Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Proposed Rules 45385 

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 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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: 

ESTIMATED 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: 

ON-CONDITION COSTS

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: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Proposed Rules 45387 

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 


emcdonald on DSK67QTVN1PROD with PROPOSALS