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

78285 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
78286 Federal Register / Vol. 78, No. 248 / Thursday, December 26, 2013 / Proposed Rules 

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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 248 / Thursday, December 26, 2013 / Proposed Rules 78287 

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: 

ESTIMATED 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); 


tkelley on DSK3SPTVN1PROD with PROPOSALS
78288 Federal Register / Vol. 78, No. 248 / Thursday, December 26, 2013 / Proposed Rules 

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). 


tkelley on DSK3SPTVN1PROD with PROPOSALS
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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 an 

ultrasonic 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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
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 


tkelley on DSK3SPTVN1PROD with PROPOSALS