Federal Register / Vol. 77, No. 25 / Tuesday, February 7, 2012 / Rules and Regulations 5991 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0005; Directorate 

Identifier 2010–SW–091–AD; Amendment 

39–16914; AD 2012–01–03] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting an 

airworthiness directive (AD) for the 

Eurocopter France (ECF) Model 

AS332L2 helicopter and superseding an 

AD for the Model EC225LP helicopter. 

This AD is prompted by the 

manufacturer issuing additional 

corrective action to prevent failure of 

the main gearbox (MGB) due to the 

degradation of the epicyclic module of 

the MGB and expands the applicability 

to include the ECF Model AS332L2 

helicopter because an investigation 

showed a failure within the epicyclic 

reduction gear module resulted in the 

rupture of the MGB case and separation 

of the main rotor head of a model 

AS332L2 helicopter in 2009. These 

actions are intended to prevent failure 

of the MGB and subsequent loss of 

control of the helicopter. 

DATES: This AD becomes effective 

February 22, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of February 22, 2012. 

We must receive comments on this 

AD by April 9, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: (202) 493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, 

Grand Prairie, Texas 75052, telephone 

(972) 641–0000 or (800) 232–0323, fax 

(972) 641–3775, or at http:// 

www.eurocopter.com/techpub. You may 

review copies of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: Rao 

Edupuganti, Aerospace Engineer, FAA, 

Rotorcraft Directorate, Regulations and 

Policy Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone: 

(817) 222–4389; fax: (817) 222–5961, 

email rao.edupaganti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this rulemaking during the 

comment period. We will consider all 

the comments we receive and may 

conduct additional rulemaking based on 

those comments. 

Discussion 

We issued Emergency AD (EAD) 

2009–09–51 on April 17, 2009, to all 

known owners and operators of the 

Eurocopter Model EC225LP helicopter, 

and published that EAD as Amendment 

39–16101 (74 FR 65679, December 11, 

2009) to require determining whether or 

not the ‘‘CHIP’’ detector light on the 

instrument panel had previously 

illuminated. If the ‘‘CHIP’’ detector light 

had illuminated because of a metal 

particle on the chip detector of the 

module, or if you could not determine 

from the maintenance records which 

‘‘CHIP’’ detector caused the ‘‘CHIP’’ 

detector light to illuminate, or if the 

chip detector light stayed illuminated 

after the ‘‘CHIP’’ detector switch was 

turned to the ‘‘CHIP PULSE’’ setting, 

you are required to replace the module 

with an airworthy module before further 

flight. You are also required, before 

further flight, to inspect the MGB 

module magnetic ‘‘CHIP’’ detector 

electrical circuit and determine whether 

the system is functioning properly, 

including whether the ‘‘CHIP’’ detector 

light annunciates on the instrument 

panel. This condition, if not corrected, 

could result in failure of the MGB and 

loss of control of the helicopter. 

Since issuing that AD, we have 

determined the AD should also apply to 

the Model AS332L2 helicopters. We 

have also determined that we 

incorrectly described a part as 

‘‘magnetic plug’’, and the correct 

nomenclature is ‘‘chip detector.’’ 

Finally, we have determined that 

modifying the chip collector and 

inspecting the chip detector should be 

required to enhance the early detection 

capability of the chip detectors of the 

gearbox sump and the epicyclic module. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

No. 2009–0099–E, dated April 23, 2009 

(EAD No. 2009–0099–E), which 

supersedes AD No. 2009–0087–E, dated 

April 11, 2009 and AD No. 2009–0095– 

E, dated April 17, 2009, to correct an 

unsafe condition for the Eurocopter 

Model AS332L2 and EC225LP 

helicopters. EASA advises that early 

investigations showed that a failure 

within the epicyclic reduction gear 

module of the MGB resulted in the 

rupture of the MGB case, which allowed 

the main rotor head to separate from the 

helicopter. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, their 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 


srobinson on DSK4SPTVN1PROD with RULES
5992 Federal Register / Vol. 77, No. 25 / Tuesday, February 7, 2012 / Rules and Regulations 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

Eurocopter has issued two Emergency 

Alert Service Bulletins (EASBs) with 

four numbers: No. 05.00.81 for FAA 

type-certificated Model AS332L2 

helicopters; No. 05.00.58 for non-FAA 

type-certificated military Model 

AS532A2 and U2 helicopters; No. 

05A016 for non-FAA type-certificated 

military Model EC725AP helicopters; 

and No. 05A017 for FAA typecertificated Model EC225LP helicopters. 

Both EASBs are Revision 2, and are 

dated April 23, 2009. The EASBs 

specify checking the chip detector on 

the MGB epicyclic module, modifying 

the main module chip collector, 

reidentifying the chip collector, and 

installing the chip collector (MOD 

0752522). EASA classified these EASBs, 

or later approved versions, as 

mandatory and issued EAD No. 2009– 

0099–E to ensure continued 

airworthiness of these helicopters. 

AD Requirements 

This AD requires: 

• Determining from the maintenance 

records whether, within the last 200 

hours time-in-service (TIS), the ‘‘CHIP’’ 

detector light illuminated because of a 

metal particle on the chip detector of 

the module, and if so, whether the 

‘‘CHIP’’ detector light stayed 

illuminated after the ‘‘CHIP’’ detector 

switch was turned to the ‘‘CHIP PULSE’’ 

setting to activate the ‘‘fuzz burn-off’’ 

feature. 

• If the maintenance records indicate 

that the ‘‘CHIP’’ detector light 

illuminated because of a metal particle 

on the chip detector of the module, and 

the ‘‘CHIP’’ detector light stayed 

illuminated after the ‘‘CHIP’’ detector 

switch was turned to the ‘‘CHIP PULSE’’ 

setting, replace the module with an 

airworthy module before further flight. 

• If the maintenance records do not 

indicate which ‘‘CHIP’’ detector caused 

the ‘‘CHIP’’ detector light to illuminate, 

or whether the detector light stayed 

illuminated after the ‘‘CHIP’’ detector 

switch was turned to the ‘‘CHIP PULSE’’ 

setting, replace the module with an 

airworthy module before further flight. 

• Inspecting the MGB module 

magnetic chip detector electrical circuit 

and determining whether the system is 

functioning properly, including whether 

the ‘‘CHIP’’ detector light annunciates 

on the instrument panel (Vehicle 

Monitoring System Screen). 

• Thereafter, if the ‘‘CHIP’’ detector 

light illuminates, stays illuminated after 

the ‘‘CHIP’’ detector switch is turned to 

the ‘‘CHIP PULSE’’ setting, and there is 

a metal particle on the epicyclic module 

chip detector, (rather than the main 

reduction gear (lower MGB), the flared 

housing (mast assembly), the 

intermediate gearbox, or the tail rotor 

gearbox chip detectors) that caused the 

‘‘CHIP’’ detector light to illuminate, 

replace the module with an airworthy 

module. 

• Unless accomplished previously, 

within 50 hours TIS, remove, modify, 

reidentify, and reinstall the chip 

collector. 

• Before installing a MGB on any 

Eurocopter Model AS332L2 or EC225LP 

helicopter, modify, reidentify, and 

reinstall the chip collector in 

accordance with paragraph (f)(3) of this 

AD. 

Differences Between This AD and the 

EASA AD 

The differences between this AD and 

the EASA AD are: 

• We use the term ‘‘hours time-inservice’’ rather than ‘‘flight hours’’ to 

describe compliance times. 

• We use the term ‘‘chip detector’’ 

rather than ‘‘magnetic plug’’ to refer to 

the same part. 

• If it is determined that within the 

past 200 hours TIS a ‘‘CHIP’’ light was 

caused by a particle in the module, we 

require replacing the module with an 

airworthy module rather than inspecting 

it and returning the same module to 

service. 

• We do not mandate a calendar time 

for complying with this AD. 

• The EASA AD specifies, for 

Eurocopter Model AS332L2 helicopters, 

checking the chip detector of the 

module after the last flight of the day, 

not to exceed 10 hours TIS, and for the 

Model EC225LP helicopters, complying 

with the maintenance manual each time 

a particle is detected. This AD requires 

treating both models the same, since 

both models have the same type of chip 

detectors and anticipate compliance 

with ‘‘normal’’ maintenance procedures 

each time a particle is detected after 

accomplishing paragraph (f)(3) of this 

AD. 

• We do not require returning 

unairworthy parts or found particles to 

the manufacturer. 

Costs of Compliance 

We estimate that this AD will affect 4 

helicopters of U.S. registry. We estimate 

that it will take about 1.0 work hour to 

inspect maintenance records to 

determine if a ‘‘CHIP’’ light illuminated 

within the past 200 hours TIS; 10 workhours to remove, inspect, and replace a 

module; 14 work-hours to remove, 

modify, and replace the module to 

incorporate the ‘‘CHIP’’ collector and 

flange modifications (MOD 0752522); 

and 0.2 work-hour, per inspection, to 

conduct the initial and repetitive 

inspection of the chip detector for metal 

particles. The average labor rate is $85 

per work-hour, and we estimate it will 

cost $85 to inspect the maintenance 

records; $850 to remove, inspect, and 

replace a module; $1,190 to incorporate 

MOD 0752522; and $408 to inspect the 

chip detector (assumes 24 inspections 

per year per helicopter), for an 

estimated total labor cost of $2,533 per 

helicopter. Required parts cost is 

approximately $512,318 to replace a 

module. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators is $522,450, assuming all 

required inspections and modifications 

are completed on all helicopters and 1 

helicopter requires a module 

replacement 

FAA’s Justification and Determination 

of the Effective Date 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect both the structural 

integrity and controllability of the 

helicopter. Therefore, because the 

determination of the ‘‘CHIP’’ light 

illumination, inspection, and 

replacement of the module (on 

condition) are required before further 

flight, this AD must be issued 

immediately. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined 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. 

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 


srobinson on DSK4SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 25 / Tuesday, February 7, 2012 / Rules and Regulations 5993 

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, 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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: 

2012–01–03 Eurocopter France: 

Amendment No. 39–16914; Docket No. 

FAA–2012–0005; Directorate Identifier 

2010–SW–091–AD. 

(a) Applicability. This AD applies to Model 

AS332L2 and EC225LP helicopters, 

certificated in any category. 

(b) Unsafe Condition. This AD defines the 

unsafe condition as degradation of the 

epicyclic reduction gear module within the 

main gearbox (MGB). This condition could 

result in failure of the MGB and subsequent 

loss of control of the helicopter. 

(c) Other Affected ADs. This AD 

supersedes AD 2009–09–51, Amendment 39– 

16101, Docket No. FAA–2009–1089, 

Directorate Identifier 2009–SW–16–AD, (74 

FR 65679, Dec. 11, 2009). 

(d) Effective Date. This airworthiness 

directive (AD) becomes effective February 22, 

2012. 

(e) Compliance. You are responsible for 

performing each action required by this AD 

within the specified compliance time unless 

it has already been accomplished prior to 

that time. 

(f) Required Actions. To prevent failure of 

the main gearbox (MGB) and loss of control 

of the helicopter: 

(1) Before further flight: 

(i) Determine from the maintenance 

records whether, within the last 200 hours 

time-in-service (TIS), the ‘‘CHIP’’ detector 

light illuminated because of a metal particle 

on the chip detector of the MGB epicyclic 

module (module), and if so, whether the 

‘‘CHIP’’ detector light stayed illuminated 

after the ‘‘CHIP’’ detector switch was turned 

to the ‘‘CHIP PULSE’’ setting to activate the 

‘‘fuzz burn-off’’ feature. 

(A) If the maintenance records indicate that 

the ‘‘CHIP’’ detector light illuminated 

because of a metal particle on the chip 

detector of the module, and the ‘‘CHIP’’ 

detector light stayed illuminated after the 

‘‘CHIP’’ detector switch was turned to the 

‘‘CHIP PULSE’’ setting, replace the module 

with an airworthy module before further 

flight. 

(B) If the maintenance records do not 

indicate which ‘‘CHIP’’ detector caused the 

‘‘CHIP’’ detector light to illuminate, or 

whether the detector light stayed illuminated 

after the ‘‘CHIP’’ detector switch was turned 

to the ‘‘CHIP PULSE’’ setting, replace the 

module with an airworthy module before 

further flight. 

(ii) Inspect the module magnetic chip 

detector electrical circuit and determine 

whether the system is functioning properly, 

including whether the ‘‘CHIP’’ detector light 

annunciates on the instrument panel (Vehicle 

Monitoring System Screen). 

(2) After accomplishing paragraph (f)(1) of 

this AD, thereafter, if the ‘‘CHIP’’ detector 

light illuminates, stays illuminated after the 

chip detector switch is turned to the ‘‘CHIP 

PULSE’’ setting, and there is a metal particle 

on the module magnetic chip detector (rather 

than the main reduction gear (lower MGB), 

the flared housing (mast assembly), the 

intermediate gearbox, or the tail rotor gearbox 

chip detectors) that caused the ‘‘CHIP’’ 

detector light to illuminate, replace the 

module with an airworthy module. 

(3) Within 50 hours TIS, remove, modify, 

reidentify, and reinstall the chip collector as 

shown in Figures 2 through 5, and in 

accordance with the Accomplishment 

Instructions, paragraph 2.B.3.b.1) through 

2.B.3.b.5) of Eurocopter Emergency Alert 

Service Bulletin (EASB) No. 05.00.81, 

Revision 2, dated April 23, 2009, or 

Eurocopter EASB No. 05A017, Revision 2, 

dated April 23, 2009, for your model 

helicopter. 

(4) Before installing a MGB, modify, 

reidentify, and reinstall the chip collector in 

accordance with paragraph (f)(3) of this AD. 

Note 1 to paragraph (f) of this AD: 

Eurocopter has issued two EASBs with four 

different numbers (Nos. 05.00.81, 05.00.58, 

05A017, and 05A016) that apply to 5 

different Eurocopter model helicopters. 

EASB No. 05.00.58 is for Eurocopter military 

Model AS532A2, and U2 helicopters, and 

EASB No. 05A016 is for Eurocopter military 

Model EC725AP helicopters that are nonFAA type-certificated. EASB No. 05.00.81 is 

for FAA type-certificated Eurocopter Model 

AS332L2 helicopters and EASB No. 05A017 

is for FAA type-certificated Eurocopter 

Model EC225LP helicopters. This AD does 

not incorporate by reference EASB Nos. 

05A016 or 05.00.58. 

(g) Alternative Methods of Compliance 

(AMOCs). 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Rao Edupuganti, 

Aerospace Engineer, FAA, Rotorcraft 

Directorate, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–4389; fax: (817) 

222–5961, email rao.edupaganti@faa.gov. 

(2) For operations conducted under a Part 

119 operating certificate or under Part 91, 

Subpart K, we suggest that you notify your 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office or certificate holding 

district office, before operating any aircraft 

complying with this AD through an AMOC. 

(h) Additional Information. The subject of 

this AD is addressed in European Aviation 

Safety Agency AD No. 2009–0099–E, dated 

April 23, 2009. 

(i) Subject. JASC Code: 6300: Rotor Drive 

System. 

(j) Material Incorporated by Reference. You 

must use the following service information to 

do the actions required by this AD, unless the 

AD specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference (IBR) of the following service 

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

part 51: 

(1) Eurocopter Emergency Alert Service 

Bulletin No. 05.00.81, Revision 2, dated April 

23, 2009, for the model AS332L2; and 

(2) Eurocopter Emergency Alert Service 

Bulletin No. 05A017, Revision 2, dated April 

23, 2009, for the model EC225LP helicopters. 

(3) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, Grand 

Prairie, Texas 75052, telephone (972) 641– 

0000 or (800) 232–0323, fax (972) 641–3775, 

or at http://www.eurocopter.com/techpub. 

(4) You may review copies of the 

referenced service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth Texas 76137 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. 


srobinson on DSK4SPTVN1PROD with RULES
5994 Federal Register / Vol. 77, No. 25 / Tuesday, February 7, 2012 / Rules and Regulations 

Issued in Fort Worth, Texas, on December 

28, 2011. 

M. Monica Merritt, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–1118 Filed 2–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0086; Directorate 

Identifier 2011–SW–045–AD; Amendment 

39–16936; AD 2012–02–13] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Eurocopter France EC130B4 helicopters 

that have not had Eurocopter 

Modification 073880 incorporated. This 

AD is prompted by several reports of 

cracks in the tailboom/Fenestron 

junction frame, which could result in 

structural failure of the tail boom, 

resulting in detachment of the Fenestron 

(tail rotor) and subsequent loss of 

control of the helicopter. We are issuing 

this AD to correct the unsafe condition 

on these helicopters. 

DATES: This AD becomes effective 

February 22, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of February 22, 2012. 

We must receive comments on this 

AD by April 9, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone (800) 647–5227) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

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 copies of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth Texas 76137. 

FOR FURTHER INFORMATION CONTACT: Jim 

Grigg, Manager, FAA, Rotorcraft 

Directorate, Safety Management Group, 

2601 Meacham Blvd., Fort Worth, TX 

76137, telephone (817) 222–5126, email: 

jim.grigg@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

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– 

0116, dated July 6, 2011 (AD 2011– 

0116) to correct an unsafe condition for 

Eurocopter EC 130 B4 helicopters. 

EASA advises of several reports of 

cracks in the tailboom/Fenestron 

junction frame. Prompted by these 

reports, Eurocopter published 

Information Notice No. 2167–I–53 

(2167–I–53). Since publication of 2167– 

I–53, new cases of cracks in the 

tailboom/Fenestron junction frame have 

been reported. Examination of the parts 

revealed the cracks were longer than the 

previously reported cracks and started 

to develop in the plane of the rivet head 

countersink on the right hand (RH) side 

of the Fenestron and spread to the web 

of the frame. This condition, if not 

corrected, could lead to structural 

failure, which could result in Fenestron 

detachment and consequent loss of 

control of the helicopter. AD 2011–0116 

requires repetitive inspections of the 

affected area and depending on 

findings, accomplishing corrective 

actions. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, their 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition is likely to exist or 

develop on other helicopters of these 

same type designs. 

Related Service Information 

We reviewed Eurocopter Emergency 

Alert Service Bulletin 53A019, dated 

June 14, 2011 (EASB). The EASB 

describes procedures for inspecting the 

RH side of the tailboom/Fenestron 

junction frame from the inside and 

outside for cracks. If a crack is present, 

the EASB requires contacting 

Eurocopter for approved repair 

instructions. 

AD Requirements 

This AD requires compliance with 

specified portions of the manufacturer’s 

service bulletin, except as discussed 

under ‘‘Differences Between this AD 

and the EASA AD.’’ 

Differences Between This AD and the 

EASA AD 

The EASA AD allows for flights for a 

certain period of time with known 

cracks. Except for limited ferry flights, 

this AD does not permit operations with 

known cracks. The EASA AD allows for 

an initial inspection which does not 


srobinson on DSK4SPTVN1PROD with RULES