Federal Register / Vol. 78, No. 37 / Monday, February 25, 2013 / Proposed Rules 12651 

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 39–16717 (76 FR 

35330, June 17, 2011), and adding the 

following new AD: 

Robinson Helicopter Company: Docket No. 

FAA–2013–0159; Directorate Identifier 

2012–SW–010–AD. 

(a) Applicability 

This AD applies to Model R22, R22 Alpha, 

R22 Beta, and R22 Mariner helicopters with 

main rotor blade (blade), part number (P/N) 

A016–2 or A016–4; and Model R44 and R44 

II helicopters with blade, P/N C016–2 or C– 

016–5, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

blade skin debonding, which could result in 

blade failure and subsequent loss of control 

of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2011–12–10, 

Amendment 39–16717 (76 FR 35330, June 

17, 2011). 

(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) Before the first flight of each day, 

visually check for any exposed (bare metal) 

skin-to-spar joint area on the lower surface of 

each blade. The actions required by this 

paragraph may be performed by the owner/ 

operator (pilot) holding at least a private pilot 

certificate and must be entered into the 

aircraft records showing compliance with 

this AD in accordance with 14 CFR 

43.9(a)(1)–(4) and 14 CFR 91.417(a)(2)(v). The 

record must be maintained as required by 14 

CFR 91.417, 121.380, or 135.439. 

(2) If there is any bare metal in the area of 

the skin-to-spar bond line, before further 

flight, inspect the blade by following the 

requirements of paragraph (e)(3) of this AD. 

(3) Within 10 hours time-in-service (TIS), 

and at intervals not to exceed 100 hours TIS 

or at each annual inspection, whichever 

occurs first, inspect each blade for corrosion, 

separation, a gap, or a dent by following the 

Compliance Procedure, paragraphs 1 through 

6 and 8, of Robinson R22 Service Bulletin 

SB–103, dated April 30, 2010 (SB103), or 

Robinson Service Bulletin SB–72, dated 

April 30, 2010 (SB72), as appropriate for your 

model helicopter. Although the Robinson 

service information limits the magnification 

to 10 x, a higher magnification is acceptable 

for this inspection. Also, an appropriate tap 

test tool which provides similar performance, 

weight, and consistency of tone may be 

substituted for the ‘‘1965 or later United 

States Quarter-dollar coin,’’ which is 

specified in the Compliance Procedure, 

paragraph 2, of SB72 and SB103. 

(4) Before further flight, refinish any 

exposed area of a blade by following the 

Compliance Procedure, paragraphs 2 through 

6, of Robinson R22 Service Letter SL–56B or 

R44 Service Letter SL–32B, both dated April 

30, 2010, as appropriate for your model 

helicopter. 

(5) Before further flight, replace any 

unairworthy blade with an airworthy blade. 

(6) Within 5 years of the effective date of 

this AD: 

(i) For Model R22 series helicopters, 

replace blade P/N A016–2 or A016–4 with a 

blade, P/N A016–6. 

(ii) For Model R44 series helicopters fitted 

with hydraulically boosted main rotor flight 

controls, replace blade P/N C016–2 or C016– 

5 with a blade, P/N C016–7. 

(iii) For Model R44 series helicopters 

without hydraulically boosted main rotor 

flight controls, replace blade P/N C016–2 or 

C016–5 with a blade, P/N C016–7. Prior to 

installing a blade P/N C016–7, verify the 

helicopter has been modified as required by 

Robinson R44 Service Letter SL–37, dated 

June 18, 2010, Compliance Procedures, 

paragraphs 1. through 10. 

(iv) Installing blades, P/N A016–6 or P/N 

C016–7, is terminating action for the 

inspection requirements of paragraphs (e)(1) 

through (e)(4) of this AD. 

(f) Special Flight Permit 

Special flight permits will not be issued. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Fred Guerin, Aviation Safety Engineer, Los 

Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712; 

telephone (562) 627–5232; email 

fred.guerin@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. 

(h) Additional Information 

The Robinson letter titled ‘‘Additional 

Information Regarding Main Rotor Blade 

Skin Debonding,’’ dated May 25, 2007, which 

is not incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this 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 a copy of this information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(i) Subject. 

Joint Aircraft Service Component (JASC) 

Code: 6210: Main Rotor Blades. 

Issued in Fort Worth, Texas, on February 

12, 2013. 

Bruce Cain, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–04217 Filed 2–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0146; Directorate 

Identifier 2012–SW–060–AD] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. 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 S.p.A. (Agusta) Model A109E 

helicopters that requires reducing the 

tail rotor (T/R) blade life limit, 

modifying a T/R hub and grip assembly, 

re-identifying two T/R assemblies, 

clarifying the never-exceed speed (Vne) 

limitation and reducing the inspection 

interval. Since we issued that AD, the 

manufacturer has redesigned a T/R grip 

bushing (bushing) that reduces the 

loads, which caused the T/R cracking, 

on the T/R blades. This action would 

require installing the new bushing and 

re-identifying the T/R hub-and-grip and 

hub-and-blade assemblies and require a 

recurring inspection of each bushing. 

The proposed actions are intended to 

prevent fatigue failure of a T/R blade 

and subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by April 26, 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. 


erowe on DSK2VPTVN1PROD with PROPOSALS-1
12652 Federal Register / Vol. 78, No. 37 / Monday, February 25, 2013 / Proposed Rules 

• 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 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 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. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 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 June 12, 2002, a T/R blade on an 

Agusta Model 119 helicopter failed and 

resulted in an autorotative landing. As 

a result of this failure, based on the 

commonality of the T/R blades on the 

model 109E helicopter, Agusta issued 

Alert Bollettino Tecnico (ABT) No. 

109EP–30, dated June 21, 2002, for the 

Model 109E helicopter. The aviation 

authority for Italy, Ente Nazionale per 

L’Aviazione Civile (ENAC), issued 

Emergency AD No. 2002–340, dated 

June 28, 2002, for the Model 109E 

helicopters. On July 9, 2002, we issued 

Emergency AD 2002–14–51 to require a 

pilot-check before each flight, and 

initial and repetitive inspections of the 

T/R blades for a crack. 

‘‘As a precautionary measure,’’ Agusta 

issued Revision A, dated July 25, 2002, 

to ABT 109EP–30. On July 29, 2002, 

ENAC issued AD No. 2002–384, 

adopting the requirements of Revision A 

of this Agusta ABT. On October 17, 

2002, we issued immediately adopted 

AD 2002–17–51 (67 FR 67510, 

November 6, 2002) to require a 

reduction in VNE, a pilot-check of each 

T/R blade before each start of the 

helicopter engines, and initial and 

recurring inspections of each T/R blade 

for a crack. 

Following increased ground 

vibrations in a Model A 109E helicopter, 

another crack was discovered in a T/R 

blade, which prompted Agusta to issue 

Revision B, dated November 17, 2002, to 

ABT 109EP–30. Analysis and tests had 

shown that the fatigue failure of the T/ 

R blade was caused by unanticipated 

loads on the T/R blade. Revision B to 

that ABT specified maintaining the VNE

reduction until a new bushing was 

installed in the T/R grip assembly. 

Further, that ABT established, for T/R 

blade P/N 109–8132–01–111 on grip 

assembly P/N 109–8131–02–127, a 

retirement life of 200 hours TIS. ENAC 

adopted the provisions of Revision B of 

the Agusta ABT in ENAC AD No. 2002– 

592, dated November 28, 2002. 

On February 14, 2003, we issued AD 

2002–25–51, Amendment 39–13060 (68 

FR 9504, February 28, 2003), to require: 

For helicopters with T/R hub and 

blade assembly, part number (P/N) 109– 

8131–02–151 (the T/R hub and blade 

assembly consists of two T/R blades, P/ 

N 109–8132–01–111, and one T/R hub 

and grip assembly, P/N 109–8131–02– 

127): 

• Before further flight, installing a 

placard and marking the airspeed 

indicator to reduce the helicopter VNE

by 28 knots-indicated air speed (KIAS) 

in addition to any additional reduction 

in VNE caused by optional equipment. 

• Before each start of the helicopter 

engines, allowing an owner/operator 

(pilot) to check the T/R blade for a crack 

so long as the pilot records that AD 

compliance in the maintenance records 

in accordance with 14 CFR 43.9(a)(1)-(4) 

and 91.417(a)(2)(v). 

• Within 5 hours time-in-service 

(TIS), and thereafter at intervals not to 

exceed 5 hours TIS, and before further 

flight any time there is an increase in 

vibration levels, inspecting each T/R 

blade for a crack using a 5x or higher 

magnifying glass. 

• Establishing a new life limit for T/ 

R blade, P/N 109–8132–01–111, of 200 

hours TIS and requiring T/R blades with 

190 hours or more TIS to be replaced 

within 10 hours TIS. 

• On or before May 31, 2003, 

modifying and re-identifying the T/R 

hub and grip assembly and the T/R hub 

and blade assembly, which removes the 

VNE restriction and restores the T/R 

blade life limit to 1,000 hours TIS. 

For helicopters with T/R hub and 

blade assembly, P/N 109–8131–02–157 

(the T/R hub and blade assembly 

consists of two T/R blades, P/N 109– 

8132–01–111, and one T/R hub and grip 

assembly, P/N 109–8131–02–159): 

• Before each start of the helicopter 

engines, allowing an owner/operator 

(pilot) to check the T/R blade for a crack 

so long as the pilot records that AD 

compliance in the maintenance records 

in accordance with 14 CFR 43.9(a)(1)-(4) 

and 91.417(a)(2)(v). 

• Within 25 hours TIS, and thereafter 

at intervals not to exceed 25 hours TIS, 

and before further flight any time there 

is an increase in vibration levels, 

inspecting each T/R blade for a crack 

using a 5x or higher magnifying glass. 

• On or before accumulating 150 

hours TIS on the T/R hub assembly, P/ 

N 109–8131–02–159, and thereafter at 

intervals not to exceed 150 hours TIS, 

inspecting the bushings, P/N 109–8131– 

30–109, linings for wear, and replacing 

any unairworthy bushing. 

Also, the existing AD states that T/R 

blades, P/N 109–8132–01–111, which 

have been operated as part of the T/R 

hub and blade assembly, P/N 109–8131– 

02–151, are considered unairworthy 

components of the T/R hub and blade 

assembly, P/N 109–8131–02–157, 

regardless of TIS. 

Finally, AD 2002–25–51 requires 

replacing any unairworthy T/R blade 

before further flight. 


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Federal Register / Vol. 78, No. 37 / Monday, February 25, 2013 / Proposed Rules 12653 

Actions Since Existing AD Was Issued 

Since we issued AD 2002–25–51, 

Agusta has issued Revision C, dated 

September 29, 2006, to ABT No. 109EP– 

30, and states that the service 

experience of T/R hub and blade 

assemblies with the newly-designed 

bushings that reduce T/R blade loading 

has shown improvement and has 

determined that increasing the amount 

of time between inspections is 

appropriate, based upon the service 

history and the results of the 

maintenance performed. 

In response to Revision C of the ABT, 

the European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2006– 

0353, dated December 4, 2006, which 

supersedes ENAC AD 2002–597 to 

extend the inspection interval ‘‘from 

150 to 200 FH.’’ Subsequently, EASA 

AD No. 2007–0010, dated January 31, 

2007, was issued to supersede AD No. 

2006–0353 to restore the initial 

requirements of ABT 109EP–30, 

Revision C, which were unintentionally 

omitted from AD No. 2006–0353. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, EASA, its 

technical representative, has notified us 

of the unsafe condition 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 the same 

type design. 

Related Service Information 

We reviewed ABT No. 109EP–30, 

Revision C, dated September 29, 2006, 

which describes procedures for 

checking/inspecting for cracks on both 

the upper and lower surfaces of T/R 

blades, P/N 109–8132–01–111; 

replacing each bushing, P/N 109–0132– 

55 and spacer P/N 109–0132–13, with 

bushing, P/N 109–8131–30–109, and 

instituting a recurring inspection of 

each bushing; and cancelling the VNE

limitations when the newly-designed 

bushing is installed on each T/R grip 

assembly, P/N 109–8131–29–101, a 

‘‘new’’ pair of T/R blades, P/N 109– 

8132–01–111, is installed, and the T/R 

hub-and-grip and hub-and-blade 

assemblies are re-identified. 

Proposed AD Requirements 

This proposed AD would require: 

• Before each start of the helicopter 

engines, visually checking both sides of 

each T/R blade for a crack. An owner/ 

operator (pilot) may perform this check 

and must enter compliance into the 

aircraft records in accordance with 14 

CFR 43.9 (a)(1)-(4) and 14 CFR 

91.417(a)(2)(v). A pilot may perform this 

check because it involves only a visual 

check for a crack and can be performed 

equally well by a pilot or a mechanic. 

This procedure is an exception to our 

standard maintenance regulations. 

• For helicopters with T/R hub and 

blade assembly, P/N 109–8131–02–151, 

before further flight, modifying each T/ 

R hub and blade assembly by installing 

a new bushing in each grip assembly 

and two zero-TIS T/R blades; and reidentifying the hub and grip assembly 

and the T/R hub and blade assembly 

with different P/Ns. 

• For helicopters with T/R hub and 

blade assembly, P/N 109–8131–02–157, 

within 25 hours TIS and thereafter at 

intervals not to exceed 25 hours TIS, 

and before further flight any time there 

is an increase in vibration levels, using 

a 5x or higher power magnifying glass, 

visually inspecting each T/R blade for a 

crack. 

• On or before accumulating 200 

hours TIS on the T/R hub and grip 

assembly, and thereafter at intervals not 

to exceed 200 hours TIS, inspecting the 

linings and measuring the internal 

diameter of the bushings. If the internal 

diameter of the bushing exceeds 41.35 

millimeters, replacing the bushing. 

• If there is a crack, before further 

flight, replacing the T/R blade. 

• Revising the Airworthiness 

Limitations section of the maintenance 

manual to reflect that a T/R blade, P/N 

109–8132–01–111, which has not been 

operated as part of T/R hub and blade 

assembly, P/N 109–8131–02–151, has a 

retirement life of 1,000 hours TIS. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 75 helicopters of U.S. 

Registry. Based on an average labor rate 

of $85 per hour, we estimate that 

operators may incur the following costs 

in order to comply with this AD: 

• Visually inspecting the T/R blades 

would require about 0.5 work hours for 

a cost per helicopter of $43 and a total 

cost to U.S. operators of $3,225 per 

inspection cycle. 

• Replacing a cracked T/R blade 

would require about 2 work hours, and 

required parts would cost about 

$25,320, for a total cost per helicopter 

of $25,490. 

• Modifying the hub assembly with 

new T/R blades and bushings would 

require about 16 work hours, and 

required parts would cost about 

$58,690, for a total cost per helicopter 

of $60,050. 

• Inspecting the T/R bushings would 

require about 7 work hours, for a cost 

per helicopter of $595 and a total cost 

to U.S. operators of $44,625 per 

inspection cycle. 

• Revising the Airworthiness 

Limitations section of the maintenance 

manual would require about .25 work 

hour, for a cost per helicopter of $22 

and a total cost to U.S. operators of 

$1,650. 

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. 


erowe on DSK2VPTVN1PROD with PROPOSALS-1
12654 Federal Register / Vol. 78, No. 37 / Monday, February 25, 2013 / Proposed Rules 

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 to read 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 39–13060 (68 FR 

9504, February 28, 2003), and adding 

the following new Airworthiness 

Directive (AD): 

AGUSTA S.p.A. (Agusta): Docket No. FAA– 

2013–0146; Directorate Identifier 2012– 

SW–060–AD. 

(a) Applicability 

This AD applies to Agusta Model 109E 

helicopters with tail rotor (T/R) hub and 

blade assembly, part number (P/N) 109– 

8131–02–151 and P/N 109–8131–02–157, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

fatigue crack in a T/R blade. This condition 

could result in failure of the T/R blade and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2002–25–51, 

Docket No. 2002–SW–55–AD, Amendment 

39–13060 (68 FR 9504, February 28, 2003). 

(d) Reserved 

(e) 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. 

(f) Required Actions 

(1) Before each start of the helicopter 

engines, visually check both sides of each 

T/R blade for a crack in the inspection area 

depicted in Figure 1 to paragraph (f) of this 

AD. This action may be performed by the 

owner/operator (pilot) holding at least a 

private pilot certificate, and must be entered 

into the aircraft records showing compliance 

with this AD in accordance with 14 CFR 43.9 

(a)(1)–(4) and 14 CFR 91.417(a)(2)(v). The 

record must be maintained as required by 14 

CFR 91.173, 121.380, or 135.439. 

BILLING CODE 4910–13–P 

BILLING CODE 4910–03–C 

(2) For helicopters with T/R hub and blade 

assembly, P/N 109–8131–02–151 (consisting 

of two T/R blades, P/N 109–8132–01–111, 

and one T/R hub and grip assembly, P/N 

109–8131–02–127), before further flight, 

modify each T/R hub and blade assembly by 

installing a new bushing, P/N 109–8131–30– 

109, in each grip assembly and two zero-hour 

time-in-service (TIS) T/R blades, P/N 109– 

8132–01–111; re-identifying the hub and grip 

assembly as P/N 109–8131–02–159; and reidentifying the T/R hub and blade assembly 

as P/N 109–8131–02–157 in accordance with 

the Compliance Instructions, Part V, 

paragraphs 2. through 13., of Agusta 

Bollettino Tecnico No. 109EP–30, Revision C, 

dated September 29, 2006 (BT). A T/R blade, 

P/N 109–8132–01–111, which has been 

operated as part of T/R hub and blade 

assembly, P/N 109–8131–02–151, must be 

retired regardless of TIS and may not be used 

as part of the T/R hub and blade assembly, 

P/N 109–8131–02–157. Returning the 

removed T/R blades, grips, or bushings to 

Agusta is not required. 

(3) For helicopters with T/R hub and blade 

assembly, P/N 109–8131–02–157 (consisting 

of two T/R blades, P/N 109–8132–01–111, 

and one T/R hub and grip assembly, P/N 

109–8131–02–159), within 25 hours TIS, and 

thereafter at intervals not to exceed 25 hours 

TIS, and before further flight any time there 

is an increase in vibration levels, using a 5x 

or higher power magnifying glass, visually 

inspect each T/R blade for a crack in 

accordance with the Compliance 

Instructions, Part III, paragraphs 1. through 5. 

of the BT. Reporting to Agusta is not 

required. 

(4) On or before accumulating 200 hours 

TIS on the T/R hub and grip assembly, P/N 


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Federal Register / Vol. 78, No. 37 / Monday, February 25, 2013 / Proposed Rules 12655 

109–8131–02–159, and thereafter at intervals 

not to exceed 200 hours TIS, inspect the 

linings and measure the internal diameter of 

the bushings, P/N 109–8131–30–109, by 

referring to Figure 2 of the BT. If the internal 

diameter of the bushing exceeds 41.35 

millimeters, replace the bushing. 

(5) If there is a crack in a T/R blade, before 

further flight, replace the cracked T/R blade. 

(6) Revise the Airworthiness Limitations 

section of the maintenance manual to reflect 

that a T/R blade, P/N 109–8132–01–111, 

which has not been operated as part of T/R 

hub and blade assembly, P/N 109–8131–02– 

151, has retirement life of 1,000 hours TIS. 

(g) Special Flight Permit 

Special flight permits will not be issued. 

(h) 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, Regulations and 

Policy Group, 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. 

(i) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2007–0010, dated January 31, 2007. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, Tail Rotor Blades. 

Issued in Fort Worth, Texas, on February 

11, 2013. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–04220 Filed 2–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Employment and Training 

Administration 

20 CFR Part 619 

RIN 1205–AB64 

Federal-State Unemployment 

Insurance (UI) Program; Data 

Exchange Standardization as Required 

by Section 2104 of the Middle Class 

Tax Relief and Job Creation Act of 

2012 

AGENCY: Employment and Training 

Administration, Labor. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Department of Labor’s 

(Department’s) Employment and 

Training Administration proposes to 

designate in regulation data exchange 

standards, developed in consultation 

with an interagency work group 

established by the Office of Management 

and Budget (OMB), for Unemployment 

Insurance (UI) administration as 

required by amendments to Title IX of 

the Social Security Act (SSA) made by 

the Middle Class Tax Relief and Job 

Creation Act of 2012 (the Act). This 

proposed regulation would establish 

data exchange standards for three 

categories of information: real-time 

applications on the Interstate 

Connection Network (ICON); the State 

Information Data Exchange System 

(SIDES); and implementation of the 

standards identified for ICON and 

SIDES in major Information Technology 

(IT) modernization projects to upgrade 

UI Benefits and Tax systems by State 

Workforce Agencies (SWAs) using 

Federal funds. 

DATES: Submit comments on or before 

April 26, 2013. 

ADDRESSES: You may submit comments, 

identified by Regulatory Information 

Number (RIN) 1205–AB64, by one of the 

following methods: 

Federal e-Rulemaking Portal: http:// 

www.regulations.gov. Follow the Web 

site instructions for submitting 

comments. 

Mail and hand delivery/courier: 

Written comments, disk, and CD–ROM 

submissions may be mailed to Michael 

S. Jones, Acting Administrator, Office of 

Policy Development and Research, U.S. 

Department of Labor, 200 Constitution 

Avenue NW., Room N–5641, and 

Washington, DC 20210. 

Instructions: Label all submissions 

with ‘‘RIN 1205–AB64.’’ 

Please submit your comments by only 

one method. Please be advised that the 

Department will post all comments 

received that relate to the proposed data 

exchange standardization on http:// 

www.regulations.gov without making 

any change to the comments or 

redacting any information. The http:// 

www.regulations.gov Web site is the 

Federal e-rulemaking portal and all 

comments posted there are available 

and accessible to the public. Therefore, 

the Department recommends that 

commenters remove personal 

information such as Social Security 

Numbers, personal addresses, telephone 

numbers, and email addresses included 

in their comments as such information 

may become easily available to the 

public via the http:// 

www.regulations.gov Web site. It is the 

responsibility of the commenter to 

safeguard personal information. 

Also, please note that due to security 

concerns, postal mail delivery in 

Washington, DC may be delayed. 

Therefore, the Department encourages 

the public to submit comments on 

http://www.regulations.gov. 

Docket: All comments on this 

proposed rule will be available on the 

http://www.regulations.gov Web site 

and can be found using RIN 1205–AB64. 

The Department also will make all the 

comments it receives available for 

public inspection by appointment 

during normal business hours at the 

above address. If you need assistance to 

review the comments, the Department 

will provide appropriate aids such as 

readers or print magnifiers. The 

Department will make copies of this 

proposed rule available, upon request, 

in large print and electronic file on 

computer disk. To schedule an 

appointment to review the comments 

and/or obtain the proposed rule in an 

alternative format, contact the Office of 

Policy Development and Research at 

(202) 693–3700 (this is not a toll-free 

number). You may also contact this 

office at the address listed below. 

Instructions for Submitting Comments 

on Paperwork Burden: Submit any 

comments that concern the information 

collection request to the Office of 

Information and Regulatory Affairs, 

Attn: OMB Desk Officer for DOL–ETA, 

Office of Management and Budget, 

Room 10235, 725 17th Street NW., 

Washington, DC 20503, Fax: 202–395– 

6881 (this is not a toll-free number), 

email: OIRA_submission@omb.eop.gov. 

OMB recommends that comments on 

the information collection requirements 

be submitted within 30 days of 

publication of this NPRM. Comments on 

the information collections may also be 

submitted to the ETA in the same 

manner as any other issue addressed in 

this NPRM. 

FOR FURTHER INFORMATION CONTACT: 

Michael S. Jones, Acting Administrator, 

Office of Policy Development and 

Research, U.S. Department of Labor, 200 

Constitution Avenue NW., Room N– 

5641, Washington, DC 20210; telephone 

(202) 693–3700 (this is not a toll-free 

number). 

Individuals with hearing or speech 

impairments may access the telephone 

number above via TTY by calling the 

toll-free Federal Information Relay 

Service at 1–800–877–8339. 

SUPPLEMENTARY INFORMATION: The 

preamble to this proposed rule is 

organized as follows: 

I. Background—provides a brief description 

of the development of the proposed rule. 


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