Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 75825 

Dated: December 20, 2012. 

Janet Napolitano, 

Secretary of Homeland Security. 

[FR Doc. 2012–31105 Filed 12–21–12; 4:15 pm] 

BILLING CODE 9111–14–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0934; Directorate 

Identifier 2011–NM–260–AD; Amendment 

39–17293; AD 2012–25–12] 

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 and –300 series 

airplanes. This AD was prompted by a 

report of a prematurely fractured main 

landing gear (MLG) bogie beam. This 

AD requires replacing certain MLG 

bogie beams before reaching new 

reduced life limits. We are issuing this 

AD to prevent fracture of the MLG bogie 

beam, which, under high speed, could 

ultimately result in the airplane 

departing the runway, the bogie beam 

detaching from the airplane, or collapse 

of the MLG; and consequent structural 

damage to the airplane and injury to the 

occupants. 

DATES: This AD becomes effective 

January 30, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 30, 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 September 12, 2012 (77 FR 

56172). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

During ground load test cycles on an 

A340–600 aeroplane, the MLG bogie beam 

has prematurely fractured. 

The results of the investigation identified 

that this premature fracture was due to high 

tensile standing stress, resulting from dry fit 

axle assembly method. Improvement has 

been introduced subsequently with a grease 

fit axle assembly method. 

Fatigue and damage tolerance analyses 

were performed, whose results demonstrated 

that the current life limit of certain MLG 

bogie beams with dry fit axles installed on 

A330 aeroplanes only must be reduced 

compared to the life limit stated in the A330 

Airworthiness Limitations Section (ALS) Part 

1-Safe Life Airworthiness Limitation Items 

revision 05 approved by EASA [European 

Aviation Safety Agency] on 29 July 2010. 

Failure to comply with the reduced life 

limit of the MLG bogie beam with dry fit axle 

might jeopardize the MLG structural 

integrity. 

For the reasons described above, this 

[EASA] AD requires the replacement of the 

affected MLG bogie beams before reaching 

the new reduced life limit. 

The unsafe condition is a possible 

fracture of the MLG bogie beam, which, 

under high speed, could ultimately 

result in the airplane departing the 

runway, the bogie beam detaching from 

the airplane, or collapse of the MLG; 

and consequent structural damage to the 

airplane and injury to the occupants. 

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 56172, September 12, 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 

56172, September 12, 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 56172, 

September 12, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

53 products of U.S. registry. We also 

estimate that it will take about 16 workhours per MLG bogie beam (2 MLG 

bogie beams per airplane) to comply 

with the basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$255,000 per MLG bogie beam. 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 up 

to $27,174,160, or $256,360 per MLG 

bogie beam. 

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, 


tkelley on DSK3SPTVN1PROD with 
75826 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 

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 56172, 

September 12, 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: 

2012–25–12 Airbus: Amendment 39–17293. 

Docket No. FAA–2012–0934; Directorate 

Identifier 2011–NM–260–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 30, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes, certificated in any category, all 

manufacturer serial numbers (S/Ns). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by a report of a 

prematurely fractured main landing gear 

(MLG) bogie beam. We are issuing this AD to 

prevent fracture of the MLG bogie beam, 

which, under high speed, could ultimately 

result in the airplane departing the runway, 

the bogie beam detaching from the airplane, 

or collapse of the MLG; and consequent 

structural damage to the airplane and injury 

to the 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) Bogie Beam Replacement 

At the later of the times specified in 

paragraph (g)(1) or (g)(2) of this AD, replace 

all MLG bogie beams having part number 

(P/N) 201485300, 201485301, 201272302, 

201272304, 201272306, or 201272307, except 

those that have S/N S2A, S2B, or S2C, as 

identified in Messier-Dowty Service Letter 

A33–34 A20, Revision 5, including 

Appendices A through F, dated July 31, 2009, 

with a new or serviceable part, in accordance 

with a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, or European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(1) Before the accumulation of the flight 

hours or landings, whichever occurs first, 

specified in table 1 to paragraph (g)(1) of this 

AD, as applicable to airplane type, model, 

and weight variant (WV). 

TABLE 1 TO PARAGRAPH (G)(1) OF THIS AD—MLG BOGIE BEAM LIFE LIMIT

Affected airplanes— Life limit from first installation of MLG bogie beam on 

an airplane— 

Model A330–201, –202, –203, –223, –243, weight variant (WV)02x, WV05x (except 

WV058), and WV06x series.

50,000 landings or 72,300 total flight hours. 

Model A330–201, –202, –203, –223, –243 WV058 ............................................................ 50,000 landings or 57,900 total flight hours. 

Model A330–301, –302, –303, –321, –322, –323, –341, –342, –343 WV00x, WV01x, 

WV02x, and WV05x series.

46,000 landings or 75,000 total flight hours. 

(2) Within 6 months after the effective date 

of this AD. 

(h) Parts Installation Limitation 

As of the effective date of this AD, a MLG 

bogie beam having any part number 

identified in paragraph (g) of this AD, may 

be installed on an airplane, provided its life 

has not exceeded the life limit defined in 

table 1 to paragraph (g)(1) of this AD, and is 

replaced with a new or serviceable part 

before reaching the life limit defined in table 

1 to paragraph (g)(1) of this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

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. 

(j) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0212, dated October 31, 2011; 

and Messier-Dowty Service Letter A33–34 

A20, Revision 5, including Appendices A 

through F, dated July 31, 2009; for related 

information. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Messier-Dowty Service Letter A33–34 

A20, Revision 5, including Appendices A 

through F, dated July 31, 2009. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Messier-Dowty: Messier 

Services Americas, Customer Support Center, 

45360 Severn Way, Sterling, VA 20166–8910; 

telephone 703–450–8233; fax 703–404–1621; 


tkelley on DSK3SPTVN1PROD with 
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 75827 

Internet https://techpubs.services/messierdowty.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 

December 5, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30370 Filed 12–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1228; Directorate 

Identifier 2012–NM–190–AD; Amendment 

39–17292; AD 2012–25–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

757–200, -200CB, and -300 series 

airplanes. That AD currently requires 

initial and repetitive inspections of the 

fuselage skin and bear strap at the 

forward, upper corner of the L1 entry 

door cutout for cracking, and repair if 

necessary. That action also provides an 

optional terminating action for the 

repetitive inspections. That AD also 

requires additional inspections for 

airplanes having repairs or preventative 

modifications installed and inspections 

for certain other airplanes. This AD 

requires the previous actions with 

additional airplane group configurations 

added to paragraph (n) of this AD. This 

AD was prompted by a determination 

that certain airplane group 

configurations in paragraph (n) of the 

existing AD were inadvertently removed 

in the final rule. We are issuing this AD 

to detect and correct cracking of the 

fuselage skin and bear strap at the 

forward upper corner of the L1 entry 

door cutout, which could result in 

reduced structural integrity of the L1 

entry door, and consequent rapid 

decompression of the airplane. 

DATES: This AD is effective January 10, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 3, 2012 (77 FR 52212, 

August 29, 2012). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 24, 2004 (69 FR 

25481, May 7, 2004). 

We must receive any comments on 

this AD by February 11, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H– 

65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https:// 

www.myboeingfleet.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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6440; fax: 

425–917–6590; email: 

nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 23, 2012, we issued AD 2012– 

15–15, Amendment 39–17144 (77 FR 

52212, August 29, 2012), which 

superseded AD 2004–09–32, 

Amendment 39–13622 (69 FR 25481, 

May 7, 2004), for certain The Boeing 

Company Model 757–200, -200CB, and 

-300 series airplanes. AD 2012–15–15 

requires initial and repetitive 

inspections of the fuselage skin and bear 

strap at the forward, upper corner of the 

L1 entry door cutout for cracking, and 

repair if necessary. That action also 

provides an optional terminating action 

for the repetitive inspections. That AD 

also requires additional inspections for 

airplanes having repairs or preventative 

modifications installed and inspections 

for certain other airplanes. That AD 

resulted from reports of additional 

cracking in the fuselage skin. We issued 

that AD to detect and correct cracking 

of the fuselage skin and bear strap at the 

forward upper corner of the L1 entry 

door cutout, which could result in 

reduced structural integrity of the L1 

entry door, and consequent rapid 

decompression of the airplane. 

Actions Since AD Was Issued 

Since we issued AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, 

August 29, 2012), it was noted that 

certain airplane group configurations 

included in paragraph (n) of the NPRM 

were inadvertently removed in the final 

rule. This AD includes Group 1, 

Configuration 4, and Group 2, 

Configuration 3, in paragraph (n) of this 

AD. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires retaining all 

requirements of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, 

August 29, 2012). 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 


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