Federal Register / Vol. 77, No. 185 / Monday, September 24, 2012 / Proposed Rules 58791 

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–2012–0999; 

Directorate Identifier 2012–NM–049–AD. 

(a) Comments Due Date 

We must receive comments by November 

8, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Airbus A330–201, A330–202, A330– 

203, A330–223, A330–223F, A330–243, 

A330–243F, A330–301, A330–302, A330– 

303, A330–321, A330–322, A330–323, A330– 

341, A330–342, and A330–343 series 

airplanes, all manufacturer serial numbers 

(MSN). 

(2) Airbus A340–211, A340–212, A340– 

213, A340–311, A340–312, and A340–313 

airplanes, all MSN. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32; Landing gear. 

(e) Reason 

This AD was prompted by a report of an 

in-flight turn-back after the nose landing gear 

(NLG) did not retract after take-off. We are 

issuing this AD to prevent failure of the 

retraction actuator, which could cause 

collapse of the NLG after touchdown and 

possible injury to flightcrew and passengers. 

(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) Actions 

At the applicable compliance time 

specified in paragraph (g)(1) or (g)(2) of this 

AD, whichever occurs later, do an overhaul 

of the NLG retraction actuator, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–32– 

3255, excluding Appendices 01 and 02, dated 

October 13, 2011 (for Model A330 airplanes); 

or Airbus Mandatory Service Bulletin A340– 

32–4291, excluding Appendices 01 and 02, 

dated October 13, 2011 (for Model A340 

airplanes). Repeat the overhaul thereafter at 

intervals not to exceed 10 years. 

(1) Prior to the accumulation of 10 years 

since the NLG retraction actuator’s first flight 

on an airplane or from its first flight 

following its last overhaul. 

(2) At the applicable time specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. 

(i) If, on the effective date of this AD, the 

NLG retraction actuator has accumulated 

more than 8 years, and less than 14 years, 

from its first flight on an airplane: Within 24 

months after the effective date of this AD or 

prior to the accumulation of 15 years since 

the NLG retraction actuator’s first flight on an 

airplane, whichever occurs first. 

(ii) If, on the effective date of this AD, the 

NLG retraction actuator has accumulated 14 

years or more since its first flight on an 

airplane: Within 12 months after the effective 

date of this AD. 

(h) Parts Installation Limitation 

As of the effective date of this AD, do not 

install on an airplane any NLG retraction 

actuator, unless in compliance with the 

requirements of this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 227–1138; fax: (425) 227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2012–0034, dated February 29, 

2012, and the service information identified 

in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD, 

for related information. 

(i) Airbus Mandatory Service Bulletin 

A330–32–3255, excluding Appendices 01 

and 02, dated October 13, 2011. 

(ii) Airbus Mandatory Service Bulletin 

A340–32–4291, excluding Appendices 01 

and 02, dated October 13, 2011. 

(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 

September 12, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23433 Filed 9–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0998; Directorate 

Identifier 2011–NM–249–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 

The Boeing Company Model 737–600, 

–700, –700C, –800, -900, and –900ER 

series airplanes. This proposed AD was 

prompted by a new revision to the 

airworthiness limitations of the 

maintenance planning data document. 

This proposed AD would require 

revising the maintenance program to 

update inspection requirements to 


emcdonald on DSK67QTVN1PROD with PROPOSALS
58792 Federal Register / Vol. 77, No. 185 / Monday, September 24, 2012 / Proposed Rules 

detect fatigue cracking of principal 

structural elements (PSEs). We are 

proposing this AD to detect and correct 

fatigue cracking of various PSEs, which 

could adversely affect the structural 

integrity of these airplanes. 

DATES: We must receive comments on 

this proposed AD by November 8, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. 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 Management Facility 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office, FAA, 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6440; fax: 425– 

917–6590; email: nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0998; Directorate Identifier 2011– 

NM–249–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 because of 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 

In accordance with airworthiness 

standards requiring ‘‘damage-tolerance 

assessments’’ (Part 25 of the Federal 

Aviation Regulations, Section 1529), all 

products certificated to comply with 

that section must have Instructions for 

Continued Airworthiness that include 

an Airworthiness Limitations Section 

(AWLs). The AWLs set forth: 

• Mandatory replacement times for 

structural components, 

• Structural inspection intervals, and 

• Related approved structural 

inspection procedures necessary to 

show compliance with the damagetolerance requirements. 

Compliance with the terms specified 

in the AWLs is required by 14 CFR 

43.16 (for persons maintaining 

products) and 14 CFR 91.403 (for 

operators). 

As airplanes gain service experience, 

or as the result of post-certification 

testing and evaluation, it might become 

necessary to add additional life limits or 

structural inspections in order to ensure 

the continued structural integrity of the 

airplane. The manufacturer might revise 

the AWLs to include new or more 

restrictive life limits and inspections. 

However, in order to require compliance 

with those revised life limits and/or 

inspection intervals, the FAA must 

engage in rulemaking. Because loss of 

structural integrity would result in an 

unsafe condition, it is appropriate to 

impose these requirements through the 

airworthiness directive (AD) process. 

Boeing has completed additional 

analyses of fatigue cracking of PSEs on 

certain Model 737 airplanes, which 

included: 

• Crack growth analysis, 

• Service experience analysis, 

• Crack growth testing, 

• Fatigue testing, and 

• Analysis of the effectiveness of 

applicable non-destructive inspection 

techniques to detect cracking and other 

anomalies. 

The results of the analyses 

demonstrated the need to incorporate 

updated inspection requirements to 

detect fatigue cracking of PSEs. We are 

proposing this AD to detect and correct 

fatigue cracking of various PSEs, which 

could adversely affect the structural 

integrity of these airplanes. 

Relevant Service Information 

We reviewed Subsection B, AWLs— 

Structural Inspections, of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of Boeing 737–600, –700, 

–700C, –800, –900, and –900ER 

Maintenance Planning Data (MPD) 

Document, D626A001–CMR, Revision 

July 2011. The service information 

describes procedures for revising the 

airworthiness limitations of the 

maintenance planning document. 

Subsection B of this document contains 

updated inspection requirements to 

detect fatigue cracking of PSEs. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,200 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 185 / Monday, September 24, 2012 / Proposed Rules 58793 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Document Revision ......................................... 1 work-hour × $85 per hour = $85 ................. $0 $85 $102,000 

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. 

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 airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2012–0998; Directorate Identifier 2011– 

NM–249–AD. 

(a) Comments Due Date 

We must receive comments by November 

8, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

certificated in any category, with an original 

airworthiness certificate or original export 

certificate of airworthiness issued before 

April 3, 2012. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new inspections. Compliance with these 

inspections is required by 14 CFR 91.403(c). 

For airplanes that have been previously 

modified, altered, or repaired in the areas 

addressed by these inspections, the operator 

may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (j) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in FAA Advisory 

Circular (AC) 25.1529–1A, dated November 

20, 2007 (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/ 

rgAdvisoryCircular.nsf/list/AC%2025.1529- 

1A/$FILE/AC%2025.1529-1A.pdf). 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 52, Doors; 53, Fuselage; 54, Nacelles/ 

Pylons; 55, Stabilizers; and 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a new revision 

to the airworthiness limitations of the 

maintenance planning data document. We 

are issuing this AD to detect and correct 

fatigue cracking of various principal 

structural elements (PSEs), which could 

adversely affect the structural integrity of 

these airplanes. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance Program Revision 

(1) Within 12 months after the effective 

date of this AD, revise the maintenance 

program by incorporating the information in 

Subsection B, AWLs—Structural Inspections, 

of Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 737–600, 

–700, –700C, –800, –900, and –900ER 

Maintenance Planning Data (MPD) 

Document, D626A001–CMR, Revision July 

2011, except as provided by paragraph (h) of 

this AD. 

(2) The initial compliance time for the 

inspections is within the applicable times 

specified in Subsection B, AWLs—Structural 

Inspections, of Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of 

Boeing 737–600, –700, –700C, –800, –900, 

and –900ER Maintenance Planning Data 

(MPD) Document, D626A001–CMR, Revision 

July 2011, or within 18 months after the 

effective date of this AD, whichever occurs 

later; or within the applicable time specified 

in Subsection B, AWLs—Structural 

Inspections, of Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of 

Boeing 737–600, –700, –700C, –800, –900, 

and –900ER Maintenance Planning Data 

(MPD) Document, D626A001–CMR, Revision 

July 2011, from the time of installation for 

new parts. 

(3) Reports specified in Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of Boeing 737–600, –700, –700C, 

–800, –900, and –900ER Maintenance 

Planning Data (MPD) Document, D626A001– 

CMR, Revision July 2011, may be submitted 

within 10 days after the airplane is returned 

to service, instead of 10 days after each 

individual finding as specified in Section 9. 

(h) No Alternative Inspections and 

Inspection Intervals 

After accomplishing the actions required 

by paragraph (g) of this AD, no alternative 

actions (i.e. alternative inspections) or 

inspection intervals may be used or 

incorporated unless the alternative action or 

interval is approved as an alternative method 

of compliance (AMOC) in accordance with 

the procedures specified in paragraph (j) of 

this AD. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
58794 Federal Register / Vol. 77, No. 185 / Monday, September 24, 2012 / Proposed Rules 

(i) Paperwork Reduction Act Burden 

Statement 

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. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), ANM–120S, 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 manager of the ACO, send it 

to the attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9–ANM– 

Seattle–ACO–AMOC–Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required in the area affected by this AD if it 

is approved by the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) that has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6440; fax: 425–917–6590; 

email: nancy.marsh@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https:// 

www.myboeingfleet.com. You may review 

copies of the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

September 12, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23434 Filed 9–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1016; Directorate 

Identifier 2010–SW–009–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Bell 

Helicopter Textron, Inc. (Bell), Model 

412 and 412EP helicopters. This 

proposed AD is prompted by reports of 

cracking in the swashplate outer ring 

assemblies (outer ring). This AD would 

establish a lower life limit on certain 

outer rings, requiring a revision of the 

retirement life on the components’ 

history card or equivalent record, and a 

revision of the maintenance manual or 

Instructions for Continued 

Airworthiness (ICA). This proposal also 

would prohibit installing these outer 

rings on any helicopter. The proposed 

actions are intended to prevent failure 

of an outer ring because of cracking, 

which could lead to the loss of main 

rotor (M/R) blade pitch control and 

subsequent loss of helicopter control. 

DATES: We must receive comments on 

this proposed AD by November 23, 

2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

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

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket: You may 

examine the AD docket on the Internet 

at http://www.regulations.gov or in 

person at the Docket Operations Office 

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

through Friday, except Federal holidays. 

The AD docket contains this proposed 

AD, the economic evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this proposed AD, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 

280–3391; fax (817) 280–6466; or at 

http://www.bellcustomer.com/files/. 

You may review a copy of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aviation Safety 

Engineer, Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5447; email 7-avsasw-170@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 


emcdonald on DSK67QTVN1PROD with PROPOSALS