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

7592 

Vol. 79, No. 27 

Monday, February 10, 2014 

1To view the notice, supporting documents, and 

the comments we received, go to http://www.

regulations.gov/#!docketDetail;D=APHIS-2012- 

0106. 

DEPARTMENT OF AGRICULTURE 

Animal and Plant Health Inspection 

Service 

9 CFR Part 3 

[Docket No. APHIS–2012–0106] 

Petition To Promulgate Standards for 

Bears Under the Animal Welfare Act 

Regulations 

AGENCY: Animal and Plant Health 

Inspection Service, USDA. 

ACTION: Notice of petition; reopening of 

comment period. 

SUMMARY: We are reopening the 

comment period for a petition 

requesting that we amend the Animal 

Welfare Act regulations to add specific 

standards for the humane handling, 

care, treatment, and transportation of all 

species of bears held in captivity except 

polar bears, for which there are already 

standards. This action will allow 

interested persons additional time to 

prepare and submit comments. 

DATES: The comment period for the 

notice published November 26, 2013 (78 

FR 70515) is reopened. We will consider 

all comments that we receive on or 

before March 12, 2014. 

ADDRESSES: You may submit comments 

by either of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov/#!document

Detail;D=APHIS-2012-0106-0001. 

• Postal Mail/Commercial Delivery: 

Send your comment to Docket No. 

APHIS–2012–0106, Regulatory Analysis 

and Development, PPD, APHIS, Station 

3A–03.8, 4700 River Road Unit 118, 

Riverdale, MD 20737–1238. 

Supporting documents and any 

comments we receive on this docket 

may be viewed at http://www.

regulations.gov/#!docketDetail;D=

APHIS-2012-0106 or in our reading 

room, located in Room 1141 of the 

USDA South Building, 14th Street and 

Independence Avenue SW., 

Washington, DC. Reading room hours 

are 8 a.m. to 4:30 p.m., Monday through 

Friday, except holidays. To be sure 

someone is there to help you, please call 

(202) 799–7039 before coming. 

FOR FURTHER INFORMATION CONTACT: Dr. 

Barbara Kohn, DVM, Senior Staff 

Officer, USDA, APHIS, Animal Care, 

4700 River Road Unit 84, Riverdale, MD 

20737–1234; (301) 851–3751. 

SUPPLEMENTARY INFORMATION: 

Background 

On November 26, 2013, the Animal 

and Plant Health Inspection Service 

published in the Federal Register (78 

FR 70515–70516, Docket No. APHIS– 

2012–0106) a notice 1 requesting 

comments on a petition from People for 

the Ethical Treatment of Animals 

requesting that we amend the Animal 

Welfare Act regulations to add specific 

standards for the humane handling, 

care, treatment, and transportation of all 

species of bears held in captivity except 

polar bears, for which there are already 

standards. 

Comments on the notice were 

required to be received on or before 

January 27, 2014. We are reopening the 

comment period on Docket No. APHIS– 

2012–0106 for an additional 30 days. 

This action will allow interested 

persons additional time to prepare and 

submit comments. We will also consider 

all comments received between January 

28, 2014 (the day after the close of the 

original comment period) and the date 

of this notice. 

We encourage the submission of 

scientific data, studies, or research to 

support your comments and position, 

including data or research that supports 

any industry or professional standards 

that pertain to the care of bears. We also 

invite data on the costs and benefits 

associated with any recommendations. 

We will consider all comments and 

recommendations we receive. 

Authority: 7 U.S.C. 2131–2159; 7 CFR 

2.22, 2.80, and 371.7. 

Done in Washington, DC, this 3rd day of 

February 2014. 

Kevin Shea, 

Administrator, Animal and Plant Health 

Inspection Service. 

[FR Doc. 2014–02756 Filed 2–7–14; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0011; Directorate 

Identifier 2013–NM–046–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) 98–13–23, 

which applies to certain Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes). AD 98–13–23 requires 

inspections to detect corrosion and 

cracking of the lower horizontal 

stabilizer cutout longeron, the corner 

fitting, the skin strap, and the outer 

skin; and repair, if necessary. Since we 

issued AD 98–13–23, we have 

determined that the risk of cracking is 

higher than initially determined. This 

proposed AD would reduce the 

compliance times and repetitive 

intervals, and changes the inspection 

procedures. We are proposing this AD to 

prevent cracking of the lower horizontal 

stabilizer cutout longeron, the corner 

fitting, the skin strap, and the outer 

skin, which could result in reduced 

structural integrity of the horizontalstabilizer cutout longeron. 

DATES: We must receive comments on 

this proposed AD by March 27, 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 


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a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAW, 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 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. 

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–2014– 

0011; 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 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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–2014–0011; Directorate Identifier 

2013–NM–046–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 June 15, 1998, we issued AD 98– 

13–23, Amendment 39–10614 (63 FR 

34576, June 25, 1998). That AD requires 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 98–13–23, 

Amendment 39–10614 (63 FR 34576, 

June 25, 1998), a fleet survey and 

updated fatigue and damage tolerance 

analyses showed that the risk of cracks 

for these airplanes is higher than 

initially determined. The European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2013–0048, dated March 4, 2013 

(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 full scale fatigue test, a crack was 

found at the lower corner of the assembly of 

the horizontal stabilizer cut-out, between 

Frame (FR)87 and FR89 and between Stringer 

(STGR)24 and STGR27, Left Hand (LH) and 

Right Hand (RH) sides. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the aeroplane. 

DGAC France issued AD * * * to require 

repetitive visual and High Frequency Eddy 

Current (HFEC) rotating probe inspections of 

the affected areas and subsequent corrective 

action, in case of cracks. 

Since that [DGAC France] AD was issued, 

a fleet survey and updated Fatigue and 

Damage Tolerance analyses have been 

performed to substantiate the second A300– 

600 Extended Service Goal (ESG2) exercise. 

The results of these analyses have shown that 

the risk of cracks for these aeroplanes is 

higher than initially determined and that, 

consequently, the thresholds and intervals 

must be reduced to allow timely detection of 

these cracks and accomplishment of an 

applicable corrective action. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

France AD * * *, which is superseded, and 

requires the accomplishment of these actions 

within the new thresholds and intervals 

defined in Revision 03 of Airbus Service 

Bulletin (SB) A300–53–6042 [dated August 

30, 2012]. 

The initial compliance times for 

airplanes with an average flight time 

greater than 1.5 hours, depending on the 

inspection area, are between before 

18,000 total flight cycles and 38,100 

total flight hours, whichever occurs 

first; and before 42,500 total flight 

cycles or 89,000 total flight hours, 

whichever occurs first. The repetitive 

compliance times for airplanes with an 

average flight time above 1.5 hours, 

depending on the inspection area, are 

between intervals not to exceed 3,900 

flight cycles or 8,200 flight hours, 

whichever occurs first; and intervals not 

to exceed 6,000 flight cycles or 12,700 

flight hours, whichever occurs first. 

The initial compliance times for 

airplanes with an average flight time of 

1.5 hours or less, depending on the 

inspection area, are between before 

19,900 total flight cycles and 29,800 

total flight hours, whichever occurs 

first; and before 47,100 total flight 

cycles or 70,500 total flight hours, 

whichever occurs first. The repetitive 

compliance times for airplanes with an 

average flight time of 1.5 hours or less, 

depending on inspection area, are 

between intervals not to exceed 4,300 

flight cycles or 6,400 flight hours, 

whichever occurs first, and intervals not 

to exceed 6,600 flight cycles or 9,900 

flight hours, whichever occurs first. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0011. 

Explanation of Change to Applicability 

We have revised the applicability of 

this AD to identify model designations 

as published in the most recent type 

certificate data sheet for the affected 

models. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–53–6042, Revision 03, 

dated August 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. 

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. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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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, certain 

new requirements of 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 the DAH with State 

of Design Authority design organization 

approval, as applicable’’ in this 

proposed AD to refer to a DAH 

authorized to approve newly required 

repairs for this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 5 products of U.S. 

registry. We estimate the following costs 

to comply with this proposed AD. 

ESTIMATED COSTS

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

Inspections [retained actions from AD 98–13–23, 

Amendment 39–10614 (63 FR 34576, June 25, 

1998].

268 work-hour × $85 per 

hour = $22,780 per inspection cycle.

$0 $22,780 per inspection 

cycle.

$45,560 per inspection 

cycle (2 airplanes) 

Inspections [new proposed action] ......................... 88 work-hour × $85 per 

hour = $7,480 per inspection cycle.

0 $7,480 per inspection 

cycle.

$37,400 per inspection 

cycle 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair .............................................. 155 work-hours × $85 per hour = $13,175 ............................................... $0 $13,175 

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); 

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. 

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) 

98–13–23, Amendment 39–10614 (63 

FR 34576, June 25, 1998), and adding 

the following new AD: 

Airbus: Docket No. FAA–2014–0011; 

Directorate Identifier 2013–NM–046–AD. 

(a) Comments Due Date 

We must receive comments by March 27, 

2014. 

(b) Affected ADs 

This AD supersedes AD 98–13–23, 

Amendment 39–10614 (63 FR 34576, June 

25, 1998). 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, and B4–622 airplanes; 

Model A300 B4–605R and B4–622R 

airplanes; Model A300 F4–605R and F4– 

622R airplanes; and Model A300 C4–605R 

Variant F airplanes; certificated in any 


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category; on which Airbus Modification 6146 

has not been installed. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of 

cracking found at the lower corner of the 

horizontal stabilizer cutout longeron during a 

full scale fatigue test, and a determination 

that the risk of cracking is higher than 

initially determined. We are issuing this AD 

to prevent cracking of the lower horizontal 

stabilizer cutout longeron, the corner fitting, 

the skin strap, and the outer skin, which 

could result in reduced structural integrity of 

the horizontal-stabilizer cutout longeron. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections and Corrective 

Actions 

This paragraph restates the requirements of 

paragraphs (a), (b), (c), (d), and (e) of AD 98– 

13–23, Amendment 39–10614 (63 FR 34576, 

June 25, 1998), with revised service 

information. 

(1) Prior to the accumulation of 18,000 

total landings, or within 2,000 landings after 

July 30, 1998 (the effective date of AD 98– 

13–23, Amendment 39–10614 (63 FR 34576, 

June 25, 1998)), whichever occurs later: 

Perform a visual and eddy current inspection 

to detect cracks and/or corrosion of Areas 1 

and 2 of the lower horizontal stabilizer 

cutout longeron, in accordance with Airbus 

Service Bulletin A300–53–6042, Revision 1, 

dated February 20, 1995; or Airbus 

Mandatory Service Bulletin A300–53–6042, 

Revision 03, dated August 30, 2012. As of the 

effective date of this AD, use only Airbus 

Mandatory Service Bulletin A300–53–6042, 

Revision 03, dated August 30, 2012, to do the 

actions required by this paragraph. 

(2) At the later of the times specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: 

Perform a visual and an eddy current 

inspection to detect cracks and corrosion of 

Area 3 of the lower horizontal stabilizer 

cutout longeron, in accordance with Airbus 

Service Bulletin A300–53–6042, Revision 1, 

dated February 20, 1995; or Airbus 

Mandatory Service Bulletin A300–53–6042, 

Revision 03, dated August 30, 2012. As of the 

effective date of this AD, use only Airbus 

Mandatory Service Bulletin A300–53–6042, 

Revision 03, dated August 30, 2012, to do the 

actions required by this paragraph. 

(i) Prior to the accumulation of 24,000 total 

landings, but not before the accumulation of 

18,000 total landings; or 

(ii) Prior to the accumulation of 2,000 

landings after July 30, 1998 (the effective date 

of AD 98–13–23, Amendment 39–10614 (63 

FR 34576, June 25, 1998)). 

(3) If no cracking is detected during any 

inspection required by paragraph (g)(1) or 

(g)(2) of this AD: Before further flight, cold 

work and ream the vacated fastener holes, in 

accordance with Airbus Service Bulletin 

A300–53–6042, Revision 1, dated February 

20, 1995; or Airbus Mandatory Service 

Bulletin A300–53–6042, Revision 03, dated 

August 30, 2012; and perform the 

requirements of paragraph (g)(3)(i) or (g)(3)(ii) 

of this AD, as applicable. As of the effective 

date of this AD, use only Airbus Mandatory 

Service Bulletin A300–53–6042, Revision 03, 

dated August 30, 2012, to do the actions 

required by this paragraph. 

(i) For airplanes on which no cracking is 

found in Area 1 or 2: Repeat the inspections 

required by paragraph (g)(1) of this AD 

thereafter at intervals not to exceed 6,000 

flight cycles. 

(ii) For airplanes on which no cracking is 

found in Area 3: Perform the various followon actions in accordance with Airbus Service 

Bulletin A300–53–6042, Revision 1, dated 

February 20, 1995; or Airbus Mandatory 

Service Bulletin A300–53–6042, Revision 03, 

dated August 30, 2012. (The follow-on 

actions include installing a new corner 

fitting, installing a new longeron, and 

performing a cold working procedure.) After 

accomplishment of these follow-on actions, 

no further action is required by this AD. After 

the effective date of this AD, use only Airbus 

Mandatory Service Bulletin A300–53–6042, 

Revision 03, dated August 30, 2012, to do the 

actions required by this paragraph. 

(4) If any cracking is detected during any 

inspection required by paragraph (g)(1) or 

(g)(2) of this AD, perform the requirements of 

paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as 

applicable. 

(i) If any cracking is found in Area 1 or 3 

that is within the limits specified in Airbus 

Service Bulletin A300–53–6042, Revision 1, 

dated February 20, 1995; or Airbus 

Mandatory Service Bulletin A300–53–6042, 

Revision 03, dated August 30, 2012: Before 

further flight, repair in accordance with 

Airbus Service Bulletin A300–53–6042, 

Revision 1, dated February 20, 1995; or 

Airbus Mandatory Service Bulletin A300–53– 

6042, Revision 03, dated August 30, 2012. As 

of the effective date of this AD, use only 

Airbus Mandatory Service Bulletin A300–53– 

6042, Revision 03, dated August 30, 2012, to 

do the actions required by this paragraph. 

(ii) If any cracking is found in Area 2, or 

if any cracking is found in any area and that 

cracking is beyond the limits described in 

Airbus Service Bulletin A300–53–6042, 

Revision 1, dated February 20, 1995; or 

Airbus Mandatory Service Bulletin A300–53– 

6042, Revision 03, dated August 30, 2012: 

Before further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated agent, 

or by the Design Approval Holder (DAH) 

with EASA design organization approval). 

(5) If any corrosion is detected during any 

inspection required by paragraph (g) of this 

AD, prior to further flight, repair the 

corrosion, in accordance with Airbus Service 

Bulletin A300–53–6042, Revision 1, dated 

February 20, 1995; or Airbus Mandatory 

Service Bulletin A300–53–6042, Revision 03, 

dated August 30, 2012. As of the effective 

date of this AD, use only Airbus Mandatory 

Service Bulletin A300–53–6042, Revision 03, 

dated August 30, 2012, to do the actions 

required by this paragraph. 

(h) New Inspections 

At the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Airbus 

Mandatory Service Bulletin A300–53–6042, 

Revision 03, dated August 30, 2012, except 

as provided by paragraph (j)(1) and (j)(2) of 

this AD: Do the actions specified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD, in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–53–6042, Revision 03, dated 

August 30, 2012. Repeat the inspections, 

thereafter, at the applicable intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Airbus Mandatory Service Bulletin A300–53– 

6042, Revision 03, dated August 30, 2012. 

Doing the initial inspections required by 

paragraph (h) of this AD and applicable 

corrective actions required by paragraph (i) of 

this AD terminates the requirements of 

paragraph (g) of this AD. 

(1) Do a general visual inspection for 

cracking and corrosion of the lower 

horizontal stabilizer cut-out longeron, the 

corner fitting, the skin strap, and the skin 

between frame (FR)87 and FR89 and between 

stringers (STGR)24 and STGR27, left- and 

right-hand sides. 

(2) Do a high frequency eddy current 

(HFEC) inspection for cracking of the flanges 

of the lower corner fittings and the edges of 

the outer skin and the edges of the longeron, 

the skin strap, and the skin at the run-out of 

the corner fitting above the last eight 

fasteners. 

(3) Do a rotating probe inspection for 

cracking of the fastener holes. If no cracking 

is found during the rotating probe inspection, 

before further flight, do a cold expansion of 

the fastener holes, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–6042, 

Revision 03, dated August 30, 2012. 

(i) New Corrective Actions 

(1) If any corrosion is found during any 

inspection required by paragraph (h) of this 

AD, before further flight, repair, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–53–6042, Revision 03, dated 

August 30, 2012. 

(2) If any cracking is found during any 

inspection required by paragraph (h) of this 

AD, before further flight, repair in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–53– 

6042, Revision 03, dated August 30, 2012, 

except where Airbus Mandatory Service 

Bulletin A300–53–6042, Revision 03, dated 

August 30, 2012, specifies to contact Airbus, 

before further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated agent, 

or the Design Approval Holder (DAH) with 

EASA design organization approval). For a 

repair method to be approved, the repair 

approval must specifically refer to this AD. 

(j) Exception 

(1) Where Airbus Mandatory Service 

Bulletin A300–53–6042, Revision 03, dated 

August 30, 2012, specifies a grace period of 

1950 flight cycles or 4100 flight hours, this 


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AD specifies the grace period after the 

effective date of this AD. 

(2) Where Airbus Mandatory Service 

Bulletin A300–53–6042, Revision 03, dated 

August 30, 2012, specifies a compliance time 

‘‘after receipt of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

corresponding actions required by paragraph 

(g) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Service Bulletin A300–53–6042, 

Revision 01, dated February 20, 1995; or 

Airbus Service Bulletin A300–53–6042, 

Revision 02, dated April 28, 1998; which are 

not incorporated by reference in this AD. 

(l) 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 for AD 98–13–23, Amendment 39– 

10614 (63 FR 34576, June 25, 1998), are 

approved as AMOCs for the corresponding 

requirements 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). 

You are required to ensure the product is 

airworthy before it is returned to service. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2013–0048, dated 

March 4, 2013, for related information. This 

MCAI may be found in the AD docket on the 

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

searching for and locating it in Docket No. 

FAA–2014–0011. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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 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. 

Issued in Renton, Washington, on January 

27, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02711 Filed 2–7–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0004; Directorate 

Identifier 2013–NM–143–AD] 

RIN 2120–AA64 

Airworthiness Directives: Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A320–111, –211, –212, 

and –231 airplanes. This proposed AD 

was prompted by reports of broken 

struts of the center wing box (CWB). 

This proposed AD would require a 

detailed inspection of the CWB struts 

for cracking, and repair if necessary. We 

are proposing this AD to detect and 

correct cracked or broken struts, which 

could result in strut failure and 

consequent reduced structural integrity 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 27, 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, 

Airworthiness Office—EAS, 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 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. 

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–2014– 

0004; 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 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–227–1405; 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–2014–0004; Directorate Identifier 

2013–NM–143–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 


emcdonald on DSK67QTVN1PROD with PROPOSALS