24368 Federal Register / Vol. 78, No. 80 / Thursday, April 25, 2013 / Proposed Rules 

and external sides of the junction areas 

would require 0.5 work-hour for a labor 

cost of about $43. No parts would be 

needed, so the cost for the U.S. fleet 

would total $2,795. 

• Adding the bonding material if 

needed would require about 1.5 workhours for a labor cost of about $128. The 

cost of materials would be negligible. 

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 airworthiness 

directive (AD): 

AGUSTAWESTLAND S.p.A.: Docket No. 

FAA–2013–0350; Directorate Identifier 

2012–SW–050–AD. 

(a) Applicability 

This AD applies to AgustaWestland S.p.A. 

(AgustaWestland) Model A119 and AW119 

MKII helicopters, serial numbers up to and 

including 14781, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

window detaching from the pilot or co-pilot 

doors, which could result in damage to the 

helicopter and injury to persons on the 

ground. 

(c) Reserved 

(d) 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. 

(e) Required Actions 

Within the next 50 hours time-in-service 

(TIS) or within the next five months, 

whichever comes first: 

(1) Visually inspect the pilot and co-pilot 

doors by referencing Figure 1 of Bollettino 

Tecnico No. 119–47, dated March 29, 2012 

(BT), to determine whether there is bonding 

between the seal (3) and the window (4) in 

the internal and external side of the seal’s 

junction area. 

(2) If there is no bonding, before further 

flight, apply bonding to the windows, seals, 

and window frames in accordance with the 

Compliance Instructions, paragraphs 5 

through 20, of the BT. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email sharon.y.miles@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR 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. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2012–0058, dated April 3, 2012. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5610, Flight Compartment Windows. 

Issued in Fort Worth, Texas, on April 12, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–09715 Filed 4–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0379; Directorate 

Identifier 2009–SW–26–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. (Bell) Model 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing revised airworthiness directive 

(AD) for all Bell Model 204B and certain 

serial-numbered Model 205A–1 

helicopters with a certain tail rotor pitch 

control chain (chain) installed. The 

existing AD requires visually inspecting 

the chain to detect a crack in the link 

segments and, for affected Model 205A– 

1 helicopters, replacing the tail rotor 

chain and cable control system with a 

push-pull control system. Since we 

issued that AD, we have determined the 

need to apply the requirements to a 

newly-produced, similarly-designed 

chain with a different part number. 

Also, for the Model 204B, data shows 

the need to reduce the inspection 

interval of the chain and revise its 

inspection procedures because the rapid 

growth of a crack can lead to premature 

chain failure and to install a tail rotor 

cable and chain damper kit (damper kit) 

to reduce the oscillatory loading. We 

have also determined that installing a 

push-pull control system should apply 

to Model 205A–1 helicopters with 


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certain serial numbers, regardless of the 

chain part number installed. These 

proposed actions are intended to 

prevent failure of the chain, loss of tail 

rotor blade pitch control, and 

subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by June 24, 2013. 

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, ASW–170, Aviation 

Safety Engineer, Rotorcraft Directorate, 

Rotorcraft Certification Office, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax 

(817) 222–5783, email 

mike.kohner@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 

On June 3, 1976, we issued AD 76– 

12–07, Amendment 39–2640 (41 FR 

23939, June 14, 1976), Docket No. 76– 

SW–19. That AD required repetitive 

inspections, at intervals not to exceed 

25 hours time-in-service (TIS), for a 

chain, part number (P/N) 204–001–739– 

003, installed on Bell Model 204B and 

205A–1 helicopters. This AD also 

required, before further flight, replacing 

chains with cracked or broken links or 

segments. 

On September 12, 1979, we revised 

AD 76–12–07 by issuing Amendment 

39–3569 (44 FR 55555, September 27, 

1979). That amendment limits the 

applicability for the Model 205A–1 

helicopter to those with a serial number 

(S/N) of 30001 through 30228; decreases 

the inspection interval of the chain from 

25 hours TIS to 10 hours TIS; and 

requires replacing the existing chain 

and cable control system with a pushpull control system. 

Both amendments were prompted by 

several chain failures occurring in flight 

and reports of cracked chain links on 

Model 205A–1 helicopters. Those 

actions are intended to detect cracks in 

the chain link segments to prevent 

failure of a chain and subsequent loss of 

directional control of the helicopter. 

Actions Since Existing ADs Were Issued 

Since we issued the original (June 3, 

1976) and revised (September 12, 1979) 

versions of AD 76–12–07, we have 

approved a very-similarly designed 

chain, P/N 204–001–739–105, eligible 

for installation on Model 204B 

helicopters. Testing by the manufacturer 

has shown that the fatigue 

characteristics for the two chains are 

almost identical, and the requirements 

of AD 76–12–07 should apply to this 

additional part-numbered chain. Also, 

we have determined that this crack can 

grow quickly, and thus the recurring 

inspection interval for the Model 204B 

should be reduced from 25 hours TIS to 

10 hours TIS and should include 

procedures to slowly operate the cockpit 

anti-torque control pedals during the 

inspection. This is so that the entire 

surface area of the chain in contact with 

the control quill sprocket (sprocket), 

including that portion underneath the 

sprocket, can be inspected. Testing has 

also shown a reduction in the 

oscillatory loading of the chain when a 

damper kit is installed. To complement 

these requirements, we have determined 

for the Model 204B that we should 

revise the Airworthiness Limitations 

section of the maintenance manual, or 

the Instructions for Continued 

Airworthiness (ICAs), to include the 10 

hours TIS recurring inspection. 

We have also determined that the 

requirement in AD 76–12–07 for the 

Model 205A–1 to replace the tail rotor 

chain and cable control system with a 

push-pull control system should apply 

regardless of chain part number 

installed. This would be required before 

further flight to ensure that any partnumbered chain cannot be installed on 

a Model 205A–1 helicopter, which 

should already have a push-pull control 

system installed in accordance with the 

requirement in AD 76–12–07. The 

actions in this proposed AD are 

intended to prevent failure of the chain, 

loss of tail rotor blade pitch control, and 

subsequent loss of control of the 

helicopter. 

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 helicopters of these 

same type designs. 

Related Service Information 

The FAA has reviewed Bell Alert 

Service Bulletin (ASB) No. 204–75–4, 

dated December 16, 1975, for the Model 

204B helicopter, which specifies to 

visually inspect the chain using a 10- 

power magnifying glass every 10 flight 

hours. The inspection intervals for a 

chain were reduced because of several 

field reports of cracked and broken 

links. We have also reviewed Bell ASB 

204–79–7, dated August 21, 1979, 


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which specifies the installation of a 

damper kit. A field evaluation has 

shown considerable improvement in the 

reliability of the chain when a damper 

kit is installed. 

Further, we have reviewed Bell ASB 

No. 205–78–5, dated May 16, 1978, for 

Model 205A–1 helicopters, serial 

number 30001 through 30228, which 

specifies removing the tail rotor chain 

and cable control system and installing 

a push-pull control system kit, P/N 205– 

704–057–001 or 205–704–057–101. The 

tail rotor push-pull control system is 

installed in accordance with Service 

Instructions (SI) No. 205–38, ‘‘changed’’ 

March 28, 1990, for an improved tail 

rotor hub and blade assembly kit, P/N 

205–704–040–001 and 205–704–040– 

003, and SI No. 205–46, revised March 

7, 1980, for installing a push/pull antitorque retrofit kit. 

Proposed AD Requirements 

The proposed AD would require: 

• For Bell Model 205A–1 helicopters, 

S/N 30001 through 30228, before further 

flight, replacing the tail rotor chain and 

cable control system with an airworthy 

tail rotor push-pull control system by 

installing an improved tail rotor hub 

and blade assembly kit, P/N 205–704– 

040–001 or 205–704–040–003, and then 

installing a push/pull anti-torque 

retrofit kit, P/N 205–704–057–001 or 

205–704–057–101. 

• For Bell Model 204B helicopters, 

visually inspecting chains, P/N 204– 

001–739–003 and –105, at 10-hour TIS 

intervals using a 10-power or higher 

magnifying glass and a light; revising 

the inspection procedures; installing a 

damper kit; and revising the 

maintenance manual or ICAs to include 

the inspection intervals. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 13 Model 204B and 52 

Model 205A–1 helicopters of U.S. 

registry and that operators may incur 

the following costs: 

• Visual inspection of the link 

segments in a chain on a Model 204B 

helicopter will require .25 work hour for 

each inspection, 60 per year, at an 

average labor rate of $85 per work hour 

for a cost per helicopter of $1,275 and 

fleet cost of $16,575; 

• Replacement of a chain having a 

cracked or broken link or segment on a 

Model 204B helicopter would require .5 

work hour and a parts cost of $4,922, for 

a cost per helicopter of $4,965 and a 

total cost of $9,930 (assuming 2 would 

be replaced); 

• Installation of a damper kit on a 

Model 204B helicopter would require 3 

work hours and a parts cost of $14,925, 

for a cost per helicopter of $15,180 and 

a total cost of $30,360 (assuming 2 

would be installed); and 

• Installation of a tail rotor push-pull 

control system on an affected Model 

205A–1 helicopter would require 225 

work hours and a parts cost of $152,214, 

for a cost per helicopter of $171,339. 

Therefore, we estimate the total cost 

impact of the proposed AD on U.S. 

operators to be $228,204. 

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, pursuant to the 

authority delegated to me by the 

Administrator, the FAA proposes to 

amend 14 CFR part 39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–3569 (44 FR 

55555, September 27, 1979), which 

amended Amendment 39–2640 (41 FR 

23939; June 14, 1976), and by adding 

the following new airworthiness 

directive (AD): 

Bell Helicopter Textron (Bell): Docket No. 

FAA–2013–0379; Directorate Identifier 

2009–SW–26–AD. 

(a) Applicability 

This AD applies to Model 204B helicopters 

with a tail rotor pitch control chain (chain), 

part number (P/N) 204–001–739–003 or –105, 

installed, and Model 205A–1 helicopters 

with a serial number (S/N) 30001 through 

30228, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a chain, which can grow quickly 

because of oscillatory loads and lead to 

premature failure of the chain, loss of the tail 

rotor blade pitch control, and subsequent loss 

of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 76–12–07, 

Amendment 39–2640 (41 FR 23939, June 14, 

1976) as revised by Amendment 39–3569 (44 

FR 55555, September 27, 1979). 

(d) 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. 

(e) Required Actions 

(1) For Model 205A–1 helicopters, before 

further flight, replace the tail rotor chain and 

cable control system with an airworthy tail 

rotor push-pull control system by installing 

an improved tail rotor hub and blade 

assembly kit, P/N 205–704–040–001 or 205– 

704–040–103, and then installing a push/pull 

anti-torque retrofit kit, P/N 205–704–057–001 

or 205–704–057–101. 

(2) For Model 204B helicopters: 

(i) Within 10 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 10 

hours TIS, using a 10-power or higher 

magnifying glass and a light, visually inspect 


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each of the link segments in the chain for a 

crack. Also, slowly operate the cockpit antitorque control pedals during the inspection 

so that the entire surface area of the chain in 

contact with the control quill sprocket 

(sprocket) is visibly accessible and can be 

inspected. Pay particular attention to the 

portion of the chain that travels over the 

sprocket and extends 6 inches to each side 

of the sprocket. 

(A) If there is no cracked or broken link 

segment, lubricate the chain with a light 

preservative oil (C–125) or wipe with a cloth 

dampened in lubricating oil (C–010). 

(B) If there is a cracked or broken link 

segment, before further flight, replace the 

chain with an airworthy chain. 

(ii) Within 50 hours TIS, install a tail rotor 

cable and chain damper kit, P/N 204–706– 

130–101, as depicted in Figures 1 through 3, 

and by following the Accomplishment 

Instructions, paragraphs 2. through 9., of Bell 

Alert Service Bulletin (ASB) No. 204–79–7, 

dated August 21, 1979. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to Michael Kohner, 

ASW–170, Aviation Safety Engineer, 

Rotorcraft Directorate, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone (817) 

222–5170, fax (817) 222–5783, email 

mike.kohner @faa.gov. 

(2) For operations conducted under 14 CFR 

part 119 operating certificate or under 14 

CFR 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. 

(g) Additional Information 

(1) Bell Alert Service Bulletin (ASB) No. 

204–75–4, dated December 16, 1975, and Bell 

ASB No. 205–78–5, dated May 16, 1978, 

which are not incorporated by reference, 

contain additional information about the 

subject of this AD. For this service 

information, 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. 

(2) The subject of this AD is addressed in 

Transport Canada AD CF–1990–06R1, issued 

January 7, 2008. 

(h) Subject 

The Joint Aircraft System Component 

(JASC) Code is 6720: Tail Rotor Control 

System. 

Issued in Fort Worth, Texas, on April 18, 

2013. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–09764 Filed 4–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0380; Directorate 

Identifier 2012–SW–067–AD] 

RIN 2120–AA64 

Airworthiness Directives; Robinson 

Helicopter Company (Robinson) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Model 

R22, R22 Alpha, R22 Beta, and R22 

Mariner helicopters with certain fuel 

shut-off valves installed. This proposed 

AD would require replacing the fuel 

shut-off valve with a newer design fuel 

shut-off valve. This proposed AD is 

prompted by three accidents that 

occurred because the fuel shut-off valve 

was inadvertently moved to the ‘‘off’’ 

position. The proposed actions are 

intended to prevent inadvertent closing 

of the fuel valve, which could result in 

engine power loss and subsequent loss 

of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by June 24, 2013. 

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 Robinson 

Helicopter Company, 2901 Airport 

Drive, Torrance, CA 90505; telephone 

(310) 539–0508; fax (310) 539–5198; or 

at http://www.robinsonheli.com/ 

servelib.htm. You may review 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: 

Danny Nguyen, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 

3960 Paramount Blvd., Lakewood, 

California 90712; telephone (562) 627– 

5247; email danny.nguyen@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 

Three accidents have occurred with 

R22 helicopters because the leverhandle fuel valve was inadvertently 

moved to the ‘‘off’’ position before 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS