Federal Register / Vol. 78, No. 166 / Tuesday, August 27, 2013 / Proposed Rules 52875 

328–52–460, Revision 2, dated March 1, 2012 

and Dornier 328 Support Services Service 

Bulletin SB–328J–52–213, Revision 1, dated 

August 17, 2011, identify 20 of 26 part 

number NAS6703U1 fasteners requiring to be 

replaced due to incorrect length. 

(j) Credit for Previous Actions 

This paragraph provides credit for certain 

actions required by paragraph (g) and (h)(2) 

of this AD, if those actions were performed 

before the effective date of this AD using 328 

Support Services Service Bulletin SB–328– 

52–460, Revision 1, dated August 17, 2011. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1175; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(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. 

(l) Related Information 

(1) Refer to European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2012–0183R1, dated September 28, 2012, for 

related information, which can be found in 

the AD docket on the Internet at http://

www.regulations.gov. 

Issued in Renton, Washington, on August 

16, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–20845 Filed 8–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0701; Directorate 

Identifier 2013–NM–073–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 all the 

Boeing Company Model 727 airplanes. 

This proposed AD is intended to 

complete certain mandated programs 

intended to support the airplane 

reaching its limit of validity (LOV) of 

the engineering data that support the 

established structural maintenance 

program. This proposed AD would 

require repetitive inspections for 

cracking of small repairs done on the 

vertical flange of the rib chord, 

repetitive inspections for cracking along 

the upper fillet radius of the rib chord, 

and a large repair or preventive 

modification if necessary. 

Accomplishment of a large repair or 

preventive modification would 

terminate the actions of the proposed 

AD. We are proposing this AD to 

prevent cracks in the rib upper chord, 

which could result in the inability of the 

wing structure to support the limit load 

condition, and consequent loss of 

structural integrity of the wing. 

DATES: We must receive comments on 

this proposed AD by October 11, 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: 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 

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 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: 

Galib Abumeri, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Blvd., Suite 

100, Lakewood, CA 90712–4137; phone: 

562–627–5324; fax: 562–672–5210; 

email: galib.abumeri@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– 

2013–0701; Directorate Identifier 2013– 

NM–073–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 

As described in FAA Advisory 

Circular 120–104 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/120–104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish a limit of validity (LOV) of the 


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52876 Federal Register / Vol. 78, No. 166 / Tuesday, August 27, 2013 / Proposed Rules 

engineering data that support the 

structural maintenance program under 

14 CFR 26.21. This proposed AD is the 

result of an assessment of the previously 

established programs by Boeing during 

the process of establishing the LOV for 

Model 727 airplanes. The actions 

specified in this proposed AD are 

necessary to complete certain programs 

to ensure the continued airworthiness of 

aging airplane structure and to support 

an airplane reaching its LOV. 

Cracks have been reported on at least 

8 airplanes in the upper vertical flange 

of the wing-to-body rib upper chord at 

body station 760. The cracks were 

detected when the airplanes had 

reached between 19,700 and 49,000 

total flight cycles, and between 35,000 

and 54,000 total flight hours. Cracks in 

the rib upper chord, if not corrected, 

could result in the inability of the wing 

structure to support the limit load 

condition, and consequent loss of 

structural integrity of the wing. 

Related Rulemaking 

AD 90–06–09, Amendment 39–6488 

(55 FR 8370, March 7, 1990), which 

affects Model 727 series airplanes, 

requires, among other things, structural 

modifications specified in Boeing 

Service Bulletin 727–57–0112, Revision 

2, dated May 19, 1988. 

AD 94–07–08, Amendment 39–8866 

(59 FR 14545, March 29, 1994), which 

affects certain Boeing Model 727 series 

airplanes, requires structural 

inspections specified in Boeing Service 

Bulletin 727–57–0112, Revision 2, dated 

May 19, 1988, and corrective actions if 

necessary. The corrective actions 

include small repairs, large repairs, and 

modifications. AD 94–07–08 requires 

repetitive inspections for cracks, but 

does not require repetitive inspections 

of small repairs. Accomplishment of the 

modification specified in AD 94–07–08 

terminates those repetitive inspections. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

727–57–0112, Revision 5, dated July 31, 

1997. For information on the procedures 

and compliance times, see this service 

information at http://

www.regulations.gov by searching for 

Docket No. FAA–2013–0701. 

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 the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

repetitive inspections for cracking of 

any small repairs done on the vertical 

flange of the rib chord from the inboard 

side. The proposed AD would require a 

large repair or modification if any 

cracking is found. Accomplishment of a 

large repair or preventive modification 

would terminate the actions of the 

proposed AD. 

Differences Between the Proposed AD 

and the Service Information 

This proposed AD would require 

repetitive inspections for cracks along 

the upper fillet radius of the rib chord. 

Boeing Service Bulletin 727–57–0112, 

Revision 5, dated July 31, 1997, does not 

specify this inspection if a small repair 

is done. This difference has been 

coordinated with Boeing. 

Costs of Compliance 

We estimate that this proposed AD 

affects 106 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 

Inspections (per wing) ... 6 work-hours × $85 per hour = $510 per inspection cycle.$0 $510 per inspection 

cycle.

$54,060 per inspection 

cycle. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Large repair 1,2 ......................................... 300 work-hours × $85 per hour = $25,500 ........................................ $12,139 $37,639 

Preventive modification 1,3 ....................... 57 work-hours × $85 per hour = $4,845 ............................................ 10,614 15,459 

1 Cost for on-condition actions (either 2 or 3), per wing. 2 Cost for large repair, per wing. 

3 Cost for preventive modification, per wing. 

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. 


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Federal Register / Vol. 78, No. 166 / Tuesday, August 27, 2013 / Proposed Rules 52877 

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: 

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): 

The Boeing Company: Docket No. FAA– 

2013–0701; Directorate Identifier 2013– 

NM–073–AD. 

(a) Comments Due Date 

We must receive comments by October 11, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 727, 727C, 727–100, 727– 

100C, 727–200, and 727–200F series 

airplanes, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD is intended to complete certain 

mandated programs intended to support the 

airplane reaching its limit of validity (LOV) 

of the engineering data that support the 

established structural maintenance program. 

We are issuing this AD to prevent cracks in 

the rib upper chord, which could result in 

the inability of the wing structure to support 

the limit load condition, and consequent loss 

of structural integrity of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Post-Repair Inspection 

For any small repair that has been done as 

specified in Boeing 727 Service Bulletin 57– 

112; or Part III of the Accomplishment 

Instructions of Boeing Service Bulletin 727– 

57–0112: Within 3,500 flight cycles after the 

small repair was installed or inspected as 

specified in Boeing Service Bulletin 727–57– 

0112, or within 18 months after the effective 

date of this AD, whichever occurs latest, do 

a high frequency eddy current inspection for 

cracking of the vertical flange of the rib chord 

from the inboard side, and do a detailed 

(close visual) inspection for cracking along 

the upper fillet radius of the rib chord, in 

accordance with Part III of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–57–0112, Revision 5, 

dated July 31, 1997. Repeat the inspections 

thereafter at intervals not to exceed 3,500 

flight cycles until accomplishment of the 

repair or modification specified in paragraph 

(i) or (j) of this AD. 

(h) Inspection Definition 

For the purposes of this AD, a detailed 

inspection is an intensive examination of a 

specific item, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at an 

intensity deemed appropriate. Inspection 

aids such as mirror, magnifying lenses, etc., 

may be necessary. Surface cleaning and 

elaborate procedures may be required. 

(i) Corrective Action for Cracks 

If any crack is found during any inspection 

required by paragraph (g) of this AD, before 

further flight, do either action specified in 

paragraph (i)(1) or (i)(2) of this AD. 

Accomplishment of either action terminates 

the requirements of paragraphs (g) and (h) of 

this AD. 

(1) Do a large repair, in accordance with 

Part IV of the Accomplishment Instructions 

of Boeing Service Bulletin 727–57–0112, 

Revision 5, dated July 31, 1997. 

(2) Do a preventive modification, in 

accordance with Part V of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–57–0112, Revision 5, 

dated July 31, 1997. 

(j) Optional Terminating Action 

Accomplishment of the actions specified in 

either paragraph (j)(1) or (j)(2) of this AD 

terminates the requirements of paragraphs 

(g), (h), and (i) of this AD. 

(1) A large repair, in accordance with Part 

IV of the Accomplishment Instructions of 

Boeing Service Bulletin 727–57–0112, 

Revision 5, dated July 31, 1997. Any crack 

found must be repaired before further flight 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(2) A preventive modification, in 

accordance with Part V of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–57–0112, Revision 5, 

dated July 31, 1997. Any crack found must 

be repaired before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

inspections, large repair, and modification 

specified in this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Service Bulletin 727–57–0112, 

Revision 4, dated October 29, 1992. 

(l) 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. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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, and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Galib Abumeri, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Blvd., Suite 100, Lakewood, 

CA 90712–4137; phone: 562–627–5324; fax: 

562–672–5210; email: galib.abumeri@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 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. 

Issued in Renton, Washington, on August 

16, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–20840 Filed 8–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

28 CFR Part 94 

[Docket No. OJP (OVC) 1523] 

RIN 1121–AA69 

VOCA Victim Assistance Program 

AGENCY: Office for Victims of Crime, 

Justice. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Office for Victims of 

Crime (‘‘OVC’’) of the U.S. Department 

of Justice’s Office of Justice Programs 

(‘‘OJP’’), proposes this rule to 


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