71992 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations 

(2) Where Appendix B of Boeing Alert 

Service Bulletin 747–71A2329, dated 

September 27, 2013, states alternate 

instruments and transducers can be used, 

this AD requires that only equivalent 

instruments and transducers can be used. 

(3) Where Appendix A of Boeing Alert 

Service Bulletin 747–71A2329, dated 

September 27, 2013, states to record flight 

hours and flight cycles, record the flight 

hours and flight cycles on the airplane and 

the flight hours and flight cycles for each 

engine since change or removal. 

(i) Reporting and Sending Parts 

After any inspection required by paragraph 

(g) of this AD: Submit a report of the 

inspection results (both positive and 

negative), and return all cracked bolts and 

barrel nuts, at the applicable time specified 

in paragraph (i)(1) or (i)(2) of this AD. The 

report must include the information 

requested in Appendix A of Boeing Alert 

Service Bulletin 747–71A2329, dated 

September 27, 2013, except as required by 

paragraph (h)(3) of this AD. Both the report 

and all cracked bolts and barrel nuts must be 

sent to the address specified in Appendix A 

of Boeing Alert Service Bulletin 747– 

71A2329, dated September 27, 2013. 

(1) For airplanes on which an ultrasonic 

inspection was done and no cracking was 

found, do the required actions at the time 

specified in paragraph (i)(1)(i) or (i)(1)(ii) of 

this AD, as applicable. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 10 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 10 days after the effective date of this 

AD. 

(2) For airplanes on which a dye penetrant 

inspection was done, do the required actions 

at the time specified in paragraph (i)(2)(i) or 

(i)(2)(ii) of this AD, as applicable. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report and return all cracked bolts and barrel 

nuts within 10 days after replacing the bolts 

and barrel nuts with new or serviceable bolt 

and barrel nuts in accordance with Part 2 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–71A2329, dated 

September 27, 2013. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

and return all cracked bolts and barrel nuts 

within 10 days after the effective date of this 

AD. 

(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, 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 

paragraph (l) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 

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) If the service information contains steps 

that are labeled as ‘‘RC’’ (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as ‘‘RC’’ are recommended. Those 

steps that are not labeled as ‘‘RC’’ may be 

deviated from, done as part of other actions, 

or done using accepted methods different 

from those identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as ‘‘RC’’ 

can be done and the airplane can be put back 

in a serviceable condition. Any substitutions 

or changes to steps labeled as ‘‘RC’’ require 

approval of an AMOC. 

(l) Related Information 

For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6432; fax: (425) 917–6590; 

email: bill.ashforth@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) Boeing Alert Service Bulletin 747– 

71A2329, dated September 27, 2013. 

(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, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, 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/ibrlocations.html. 

Issued in Renton, Washington, on 

November 19, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–28616 Filed 11–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0698; Directorate 

Identifier 2012–NM–136–AD; Amendment 

39–17682; AD 2013–24–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2006–06– 

14 for certain Airbus Model A318–100 

and A319–100 series airplanes, A320– 

111 airplanes, A320–200 series 

airplanes, and A321–100 and A321–200 

series airplanes. AD 2006–06–14 

required operators to review the 

airplane’s maintenance records to 

determine the part numbers of the 

magnetic fuel level indicators (MFLIs) of 

the wing fuel tanks, and perform related 

investigative and corrective actions if 

necessary. This new AD also requires an 

inspection (improved method) to 

determine the part numbers of the 

MFLIs, and, if necessary, replacement of 

the MFLI or repair. This AD was 

prompted by information that the 

related investigative actions of AD 

2006–06–14 are not fully effective and 

that an affected MFLI could still be 

installed on airplanes on which the 


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related investigative actions were 

accomplished. We are issuing this AD to 

prevent an ignition source in the wing 

fuel tank in the event of a lightning 

strike, which could result in a fire or 

explosion. 

DATES: This AD becomes effective 

January 6, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 6, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 1, 2006 (71 FR 15023, 

March 27, 2006). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0698; 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 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. 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. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

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 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on August 20, 2013 (78 FR 

51117), and proposed to supersede AD 

2006–06–14, Amendment 39–14523 (71 

FR 15023, March 27, 2006). The NPRM 

proposed to correct an unsafe condition 

for the specified products. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0119, 

dated July 4, 2012 (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: 

In 2005, several in-service occurrences 

were reported of finding wear and/or 

detachment of the top stop of magnetic fuel 

level indicators (MFLI), either observed 

during tank maintenance activities, or on 

MFLI returned to the MFLI manufacturer. 

The investigation results indicated that the 

wear of the top stop retaining ‘S’ shaped wire 

had been caused by repetitive impact with 

the float, resulting in complete detachment of 

the top stop. 

This condition, if not detected and 

corrected, could lead an MFLI top stop to 

come into contact with a probe, which could, 

in the event of a lightning strike, create an 

ignition source in the fuel tank vapour space, 

possibly resulting in a fuel tank explosion 

and consequent loss of the aeroplane. 

DGAC France issued AD F–2005–108 

(EASA approval 2005–6026) [http://

ad.easa.europa.eu/ad/F-2005-108] 

[corresponding FAA AD 2006–06–14] to 

require identification (by inspection) and 

replacement of the affected metallic MFLI 

(3508802–xx series with the ‘S’ shaped 

retaining wire) with a metallic MFLI with the 

top stop retained by a ‘trapped wire’, or with 

a composite MFLI. 

Since that [French] AD was issued, it has 

been identified that the inspection procedure 

(visual check) detailed in Airbus Service 

Bulletin (SB) A320–28–1138 was not fully 

effective, and that affected MFLI could still 

be fitted on aeroplanes which have passed 

the inspection in accordance with the 

instructions of this SB. 

For the reasons described above, this 

[EASA] AD, which supersedes DGAC France 

AD F–2005–108, requires a one-time 

inspection (improved method) to identify the 

type of MFLI installed and, depending on 

findings, replacement or repair, as 

applicable. This [EASA] AD also prohibits 

the installation of the affected MFLI on any 

aeroplane as replacement parts. 

The repair may also include locating 

and removing any missing top stop, and 

inspecting for any damage caused to the 

fuel tank by a missing top stop. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0698- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 51117, August 20, 2013) or on the 

determination of the cost to the public. 

Change to ‘‘Applicability,’’ Paragraph 

(c) of This Final Rule 

We have removed Airbus Model 

A320–215 and A320–216 airplanes from 

paragraph (c) of this final rule. These 

airplane models are not listed on a U.S. 

type certificate data sheet (TCDS). If 

those airplane models are later 

certificated in the U.S. and listed on a 

U.S. TCDS, we may consider further 

action then. 

Conclusion 

We reviewed the available 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 (78 FR 

51117, August 20, 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 51117, 

August 20, 2013). 

Costs of Compliance 

We estimate that this AD affects 755 

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 

Part numbers review 

[retained actions 

from AD 2006–06– 

14, Amendment 

39-14523 (71 FR 

15023, March 27, 

2006)].

Between 1 and 8 work-hours × $85 per hour 

= Between $85 and $680.

None .......................... Between $85 and 

$680.

Between $64,175 and 

$513,400 


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ESTIMATED COSTS—Continued 

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

operators 

Inspection for part 

numbers [new action].

21 work-hours × $85 per hour = $1,785 ........ $0 ............................... $1,785 ........................ $1,347,675. 

We estimate the following costs to do 

any necessary replacement or repair that 

would be required based on the results 

of the inspection. We have no way of 

determining the number of aircraft that 

might need the replacement or repair: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement or repair ........................ 4 work-hours × $85 per hour = $340 ............................................................. $0 $340 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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. 

Examining the AD Docket 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0698- 

0002; 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 this AD, 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: 

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) 

2006–06–14, Amendment 39–14523 (71 

FR 15023, March 27, 2006), and adding 

the following new AD: 

2013–24–08 Airbus: Amendment 39–17682. 

Docket No. FAA–2013–0698; Directorate 

Identifier 2012–NM–136–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 6, 2014. 

(b) Affected ADs 

This AD supersedes AD 2006–06–14, 

Amendment 39–14523 (71 FR 15023, March 

27, 2006). 

(c) Applicability 

This AD applies to Airbus Model A318– 

111, A318–112, A318–121, A318–122, A319– 

111, A319–112, A319–113, A319–114, A319– 

115, A319–131, A319–132, A319–133, A320– 

111, A320–211, A320–212, A320–214, A320– 

231, A320–232, A320–233, A321–111, A321– 

112, A321–131, A321–211, A321–212, A321– 

213, A321–231, and A321–232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Reason 

This AD was prompted by a report of 

several in-service incidents of wear and 

detachment of the top-stops from magnetic 

fuel level indicators (MFLI) in a wing fuel 

tank. We are issuing this AD to prevent an 

ignition source in the wing fuel tank in the 

event of a lighting strike, which could result 

in a fire or explosion. 

(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) Retained Review of Airplane 

Maintenance Records/Investigative and 

Corrective Actions 

This paragraph restates the requirements of 

paragraph (f) of AD 2006–06–14, Amendment 

39–14523 (71 FR 15023, March 27, 2006). For 

Model A318–111 and –112 airplanes; Model 


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A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; A320–111 

airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; Model 

A321–111, –112, and –131 airplanes; and 

Model A321–211, –212, –213, –231, and –232 

airplanes; on which Airbus Modification 

27496 has not been installed in production: 

Within 65 months or 6,500 flight hours after 

May 1, 2006 (the effective date of AD 2006– 

06–14), whichever is first, review the 

airplane’s maintenance records to determine 

the part number (P/N) of each MFLI of the 

wing fuel tanks in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1138, dated March 

18, 2005. If the P/N cannot be identified, or 

the P/N is identified in the ‘‘old P/N’’ column 

of the table in paragraph 1.L., 

‘‘Interchangeability/Mixability,’’ of Airbus 

Service Bulletin A320–28–1138, dated March 

18, 2005, before further flight, do the 

applicable related investigative and 

corrective actions by accomplishing all of the 

actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1138, dated March 

18, 2005. 

(h) Retained Parts Installation Prohibition 

This paragraph restates the requirements 

paragraph (g) of AD 2006–06–14, 

Amendment 39–14523 (71 FR 15023, March 

27, 2006). For Model A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

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

A320–111 airplanes; Model A320–211, –212, 

–214, –231, –232, and –233 airplanes; Model 

A321–111, –112, and –131 airplanes; and 

Model A321–211, –212, –213, –231, and –232 

airplanes; on which Airbus Modification 

27496 has not been installed in production: 

As of May 1, 2006 (the effective date of AD 

2006–06–14), no person may install on any 

airplane any MFLI of the wing fuel tanks 

with a P/N identified in the ‘‘old P/N’’ 

column of the table in paragraph 1.L., 

‘‘Interchangeability/Mixability,’’ of Airbus 

Service Bulletin A320–28–1138, dated March 

18, 2005. 

(i) New Requirement of This AD: Inspection 

For all airplanes, except as provided by 

paragraph (k) of this AD: At the next 

scheduled fuel tank entry after the effective 

date of this AD, or within 49,000 flight hours 

after May 1, 2006 (the effective date of AD 

2006–06–14, Amendment 39–14523 (71 FR 

15023, March 27, 2006)), whichever occurs 

first, perform a special detailed inspection of 

the wing tank to determine which type of 

magnetic fuel level indicators (MFLI) are 

installed, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1209, dated 

December 12, 2011. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection, if the part number and the 

type of the installed MFLI can be 

conclusively determined from that review. 

Paragraphs (i)(1) through (i)(11) of this AD 

identify the affected MLFI part numbers. 

(1) 3508802–24. 

(2) 3508802–25. 

(3) 3508802–26. 

(4) 3508802–27. 

(5) 3508802–28. 

(6) 3508802–34. 

(7) 3508802–39. 

(8) 3508802–74. 

(9) 3508802–75. 

(10) 3508802–76. 

(11) 3508802–91. 

Note 1 to paragraph (i) of this AD: The 

affected MFLI have the ‘S’-shaped lock-wire 

design. 

(j) New Requirement of This AD: 

Replacement or Repair 

If, during the inspection required by 

paragraph (i) of this AD, a MFLI with the ‘S’ 

shaped lock-wire design (Part Number (P/N) 

listed in paragraphs (i)(1) through (i)(11) of 

this AD) is found, then at the next scheduled 

fuel tank entry after the effective date of this 

AD, or within 49,000 flight hours after May 

1, 2006 (the effective date of AD 2006–06–14, 

Amendment 39–14523 (71 FR 15023, March 

27, 2006)), whichever occurs first, replace the 

affected MFLI with a serviceable part and 

accomplish the corrective actions (repair), as 

applicable, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1209, dated 

December 12, 2011. For the purpose of this 

AD, a serviceable part is a composite MFLI, 

or a metallic MFLI with the top stop retained 

by a ‘trapped wire,’ as applicable to the 

location identified in Table 1 of paragraph (j) 

of this AD. 

TABLE 1 OF PARAGRAPH (J) OF THIS

AD—METALLIC MFLI WITH THE TOP

STOP RETAINED BY A ‘TRAPPED

WIRE,’ INCLUDING APPLICABLE LOCATION (FIN) 

MFLI P/N Applicable Location 

(FIN) 

3508802–35 .............. 56/57QM 

3508802–36 .............. 58/59QM 

3508802–37 .............. 60/61QM 

3508802–38 .............. 62/63QM 

(k) New Requirement of This AD: Exception 

for Paragraph (i) of This AD 

Airplanes on which Airbus Modification 

(mod) 27496 has been embodied in 

production, and on which no wing tank 

MFLI replacement with a part number listed 

in paragraphs (i)(1) through (i)(11) of this AD 

has been made since first flight, are not 

affected by the requirement of paragraph (i) 

of this AD. 

(l) New Requirement of This AD: Parts 

Installation Prohibition 

As of the effective date of this AD, do not 

install on any airplane a MFLI with a part 

number listed in paragraphs (i)(1) through 

(i)(11) of this AD. 

(m) 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, WA 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 its delegated agent, or by the Design 

Approval Holder with a State of Design 

Authority’s design organization approval). 

For a repair method to be approved, the 

repair approval must specifically refer to this 

AD. You are required to assure the product 

is airworthy before it is returned to service. 

(n) Special Flight Permits 

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. 

(o) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2012–0119, dated 

July 4, 2012, for related information. You 

may examine the MCAI in the AD docket on 

the Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0698-0002. 

(p) 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. 

(3) The following service information was 

approved for IBR on January 6, 2014. 

(i) Airbus Service Bulletin A320–28–1209, 

dated December 12, 2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 1, 2006 (71 FR 

15023, March 27, 2006). 

(i) Airbus Service Bulletin A320–28–1138, 

dated March 18, 2005. 

(ii) Reserved. 

(5) 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.airworth-eas@

airbus.com; Internet http://www.airbus.com. 


sroberts on DSK5SPTVN1PROD with RULES
71996 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations 

(6) You may view this 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. 

(7) 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 

November 15, 2013. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–28192 Filed 11–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0096; Directorate 

Identifier 2012–NM–143–AD; Amendment 

39–17566; AD 2013–17–02] 

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 A318–112, A319–111, 

A319–112, A319–115, A319–132, and 

A319–133 airplanes. This AD was 

prompted by a report that a fastener, 

which connects the cargo door keel 

beam foot to the circumferential buttstrap and the section 13–14 lower shell 

panel, was not installed on airplanes 

during production. This AD requires 

inspecting forward fuselage frame 24, 

stringer 39, right hand, to determine if 

the fastener is missing; measuring the 

hole dimensions of the five holes 

surrounding the missing fastener if 

necessary; and doing related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct the missing fastener, 

which could result in reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective 

January 6, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 6, 2014. 

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 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on March 4, 2013 (78 FR 

14029). The NPRM proposed to correct 

an unsafe condition for the specified 

products. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Airworthiness 

Directive 2012–0132, dated July 19, 

2012 (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: 

During a ground inspection of an A319 

aeroplane in production, it was discovered 

that one fastener was missing at stringer 

(STGR) 39 on the right-hand (RH) side of FR 

[forward fuselage frame] 24 (Section 13–14 

side). The hole of the missing fastener was 

not drilled. The missing fastener, a 4.8 mm 

[millimeter] diameter titanium bolt, Part 

Number (P/N) EN 6114 V3–7, should connect 

the cargo door keel beam foot to the 

circumferential butt-strap and the section 13– 

14 lower shell panel. Further investigations 

have revealed that the affected fastener has 

not been installed on a limited number of 

aeroplanes in production, due to incorrect 

production instructions. 

This condition, if not corrected, could 

impair the structural integrity of the affected 

aeroplanes. 

* * * * * 

The required actions include doing a 

detailed inspection to determine if the 

fastener is missing, measuring the hole 

dimensions of the five holes 

surrounding the missing fastener if 

necessary, and doing related 

investigative and corrective actions if 

necessary. The related investigative 

actions include a rototest inspection of 

the five holes for cracking. The 

corrective actions include repairing any 

holes with diameter values that exceed 

the specified dimensions, repairing any 

cracking found, and installing new 

fasteners. You may obtain further 

information by examining the MCAI in 

the AD docket on the Internet at http:// 

www.regulations.gov/

#!documentDetail;D=FAA-2013-0096- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Request To Refer to Revised EASA AD 

Airbus requested that paragraph (j) of 

the NPRM (78 FR 14029, March 4, 2013) 

be revised to refer to revised EASA AD 

2012–0132R1, dated March 1, 2013 

(http://ad.easa.europa.eu/blob/easa_ad_

2012_0132_R1.pdf). 

We do not agree with the commenter’s 

request. EASA AD 2012–0132R1, dated 

March 1, 2013, was revised to clarify the 

configurations of the Airbus Model 

A318 and A319 airplanes included in 

table 1 of EASA AD 2012–0132R1, dated 

March 1, 2013. The clarifying text that 

EASA included in EASA AD 2012– 

0132R1, dated March 1, 2013, was 

designated in the NPRM (78 FR 14029, 

March 4, 2013) as ‘‘Table 1 to 

Paragraphs (g) and (h) of this AD.’’ 

We have re-designated the material in 

table 1 to paragraphs (g) and (h) of the 

NPRM (78 FR 14029, March 4, 2013) as 

paragraphs (g)(1), (g)(2), and (g)(3) in 

this final rule. This change does not 

affect the intent of this AD. In addition, 

we revised references to ‘‘Table 1 to 

Paragraphs (g) and (h) of this AD’’ that 

appeared in paragraphs (g) and (h) of the 

NPRM to instead refer to paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD. No 

change was made to this final rule with 

respect to the commenter’s request to 

revise paragraph (j) of this final rule. 

Request To Allow Credit for Actions 

Previously Accomplished Using 

Previous Revisions of the Service 

Information 

Airbus requested that table 1 to 

paragraphs (g) and (h) of the NPRM (78 

FR 14029, March 4, 2013) be revised to 

provide credit for actions that are 

accomplished before the effective date 

of this AD using Airbus Service Bulletin 

A320–00–1219 dated November 9, 2010; 

Revision 01, dated December 8, 2010; 

Revision 02, dated September 6, 2011; 

or Revision 03, dated March 28, 2012. 

We do not agree with the commenter’s 

request. As stated previously, the 

material in table 1 to paragraphs (g) and 

(h) of the NPRM (78 FR 14029, March 

4, 2013) has been re-designated as 

paragraphs (g)(1), (g)(2), and (g)(3) of 

this final rule. Those paragraphs do not 

mandate accomplishing any actions 

using Airbus Service Bulletin A320–00– 


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