This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

17071 

Vol. 78, No. 54 

Wednesday, March 20, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1160; Directorate 

Identifier 2012–NM–096–AD; Amendment 

39–17381; AD 2013–05–09] 

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 A330–200, –300, and 

–200 Freighter series airplanes; and all 

Airbus Model A340–200 and –300 series 

airplanes. This AD was prompted by a 

determination that the bonding lead 

from a certain isolation valve to a frame 

was too close to an electrical harness, 

which might cause chafing between the 

electrical harness and the associated 

bonding lead. This chafing could lead to 

a short circuit of the isolation valve and 

consequent non-closure of the isolation 

valve, which would prevent the air flow 

to be shut off in case of fire. This AD 

requires modifying the bonding lead 

installation of the isolation valve. We 

are issuing this AD to prevent such 

chafing, which could result in nonclosure of the isolation valve in the 

event of a fire and consequent damage 

to the airplane and injury to its 

occupants. 

DATES: This AD becomes effective April 

24, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 24, 2013. 

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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

fax (425) 227–1149. 

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. That 

NPRM was published in the Federal 

Register on November 7, 2012 (77 FR 

66764). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

It was noticed in production that the 

bonding lead from the isolation valve 283HN 

to Frame (FR) 64, between Stringer (STGR) 33 

and STGR 34, was too close to the electrical 

harness 5871VB. The results of the technical 

investigations carried out by Airbus 

determined that this insufficient clearance 

may cause chafing between the electrical 

harness 5871VB and the associated bonding 

lead. 

This condition, if not corrected, could lead 

to a short circuit of the isolation valve and 

consequent non-closure of the isolation valve 

283HN, which would prevent the air flow to 

be shut-off in case of fire, potentially 

resulting in damage to the aeroplane and 

injury to its occupants. 

For the reasons described above, this 

European Aviation Safety Agency (EASA) AD 

requires the installation of a new bonding 

bracket and new bonding lead at STGR33, 

between FR64 and FR65 introduced by 

Airbus modification (mod.) 201500, or mod. 

201681 in production, or Airbus Service 

Bulletin (SB) A330–21–3165, SB A330–21– 

3160 or SB A340–21–4152 in service. 

In addition, for aeroplanes already 

modified in accordance with the instructions 

of Airbus SB A330–21–3165, SB A330–21– 

3160 or SB A340–21–4152 at original issue 

or Revision 01, it [this EASA AD] requires 

accomplishment of the additional work 

(additional wiring connected to the structure 

of the aeroplane). 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 66764, November 7, 2012) or on the 

determination of the cost to the public. 

Actions Since the NPRM (77 FR 66764, 

November 7, 2012) Was Issued 

Since the NPRM (77 FR 66764, 

November 7, 2012) was issued, Airbus 

has issued Mandatory Service Bulletin 

A330–21–3165, Revision 03, dated 

December 7, 2012 (for Model A330–201, 

–202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and 

–343 airplanes); and Mandatory Service 

Bulletin A340–21–4152, Revision 03, 

dated December 7, 2012 (for Model 

A340–211, –212, –213, –311, –312, and 

–313 airplanes). No additional work is 

required by these revisions for airplanes 

modified by Airbus Mandatory Service 

Bulletin A330–21–3165, Revision 02, 

dated March 29, 2012; or Airbus 

Mandatory Service Bulletin A340–21– 

4152, Revision 02, dated March 29, 

2012; as applicable. 

We have changed paragraphs (g), (h), 

and (k) (which was identified as 

paragraph (j) in the NPRM (77 FR 66764, 

November 7, 2012)) of this AD to refer 

to Airbus Mandatory Service Bulletin 

A330–21–3165, Revision 03, dated 

December 7, 2012; and Airbus 

Mandatory Service Bulletin A340–21– 

4152, Revision 03, dated December 7, 

2012. We also have added new 

paragraph (i) to this AD to give credit for 

actions accomplished before the 

effective date of this AD performed 

using previous service information and 

have re-identified subsequent 

paragraphs accordingly. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

except for minor editorial changes. We 

have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

66764, November 7, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 66764, 

November 7, 2012). 


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17072 Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations 

Costs of Compliance 

We estimate that this AD will affect 

58 products of U.S. registry. We also 

estimate that it will take about 6 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $66 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 

to the U.S. operators to be $33,408, or 

$576 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; 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 the NPRM (77 FR 66764, 

November 7, 2012), 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. 

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: 

2013–05–09 Airbus: Amendment 39–17381. 

Docket No. FAA–2012–1160; Directorate 

Identifier 2012–NM–096–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 24, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category. 

(1) Model A330–201, –202, –203, –223, 

–243, –301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes, all 

manufacturer serial numbers, except for 

airplanes on which Airbus modification 

201500 has been embodied in production. 

(2) Model A330–223F and –243F airplanes, 

all manufacturer serial numbers, except for 

airplanes on which Airbus modification 

201681 has been embodied in production. 

(3) Model A340–211, –212, –213, –311, 

–312, and –313 airplanes, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 21, Air conditioning. 

(e) Reason 

This AD was prompted by a determination 

that the bonding lead from a certain isolation 

valve to a frame was too close to an electrical 

harness, which might cause chafing between 

the electrical harness and the associated 

bonding lead. This chafing could lead to a 

short circuit of the isolation valve and 

consequent non-closure of the isolation 

valve, which would prevent the air flow to 

be shut off in case of fire. We are issuing this 

AD to prevent such chafing, which could 

result in non-closure of the isolation valve in 

the event of a fire and consequent damage to 

the airplane and injury to its occupants. 

(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) Bonding Lead Installation Modification 

Within 48 months after the effective date 

of this AD, modify the bonding lead 

installation of isolation valve 283HN, in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

specified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD. 

(1) Airbus Mandatory Service Bulletin 

A330–21–3165, Revision 03, dated December 

7, 2012 (for Model A330–201, –202, –203, 

–223, –243, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes). 

(2) Airbus Mandatory Service Bulletin 

A330–21–3160, dated August 4, 2011 (for 

Model A330–223F and –243F airplanes). 

(3) Airbus Mandatory Service Bulletin 

A340–21–4152, Revision 03, dated December 

7, 2012 (for Model A340–211, –212, –213, 

–311, –312, and –313 airplanes). 

(h) Bonding Lead Additional Work 

Modification 

For airplanes that have already been 

modified prior to the effective date of this 

AD, as specified in Airbus Mandatory Service 

Bulletin A330–21–3165, dated September 27, 

2011, or Mandatory Service Bulletin A330– 

21–3165, Revision 01, dated November 21, 

2011; or Airbus Mandatory Service Bulletin 

A340–21–4152, dated September 27, 2011, or 

Airbus Mandatory Service Bulletin A340–21– 

4152, Revision 01, dated November 21, 2011: 

Within 48 months after the effective date of 

this AD, perform the ‘‘Additional Work’’ 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–21–3165, Revision 03, dated 

December 7, 2012; or Airbus Mandatory 

Service Bulletin A340–21–4152, Revision 03, 

dated December 7, 2012; as applicable. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus 

Mandatory Service Bulletin A330–21–3165, 

Revision 02, dated March 29, 2012; or Airbus 

Mandatory Service Bulletin A340–21–4152, 

Revision 02, dated March 29, 2012; as 

applicable; which are not incorporated by 

reference in this AD. 


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Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations 17073 

(j) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; 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. 

(k) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2012– 

0090, dated May 22, 2012, and the following 

service information, for related information. 

(i) Airbus Mandatory Service Bulletin 

A330–21–3160, dated August 4, 2011. 

(ii) Airbus Mandatory Service Bulletin 

A330–21–3165, Revision 03, dated December 

7, 2012. 

(iii) Airbus Mandatory Service Bulletin 

A340–21–4152, Revision 03, dated December 

7, 2012. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(l) 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 the AD specifies otherwise. 

(i) Airbus Mandatory Service Bulletin 

A330–21–3160, dated August 4, 2011. 

(ii) Airbus Mandatory Service Bulletin 

A330–21–3165, Revision 03, dated December 

7, 2012. 

(iii) Airbus Mandatory Service Bulletin 

A340–21–4152, Revision 03, dated December 

7, 2012. 

(3) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. 

(4) You may review copies of the 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 March 1, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05836 Filed 3–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0641; Directorate 

Identifier 2011–NM–258–AD; Amendment 

39–17378; AD 2013–05–06] 

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–600–2A12 

(CL–601) and CL–600–2B16 (CL–601– 

3A, CL–601–3R, and CL–604 Variants) 

airplanes. This AD was prompted by 

reports of jamming/malfunctioning of 

the left-hand engine thrust control 

mechanism. This AD requires modifying 

the left-hand engine upper core-cowl. 

We are issuing this AD to prevent 

jamming/malfunctioning of the lefthand engine thrust control mechanism, 

which could lead to loss of control of 

the airplane. 

DATES: This AD becomes effective April 

24, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 24, 2013. 

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: 

Mazdak Hobbi, Aerospace Engineer, 

Propulsion and Services Branch, ANE– 

173, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Westbury, NY 11590; 

telephone (516) 228–7330; 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. That 

NPRM was published in the Federal 

Register on June 21, 2012 (77 FR 37342). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

There have been several reported incidents 

of jamming/malfunctioning of the left hand 

(L/H) engine thrust control mechanism on 

the affected aeroplanes. The investigation has 

shown that an improperly stowed or 

dislodged upper core-cowl-door Hold Open 

Rod, can impede a Fuel Control Unit (FCU) 

function by obstructing the movement of the 

FCU actuating lever arm, hence rendering the 

L/H engine thrust control inoperable. 

Due to the engine’s orientation, the subject 

FCU fouling is limited only to the L/H engine 

installation on the affected twin engine 

powered aeroplanes; however the potential 

hazard of any in-flight engine shut down 

caused by jammed engine fuel control lever 

is a safety concern that warrants mitigating 

action. 

In order to help alleviate the possibility of 

an in-flight engine shut down due to the 

subject fouling of the FCU lever by the corecowl-door Hold Open Rod, Bombardier has 

issued three Service Bulletins to [modify the 

L/H engine upper core cowl by] install[ing] 

a new bracket at the L/H engine upper corecowl-door location. This [Canadian] directive 

is issued to mandate the incorporation of the 

Service Bulletins 604–71–005, 601–0609 or 

605–71–002, as applicable on the affected 

aeroplanes. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Request To Revise Unsafe Condition 

Bombardier, Inc. requested that we 

revise the end of the unsafe condition 

sentence in the SUMMARY section and 

paragraph (e) of the NPRM (77 FR 


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