heat shield 

cavity of the aft fairing. There have also 

been reports of tube wear at this clamp 

location on additional airplanes. We are 

issuing this AD to prevent failure of the 

drain tube assemblies and clamps on the 

aft fairings of the engine struts. Such 

failure could allow leaked flammable 

fluids in the drain systems to discharge 

onto the heat shields of the aft fairings 

of the engine struts, which could result 

in an undetected and uncontrollable 

fire. 

DATES: This AD is effective December 

31, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 31, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

mstockstill on DSK4VPTVN1PROD with RULES

70358 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 address for the 

Docket Office (phone: 800–647–5527) is 

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: 

Ansel James, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6497; fax: 

425–917–6590; email: 

ansel.james@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–08–24, 

Amendment 39–15478 (73 FR 21242, 

April 21, 2008). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

June 12, 2012 (77 FR 34879). That 

NPRM proposed to require replacing the 

drain tube assembly of the left and right 

engine strut aft fairings with a new one 

which includes an integral support 

clamp made of nickel alloy 625. That 

NPRM also proposed to add airplanes to 

the applicability. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 34879, 

June 12, 2012) and the FAA’s response 

to each comment. 

Support for the NPRM (77 FR 34879, 

June 12, 2012) 

United Airlines supports the 60- 

month compliance time specified in the 

NPRM (77 FR 34879, June 12, 2012). 

Clarification of Effect of Winglet 

Installation 

Aviation Partners Boeing stated that 

accomplishing the supplemental type 

certificate (STC) ST00830SE does not 

affect the actions specified in the NPRM 

(77 FR 34879, June 12, 2012). 

We concur. We have added new 

paragraph (c)(2) to this AD, which states 

that STC ST00830SE (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/

rgstc.nsf/0/408E012E008616A78

62578880060456C?OpenDocument&

Highlight=st00830se) does not affect the 

ability to accomplish the actions 

required by this AD. Therefore, for 

airplanes on which STC ST00830SE is 

installed, a ‘‘change in product’’ 

alternative method of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17 section 

39.17 of the Federal Aviation 

Regulations. For all other AMOC 

requests, the operator must request 

approval for an AMOC in accordance 

with the procedures specified in 

paragraph (h) of this AD. 

Request To Extend Compliance Time 

American Airlines (AAL) requested 

that the compliance time specified in 

paragraph (g) of the NPRM (77 FR 

34879, June 12, 2012) be extended from 

60 to 72 months. AAL stated that the 

routine maintenance schedule does not 

allow for accomplishment of the 

replacements during the proposed 

compliance time. AAL stated that the 

compliance time could be extended for 

all airplanes without jeopardizing 

aviation safety. 

We disagree with the request to 

change the compliance time. In 

developing an appropriate compliance 

time for this AD, we considered not 

only the safety implications, but the 

manufacturer’s recommendations, the 

availability of required parts, and the 

practical aspect of accomplishing the 

actions within an interval of time that 

corresponds to typical scheduled 

maintenance for affected operators. 

Under the provisions of paragraph (h) of 

the final rule, however, we may 

consider requests for adjustments to the 

compliance time if data are submitted to 

substantiate that such adjustments 

would provide an acceptable level of 

safety. No change has been made to this 

AD in this regard. 

Request To Revise Paragraph (f) of the 

NPRM (77 FR 34879, June 12, 2012) To 

Include Terminating Action 

AAL requested that we revise 

paragraph (f) of the NPRM (77 FR 34879, 

June 12, 2012) to state that 

accomplishment of Boeing Special 

Attention Service Bulletin 737–54– 

1043, Revision 2, dated November 4, 

2011, constitutes a terminating action 

for the specified unsafe condition and 

that no further action is required. 

We disagree with the request to revise 

paragraph (f) of the NPRM (77 FR 34879, 

June 12, 2012). The action required by 

paragraph (g) of this AD, which is 

specified in the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–54–1043, Revision 

2, dated November 4, 2011, is the only 

action required by this AD. If operators 

have previously accomplished the 

actions specified in Boeing Special 

Attention Service Bulletin 737–54– 

1043, Revision 2, dated November 4, 

2011, they are in compliance with the 

AD, as specified in paragraph (f) of this 

AD. No change has been made to this 

AD in this regard. 

Request To Clarify Conflicting AMOC 

Statements 

Alaska Airlines (ASA) requested 

clarification regarding conflicting 

AMOC statements. ASA stated that 

paragraph (h)(3) of the NPRM (77 FR 

34879, June 12, 2012) does not allow 

AMOCs approved for AD 2008–08–24, 

Amendment 39–15478 (73 FR 21242, 

April 21, 2008), to be used for the 

actions proposed in the NPRM. 

However, ASA pointed out that Boeing 

Special Attention Service Bulletin 737– 

54–1043, Revision 2, dated November 4, 

2011, states that it is an approved 

AMOC for paragraphs (f) and (h) of AD 

2008–08–24. ASA also requested credit 

for actions done previously using 

Boeing Special Attention Service 

Bulletin 737–54–1043, Revision 2, dated 

November 4, 2011. 

We agree to clarify. Paragraph 1.F., 

‘‘Approval,’’ of Boeing Special Attention 

Service Bulletin 737–54–1043, Revision 

2, dated November 4, 2011, states that 

the actions specified in that service 

bulletin are approved as an AMOC for 

paragraphs (f) and (h) of AD 2008–08– 

24, Amendment 39–15478 (73 FR 

21242, April 21, 2008). That AMOC 

approval allows operators to use Boeing 

Special Attention Service Bulletin 737– 

54–1043, Revision 2, dated November 4, 

2011, to comply with AD 2008–08–24. 

However, on the effective date of this 

AD, AD 2008–08–24 will be superseded 

(i.e., will no longer exist), and the fact 

that Boeing Special Attention Service 

Bulletin 737–54–1043, Revision 2, dated 

November 4, 2011, refers to AD 2008– 

08–24 will be moot. This AD requires 

the accomplishment of the actions of 

that service bulletin as the primary 

means of compliance with this AD, and 

not as an AMOC. 

The intent of paragraph (h)(3) of this 

AD is to prevent the use of any AMOC 

for AD 2008–08–24, Amendment 39– 

15478 (73 FR 21242, April 21, 2008), as 

an AMOC for this new AD. This new 

AD requires accomplishment of Boeing 

Special Attention Service Bulletin 737– 

54–1043, Revision 2, dated November 4, 

2011. No credit is given for Boeing 

Special Attention Service Bulletin 737– 

54–1043, Revision 1, dated October 19, 

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Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations 70359 

2009; or Boeing Special Attention 

Service Bulletin 737–54–1043, dated 

May 2, 2007; because additional work is 

necessary for airplanes on which Boeing 

Special Attention Service Bulletin 737– 

54–1043, Revision 1, dated October 19, 

2009; or Boeing Special Attention 

Service Bulletin 737–54–1043, dated 

May 2, 2007; was accomplished. No 

change has been made to this AD in this 

regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

34879, June 12, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 34879, 

June 12, 2012). 

Costs of Compliance 

We estimate that this AD affects 1,098 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product 

Cost on U.S. 

operators 

Replacement ................................................... 14 work-hours × $85 per hour = $1,190 ........ $12,326 $13,516 $14,840,568 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 

removing airworthiness directive (AD) 

2008–08–24, Amendment 39–15478 (73 

FR 21242, April 21, 2008), and adding 

the following new AD: 

2012–23–08 The Boeing Company: 

Amendment 39–17264; Docket No. 

FAA–2012–0591; Directorate Identifier 

2012–NM–015–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective December 31, 2012. 

(b) Affected ADs 

This AD supersedes AD 2008–08–24, 

Amendment 39–15478 (73 FR 21242, April 

21, 2008). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

certificated in any category, as identified in 

Boeing Special Attention Service Bulletin 

737–54–1043, Revision 2, dated November 4, 

2011. 

(2) Supplemental Type Certificate (STC) 

ST00830SE (http://rgl.faa.gov/Regulatory_

and_Guidance_Library/rgstc.nsf/0/408E0

12E008616A7862578880060456C?Open

Document&Highlight=st00830se) does not 

affect the ability to accomplish the actions 

required by this AD. Therefore, for airplanes 

on which STC ST00830SE is installed, a 

‘‘change in product’’ alternative method of 

compliance (AMOC) approval request is not 

necessary to comply with the requirements of 

14 CFR 39.17. For all other AMOC requests, 

the operator must request approval for an 

AMOC in accordance with the procedures 

specified in paragraph (h) of this AD. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 54, Nacelles/pylons. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

broken drain tube assembly on the aft fairing 

of the left engine strut at the clamp support 

location under the aft fairing compartment, 

inside the heat shield cavity of the aft fairing. 

There have also been reports of tube wear at 

the clamp location on additional airplanes. 

We are issuing this AD to prevent failure of 

the drain tube assemblies and clamps on the 

aft fairings of the engine struts. Such failure 

could allow leaked flammable fluids in the 

drain systems to discharge onto the heat 

shields of the aft fairings of the engine struts, 

which could result in an undetected and 

uncontrollable fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

Within 60 months after the effective date 

of this AD, replace the drain tube assemblies 

and support clamps on the aft fairing of the 

struts of engines 1 and 2 with new drain tube 

assemblies and clamps, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–54– 

1043, Revision 2, dated November 4, 2011. 

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70360 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9–ANM– 

Seattle–ACO–AMOC–Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) AMOCs approved previously in 

accordance with AD 2008–08–24, 

Amendment 39–15478 (73 FR 21242, April 

21, 2008), are not approved as AMOCs with 

this AD. 

(i) Related Information 

For more information about this AD, 

contact Ansel James, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6497; fax: 425–917–6590; 

email: ansel.james@faa.gov. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 737–54–1043, Revision 2, dated 

November 4, 2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may view this service information 

that is incorporated by reference 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 Renton, Washington, on 

November 9, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–28029 Filed 11–23–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0339; Directorate 

Identifier 2011–SW–051–AD; Amendment 

39–17259; AD 2012–23–03] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Eurocopter France (Eurocopter) Model 

SA.315B Alouette III, SE.3160 Alouette 

III, SA.316B Alouette III, SA.316C 

Alouette III, SA.319B Alouette III, SA 

3180–ALOUETTE ASTAZOU, SA 

318B–ALOUETTE ASTAZOU, and SA 

318 C–ALOUETTE ASTAZOU 

helicopters. This AD requires inspecting 

the cage of the free-wheel assembly for 

the correct alignment of the roller drive 

pocket recesses and replacing the freewheel cage with an airworthy freewheel cage if a defect exists. This AD 

was prompted by incorrect positioning 

of the roller drive pocket recesses on the 

tail rotor drive shaft free-wheel cage, 

which caused a pilot to experience a 

heavy jerk in the yaw control during inflight autorotation training. The 

requirements of this AD are intended to 

prevent a loss of tail rotor drive and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective December 

31, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 31, 2012. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, 

telephone (972) 641–0000 or (800) 232– 

0323, fax (972) 641–3775, or at http:// 

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

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, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Rao 

Edupuganti, Aerospace Engineer, FAA, 

Rotorcraft Directorate, Regulations and 

Policy Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone 

(817) 222–5110, email 

rao.edupuganti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 29, 2012, at 77 FR 18967, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 to include an AD that would apply 

to Eurocopter Model SA.315B Alouette 

III, SE.3160 Alouette III, SA.316B 

Alouette III, SA.316C Alouette III, 

SA.319B Alouette III, SA 3180– 

ALOUETTE ASTAZOU, SA 318B– 

ALOUETTE ASTAZOU, and SA 318C– 

ALOUETTE ASTAZOU helicopters. 

That NPRM proposed to require 

inspecting the cage of the free-wheel 

assembly for the correct alignment of 

the roller drive pocket recesses and 

replacing the free-wheel cage with an 

airworthy free-wheel cage if a defect 

exists. The proposed requirements were 

intended to prevent a loss of tail rotor 

drive and subsequent loss of control of 

the helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2011– 

0143, dated July 26, 2011 (AD 2011– 

0143), to correct an unsafe condition for 

Eurocopter helicopters. EASA advises 

that during in-flight autorotation 

training, a pilot experienced a heavy 

jerk in the yaw control at the time of 

resynchronization. The free-wheel 

assembly of the helicopter had been 

replaced shortly before this flight. 

Internal inspection of the free-wheel 

assembly revealed incorrect positioning 

of the roller drive pocket recesses on the 

free-wheel cage. The subsequent offmstockstill on DSK4VPTVN1PROD with RULES