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

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

7257 

Vol. 78, No. 22 

Friday, February 1, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1074; Directorate 

Identifier 2012–NM–027–AD; Amendment 

39–17331; AD 2013–02–10] 

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 all 

Airbus Model A330–200 Freighter series 

airplanes; Model A330–200 and –300 

series airplanes; and Model A340–200 

and –300 series airplanes. This AD was 

prompted by a report of a manufacturing 

defect in certain rods installed in the 

belly fairing, which could lead to cracks 

at the crimped end of the rod. This AD 

requires an inspection of the rods to 

determine the manufacturer; and for 

affected parts, an inspection for any 

cracking of the rods, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct cracking of the rods, 

which could result in rupture of rods 

that attach the belly fairing to the 

airframe, leading to separation of the 

belly fairing from the airframe, and 

consequent damage to airplane structure 

and airplane systems. 

DATES: This AD becomes effective 

March 8, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 8, 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 October 16, 2012 (77 FR 

63264). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

A rod manufacturing process defect has 

been identified at the supplier, Technical 

Airborne Components Industries (TAC), 

which could lead to cracks at the crimped 

end of the rod. 

A design review of all affected rods has 

demonstrated that rupture of rods which 

attach the belly fairing can lead to separation 

of the belly fairing from the airframe, which 

would constitute an unsafe condition. 

For the reasons described above, this 

[European Aviation Safety Agency (EASA)] 

AD requires detailed visual inspections of the 

21 affected rods installed in the belly fairing 

for manufacturer identification, and if TAC is 

identified as manufacturer, or if the 

manufacturer cannot be identified, to further 

inspect the rods to find any crack, using a 

high frequency eddy current (HFEC) method 

and, depending on findings, accomplishment 

of the applicable [related investigative and] 

corrective actions, to ensure structural 

integrity of the belly fairing rods. This 

[EASA] AD also prohibits installation of an 

affected TAC rod as replacement part in the 

belly fairing to all aeroplanes. 

A design review of all affected rods has 

demonstrated that rupture of rods that 

attach the belly fairing can lead to 

separation of the belly fairing from the 

airframe, which can cause damage to 

airplane structure and airplane systems. 

The related investigative actions include 

an inspection to determine the 

manufacturer and an HFEC inspection 

of any affected replacement rod for any 

cracking. The corrective actions include 

replacing the cracked rod with a new 

rod. 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 63264, October 16, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the 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 (77 FR 

63264, October 16, 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 63264, 

October 16, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

54 products of U.S. registry. We also 

estimate that it will take about 13 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $59,670, or $1,105 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 28 work-hours and require parts 

costing $0, for a cost of $2,380 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. We have no way of 

determining the number of products 

that may need these actions. 

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, 


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7258 Federal Register / Vol. 78, No. 22 / Friday, February 1, 2013 / Rules and Regulations 

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 63264, 

October 16, 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: 

2013–02–10 Airbus: Amendment 39–17331. 

Docket No. FAA–2012–1074; Directorate 

Identifier 2012–NM–027–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective March 8, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

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

–223, –223F, –243, –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

manufacturing defect in certain rods installed 

in the belly fairing, which could lead to 

cracks at the crimped end of the rod. We are 

issuing this AD to detect and correct cracking 

of the rods, which could result in rupture of 

rods that attach the belly fairing to the 

airframe, leading to separation of the belly 

fairing from the airframe, and consequent 

damage to airplane structure and airplane 

systems. 

(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) Actions 

For Model A330–201, –202, –203, –223, 

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

–322, –323, –341, –342, and –343 airplanes, 

having manufacturer serial number (MSN) 

0002 to 1113 inclusive, except MSN 0996, 

1039, 1054, 1059, 1105, 1107, 1108 and 1112; 

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

–312, and –313 airplanes: Within 72 months 

after the effective date of this AD, accomplish 

the actions in paragraphs (g)(1) and (g)(2) of 

this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–53–3186, 

Revision 01, dated April 7, 2011 (for Model 

A330 airplanes); or A340–53–4185, Revision 

01, dated April 7, 2011 (for Model A340 

airplanes). 

(1) Do a detailed inspection of the 21 rods 

of the belly fairing identified in Airbus 

Mandatory Service Bulletin A330–53–3186, 

Revision 01, dated April 7, 2011 (for Model 

A330 airplanes); or A340–53–4185, Revision 

01, dated April 7, 2011 (for Model A340 

airplanes); for rod manufacturer 

identification. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the manufacturer of the 

rods can be conclusively determined from 

that review. 

(2) If the rod manufacturer is found to be 

Technical Airborne Components Industries 

(TAC), or if the manufacturer cannot be 

identified, do a high frequency eddy current 

(HFEC) inspection for cracking of the 

crimped end of the rod body and, if any crack 

is found, before further flight, do all 

applicable related investigative and 

corrective actions. 

(h) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install any affected TAC rod, as 

identified in Airbus Mandatory Service 

Bulletin A330–53–3186, Revision 01, dated 

April 7, 2011; or A340–53–4185, Revision 01, 

dated April 7, 2011; as applicable; on any 

airplane unless the rod has passed (found to 

have no cracking) the inspection as required 

by paragraph (g)(2) of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

inspections and corrective actions required 

by paragraph (g) of this AD, if those actions 

were performed before the effective date of 

this AD using Airbus Mandatory Service 

Bulletin A330–53–3186, dated January 17, 

2011 (for Model A330 airplanes); or A340– 

53–4185, dated January 17, 2011 (for Model 

A340 airplanes); which are not incorporated 

by reference in this AD. 

(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 


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Federal Register / Vol. 78, No. 22 / Friday, February 1, 2013 / Rules and Regulations 7259 

(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 Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2012–0005, dated 

January 10, 2012, and the Airbus service 

information identified in paragraphs (k)(1)(i) 

and (k)(1)(ii) of this AD, for related 

information. 

(i) Airbus Mandatory Service Bulletin 

A330–53–3186, Revision 01, dated April 7, 

2011. 

(ii) Airbus Mandatory Service Bulletin 

A340–53–4185, Revision 01, dated April 7, 

2011. 

(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. You may 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

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

(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 

A330–53–3186, Revision 01, dated April 7, 

2011. 

(ii) Airbus Mandatory Service Bulletin 

A340–53–4185, Revision 01, dated April 7, 

2011 

(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 January 

16, 2013. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–01822 Filed 1–31–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1040; Directorate 

Identifier 2012–NM–029–AD; Amendment 

39–17330; AD 2013–02–09] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (OPERATIONS) LIMITED 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all BAE 

SYSTEMS (OPERATIONS) LIMITED 

Model BAe 146, and Avro 146–RJ series 

airplanes. This AD was prompted by a 

report of loss of the end caps on the 

anti-icing piccolo tube of the wing 

leading edge. This AD requires a 

detailed inspection of the end caps on 

the anti-icing piccolo tube for lost or 

loose end caps, and replacing or 

repairing the end caps if necessary. We 

are issuing this AD to detect and correct 

lost and loose end caps on the anti-icing 

piccolo tube, and ice accretion on the 

wing leading edge or run-back ice, 

which could lead to a reduction in the 

stall margin on approach and loss of 

controllability of the airplane. 

DATES: This AD becomes effective 

March 8, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 8, 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1175; 

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 October 4, 2012 (77 FR 

60651). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

An operator reported the loss of the wing 

leading edge anti-icing piccolo tube end caps 

on two aircraft. This was discovered during 

routine zonal inspections when the wing tips 

were removed. The loss of the end cap would 

result in a reduction in anti-icing efficiency, 

over the outboard portion of the leading edge 

of that wing, affecting approximately 25% of 

the wingspan towards the wing tip. 

The System Safety Analysis (SSA) 

classifies the loss of anti-icing of both of the 

outer wings as hazardous if the loss is not 

indicated to the crew. The loss of a piccolo 

tube end cap would not be indicated to the 

flight crew and, therefore, this reduction in 

anti-icing capability on one wing must also 

be classified as hazardous. 

This condition, if not detected and 

corrected, could result in ice accretion on the 

wing leading edge, or run-back ice and could 

lead to a reduction in the stall margin on 

approach together with a reduction in roll 

control authority. 

For the reasons described above, this 

[European Aviation Safety Agency (EASA)] 

AD [2012–0003, dated January 6, 2012] 

requires a one-off [detailed] inspection [for 

lost and loose end caps] of the piccolo tube 

end caps. The results of this inspection will 

be used to establish a suitable repeat 

inspection period, which will be introduced 

through the Maintenance Review Board 

(MRB) process. 

The corrective action is replacing or 

repairing the end caps if necessary. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Clarification of ‘‘No Reporting 

Requirement’’ Paragraph 

Paragraph (i) of the NPRM (77 FR 

60651, October 4, 2012) refers to EASA 

AD 2012–0003, dated January 6, 2012. 

However, we have revised paragraph (i) 

of this AD to refer to BAE SYSTEMS 

(OPERATIONS) LIMITED Inspection 

Service Bulletin ISB.30–025, dated 

April 19, 2011, because that service 

bulletin is the appropriate source of 

service information for doing the actions 

required by this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 60651, October 4, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes and clarification of paragraph 

(i) of this AD. We have determined that 

these minor changes: 


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