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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.

7 EOIR 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 theirstored 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


### 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 upperpicture 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:


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

E STIMATED 

### C OSTS

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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(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 suctionfeed 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