This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final
rules. 

# Proposed Rules Federal Register 

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Vol. 78, No. 248

Thursday, December 26, 2013

**NUCLEAR REGULATORY**
**COMMISSION**

**10 CFR Part 72**

**[NRC–2012–0052]**

**RIN 3150–AJ12**

**List of Approved Spent Fuel Storage Casks: HI–STORM 100 Cask System;** 
**Amendment No. 9**

**AGENCY :**  Nuclear Regulatory

Commission.

**ACTION :**  Proposed rule; correction and extension of comment period.

**SUMMARY :**  The U.S. Nuclear Regulatory Commission (NRC) is correcting a proposed rule that appeared in the Federal Register on December 6, 2013, and is extending the public comment period. The document proposed to amend the NRC’s spent fuel storage regulations by revising the Holtec
International HI–STORM 100 Cask System listing within the ‘‘List of Approved Spent Fuel Storage Casks’’ to
include Amendment No. 9 to Certificate of Compliance (CoC) No. 1014. This action is necessary to correct the NRC’s Agencywide Documents Access and Management System (ADAMS)
accession numbers for the CoC and the ADAMS document package containing the CoC, the Safety Evaluation Report (SER), and the Technical Specifications (TSs) for this amendment; and to extend the public comment period.

**DATES :**  The comment period for the proposed rule published December 6, 2013, at 78 FR 73456, is extended. Comments are due by January 27, 2014.

**ADDRESSES :**  Please refer to Docket ID NRC–2012–0052 when contacting the NRC about the availability of information for this action. You may access publicly-available information related to this action by any of the following methods:

• Federal Rulemaking Web site: Go to http://www.regulations.gov and search
for Docket ID NRC–2012–0052. Address questions about NRC dockets to Carol Gallagher, telephone: 301–287–3422, email: Carol.Gallagher@nrc.gov. For technical questions, contact the
individual listed in the **FOR FURTHER**

**INFORMATION CONTACT** section of this
document.

• NRC’s Agencywide Documents Access and Management System (ADAMS): You may access publicly
available documents online in the NRC Library at: http://www.nrc.gov/readingrm/adams.html. To begin the search,
select ‘‘ADAMS Public Documents’’ and
then select ‘‘ Begin Web-based ADAMS
Search.’’ For problems with ADAMS, please contact the NRC’s Public Document Room (PDR) reference staff

at: 1–800–397–4209, 301–415–4737, or by email to: pdr.resource@nrc.gov.

• NRC’s PDR: You may examine and purchase copies of public documents at the NRC’s PDR, Room O–1F21, One White Flint North, 11555 Rockville Pike, Rockville, Maryland 20852.

**FOR FURTHER INFORMATION CONTACT :**  Naiem S. Tanious, Office of Federal and
State Materials and Environmental Management Programs, U.S. Nuclear Regulatory Commission, Washington, DC 20555–0001, telephone: 301–415– 6103, email: Naiem.Tanious@nrc.gov.

**SUPPLEMENTARY INFORMATION :** 

Corrections

The NRC is correcting the ADAMS
accession numbers for the CoC and the ADAMS document package containing the CoC, SER, and the TSs for this
amendment because the documents referenced by accession numbers in the proposed rule the NRC published on December 6, 2013 (78 FR 73456; Fr. Doc. 2013–29160), do not clearly display the proposed changes to the documents.

In Fr. Doc. 2013–29160, on page 73456, in the second column, second line from the bottom of the page,
‘‘ML120530246’’ is corrected to read ‘‘ML13351A224.’’ On page 73456, in the third column, second line from the top of the page, ‘‘ML120530271’’ is
corrected to read ‘‘ML13351A205.’’

In the Rules and Regulations section
of this issue of the Federal Register, the NRC is publishing a document to correct and delay the effective date of the direct final rule (78 FR 73379; December 6, 2013). Specifically, ADAMS accession numbers for the CoC, the SER, and the ADAMS document package containing the CoC, the SER, and the TSs for this
amendment will be corrected and the effective date will be delayed from February 19, 2014, to March 11, 2014.

Extension of Comment Period

The public comment period is being extended from January 6, 2014, to January 27, 2014, to provide the public the opportunity to review all information related to the rulemaking.

Dated at Rockville, Maryland, this 19th day of December, 2013.

For the Nuclear Regulatory Commission. Leslie Terry, Acting Chief, Rules, Announcements, and Directives Branch, Division of Administrative Services, Office of Administration.

[FR Doc. 2013–30864 Filed 12–24–13; 8:45 am]

**BILLING CODE 7590–01–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–1064; Directorate Identifier 2012–NM–101–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to supersede airworthiness directive (AD) 2005–23– 08 that applies to certain Airbus Model A300 B4–605R and B4–622R airplanes; Model A300 F4–605R airplanes; and
Model A300 C4–605R Variant F airplanes. AD 2005–23–08 required repetitive inspections to detect cracks of certain attachment holes, installation of new fasteners, follow-on inspections or repair if necessary, and modification of the angle fittings of fuselage frame FR47. Since we issued AD 2005–23–08, we have received reports of cracks found on the horizontal flange of the Frame 47 internal corner angle fitting while accomplishing the modification required by AD 2005–23–08. This proposed AD would add new repetitive ultrasonic inspections for cracks of the center wing box lower panel; and repair if necessary. This proposed AD also removes certain airplanes from the applicability. We are proposing this AD to detect and correct fatigue cracking of


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the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame.

**DATES :**  We must receive comments on this proposed AD by February 10, 2014.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: (202) 493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Airbus SAS— EAW (Airworthiness Office), 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 . You may review copies of the 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.

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 this proposed AD, the MCAI, 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. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: (425) 227–2125; fax: (425) 227–1149.

**SUPPLEMENTARY INFORMATION :** 

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments
to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2013–1064; Directorate Identifier 2012–NM–101–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each
substantive verbal contact we receive about this proposed AD.

Discussion

On October 31, 2005, we issued AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005). That AD required actions intended to address an
unsafe condition on certain Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes; Model A300 B4–605R and B4–622R airplanes; Model A300 F4– 605R airplanes; and Model A300 C4– 605R Variant F airplanes.

Since we issued AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005), the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has
issued EASA Airworthiness Directive 2012–0092, dated May 25, 2012; correction dated June 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:

Prompted by cracks found on the Frame 47 angle fitting, DGAC France published AD 2000–533–328 [(http://ad.easa.europa.eu/ad/

F-2000-533-328R1 )] to require [a] repetitive inspection programme for fuselage frame 47. If not detected and corrected, these cracks could affect the structural integrity of the Centre Wing Box (CWB) of the aeroplane.

Subsequent to the publication of a new repetitive inspection programme for fuselage
frame 47 at certain fasteners of the CWB angle fitting, DGAC France issued AD F– 2004–159 [(http://ad.easa.europa.eu/ad/F2004-159)] [which corresponds to AD 2005– 23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005)], superseding AD 2000–

533–328.

After DGAC France AD F–2004–159 was issued, cracks were reportedly found on the horizontal flange of the Frame 47 internal corner angle fitting during accomplishment of routine maintenance structural inspection
and modification in accordance with Airbus

SB A300–57–6050.

Prompted by these findings, Airbus reviewed and amended the inspection programme for the internal lower angle fitting flange (horizontal face). The inspection programme for the lower angle fitting web (vertical face) related to SB A300– 57–6049 and internal lower angle fitting modification programme related to SB A300– 57–6050 remain unchanged.

For the reasons explained above, this new [EASA] AD retains the requirements of DGAC France AD F–2004–159, which is superseded, and requires additional repetitive [ultrasonic] inspections [for cracks] of the CWB lower panel through the ultrasonic method and, depending on findings, [repair, e.g.,] re-installation of

removed fasteners in transition fit instead of

interference.

This [EASA] AD has been republished to correct a typographical error * * *.

The repetitive interval for the new ultrasonic inspection is either 1,260 flight cycles or 2,720 flight hours, whichever occurs first; or 1,360 flight cycles or 2,200 flight hours, whichever occurs first; depending on average flight time of the airplane. You may obtain further information by examining the
MCAI in the AD docket.

Relevant Service Information

Airbus has issued Mandatory Service Bulletins A300–57–6049, Revision 07, dated December 22, 2006, and A300– 57–6086, Revision 05, dated January 30,
2012. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.

FAA’s Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation
in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent
information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

Difference Between This Proposed AD
and the MCAI or Service Information

Although the MCAI and service information specify to contact the manufacturer for instructions to repair certain conditions, this proposed AD would require repairing those conditions using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA (or its delegated agent; or the Design Approval Holder with EASA’s design organization approval), as applicable.


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Explanation of Changes to AD 2005–23– 08, Amendment 39–14366 (70 FR 69056, November 14, 2005)

In many FAA transport ADs, when the service information specifies to
contact the manufacturer for further instructions if certain discrepancies are found, we typically include in the AD a requirement to accomplish the action using a method approved by either the FAA or the State of Design Authority (or its delegated agent).

We have recently been notified that
certain laws in other countries do not allow such delegation of authority, but some countries do recognize design approval organizations. In addition, we
have become aware that some U.S. operators have used repair instructions that were previously approved by a State of Design Authority or a Design Approval Holder (DAH) as a method of compliance with this provision in FAA ADs. Frequently, in these cases, the previously approved repair instructions come from the airplane structural repair manual or the DAH repair approval statements that were not specifically developed to address the unsafe condition corrected by the AD. Using repair instructions that were not specifically approved for a particular AD creates the potential for doing repairs that were not developed to
address the unsafe condition identified by the MCAI AD, the FAA AD, or the applicable service information, which
could result in the unsafe condition not being fully corrected.

To prevent the use of repairs that were not specifically developed to correct the unsafe condition, this proposed AD would require that the repair approval specifically refer to the FAA AD. This change is intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we use the phrase ‘‘its delegated agent, or by the DAH with State of Design Authority design organization approval, as applicable’’ in this proposed AD to refer to an DAH authorized to approve required repairs for this proposed AD.

Explanation of Change to Applicability

AD 2005–23–08, Amendment 39– 14366 (70 FR 69056, November 14, 2005), includes Airbus Model A300 B4– 601 airplanes in the applicability. However, this proposed AD does not include Model A300 B4–601 airplanes because these airplanes are no longer in

service.

Costs of Compliance

We estimate that this proposed AD affects about 65 products of U.S. registry.

We estimate the following costs to comply with this proposed AD:



### E STIMATED 

### COSTS

Action Work hours Average labor rate per hour Parts Cost per airplane

Inspection [retained action from existing AD] AD

2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). 13 ................................. $85 $0 ................................. $1,105.

Inspection [retained action from existing AD] AD

2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005). 30 ................................. 85 Between $6,637 and $19,091. Between $9,187 and$21,641, per inspection cycle. Modification [retained action from existing AD]

AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005). Between 65 and 365 .... 85 $3,370 .......................... Between $8,895 and $34,395.

New ultrasonic inspection .................................... 35 ................................. 85 Between $11,750 and $18,720. Between $14,725 and$21,695 per inspection cycle.

We have received no definitive data that would enable us to provide cost
estimates for the on-condition actions specified in this proposed AD.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork
Reduction Act unless that collection of information displays a current valid
OMB control number. The control
number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD
has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden
should be directed to the FAA at 800 Independence Ave., SW., Washington,
DC 20591. ATTN: Information Collection Clearance Officer, AES–200.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority
because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking

action.

Regulatory Findings

We determined that this proposed AD would not have federalism implications
under Executive Order 13132. This proposed AD would 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 this proposed regulation:

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);


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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 proposed AD and placed it in the
AD docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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) 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005) and adding the following new AD:

Airbus: Docket No. FAA–2013–1064;
Directorate Identifier 2012–NM–101–AD.

(a) Comments Due Date

We must receive comments by February

10, 2014.

(b) Affected ADs

This AD supersedes AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005).

(c) Applicability

This AD applies to Airbus Model B4–603, B4–620, and B4–622 airplanes; Model A300 B4–605R and B4–622R airplanes; Model A300 F4–605R airplanes; and Model A300 C4–605R Variant F airplanes; certificated in any category; except airplanes on which
Airbus Modification 12171 or 12249 has been embodied in production, or on which Airbus
Service Bulletin A300–57–6069 has been
embodied in service.

(d) Subject

Air Transport Association (ATA) of America Code 57: Wings.

(e) Reason

This AD was prompted by reports of cracks found on the horizontal flange of the Frame 47 internal corner angle fitting while accomplishing the modification required by AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005). We are issuing this AD to detect and correct fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame.

(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 Inspections for Attachment Holes on the Internal Angles of the Wing Center Box, and Corrective Action

This paragraph restates the requirements of paragraphs (f), (g), and (h) of AD 2005–23– 08, Amendment 39–14366 (70 FR 69056, November 14, 2005), with revised service information. Perform a rotating probe inspection to detect cracking of the applicable attachment holes on the left and right internal angles of the wing center box in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300– 57–6049, Revision 06, dated July 15, 2004; or Airbus Mandatory Service Bulletin A300–57– 6049, Revision 07, dated December 22, 2006. Do the inspection at the applicable time specified by paragraph 1.E.(2), Accomplishment Timescale, of Airbus Service Bulletin A300–57–6049, Revision 06, dated July 15, 2004; except as required by paragraph (j) of this AD. Repeat the rotating probe inspection specified in this paragraph
thereafter at intervals not to exceed the applicable interval specified in Airbus Mandatory Service Bulletin A300–57–6049, Revision 06, dated July 15, 2004, except that all touch-and-go landings must be counted in determining the total number of flight cycles between consecutive inspections. As of the effective date of this AD, only Airbus Mandatory Service Bulletin A300–57–6049, Revision 07, dated December 22, 2006, may be used to accomplish the actions required by this paragraph.

(1) If no cracking is found during any inspection required by paragraph (g) of this AD: Prior to further flight, install new
fasteners in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6049, Revision 06, dated July 15, 2004; or Airbus Mandatory Service Bulletin A300–57–6049, Revision 07, dated December 22, 2006. As of the effective date of this AD, only Airbus Mandatory Service Bulletin A300–57–6049, Revision 07, dated December 22, 2006, may be used to accomplish the actions required by this paragraph.

(2) If any cracking is found during any inspection required by paragraph (g) of this AD: Prior to further flight, perform applicable corrective actions (including reaming, drilling, drill-stopping holes, chamfering, performing follow-on inspections, and installing new or oversize fasteners) in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300– 57–6049, Revision 06, dated July 15, 2004; or Airbus Mandatory Service Bulletin A300–57– 6049, Revision 07, dated December 22, 2006; except as required by paragraph (k) of this AD. As of the effective date of this AD, only Airbus Mandatory Service Bulletin A300–57– 6049, Revision 07, dated December 22, 2006, may be used to accomplish the actions required by this paragraph. (h) Retained Inspections for Attachment Holes in the Horizontal Flange of the Internal Corner Angle Fitting of Fuselage Frame FR47, and Corrective Action

This paragraph restates the requirements of paragraphs (i), (j), and (k) of AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005), with revised service information. Perform a rotating probe inspection to detect cracking of the applicable attachment holes in the horizontal flange of the internal corner angle fitting of fuselage frame FR47, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6086, Revision 01, dated April 2, 2002; or Airbus Mandatory Service Bulletin A300–57–6086, Revision 05, dated January 30, 2012. Do the inspection at the applicable time specified in paragraph 1.E., Compliance, of Airbus Service Bulletin A300–57–6086, Revision 01, dated April 2, 2002, except as provided by paragraph (j) of this AD; or within 1,500 flight cycles after July 8, 2002 (the effective date of AD 2002– 11–04, amendment 39–12765 (67 FR 38193, June 3, 2002)); whichever occurs later. Repeat the rotating probe inspection specified in this paragraph thereafter at intervals not to exceed the applicable interval specified in Airbus Service Bulletin A300–57–6086,dated June 6, 2000, except that all touch-andgo landings must be counted in determining the total number of flight cycles between consecutive inspections. As of the effective date of this AD, only Airbus Mandatory Service Bulletin A300–57–6086, Revision 05, dated January 30, 2012, may be used to accomplish the actions required by this paragraph.

(1) If no cracking is found during any inspection required by paragraph (h) of this AD: Prior to further flight, install new
fasteners in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6086, Revision 01, dated April 2, 2002; or Airbus Mandatory Service Bulletin A300–57–6086, Revision 05, dated January 30, 2012. As of the effective date of this AD, only Airbus Mandatory Service Bulletin A300–57–6086, Revision 05, dated January 30, 2012, may be used to accomplish the actions required by this paragraph.

(2) If any cracking is found during any inspection required by paragraph (h) of this AD: Prior to further flight, perform applicable corrective actions (including inspecting hole T if any cracking is found at hole G, reaming the holes, and installing oversize fasteners) in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300– 57–6086, Revision 01, dated April 2, 2002; or Airbus Mandatory Service Bulletin A300–57– 6086, Revision 05, dated January 30, 2012; except as required by paragraph (k) of this AD. As of the effective date of this AD, only Airbus Mandatory Service Bulletin A300–57– 6086, Revision 05, dated January 30, 2012, may be used to accomplish the actions required by this paragraph.

(i) Retained Modification of Angle Fittings of the Wing Center Box

This paragraph restates the requirements of paragraph (l) of AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005).


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Modify the left and right internal angle fittings of the wing center box. The modification includes performing a rotating probe inspection to detect cracking, repairing cracks, cold expanding holes, and installing medium interference fitting bolts. Perform
the modification in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6050, Revision 03, dated May 31, 2001; and at the applicable time specified by paragraph 1.B.(4), Accomplishment Timescale, of Airbus Service Bulletin A300–57–6050, Revision 03, dated May 31, 2001; except as required by paragraphs (j) and (k) of this AD.

(j) Retained Compliance Time Exception to Service Information Specified in Paragraphs (g), (h), and (i) of This AD

This paragraph restates the requirements of paragraph (m) of AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005). Where the service information specified in paragraphs (g), (h), and (i) of this AD specify a grace period relative to receipt of the service bulletin, this AD requires compliance within the applicable grace period following December 19, 2005, (the effective date of AD 2005–23– 08), if the threshold has been exceeded.

(k) Retained Corrective Action Exception to Service Information Specified in Paragraphs (g), (h), and (i) of This AD

This paragraph restates the requirements of paragraph (n) of AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005). If any crack is detected during any inspection required by paragraph (g), (h), or (i) of this AD, and the applicable service information specifies to contact the manufacturer for disposition of certain corrective actions: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or
the Direction Ge  ́ ne

 ́ rale de l’Aviation Civile (DGAC) (or its delegated agent).

(l) Credit for Previous Actions

(1) This paragraph restates the credit provided by paragraph (o) of AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005): This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before December 19. 2005, (the effective date of AD 2005–23–08) using Airbus Service Bulletin A300–57–6086, dated June 6, 2000.

(2) This paragraph restates the credit provided by paragraph (p) of AD 2005–23– 08, Amendment 39–14366 (70 FR 69056, November 14, 2005): This paragraph provides credit for the modification required by paragraph (i) of this AD, if the modification was performed before December 19, 2005, (the effective date of AD 2005–23–08) using Airbus Service Bulletin A300–57–6050, Revision 02, dated February 10, 2000.

(m) New Requirements of This AD: Repetitive Ultrasonic Inspections and

Corrective Action

(1) For airplanes on which Airbus Service Bulletin A300–57–6050, Revision 03, dated May 31, 2001, has not been done, or on
which Airbus Modification 10155 has been done: Perform an ultrasonic inspection for cracking of the left- and right-hand aft bottom panel of the center wing box (CWB) in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–6086, Revision 05, dated January 30, 2012. Do the inspection at the later of the times specified in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD. If any cracking is found, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent, or the Design Approval Holder with EASA’s design organization approval, as applicable. For a repair method to be approved, the repair approval must specifically refer to this AD. Repeat the inspection thereafter at intervals not to exceed the applicable interval specified in paragraph 1.E.(2), Accomplishment Timescale, of Airbus Mandatory Service Bulletin A300–57–6086, Revision 05, dated January 30, 2012.

(i) Within 13,400 flight cycles or 34,600 flight hours after the first flight of the airplane, whichever occurs first.

(ii) Within 650 flight cycles or 8 months after the effective date of this AD, whichever
occurs first.

(2) For airplanes on which Airbus Service Bulletin A300–57–6050, Revision 03, dated May 31, 2001, has been done: Perform anultrasonic inspection for cracking of the leftand right-hand aft bottom panel of the center wing box (CWB), in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–6086, Revision 05, dated January 30, 2012. Do the inspection at the later of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. If any cracking is found, before further flight repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent, or the Design Approval Holder with EASA’s design organization approval), as applicable. For a repair method to be approved, the repair approval must specifically refer to this AD. Repeat the inspection thereafter at intervals not to exceed the applicable interval specified in paragraph 1.E.(2), Accomplishment Timescale, of Airbus Mandatory Service Bulletin A300–57–6086, Revision 05, dated January 30, 2012.

(i) Within 13,400 flight cycles or 34,600 flight hours after accomplishing Airbus Service Bulletin A300–57–6050, whichever
occurs first.

(ii) Within 650 flight cycles or 8 months after the effective date of this AD, whichever
occurs first.

(n) New Reporting Requirement

Submit a report of the findings (both positive and negative) of the inspection required by paragraph (m) of this AD to the Design Approval Holder, at the applicable time specified in paragraph (n)(1) or (n)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of flight cycles and flight hours on the airplane. The inspection report form in Appendix 01 of Airbus Mandatory Service Bulletin A300–57–6086, Revision 05, dated January 30, 2012, may be
used.

(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.

(o) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: (425) 227–2125; 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. AMOCs approved previously in accordance with AD 2005–23–08, Amendment 39–14366 (70 FR 69056, November 14, 2005), are approved as AMOCs for the corresponding provision of this AD.

(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the Design Approval Holder with a State of Design Authority’s design organization approval), as applicable. For a repair method to be approved, the repair approval must specifically refer to this AD. You are required to ensure the product is airworthy before it is returned to service.

(p) Related Information

(1) Refer to Mandatory Continuing
Airworthiness Information EASA Airworthiness Directive 2012–0092, dated May 25, 2012: Correction dated June 4, 2012, for related information. This MCAI may be
found in the AD docket on the Internet at http://www.regulations.gov.

(2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 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.

(3) You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information


### 78290 Federal Register / Vol. 78, No. 248 / Thursday, December 26, 2013 / Proposed Rules

on the availability of this material at the FAA, call 425–227–1221.

Issued in Renton, Washington, on December 17, 2013. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–30893 Filed 12–24–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2008–1088; Directorate Identifier 2008–NE–15–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Dowty Propellers** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to revise airworthiness directive (AD) 2008–21– 07 that applies to certain Dowty Propellers model R408/6–123–F/17 propellers. AD 2008–21–07 requires initial and repetitive inspections of the blade bonded metallic leading edge (L/ E) guards for correct bonding until they accumulate more than 1,200 flight hours (FH) time in service. Since we issued AD 2008–21–07, Dowty Propellers has introduced updated service bulletins that identify terminating action to the requirements of AD 2008–21–07. This proposed AD would maintain the inspection and replacement requirements of AD 2008–21–07, provide an optional terminating action to those requirements, and add a new part number to the list of affected parts. We are proposing this AD to prevent the loss of the bonded metallic L/E guard of the propeller, which could result in damage to the propeller or to the airplane, or injury to personnel.

**DATES :**  We must receive comments on this proposed AD by February 24, 2014.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following
methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this AD, contact Dowty Propellers, Anson Business Park, Cheltenham Road East, Gloucester GL2 9QN, UK; phone 44 (0) 1452 716000; fax 44 (0) 1452 716001. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125.

Examining the AD Docket

You may examine the AD docket on
the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2008– 1088; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the mandatory continuing airworthiness information, the regulatory evaluation, any comments received, and other
information. The street address for the Docket Office (phone: 800–647–5527) is
in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Michael Schwetz, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781– 238–7761; fax: 781–238–7170; email: michael.schwetz@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments
to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2008–1088; Directorate Identifier 2008–NE–15–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those

comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each
substantive verbal contact we receive about this proposed AD. Discussion

On October 3, 2008, we issued AD 2008–21–07, Amendment 39–15691 (73 FR 61346, October 16, 2008), (‘‘AD 2008–21–07’’), for all Dowty Propellers model R408/6–123–F/17 propellers. AD 2008–21–07 requires initial and repetitive inspections of the blade bonded metallic L/E guards for correct bonding until they accumulate more than 1,200 FH time in service. AD 2008–
21–07 resulted from three in-service occurrences of blades losing the bonded metallic L/E guard. We issued AD 2008– 21–07 to prevent the loss of the bonded metallic L/E guard of the propeller, which could result in damage to the propeller or to the airplane, or injury to personnel.

Actions Since Existing AD Was Issued

Since we issued AD 2008–21–07, Dowty Propellers has introduced updated service bulletins that identify terminating action to the repetitive inspection requirements of AD 2008– 21–07. Dowty has also informed us of the need to add blade part number
697071278–18 to the list of affected parts. Also since we issued AD 2008– 21–07, the European Aviation Safety Agency (EASA) has issued AD 2007– 0223R4, dated September 30, 2013, which requires repetitive inspections of the affected propellers and clarifies terminating action.

Relevant Service Information

We reviewed Dowty Propellers Alert Service Bulletin (ASB) No. D8400–61– A69, Revision 1, dated September 18, 2007. The ASB describes procedures for initial and repetitive inspections of blade bonded metallic L/E guards, and repair or replacement of blades that fail inspection. We also reviewed Service Bulletin (SB) No. D8400–61–70, Revision 3, dated June 3, 2013, and SB No. D8400–61–83, Revision 4, dated June 3, 2013, which provide optional terminating action for the repetitive inspection requirement of this proposed

AD.

FAA’s Determination

We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.

Proposed AD Requirements

This proposed AD would maintain the initial and repetitive inspections of the propeller blade bonded metallic L/ E guards required by AD 2008–21–07 (73 FR 61346, October 16, 2008). This proposed AD would also provide an