Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 21227 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0111; Directorate 

Identifier 2011–NM–089–AD; Amendment 

39–17407; AD 2013–07–03] 

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, A330–200 

Freighter, A330–300, A340–200, and 

A340–300 series airplanes; and Model 

A340–541 airplanes and Model A340– 

642 airplanes. This AD was prompted 

by reports of cracks in the bogie pivot 

pin caused by material heating due to 

friction between the bogie pivot pin and 

bush, leading to chrome detachment 

and chrome dragging on the bogie pivot 

pin. This AD requires repetitive detailed 

inspections for degradation of the bogie 

pivot pins and for any cracks and 

damage of the pivot pin bushes of the 

main and central landing gear; a 

magnetic particle inspection of the 

affected bogie pivot pins for corrosion 

and base metal cracks; and repairing or 

replacing bogie pivot pins and pivot pin 

bushes, if necessary. We are issuing this 

AD to detect and correct cracks and 

damage to the main and central landing 

gear, which could result in the collapse 

of the landing gear and adversely affect 

the airplane’s continued safe flight and 

landing. 

DATES: This AD becomes effective May 

15, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 15, 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, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an AD 

that would apply to the specified 

products. That SNPRM was published 

in the Federal Register on September 7, 

2012 (77 FR 55163). That SNPRM 

proposed to correct an unsafe condition 

for the specified products. The 

Mandatory Continuing Airworthiness 

Information (MCAI) states: 

During removals of A330/340 Main 

Landing Gear (MLG) Bogie Beams and A340– 

500/600 Center Landing Gear (CLG) Bogie 

Beams, cracks in the bogie pivot pin were 

found. 

Investigations indicated that these findings 

were the result of material heating, caused by 

friction between bogie pivot pin and bush, 

leading to chrome detachment and stress 

corrosion cracking. 

This condition, if not detected and 

corrected, could lead to collapse of the main 

or center landing gear, possibly resulting in 

damage to the aeroplane and/or injury to 

occupants. 

As a precautionary measure, EASA 

[European Aviation Safety Agency] issued 

AD 2011–0040 to require a one-time 

[detailed] inspection of the MLG (all types of 

A330 and A340 aeroplanes) and CLG (A340– 

500/600 aeroplanes only) to detect 

degradation or cracking of the bogie pivot pin 

[and to detect cracks and damage of the 

bushes], as applicable to aeroplane model, 

and the reporting of inspections results. 

Following issuance of EASA AD 2011– 

0040, several operators reported finding 

chrome detachment or chrome dragging on 

bogie pivot pin. New cases of cracks were 

also reported. It has been confirmed as well 

that, due to similar design, the enhanced 

MLG bogie pivot pin (Airbus modification 

54500) could also be affected by this 

condition. 

Prompted by these findings, Airbus have 

developed an inspection programme 

consisting of repetitive inspections of the 

bogie pivot pin and applicable corrective 

actions. 

For the reasons described above, this 

[EASA] AD, which supersedes EASA AD 

2011–0040 and extends the applicability to 

all A330 and A340 aeroplanes, requires 

accomplishment of repetitive inspections of 

the MLG and CLG (for A340–500 and A340– 

600 aeroplanes) bogie pivot pins and pivot 

pin bushes, and corrective actions, 

depending on findings. 

Required actions also include, for 

certain airplanes, a magnetic particle 

inspection of the bogie pivot pin for 

corrosion and base metal cracks. The 

corrective actions include replacing any 

cracked or damaged pivot pin bush with 

a new or serviceable pivot pin bush, and 

replacing any corroded or cracked bogie 

pin with a new bogie pin. 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 comments received. 

Request To Change the Compliance 

Time 

Delta Air Lines, Inc. (DAL) requested 

that the initial compliance time in 

paragraph (g) of the SNPRM (77 FR 

55163, September 7, 2012) be changed 

from ‘‘* * * first flight of the airplane,’’ 

to ‘‘* * * first flight of the new or 

overhauled landing gear,’’ in two 

locations in that paragraph. The 

commenter did not provide rationale for 

this request. 

We disagree with DAL’s request. Our 

compliance time coincides with EASA 

AD 2012–0053, dated March 30, 2012, 

which specifically states, 

‘‘Accomplishment of an overhaul of the 

landing gear does not substitute the 

accomplishment of an inspection as 

required by paragraph (1) of this [EASA] 

AD.’’ The inspections required by this 

final rule are not equivalent to what is 

accomplished during landing gear 

overhaul. However, if the inspections 

required by this final rule are positively 

verified to have been accomplished 

during overhaul, the overhaul date may 

be used to determine the next repetitive 

inspection date. We have not changed 

this final rule in this regard. 

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 SNPRM (77 FR 

55163, September 7, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (77 FR 55163, 

September 7, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

29 products of U.S. registry. We also 

estimate that it will take about 22 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 $54,230, or $1,870 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 6 work-hours and require parts 

costing $21,222, for a cost of $21,732 

per product. We have no way of 

determining the number of products 

that may need these actions. 

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21228 Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 

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 SNPRM (77 FR 55163, 

September 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: 

2013–07–03 Airbus: Amendment 39–17407. 

Docket No. FAA–2012–0111; Directorate 

Identifier 2011–NM–089–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 15, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –223F, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; Model A340–211, 

–212, –213, –311, –312, and –313 airplanes; 

and Model A340–541 and Model A340–642 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by reports of cracks 

in the bogie pivot pin caused by material 

heating due to friction between the bogie 

pivot pin and bush, leading to chrome 

detachment and chrome dragging on the 

bogie pivot pin. We are issuing this AD to 

detect and correct cracks and damage to the 

main and central landing gear, which could 

result in the collapse of the landing gear and 

adversely affect the airplane’s continued safe 

flight and landing. 

(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) Detailed Inspection 

Within 26 months after the effective date 

of this AD or 26 months after the first flight 

of the airplane, whichever occurs later, but 

no earlier than 12 months after the first flight 

of the airplane: Do a detailed inspection for 

degradation (i.e., loss of chromium plate, 

loose chromium, sharp edges) of the bogie 

pivot pins and for any cracks and damage of 

the pivot pin bushes of the main landing 

gear, and, as applicable, the central landing 

gear, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin specified in 

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

Repeat the inspection thereafter at intervals 

not to exceed 26 months. Accomplishment of 

an overhaul of the landing gear does not 

substitute the accomplishment of the 

inspection as required by this paragraph. 

(1) Airbus Mandatory Service Bulletin 

A330–32–3240, Revision 02, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A330–200 series airplanes, 

Model A330–200 Freighter series airplanes, 

and Model A330–300 series airplanes). 

(2) Airbus Mandatory Service Bulletin 

A340–32–4281, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A340–200 series airplanes 

and Model A340–300 series airplanes). 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A340–541 airplanes and 

Model A340–642 airplanes). 

(h) Corrective Action for Any Pivot Pin Bush 

Found Cracked or Damaged 

If, during any inspection required by 

paragraph (g) of this AD, any pivot pin bush 

is found cracked or damaged: Before further 

flight, repair or replace the pivot pin bush 

with a new or serviceable pivot pin bush, in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

specified paragraph (h)(1), (h)(2), or (h)(3) of 

this AD. 

(1) Airbus Mandatory Service Bulletin 

A330–32–3240, Revision 02, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A330–200 series airplanes, 

Model A330–200 Freighter series airplanes, 

and Model A330–300 series airplanes). 

(2) Airbus Mandatory Service Bulletin 

A340–32–4281, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A340–200 series airplanes 

and Model A340–300 series airplanes). 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A340–541 airplanes and 

Model A340–642 airplanes). 

(i) Corrective Action for Any Bogie Pivot Pin 

Found With Degraded Chrome Plating 

If, during any inspection required by 

paragraph (g) of this AD, degraded chrome 

plating on any bogie pivot pin is found: 

Before further flight, do a non-destructive test 

(magnetic particle inspection) of the affected 

bogie pivot pin for corrosion and base metal 

cracks, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin specified 

paragraph (i)(1), (i)(2), or (i)(3) of this AD. 

(1) Airbus Mandatory Service Bulletin 

A330–32–3240, Revision 02, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A330–200 series airplanes, 

Model A330–200 Freighter series airplanes, 

and Model A330–300 series airplanes). 

(2) Airbus Mandatory Service Bulletin 

A340–32–4281, Revision 01, including 

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Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 21229 

Appendices 01 and 02, dated December 2, 

2011 (for Model A340–200 series airplanes 

and Model A340–300 series airplanes). 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A340–541 airplanes and 

Model A340–642 airplanes). 

(j) Corrective Action for Any Bogie Pivot Pin 

Found Corroded or Found With Cracked 

Base Metal 

If, during the non-destructive test 

(magnetic particle inspection) specified in 

paragraph (i) of this AD, the bogie pivot pin 

is found corroded or the base metal is found 

cracked: Before further flight, repair or 

replace the bogie pin with a new or 

serviceable bogie pin, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin specified 

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

(1) Airbus Mandatory Service Bulletin 

A330–32–3240, Revision 02, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A330–200 series airplanes, 

Model A330–200 Freighter series airplanes, 

and Model A330–300 series airplanes). 

(2) Airbus Mandatory Service Bulletin 

A340–32–4281, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A340–200 series airplanes 

and Model A340–300 series airplanes). 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011 (for Model A340–541 airplanes and 

Model A340–642 airplanes). 

(k) No Terminating Action 

Accomplishment of the corrective actions 

required by paragraphs (h) and (j) of this AD 

does not terminate the repetitive inspections 

required by paragraph (g) of this AD. 

(l) Reporting Requirement 

Submit a one-time report of the findings 

(both positive and negative) of the 

inspections required by paragraphs (g) and (i) 

of this AD to Airbus, Customer Services 

Directorate, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex France, ATTN: SDC32 

Technical Data and Documentation Services; 

fax (+33) 5 61 93 28 06; email 

sb.reporting@airbus.com; at the applicable 

time specified in paragraph (l)(1) or (l)(2) of 

this AD. The report must include the 

inspection results and a description of any 

discrepancies found. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) through (j) 

of this AD, if those actions were performed 

before the effective date of this AD using the 

service information specified in paragraphs 

(m)(1) through (m)(4) of this AD, which are 

not incorporated by reference in this AD. 

(1) Airbus Mandatory Service Bulletin 

A330–32–3240, including Appendix 1, dated 

December 8, 2010 (for Model A330–200 

series airplanes, Model A330–200 Freighter 

series airplanes, and Model A330–300 series 

airplanes). 

(2) Airbus Mandatory Service Bulletin 

A330–32–3240, including Appendix 1, 

Revision 01, dated May 4, 2011 (for Model 

A330–200 series airplanes, Model A330–200 

Freighter series airplanes, and Model A330– 

300 series airplanes). 

(3) Airbus Mandatory Service Bulletin 

A340–32–4281, including Appendix 1, dated 

December 8, 2010 (for Airbus Model A340– 

200 series airplanes and Model A340–300 

series airplanes). 

(4) Airbus Mandatory Service Bulletin 

A340–32–5096, including Appendix 1, dated 

December 8, 2010 (for Model A340–541 

airplanes and Model A340–642 airplanes). 

(n) 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, Washington 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(o) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2012–0053, 

dated March 30, 2012, and the service 

information specified in paragraphs (o)(1) 

through (o)(3) of this AD, for related 

information. 

(1) Airbus Mandatory Service Bulletin 

A330–32–3240, Revision 02, including 

Appendices 01 and 02, dated December 2, 

2011. 

(2) Airbus Mandatory Service Bulletin 

A340–32–4281, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011. 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Registe 

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 

A330–32–3240, Revision 02, including 

Appendices 01 and 02, dated December 2, 

2011. 

(ii) Airbus Mandatory Service Bulletin 

A340–32–4281, Revision 01, including 

Appendices 01 and 02, dated December 2, 

2011. 

(iii) Airbus Mandatory Service Bulletin 

A340–32–5096, Revision 01, including 

Appendices 01 and 02, dated December 2, 

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 March 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08047 Filed 4–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

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