5420 Federal Register / Vol. 77, No. 23 / Friday, February 3, 2012 / Proposed Rules 

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 an economic 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 Airworthiness 

Directive (AD): 

Sikorsky Aircraft Corporation: Docket No. 

FAA–2012–0085; Directorate Identifier 

2011–SW–004–AD. 

(a) Applicability 

This AD applies to Sikorsky Aircraft 

Corporation (Sikorsky) Model S–61A, D, E, L, 

N, NM, R, and V helicopters with a fuel 

system 40 micron fuel filter element, part 

number (P/N) 52–0505–2 or 52–01064–1, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

contaminants present in the engine fuel 

control units (FCUs). This AD was prompted 

by a National Transportation Safety Board 

review of in-service events where engine 

performance degradation occurred. This 

condition could result in particulate 

contamination in the FCU, which could lead 

to malfunction of an internal valve, power 

loss at a critical phase of flight, and loss of 

control of the helicopter. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(d) Required Actions 

(1) Within 150 hours time-in-service, do 

the following: 

(i) Replace each forward and aft fuel 

system 40 micron fuel filter element with a 

10 micron fuel filter element, P/N AM52– 

01064–1. 

(ii) Re-identify the fuel filter, P/N 52– 

2145–009, and fuel control assembly bracket 

as follows: 

(A) On the fuel filter identification plate, 

cross out the last two digits (‘‘09’’) of the 

existing fuel filter P/N 52–2145–009, and 

replace those last two digits with ‘‘14’’ to reidentify the fuel filter as P/N 52–2145–014. 

(B) Change the existing fuel control 

assembly part number on the fuel control 

assembly bracket to re-identify it as follows: 

(1) Change fuel control assembly P/N 

S6130–63209–001 to P/N S6130–63209–041. 

(2) Change fuel control assembly P/N 

S6130–63209–002 to P/N S6130–63209–042. 

(3) Change fuel control assembly P/N 

S6130–63209–003 to P/N S6130–63209–043. 

(4) Change fuel control assembly P/N 

S6130–63209–004 to P/N S6130–63209–044. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Boston Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Kirk Gustafson, Aerospace Engineer, Boston 

Aircraft Certification Office, Engine and 

Propeller Directorate, FAA,12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7190; email 

kirk.gustafson@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 

Sikorsky Aircraft Corporation Alert Service 

Bulletin No. 61B30–16, dated February 2, 

1010, which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For this service 

information, contact Sikorsky Aircraft 

Corporation, Attn: Manager, Commercial 

Technical Support, mailstop s581a, 6900 

Main St., Stratford, CT; telephone (203) 383– 

4866; email tsslibrary@sikorsky.com, or at 

http://www.sikorsky.com. You may review 

copies of this information at the FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2800, Fuel system. 

Issued in Fort Worth, Texas, on January 23, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–2421 Filed 2–2–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0083; Directorate 

Identifier 2010–SW–022–AD] 

RIN 2120–AA64 

Airworthiness Directives; Aeronautical 

Accessories Inc. High Landing Gear 

Aft Crosstube Assembly 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

Aeronautical Accessories Inc. (AAI) 

High Landing Gear Aft Crosstube 

Assembly (aft crosstube) installed on 

certain Bell Helicopter Textron, Inc. 

(Bell) and Agusta S.p.A. (Agusta) model 

helicopters as an approved Bell part 

installed during production or based on 

a Supplemental Type Certificate (STC). 

This proposed AD is prompted by three 

reports of failed crosstubes because of 

cracks. The proposed actions are 

intended to prevent failure of a 

crosstube, collapse of the landing gear, 

and subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by April 3, 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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 77, No. 23 / Friday, February 3, 2012 / Proposed Rules 5421 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed AD, contact Aeronautical 

Accessories, Inc., P.O. Box 3689, Bristol, 

Tennessee 37625–3689, telephone (423) 

538–5151 or 1–800–251–7094, fax (423) 

538–8469 or at http://www.aeroaccess.com. You may also get service 

information from 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 copies of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, TX 76137. 

FOR FURTHER INFORMATION CONTACT: 

Martin R. Crane, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Rotorcraft Certification Office, 2601 

Meacham Blvd., Fort Worth, TX 76137, 

telephone (817) 222–5170, email 

martin.r.crane@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 

proposal in light of the comments we 

receive. 

Discussion 

This document proposes adopting a 

new AD for AAI aft crosstubes installed 

during production or based on STC 

SR01502AT on certain Bell and Agusta 

model helicopters. This proposal would 

require certain recurring visual, 

dimensional, and fluorescent penetrant 

inspections of each aft crosstube. If 

there is a crack, the AD would require, 

before further flight, replacing any 

cracked aft crosstube with an airworthy 

aft crosstube. This proposal would also 

require establishing a life limit for one 

of the affected part-numbered aft 

crosstubes (as the later part-numbered 

aft crosstube already has limits 

established) and creating a component 

history card or equivalent record for aft 

crosstube part number (P/N) 412–321– 

304. This proposal is prompted by three 

reports of failed aft crosstubes. This 

condition, if not corrected, could result 

in collapse of the landing gear, and 

subsequent loss of control of the 

helicopter. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Related Service Information 

We have reviewed AAI Alert Service 

Bulletin No. AA–07109, dated April 3, 

2008 (ASB), which specifies recurring 

inspections and maintenance of each aft 

crosstube, P/N 412–321–104, installed 

as an approved part by Bell during 

production, and P/N 412–321–304, 

installed under STC SR01052AT, on 

Bell Model 412, 412EP, and 412CF and 

Agusta Model AB412 and AB412EP 

helicopters. The ASB specifies 

establishing a high aft crosstube, P/N 

412 321–304, ‘‘takeoff/landing’’ life 

limit of 20,000. Also, the ASB specifies 

that operators should follow helicopter 

towing instructions to prevent crosstube 

damage or failure as a result of ground 

handling or towing. 

We have also reviewed Bell ASB 412– 

08–129, dated May 12, 2008, for Bell 

Model 412 and 412EP helicopters, serial 

numbers 33001 through 33213, 36001 

and subsequent, with an aft crosstube P/ 

N 412–321–104 installed. Bell issued its 

ASB ‘‘to achieve complete distribution 

of AA–07109 vendor bulletin to the 

current affected model distribution list.’’ 

Proposed AD Requirements 

This proposed AD would require: 

• Within 50 hours time-in-service 

(TIS), establishing a life limit of 20,000 

takeoffs and landings for aft crosstube 

P/N 412 321 304; creating a component 

history card or equivalent record; and 

determining and recording the total 

number of takeoffs and landings for 

each aft crosstube. 

• Within the next 450 takeoffs and 

landings, if an aft crosstube has reached 

20,000 or more takeoffs and landings, 

replacing it with an airworthy aft 

crosstube. 

• At specified intervals, preparing the 

aft crosstube inspection areas and 

inspecting each aft crosstube for a crack. 

If there are no cracks, thereafter at 

specified intervals, priming and 

cleaning the inspection area, and 

inspecting each aft crosstube for a crack. 

If there is a crack, before further flight, 

replacing the cracked aft crosstube with 

an airworthy aft crosstube. 

• At specified intervals, determining 

the horizontal deflection of each aft 

crosstube from the centerline of the 

helicopter (BL 0.0) to the outside of the 

skid tubes. If the measured horizontal 

deflection exceeds aft crosstube limits, 

replacing the aft crosstube with an 

airworthy aft crosstube. 

• At specified intervals, removing the 

aft crosstube assembly, removing paint 

and sealant, and fluorescent penetrant 

inspecting each aft crosstube for a crack. 

If there are no cracks, priming and 

painting the inspection area. If there is 

a crack, before further flight, replacing 

each cracked aft crosstube with an 

airworthy aft crosstube. 

This proposed AD would revise the 

Airworthiness Limitations section of the 

applicable maintenance manuals or the 

Instructions for Continued 

Airworthiness (ICA) by establishing a 

new retirement life of 20,000 takeoffs 

and landings for aft crosstube P/N 412– 

321–304 by making pen and ink changes 

or inserting a copy of the AD into the 

maintenance manual or the ICAs. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 115 helicopters of U.S. 

Registry. 

We also estimate that the proposed 

actions would take about: 

• 1 hour to create a component 

history card or equivalent record and 

determine and record the number of 

accumulated takeoffs and landings for 

each affected aft crosstube; 

• 3 hours to prepare the area for a 

visual inspection; 

• 1⁄2 hour to do the repetitive visual 

inspections, assuming 14 repetitive 

visual inspections per year; 

• 1 hour to do a dimensional 

inspection of the skid gear, assuming 3 

inspections per year; 

• 24 hours to prepare and fluorescent 

penetrant inspect the aft crosstube, 

assuming 2 inspections per year; and 

• 10 hours to replace an aft crosstube, 

if necessary, assuming 3 aft crosstubes 

would be replaced. 

The average labor rate is $85 per work 

hour. Required parts would cost about 

$9,315 per aft crosstube. Based on these 

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5422 Federal Register / Vol. 77, No. 23 / Friday, February 3, 2012 / Proposed Rules 

figures, we estimate the total cost 

impact of the proposed AD on U.S. 

operators to be $636,545. 

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, 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 to the extent that it justifies 

making a regulatory distinction; 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 an economic 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: 

Aeronautical Accessories, Inc.: Docket No. 

FAA–2012–0083; Directorate Identifier 

2010–SW–022–AD. 

(a) Applicability 

This AD applies to High Landing Gear Aft 

Crosstube Assembly (aft crosstube) part 

number (P/N) 412–321–104 and P/N 412– 

321–304, installed on Agusta S.p.A. Model 

AB412 and AB412EP and Bell Helicopter 

Textron, Inc., Model 412, 412CF, and 412EP 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

cracked aft crosstube which could result in 

collapse of the landing gear, and subsequent 

loss of control of the helicopter. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(d) Required Actions 

(1) Within 50 hours time-in-service (TIS) 

establish a life limit of 20,000 takeoffs and 

landings for each aft crosstube P/N 412–321– 

304. For the purposes of this AD, a takeoff 

and landing is defined as the cycle from 

when the helicopter gets light on the skids 

(takeoff) unloading the aft crosstube and then 

settles on the skids again (landing) reloading 

the aft crosstubes. Either the number of 

landings or takeoffs may be counted. 

(i) Create a component history card or 

equivalent record. 

(ii) Determine and record on the history 

card or equivalent record the total number of 

takeoffs and landings for each aft crosstube. 

If the takeoff and landing information is 

unavailable, estimate the number by 

multiplying the airframe hours by 10. 

(2) Within the next 450 takeoffs and 

landings, if an aft crosstube has reached 

20,000 or more takeoffs and landings, replace 

it with an airworthy aft crosstube. 

(3) Before reaching 2,500 takeoffs and 

landings or for an aft crosstube with 2,500 or 

more takeoffs and landings, within 50 hours 

TIS or within the next 250 takeoffs and 

landings, whichever occurs first, prepare the 

aft crosstube inspection areas as depicted in 

Figure 1 of Aeronautical Accessories, Inc. 

(AAI) Alert Service Bulletin No. AA–07109, 

dated April 3, 2008 (ASB), by following the 

Accomplishment Instructions, Part B, 

paragraphs 1 through 4, of the ASB. Using a 

10X or higher magnifying glass, inspect the 

prepared areas of each aft crosstube for a 

crack. If there is a crack, before further flight, 

replace the cracked aft crosstube with an 

airworthy aft crosstube. If there are no cracks, 

after completing the aft crosstube inspection, 

prime and paint the inspection area by 

following the Accomplishment Instructions, 

Part B, paragraphs 6 and 7, of the ASB. 

(4) Thereafter, at intervals not to exceed 

450 takeoffs and landings, clean the 

inspection area. Using a 10X or higher 

magnifying glass, inspect the clear-coated 

area of the aft crosstube for a crack. 

(5) If there is a crack, before further flight, 

replace the cracked aft crosstube with an 

airworthy aft crosstube. 

(6) Within 30 days or before reaching 2,500 

takeoffs and landings, whichever occurs 

later, and thereafter at intervals not to exceed 

2,500 takeoffs and landings or 12 months, 

whichever occurs first, determine the 

horizontal deflection of each aft crosstube 

from the centerline of the helicopter (BL 0.0) 

to the outside of the skid tubes by following 

the Accomplishment Instructions, Part D, 

paragraphs 1 through 3, of the ASB. If the 

measured aft crosstube horizontal deflection 

depicted in Figure 2 of the ASB is less than 

57 inches (1448 mm) or greater than 59 

inches (1499 mm), replace the aft crosstube 

with an airworthy aft crosstube. 

(7) Within 3 months or on or before 

reaching 7,500 takeoffs and landings, 

whichever occurs later, and thereafter at 

intervals not to exceed 5,000 takeoffs and 

landings: 

(i) Remove the aft crosstube assembly by 

removing the aft crosstube support beam 

assembly, P/N 604–030–001, and both aft 

crosstube clamp assemblies, P/N 604–027– 

002. 

(ii) Remove paint and sealant from the aft 

crosstube outboard of the upper center 

support to top of saddles, both sides, as 

depicted in Figure 3 of the ASB. 

(iii) Fluorescent penetrant inspect each aft 

crosstube outboard of the upper center 

support as depicted in Figure 3 of the ASB 

for a crack. 

(iv) If there is a crack, before further flight, 

replace the cracked aft crosstube with an 

airworthy aft crosstube. 

(8) Revise the helicopter Airworthiness 

Limitations section of the applicable 

maintenance manuals or the Instructions for 

Continued Airworthiness (ICA) by 

establishing a new retirement life of 20,000 

takeoff and landings for aft crosstube P/N 

412–321–304 by making pen and ink changes 

or inserting a copy of this AD into the 

maintenance manual or the ICAs. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Martin R. Crane, 

Aviation Safety Engineer, Rotorcraft 

Directorate, Rotorcraft Certification Office, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, email 

martin.r.crane@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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 77, No. 23 / Friday, February 3, 2012 / Proposed Rules 5423 

(f) Additional Information 

The FAA approved AAI Instructions for 

Continued Airworthiness Report Number 

AA–01136 and the Bell Helicopter Textron 

Alert Service Bulletin No. 412–08–129, dated 

May 12, 2008, which are not incorporated by 

reference, contain additional information 

about inspecting the aft crosstube for a crack. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 32: Landing Gear. 

Issued in Fort Worth, Texas, on January 23, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–2423 Filed 2–2–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0087; Directorate 

Identifier 2011–SW–029–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada, Limited 

(Bell) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the Bell 

Model 206, 206A, 206A–1, 206B, 

206B–1, 206L, 206L–1, 206L–3, and 

206L–4 helicopters with Aviation 

Specialties Unlimited Inc. (ASU) Night 

Vision Imaging System (NVIS) lighting 

modified by Supplemental Type 

Certificate SR01383SE (STC). This 

proposed AD is prompted by the finding 

that an unfiltered turbine outlet 

temperature (TOT) indicator overtemperature warning light, when 

illuminated, created glare and 

reflections that could degrade the pilot’s 

view while using night vision goggles 

thereby creating an unsafe condition. 

The proposed actions are intended to 

modify any unfiltered TOT indicator 

unit over-temperature warning light by 

installing a filter to prevent degradation 

of the pilot’s vision while using night 

vision goggles and to prevent 

subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by April 3, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

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 Mail 

address above 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 Aviation 

Specialties Unlimited Inc., 4632 

Aeronca Street, Boise, Idaho 83705, 

telephone (208) 426–8117, fax (208) 

426–8975 or http://www.asu-nvg.com/. 

You may review copies of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd. 

Room 663, Fort Worth, TX 76137. 

FOR FURTHER INFORMATION CONTACT: 

Kathleen Arrigotti, Aviation Safety 

Engineer, FAA, Seattle Aircraft 

Certification Office, Airframe Branch, 

1601 Lind Avenue SW., Renton, 

Washington 98057, telephone (425) 

917–6426, fax (425) 917–6590; email 

kathleen.arrigotti@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 

proposal in light of the comments we 

receive. 

Discussion 

We propose to adopt a new AD for the 

specified Bell model helicopters with an 

ASU Night Vision Lighting Imaging 

System installed per STC SR01383SE. 

This proposed AD is prompted by the 

finding that an unfiltered TOT indicator 

over-temperature warning light, when 

illuminated, created glare and 

reflections that could degrade the pilot’s 

view while the pilot is using night 

vision goggles. This proposed AD would 

require determining the date of the STC 

installation, determining whether each 

helicopter has a TOT indicator unit with 

an internal over-temperature warning 

light. If an unfiltered TOT indicator 

over-temperature warning light is 

installed, this AD would require 

installing an NVIS filter. The proposed 

actions are intended to modify any 

unfiltered TOT indicator unit overtemperature warning light by installing 

a filter to prevent degradation of the 

pilot’s vision while using night vision 

goggles and to prevent subsequent loss 

of control of the helicopter. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other helicopters 

with NVIS lighting installed per STC 

SR01383SE on or before April 6, 2011. 

Relevant Service Information 

We reviewed ASU’s Alert Service 

Bulletin No. ASU 206–2010–11–1, dated 

November 4, 2010 (ASB) for the Bell 

Helicopter Textron 206 series 

helicopters. The ASB states to visually 

inspect each helicopter to determine if 

the TOT indicator/gauge has an internal 

over-temperature warning light 

installed. If the over-temperature 

warning light is internal, the ASB 

specifies notifying ASU. ASU states it 

will immediately ship an NVIS filter, 

part number (P/N) ASU–TOTGAG–1. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS