Federal Register / Vol. 79, No. 79 / Thursday, April 24, 2014 / Proposed Rules 22783 

reworked and re-identified RAT or RAT hub 

assembly, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–29– 

0069, dated June 24, 2010 (for Model 757 

airplanes); or Boeing Special Attention 

Service Bulletin 767–29–0112, dated June 24, 

2010 (for Model 767 airplanes); except as 

provided by paragraphs (h)(2)(i) and (h)(2)(ii) 

of this AD. 

(i) Where Boeing Special Attention Service 

Bulletin 757–29–0069, dated June 24, 2010 

(for Model 757 airplanes); and Boeing Special 

Attention Service Bulletin 767–29–0112, 

dated June 24, 2010 (for Model 767 

airplanes); specify to contact Hamilton 

Sundstrand for a replacement unit, this AD 

does not require that action. 

(ii) Where the Boeing Special Attention 

Service Bulletin 757–29–0069, dated June 24, 

2010 (for Model 757 airplanes); and Boeing 

Special Attention Service Bulletin 767–29– 

0112, dated June 24, 2010 (for Model 767 

airplanes); instruct operators to return all 

RAT or RAT hub assemblies to Hamilton 

Sundstrand for rework and test, operators 

may return the RAT or RAT hub assembly to 

Hamilton Sundstrand or an FAA-approved 

repair facility that has the capability to 

disassemble, repair, balance, and test the 

RAT or RAT hub assembly. 

(3) If there are no missing balance washers 

and no fractured screws: Prior to the next 

RAT backdrive test or within 24 months after 

the effective date of this AD, whichever 

occurs first: Replace the balance washer 

screws, one at a time, in accordance with 

Hamilton Sundstrand Service Bulletin 

730814–29–15, dated February 10, 2010 (for 

Model 757 airplanes); or Hamilton 

Sundstrand Service Bulletin 729548–29–18, 

dated February 10, 2010 (for Model 767 

airplanes). 

(i) Parts Installation Limitations 

(1) As of the effective date of this AD, no 

person may install a RAT hub assembly 

having any applicable part number and serial 

number specified in paragraphs (i)(1)(i) and 

(i)(1)(ii) of this AD, on any airplane, unless 

it has been reworked and re-identified in 

accordance with Hamilton Sundstrand 

Service Bulletin 730814–29–12, dated 

November 30, 2005 (for Model 757 

airplanes); or Hamilton Sundstrand Service 

Bulletin 729548–29–15, dated November 30, 

2005 (for Model 767 airplanes). 

(i) Model 757–200, –200PF, –200CB, and 

–300 series airplanes having P/N 733785A or 

733785B, and S/N 0410 through 0413 

inclusive, 0415, 0417 through 0430 inclusive, 

0432, or 0434. 

(ii) Model 767–200, –300, –300F, and 

–400ER series airplanes having P/N 734350A, 

734350B, 734350C, or 734350D, and S/N 

0666, 0673 through 0684 inclusive, 0686, 

0687, or 0689. 

(2) As of the effective date of this AD, no 

person may install a RAT hub assembly 

having any applicable part number and serial 

number specified in paragraph (i)(2)(i) and 

(i)(2)(ii) of this AD, on any airplane, unless 

it has been inspected and reworked and reidentified in accordance with Hamilton 

Sundstrand Service Bulletin 730814–29–15, 

dated February 10, 2010 (for Model 757 

airplanes); or 729548–29–18, dated February 

10, 2010 (for Model 767 airplanes). 

(i) Model 757–200, –200PF, –200CB, and 

–300 series airplanes having P/N 733785AB 

Series, and S/N 0107, 0105, 0121, 0151, 0179, 

0204, 0282, 0289, 0296, 0315, 0319, 0337, 

0390, 0403, 0412, 0421, 0424, 0426, 0429, 

0430, 0439, 0445, 0450, 0477, 0503, 0510, 

0512, 0584, 0585, 0591, 0599, 0609, 0617, 

0624, 0656, 0673, 0685, 0789, 0822, 0841, 

0854, 0911, 0912, 0936, 0957, 0961, 0971, 

1061, 1064, 1096, 1101, 1102, 1105, 1113, 

1117, 1170, 1172, 1173, X2069. 

(ii) Model 767–200, –300, –300F, and 

–400ER series airplanes having P/N 734350 

Series, and S/N 0042, 0074, 0170, 0183, 0207, 

0311, 0312, 0324, 0336, 0337, 0347, 0367, 

0372, 0379, 0381, 0391, 0427, 0431, 0469, 

0495, 0500, 0530, 0531, 0533, 0538, 0539, 

0550, 0551, 0575, 0584, 0619, 0626, 0666, 

0670, 0676, 0690, 0700, 0701, 0734, 0750, 

0800, 0801, 0813, 0835, 0836, 0908, 0923, 

0958, 0968, 0980, 1009, 1012, 1019, 1046, 

1052, 1054, 1102, 1127, 1167, 1264, 1285, 

1300, 1317, 1322, 1362, 1372, 1394, 1398, 

1436, 1594, 1633, 1634, 1635, 1636, 1637, 

1638, 1639, 1640, 1641, 1642, 1643, 1644, 

1645, 1646, 1647, 1648, 1649, 1650, 1651, 

1652, X2063. 

(3) As of the effective date of this AD, no 

person may install a balance washer screw 

having part number MS24667–14, on any 

airplane unless a records review can 

positively determine that the screws did not 

come from Northeast Fasteners, lots 24057 

and 30533. 

(j) No Information Submission 

Although Boeing Alert Service Bulletin 

757–29A0066, Revision 1, dated March 8, 

2010 (for Model 757 airplanes); and Boeing 

Alert Service Bulletin 767–29A0110, 

Revision 1, dated March 8, 2010 (for Model 

767 airplanes); specify to submit information 

to the manufacturer, this AD does not 

include that requirement. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraph (k)(1) or 

(k)(2) of this AD, as applicable. These 

documents are not incorporated by reference 

in this AD. 

(1) Boeing Alert Service Bulletin 757– 

29A0066, dated January 2, 2007 (for Model 

757–200 and –200PF series airplanes). 

(2) Boeing Alert Service Bulletin 767– 

29A0110, dated January 2, 2007 (for Model 

767–200 and –300 series airplanes). 

(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 

paragraph (m)(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 and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6418; fax: 425–917– 

6590; marie.hogestad@faa.gov. 

(2) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; fax 

206–766–5680; email me.boecom@

boeing.com; Internet https://

www.myboeingfleet.com. For Hamilton 

Sundstrand service information identified in 

this AD, contact Hamilton Sundstrand, 

Technical Publications, Mail Stop 302–9, 

4747 Harrison Avenue, P.O. Box 7002, 

Rockford, IL 61125–7002; phone: 860–654– 

3575; fax: 860–998–4564; email: tech.

solutions@hs.utc.com; Internet: http://www.

hamiltonsundstrand.com. You may view this 

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 April 17, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–09348 Filed 4–23–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0254; Directorate 

Identifier 2013–NM–047–AD] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

22784 Federal Register / Vol. 79, No. 79 / Thursday, April 24, 2014 / Proposed Rules 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Beechcraft Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company) Model Hawker 800XP, 

850XP, and 900XP airplanes. This 

proposed AD was prompted by a design 

review that revealed there were no 

instructions to apply sealant to 

structural components in the fuel tank 

during the winglet installation process. 

This proposed AD would require an 

inspection for the presence of sealant on 

doubler plate edges, doubler plate 

rivets, and adjacent skin in the fuel vent 

surge tanks; and corrective actions if 

necessary. We are proposing this AD to 

detect and correct missing sealant, 

which, during a lightning strike, could 

result in a potential source of ignition in 

a fuel tank and consequent explosion or 

fire and subsequent in-flight breakup of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by June 9, 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 Beechcraft 

Corporation, TMDC, P.O. Box 85, 

Wichita, KS 67201–0085; telephone 

316–676–8238; fax 316–671–2540; email 

tmdc@beechcraft.com; Internet http://

pubs.beechcraft.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– 

0254; 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: 

Jeffrey Englert, Aerospace Engineer, 

Mechanical Systems and Propulsion 

Branch, ACE–116W, FAA, Wichita 

Aircraft Certification Office, 1801 

Airport Road, Room 100, Mid-Continent 

Airport, Wichita, KS 67209; phone: 

(316) 946–4167; fax: (316) 946–4107; 

email: jeffrey.englert@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– 

2014–0254; Directorate Identifier 2013– 

NM–047–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 found during a design review that 

included the winglet kit that there were 

no instructions to apply sealant to 

structural components in the fuel tank 

during the winglet installation process. 

The sealant is part of the lightning 

protection design for the fuel tanks. 

Missing sealant, if not detected and 

corrected, could result in a potential 

source of ignition in a fuel tank during 

a lightning strike and consequent 

explosion or fire and subsequent inflight breakup of the airplane. 

Relevant Service Information 

We reviewed Hawker Beechcraft 

Mandatory Service Bulletin SB 57–4112, 

dated February 2013. The service 

information describes procedures for 

inspecting for the presence of sealant on 

doubler plate edges, doubler plate 

rivets, and adjacent skin in the top and 

bottom of the left and right fuel vent 

surge tanks; and applying sealant if 

necessary. 

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 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

Differences Between This Proposed AD 

and the Service Information 

The service information identifies 

Model 800XP and 850XP airplanes 

equipped with certain kits, but does not 

specify the serial numbers of Model 

800XP and 850XP airplanes that are 

eligible to have those kits installed. We 

have listed those serial numbers in 

paragraph (g) of this proposed AD. 

The service information refers only to 

an ‘‘inspection’’ to determine the 

presence of sealant. We have 

determined that the inspection should 

be described as a ‘‘general visual 

inspection.’’ We have defined this type 

of inspection in paragraph (h) of this 

proposed AD. 

The service information includes a 

note in the Accomplishment 

Instructions to inform operators to 

contact Hawker Beechcraft ‘‘should any 

difficulty be encountered’’ in 

accomplishing the service information. 

We have clarified in paragraph (i) of this 

proposed AD that any deviation from 

the instructions provided in the service 

information must be approved as an 

alternative method of compliance under 

the provisions of paragraph (k) of this 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 50 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 79, No. 79 / Thursday, April 24, 2014 / Proposed Rules 22785 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

Product 

Cost on U.S. 

operators 

Inspection ....................................... 2 work-hours × $85 per hour = 

$170.

None ............................................... $170 $8,500 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Sealant application ....................................................... 36 work-hours × $85 per hour = $3,060 ...................... $32 $3,092 

According to the manufacturer, all of 

the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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: 

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): 

Beechcraft Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company): Docket No. FAA–2014–0254; 

Directorate Identifier 2013–NM–047–AD. 

(a) Comments Due Date 

We must receive comments by June 9, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Beechcraft Corporation 

(Type Certificate previously held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company) Model Hawker 800XP, 850XP, and 

900XP airplanes, certificated in any category, 

all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by a design review 

that revealed there were no instructions to 

apply sealant to structural components in the 

fuel tank during the winglet installation 

process. We are issuing this AD to detect and 

correct missing sealant, which, during a 

lightning strike, could result in a potential 

source of ignition in a fuel tank and 

consequent explosion or fire and subsequent 

in-flight breakup of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Action 

For airplanes identified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD: Within 600 

flight hours or 12 months after the effective 

date of this AD, whichever occurs first, do a 

general visual inspection for the presence of 

sealant on doubler plate edges, doubler plate 

rivets, and adjacent skin in the top and 

bottom of the left and right fuel vent surge 

tanks, and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Hawker 

Beechcraft Mandatory Service Bulletin SB 

57–4112, dated February 2013, except as 

required by paragraph (i) of this AD. Do all 

applicable corrective actions before further 

flight. 

(1) Beechcraft Corporation (Type 

Certificate previously held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company) Model Hawker 800XP airplanes, 

serial numbers 258324, 258326 through 

258332 inclusive, 258334 through 258340 

inclusive, 258342 through 258347 inclusive, 

258349 through 258359 inclusive, 258361 

through 258369 inclusive, 258371 through 

258380 inclusive, 258382 through 258406 

inclusive, 258408 through 258426 inclusive, 

258428 through 258444 inclusive, 258446 

through 258468 inclusive, 258470 through 

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22786 Federal Register / Vol. 79, No. 79 / Thursday, April 24, 2014 / Proposed Rules 

258492 inclusive, 258494 through 258512 

inclusive, 258514 through 258532 inclusive, 

258534 through 258540 inclusive, 258542 

through 258555 inclusive, 258557 through 

258566 inclusive, 258278, 258541, 258556, 

258567 through 258609 inclusive, 258611 

through 258628 inclusive, 258630 through 

258684 inclusive, 258686 through 258734 

inclusive, 258736 through 258788 inclusive, 

258795, 258802, 258821, 258825, 258829, 

258834, 258840, and 258847; equipped with 

a kit numbered 140–1701–1, 140–1702–1, 

140–1703–1,140–1703–5, 140–1703–7, or 

140–1704–1 that was purchased from Hawker 

Beechcraft on or before February 13, 2013. 

(2) Beechcraft Corporation (Type 

Certificate previously held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company) Model Hawker 850XP airplanes 

having serial numbers 258789 through 

258794 inclusive, 258796, 258798 through 

258801 inclusive, 258803 through 258819 

inclusive, 258822, 258823, 258826 through 

258828 inclusive, 258830 through 258833 

inclusive, 258835 through 258838 inclusive, 

258841, 258844, 258845, 258848, 258852, 

258855, 258856, 258858, 258859, 258861, 

258872, 258874, 258876, 258891, 258893, 

258895, 258900, 258901, 258904, 258907, 

258909, 258912, 258915, 258921, 258959, 

258961, 258963, 258977, 258980, 258982, 

and subsequent serial numbers; equipped 

with a kit numbered 140–1701–1, 140–1702– 

1, 140–1703–1, 140–1703–5, 140–1703–7, or 

140–1704–1 that was purchased on or before 

February 13, 2013. 

(3) Beechcraft Corporation (Type 

Certificate previously held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company) Model Hawker 900XP airplanes, 

having serial numbers HA–0156 and HA– 

0159. 

(h) Definition 

For the purposes of this AD, a general 

visual inspection is a visual examination of 

an interior or exterior area, installation, or 

assembly to detect obvious damage, failure, 

or irregularity. This level of inspection is 

made from within touching distance unless 

otherwise specified. A mirror may be 

necessary to ensure visual access to all 

surfaces in the inspection area. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or droplight and may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked. 

(i) Exception to the Service Information 

A note in the Accomplishment Instructions 

of the Hawker Beechcraft Mandatory Service 

Bulletin SB 57–4112, dated February 2013, 

instructs operators to contact Hawker 

Beechcraft if any difficulty is encountered in 

accomplishing the service information. 

However, this AD requires that any deviation 

from the instructions provided in Hawker 

Beechcraft Mandatory Service Bulletin SB 

57–4112, dated February 2013, must be 

approved as an alternative method of 

compliance (AMOC) under the provisions of 

paragraph (k) of this AD. 

(j) Parts Installation Limitation 

For all airplanes: As of the effective date 

of this AD, no kit having kit number 140– 

1701–1, 140–1702–1, 140–1703–1, 140– 

1703–5, 140–1703–7, or 140–1704–1 that was 

purchased before February 13, 2013, may be 

installed on any airplane unless the 

installation includes sealant on doubler plate 

edges, doubler plate rivets, and adjacent skin 

in the top and bottom of the left and right 

fuel vent surge tanks, as specified in the 

Accomplishment Instructions of Hawker 

Beechcraft Mandatory Service Bulletin SB 

57–4112, dated February 2013. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Jeffrey Englert, Aerospace Engineer, 

Mechanical Systems and Propulsion Branch, 

ACE–116W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, Wichita, 

KS 67209; phone: (316) 946–4167; fax: (316) 

946–4107; email: jeffrey.englert@faa.gov. 

(2) For service information identified in 

this AD, contact Beechcraft Corporation, 

TMDC, P.O. Box 85, Wichita, KS 67201– 

0085; telephone 316–676–8238; fax 316–671– 

2540; email tmdc@beechcraft.com; Internet 

http://pubs.beechcraft.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 April 17, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–09311 Filed 4–23–14; 8:45 am] 

BILLING CODE 4910–13–P 

POSTAL SERVICE 

39 CFR Part 492 

Collection of Delinquent Non-Tax 

Debts by Administrative Wage 

Garnishment 

AGENCY: Postal Service. 

ACTION: Proposed rule. 

SUMMARY: The United States Postal 

Service proposes to add a provision to 

its regulations in order to implement the 

administrative wage garnishment 

(AWG) provisions of the Debt Collection 

Improvement Act of 1996 (DCIA), and to 

allow the Bureau of the Fiscal Service 

(BFS) of the United States Treasury to 

collect debts owed to the Postal Service, 

that the Postal Service refers to BFS for 

collection, by AWG. 

DATES: Comments must be received on 

or before June 23, 2014. 

ADDRESSES: Mail or deliver written 

comments to Ruth Stevenson, U.S. 

Postal Service, 475 L’Enfant Plaza SW., 

Room 6416, Washington, DC 20260– 

1150. You may inspect and photocopy 

all written comments at USPS 

Headquarters Library, 475 L’Enfant 

Plaza SW., 11th Floor North, 

Washington, DC, by appointment only 

between the hours of 9 a.m. and 4 p.m., 

Monday through Friday. Call 1–202– 

268–2906 in advance for an 

appointment. Email comments, 

containing the name and address of the 

commenter, may be sent to: 

awgcomments@ usps.gov. Faxed 

comments are not accepted. 

FOR FURTHER INFORMATION CONTACT: 

Ruth Stevenson at (202) 268–6724. 

SUPPLEMENTARY INFORMATION: After 

providing debtors with the requisite 

opportunity for notice and review, the 

Postal Service currently may refer nontax delinquent debts to the United 

States Treasury Bureau of the Fiscal 

Service (BFS), formerly the Financial 

Management Service (FMS), for 

centralized collection and/or offset. 

Among other potential collection tools, 

BFS may utilize Administrative Wage 

Garnishment (AWG) to collect 

delinquent debts referred to it by federal 

agencies. AWG allows a federal entity to 

enforce collection of a debt by 

garnishing wages the debtor receives 

from a non-federal (private) employer 

after affording the debtor with notice 

and certain administrative proceedings, 

including the right to a hearing. 

Provisions of the DCIA, codified at 31 

U.S.C. 3720D, authorize Federal 

agencies to collect non-tax debt owed to 

the United States by AWG. The 

Treasury has also issued an 

implementing regulation at 31 CFR 

285.11. However, before BFS may 

utilize AWG to collect debts that the 

Postal Service refers to it, the Postal 

Service must first implement 

regulations authorizing the collection of 

non-tax delinquent debt by AWG. The 

Postal Service accordingly proposes to 

add new part 492, containing § 492.1, to 

title 39 of the Code of Federal 

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