22364 Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations 

821 4504060; fax: +49 821 419641; Internet: 

www.ballonbau.de. 

(4) You may view this service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on April 

4, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–08072 Filed 4–21–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1072; Directorate 

Identifier 2012–NM–164–AD; Amendment 

39–17828; AD 2014–08–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–03– 

04 for certain Airbus Model A310 series 

airplanes. AD 2012–03–04 required for 

certain airplanes, modifying the wire 

routing and installing additional 

protective sleeves. This new AD 

continues to require the actions in AD 

2012–03–04, and requires additional 

work for certain airplanes. This AD was 

prompted by reports of new 

interferences of newly routed wire 

bundle 2S. We are issuing this AD to 

prevent short circuits leading to arcing, 

and possible fuel tank explosion. 

DATES: This AD becomes effective May 

27, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 27, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of May 15, 2012 (77 FR 

21397, April 10, 2012). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-1072; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Airbus 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. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–03–04, 

Amendment 39–16945 (77 FR 21397, 

April 10, 2012). AD 2012–03–04 applied 

to certain Airbus Model A310 series 

airplanes. The NPRM published in the 

Federal Register on January 14, 2014 

(79 FR 2391). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0188, 

dated September 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: 

Within the scope of the Fuel System Safety 

Program (FSSP), analyses of the wire routing 

showed that the route 2S of the fuel electrical 

circuit in the Right Hand (RH) wing ensures 

insufficient segregation between fuel quantity 

indication wires and the 115 Volts 

Alternating Current (VAC) wires of route 2S 

which could, under certain conditions, lead 

to a short circuit and subsequent arcing, 

creating a potential ignition source in the fuel 

tank vapour space. 

This condition, if not detected, could result 

in a fuel tank explosion and consequent loss 

of the aeroplane. 

To address this potential unsafe condition, 

DGAC France issued [an] AD *** to require 

improvements of the design as specified in 

Airbus Service Bulletin (SB) A310–28–2148 

original issue or Revision 01. EASA AD 

2007–0230 [(http://ad.easa.europa.eu/blob/

easa_ad_2007_0230_Superseded.pdf/AD_

2007-0230_1)], which superseded [a] DGAC 

France AD ***, [which] required those same 

actions, plus additional work 1, as defined in 

Airbus SB A310–28–2148 Revision 02. 

Since EASA AD 2007–0230 was issued, an 

operator reported the possibility of chafing 

between the new routing of the wire bundle 

2S in the RH wing pylon area and the wire 

bundle of No.2 engine generator. The 

modification of this zone was introduced by 

Airbus SB A310–28–2148 Revision 02 as 

additional work 1. Investigation results 

showed that, to avoid the risk of chafing, the 

affected wiring harnesses must be installed at 

a higher position to provide sufficient 

clearance with the newly routed wire bundle 

2S conduit. 

Airbus published Revision 03 of SB A310– 

28–2148 to implement these changes as 

additional work 2. Subsequently, a new 

potential interference due to insufficient 

clearance was found, which prompted Airbus 

to issue SB A310–28–2148 Revision 04. 

Prompted by these findings and actions, 

EASA issued AD 2011–0005 [(http://

ad.easa.europa.eu/blob/easa_ad_2011_0005_

Superseded.pdf/AD_2011-0005_1)], retaining 

the requirements of EASA AD 2007–0230, 

which was superseded, and required the 

additional work 2 as specified in Revisions 

03 and 04 of Airbus SB A310–28–2148. 

Since EASA AD 2011–0005 was issued, 

several operators of aeroplanes not having 

been modified in-service through Airbus SB 

A310–36–2015, or without having Airbus 

modification 07633 applied in production, 

reported to have embodied Airbus SB A310– 

28–2148 at Revision 02 or Revision 03 on the 

aeroplane. However, the adequate 

instructions to avoid the new interferences 

were only introduced in Airbus SB A310–28– 

2148 Revision 04. 

For the reasons described above, this new 

[EASA] AD retains the requirements of EASA 

AD 2011–0005, which is superseded, and 

requires, for certain aeroplanes, the 

additional work 3 [segregating wire route 2S 

in the RH pylon area or modifying the wire 

routings] as defined in Airbus SB A310–28– 

2148 Revision 06. As SB A310–28–2148 

Revision 07 was issued to clarify the 

additional work 1, 2 and 3 [segregating wire 

route 2S in the RH pylon area or modifying 

the wire routings] for aeroplanes that have 

previously embodied that SB at original 

issue, Revision 01 or Revision 02, this AD 

also clarifies the required additional work. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-1072- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 2391, January 14, 2014) or on the 

determination of the cost to the public. 


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Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations 22365 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 2391, 

January 14, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 2391, 

January 14, 2014). 

Costs of Compliance 

We estimate that this AD affects 41 

airplanes of U.S. registry. 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modification [retained actions from AD 2012– 

03–04, Amendment 39–16945 (77 FR 

21397, April 10, 2012)].

62 work-hours × $85 per hour = $5,270 ........ $2,210 $7,480 $306,680 

Modification (additional work) [new action] ..... 32 work-hours × $85 per hour = $2,720 ........ 1,100 3,820 156,620 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov/ 

#!docketDetail;D=FAA-2013-1072; 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 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2012–03–04, Amendment 39–16945 (77 

FR 21397, April 10, 2012), and adding 

the following new AD: 

2014–08–04 Airbus: Amendment 39–17828. 

Docket No. FAA–2013–1072; Directorate 

Identifier 2012–NM–164–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 27, 2014. 

(b) Affected ADs 

This AD supersedes AD 2012–03–04, 

Amendment 39–16945 (77 FR 21397, April 

10, 2012). 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all certified models, all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by reports of new 

interferences of newly routed wire bundle 

2S. We are issuing this AD to prevent short 

circuits leading to arcing, and possible fuel 

tank explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification of Routing Wires 

With Revised Service Information 

This paragraph restates the modification 

required by paragraph (g) of AD 2012–03–04, 

Amendment 39–16945 (77 FR 21397, April 

10, 2012), with revised service information. 

For all airplanes except airplanes on which 

Airbus Service Bulletin A310–28–2148, 

Revision 02, dated March 9, 2007, has been 

done (Airbus Modifications 12427 and 

12435): Within 4,000 flight hours after 

September 3, 2004 (the effective date of AD 

2004–15–16, Amendment 39–13750 (69 FR 

45578, July 30, 2004)), modify the routing of 

wires in the right-hand (RH) wing by 

installing cable sleeves. Do the modification 

as per the Accomplishment Instructions of 

the service information specified in 

paragraph (g)(1), (g)(2), (g)(3), (g)(4), or (g)(5) 

of this AD. As of February 20, 2008 (the 

effective date of AD 2008–01–05, 

Amendment 39–15330 (73 FR 2795, January 

16, 2008)), only the service information 

specified in paragraphs (g)(2), (g)(3), (g)(4), 

and (g)(5) of this AD may be used. As of May 

15, 2012 (the effective date of AD 2012–03– 

04), only the service information specified in 

paragraphs (g)(3), (g)(4), and (g)(5) of this AD 

may be used. As of the effective date of this 


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22366 Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations 

AD, only the service bulletin specified in 

paragraph (g)(5) of this AD may be used. 

(1) Airbus Service Bulletin A310–28–2148, 

Revision 01, dated October 29, 2002. 

(2) Airbus Service Bulletin A310–28–2148, 

Revision 02, dated March 9, 2007. 

(3) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 05, dated August 3, 

2010. 

(4) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 06, dated August 

31, 2011. 

(5) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 07, dated February 

13, 2012. 

(h) Retained Modification of Protection 

Sleeves With Revised Service Information 

This paragraph restates the modification 

required by paragraph (i) of AD 2012–03–04, 

Amendment 39–16945 (77 FR 21397, April 

10, 2012), with revised service information. 

For airplanes on which the actions specified 

in Airbus Service Bulletin A310–28–2148, 

dated January 23, 2002; or Airbus Service 

Bulletin A310–28–2148, Revision 01, dated 

October 29, 2002; have been done before 

February 20, 2008 (the effective date of AD 

2008–01–05, Amendment 39–15330 (73 FR 

2795, January 16, 2008)), except for airplanes 

on which Airbus Service Bulletin A310–28– 

2148, Revision 02, dated March 9, 2007, has 

been done (Airbus Modifications 12427 and 

12435): Within 6,000 flight hours or 30 

months after February 20, 2008 (the effective 

date of AD 2008–01–05), whichever occurs 

first, perform further modification by 

installing additional protection sleeves in the 

outer wing area near the cadensicon sensor 

and segregating wire route 2S in the RH 

pylon area, in accordance with the 

Accomplishment Instructions of service 

information specified in paragraph (h)(1), 

(h)(2), (h)(3), or (h)(4) of this AD. As of May 

15, 2012 (the effective date of AD 2012–03– 

04), only the service information specified in 

paragraphs (h)(2), (h)(3), and (h)(4) of this AD 

may be used. As of the effective date of this 

AD, only the service bulletin specified in 

paragraph (h)(4) of this AD may be used. 

(1) Airbus Service Bulletin A310–28–2148, 

Revision 02, dated March 9, 2007. 

(2) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 05, dated August 3, 

2010. 

(3) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 06, dated August 

31, 2011. 

(4) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 07, dated February 

13, 2012. 

(i) Retained New Modification/Installation of 

Wire Routings for Certain Airplanes With 

Revised Service Information 

This paragraph restates the new 

modification/installation required by 

paragraph (j) of AD 2012–03–04, Amendment 

39–16945 (77 FR 21397, April 10, 2012), with 

revised service information. For airplanes on 

which the actions specified in Airbus Service 

Bulletin A310–28–2148, Revision 02, dated 

March 9, 2007, have been accomplished, and 

do not have production modification 07633; 

and on which Airbus Service Bulletin A310– 

36–2015 has not been done: Within 6,000 

flight hours or 30 months after May 15, 2012 

(the effective date of AD 2012–03–04), 

whichever occurs first, modify the wire 

routings, in accordance with the 

Accomplishment Instructions of the service 

information specified in paragraph (i)(1), 

(i)(2), or (i)(3) of this AD. As of the effective 

date of this AD, only the service bulletin 

specified in paragraph (i)(3) of this AD may 

be used. 

(1) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 05, dated August 3, 

2010. 

(2) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 06, dated August 

31, 2011. 

(3) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 07, dated February 

13, 2012. 

(j) Retained New Modification/Installation of 

Bracket for Certain Other Airplanes With 

Revised Service Information 

This paragraph restates the new 

modification/installation required by 

paragraph (k) of AD 2012–03–04, 

Amendment 39–16945 (77 FR 21397, April 

10, 2012), with revised service information. 

For airplanes on which the actions specified 

in Airbus Service Bulletin A310–28–2148, 

Revision 02, dated March 9, 2007, have been 

accomplished, and have production 

modification 07633; or on which Airbus 

Service Bulletin A310–36–2015 has been 

done: Within 1,000 flight hours after May 15, 

2012 (the effective date of AD 2012–03–04), 

install a modified bracket, in accordance 

with paragraph 3.B.(7), ‘‘Additional Work 2,’’ 

of the Accomplishment Instructions of the 

service information specified in paragraph 

(j)(1), (j)(2), or (j)(3) of this AD. As of the 

effective date of this AD, only the service 

bulletin specified in paragraph (j)(3) of this 

AD may be used. 

(1) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 05, dated August 3, 

2010. 

(2) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 06, dated August 

31, 2011. 

(3) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 07, dated February 

13, 2012. 

(k) Retained Modification/Installation 

Provision for Certain Airplanes 

This paragraph restates the modification/

installation provision specified in paragraph 

(l) of AD 2012–03–04, Amendment 39–16945 

(77 FR 21397, April 10, 2012). For airplanes 

on which the actions specified in Airbus 

Service Bulletin A310–28–2148, Revision 03, 

dated June 2, 2009, have been accomplished; 

and have modification 07633 done in 

production; or on which the actions specified 

in Airbus Service Bulletin A310–36–2015 

have been done; no further action is required 

by paragraphs (g) through (j) of this AD. 

(l) Retained Credit for Previous Actions 

(1) This paragraph restates the credit for 

previous actions required by paragraph (h) of 

AD 2012–03–04, Amendment 39–16945 (77 

FR 21397, April 10, 2012). This paragraph 

provides credit for the modification of the 

routing of wires required by paragraph (g) of 

AD 2012–03–04, if the modification was 

performed before September 3, 2004 (the 

effective date of AD 2004–15–16, 

Amendment 39–13750 (69 FR 45578, July 30, 

2004)), using Airbus Service Bulletin A310– 

28–2148, dated January 23, 2002. 

(2) This paragraph restates the credit for 

previous actions required by paragraph (m) of 

AD 2012–03–04, Amendment 39–16945 (77 

FR 21397, April 10, 2012). This paragraph 

provides credit for modifications required by 

paragraphs (g), (i), (j), and (k) of AD 2012– 

03–04, if the modifications were performed 

before May 15, 2012 (the effective date of AD 

2012–03–04), using Airbus Mandatory 

Service Bulletin A310–28–2148, Revision 04, 

dated April 14, 2010. 

(m) New Requirement of This AD: 

Additional Work 2 and 3 

For airplanes on which the actions 

specified in Airbus Service Bulletin A310– 

28–2148, Revision 02, dated March 9, 2007, 

have been accomplished, and on which the 

actions specified in Airbus Service Bulletin 

A310–36–2015 have not been done; or have 

Airbus Modification 07633 done in 

production: Within 1,000 flight hours or 12 

months after the effective date of this AD, 

whichever occurs first, do the modification, 

in accordance with paragraphs ‘‘Additional 

Work 2’’ and ‘‘Additional Work 3’’ of the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–28–2148, Revision 07, 

dated February 13, 2012. 

(n) New Requirement of This AD: Additional 

Work 3 

For airplanes on which the actions 

specified in Airbus Service Bulletin A310– 

28–2148, Revision 03, dated June 2, 2009, 

have been accomplished, and do not have 

production modification 07633 or Airbus 

Service Bulletin A310–36–2015 has not been 

done: Within 1,000 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first, do the modification, in 

accordance with paragraph ‘‘Additional 

Work 3’’ of the Accomplishment Instructions 

of Airbus Service Bulletin A310–28–2148, 

Revision 07, dated February 13, 2012. 

(o) New Requirement of This AD: Additional 

Work 1 and 2 

For airplanes on which the actions 

specified in Airbus Service Bulletin A310– 

36–2015 have not been accomplished and 

production modification 07633 has not been 

done, and that have done the actions 

specified in paragraphs (o)(1) and (o)(2) of 

this AD: Within 6,000 flight hours or 30 

months after the effective date of this AD, 

whichever occurs first, do the modification, 

in accordance with paragraphs ‘‘Additional 

Work 1’’ and ‘‘Additional Work 2’’ of the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–28–2148, Revision 07, 

dated February 13, 2012. 

(1) Modification in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–28–2148, dated 

January 23, 2002; or Airbus Service Bulletin 

A310–28–2148, Revision 01, dated October 

29, 2002. 

(2) Further modification by ‘‘Additional 

Work 3’’ of the Accomplishment Instructions 

of Airbus Service Bulletin A310–28–2148, 

Revision 06, dated August 31, 2011. 


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Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations 22367 

(p) 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. 

(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 by 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. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0188, dated September 19, 

2012, for related information. You may 

examine the MCAI in the AD docket on the 

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

#!documentDetail;D=FAA-2013-1072-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (r)(5) and (r)(6) of this 

AD. 

(r) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on May 27, 2014. 

(i) Airbus Service Bulletin A310–28–2148, 

Revision 07, dated February 13, 2012. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 15, 2012, (77 FR 

21397, April 10, 2012). 

(i) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 05, dated August 3, 

2010. 

(ii) Airbus Mandatory Service Bulletin 

A310–28–2148, Revision 06, dated August 

31, 2011. 

(5) 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. 

(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 April 4, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–08597 Filed 4–21–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0042; Directorate 

Identifier 2013–CE–050–AD; Amendment 

39–17823; AD 2014–07–09] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Regional Aircraft Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for British 

Aerospace Regional Aircraft Jetstream 

Series 3101 and Jetstream Model 3201 

airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as 

inadequate instructions for inspection 

for corrosion on the rudder upper hinge 

bracket and certain internal wing and 

drainage paths. We are issuing this AD 

to require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective May 27, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 27, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0042; or in person at Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

For service information identified in 

this AD, contact BAE Systems 

(Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 

2RW, Scotland, United Kingdom; 

telephone: +44 1292 675207; fax: +44 

1292 675704; email: RApublications@

baesystems.com; Internet: http://

www.baesystems.com/Businesses/

RegionalAircraft/. You may review this 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

FOR FURTHER INFORMATION CONTACT: 

Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4138; fax: (816) 329–4090; email: 

taylor.martin@faa.gov. 

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 British Aerospace Regional 

Aircraft Jetstream Series 3101 and 

Jetstream Model 3201 airplanes. The 

NPRM was published in the Federal 

Register on January 31, 2014 (79 FR 

5323). The NPRM proposed to correct 

an unsafe condition for the specified 

products and was based on mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country. The MCAI 

states: 

Compliance with the inspections in the 

Corrosion Prevention and Control Programme 

(CPCP) has been identified as a mandatory 

action for continued airworthiness and UK 

CAA AD 003–04–94 was issued to require 

operators to comply with those inspection 

instructions. 

Since the issuance of that AD, reports have 

been received of finding extensive corrosion 

on the rudder upper hinge bracket. Although 

there is an existing zonal inspection of the 

area in the CPCP, it has been concluded that 

this is inadequate to identify the corrosion on 

this bracket and consequently, a new specific 

inspection of the rudder upper hinge bracket, 


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