59568 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Rules and Regulations 

* * * * * 

(iii) For information on rules 

pertaining to the charges associated 

with employees of U.S. Customs and 

Border Protection performing 

agricultural inspection services, please 

see 7 CFR 354.1 and 9 CFR 97.1. 

* * * * * 

Done in Washington, DC, this 28th day of 

September 2015. 

Kevin Shea, 

Administrator, Animal and Plant Health 

Inspection Service. 

[FR Doc. 2015–25101 Filed 10–1–15; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0493; Directorate 

Identifier 2014–NM–184–AD; Amendment 

39–18283; AD 2015–20–05] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model 

188 series airplanes. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the upper and lower 

wing skin planks at the attachment of 

the main landing gear (MLG) ribs at 

certain wing-stations are subject to 

widespread fatigue damage (WFD). This 

AD requires an inspection (for cracking) 

and modification of the chordwise 

fastener rows of the upper and lower 

wing planks at the attachments to the 

MLG ribs at certain wing-stations. We 

are issuing this AD to prevent fatigue 

cracking of the upper and lower wing 

skin planks at the attachment of the 

MLG ribs, which could result in failure 

of the wing. 

DATES: This AD is effective November 6, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 6, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, GA 

30063; telephone 770–494–5444; fax 

770–494–5445; email ams.portal@

lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. You may view this 

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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–0493. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0493; 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 

Docket 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: Carl 

Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, GA 

30337; phone: 404–474–5554; fax: 404– 

474–5605; email: Carl.W.Gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Lockheed Martin 

Corporation/Lockheed Martin 

Aeronautics Company Model 188 series 

airplanes. The NPRM published in the 

Federal Register on March 24, 2015 (80 

FR 15525). The NPRM was prompted by 

an evaluation by the DAH indicating 

that the upper and lower wing skin 

planks at the attachment of the MLG 

ribs at certain wing-stations are subject 

to WFD. The NPRM proposed to require 

an inspection (for cracking) and 

modification of the chordwise fastener 

rows of the upper and lower wing 

planks at the attachments to the MLG 

ribs at certain wing-stations. We are 

issuing this AD to prevent fatigue 

cracking of the upper and lower wing 

skin planks at the attachment of the 

MLG ribs, which could result in failure 

of the wing. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 15525, March 24, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

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 (80 FR 

15525, March 24, 2015) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 15525, 

March 24, 2015). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Lockheed Martin Electra 

Service Bulletin 88/SB–721, dated April 

30, 2014. This service information 

describes procedures for doing a bolthole eddy current (BHEC) inspection for 

cracking and repair of cracking. This 

service information also describes 

procedures for modification of the 

chordwise fastener rows of the upper 

and lower wing planks at the 

attachments to the MLG ribs at wingstation (WS) 167 and WS 209 by 

removing the original fasteners and 

replacing them with new first oversize 

fasteners of the same type or approved 

substitute type for original fasteners. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 4 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Rules and Regulations 59569 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection and Modification ............................ 560 work-hours × $85 per hour = $47,600 .... $5,000 $52,600 $210,400 

We have received no definitive data 

that will enable us to provide cost 

estimates 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 

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): 

2015–20–05 Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company: 

Amendment 39–18283; Docket No. 

FAA–2015–0493; Directorate Identifier 

2014–NM–184–AD. 

(a) Effective Date 

This AD is effective November 6, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company Model 188A and 188C airplanes, 

certificated in any category, serial numbers 

1001 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the upper and lower wing skin planks at the 

attachment of the main landing gear (MLG) 

ribs at certain wing-stations are subject to 

widespread fatigue damage. We are issuing 

this AD to prevent fatigue cracking of the 

upper and lower wing skin planks at the 

attachment of the MLG ribs, which could 

result in failure of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection, Modification, and Corrective 

Action 

At the later of the times specified in 

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

Remove the chordwise fastener rows of the 

upper and lower wing planks at the 

attachments to the MLG ribs at wing-station 

(WS) 167 and WS 209; do a bolt-hole eddy 

current (BHEC) inspection to detect cracking 

of the fastener rows; and replace the original 

fasteners with new, first oversize fasteners; in 

accordance with the Accomplishment 

Instructions of Lockheed Martin Electra 

Service Bulletin 88/SB–721, dated April 30, 

2014. If any cracking is found during any 

inspection required by this paragraph: Before 

further flight, repair the cracking, in 

accordance with the Accomplishment 

Instructions of Lockheed Martin Electra 

Service Bulletin 88/SB–721, dated April 30, 

2014. 

(1) At the applicable time specified table 1 

of paragraph 1.E., ‘‘Compliance,’’ of 

Lockheed Martin Electra Service Bulletin 88/ 

SB–721, dated April 30, 2014. Where table 1 

of paragraph 1.E., ‘‘Compliance,’’ of 

Lockheed Martin Electra Service Bulletin 88/ 

SB–721, dated April 30, 2014, specifies ‘‘Flt. 

Hrs,’’ this AD specifies ‘‘total flight hours.’’ 

(2) Within 365 days or 600 flight hours 

after the effective date of this AD, whichever 

occurs first. 

(h) No Reporting 

Although Lockheed Martin Electra Service 

Bulletin 88/SB–721, dated April 30, 2014, 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 (j) 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. 

(j) Related Information 

For more information about this AD, 

contact Carl Gray, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, Atlanta 

ACO, 1701 Columbia Avenue, College Park, 

GA 30337; phone: 404–474–5554; fax: 404– 

474–5605; email: carl.w.gray@faa.gov. 

(k) 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) Lockheed Martin Electra Service 

Bulletin 88/SB–721, dated April 30, 2014. 


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59570 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Rules and Regulations 

(ii) Reserved. 

(3) For Lockheed service information 

identified in this AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness Office, 

Dept. 6A0M, Zone 0252, Column P–58, 86 S. 

Cobb Drive, Marietta, GA 30063; telephone 

770–494–5444; fax 770–494–5445; email 

ams.portal@lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. 

(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 18, 2015. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–24839 Filed 10–1–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0128; Directorate 

Identifier 2013–NM–133–AD; Amendment 

39–18278; AD 2015–19–16] 

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 The 

Boeing Company Model 777 airplanes 

equipped with Rolls-Royce Trent 800 

series engines. This AD was prompted 

by reports of in-flight separation of the 

engine’s aft plug from the forward plug, 

which are the two parts of the turbine 

exhaust plug assembly. This AD 

requires installation of a serviceable 

turbine exhaust plug assembly (for 

certain airplanes), and a general visual 

inspection (for certain airplanes) to 

determine the diameter of the bolt used 

at the forward and aft plug interface, 

and applicable corrective actions. We 

are issuing this AD to prevent 

separation of the aft plug from the 

forward plug of the turbine exhaust plug 

assembly, which could result in parts 

departing the airplane and hitting the 

empennage, and destabilizing the 

airplane during a critical flight phase. In 

addition, parts remaining on a runway 

could pose a hazard to another airplane. 

DATES: This AD is effective November 6, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 6, 2015. 

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 view 

this 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0128. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0128; 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 

Docket 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: 

Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6501; 

fax: 425–917–6590; email: 

kevin.nguyen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to The Boeing Company Model 

777 airplanes equipped with RollsRoyce Trent 800 series engines. The 

NPRM published in the Federal 

Register on March 3, 2014 (79 FR 

11725); corrected March 11, 2014 (79 FR 

13592). The NPRM was prompted by 

reports of in-flight separation of the 

engine’s aft plug from the forward plug, 

which are the two parts of the turbine 

exhaust plug assembly. The NPRM 

proposed to require installation of a 

serviceable turbine exhaust plug 

assembly (for certain airplanes), and a 

general visual inspection (for certain 

airplanes) to determine the diameter of 

the bolt used at the forward and aft plug 

interface, and applicable corrective 

actions. We are issuing this AD to 

prevent separation of the aft plug from 

the forward plug of the turbine exhaust 

plug assembly, which could result in 

parts departing the airplane and hitting 

the empennage, and destabilizing the 

airplane during a critical flight phase. In 

addition, parts remaining on a runway 

could pose a hazard to another airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 11725, 

March 3, 2014; corrected March 11, 

2014 (79 FR 13592); and the FAA’s 

response to each comment. 

Request To Match Compliance Time 

Cathay Pacific requested that we 

ensure that the AD compliance date will 

be the same as the compliance time of 

Boeing Special Attention Service 

Bulletin 777–78–0051, Revision 3, dated 

August 23, 2012; or Boeing Special 

Attention Service Bulletin 777–78– 

0051, Revision 4, dated February 7, 

2014. Cathay Pacific reasoned that 

paragraph (i) of the proposed AD 

specified compliance within 60 months 

after the effective date of the proposed 

AD, and both revisions of this service 

information specify a compliance time 

that is within 60 months after the 

Revision 3 date of the service bulletin. 

We infer that Cathay Pacific is 

requesting that we reduce the 

compliance time of this final rule to 

match the compliance time listed in the 

service information. We do not agree 

with the commenter’s request. In 

developing an appropriate compliance 

time for this action, we considered not 

only the degree of urgency associated 

with addressing the subject unsafe 

condition, but the manufacturer’s 

recommendation for an appropriate 

compliance time, the time required for 

the rulemaking process, the availability 

of required parts, and the practical 

aspect of installing the required 

modification within an interval of time 

that corresponds to the typical 

scheduled maintenance for the majority 

of affected operators. Under the 

provisions of paragraph (l) of this AD, 


asabaliauskas on DSK5VPTVN1PROD with RULES