Federal Register / Vol. 77, No. 28 / Friday, February 10, 2012 / Proposed Rules 7007 

(C) Attach each revised page 11–1–7 

(ASB121, page 11) through 11–1–10 

(ASB121, page 14) to the unrevised samenumbered page in the Performance section of 

the RFM. 

(ii) Within 50 hours time-in-service (TIS), 

unless accomplished previously: 

(A) Revise the RFM as required by 

paragraph (1)(i)(B) and (1)(i)(C) of this AD; 

and 

(B) Affix the placard as required by 

paragraph (1)(i)(A) of this AD or comply with 

paragraph (1)(iii) of this AD. 

(iii) At intervals not to exceed 600 hours 

TIS: 

(A) Before operating between a 16,000 ft 

PA and 18,000 ft PA, perform the ‘‘MAX N1 

CHECK’’ by following the Accomplishment 

Instructions, paragraph 2.B.1.1., of ASB121. 

If the OEI rating is not reached, either affix 

a placard as required by paragraph (1)(i)(A) 

or comply with paragraph (1)(iii)(B) or 

(1)(iii)(C) of this AD. 

(B) Before operating between 13,000 ft PA 

and 16,000 ft PA, perform the ‘‘MAX N1 

CHECK’’ by following the Accomplishment 

Instructions, paragraph 2.B.1.4., of ASB121. 

(1) If the OEI rating is reached, affix a 

placard to the instrument panel in plain view 

of the pilot(s), which states: ‘‘Maximum 

operating altitude is 16,000 ft PA.’’ 

(2) If the OEI rating is not reached, either 

affix a placard as required by paragraph 

(1)(i)(A) of this AD or comply with paragraph 

(1)(iii)(C) of this AD. 

(C) Before operating between 10,000 ft PA 

and 13,000 ft PA, perform the ‘‘MAX N1 

CHECK’’ by following the Accomplishment 

Instructions, paragraph 2.B.1.7., of ASB121. 

(1) If the OEI rating is reached, affix a 

placard to the instrument panel in plain view 

of the pilot(s), which states: ‘‘Maximum 

operating altitude is 13,000 ft PA.’’ 

(2) If the OEI rating is not reached, affix a 

placard as required by paragraph (1)(i)(A) of 

this AD. 

(2) For Model MBB–BK 117 C–2 

helicopters: 

(i) Before any flight operation at or above 

a PA of 10,000 feet, unless accomplished 

previously: 

(A) Affix a placard to the instrument panel 

in plain view of the pilot(s), which states: 

‘‘Maximum altitude for takeoff, landing, and 

hovering is 10,000 ft PA. Maximum operating 

altitude above effective translational lift is 

13,000 ft PA,’’ or comply with paragraph 

(2)(iii) of this AD. The term ‘‘hovering’’ as 

used in this placard includes both IGE and 

OGE hovering. 

(B) Revise the Altitude Limitations section 

of the RFM in accordance with paragraph 

A.2.3. on page 10 and paragraph 2.8. on page 

11 of Eurocopter ASB No. MBB BK117 C–2– 

71A–003, Revision 3, dated December 11, 

2007 (ASB003). 

(ii) Within 50 hours TIS, unless 

accomplished previously: 

(A) Revise the RFM as required by 

paragraph (2)(i)(B) of this AD; and 

(B) Affix a placard as required by 

paragraph (2)(i)(A) of this AD or comply with 

paragraph (2)(iii) of this AD. 

(iii) At intervals not to exceed 600 hours 

TIS: 

(A) Before operating between 16,000 ft PA 

and 18,000 ft PA, perform the ‘‘MAX N1 

CHECK’’ by following the Accomplishment 

Instructions, paragraph 3.A.(1) (on pages 4 

and 5), of ASB003. If the OEI rating is not 

reached, either affix a placard as required by 

paragraph (2)(i)(A) or comply with paragraph 

(2)(iii)(B) or (2)(iii)(C) of this AD. 

(B) Before operating between 13,000 ft PA 

and 16,000 ft PA, perform the ‘‘MAX N1 

CHECK’’ by following the Accomplishment 

Instructions, paragraph 3.A.(1) (on pages 5 

and 6) of ASB003. 

(1) If the OEI rating is reached, affix a 

placard to the instrument panel in plain view 

of the pilot(s), which states: ‘‘Maximum 

operating altitude is 16,000 ft PA.’’ 

(2) If the OEI rating is not reached, either 

affix a placard as required by paragraph 

(2)(i)(A) or comply with paragraph (2)(iii)(C) 

of this AD. 

(C) Before operating between 10,000 ft PA 

and 13,000 ft PA, perform the ‘‘MAX N1 

CHECK’’ by following the Accomplishment 

Instructions, paragraph 3.A.1. (on page 7) of 

ASB003. 

(1) If the OEI rating is reached, affix a 

placard to the instrument panel in plain view 

of the pilot(s), which states: ‘‘Maximum 

operating altitude is 13,000 ft PA.’’ 

(2) If the OEI rating is not reached, affix a 

placard as required by paragraph (2)(i)(A) of 

this AD. 

(3) If an engine, FCU, engine module 2 or 

engine module 3 is replaced, before any flight 

operation at or above a PA of 10,000 feet, 

comply with the requirements of paragraph 

(1) of this AD for the Model MBB–BK 117 

C–1 helicopter or paragraph (2) of this AD for 

the Model MBB–BK 117 C–2 helicopter. 

(4) Modifying both engines with 

Turbomeca Modification TU 358 is 

terminating action for the requirements of 

this AD. After modifying both engines, 

remove from the RFM the revised altitude 

limitations and the revised performance 

pages required by this AD. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Ed Cuevas, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

ed.cuevas@faa.gov. 

(2) For operations conducted under a Part 

119 operating certificate or under Part 91, 

Subpart K, we suggest that you notify your 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office or certificate holding 

district office before operating any aircraft 

complying with this AD through an AMOC. 

(f) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (Germany) 

AD No.: 2008–0061, dated March 27, 2008. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 1100, Placards and Markings. 

Issued in Fort Worth, Texas, on January 27, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–3187 Filed 2–9–12; 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: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 series 

airplanes; Model A330–300 series 

airplanes, Model A340–200 series 

airplanes; Model A340–300 series 

airplanes; Model A340–541 airplanes; 

and Model A340–642 airplanes. This 

proposed 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. 

This proposed AD would require 

performing a detailed inspection for 

degradation of the bogie pivot pins and 

pivot pin bushes of the main and central 

landing gear for any cracks and damage, 

and repairing or replacing bogie pivot 

pins and pivot pin bushes, if necessary. 

We are proposing this AD to correct and 

detect 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: We must receive comments on 

this proposed AD by March 26, 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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

7008 Federal Register / Vol. 77, No. 28 / Friday, February 10, 2012 / Proposed Rules 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0040, 

dated March 8, 2011 (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 Bogie Beams and A340–500/ 

600 Centre Landing Gear Bogie Beams, cracks 

in the Bogie Pivot Pin (BPP) have been found. 

Investigations indicated that the main root 

cause is material heating due to friction 

between bogie pivot pin and bush. 

Consequences of that heating are chrome 

detachment and stress corrosion cracking 

(SCC). 

This situation, if not corrected, could result 

in the collapse of the main or central landing 

gear. 

As a precautionary measure, this [EASA] 

AD requires a one-time [detailed] inspection 

of the main landing gear (all types of A330 

and A340) and central landing gear (A340– 

500/600 only) to detect degradation * * * of 

the BPP [and cracks and damages of the 

bushes], as applicable to aeroplane model, 

and the reporting of inspections results. 

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, including Appendix 1, 

dated December 8, 2010 (for Model 

A330–200 series airplanes and Model 

A330–300 series airplanes); 

• Airbus Mandatory Service Bulletin 

A340–32–4281, including Appendix 1, 

dated December 8, 2010 (for Model 

A340–200 series airplanes and Model 

A340–300 series airplanes); and 

• Airbus Mandatory Service Bulletin 

A340–32–5096, including Appendix 1, 

dated December 8, 2010 (for Model 

A340–541 airplanes and A340–642 

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. 

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: 

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Federal Register / Vol. 77, No. 28 / Friday, February 10, 2012 / Proposed Rules 7009 

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 March 26, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

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

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

airplanes; Model A340–211, –212, and –213 

airplanes; Model A340–311, –312, and –313 

airplanes; Model A340–541 airplanes; and 

Model A340–642 airplanes; certificated in 

any category; all manufacturer serial 

numbers, except those on which Airbus 

modification 54500 has been embodied in 

production. 

(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. We are issuing this AD 

to correct and detect 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) Inspection 

Within 26 months after the effective date 

of this AD or within 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 of the bogie pivot 

pins and pivot pin bushes of the main and 

central landing gear, for any cracks and 

damage (i.e., loss of chromium plate, loose 

chromium, sharp edges), in accordance with 

the Accomplishment Instructions of the 

applicable service bulletin specified in 

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

(1) Airbus Mandatory Service Bulletin 

A330–32–3240, including Appendix 1, dated 

December 8, 2010 (for Model A330–200 

series airplanes and Model A330–300 series 

airplanes). 

(2) 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). 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, including Appendix 1, dated 

December 8, 2010 (for Model A340–541 

airplanes and A340–642 airplanes). 

(h) Corrective Action 

If, during the inspection specified in 

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

is found cracked or damaged: Before further 

flight, record all findings (both positive and 

negative), as required by paragraph (k) of this 

AD, and 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, including Appendix 1, dated 

December 8, 2010 (for Model A330–200 

series airplanes and Model A330–300 series 

airplanes). 

(2) 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). 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, including Appendix 1, dated 

December 8, 2010 (for Model A340–541 

airplanes and A340–642 airplanes). 

(i) Record Findings and Inspection 

If, during the inspection specified in 

paragraph (g) of this AD, degraded chrome 

plating on any bogie pivot pin is found: 

Before further flight, record findings (both 

positive and negative), as required by 

paragraph (k) of this AD, and do a nondestructive 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, including Appendix 1, dated 

December 8, 2010 (for Model A330–200 

series airplanes and Model A330–300 series 

airplanes). 

(2) 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). 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, including Appendix 1, dated 

December 8, 2010 (for Model A340–541 

airplanes and A340–642 airplanes). 

(j) Repair or Replacement 

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, including Appendix 1, dated 

December 8, 2010 (for Model A330–200 

series airplanes and Model A330–300 series 

airplanes. 

(2) 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). 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, including Appendix 1, dated 

December 8, 2010 (for Model A340–541 

airplanes and A340–642 airplanes). 

(k) Reporting Requirement 

Submit a 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 

(k)(1) or (k)(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. 

(l) 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 

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7010 Federal Register / Vol. 77, No. 28 / Friday, February 10, 2012 / Proposed Rules 

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. 

(m) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011–0040, 

dated March 8, 2011, and the service 

information specified in paragraphs (m)(1) 

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

information. 

(1) Airbus Mandatory Service Bulletin 

A330–32–3240, including Appendix 1, dated 

December 8, 2010. 

(2) Airbus Mandatory Service Bulletin 

A340–32–4281, including Appendix 1, dated 

December 8, 2010. 

(3) Airbus Mandatory Service Bulletin 

A340–32–5096, including Appendix 1, dated 

December 8, 2010. 

Issued in Renton, Washington on February 

3, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–3105 Filed 2–9–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 135 

[Docket No. FAA 2011–1397] 

Clarification of Policy Regarding 

Approved Training Programs; 

Correction 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of availability; 

Correction. 

SUMMARY: The FAA is correcting a 

notice published on December 27, 2011 

(76 FR 80831). In that notice of 

availability the FAA announced the 

availability of an FAA Notice that 

would require FAA inspectors to review 

policy regarding approved training 

programs as well as to identify and 

correct those training programs which 

erroneously issued credit for previous 

training or checking. The Notice also 

provided guidance on constructing 

reduced hour training programs based 

on previous experience. Upon review of 

the comments and any necessary 

revision, the Notice would cancel and 

replace FAA Order 8900.1, Volume 3, 

Chapter 19, Paragraph 3–1111. This 

document corrects an incorrect 

comment due date. 

DATES: Written comments must be 

received on or before February 27, 2012. 

ADDRESSES: Send comments identified 

by docket number FAA–2011–1397 

using any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30; U.S. Department of 

Transportation (DOT), 1200 New Jersey 

Avenue SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: The FAA will post all 

comments it receives, without change, 

to http://www.regulations.gov, including 

any personal information the 

commenter provides. Using the search 

function of the docket web site, anyone 

can find and read the electronic form of 

all comments received into any FAA 

dockets, including the name of the 

individual sending the comment (or 

signing the comment for an association, 

business, labor union, etc.). DOT’s 

complete Privacy Act Statement can be 

found in the Federal Register published 

on April 11, 2000 (65 FR 19477–19478), 

as well as at http://DocketsInfo.dot.gov. 

Docket: Background documents or 

comments received may be read at 

http://www.regulations.gov at any time. 

Follow the online instructions for 

accessing the docket or Docket 

Operations in Room W12–140 of the 

West Building Ground Floor at 1200 

New Jersey Avenue SE., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: 

Robert Burke, Air Carrier Training 

Branch, Air Transportation Division, 

Flight Standards Service, Federal 

Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone: 202– 

267–8262; facsimile: 202–267–5229; 

email: robert.burke@faa.gov. 

Background 

On December 27, 2011, the FAA 

published a notice of availability 

entitled, ‘‘Clarification of Policy 

Regarding Approved Training 

Programs’’ (76 FR 80831). 

The FAA Order 8900.1, Flight 

Standards Information Management 

System, was issued on September 13, 

2007. This order consolidated and 

replaced FAA Orders 8300.1, 8400.1, 

and 8700.1, the FAA’s guidance to 

inspectors. There have been numerous 

inquiries by part 135 certificate holders 

regarding the acceptance of training/ 

evaluations previously completed by a 

crewmember while in the employment 

of another certificate holder. 

Regulations do not permit the crediting 

of such training (with the specific 

exception of CRM and DRM training). 

Additionally, some training centers 

have distributed a training program 

template that provides credit for 

training/evaluations conducted by 

another operator. Such provisions are 

contrary to the intent as well as the 

technical provisions of part 135 and are 

not appropriate for inclusion in a 

certificate holder’s approved training 

program. 

Part 135 certificate holders may 

develop and submit for approval 

multiple curriculums for a particular 

crewmember position and aircraft make/ 

model/variant. For example, a part 135 

certificate holder may have a an initial 

new-hire curriculum designed to meet 

the requirements of new hire 

crewmembers that have minimal flight 

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