Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Rules and Regulations 28125 

that applicants may be able to present their 

identification at other locations where EOIR 

hearings are conducted, including those where 

hearings are conducted by video conference. 

Detailed information about the required identity 

validation process for eRegistry, including 

permissible forms of identification and locations 

where EOIR will validate identities, will be 

available on EOIR’s Web site. The list of permissible 

forms of identification will also be available during 

the online registration process. 

7EOIR will not permit electronic filing of the 

Form EOIR–27 and Form EOIR–28 in certain 

limited situations, including, but not limited to, 

bond redetermination requests made before the 

filing of a Notice to Appear with the immigration 

court, appeals of decisions involving fines and 

penalties, and appeals of decisions of adjudicating 

officials in practitioner disciplinary proceedings. A 

complete list of situations in which EOIR will not 

permit electronic filing of the Form EOIR–27 and 

Form EOIR–28 will be available on EOIR’s Web site. 

registry applicant successfully 

completes the identity validation 

process, EOIR will send an email 

notifying the registrant that it has 

activated his or her account and will 

assign an EOIR ID number. Each 

registrant will be required to include the 

EOIR ID number when filing a Form 

EOIR–27, Notice of Entry of Appearance 

as Attorney or Representative Before the 

Board of Immigration Appeals, or Form 

EOIR–28, Notice of Entry of Appearance 

as Attorney or Representative Before the 

Immigration Court. 

IV. Failure To Register 

By December 10, 2013, all attorneys 

and accredited representatives 

authorized to appear before EOIR must 

be registered as a condition to practice 

before the immigration courts and the 

Board. If an attorney or accredited 

representative who has cases pending 

before EOIR fails to register by 

December 10, 2013, EOIR may 

administratively suspend that 

individual from practicing before EOIR. 

See 8 CFR 1292.1(f). An attorney or 

accredited representative subject to 

administrative suspension can resume 

practicing before EOIR upon completing 

the registration process. While 

administrative suspension, on its own, 

is not disciplinary in nature, an 

unregistered attorney or accredited 

representative’s multiple attempts to 

appear before EOIR may result in 

disciplinary sanctions. Any individual 

who meets the definition of attorney in 

8 CFR 1001.1(f) or the definition of 

representative in 8 CFR 1001.1(j) is 

subject to disciplinary sanctions for 

misconduct, even if the individual is 

not registered. See 8 CFR 1003.101(b). 

V. Voluntary Electronic Submission of 

Form EOIR–27 and Form EOIR–28 

Upon implementation of eRegistry, 

registered attorneys and accredited 

representatives will be able to use their 

stored eRegistry information to prepopulate and, on a voluntary basis, 

electronically file entry of appearance 

forms for certain designated proceedings 

before the immigration courts and the 

Board.7 Registered attorneys and 

accredited representatives who 

electronically file a Form EOIR–27 or 

Form EOIR–28 will still be required to 

serve DHS with a printed copy of the 

completed Form EOIR–27 or Form 

EOIR–28. 

EOIR will continue to accept paper 

submissions of the Form EOIR–27 and 

Form EOIR–28. At this time, 

immigration practitioners who are not 

required to register will not be able to 

file these forms electronically. 

VI. Official Correspondence and 

Representative Change of Address 

EOIR will send all official 

correspondence to the representative’s 

address included on the most recent 

Form EOIR–27 or Form EOIR–28 for 

each case. Representatives are under an 

obligation to notify the immigration 

court and the Board of any change in 

their current address or any change in 

affiliations with recognized 

organizations, including branch offices. 

Registrants may change their 

addresses electronically by completing a 

two-step process. First, registrants must 

log in to their eRegistry account and add 

the new address to their account profile. 

Second, registrants must electronically 

file a Form EOIR–27 or Form EOIR–28 

for each of their cases to which the 

newly-added address should be 

assigned. In such cases, registrants 

should check the ‘‘new address’’ box on 

the Form EOIR–27 or Form EOIR–28. As 

with all submissions of the Form EOIR– 

27 or the Form EOIR–28, registrants are 

required to serve DHS with a printed 

copy of the completed Form EOIR–27 or 

Form EOIR–28. 

Registrants should note that adding a 

new address to their eRegistry profiles 

will not serve to update their addresses 

with the immigration court or the Board 

unless and until the Form EOIR–27 or 

Form EOIR–28 has been filed in each of 

their cases with their updated address. 

In matters in which EOIR does not yet 

accept electronic filings of the Form 

EOIR–27 or Form EOIR–28, registrants 

will need to file paper versions of those 

forms with the immigration court or the 

Board to complete the address change. 

VII. Responsibilities of Users 

Registered attorneys and accredited 

representatives will be responsible for 

all activity conducted under the 

attorney’s or accredited representative’s 

account. Once eRegistry is operational, 

registered attorneys and accredited 

representatives should immediately 

contact EOIR if they think that their 

account has been compromised. 

VIII. Effect of Disciplinary Orders on 

Registry 

Individuals with law licenses are not 

permitted to register as attorneys if they 

are under any order suspending, 

enjoining, restraining, disbarring, or 

otherwise restricting them in the 

practice of law, or are otherwise not a 

member in good standing of the bar. 

Such individuals do not meet the 

definition of ‘‘attorney’’ under 8 CFR 

1001.1(f). 

EOIR will deactivate the EOIR ID of 

an attorney or accredited representative 

who has been disbarred or suspended 

pursuant to 8 CFR 1003.101 et seq. 

unless and until the Board reinstates or 

otherwise permits the attorney or 

accredited representative to practice. 

IX. Additional Information 

Additional information regarding 

eRegistry will be available on EOIR’s 

Web site. 

Dated: May 7, 2013. 

Juan P. Osuna, 

Director. 

[FR Doc. 2013–11426 Filed 5–13–13; 8:45 am] 

BILLING CODE 4410–30–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0393; Directorate 

Identifier 2012–CE–025–AD; Amendment 

39–17446; AD 2013–09–05] 

RIN 2120–AA64 

Airworthiness Directives; Twin 

Commander Aircraft LLC Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Twin Commander Aircraft LLC Models 

690, 690A, and 690B airplanes. This AD 

requires inspection for cracking of the 

outer fuselage attachments, the lower 

wing main spar, the vertical channels, 

the upper picture window channels, aft 

cabin pressure web, external wing to 

fuselage fillets, and fasteners; repair or 

replacement of damaged parts as 

necessary; and modification of the 

structure with reinforced parts. This AD 


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28126 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Rules and Regulations 

was prompted by cracks found in the 

upper picture window frame channels, 

left- and right-hand wing main spar 

frame support channels, and aft 

pressure bulkhead web. This condition, 

if not corrected, could result in 

structural failure of the airplane. We are 

issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective May 29, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 29, 2013. 

We must receive comments on this 

AD by June 28, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Twin Commander 

Aircraft LLC; 1176 Telecom Drive, 

Creedmoor, NC 27522; telephone: (360) 

403–0258; email: 

gpence@twincommander.com; Internet: 

http://www.twincommander.com. You 

may review copies of the referenced 

service information at the FAA, Small 

Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329– 

4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vince Massey, Aerospace Engineer, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057; telephone: (425) 917–6475; 

fax: (425) 917–6590; email: 

vince.massey@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We were notified of cracks found in 

the left and right wing main spar frame 

support channels, the aft pressure 

bulkhead web, and the left and right 

picture window upper frame channels 

of a Twin Commander Aircraft LLC 

Model 690B airplane. Nineteen 

airplanes were inspected with one 

having severe cracking in the left and 

right wing main spar frame support 

channels, the aft pressure bulkhead 

web, and the left and right picture 

window upper frame channels. Five 

other of the inspected airplanes had 

similar but less severe damage. This 

condition, if not corrected, could result 

in structural failure of the aircraft. 

Relevant Service Information 

We reviewed Twin Commander 

Aircraft LLC Service Bulletin 241, dated 

September 26, 2012. The service 

information describes procedures for 

access, disassembly, and inspecting the 

outer fuselage attachments, the lower 

wing main spar, the vertical channels, 

the upper picture window channels, aft 

cabin pressure web, external wing to 

fuselage fillets, and fasteners for 

cracking. The service information also 

describes procedures for modifying the 

structure with reinforced parts and 

reassembly. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires inspection for 

cracking of the outer fuselage 

attachments, the lower wing main spar, 

the vertical channels, the upper picture 

window channels, aft cabin pressure 

web, external wing to fuselage fillets, 

and fasteners; repair or replacement of 

damaged parts as necessary; and 

modification of the structure with 

reinforced parts. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because cracking in the upper 

picture window frame channels, leftand right-hand wing main spar frame 

support channels, and/or aft pressure 

bulkhead web could result in structural 

failure of the aircraft. Therefore, we find 

that notice and opportunity for prior 

public comment are impracticable and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2013–0393 and Directorate 

Identifier 2012–CE–025–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 280 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Rules and Regulations 28127 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Disassembly, inspection, and modification ............................. 584 work-hours × $85 per 

hour = $49,640.

$8,450 $58,090 $16,265,200 

The scope of damage found in the 

required inspection could vary 

significantly from airplane to airplane. 

We have no way of determining how 

much damage may be found on each 

airplane or the cost to repair damaged 

parts on each airplane. The damage 

could be as minor as replacing rivets or 

fasteners or as extensive as a major 

wing/fuselage repair or replacement. 

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 

The Regulatory Flexibility Act of 1980 

(Pub. L. 96–354) (RFA) establishes as a 

principle of regulatory issuance that 

agencies shall endeavor, consistent with 

the objective of the rule and of 

applicable statutes, to fit regulatory and 

informational requirements to the scale 

of the businesses, organizations, and 

governmental jurisdictions subject to 

regulation. 

To achieve that principle, the RFA 

requires agencies to solicit and consider 

flexible regulatory proposals and to 

explain the rationale for their actions. 

The RFA covers a wide-range of small 

entities, including small businesses, 

not-for-profit organizations, and small 

governmental jurisdictions. 

Agencies must perform a review to 

determine whether a proposed or final 

rule will have a significant economic 

impact on a substantial number of small 

entities. In accordance with Section 608 

of the Regulatory Flexibility Act, an 

agency head may waive or delay 

completion of some or all of the 

requirements of Section 603 by 

providing a written finding that this 

final rule is being promulgated in 

response to an emergency that makes 

compliance or timely compliance with 

the provisions of Section 603 

impracticable. 

We are performing a review to 

determine whether this final rule AD 

action will have a significant economic 

impact on a substantial number of small 

entities. However, the immediate safety 

of flight conditions of this AD action 

make compliance with the provisions of 

Section 603 impracticable. Our 

justification for immediate adoption of 

this rule, and therefore of 

impracticability, is stated in FAA’s 

Justification and Determination of the 

Effective Date. After we determine 

whether this final rule AD action has a 

significant economic impact on a 

substantial number of small entities or 

not, we will publish in the Federal 

Register our determination and, if 

required, our final regulatory flexibility 

analysis. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2013–09–05 Twin Commander Aircraft 

LLC: Amendment 39–17446 ; Docket No. 

FAA–2013–0393; Directorate Identifier 

2012–CE–025–AD. 

(a) Effective Date 

This AD is effective May 29, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Twin 

Commander Aircraft LLC airplanes, 

certificated in any category: 

(1) Model 690, all serial numbers except 

11057; 

(2) Model 690A, all serial numbers except 

11104, 11106, 11129, 11134, 11146, 11159, 

11173, 11192, 11220, 11237, 11252, 11263, 

11280, 11287, 11298, 11303, 11317, 11339, 

and 11341; and 

(3) Model 690B, all serial numbers except 

11383, 11384, 11401, and 11436. 

(4) Aircraft equipped with AVIADESIGN, 

Inc. STC No. SA5740NM (You may find 

information on STC No. SA5740NM at 

Internet: http://rgl.faa.gov/Regulatory_and_

Guidance_Library/rgstc.nsf/0/

FEC5B7544E15F14C85256CC200122B19?

OpenDocument&Highlight=sa5740nm) are 

not compatible with the modifications 

contained in Twin Commander Aircraft LLC 

Service Bulletin 241, dated September 26, 

2012. When an airplane has been modified, 

altered, or repaired in the area addressed by 

the AD action, according to 14 CFR part 

39.15, the AD action still applies to that 

airplane. Following 14 CFR 39.19, the owner/ 

operator of that airplane must request 

approval from the FAA for an alternative 

method of compliance (AMOC) following the 

instructions in paragraph (j) of this AD. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53; Fuselage. 

(e) Unsafe Condition 

This AD was prompted by cracks found in 

the upper picture window frame channels, 

left- and right-hand wing main spar frame 

support channels, and aft pressure bulkhead 

web. This condition, if not corrected, could 

result in structural failure of the airplane. We 

are issuing this AD to correct the unsafe 

condition on these products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

(1) Inspect the airplane structural 

components, at the compliance times 

specified in paragraphs (g)(1)(i) through 

(g)(1)(iv) of this AD following Part I of Twin 

Commander Aircraft LLC Service Bulletin 

241, September 26, 2012: 

(i) For airplanes with 10,000 or more hours 

time-in-service (TIS), inspect within the next 

30 days after the effective date of this AD. 


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28128 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Rules and Regulations 

(ii) For airplanes with 7,500 through 9,999 

hours TIS, inspect within the next 60 days 

after the effective date of this AD. 

(iii) For airplanes with 5,000 through 7,499 

hours TIS, inspect within the next 6 months 

after the effective date of this AD. 

(iv) For airplanes with less than 5,000 

hours TIS, inspect when the airplane 

accumulates a total of 5,000 hours TIS or 

within the next 12 months after the effective 

date of this AD, whichever occurs later. 

(h) Repair 

If any damage, cracks, and/or cracks that 

exceed the allowable limits specified in the 

service bulletin are found during the 

inspection required in paragraph (g)(1) of this 

AD, before further flight, repair or replace 

parts as necessary following Twin 

Commander Aircraft LLC Service Bulletin 

241, dated, September 26, 2012. If Twin 

Commander Aircraft LLC Service Bulletin 

241, dated, September 26, 2012, does not give 

procedures for repair of the damaged area, 

before further flight, you must contact Twin 

Commander Aircraft LLC to obtain repair 

instructions approved by the Seattle Aircraft 

Certification Office (ACO) specifically for 

compliance with this AD and incorporate 

those instructions. You can find contact 

information for Twin Commander Aircraft 

LLC in paragraph (l)(2) of this AD. 

(i) Modification and Reassembly 

(1) Before further flight after completing 

the actions in paragraphs (g) and (h) of this 

AD, modify and reassemble the airplane 

using the modification and reassembly 

procedures in Part II of Twin Commander 

Aircraft LLC Service Bulletin 241, dated, 

September 26, 2012. 

(2) Although Twin Commander Aircraft 

LLC Service Bulletin 241, dated September 

26, 2012, states that at least one person on 

the modification team must have completed 

the Twin Commander Aircraft LLC approved 

training, the FAA does not require that a 

mechanic complete this specialized training 

to do the modification work required in this 

AD. Regulations 14 CFR 65.81(a) and 14 CFR 

65.81(b) provide criteria about qualifications 

of those performing maintenance; in this 

case, the requirements of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(k) Related Information 

For more information about this AD, 

contact Vince Massey, Aerospace Engineer, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057; telephone: (425) 917– 

6475; fax: (425) 917–6590; email: 

vince.massey@faa.gov. 

(l) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51: 

(i) Twin Commander Aircraft LLC Service 

Bulletin 241, dated September 26, 2012. 

(ii) Reserved. 

(2) For service information identified in 

this AD, contact Twin Commander Aircraft 

LLC; 1176 Telecom Drive, Creedmoor, NC 

27522; telephone: (360) 403–0258; email: 

gpence@twincommander.com; Internet: 

http://www.twincommander.com. 

(3) You may review copies of the service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr_locations.html. 

Issued in Kansas City, Missouri, on April 

25, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–10498 Filed 5–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0614; Directorate 

Identifier 2007–NM–351–AD; Amendment 

39–17450; AD 2013–09–08] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–300, –400, 

and –500 series airplanes. This AD was 

prompted by reports of two in-service 

occurrences on Model 737–400 

airplanes of total loss of boost pump 

pressure of the fuel feed system, 

followed by loss of fuel system suction 

feed capability on one engine, and inflight shutdown of the engine. This AD 

requires repetitive operational tests of 

the engine fuel suction feed of the fuel 

system, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct loss of the engine fuel 

suction feed capability of the fuel 

system, which, in the event of total loss 

of the fuel boost pumps, could result in 

dual engine flameout, inability to restart 

the engines, and consequent forced 

landing of the airplane. 

DATES: This AD is effective June 18, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 18, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. For 

information on the availability of this 

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

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Sue 

Lucier, Aerospace Engineer, Propulsion 

Branch, ANM–140S, Seattle Aircraft 

Certification Office, FAA, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6438; fax: 

425–917–6590; email: 

suzanne.lucier@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an AD 

that would apply to the specified 

products. That SNPRM published in the 

Federal Register on January 30, 2013 

(78 FR 6254). The original NPRM (73 FR 

32258, June 6, 2008) proposed to require 

repetitive operational tests of the engine 


wreier-aviles on DSK5TPTVN1PROD with RULES