Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 60679 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

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

6483; fax: 425–917–6590; email: 

sarah.piccola@faa.gov. 

(2) For Goodrich service information 

identified in this AD, contact Goodrich 

Corporation, Aircraft Interior Products, 

ATTN: Technical Publications, 3414 South 

Fifth Street, Phoenix, AZ 85040–1169; 

telephone 602–243–2200; Internet http://

www.goodrich.com/TechPubs. 

(3) Boeing service information identified in 

this AD that is not incorporated by reference 

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 Special Attention Service 

Bulletin 747–25–3428, Revision 4, dated 

February 25, 2013. 

(ii) Boeing Service Bulletin 747–25–2425, 

Revision 1, dated September 7, 1979. (Pages 

1 through 4 of this document are dated 

September 7, 1979. Pages 5 through 20 of this 

document are dated August 25, 1978.) 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P. O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

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

5680; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 13, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24031 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–2012–0425; Directorate 

Identifier 2011–NM–273–AD; Amendment 

39–17604; AD 2013–19–22] 

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 all The 

Boeing Company Model 717–200 

airplanes. This AD was prompted by 

multiple reports of cracks of overwing 

frames. This AD requires repetitive 

inspections for cracking of the overwing 

frames, and corrective actions if 

necessary. 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. 

DATES: This AD is effective November 6, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 6, 2013. 

ADDRESSES: 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. 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 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued an SNPRM (supplemental 

notice of proposed rulemaking) to 

amend 14 CFR part 39 by adding an 

airworthiness directive (AD) that would 

apply to the specified products. The 

SNPRM published in the Federal 

Register on May 6, 2013 (78 FR 26286). 

We preceded the SNPRM with a notice 

of proposed rulemaking (NPRM) that 

published in the Federal Register on 

May 9, 2012 (77 FR 27142). The NPRM 

(77 FR 27142, May 9, 2012) proposed to 

require repetitive inspections for 

cracking of the overwing frames, and 

corrective actions if necessary. The 

SNPRM proposed to revise the initial 

compliance time and provide an 

optional modification that would extend 

the compliance time for the next 

repetitive inspection. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the SNPRM (78 FR 26286, 

May 6, 2013) and the FAA’s response to 

each comment. 

Request To Correct Service Bulletin 

Title 

Boeing noted an error in the title of a 

service bulletin referenced in 

paragraphs (h) and (h)(2) of the SNPRM 

(78 FR 26286, May 6, 2013). Boeing 

requested the word ‘‘Alert’’ be removed 

with reference to ‘‘Boeing ‘Alert’ Service 

Bulletin 717–53–0035, dated June 8, 

2012.’’ 

We agree with Boeing’s request. We 

have revised paragraphs (h) and (h)(2) of 

this final rule to correct the service 

bulletin title accordingly, since the 

referenced service bulletin is not an 

‘‘Alert’’ service bulletin. 

Request To Provide Credit for Previous 

Actions 

Boeing stated that cracked overwing 

frames had been found during 

scheduled inspections done in 

accordance with 717 Maintenance Task 

53–129–01, and that the frames were 

replaced as a consequence. Boeing 

requested that we revise the SNPRM (78 


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60680 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Rules and Regulations 

FR 26286, May 6, 2013) to allow credit 

for work done prior to the effective date 

of the SNPRM using 717 Maintenance 

Task 53–129–01. Boeing stated those 

new frames should be given the same 

credit as the frames that were replaced 

using Boeing Alert Service Bulletin 

717–53A0034, dated October 5, 2011. 

We disagree with the request to allow 

credit for frames replaced using 717 

Maintenance Task 53–129–01, which 

references the manufacturer’s original 

production drawing. Paragraph (i) of the 

SNPRM (78 FR 26286, May 6, 2013) was 

added to allow credit for work done 

prior to the effective date of this final 

rule using Boeing Alert Service Bulletin 

717–53A0034, dated October 5, 2011, 

which references Service Rework 

Drawing SR95530013. We disagree with 

changing this final rule because due to 

a large number of configurations, Boeing 

would be required to release numerous 

proprietary production drawings. 

However, operators may apply for 

approval of an alternative method of 

compliance (AMOC) (for credit for 

previously replaced frames) in 

accordance with the provisions of 

paragraph (j) of this AD. We have not 

changed this final rule in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (78 FR 

26286, May 6, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (78 FR 26286, 

May 6, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 129 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspections .................................... 46 work-hours × $85 per hour = 

$3,910 per inspection cycle.

$0 .............................. $3,910 ....................... $504,390. 

Installation of optional modification.30 work-hours × $85 per hour = 

$2,550 per inspection cycle.

Up to $2,727 ............. Up to $5,277 ............. Up to $680,733. 

We estimate the following costs to do 

any necessary replacements/repairs that 

would be required based on the results 

of the inspections. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Blendout repair ................................................. 12 work-hours × $85 per hour = $1,020 .......... $0 .............................. $1,020. 

Replacement of a frame station ....................... 130 work-hours × $85 per hour = $11,050 ...... Up to $86,977 ........... Up to $98,027. 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2013–19–22 The Boeing Company: 

Amendment 39–17604; Docket No. 

FAA–2012–0425; Directorate Identifier 

2011–NM–273–AD. 


sroberts on DSK5SPTVN1PROD with RULES
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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