Federal Register / Vol. 77, No. 174 / Friday, September 7, 2012 / Proposed Rules 55163 

Avenue SW., Renton, Washington 98057– 

3356; telephone: 425–917–6457; fax: 425– 

917–6590; email: susan.l.monroe@faa.gov. 

(2) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; fax 

206–766–5680; Internet https:// 

www.myboeingfleet.com. For Intertechnique 

service information identified in this AD, 

contact Zodiac, 2, rue Maurice Mallet—92137 

Issy-les-Moulineaux Cedex France; telephone 

+33 1 41 23 23 23; fax +33 1 46 48 83 87; 

Internet http://www.zodiac.com. You may 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on August 

31, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–22040 Filed 9–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0111; Directorate 

Identifier 2011–NM–089–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Airbus Model A330–200, 

A330–300, A340–200, and A340–300 

series airplanes; and Model A340–541 

airplanes and Model A340–642 

airplanes. That NPRM proposed to 

require performing a detailed inspection 

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. That NPRM 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 action revises that NPRM by 

adding repetitive inspections and 

expanding the applicability. We are 

proposing 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. Since these 

actions impose an additional burden 

over that proposed in the NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these proposed changes. 

DATES: We must receive comments on 

this proposed AD by October 22, 2012. 

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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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, Washington. 

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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0111; Directorate Identifier 

2011–NM–089–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We proposed to amend 14 CFR part 

39 with an earlier NPRM for the 

specified products, which was 

published in the Federal Register on 

February 10, 2012 (77 FR 7007). That 

earlier NPRM proposed to require 

actions intended to address the unsafe 

condition for the products listed above. 

Since that NPRM (77 FR 7007, 

February 10, 2012) was issued, we have 

determined that repetitive inspections 

of the bogie pivot pin are necessary to 

address the identified unsafe condition, 

and we have expanded the applicability 

to include all Airbus Model A330–200, 

A330–200 Freighter, A330–300, A340– 

200, and A340–300 series airplanes; and 

Model A340–541 and Model A340–642 

airplanes. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0053, 

dated March 30, 2012 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The 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. 

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55164 Federal Register / Vol. 77, No. 174 / Friday, September 7, 2012 / Proposed Rules 

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 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. 

Relevant Service Information 

Airbus has issued the following 

service bulletins: 

• 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). 

• 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). 

• 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). 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

Comments 

We gave the public the opportunity to 

comment on the original NPRM (77 FR 

7007, February 10, 2012). We received 

no comments on that NPRM or on the 

determination of the cost to the public. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Certain changes described above 

expand the scope of the earlier NPRM 

(77 FR 7007, February 10, 2012). As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this proposed 

AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 29 products of U.S. registry. 

We also estimate that it would take 

about 22 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on 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. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Airbus: Docket No. FAA–2012–0111; 

Directorate Identifier 2011–NM–089–AD. 

(a) Comments Due Date 

We must receive comments by October 22, 

2012. 

(b) Affected ADs 

None. 

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Federal Register / Vol. 77, No. 174 / Friday, September 7, 2012 / Proposed Rules 55165 

(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 if any Pivot Pin Bush 

is 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 if Any Bogie Pivot Pin 

is 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 

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 if Any Bogie Pivot Pin 

Is Found Corroded or the Base Metal Is 

Found Cracked During the Non-Destructive 

Test 

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 

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) does not 

terminate the repetitive inspections in 

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 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, 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: 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

55166 Federal Register / Vol. 77, No. 174 / Friday, September 7, 2012 / Proposed Rules 

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 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2012– 

0053, dated March 30, 2012, and the service 

information specified in paragraphs (o)(1)(i) 

through (o)(1)(iii) of this AD, for related 

information. 

(i) 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). 

(ii) 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). 

(iii) 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). 

(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, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on August 

31, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–22063 Filed 9–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0945; Directorate 

Identifier 2010–SW–110–AD] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) Model 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

Sikorsky Model S–70, S–70A, S–70C, S– 

70C (M), and S–70C (M1) helicopters 

with General Electric (GE) T700–GE– 

401C or T700–GE–701C engines 

installed. This proposed AD is 

prompted by a reevaluation of the 

method for determining the life limit for 

certain GE engine gas generator turbine 

(GGT) rotor parts and the determination 

that these life limits need to be based on 

low cycle fatigue events instead of hours 

time-in-service. The proposed actions 

are intended to establish new fatigue life 

limits for certain GGT rotor parts to 

prevent fatigue failure of a GGT rotor 

part, engine failure, and subsequent loss 

of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by November 6, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 this proposed 

AD, the economic 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. 

For service information identified in 

this proposed AD, contact Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT, telephone (800) 562–4409, 

email address tsslibrary@sikorsky.com, 

or at http://www.sikorsky.com. You may 

review a copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Michael Davison, Flight Test Engineer, 

New England Regional Office, FAA, 12 

New England Executive Park, 

Burlington, MA 01803; phone: (781) 

238–7156; fax: (781) 238–7170; email: 

michael.davison@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

mstockstill on DSK4VPTVN1PROD with PROPOSALS