This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

54594 

Vol. 78, No. 172 

Thursday, September 5, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0752; Directorate 

Identifier 2009–SW–44–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Scientific Aviation Services (Pacific 

Scientific) Seat Restraint System 

Rotary Buckle Assemblies 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

specified Pacific Scientific seat restraint 

rotary buckle assemblies (buckle). This 

proposed AD is prompted by several 

reports of a cracked handle on certain 

buckles. Testing on these buckles 

indicates that in some circumstances a 

load placed on the restraint system 

prevents a strap from releasing as 

intended when the buckle is rotated. 

The proposed actions are intended to 

replace cracked buckle handles and 

allow the release of the restraint system 

strap in an emergency. 

DATES: We must receive comments on 

this proposed AD by November 4, 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 Pacific 

Scientific Aviation Services, 11700 NW 

102nd Rd. #6, Miami, Florida 33178, 

telephone 305–477–4711, fax 305–477– 

9799 or at www.pacscimiami. 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: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone 817–222–5110; email 

robert.grant@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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No. 

2007–0256, dated September 19, 2007, 

to correct an unsafe condition for 

certain Pacific Scientific Seat Restraint 

System Plastic Rotary Buckle Handles. 

According to EASA, Pacific Scientific 

reports several instances of cracked 

handles on certain buckles with a date 

of manufacture from November 2004 

through May 2007. Testing on buckles 

with a cracked handle indicates that in 

some circumstances a load placed on 

the restraint system prevents a strap 

from releasing as intended when the 

buckle is rotated. EASA states that these 

circumstances happen when a passenger 

weighs more than 50 kg (approximately 

110 lbs.) and an aircraft is upside down. 

The EASA AD also states that these 

circumstances are considered ‘‘possible 

to take place for helicopters only and 

not for large aeroplanes.’’ 

Further, EASA states that buckle part 

numbers 1111430–XX and 1111475–XX, 

manufactured from November 2004 

through May 2007, are used in 7 partnumbered restraint systems, which are 

known to be installed on, but not 

limited to, Eurocopter France Model 

AS350, AS355, EC120, EC 130, and 

EC155 helicopters. 

The proposed actions are intended to 

prevent a buckle from not releasing the 

restraint system strap in an emergency. 

FAA’s Determination 

This product has been approved for 

operation in the United Kingdom and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with the United Kingdom, 

EASA, its technical representative, has 

notified the FAA of the situation 

described in its AD. We are proposing 

this AD because we evaluated all known 

relevant information and determined 

that an unsafe condition is likely to 

exist or develop on other products of 

this same type design. 

Related Service Information 

Pacific Scientific has issued Service 

Bulletin 25–1111432, dated May 22, 

2007 (SB). The SB specifies inspecting 


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Federal Register / Vol. 78, No. 172 / Thursday, September 5, 2013 / Proposed Rules 54595 

each buckle, part number (P/N) 

1111430–XX or 1111475–XX with a date 

of manufacture between November 2004 

and May 2007, to identify whether the 

handle is one susceptible to cracking by 

checking the P/N on the reverse side of 

the buckle assembly against the P/N 

listed in Appendix 1 of the SB or by 

measuring the thickness of the handle 

vane. If the buckle is identified as a 

‘‘suspect’’ buckle, the SB provides 

procedures for removing the buckle and 

replacing it with an acceptable buckle. 

Information in the SB also advises that 

buckles with a cracked handle should 

be removed from service immediately. 

Proposed AD Requirements 

This proposed AD would require, 

within 30 days, inspecting each buckle 

for a crack and replacing any cracked 

buckle with an airworthy buckle by 

complying with paragraph 9 of the SB. 

Also, within 6 months, this proposed 

AD would require inspecting the 

thickness of the buckle handle vane and 

replacing any buckle with a handle vane 

thickness of 0.125 inch or greater. 

Lastly, this proposed AD would prohibit 

installing an affected buckle on any 

helicopter or airplane. 

Differences Between This Proposed AD 

and the EASA AD 

The EASA AD applies to certain 

Eurocopter model helicopters only. 

Since the affected buckles may be 

installed in other aircraft resulting in 

the same unsafe condition, this 

proposed AD would also apply to those 

aircraft. We would not require you to 

return the unairworthy buckle assembly 

to the manufacturer, and this AD would 

not apply to ‘‘spare’’ parts that are not 

installed on an aircraft. Also, this AD 

would apply to buckle P/Ns 1111430 

and 1111475, all dash numbers, and 

would not be dependent on the restraint 

P/Ns. This AD would not require an 

inspection for cracks ‘‘before any flight’’ 

for the 6 months until the affected 

buckles are replaced. Finally, the EASA 

AD identifies suspect parts by date of 

manufacture, and this AD would not. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 1,435 restraint systems 

installed on aircraft of U.S. registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD: 

• A minimal cost and amount of time 

to inspect for an affected buckle. 

• $43 in labor costs for 0.5 hour to 

replace any affected buckle at an 

estimated labor cost of $85 per workhour. 

• $250 for required parts to replace a 

buckle. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators would be $293 per restraint 

system or $420,455 for the fleet. 

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): 

Pacific Scientific Aviation Services: Docket 

No. FAA–2003–0752; Directorate 

Identifier 2009–SW–44–AD. 

(a) Applicability 

This AD applies to Pacific Scientific rotary 

buckle assembly (buckle), part number (P/N) 

1111430 or 1111475, all dash numbers, 

installed on but not limited to Cessna 

Aircraft Company, de Havilland, Inc. (TC 

currently held by Viking Air Limited), and 

Learjet Inc. model airplanes and Eurocopter 

France model helicopters, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

cracked rotary buckle handle, which could 

prevent a strap from releasing as intended 

when the buckle is rotated. 

(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) Comments Due Date 

We must receive comments by November 

4, 2013. 

(e) Required Actions 

(1) Within 30 days, inspect the buckle 

handle for a crack. If the buckle handle is 

cracked, before further flight, remove the 

buckle as depicted in Figure 5 and by 

following the Procedures, paragraph 9, of 

Pacific Scientific Service Bulletin (SB) 25– 

1111432, dated May 22, 2007, and replace it 

with an airworthy buckle, except you are not 

required to return the removed buckle to 

Pacific Scientific. 

(2) Within 6 months, measure the thickness 

of the buckle handle vane as depicted in 

Figure 3 of the SB. If the handle vane 

thickness is 0.125 inch or greater, before 

further flight, remove the buckle from service 

and replace it with an airworthy buckle. 

(3) Do not install a buckle or a restraint 

system with a buckle, P/N 1111430 or 

1111475, all dash numbers, with a handle 

vane thickness of 0.125 inch or greater on 

any helicopter or airplane. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 


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54596 Federal Register / Vol. 78, No. 172 / Thursday, September 5, 2013 / Proposed Rules 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone 817–222– 

5110; email robert.grant@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. 

(g) Additional Information 

(1) You may review a copy of the 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 

European Aviation Safety Agency AD 

No.2007—0256, dated September 19, 2007. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2500 Cabin Equipment/Furnishings. 

Issued in Fort Worth, Texas, on August 22, 

2013. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–21570 Filed 9–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0751; Directorate 

Identifier 2012–SW–051–AD] 

RIN 2120–AA64 

Airworthiness Directives; 

AgustaWestland S.p.A. (Type 

Certificate Formerly Held by Agusta 

S.p.A) (Agusta) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) for 

Agusta Model AB139 and AW139 

helicopters. The existing AD currently 

requires establishing a revised life limit 

for each tail rotor blade (blade), 

updating the helicopter’s historical 

records, repetitively inspecting each 

blade for a crack, and replacing certain 

blades. Since we issued that AD, the 

manufacturer has improved the design 

of the blades using different materials 

and established life limits for each 

newly-designed blade. This proposed 

AD would expand the applicability to 

include the newly-designed blades and 

establish their life limits. This proposed 

AD would also retain the requirement to 

inspect each blade for a crack and, if 

there is a crack, replace each blade with 

an airworthy blade. The proposed 

actions are intended to detect a crack in 

a blade to prevent failure of a blade and 

subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by November 4, 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 

foreign authority’s 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 Agusta 

Westland, Customer Support & Services, 

Via Per Tornavento 15, 21019 Somma 

Lombardo (VA) Italy, ATTN: Giovanni 

Cecchelli; telephone 39–0331–711133; 

fax 39 0331 711180; or at http://

www.agustawestland.com/technicalbullettins. 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: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@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 August 26, 2011, we issued 

Emergency AD (EAD) 2011–18–52 for 

the Agusta Model AB139 and AW139 

helicopters. We published EAD 2011– 

18–52 as a final rule; request for 

comments in the Federal Register (77 

FR 23109, April 18, 2012). EAD 2011– 

18–52 requires revising the life limits 

for each blade, part number (P/N) 

3G6410A00131 and 4G6410A00131, 

updating the helicopter’s historical 

records, repetitively inspecting each 

blade for a crack, and replacing certain 

blades. That action was prompted by a 

fatal accident involving an Agusta 

Model AW139 helicopter, which may 

have been caused by cracks in a blade. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, notified us of the unsafe 

condition and issued EASA EAD No. 

2011–0156–E, dated August 25, 2011, to 

require repetitive inspections and 

reduce the life limit of the blades. This 

condition, if not detected and corrected, 

could result in failure of a blade and 

subsequent loss of control of the 

helicopter. 

Actions Since Existing AD Was Issued 

Since we issued EAD No. 2011–18– 

52, the manufacturer first developed 

two new blades with an improved 


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