41280 Federal Register / Vol. 78, No. 132 / Wednesday, July 10, 2013 / Rules and Regulations 

(4) In lieu of doing the modification 

required in paragraph (g)(3) of this AD, you 

may within the next 10 hours TIS after July 

10, 2013 (the effective date of this AD), do 

the fuel vent valve replacement required in 

paragraph (h)(1) of this AD following Part III 

of Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 1258, dated June 5, 2013. 

(h) Replacement 

(1) If during the inspection required in 

paragraph (g)(1) of this AD, you find that a 

nitrile (black) fuel vent valve is installed, 

within the next 90 days after July 10, 2013 

(the effective date of this AD) if not already 

done before further flight as specified in 

paragraph (i)(4) of this AD, replace the nitrile 

(black) fuel vent valve with the fluorosilicone 

(orange) fuel vent valve following Part III of 

Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 1258, dated June 5, 2013. This 

would include removing the limitations 

requirement in paragraphs 3 and 4 of Part II 

of the service bulletin. 

(2) You may at any time before 90 days 

after July 10, 2013 (the effective date of this 

AD), replace the nitrile (black) fuel vent valve 

with the flourosilicone (orange) fuel vent 

valve. This would include removing the 

limitations requirement in paragraphs 3 and 

4 of Part II of the service bulletin. 

(3) After July 10, 2013 (the effective date 

of this AD), do not install the nitrile (black) 

fuel vent valve on any of the affected 

airplanes. 

(i) Positioning Flight 

For the purpose of complying with 

paragraph (g)(1) of this AD, a singlepositioning flight is allowed to a location 

where the inspection required in paragraph 

(g)(1) can be done provided the actions and 

limitations specified in paragraphs (i)(1) 

through (i)(4) of this AD are followed, and 

the flight is done within the initial 10-hour 

TIS inspection compliance time. A copy of 

the limitations from paragraphs 3 and 4 of 

Part II of Piper Aircraft, Inc. Mandatory 

Service Bulletin No. 1258, dated June 5, 

2013, must be inserted in the pilot’s 

operating handbook before the positioning 

flight and removed after the flight. An owner/ 

operator (pilot) holding at least a private pilot 

certificate is allowed to insert these 

limitations and do the action of paragraph 

(i)(1) of this AD. 

(1) During normal procedures checklist of 

every preflight inspection, check condition of 

wing surface for buckling, skin wrinkling, 

distortion or other damage. If any damage is 

found during the preflight inspection, before 

further flight, repairs must be done. Contact 

Piper Aircraft, Inc. at contact information 

found in paragraph (l)(3) of this AD for an 

FAA-approved repair and incorporate the 

repair. At the operator’s discretion, this 

preflight inspection may be delegated to an 

appropriately certified mechanic. 

(2) Flights must be limited to the minimum 

required crew. No passenger flights are 

allowed. 

(3) Outside air temperature must not be 

lower than ¥34 degrees Celsius (¥30 

degrees Fahrenheit) during all phases of 

flight. 

(4) Avoid unnecessary rapid decent 

maneuvers. 

(j) 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. 

(k) Related Information 

For more information about this AD, 

contact Gary Wechsler, Aerospace Engineer, 

Atlanta ACO, FAA, 1701 Columbia Avenue, 

College Park, Georgia 30337; telephone: (404) 

474–5575; fax: (404) 474–5606; email: 

gary.wechsler@faa. 

(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) Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 1258, dated June 5, 2013. 

(ii) Reserved. 

(3) For Piper Aircraft, Inc. service 

information identified in this AD, contact 

Piper Aircraft, Inc., 2926 Piper Drive, Vero 

Beach, FL 32960; telephone: 1–877–879– 

0275; fax: (772) 978–6573; email: 

customer.service@piper.com; Internet: http:// 

www.piper.com/pages/publications.cfm. 

(4) You may view this service information 

at 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 June 

18, 2013. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–15149 Filed 7–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1039; Directorate 

Identifier 2011–NM–275–AD; Amendment 

39–17491; AD 2013–13–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A319–112, –113, and 

–132 airplanes; Model A320–211, –212, 

–214, –231, and –232 airplanes; and 

Model A321–111 and –131 airplanes. 

This AD was prompted by a report of 

two fatigue cracks on the left-hand and 

right-hand sides of the continuity 

fittings at the front windshield lower 

framing on a Model A319 series 

airplane. This AD requires a high 

frequency eddy current (HFEC) 

inspection for any cracking on the lefthand and right-hand sides of the 

windshield central lower node 

continuity fittings, and repair if 

necessary. We are issuing this AD to 

detect and correct cracking of the 

windshield central lower node 

continuity fittings, which could reduce 

the structural integrity of the airplane. 

DATES: This AD becomes effective 

August 14, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 14, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

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. That 


TKELLEY on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 132 / Wednesday, July 10, 2013 / Rules and Regulations 41281 

NPRM was published in the Federal 

Register on October 4, 2012 (77 FR 

60658). The European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2011–0231, 

dated December 9, 2011 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

One operator reported finding two fatigue 

cracks on continuity fittings at left-hand (LH) 

and right-hand (RH) sides at the front 

windshield lower framing on an A319 

aeroplane on which Airbus modification 

(mod.) 22058 had been embodied in 

production. Airbus mod. 22058 (which is 

included in Airbus mod. 21999) was 

introduced to improve the fatigue strength of 

the windshield front framing by increasing 

the thickness of framing flanges adjacent to 

the concerned fittings. 

Further analyses have demonstrated that 

the damage tolerance and fatigue 

requirements of JAR 25.571 (b) are not met 

on aeroplanes in post-mod. 22058 

configuration. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the affected aeroplanes. 

Required actions include an HFEC 

inspection for any cracking on the lefthand and right-hand sides of the 

windshield central lower node 

continuity fittings, and repair if 

necessary. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Revise HFEC Inspection 

Requirement 

Airbus requested that the one-time 

HFEC inspection in paragraph (g) of the 

NPRM (77 FR 60658, October 4, 2012) 

be revised in anticipation of further 

rulemaking by the EASA, which would 

mandate the airworthiness limitation 

inspection task and would correspond 

with the one-time HFEC inspection. 

We disagree with Airbus’s request. 

We have determined that publishing 

this final rule without any further delay 

is in the interest of safety of the flying 

public. However, we will consider 

additional AD rulemaking, if 

appropriate, in the future. We have not 

revised this final rule in this regard. 

Request for Approval of Repair 

Airbus requested consideration that 

each Airbus Repair Approval Sheet 

(RAS) be approved under ‘‘AIRBUS 

DOA EASA.21J.031,’’ provided that this 

is done after cracking is reported. 

Airbus stated that this would be an 

approved method for repair as required 

by paragraph (g) of the NPRM (77 FR 

60658, October 4, 2012). 

We agree. Airbus is an EASAdelegated agent; therefore, a RAS 

approved under Airbus Design 

Organization Approval (DOA) 

EASA.21J.031 would be a method of 

compliance for a repair required by this 

AD. We have not changed the final rule 

in this regard. 

Request To Update Address for the 

Manufacturer 

Airbus requested that the address for 

the manufacturer be updated. Airbus 

stated that in paragraph (k)(2) of the 

NPRM (77 FR 60658, October 4, 2012), 

‘‘EAS’’ should be replaced with ‘‘EIAS.’’ 

We agree with Airbus’s request to 

update the manufacturer’s address. 

Paragraphs (k)(2) and (l)(3) of this final 

rule have been updated accordingly. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously— 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

60658, October 4, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 60658, 

October 4, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

105 products of U.S. registry. We also 

estimate that it will take about 20 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $178,500, or $1,700 per product. 

We have received no definitive data 

that would 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 

We 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 the 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 the NPRM (77 FR 60658, 

October 4, 2012), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. 

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: 


TKELLEY on DSK3SPTVN1PROD with RULES
41282 Federal Register / Vol. 78, No. 132 / Wednesday, July 10, 2013 / Rules and Regulations 

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 AD: 

2013–13–03 Airbus: Amendment 39–17491. 

Docket No. FAA–2012–1039; Directorate 

Identifier 2011–NM–275–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective August 14, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A319– 

112, –113, and –132 airplanes; Model A320– 

211, –212, –214, –231, and –232 airplanes; 

and Model A321–111 and –131 airplanes; 

certificated in any category; manufacturer 

serial numbers 0259, 0260, 0264, 0266 

through 0270 inclusive, 0275, 0276, 0278, 

0287, 0296, 0300, 0303, 0312, 0320, 0321, 

0323, 0325, 0328, 0332, 0334, 0335, 0337, 

0346, 0352, 0353, 0356, 0365, 0369, 0375, 

0377, 0382, 0383, 0396, 0398, 0401, 0412, 

0413, 0416, 0419, 0421, 0431, 0432, 0438, 

0440, 0441, 0445, 0453, 0458, 0459, 0466, 

0468, 0473, 0474, 0482, 0484, 0491, 0493, 

0497, 0498, 0501, 0502, 0505, 0507, 0509, 

0518, 0520, 0521, 0529, 0531, 0534, 0537, 

0538, 0544, 0549, 0554, 0555, 0560, 0563, 

0577, 0578, 0585, 0598, 0600, 0608, 0612, 

0618, 0621, 0625, 0637, 0660, 0685, 0976, 

1010, 1092, 1096, 1103, 1139, 1143, 1158, 

1251, 1356, and 1511. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of two 

fatigue cracks on the left-hand and right-hand 

sides of the continuity fittings at the front 

windshield lower framing on a Model A319 

series airplane. We are issuing this AD to 

detect and correct cracking of the windshield 

central lower node continuity fittings, which 

could reduce the structural integrity of the 

airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection and Corrective Action 

Before the accumulation of 34,000 total 

flight cycles since the airplane’s first flight, 

or within 4,500 flight cycles after the 

effective date of this AD, whichever occurs 

later: Perform a high frequency eddy current 

(HFEC) inspection for any cracking on the 

left-hand and right-hand sides of the 

windshield central lower node continuity 

fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1245, Revision 01, 

including Appendix 1, dated May 17, 2011. 

If any cracking is found, before further flight, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

FAA, or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

(h) Reporting Requirement 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) of this AD to 

Airbus, Customer Service Directorate, Attn: 

SDC32 Technical Data and Documentation 

Services, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; fax +33 5 61 

93 28 06; email sb.reporting@airbus.com; at 

the applicable time specified in paragraph 

(h)(1) or (h)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–53–1245, including Appendix 

1, dated March 2, 2011, which is not 

incorporated by reference in this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: 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) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0231, dated December 9, 

2011, for related information. The MCAI may 

be viewed on the Internet at http:// 

ad.easa.europa.eu/blob/ 

easa_ad_2011_0231.pdf. 

(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) Airbus Service Bulletin A320–53–1245, 

Revision 01, including Appendix 1, dated 

May 17, 2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(4) You may review copies of the 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 June 14, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–15153 Filed 7–9–13; 8:45 am] 

BILLING CODE 4910–13–P 


TKELLEY on DSK3SPTVN1PROD with RULES