71996 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations 

(6) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

November 15, 2013. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

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

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0096; Directorate 

Identifier 2012–NM–143–AD; Amendment 

39–17566; AD 2013–17–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A318–112, A319–111, 

A319–112, A319–115, A319–132, and 

A319–133 airplanes. This AD was 

prompted by a report that a fastener, 

which connects the cargo door keel 

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

panel, was not installed on airplanes 

during production. This AD requires 

inspecting forward fuselage frame 24, 

stringer 39, right hand, to determine if 

the fastener is missing; measuring the 

hole dimensions of the five holes 

surrounding the missing fastener if 

necessary; and doing related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct the missing fastener, 

which could result in reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective 

January 6, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 6, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on March 4, 2013 (78 FR 

14029). The NPRM proposed to correct 

an unsafe condition for the specified 

products. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Airworthiness 

Directive 2012–0132, dated July 19, 

2012 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a ground inspection of an A319 

aeroplane in production, it was discovered 

that one fastener was missing at stringer 

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

[forward fuselage frame] 24 (Section 13–14 

side). The hole of the missing fastener was 

not drilled. The missing fastener, a 4.8 mm 

[millimeter] diameter titanium bolt, Part 

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

the cargo door keel beam foot to the 

circumferential butt-strap and the section 13– 

14 lower shell panel. Further investigations 

have revealed that the affected fastener has 

not been installed on a limited number of 

aeroplanes in production, due to incorrect 

production instructions. 

This condition, if not corrected, could 

impair the structural integrity of the affected 

aeroplanes. 

* * * * * 

The required actions include doing a 

detailed inspection to determine if the 

fastener is missing, measuring the hole 

dimensions of the five holes 

surrounding the missing fastener if 

necessary, and doing related 

investigative and corrective actions if 

necessary. The related investigative 

actions include a rototest inspection of 

the five holes for cracking. The 

corrective actions include repairing any 

holes with diameter values that exceed 

the specified dimensions, repairing any 

cracking found, and installing new 

fasteners. You may obtain further 

information by examining the MCAI in 

the AD docket on the Internet at http:// 

www.regulations.gov/

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

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Request To Refer to Revised EASA AD 

Airbus requested that paragraph (j) of 

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

be revised to refer to revised EASA AD 

2012–0132R1, dated March 1, 2013 

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

2012_0132_R1.pdf). 

We do not agree with the commenter’s 

request. EASA AD 2012–0132R1, dated 

March 1, 2013, was revised to clarify the 

configurations of the Airbus Model 

A318 and A319 airplanes included in 

table 1 of EASA AD 2012–0132R1, dated 

March 1, 2013. The clarifying text that 

EASA included in EASA AD 2012– 

0132R1, dated March 1, 2013, was 

designated in the NPRM (78 FR 14029, 

March 4, 2013) as ‘‘Table 1 to 

Paragraphs (g) and (h) of this AD.’’ 

We have re-designated the material in 

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

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

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

this final rule. This change does not 

affect the intent of this AD. In addition, 

we revised references to ‘‘Table 1 to 

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

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

NPRM to instead refer to paragraphs 

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

change was made to this final rule with 

respect to the commenter’s request to 

revise paragraph (j) of this final rule. 

Request To Allow Credit for Actions 

Previously Accomplished Using 

Previous Revisions of the Service 

Information 

Airbus requested that table 1 to 

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

FR 14029, March 4, 2013) be revised to 

provide credit for actions that are 

accomplished before the effective date 

of this AD using Airbus Service Bulletin 

A320–00–1219 dated November 9, 2010; 

Revision 01, dated December 8, 2010; 

Revision 02, dated September 6, 2011; 

or Revision 03, dated March 28, 2012. 

We do not agree with the commenter’s 

request. As stated previously, the 

material in table 1 to paragraphs (g) and 

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

4, 2013) has been re-designated as 

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

this final rule. Those paragraphs do not 

mandate accomplishing any actions 

using Airbus Service Bulletin A320–00– 


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Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations 71997 

1219. That service information is only 

referenced to provide guidance to 

operators regarding certain 

configurations of Model A318 and A319 

airplanes. No change was made to this 

final rule with regard to the 

commenter’s request. 

Request To Revise Airbus Contact 

Information 

Airbus requested that we revise the 

contact information for the Airbus office 

of airworthiness from EAS to EIAS. 

We agree with the request and have 

included the revised contact 

information in paragraph (k)(3) of this 

final rule. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

14029, March 4, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 14029, 

March 4, 2013). 

Costs of Compliance 

We estimate that this AD affects about 

3 products of U.S. registry. We also 

estimate that it takes about 26 work 

hours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work hour. 

Required parts cost $1,904 per product. 

Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these parts. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

up to $12,342, or $4,114 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0096; or in 

person at the Docket Operations office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, the 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2013–17–02 Airbus: Amendment 39–17566. 

Docket No. FAA–2013–0096; Directorate 

Identifier 2012–NM–143–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 6, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A318– 

112, A319–111, A319–112, A319–115, A319– 

132, and A319–133 airplanes; certificated in 

any category; manufacturer serial numbers 

3983, 3985, 3998, 4000, 4004, 4007, 4018, 

4020, 4029, 4036, 4038 through 4040 

inclusive, 4048, 4052, 4056, 4069, 4071, 

4076, 4080, 4087, 4089, 4121, 4125, 4127, 

4129, 4132, 4141, 4151, 4163, 4164, 4166, 

4169, 4171, 4182, 4192, 4200, 4204, 4211, 

4215, 4222, 4227, 4228, 4254, 4256, 4258, 

4259, 4262, 4268, 4275, 4282, 4285, 4287, 

4301, 4313, 4319, 4327, 4332, and 4336. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report that a 

fastener, which connects the cargo door keel 

beam foot to the circumferential butt-strap 

and the section 13–14 lower shell panel, was 

not installed on airplanes during production. 

We are issuing this AD to detect and correct 

the missing fastener, which could result in 

reduced structural integrity of the airplane. 

(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) Inspections 

At the applicable time specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD: 

Do a detailed inspection at forward fuselage 

frame 24, stringer 39, right hand, to 

determine if the fastener is missing, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1242, dated May 22, 2012. 

(1) For Model A319 airplanes, except 

manufacturer serial numbers 4151, 4228, and 

4319; and Model A318 airplanes, premodification 39195, and on which the 

actions specified in Airbus Service Bulletin 

A320–00–1219 have not been embodied in 

service: Inspect before the accumulation of 

5,000 total flight cycles since first flight of 

the airplane, or within 4,300 flight cycles 

after the effective date of this AD, whichever 

occurs later. 

(2) For Model A318 airplanes, postmodification 39195; and Model A318 

airplanes on which the actions specified in 

Airbus Service Bulletin A320–00–1219 have 

been embodied in service: Inspect before the 


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71998 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations 

accumulation of 3,000 total flight cycles 

since first flight of the airplane, or within 90 

days after the effective date of this AD, 

whichever occurs later. 

(3) For Model A319 airplanes, 

manufacturer serial numbers 4151, 4228, and 

4319 (post-modification 28238, 28162, and 

28342): Inspect before the accumulation of 

2,500 total flight cycles since first flight of 

the airplane, or within 90 days after the 

effective date of this AD, whichever occurs 

later. 

(h) Measurements and Corrective Actions 

If, during any inspection required by 

paragraph (g) of this AD, the fastener is 

determined to be missing, within the 

applicable compliance time specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD: 

Measure the hole dimensions of the five 

holes surrounding the missing fastener, and 

do all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1242, dated May 

22, 2012; except where the service bulletin 

specifies to contact Airbus, before further 

flight, repair using a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent). Do 

all applicable related investigative and 

corrective actions before further flight. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2012–0132, dated 

July 19, 2012, for related information, which 

can be found in the AD docket on the 

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

#!documentDetail;D=FAA-2013-0096-0002. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–53–1242, 

dated May 22, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

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

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

9, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–28170 Filed 11–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0700; Directorate 

Identifier 2013–NM–102–AD; Amendment 

39–17676; AD 2013–24–02] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by 

reports of fractured rudder pedal tubes 

installed on the pilot-side rudder bar 

assembly. This AD requires repetitive 

inspections for cracking and damage of 

both pilot-side rudder pedal tubes, and 

replacement of affected pilot-side 

rudder bar assemblies if necessary. We 

are issuing this AD to detect and correct 

cracking of both pilot-side rudder pedal 

tubes, which could result in loss of pilot 

rudder pedal input causing reduced yaw 

controllability or a runway excursion. 

DATES: This AD becomes effective 

January 6, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 6, 2014. 

ADDRESSES: You may examine the AD 

on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0700 or in 

person at the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

5000; fax 514–855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7331; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on August 26, 2013 (78 FR 

52712). The NPRM proposed to correct 

an unsafe condition for the specified 

products. Transport Canada Civil 

Aviation (TCCA), which is the aviation 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2013–12, dated May 14, 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: 


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