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

(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


## 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:


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

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 byparagraph (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


## 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