Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations 45851 

determination as to whether a conflict of 

interest exists. 

[FR Doc. 2015–18642 Filed 7–31–15; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0826; Directorate 

Identifier 2014–NM–221–AD; Amendment 

39–18222; AD 2015–15–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A318, A319, and A320 

series airplanes modified by a particular 

supplemental type certificate (STC). 

This AD was prompted by reports of 

cracks found during inspections of the 

in-flight entertainment system radome 

assembly. This AD requires repetitive 

detailed inspections for cracks in the 

radome assembly, and replacement of 

the radome if necessary. We are issuing 

this AD to detect and correct cracks in 

the radome assembly, which could 

result in the radome (or pieces) 

separating from the airplane and 

striking the tail, consequently reducing 

the controllability of the airplane. 

DATES: This AD is effective September 8, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 8, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Live TV, 

7415 Emerald Dunes Drive, Orlando, FL 

32822; telephone 407–812–2643; email: 

CertificationEngineering@livetv.net; 

Internet: http://www.LiveTV.net. 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– 

0826. 

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– 

0826; 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: 

Barry Culler, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, 

Atlanta Aircraft Certification Office 

(ACO), 1701 Columbia Avenue, College 

Park, GA 30337; phone: 404–474–5546; 

fax: 404–474–5605; email: 

william.culler@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 Airbus Model A318, 

A319, and A320 series airplanes 

modified by a particular STC. The 

NPRM published in the Federal 

Register on April 15, 2015 (80 FR 

20175). The NPRM was prompted by 

reports of cracks found during 

inspections of the in-flight 

entertainment system radome assembly 

that had in-flight entertainment systems 

installed using an STC issued to Live 

TV (STC ST00788SE, http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

6df40775b10ef09a86257ae200613cfe/

$FILE/ST00788SE.pdf). Investigation of 

the cause of the cracks revealed that 

radome manufacturing variation, due to 

a lack of dimensional controls on the 

radome manufacturing drawings, can 

result in the introduction of preload 

stress on the radome during its assembly 

with the skirt fairing. Preload stress 

combined with flight or handling stress, 

such as maintenance personnel stepping 

on the radome fairing assembly, might 

initiate a crack. The radome 

manufacturing drawings were revised 

on September 13, 2010, to add a control 

dimension, which was incorporated into 

production at radome serial number 

498. The NPRM proposed to require 

detailed inspections for cracks in the 

radome assembly, and replacement of 

the radome if necessary. We are issuing 

this AD to detect and correct cracks in 

the radome assembly, which could 

result in the radome (or pieces) 

separating from the airplane and 

striking the tail, consequently reducing 

the controllability of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 20175, April 15, 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 

20175, April 15, 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 20175, 

April 15, 2015). 

Related Service Information Under 

1 CFR Part 51 

We reviewed Live TV Service Bulletin 

A320–53–006, Rev 01, dated September 

10, 2014. The service information 

describes procedures for repetitive 

detailed inspections for cracks in the 

outer ply of the radome, and 

replacement of the radome with a new 

or serviceable radome if any crack is 

found. 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 120 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

mstockstill on DSK4VPTVN1PROD with RULES

45852 Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations 

ESTIMATED COSTS

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

Inspections ........ 1 work-hour × $85 per hour = $85 per inspection 

cycle.

N/A $85 per inspection cycle $10,200 per inspection 

cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspections. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .................................... 8 work-hours × $85 per hour = $ 680 ....................................................... $0 $680 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 

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): 

2015–15–12 Airbus: Amendment 39–18222; 

Docket No. FAA–2015–0826; Directorate 

Identifier 2014–NM–221–AD. 

(a) Effective Date 

This AD is effective September 8, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplane models 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category, 

with Live TV radomes having part number 

(P/N) 5063–100–XX (XX designates the color 

option) and a serial number in the range of 

001 through 497 inclusive, and modified by 

supplemental type certificate (STC) 

ST00788SE, http://rgl.faa.gov/Regulatory_

and_Guidance_Library/rgstc.nsf/0/ 

6df40775b10ef09a86257ae200613cfe/$FILE/

ST00788SE.pdf. 

(1) Airbus Model A318–111 and –112 

airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–111, –211, –212, 

–214, –231, –232, and –233 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found during inspections of the in-flight 

entertainment system radome assembly. We 

are issuing this AD to detect and correct 

cracks in the in-flight entertainment system 

radome assembly, which could result in the 

radome (or pieces) separating from the 

airplane and striking the tail, consequently 

reducing the controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Corrective 

Actions 

Within 3,900 flight hours after the effective 

date of this AD: Perform a detailed inspection 

for cracks of the radome assembly, in 

accordance with the Accomplishment 

Instructions of Live TV Service Bulletin 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations 45853 

A320–53–006, Rev 01, dated September 10, 

2014. Repeat the inspection thereafter at 

intervals not to exceed 3,900 flight hours. If 

any crack is found during any inspection 

required by this paragraph, before further 

flight, replace the radome with a new or 

serviceable radome, in accordance with the 

Accomplishment Instructions of Live TV 

Service Bulletin A320–53–006, Rev 01, dated 

September 10, 2014. 

(h) Reporting Requirement 

If any crack is found during any inspection 

required by paragraph (g) of this AD, submit 

a report of the findings to Live TV, Attn: 

Oscar Hernandez, email: 

CertificationEngineering@livetv.net; at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD. The report must include 

the information specified in the service 

bulletin reporting form provided in Live TV 

Service Bulletin A320–53–006, Rev 01, dated 

September 10, 2014. 

(1) If the inspection was accomplished on 

or after the effective date of this AD: Submit 

the report within 30 days after the 

inspection. 

(2) If the inspection was accomplished 

before the effective date of this AD: Submit 

the report within 30 days after the effective 

date of this AD. 

(i) Special Flight Permit 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(j) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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. 

(3) If any service information contains 

steps that are identified as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

identified as RC are recommended. Those 

steps that are not identified as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the steps 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to steps 

identified as RC require approval of an 

AMOC. 

(l) Related Information 

For more information about this AD, 

contact Barry Culler, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, GA 30337; 

phone: 404–474–5546; fax: 404 474 5605; 

email: william.culler@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 the AD specifies otherwise. 

(i) Live TV Service Bulletin A320–53–006, 

Rev 01, dated September 10, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Live TV, 7415 Emerald 

Dunes Drive, Orlando, FL 32822; telephone 

407–812–2643; email: 

CertificationEngineering@livetv.net; Internet: 

http://www.LiveTV.net. 

(4) 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. 

(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 July 17, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18535 Filed 7–31–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0348; Directorate 

Identifier 2014–NM–033–AD; Amendment 

39–18225; AD 2015–15–15] 

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 777–200, 

777–200LR, 777–300ER, and 777F series 

airplanes. This AD was prompted by a 

report indicating that sealant might not 

have been applied in production to the 

wing skin panel gaps above certain 

underwing fittings. This AD would 

require an inspection for missing 

sealant, and applicable other specified, 

related investigative, and corrective 

actions. We are proposing this AD to 

detect and correct missing sealant from 

the wing skin panel gaps above the 

underwing fittings, which could result 

in corrosion and fatigue cracking in the 

wing skin panel, and consequent loss of 

limit load capability of the wing skin 

and potential subsequent structural 

failure of the wings. 

DATES: This AD is effective September 8, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 8, 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– 

0348. 

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– 

mstockstill on DSK4VPTVN1PROD with RULES