49910 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations 

autopilot control panel and the center switch 

panel. We are issuing this AD to prevent 

failure of the hardware/software combination 

within the autopilot control panel and/or 

center switch panel, which could result in 

uncommanded fire suppression system 

activation and simultaneous shutdown of 

both engines. 

(f) Compliance 

Unless already done, do the following 

actions within the compliance times 

specified in paragraph (g) of this AD. 

(g) Update Aircraft Computer Software 

(ACS) 

(1) For airplanes equipped with Avio or 

Avio with ETT avionics suites: Within 6 

calendar months after September 20, 2013 

(the effective date of this AD), update the 

ACS following paragraphs 3.A. through 3.C. 

of the Accomplishment Instructions in 

Eclipse Aerospace, Inc. Mandatory Service 

Bulletin Number SB 500–31–014, Rev. A, 

dated February 15, 2011. 

(2) For airplanes equipped with NG 1.0 

avionics suites: Within 6 calendar months 

after September 20, 2013 (the effective date 

of this AD), do one of the following: 

(i) Insert Temporary Revision No. 016, to 

EA500 POH and FAA-Approved Airplane 

Flight Manual, Firewall Valve, 06–122204– 

TR016, issued November 9, 2012, into the 

Limitations section of the airplane flight 

manual following paragraph 3.B.(1)(a) of the 

Accomplishment Instructions in Eclipse 

Aerospace, Inc. Mandatory Service Bulletin 

Number SB 500–31–026, Rev. A, dated 

December 7, 2012, or Eclipse Aerospace, Inc. 

Mandatory Service Bulletin Number SB 500– 

31–026, Rev. B, dated March 27, 2013; or 

(ii) Update the ACS following paragraphs 

3.A. through 3.C. of the Accomplishment 

Instructions in Eclipse Aerospace, Inc. 

Mandatory Service Bulletin Number SB 500– 

31–019, Rev. B, dated March 13, 2013. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Chicago 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 the 

Related Information section 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. 

(i) Related Information 

For more information about this AD, 

contact Scott Fohrman, Aerospace Engineer, 

FAA, Chicago ACO, 2300 East Devon 

Avenue, Room 107, Des Plaines, Illinois 

60018; phone: (847) 294–7136; fax: (847) 

294–7834; email: scott.fohrman@faa.gov. 

(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) Eclipse Aerospace, Inc. Mandatory 

Service Bulletin Number SB 500–31–014, 

Rev. A, dated February 15, 2011. 

(ii) Eclipse Aerospace, Inc. Mandatory 

Service Bulletin Number SB 500–31–019, 

Rev. B, dated March 13, 2013. 

(iii) Eclipse Aerospace, Inc. Mandatory 

Service Bulletin Number SB 500–31–026, 

Rev. A, dated December 7, 2012. 

(iv) Eclipse Aerospace, Inc. Mandatory 

Service Bulletin Number SB 500–31–026, 

Rev. B, dated March 27, 2013. 

(v) Temporary Revision No. 016, to EA500 

POH and FAA-Approved Airplane Flight 

Manual, Firewall Valve, 06–122204–TR016, 

issued November 9, 2012. 

(3) For Eclipse Aerospace, Inc. service 

information identified in this AD, contact 

Eclipse Aerospace, Inc. 26 East Palatine 

Road, Wheeling, Illinois 60090; telephone: 

(877) 373–7978; Internet: www.eclipse.aero. 

(4) You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on July 31, 

2013. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–18912 Filed 8–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0207; Directorate 

Identifier 2011–NM–071–AD; Amendment 

39–17530; AD 2013–15–14] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2008–06– 

29, which applied to all The Boeing 

Company Model 737–300, –400, and 

–500 series airplanes. AD 2008–06–29 

required repetitive inspections of the 

downstop assemblies on the main tracks 

of the No. 2, 3, 4, and No. 5 slats and 

the inboard track of the No. 1 and 6 slats 

to verify if any parts are missing, 

damaged, or in the wrong order; other 

specified actions; and related 

investigative and corrective actions if 

necessary. This new AD retains these 

requirements and adds an inspection of 

the slat can interior for foreign object 

debris (FOD), and removal of any FOD 

found; modification of the slat track 

hardware; an inspection for FOD and for 

damage to the interior surface of the slat 

cans; and related investigative and 

corrective actions, if necessary. This AD 

was prompted by development of a 

modification by the manufacturer, 

which, when installed, would terminate 

the repetitive inspections. We are 

issuing this AD to prevent loose or 

missing parts in the main slat track 

downstop assemblies, which could 

puncture the slat track housing and 

result in a fuel leak and consequent fire. 

DATES: This AD is effective September 

20, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 20, 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, Washington 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, Washington. 

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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations 49911 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6440; fax: (425) 917–6590; email: 

nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–06–29, 

Amendment 39–15441 (73 FR 15397, 

March 24, 2008) (‘‘AD 2008–06–29’’). 

AD 2008–06–29 applied to the specified 

products. The NPRM published in the 

Federal Register on March 11, 2013 (78 

FR 15332). The NPRM proposed to 

continue to require repetitive 

inspections of the downstop assemblies 

on the main tracks of the No. 2, 3, 4, and 

No. 5 slats and the inboard track of the 

No. 1 and 6 slats to verify if any parts 

are missing, damaged, or in the wrong 

order; other specified actions; and 

related investigative and corrective 

actions if necessary. The NPRM also 

proposed to add an inspection of the 

slat can interior for foreign object debris 

(FOD), and removal of any FOD found; 

modification of the slat track hardware; 

an inspection for FOD and for damage 

to the interior surface of the slat cans; 

and related investigative and corrective 

actions, if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 15332, 

March 11, 2013) and the FAA’s response 

to each comment. 

Concurrence With NPRM (78 FR 15332, 

March 11, 2013) 

Boeing stated that it concurs with the 

content of the proposed rule (78 FR 

15332, March 11, 2013). 

Statement Regarding Installation of 

Winglets 

Aviation Partners Boeing (APB) stated 

that the installation of winglets per STC 

ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/2C6E3DBDDD36F91C8

62576A4005D64E2?OpenDocument&

Highlight=st01219se) does not affect the 

actions specified in the NPRM (78 FR 

15332, March 11, 2013). 

We concur. We have added new 

paragraph (c)(2) to this AD, which states 

that STC ST01219SE (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/

rgstc.nsf/0/2C6E3DBDDD36F91C8625

76A4005D64E2?OpenDocument&

Highlight=st01219se) does not affect the 

ability to accomplish the actions 

required by this AD. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ‘‘change in product’’ 

alternative method of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of Section 39.17 of the 

Federal Aviation Regulations (14 CFR 

39.17). For all other AMOC requests, the 

operator must request approval of an 

AMOC in accordance with the 

procedures specified in paragraph (k) of 

this AD. 

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 change described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

15332, March 11, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 15332, 

March 11, 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 568 

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 

Inspection of slat track housing [retained actions from AD 2008–06–29 (73 FR 15397, 

March 24, 2008)].

4 work-hours × $85 per hour = $340 per inspection cycle.$0 $340 $193,120 

One-time detailed inspection of slat can [new 

action].

5 work-hours × $85 per hour = $85 ............... 0 425 241,400 

Installation of modification [new action] .......... 12 work-hours × $85 per hour = $1,020 ........ 3,124 4,144 2,353,792 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this AD. 

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 have 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 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. 


tkelley on DSK3SPTVN1PROD with RULES
49912 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations 

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) 

2008–06–29, Amendment 39–15441 (73 

FR 15397, March 24, 2008), and adding 

the following new AD: 

2013–15–14 The Boeing Company: 

Amendment 39–17530; Docket No. 

FAA–2013–0207; Directorate Identifier 

2011–NM–071–AD. 

(a) Effective Date 

This AD is effective September 20, 2013. 

(b) Affected ADs 

This AD supersedes AD 2008–06–29, 

Amendment 39–15441 (73 FR 15397, March 

24, 2008). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–300, –400, and –500 

series airplanes, certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://rgl.

faa.gov/Regulatory_and_Guidance_Library/

rgstc.nsf/0/2C6E3DBDDD36F91C862576A40

05D64E2?OpenDocument&Highlight=

st01219se) does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST01219SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57: Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of fuel 

leaking from a puncture in the slat track 

housing (referred to as ‘‘slat can’’). We are 

issuing this AD to prevent loose or missing 

parts in the main slat track downstop 

assemblies, which could puncture the slat 

track housing and result in a fuel leak and 

consequent fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection of Downstop 

Assemblies and Corrective Action 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–06–29, Amendment 

39–15441 (73 FR 15397, March 24, 2008), 

with revised service information. At the 

applicable times specified in Table 1 of 

paragraph 1.E. of Boeing Alert Service 

Bulletin 737–57A1301, dated February 5, 

2008; or Boeing Service Bulletin 737– 

57A1301, Revision 3, dated August 11, 2011; 

except as provided by paragraph (g)(1) of this 

AD: Do a detailed inspection or borescope 

inspection of the downstop assemblies on the 

main tracks of the No. 2, 3, 4, and 5 slats and 

the inboard track of the No. 1 and 6 slats to 

verify if any parts are missing, damaged, or 

installed in the wrong order; and do all the 

other specified, related investigative, and 

corrective actions as applicable; by 

accomplishing all of the applicable actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1301, dated February 5, 2008; or 

Boeing Service Bulletin 737–57A1301, 

Revision 3, dated August 11, 2011; except as 

provided by paragraphs (g)(2) and (g)(3) of 

this AD. Repeat the inspection thereafter at 

the applicable times specified in Table 1 of 

paragraph 1.E. of Boeing Alert Service 

Bulletin 737–57A1301, dated February 5, 

2008; or Boeing Service Bulletin 737– 

57A1301, Revision 3, dated August 11, 2011. 

Do all applicable related investigative and 

corrective actions before further flight. As of 

the effective date of this AD, only Boeing 

Service Bulletin 737–57A1301, Revision 3, 

dated August 11, 2011, may be used to 

accomplish the actions required by this 

paragraph. 

(1) Where Boeing Alert Service Bulletin 

737–57A1301, dated February 5, 2008, or 

Boeing Service Bulletin 737–57A1301, 

Revision 3, dated August 11, 2011, specifies 

counting the compliance time from ‘‘the date 

on the service bulletin,’’ this AD requires 

counting the compliance time from April 8, 

2008 (the effective date of AD 2008–06–29, 

Amendment 39–15441 (73 FR 15397, March 

24, 2008)). 

(2) For airplanes on which any downstop 

assembly part is missing or damaged, a 

borescope inspection of the inside of the slat 

track housing for loose parts and damage to 

the wall of the slat track housing may be 

accomplished in lieu of the detailed 

inspection of the inside of the slat track 

housing that is specified in Boeing Alert 

Service Bulletin 737–57A1301, dated 

February 5, 2008; or Boeing Service Bulletin 

737–57A1301, Revision 3, dated August 11, 

2011. As of the effective date of this AD, only 

Boeing Service Bulletin 737–57A1301, 

Revision 3, dated August 11, 2011, may be 

used to do the actions specified in this 

paragraph. 

(3) If any damaged slat track housing is 

found during any inspection required by 

paragraph (g) of this AD: Before further flight, 

repair in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–57A1301, Revision 3, 

dated August 11, 2011; replace the slat can 

with a new slat can having the same part 

number, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–57A1301, Revision 3, 

dated August 11, 2011; or repair the slat can 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(h) New Detailed Inspection for Foreign 

Object Debris (FOD) 

Within 24 months after the effective date 

of this AD, do a one-time detailed inspection 

of the slat can interior to detect FOD, in 

accordance with Part III of the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–57A1301, Revision 3, 

dated August 11, 2011. If any FOD is found, 

before further flight, remove it, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 737–57A1301, 

Revision 3, dated August 11, 2011. 

(i) New Modification and Inspection 

Within 72 months or 15,000 flight cycles, 

whichever occurs first, after the effective date 

of this AD: Modify the slat track hardware by 

installing new downstop assembly hardware, 

and do a detailed inspection for FOD and a 

one-time inspection for damage to the 

interior surface of the slat can for the inboard 

and outboard tracks of slats 2 through 5, and 

the inboard slats of tracks 1 and 6; and do 

all applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–57A1301, Revision 3, 

dated August 11, 2011. Do all applicable 

related investigative and corrective actions 

before further flight. Accomplishment of the 

actions required by this paragraph terminates 

the inspections required by paragraphs (g) 

and (h) of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), and 

(i) of this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 737–57A1301, 

Revision 1, dated September 24, 2009; or 

Boeing Alert Service Bulletin 737–57A1301, 

Revision 2, dated January 17, 2011; which are 

not incorporated by reference in this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations 49913 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2008–06–29, 

Amendment 39–15441 (73 FR 15397, March 

24, 2008), are approved as AMOCs for the 

corresponding provisions of this AD. 

(l) Related Information 

For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6440; fax: (425) 917–6590; 

email: nancy.marsh@faa.gov. 

(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 this AD specifies otherwise. 

(i) Boeing Service Bulletin 737–57A1301, 

Revision 3, dated August 11, 2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 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, Washington. 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/ibr-locations.html. 

Issued in Renton, Washington, on July 21, 

2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19811 Filed 8–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0362; Directorate 

Identifier 2013–NM–030–AD; Amendment 

39–17531; AD 2013–15–15] 

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 727 

airplanes. This AD was prompted by an 

evaluation by the design approval 

holder indicating that the frame-to-floor 

beam attachment is subject to 

widespread fatigue damage. This AD 

requires repetitive high frequency eddy 

current inspections for any crack of the 

frames at body station (STA) 188 

through STA 344, and repair if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking at the 

frame-to-floor beam attachment, on both 

the left- and right-sides, which could 

result in reduced structural integrity of 

the airplane, and decompression of the 

cabin. 

DATES: This AD is effective September 

20, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 20, 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, Washington 98057–3356. 

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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on May 3, 2013 (78 FR 25905). 

The NPRM proposed to require 

repetitive high frequency eddy current 

inspections for any crack of the frames 

at body STA 188 through STA 344, and 

repair if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Boeing stated that it supports the 

NPRM (78 FR 25905, May 3, 2013). 

Fedex stated that the NPRM (78 FR 

25905, May 3, 2013) will be effective for 

twenty of its Model 727–200 airplanes, 

the inspection threshold and intervals 

will fit within its planned scheduled 

maintenance checks and therefore will 

be no impact to available lift, the 

number of man-hours and elapsed time 

to accomplish the inspections will not 

impact the overall span-time of its 

planned scheduled maintenance check, 

and the inspections do not require any 

special inspection techniques, training, 

or tooling. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting thisAD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

25905, May 3, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 25905, 

May 3, 2013). 


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