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this AD, following the accomplishment instructions in Pacific Aerospace Limited Mandatory Service Bulletin PACSB/FU/095, Issue 2, dated May 28, 2014.

(1) Within the next 50 hours time-inservice (TIS) after the effective date of this AD, inspect the control column part number (P/N) 08–45031/32 for cracks.

(2) If any mechanical damage, deformation, or cracks are found, before further flight, replace the control column with an airworthy control column P/N 08–45031/32.

(3) If no mechanical damage, deformation, or cracks are found after the inspection required in paragraph (f)(1) of this AD, at the next scheduled maintenance inspection or within the next 150 hours TIS, whichever occurs later, replace the control column with an airworthy P/N 08–45031/32.
(g) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4123 ; fax: (816) 329–4090; email: karl.schletzbaum@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.
(h) Related Information

Refer to MCAI Civil Aviation Authority (CAA) AD DCA/FU24/183, dated May 29, 2014, and Pacific Aerospace Limited Mandatory Service Bulletin PACSB/FU/095, Issue 2, dated May 28, 2014, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2014–0532. For service information related to this AD, contact Pacific Aerospace Limited, Airport Road, Hamilton Private Bag 3027 Hamilton 3240, New Zealand; telephone: +64 7 843 6144; fax: +64 7 843 6134; email: pacific@aerospace.co.nz; Internet: http:// www.aerospace.co.nz/. You may review this 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.

Issued in Kansas City, Missouri, on July 29,
2014. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014–18449 Filed 8–4–14; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0522; Directorate Identifier 2014–NM–087–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. This proposed AD was prompted by reports of cracks at the lower forward corner of the main entry door (MED) 1 cutout. This proposed AD would require repetitive inspections of the MED door 1 for cracking, and repair if necessary. This proposed AD also provides optional terminating modification; and would require post-repair or post-modification inspections for cracking, and corrective actions if necessary. We are proposing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane.

**DATES :**  We must receive comments on this proposed AD by September 19,
2014.

**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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed 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 view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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 by searching for and locating Docket No. FAA–2014– 0522; 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 proposed 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 :**  Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov

. **SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2014–0522; Directorate Identifier 2014– NM–087–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed 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 proposed AD.

Discussion

We have received reports of cracks at the lower forward corner of the MED 1 cutout on two airplanes. A 1.0-inch crack in the skin and bearstrap was found on an airplane with 17,605 total flight cycles. A 5.0-inch crack was found in the skin, skin doubler, and bearstrap on an airplane with 21,759 total flight cycles. In addition, four cracks between 0.18- and 1.85-inch were found on Boeing’s fatigue test airplane


### 45386 Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Proposed Rules

between 40,000 and 52,250 total pressure cycles. The manufacturer’s analysis has determined that the cracking initiates in the skin and can propagate into the bonded doubler and bearstrap. Skin cracks that are not found and repaired can become large and could adversely affect the structural integrity of the airplane.

Relevant Service Information

We reviewed Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for Docket No. FAA–2014–0522.

FAA’s Determination

We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements

This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’

The phrase ‘‘corrective actions’’ is used in this proposed AD. ‘‘Corrective actions’’ correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information

The service bulletin specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways:

• In accordance with a method that

we approve; or

• Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings.
Costs of Compliance

We estimate that this proposed AD affects 165 airplanes of U.S. registry.

We estimate the following costs to comply with this proposed AD:



### E STIMATED 

### COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspection (per door) ..... 11 work-hours × $85 per hour = $935 per inspection cycle. $0 $935 per inspection cycle. $154,275 per inspection cycle. Optional modification

(per door). Up to 66 work-hours × $85 per hour = $5,610 .... 0 Up to $5,610 ................. Up to $925,650.

Post-repair or -modification inspection (per door). 11 work-hours × $85 per hour = $935 per inspection cycle. 0 $935 per inspection cycle. $154,275 per inspection cycle.

We estimate the following costs to do any necessary repair that would be required based on the results of the proposed inspection. We have no way of determining the number of airplanes that might need this repair:



### O N 

### -C ONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Repair (per door) ................. 66 work-hours × $85 per hour = $5,610 ....................... $7,380 or $9,360 ............... $12,990 or $14,970.

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 above, 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, 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. 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:


### 45387 Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Proposed Rules

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

**§ 39.13 [Amended]**

■ 2. Amend § 39.13 by adding the following new airworthiness directive (AD):
The Boeing Company: Docket No. FAA– 2014–0522; Directorate Identifier 2014– NM–087–AD.
(a) Comments Due Date

We must receive comments by September 19, 2014.
(b) Affected ADs

None. (c) Applicability

This AD applies to all The Boeing Company Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014.
(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

This AD was prompted by reports of cracks at the lower forward corner of the main entry door (MED) 1 cutout. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Repetitive Inspections and Corrective Actions

Except as specified in paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014: Do a detailed inspection and a surface high frequency eddy current inspection for cracking of the applicable main entry door 1; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. Do all applicable corrective actions before further flight. Repeat the inspections of the applicable main entry door 1 thereafter at the intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. Accomplishing the corrective actions required by this paragraph terminates the repetitive inspection requirements of this paragraph.
(h) Optional Terminating Action

For airplanes on which no crack is found during the initial inspections required by paragraph (g) of this AD: Installing the preventive modification in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, terminates the repetitive inspections required by paragraph (g) of this
AD.
(i) Post-Repair or Post-Modification Repetitive Inspections and Corrective Actions

For airplanes on which the corrective actions required by paragraph (g) of this AD have been done, or airplanes that have installed the preventive modification specified in paragraph (h) of this AD: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, do a detailed inspection for cracking of the applicable main entry door 1; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, except as specified in paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the applicable main entry door 1 thereafter at the intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014.
(j) Exceptions to Service Information

(1) Where paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, specifies a compliance time ‘‘after the Original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.

(2) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
(k) 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 paragraph (l)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov

.

(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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane. (l) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425– 917–6590; email: Nathan.P.Weigand@ faa.gov

.

(2) 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 view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

Issued in Renton, Washington, on July 25,
2014. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014–18465 Filed 8–4–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF JUSTICE**

**28 CFR Parts 0 and 90**

**[OVW Docket No. 111]**

**RIN 1105–AB43**

**Grants To Encourage Arrest Policies and Enforcement of Protection Orders** 

**AGENCY :**  Office on Violence Against Women, Justice.

**ACTION :**  Proposed rule.

**SUMMARY :**  This rule proposes to amend the regulations for the Grants To Encourage Arrest Policies and Enforcement of Protection Orders Program (Arrest Program) to incorporate statutory changes, make minor technical corrections, and streamline existing regulations to reduce repetition of statutory language. This rule would also amend the regulations to clarify that existing regulations on grant-related procedures continue to apply to grants made by the Office on Violence Against Women.

**DATES :**  Written comments must be submitted on or before October 6, 2014.

**ADDRESSES :**  To ensure proper handling of comments, please reference ‘‘Docket No. OVW 111 on all electronic and written correspondence. The Department encourages the electronic submission of all comments through http://www.regulations.gov using the electronic comment form provided on that site. For easy reference, an electronic copy of this document is also