Federal Register / Vol. 78, No. 75 / Thursday, April 18, 2013 / Rules and Regulations 23107 

be counted from the date of installation of the 

MLG wheel axle on an airplane, which 

occurs after the date of repair specified in the 

Part 1 of Appendix 1 of Airbus AOT A330– 

32A–3256, Revision 01, dated October 18, 

2012 (for Model A330–200 and –300 series 

airplanes); or Airbus AOT A340–32A–4292, 

Revision 01, dated October 18, 2012 (for 

Model A340–200 and –300 series airplanes). 

TABLE 2 TO PARAGRAPH (h)(2) OF THIS AD—POST-REPAIR MLG WHEEL AXLE FLIGHT HOURS OR LANDINGS

Affected airplanes 

Post-repair MLG wheel axle flight hours or 

landings, whichever occurs first, not to be 

exceeded (see paragraph (h)(2) of this 

AD) 

Model A340–311, –312, and –313 airplanes, WV00 ............................................................................. 7,830 landings or 37,080 flight hours. 

Model A340–211, –212, and –213 airplanes, WV00 ............................................................................. 7,660 landings or 48,330 flight hours. 

Model A340–313 airplanes, WV02 and WV05 ....................................................................................... 6,580 landings or 28,160 flight hours. 

Model A330–301, –321, –322, –341, and –342 airplanes, WV00 and WV01 ....................................... 8,410 landings or 25,330 flight hours. 

Model A330–201, –202, –203, –223, and –243 airplanes, WV02, WV05, and WV06 .......................... 7,410 landings or 29,830 flight hours. 

Model A330–301, –302, –303, –323, –342, and –343 airplanes, WV02 and WV05 ............................. 8,580 landings or 22,580 flight hours. 

(i) Parts Installation Limitation 

As of the effective date of this AD: An 

affected MLG wheel axle may be installed on 

an airplane, provided the MLG wheel axle 

has not exceeded the limits specified in table 

1 to paragraph (h)(1) of this AD and it is 

replaced with a serviceable part before 

reaching the life limit defined in table 1 to 

paragraph (h)(1) of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (h) of this AD 

with respect to the affected MLG wheel axle 

defined in paragraph (g)(1) of this AD, if 

those actions were performed before the 

effective date of this AD using the applicable 

service information specified in paragraph 

(j)(1) or (j)(2) of this AD, which is not 

incorporated by reference in this AD. 

(1) Airbus All Operator Telex A330– 

32A3256, including Appendix 1, dated 

August 24, 2011 (for Model A330–200 and 

–300 series airplanes). 

(2) Airbus All Operator Telex A340– 

32A4292, including Appendix 1, dated 

August 24, 2011 (for Model A340–200 and 

–300 series airplanes). 

(k) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; 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 reference 

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 assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0170, dated September 7, 2011, and the 

service information specified in paragraphs 

(l)(1)(i) and (l)(1)(ii) of this AD, for related 

information. 

(i) Airbus AOT A330–32A–3256, Revision 

01, including Appendix 1, dated October 18, 

2012. 

(ii) Airbus AOT A340–32A–4292, Revision 

01, including Appendix 1, dated October 18, 

2012. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(m) 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) Airbus Alert Operators Transmission 

(AOT) A330–32A–3256, Revision 01, 

including Appendix 1, dated October 18, 

2012. The Document number and revision 

level are not identified on pages 2–5 of this 

AOT; the revision date is identified on only 

page 1 of this AOT and the first page of 

Appendix 1 of this AOT. 

(ii) AOT A340–32A–4292, Revision 01, 

including Appendix 1, dated October 18, 

2012. The Document number and revision 

level are not identified on pages 2–5 of this 

AOT; the revision date is identified on only 

page 1 of this AOT and the first page of 

Appendix 1 of this AOT. 

(3) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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 5, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08741 Filed 4–17–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1087; Directorate 

Identifier 2009–SW–32–AD; Amendment 39– 

17424; AD 2013–08–07] 

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 

Eurocopter France (ECF) Model 

AS332C, L, and L1 helicopters to 

require an initial and repetitive 

inspections of the outer skin, butt strap, 

and fuselage frame for a crack and 

modification of the helicopter. This AD 

was prompted by an AD issued by the 


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23108 Federal Register / Vol. 78, No. 75 / Thursday, April 18, 2013 / Rules and Regulations 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, which states that a crack was 

discovered in a fuselage frame during a 

daily check. The actions of this AD are 

intended to detect a crack, to prevent 

loss of airframe structural integrity and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective May 23, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of May 23, 2013. 

ADDRESSES: 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. 

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: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 16, 2012, at 77 FR 63262, 

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 certain ECF Model 

AS332C, L, and L1 helicopters without 

modification (MOD) 0722907. That 

NPRM proposed to require an initial 

and repetitive visual inspections for a 

crack in the outer skin and the butt strap 

in the sliding cowling right-hand and 

left-hand rail attachment areas on Frame 

5295, and if there is a crack, inspecting 

for a crack in Frame 5295 and repairing 

any cracked part. The NPRM also 

proposed to require modifying each 

helicopter with MOD 0726478R2 on the 

sliding cowling rails and shims in the 

attachment areas on Frame 5295. The 

proposed requirements were intended to 

detect a crack, to prevent loss of 

airframe structural integrity and 

subsequent loss of control of the 

helicopter. 

EASA issued EASA AD No. 2008– 

0035–E, dated February 21, 2008, to 

correct an unsafe condition for the ECF 

Model AS 332 C, C1, L, and L1 

helicopters. EASA advises that a crack 

was discovered on an ECF Model 

AS332L helicopter in fuselage frame 

5295, which has plates and angles 

assembled by riveting that corresponds 

to the first generation frame (before 

MOD 0722907). The crack in the frame 

was found because of a crack in the 

outer skin and in the butt strap where 

the rail of the main gear box (MGB) 

sliding cowling is attached to the frame. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (77 FR 63262, October 16, 2012). 

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 and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed, except we have updated the 

contact information for American 

Eurocopter Corporation. This minor 

editorial change is consistent with the 

intent of the proposals in the NPRM (77 

FR 63262, October 16, 2012) and will 

not increase the economic burden on 

any operator nor increase the scope of 

the AD. 

Differences Between This AD and the 

EASA AD 

This AD requires you to repair Frame 

5295 before further flight rather than 

contacting the manufacturer. This AD 

refers to a check as an inspection to be 

performed by a mechanic versus a check 

that a pilot can do if specifically 

allowed by the AD. This AD also does 

not list the Model AS332C1 in the 

applicability because this model is not 

type certificated in the U.S. This AD 

also does not allow further flight with 

the outer skin or butt strap cracked 

unless it is a ferry flight to a repair 

facility. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin No. 05.00.76, Revision 0, dated 

February 20, 2008 (ASB), which 

specifies checking for a crack on the 

outside of the helicopter, on the skin, 

and the butt strap near the sliding 

cowling rail attachment. If a crack is 

found in the outer skin or butt strap, the 

ASB specifies visually checking for a 

crack in Frame 5295. The ASB specifies 

doing MOD 0726478R2, which consists 

of cutting out a section of the sliding 

cowling rails. This cut-out exposes the 

splice near the rail attachment holes, 

making it easier to detect a crack in the 

frame during the 10-hour repetitive 

inspection and thus reducing the risks 

of a crack going undetected in Frame 

5295. Also, the ASB specifies contacting 

the manufacturer for the ‘‘appropriate 

repair sheet according to how the crack 

is situated’’ if there is a crack in Area 

1 of Frame 5295. EASA classified this 

ASB as mandatory and issued AD No. 

2008–0035–E, dated February 21, 2008, 

to ensure the continued airworthiness of 

these helicopters. 

Costs of Compliance 

We estimate that this AD will affect 5 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

We estimate that it will take about 4.25 

work-hours per helicopter to initially 

inspect for a crack and to modify the 

MGB sliding cowling rails. Each 10-hour 

repetitive inspection will take about 

0.25 work-hour. The average labor rate 

is $85 per work-hour and required parts 

will cost about $1,793 per helicopter. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators will be 

$17,145 or $3,429 per helicopter, 

assuming 60 repetitive inspections will 

be performed each year and assuming 

the entire fleet is modified and no 

cracks are found. 

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. 


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Federal Register / Vol. 78, No. 75 / Thursday, April 18, 2013 / Rules and Regulations 23109 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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 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 airworthiness 

directive (AD): 

2013–08–07 Eurocopter France: 

Amendment 39–17424; Docket No. 

FAA–2012–1087; Directorate Identifier 

2009–SW–32–AD. 

(a) Applicability 

This AD applies to all Model AS332C, L, 

and L1 helicopters without modification 

(MOD) 0722907, except helicopters with 

serial numbers 2078 and 2102, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the outer skin, butt strap, or fuselage 

frame, which could result in loss of airframe 

structural integrity, and subsequent loss of 

control of the helicopter. 

(c) Effective Date 

This AD becomes effective May 23, 2013. 

(d) 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. 

(e) Required Actions 

(1) Within 10 hours time-in-service (TIS) 

for helicopters that have 8,800 or more hours 

TIS or before or upon reaching 8,810 hours 

TIS for helicopters that have less than 8,800 

hours TIS, and thereafter at intervals not to 

exceed 10 hours TIS, visually inspect for a 

crack on the outer skin and the butt strap in 

the sliding cowling right-hand and left-hand 

rail attachment areas on Frame 5295 as 

shown in Figure 2 of Eurocopter Alert 

Service Bulletin No. 05.00.76, Revision 0, 

dated February 20, 2008 (ASB). 

(i) If there is a crack in the outer skin or 

in the butt strap per paragraph (e)(1) of this 

AD, before further flight, inspect for a crack 

in Frame 5295 in the areas shown in Figure 

3, Area 1, and Figure 4, of the ASB. 

(ii) If there is a crack in the outer skin, the 

butt strap, or in Frame 5295 in the areas 

inspected as required by this AD, before 

further flight, repair the part in accordance 

with a method approved by the FAA. 

(2) Within 300 hours TIS, for each 

helicopter that has 8,800 or more hours TIS, 

modify the sliding cowling rails and shims in 

the attachment areas on Frame 5295 

(corresponds to MOD 0726478R2), as 

depicted in Figure 5 and by following the 

Accomplishment Instructions, paragraph 

2.B.3., of the ASB. 

(f) Special Flight Permits 

A special flight permit is permitted for a 

helicopter with a crack in the outer skin or 

butt strap to operate the helicopter to a 

location where the requirements of this AD 

can be accomplished. A special flight permit 

is not permitted for a helicopter with a crack 

in Frame 5295. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@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 

The subject of this AD is addressed in 

European Aviation Safety Agency (France) 

AD No. 2008–0035–E, dated February 21, 

2008. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5311, Fuselage, Main Frame. 

(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 Alert Service Bulletin No. 

05.00.76, Revision 0, dated February 20, 

2008. 

(ii) Reserved. 

(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 April 8, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08763 Filed 4–17–13; 8:45 am] 

BILLING CODE 4910–13–P 


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