Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 60681 

(a) Effective Date 

This AD is effective November 6, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 717–200 airplanes, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of cracks of overwing frames. We are issuing 

this AD to detect and correct such cracking 

that could sever a frame, which may increase 

the loading of adjacent frames, and result in 

damage to the adjacent structure and 

consequent loss of structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: Do a 

general visual inspection and a high 

frequency eddy current (HFEC) inspection for 

cracking of the left-side and right-side 

overwing frames at stations 674, 696, and 

715; and do all applicable corrective actions; 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

717–53A0034, Revision 1, dated November 7, 

2012. Repeat the inspections thereafter at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 717–53A0034, Revision 1, dated 

November 7, 2012, except as provided by 

paragraph (h) of this AD. 

(1) Before the accumulation of 12,000 total 

flight cycles. 

(2) Within 24 months or 8,275 flight cycles 

after the effective date of this AD, whichever 

occurs first. 

(h) Optional Terminating Action 

Modification of left-side and right-side 

overwing frames at stations 674, 696, and 

715, in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 717– 

53–0035, dated June 8, 2012, terminates the 

inspections required by paragraph (g) of this 

AD, and extends the compliance time of the 

modified area for the next repetitive HFEC 

inspection to 45,000 flight cycles after the 

modification, provided that the actions 

specified in paragraphs (h)(1), (h)(2), and 

(h)(3) of this AD are accomplished, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 717– 

53–0035, dated June 8, 2012. Do the 

inspections specified in paragraph (g) of this 

AD prior to, or concurrently with, the 

modification specified in paragraph (h) of 

this AD. 

(1) The overwing frame improvement 

modification of left-side and right-side 

overwing frames at stations 674, 696, and 715 

is installed and HFEC inspection is done 

within 45,000 flight cycles from the time the 

modification is installed, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 717–53–0035, dated June 8, 

2012. 

(2) If no crack is found during any 

inspection specified by paragraph (h)(1) of 

this AD, the HFEC inspections at the 

modified area are repeated thereafter at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

717–53–0035, dated June 8, 2012. 

(3) If any crack is found during any 

inspection specified by paragraph (h)(1) of 

this AD, the frame is repaired or replaced 

using a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD, before further flight. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if the general visual inspection and HFEC 

inspection for cracking of the left-side and 

right-side overwing frames at stations 674, 

696, and 715, and the applicable related 

investigative and corrective actions, were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 717– 

53A0034, dated October 5, 2011, which is not 

incorporated by reference in this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 

paragraph (k)(1) of this AD. 

(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 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, Los Angeles 

ACO to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

FR 25.571, Amendment 45, and the approval 

must specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact George Garrido, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, CA 90712– 

4137; phone: 562–627–5357; fax: 562–627– 

5210; email: george.garrido@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (l)(3) and (l)(4) of this 

AD. 

(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 717– 

53A0034, Revision 1, dated November 7, 

2012. 

(ii) Boeing Service Bulletin 717–53–0035, 

dated June 8, 2012. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; fax 

206–766–5683; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. 

(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 

September 17, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23321 Filed 10–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0480; Directorate 

Identifier 2012–SW–090–AD; Amendment 

39–17589; AD 2013–19–07] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Model SA–365N, SA– 

365N1, AS–365N2, AS 365 N3, EC 

155B, EC155B1, AS332C, AS332L, 

AS332L1, AS332L2, and EC225LP 

helicopters with certain EADS Sogerma 

pilot and co-pilot seats installed. This 

AD requires inspecting the rear beam of 


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60682 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 

each seat to determine if all of the weld 

beads are present and replacing the seat 

if any weld bead is missing. This AD is 

prompted by a maintenance inspection 

that discovered a missing weld bead on 

the rear beam of a pilot seat. These 

actions are intended to prevent failure 

of the pilot and co-pilot seats and 

subsequent injury to the pilot or copilot. 

DATES: This AD is effective November 6, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of November 6, 2013. 

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, the European 

Aviation Safety Agency (EASA) 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: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone 817–222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 5, 2013, at 78 FR 33766, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Eurocopter Model SA–365N, SA– 

365N1, AS–365N2, AS 365 N3, EC 

155B, EC155B1, AS332C, AS332L, 

AS332L1, AS332L2, and EC225LP 

helicopters with an EADS Sogerma pilot 

or co-pilot seat, part number (P/N) 

2510106–03–00 or P/N 2510106–06–00, 

with a serial number 720 through 1451, 

installed. The NPRM proposed to 

require, within 50 hours time-in-service 

(TIS), inspecting the rear beam of each 

pilot and co-pilot seat to determine if 

any weld beads are missing. If any weld 

beads are missing, before further flight, 

the NPRM proposed removing the seat 

from the helicopter and replacing it 

with an airworthy seat. The proposed 

requirements were intended to prevent 

failure of the pilot and co-pilot seats and 

subsequent injury to the pilot or copilot. 

The NPRM was prompted by AD No. 

2012–0206, dated October 2, 2012 (AD 

2012–0206), issued by EASA, which is 

the Technical Agent for the Member 

States of the European Union. EASA 

advised that during a maintenance 

inspection, a weld bead was found 

missing on the rear beam of an EADS 

Sogerma pilot seat. According to EASA, 

this non-conformity impairs the seat 

anti-crash function and may be present 

on a limited number of seats installed 

on Eurocopter helicopters. EASA states 

that this condition, if not corrected, 

could lead to pilot injury following a 

hard landing following an emergency. 

To address this unsafe condition, 

EASA issued AD No. 2012–0084, dated 

May 16, 2012 (AD 2012–0084), to 

require inspecting the flight crew seats, 

replacing any improperly welded seat, 

and marking all correctly welded seats. 

After issuing AD 2012–0084, a missing 

weld bead was discovered on another 

part of the seat rear beam that was not 

required to be inspected. As a result, 

EASA issued AD 2012–0206, which 

superseded AD 2012–0084, to revise the 

inspection procedure and add new areas 

of the rear beam of the seat to be 

inspected. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 33766, June 5, 2013). 

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. 

Differences Between This AD and the 

EASA AD 

The EASA AD allows compliance 

within 3 months or 50 flight hours, 

whichever occurs earlier; this AD 

requires compliance within 50 hours 

TIS. The EASA AD applies to Model 

AS332C1 helicopters. This AD does not 

because this model is not FAA typecertificated. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin (ASB) No. AS365–25.01.18 for 

Model SA–365N, SA–365 N1, AS– 

365N2, and AS 365 N3 helicopters; ASB 

No. EC155–25A114 for Model EC155 B 

and EC155B1 helicopters; ASB No. 

AS332–25.02.49 for model AS332C, 

AS332L, AS332L1, and AS332L2 

helicopters; and ASB No. EC225– 

25A110 for Model EC225LP helicopters; 

all Revision 1, dated August 9, 2012. 

The ASBs incorporate the procedures in 

EADS Sogerma Inspection Service 

Bulletin No. 2510106–25–888, Revision 

1, dated July 16, 2012, for inspecting the 

rear beam of the pilot and co-pilot seats 

to verify all of the weld beads are 

present. The complete EADS Sogerma 

bulletin is contained in the Appendix of 

the ASBs. EASA classified these ASBs 

as mandatory and issued AD 2012–0206 

to ensure the continued airworthiness of 

these helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

65 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. At an average labor rate of $85 

per hour, inspecting the seats will 

require about .2 work-hour, for a cost 

per helicopter of $17 and a total cost to 

U.S. operators of $1,105. Replacing a 

seat with a missing weld bead will 

require about 1 work-hour, and required 

parts will cost about $30,251, for a cost 

per helicopter of $30,336. 

According to Eurocopter’s service 

information some of the costs of this AD 

may be covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage by Eurocopter. Accordingly, 

we have included all costs in our cost 

estimate. 

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 


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Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 60683 

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 

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): 

2013–19–07 Eurocopter France 

(Eurocopter): Amendment 39–17589; 

Docket No. FAA–2013–0480; Directorate 

Identifier 2012–SW–090–AD. 

(a) Applicability 

This AD applies to Eurocopter Model SA– 

365N, SA–365N1, AS–365N2, AS 365 N3, EC 

155B, EC155B1, AS332C, AS332L, AS332L1, 

AS332L2, and EC225LP helicopters with an 

EADS Sogerma pilot or co-pilot seat, part 

number (P/N) 2510106–03–00 or P/N 

2510106–06–00, with a serial number 720 

through 1451, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

missing weld on a seat rear beam, which 

could result in failure of the seat and injury 

to the pilot during a hard landing. 

(c) Effective Date 

This AD becomes effective November 6, 

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 50 hours time-in-service, using 

a mirror, inspect the rear beam of each seat 

for weld beads in the areas depicted in the 

Appendix, Figure 1, of Eurocopter Alert 

Service Bulletin (ASB) No. AS365–25.01.18 

for model SA–365N, SA–365N1, AS–365N2, 

and AS 365 N3 helicopters; ASB No. EC155– 

25A114 for model EC155 B and EC155B1 

helicopters; ASB No. AS332–25.02.49 for 

model AS332C, AS332L, AS332L1, and 

AS332 L2 helicopters; and ASB No. EC225– 

25A110 for model EC225LP helicopters. All 

ASBs are Revision 1 and dated August 9, 

2012. 

(2) If any weld bead is missing from the 

rear beam, before further flight, remove the 

seat and replace it with an airworthy seat. 

(3) Do not install a seat listed in paragraph 

(a) of this AD on any helicopter unless it has 

been inspected as required by this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone 817–222– 

5110; email robert.grant@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. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2012–0206, dated October 2, 2012. You 

may view the EASA AD on the internet in 

the AD Docket at http://www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2510: Flight Compartment Equipment. 

(i) 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 ASB No. AS365–25.01.18, 

Revision 1, dated August 9, 2012. 

(ii) Eurocopter ASB No. AS332–25.02.49 

Revision 1, dated August 9, 2012. 

(iii) Eurocopter ASB No. EC155–25A114, 

Revision 1, dated August 9, 2012. 

(iv) Eurocopter ASB No. EC225–25A110 

Revision 1, dated August 9, 2012. 

(3) For Eurocopter 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. 

(4) You may view this service information 

that is incorporated by reference at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(5) You may also 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 September 

13, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23092 Filed 10–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2013–0275; Airspace 

Docket No. 13–AGL–15]; 

Amendment of Class E Airspace; 

Mandan, ND 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends Class E 

airspace at Mandan, ND. Additional 

controlled airspace is necessary to 

accommodate new Area Navigation 

(RNAV) Standard Instrument Approach 


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