## 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


## 71993 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations

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:



### E STIMATED 

### C OSTS

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


## 71994 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations

E STIMATED 

### C OSTS 

### —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:



### O N



### - CONDITION 

### C OSTS

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


## 71995 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations

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 

### P ARAGRAPH 

### ( J 

### ) OF 

### T HIS



### AD—M ETALLIC 

### MFLI W ITH THE 

### T OP 

### S TOP 

### R ETAINED BY A 

### ‘T RAPPED 

### W IRE 

### ,’ I NCLUDING 

### A PPLICABLE 

### L O



### CATION 

### (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.


## 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 keelbeam 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–