23462 Federal Register / Vol. 78, No. 76 / Friday, April 19, 2013 / Rules and Regulations 

(k) Definition 

For purposes of this AD, a serviceable 

stowage box has P/N CSD 30–005–3–8 with 

any S/N 1013 or higher, or any serial number 

below 1013 with the suffix ‘‘–A.’’ 

(l) Terminating Action 

Except as required by paragraph (j) of this 

AD, at the applicable time specified in 

paragraph (l)(1) or (l)(2) of this AD, replace 

any non-serviceable stowage box with a 

serviceable stowage box, in accordance with 

the Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–241, dated 

March 7, 2013. Replacement of all affected 

stowage boxes terminates the requirements of 

paragraphs (h) and (i) of this AD, and the 

AFM revision required by paragraph (h) of 

this AD may be removed from the AFM. 

(1) For a stowage box that has accumulated 

less than 50 total flight hours as of the 

effective date of this AD: Replace the stowage 

box within 8 days after the AFM revision 

required by paragraph (h) of this AD. 

(2) For a stowage box that has accumulated 

50 or more total flight hours as of the 

effective date of this AD: Replace the stowage 

box within 65 days after the AFM revision 

required by paragraph (h) of this AD. 

(m) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a non-serviceable flight 

crew oxygen mask stowage box any airplane. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone 425–227–1137; fax 425–227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically refer to this 

AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA approved. Corrective 

actions are considered FAA approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to ensure the product is airworthy before it 

is returned to service. 

(o) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) 

emergency European Aviation Safety Agency 

(EASA) Airworthiness Directive 2013–0059– 

E, dated March 8, 2013; and Dassault 

Mandatory Service Bulletin 7X–241, dated 

March 7, 2013; for related information. 

(p) 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) Dassault Mandatory Service Bulletin 

7X–241, dated March 7, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http:// 

www.dassaultfalcon.com. 

(4) You may review copies of the 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. 

(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 April 3, 

2013. 

Ali Bahrami, 

Manager,Transport Airplane 

Directorate,Aircraft Certification Service. 

[FR Doc. 2013–09108 Filed 4–18–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0307; Directorate 

Identifier 2012–SW–079–AD; Amendment 

39–17410; AD 2013–07–06] 

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 

Eurocopter France (Eurocopter) Model 

AS332C, AS332L, and AS332L1 

helicopters and superseding an AD for 

Model AS332L2 and EC225LP 

helicopters. This AD requires inspecting 

the chip detector and modifying the 

chip collector, both installed on the 

main gearbox (MGB). This AD is 

prompted by an investigation which 

showed a failure within the epicyclic 

reduction gear module (epicyclic 

module) resulted in the rupture of the 

MGB case and separation of the main 

rotor head of a Model AS332L2 

helicopter. These actions are intended 

to prevent failure of the MGB and 

subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective May 

6, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of May 6, 2013. 

We must receive comments on this 

AD by June 18, 2013. 

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 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., 


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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 

On December 28, 2011, we issued AD 

2012–01–03, Amendment 39–16914 (77 

FR 5991, February 7, 2012) for 

Eurocopter Model AS332L2 and 

EC225LP helicopters. AD 2012–01–03, 

Amendment 39–16914 requires 

determining whether the ‘‘CHIP’’ 

detector light illuminated because of a 

metal particle on the chip detector of 

the epicyclic module, and whether the 

‘‘CHIP’’ detector light stayed 

illuminated after the ‘‘CHIP’’ detector 

switch was turned to the ‘‘CHIP PULSE’’ 

setting. If so, or 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 switch was turned, AD 2012–01–03 

requires replacing the epicyclic module 

before further flight. AD 2012–01–03 

also requires replacing the epicyclic 

module if, thereafter, the ‘‘CHIP’’ 

detector light illuminates, stays 

illuminated after the switch is turned, 

and there is a metal particle on the 

epicyclic module chip detector. Lastly, 

AD 2012–01–03 requires removing, 

modifying, re-identifying, and 

reinstalling the chip collector within 50 

hours time-in-serivce (TIS) and before 

installing a MGB on any applicable 

helicopter. 

AD 2012–01–03, Amendment 39– 

16914 (77 FR 5991, February 7, 2012) 

was prompted by an investigation of an 

accident that showed 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. The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Union, had issued 

EASA AD 2009–0099–E, dated April 23, 

2009 (2009–0099–E) to correct an unsafe 

condition for Eurocopter Model 

AS332L2 and EC225LP helicopters, and 

notified us of the unsafe condition in its 

AD. The actions of AD 2012–01–03 are 

intended to prevent failure of the MGB 

and subsequent loss of control of the 

helicopter. 

Actions Since Existing AD Was Issued 

Since we issued AD 2012–01–03, 

Amendment 39–16914 (77 FR 5991, 

February 7, 2012), EASA issued EASA 

AD No. 2012–0129–E, dated July 13, 

2012 (2012–0129–E), which superseded 

EASA AD 2009–0099–E, to correct an 

unsafe condition for Eurocopter Model 

AS332C, AS332C1, AS332L, AS332L1, 

AS332L2, and EC225LP helicopters. 

EASA advises that, based on the final 

accident report following investigation 

of the accident that prompted its 

original AD, it is necessary to 

standardize the inspection intervals for 

all electrical and non-electrical chip 

detectors, require the inspection for all 

models of the ‘‘Super-Puma’’ helicopter 

family, and expand the inspection to all 

rotor drive system gear boxes (the 

intermediate gearbox (IGB) and the tail 

gear box (TGB), in addition to the MGB. 

EASA AD 2012–0129–E retains the 

modification of the MGB epicyclic 

reduction gear module requirement of 

EASA AD 2009–0099–E, but expands 

the applicability and requires a 

recurring inspection of all electrical and 

non-electrical chip detectors installed 

on the MGB, IGB, and TGB. 

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, its 

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 exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

Eurocopter has issued Emergency 

ASB No. 05.00.81, Revision 3, dated 

July 13, 2012 (EASB 05.00.81), for 

Model AS332L2 helicopters and 

Emergency ASB No. 05A017, Revision 

3, dated July 13, 2012 (EASB 05A017) 

for Model EC225LP helicopters. Both 

Emergency ASBs specify procedures for 

checking the chip detector on the MGB 

epicyclic module, modifying the main 

module chip collector, reidentifying the 

chip collector, and installing the chip 

detector. 

Eurocopter has also issued Alert 

Service Bulletin (ASB) No. AS332– 

05.00.94, Revision 0, dated July 13, 2012 

(ASB AS332–05.00.94), for Model 

AS332 C, C1, L, L1, and L2 helicopters 

and ASB No. EC225–05A29, Revision 0, 

dated July 13, 2012 (ASB EC225–05A29) 

for Model EC225 LP helicopters. Both 

ASBs standardize the time interval 

between chip detector inspections of the 

MGB, IGB, and TGB. 

EASA classified these ASBs as 

mandatory and issued EASA AD 2012– 

0129–E to ensure continued 

airworthiness of these helicopters. 

AD Requirements 

This AD retains the inspection and 

modification requirements of AD 2012– 

01–03, Amendment 39–16914 (77 FR 

5991, February 7, 2012), and adds the 

following requirements: 

• For AS332 helicopters with nonelectrical chip detectors and electrical 

chip detectors without a caution light 

on the instrument panel, within 25 

hours TIS and thereafter at intervals not 

exceeding 25 hours TIS, inspecting the 

MGB, IGB, and TGB chip detectors for 

a chip or magnetic particle. 

• For AS332 helicopters with 

electrical chip detectors with a caution 

light on the instrument panel, within 50 

hours TIS and thereafter at intervals not 

exceeding 50 hours TIS, inspecting the 

MGB, IGB, and TGB chip detectors for 

a chip or magnetic particle. 

• For EC225 helicopters, within 50 

hours TIS and thereafter at intervals not 

exceeding 50 hours TIS, inspecting the 

MGB, IGB, and TGB chip detectors for 

a chip or magnetic particle. If there is a 

chip or magnetic particle, verifying that 

the ‘‘CHIP’’ caution light illuminates on 

the ‘‘Vehicle’’ page of the Vehicle 

Management System. 

Costs of Compliance 

We estimate that this AD will affect 6 

helicopters of U.S. Registry. Based on an 

average labor rate of $85 per work hour, 

we estimate that operators may incur 

the following costs in order to comply 

with this AD: 


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• Inspecting maintenance records to 

determine if a ‘‘CHIP’’ light illuminated 

within the past 200 hours TIS will take 

about 1.0 work-hour, for a total cost per 

helicopter of $85; 

• Removing, inspecting, and 

replacing an affected epicyclic module 

will require about 10 work-hours and 

required parts would cost 

approximately $512,318, for a total cost 

per helicopter of $513,168; 

• Removing, modifying, and 

reidentifying the ‘‘CHIP’’ collector will 

require about 14 work-hours, for a total 

cost per helicopter of $1,190; and 

• Inspecting the module magnetic 

chip detector circuit and the MGB, IGB, 

and TGB chip detectors will require 

about 2 work-hours, for a total cost per 

helicopter of $170 per inspection cycle. 

FAA’s Justification and Determination 

of the Effective Date 

The short compliance time involved 

is required because the previouslydescribed unsafe condition can 

adversely affect both the structural 

integrity and controllability of the 

helicopter. Therefore, because these 

helicopters are primarily used for longrange offshore transportation and the 

inspection of the MGB, IGB, and TGB 

chip detectors is required within 25 

hours TIS, a very short time period 

based on the average flight-hour 

utilization rate of these helicopters, 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 

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 

removing airworthiness directive (AD) 

2012–01–03, Amendment 39–16914 (77 

FR 5991, February 7, 2012) and adding 

the following new AD: 

2013–07–06 Eurocopter France 

(Eurocopter): Amendment 39–17410; 

Docket No. FAA–2013–0307; Directorate 

Identifier 2012–SW–079–AD. 

(a) Applicability 

This AD applies to Eurocopter Model 

AS332C, AS332L, AS332L1, 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 a rotor drive system gearbox. 

This condition could result in failure of the 

main gearbox (MGB), intermediate gearbox 

(IGB), or tail gearbox (TGB) and subsequent 

loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2012–01–03, 

Amendment No. 39–16914 (77 FR 5991, 

February 7, 2012). 

(d) Effective Date 

This AD becomes effective May 6, 2013. 

(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 

(1) For Model AS332L2 and EC225LP 

helicopters, 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). 

(iii) After accomplishing paragraph 

(f)(1)(i)–(ii) 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 IGB, or the TGB 

chip detectors) that caused the ‘‘CHIP’’ 

detector light to illuminate, replace the 

module with an airworthy module. 

(iv) 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.1.b.1 through 

2.B.1.b.5, of Eurocopter Emergency Alert 

Service Bulletin (EASB) No. 05.00.81, 

Revision 3, dated July 13, 2012, or 

Eurocopter EASB No. 05A017, Revision 3, 


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dated July 13, 2012, for your model 

helicopter. 

(v) Before installing a MGB, modify, 

reidentify, and reinstall the chip collector in 

accordance with paragraph (f)(1)(iv) of this 

AD. 

(2) Within 25 hours TIS, and thereafter at 

intervals not exceeding 25 hours TIS: 

(i) For Model AS332C, L, and L1 

helicopters with non-electrical chip detectors 

and electrical chip detectors without a 

caution light on the instrument panel, 

inspect the IGB, TGB, tapered housing, and 

MGB bottom casing chip detectors for a chip 

or metallic particle. 

(ii) For Model AS332L2 helicopters with 

non-electrical chip detectors and electrical 

chip detectors without a caution light on the 

instrument panel, inspect the module, main 

rotor mast tapered housing, IGB, and TGB 

chip detectors for a chip or metallic particle. 

(3) Within 50 hours TIS, and thereafter at 

intervals not exceeding 50 hours TIS: 

(i) For Model AS332C, L, and L1 

helicopters with electrical chip detectors 

with a caution light on the instrument panel, 

inspect the MGB bottom casing, TGB, and 

IGB chip detectors for a chip or metallic 

particle. 

(ii) For Model AS332L2 helicopters with 

electrical chip detectors with a caution light 

on the instrument panel, inspect the MGB 

bottom casing chip detector for a chip or 

magnetic particle. 

(iii) For Model EC225LP helicopters, 

inspect the MGB, IGB, and TGB chip 

detectors for a chip or magnetic particle. If 

there is a chip or magnetic particle, 

determine whether the ‘‘CHIP’’ caution light 

illuminates on the ‘‘Vehicle’’ page of the 

Vehicle Management System. If the ‘‘CHIP’’ 

caution light does not illuminate on the 

‘‘Vehicle’’ page, perform a fault analysis. 

(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) 222–5110; fax: (817) 

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

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR 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 

(1) Eurocopter Alert Service Bulletin (ASB) 

No. AS332–05–00–94, Revision 0, dated July 

13, 2012, and ASB No. EC225–05A29, 

Revision 0, dated July 13, 2012, which are 

not incorporated by reference, contain 

additional information about the subject of 

this AD. 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 a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2012–0129–E, dated July 13, 2012. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6320: Main Rotor Gearbox and 6520: 

Tail Rotor Gearbox. 

(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) Eurocopter Emergency Alert Service 

Bulletin (EASB) No. 05.00.81, Revision 3, 

dated July 13, 2012. 

Note 1 to paragraph (j)(2)(i): Eurocopter 

EASB No. 05.00.81, Revision 3, dated July 13, 

2012, and EASB No. 05.00.58, Revision 3, 

dated July 13, 2012, were published together 

as a single document. EASB No. 05.00.58, 

Revision 3, dated July 13, 2012 is not 

incorporated by reference. 

(ii) Eurocopter EASB No. 05A017, Revision 

3, dated July 13, 2012. 

Note 2 to paragraph (j)(2)(ii): Eurocopter 

EASB No. 05A017, Revision 3, dated July 13, 

2012, and EASB No. 05A016, Revision 3, 

dated July 13, 2012, were published together 

as a single document. EASB No. 05A016, 

Revision 3, dated July 13, 2012 is not 

incorporated by reference. 

(3) For Eurocopter 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 view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on March 27, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08459 Filed 4–18–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0938; Directorate 

Identifier 2011–NM–271–AD; Amendment 

39–17425; AD 2013–08–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–600 

series airplanes. This AD was prompted 

by reports of early fatigue cracks at 

chem-mill areas on the crown skin 

panels. This AD requires repetitive 

inspections for cracking of the fuselage 

skin at certain locations at chem-mill 

areas, and repair if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking of the skin panel at the 

specified chem-mill step locations, 

which could result in rapid 

decompression of the airplane. 

DATES: This AD is effective May 24, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 24, 2013. 

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. 

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 


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