Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules 68711 

Dated: September 21, 2012. 

John Charles Padalino, 

Acting Administrator, Rural Utilities Service. 

[FR Doc. 2012–27631 Filed 11–15–12; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1163; Directorate 

Identifier 2011–NM–246–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Airbus Model A330– 

200 and –300 series airplanes; and 

Model A340–200, –300, –500, and –600 

series airplanes. The existing AD 

currently requires a one-time detailed 

inspection of both main landing gear 

(MLG) bogie beams in the region of the 

bogie stop pad for detection of 

deformation and damage, and corrective 

actions if necessary. Since we issued 

that AD, we have received reports of 

corroded bogie stop pads, including 

some with cracking. This proposed AD 

would add Model A330–200 Freighter 

series airplanes to the applicability. For 

certain airplanes, this proposed AD 

would also add repetitive inspections 

for damage and corrosion of the sliding 

piston sub-assembly, with new related 

investigative and corrective actions. We 

are proposing this AD to detect and 

correct deformation or damage under 

the bogie stop pad of both MLG bogie 

beams, which could result in a damaged 

bogie beam and consequent detachment 

of the beam from the airplane or 

collapse of the MLG and departure of 

the airplane from the runway. 

DATES: We must receive comments on 

this proposed AD by December 31, 

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, 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 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–2012–1163; Directorate Identifier 

2011–NM–246–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 

On January 14, 2010, we issued AD 

2010–02–10, Amendment 39–16181 (75 

FR 4477, January 28, 2010). That AD 

required actions intended to address an 

unsafe condition on Airbus Model 

A330–200 and –300 series airplanes; 

and Model A340–200, –300, –500, and 

–600 series airplanes. 

Since we issued AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, 

January 28, 2010), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2011–0211, dated October 31, 2011 

(referred to after this as ‘‘the MCAI’’), to 

supersede EASA AD 2008–0223, dated 

December 15, 2008 (referred to in the 

existing AD), and correct an unsafe 

condition for the specified products. 

The MCAI states: 

During a scheduled maintenance 

inspection on the MLG [main landing gear], 

the bogie stop pad was found deformed and 

cracked. Upon removal of the bogie stop pad 

for replacement, the bogie beam was also 

found cracked. 

Laboratory investigation indicates that an 

overload event has occurred and no fatigue 

propagation of the crack was evident. 

A second bogie beam crack has 

subsequently been found on another 

aeroplane, located under a bogie stop pad 

which only had superficial paint damage. 

This condition, if not detected and 

corrected, could result in the aeroplane 

departing the runway or to the bogie 

detaching from the areoplane or gear 

collapses, which would all constitute unsafe 

conditions at speeds above 30 knots. 

As a precautionary measure, EASA AD 

2008–0223 [which corresponds to FAA AD 

2010–02–10, Amendment 39–16181 (75 FR 

4477, January 28, 2010] required one-time 

detailed inspections under the bogie stop pad 

of both MLG bogie beams and, in case 

deformation or damage is detected, to apply 

the associated repair. 

Numerous bogie stop pad were found 

corroded and a few cracked as a result of the 

one-time inspection required by EASA AD 

2008–0223 on A330, A340–200, and A340– 

300 aeroplanes. 

For the reasons describe above, this 

[EASA] AD, which supersedes EASA AD 

2008–0223: 

—Retains the initial inspection requirement 

of EASA AD 2008–0223 for A330, A340– 

200, and A340–300 aeroplanes. 

—Introduces a repetitive detailed visual 

inspection for A330, A340–200, and A340– 

300 aeroplanes. 

—Retains the requirement of EASA AD 

2008–0223 for A340–500 and A340–600 

aeroplanes, for which further mandatory 

requirements might follow in future 

mandatory requirements might follow in 

future depending on the results of the onetime mandatory inspection in place. 

The required actions include 

repetitive detailed inspections for 


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68712 Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules 

damage and corrosion of the sliding 

piston sub-assembly, with new related 

investigative and corrective actions. 

Related investigative actions include a 

test for indications of corrosion and 

damage to the bogie assembly base 

material, and a magnetic particle 

inspection for cracks, corrosion, and 

damage of the bogie beam. Corrective 

actions include repairing affected parts. 

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 

A330–32–3220, Revision 01, dated 

October 5, 2011 (for Model A330–200 

and –300 series airplanes). 

• Airbus Mandatory Service Bulletin 

A330–32–3248, including Appendix 1, 

dated October 5, 2011 (for Model A330– 

200, –200 Freighter, and –300 series 

airplanes). 

• Airbus Mandatory Service Bulletin 

A340–32–4286, including Appendix 1, 

dated October 5, 2011 (for Model A340– 

200 and –300 series airplanes). 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

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. 

Differences Between Proposed AD and 

Service Information 

Although the service information 

specifies to contact the manufacturer for 

instructions to repair certain conditions, 

this proposed AD would require 

repairing those conditions using a 

method approved by the Manager, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

the EASA (or its delegated agent). 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 67 products of U.S. registry. 

The actions that are required by AD 

2010–02–10, Amendment 39–16181 (75 

FR 4477, January 28, 2010), and retained 

in this proposed AD take about 2 workhours per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is $170 per 

product. 

We estimate that it would take about 

16 work-hours per product to comply 

with the new 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 

$91,120, or $1,360 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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 

removing airworthiness directive (AD) 

2010–02–10, Amendment 39–16181 (75 

FR 4477, January 28, 2010), and adding 

the following new AD: 

Airbus: Docket No. FAA–2012–1163; 

Directorate Identifier 2011–NM–246–AD. 

(a) Comments Due Date 

We must receive comments by December 

31, 2012. 

(b) Affected ADs 

This AD supersedes AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010). 

(c) Applicability 

This AD applies to all Airbus Model A330– 

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

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

–342, and –343 series airplanes; and Model 

A340–211, –212, –213, –311, –312, –313 

series airplanes; and A340–541 and –642 

airplanes; certificated in any category; all 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by reports of 

corroded bogie stop pads, some with 

cracking. We are issuing this AD to detect 

and correct deformation or damage under the 

bogie stop pad of both main landing gear 

(MLG) bogie beams, which could result in a 

damaged bogie beam and consequent 

detachment of the beam from the airplane or 

collapse of the MLG and departure of the 

airplane from the runway. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 


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Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules 68713 

compliance times specified, unless the 

actions have already been done. 

(g) Retained One-Time Inspection and 

Corrective Actions, With Revised Service 

Information 

This paragraph restates the requirements of 

paragraph (f)(1) of AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010), with revised service information. 

For Model A330–200 and –300 series 

airplanes, and Model A340–200, –300, –500, 

and –600 series airplanes, except as required 

by paragraph (i) of this AD: At the applicable 

compliance time specified in paragraph 

(g)(1), (g)(2), (g)(3), (g)(4), (g)(5), or (g)(6) of 

this AD, perform one-time detailed 

inspections of both MLG bogie beams in the 

region of the bogie stop pad for detection of 

deformation and damage, and apply the 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin specified in 

paragraph (g)(7) of this AD. Do all applicable 

corrective actions before further flight. 

(1) Airplanes with 22 months or less and 

2,500 flight cycles or less from the first flight 

with the original bogie beam as of March 4, 

2010 (the effective date of AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010)): Not earlier than 2,500 flight cycles 

or 22 months on the original bogie beam, 

whichever occurs first, but not later than 40 

months from first flight. 

(2) Airplanes with 22 months or less and 

2,500 flight cycles or less from the 

installation date of a new bogie beam in 

service as of March 4, 2010 (the effective date 

of AD 2010–02–10, Amendment 39–16181 

(75 FR 4477, January 28, 2010)): Not earlier 

than 2,500 flight cycles or 22 months from 

the installation date of the new bogie beam, 

whichever occurs first, but not later than 40 

months from the installation date of a new 

bogie beam in service. 

(3) Airplanes with 22 months or less and 

2,500 flight cycles or less from the 

installation date of an overhauled bogie beam 

in service as of March 4, 2010 (the effective 

date of AD 2010–02–10, Amendment 39– 

16181 (75 FR 4477, January 28, 2010)): Not 

earlier than 2,500 flight cycles or 22 months 

from the installation date of the overhauled 

bogie beam in service, whichever occurs first, 

but not later than 40 months from the 

installation date of the overhauled bogie 

beam in service. 

(4) Airplanes with more than 22 months or 

more than 2,500 flight cycles from the first 

flight with the original bogie beam, as of 

March 4, 2010 (the effective date of AD 2010– 

02–10, Amendment 39–16181 (75 FR 4477, 

January 28, 2010)): Within 18 months after 

March 4, 2010 (the effective date of AD 2010– 

02–10). 

(5) Airplanes with more than 22 months or 

more than 2,500 flight cycles from the 

installation date of a new bogie beam in 

service, as of March 4, 2010 (the effective 

date of AD 2010–02–10, Amendment 39– 

16181 (75 FR 4477, January 28, 2010)): 

Within 18 months after March 4, 2010 (the 

effective date of AD 2010–02–10). 

(6) Airplanes with more than 22 months or 

more than 2,500 flight cycles from the 

installation date of an overhauled bogie beam 

in service, as of March 4, 2010 (the effective 

date of AD 2010–02–10, Amendment 39– 

16181 (75 FR 4477, January 28, 2010)): 

Within 18 months after March 4, 2010 (the 

effective date of AD 2010–02–10). 

(7) Use the applicable service information 

to accomplish the actions required by 

paragraph (g) of this AD. 

(i) For Model A330–200 and –300 series 

airplanes: Airbus Mandatory Service Bulletin 

A330–32–3220, dated October 10, 2008; or 

Airbus Mandatory Service Bulletin A330–32– 

3220, Revision 01, dated October 5, 2011. 

(ii) For Model A340–200 and –300 series 

airplanes: Airbus Mandatory Service Bulletin 

A340–32–4264, dated October 10, 2008. 

(iii) For Model A340–500 and –600 series 

airplanes: Airbus Mandatory Service Bulletin 

A340–32–5087, dated October 10, 2008. 

(h) Retained Reporting Requirement 

This paragraph restates the requirements of 

paragraph (f)(2) of AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010). Report the results of the inspection 

required by paragraph (g) of this AD, 

including no findings, to Airbus, Customer 

Services Directorate, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex France; Attn: 

SEDCC1 Technical Data and Documentation 

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

sb.reporting@airbus.com; at the applicable 

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

this AD. 

(1) If the inspection is done on or after 

March 4, 2010 (the effective date of AD 2010– 

02–10, Amendment 39–16181 (75 FR 4477, 

January 28, 2010)): Submit the report within 

30 days after doing the inspection. 

(2) If the inspection was done prior to 

March 4, 2010 (the effective date of AD 2010– 

02–10, Amendment 39–16181 (75 FR 4477, 

January 28, 2010)): Submit the report within 

30 days after March 4, 2010 (the effective 

date of AD 2010–02–10). 

(i) New Inspections of Beams That Have Not 

Been Inspected as of the Effective Date of 

This AD 

For bogie beams on which the inspection 

required by paragraph (g) of this AD has not 

been accomplished as of the effective date of 

this AD: At the later of the times specified 

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

perform one-time detailed inspections of 

both main landing gear bogie beams in the 

region of the bogie stop pad for detection of 

deformation and damage, and apply the 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of the 

applicable service information specified in 

paragraph (i)(3) of this AD. Do all applicable 

corrective actions before further flight. 

(1) At the applicable time in paragraph 

(i)(1)(i) or (i)(1)(ii) of this AD. 

(i) For bogie beams that have not been 

overhauled: Not earlier than 2,500 flight 

cycles or 22 months, whichever occurs first, 

on a bogie beam since its first flight on an 

airplane since new, but not later than 40 

months since its first flight on an airplane 

since new. 

(ii) For bogie beams that have been 

overhauled: Not earlier than 2,500 flight 

cycles or 22 months, whichever occurs first, 

on a bogie beam since its first flight on an 

airplane after its most recent overhaul, but 

not later than 40 months since its first flight 

on an airplane after its most recent overhaul. 

(2) Within 90 days after the effective date 

of this AD. 

(3) Use the applicable service information 

specified in paragraph (i)(3)(i), (i)(3)(ii), or 

(i)(3)(iii) of this AD, to accomplish the 

actions required by paragraph (i) of this AD. 

(i) For Model A330–200 and –300 series 

airplanes: Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 01, dated October 5, 

2011. 

(ii) For Model A340–200 and –300 series 

airplanes: Airbus Mandatory Service Bulletin 

A340–32–4264, dated October 10, 2008. 

(iii) For Model A340–500 and –600 series 

airplanes: Airbus Mandatory Service Bulletin 

A340–32–5087, dated October 10, 2008. 

(j) New Repetitive Inspections 

Except for bogie beams that have been 

inspected as specified in Airbus Mandatory 

Service Bulletin A340–32–5087: At the later 

of the times specified in paragraphs (j)(1) and 

(j)(2) of this AD, do the detailed inspection 

of both MLG bogie beams in the bogie stop 

pad area for damage and corrosion, and all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3248, 

dated October 5, 2011 (for Model A330–200, 

–200 Freighter, and –300 series airplanes); or 

Airbus Mandatory Service Bulletin A340–32– 

4286, dated October 5, 2011 (for Model 

A340–200 and –300 series airplanes); except 

as required by paragraph (k) of this AD. Do 

all applicable related investigative and 

corrective actions before further flight. 

Repeat the inspection thereafter at intervals 

not to exceed 2,500 flight cycles or 24 

months, whichever is first. 

(1) Within 2,500 flight cycles or 24 months, 

whichever occurs first, accumulated by a 

MLG bogie beam since its first flight after the 

most recent accomplishment of Airbus 

Mandatory Service Bulletin A330–32–3220 

or A340–32–4264, as applicable. 

(2) Within 3 months after the effective date 

of this AD. 

(k) Service Information Exception 

If any cracking of the bogie beam is 

detected during any inspection or repair 

required by paragraph (j) of this AD, or any 

repair required by paragraph (j) of this AD is 

beyond the maximum repair allowance 

specified in the service information required 

by paragraph (j) of this AD: Before further 

flight, repair using a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

(l) New Reporting Requirement 

Report the results of the initial inspection 

required by paragraph (j) of this AD, 

including both positive and negative 

findings, to Airbus, Customer Services 

Directorate, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex France; Attn: SEDCC1 

Technical Data and Documentation Services; 

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

sb.reporting@airbus.com at the applicable 


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68714 Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules 

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

this AD. 

(1) If the inspection is done on or after the 

effective date of this AD: Submit the report 

within 30 days after doing the inspection. 

(2) If the inspection was done prior to the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(m) 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. AMOCs approved previously in 

accordance with AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010), are approved as AMOCs for the 

corresponding provisions of 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. 

(n) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed if any crack is 

found during any inspection required by this 

AD. 

(o) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0211, dated October 1, 2011, 

and the service information specified in 

paragraphs (o)(1)(i) through (o)(1)(vi) of this 

AD, for related information. 

(i) Airbus Mandatory Service Bulletin 

A330–32–3220, dated October 10, 2008. 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 01, dated October 5, 

2011. 

(iii) Airbus Mandatory Service Bulletin 

A330–32–3248, dated October 5, 2011. 

(iv) Airbus Mandatory Service Bulletin 

A340–32–4264, dated October 10, 2008. 

(v) Airbus Mandatory Service Bulletin 

A340–32–4286, dated October 5, 2011. 

(vi) Airbus Mandatory Service Bulletin 

A340–32–5087, dated October 10, 2008. 

(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. 

Issued in Renton, Washington, on 

November 8, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27847 Filed 11–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1055; Directorate 

Identifier 2012–NE–33–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) BR700–710A1–10 and BR700– 

710A2–20 turbofan engines, and certain 

BR700–710C4–11 model engines. This 

proposed AD was prompted by RRD 

performing an evaluation that 

determined that certain high-pressure 

turbine (HPT) stage 1 and stage 2 discs 

from a specific supplier may contain 

steel inclusions that may cause the discs 

to fail before they reach their current life 

limits. This proposed AD would require 

reducing the life limits for certain HPT 

stage 1 and stage 2 discs. We are 

proposing this AD to prevent failure of 

the HPT stage 1 and stage 2 discs, which 

could result in uncontained failure of 

the engine and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by January 15, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this proposed AD, contact Rolls-Royce 

Deutschland Ltd & Co KG, Eschenweg 

11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; phone: 49 0 33– 

7086–1883; fax: 49 0 33–7086–3276. 

You may view this service information 

at the FAA, Engine & Propeller 

Directorate, 12 New England Executive 

Park, Burlington, MA. For information 

on the availability of this material at the 

FAA, call 781–238–7125. 

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 (phone: 800–647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7154; fax: 781–238– 

7199; email: robert.c.morlath@faa.gov. 


emcdonald on DSK7TPTVN1PROD with PROPOSALS