Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 15651 

Committee prior to Debenture closing. 

Only the Board or Executive Committee, 

if authorized by the Board, may provide 

credit approval for loans greater than 

$2,000,000. 

(15) All members of the Board of 

Directors must annually certify in 

writing that they have read and 

understand this section, and copies of 

the certification must be included in the 

Annual Report to SBA. 

(e) The Board of Directors shall 

maintain Directors’ and Officers’ 

Liability and Errors and Omissions 

insurance in amounts established by 

SBA that are based on the size of the 

CDC’s portfolio and other relevant 

factors. 

■ 8. Amend § 120.830 by revising 

paragraph (a) to read as follows: 

§ 120.830 Reports a CDC must submit. 

* * * * * 

(a) An Annual Report within one 

hundred-eighty days after the end of the 

CDC’s fiscal year (to include Federal tax 

returns for that year). A CDC that is 

certified by SBA within 6 months of the 

CDC’s fiscal year-end is not required to 

submit an Annual Report for that year. 

The Annual Report must include, but is 

not limited to, the following: 

(1) Audited or Reviewed Financial 

Statements as required in § 120.826(c) 

and (d) for the CDC and any affiliates or 

subsidiaries of the CDC. 

(i) Audited financial statements must, 

at a minimum, include the following: 

(A) Audited balance sheet; 

(B) Audited statement of income (or 

receipts) and expenses; 

(C) Audited statement of source and 

application of funds; 

(D) Such footnotes as are necessary to 

an understanding of the financial 

statements; 

(E) Auditor’s letter to management on 

internal control weaknesses; and 

(F) The auditor’s report; and 

(ii) Reviewed financial statements 

must, at a minimum, include the 

following: 

(A) Balance sheet; 

(B) Statement of income (or receipts) 

and expenses; 

(C) Statement of source and 

application of funds; 

(D) Such footnotes as are necessary to 

an understanding of the financial 

statements; 

(E) The accountant’s review report; 

and 

(2) Report on compensation: CDCs are 

required to provide detailed information 

on total compensation (including salary, 

bonuses and expenses) paid within the 

CDC’s most recent tax year for current 

and former officers and directors, and 

for current and former employees and 

independent contractors with total 

compensation of more than $100,000 

during that period. 

(3) Certification of members of the 

Board of Directors. Written annual 

certification by each Board member that 

he or she has read and understands the 

requirements set forth in § 120.823. 

(4) Report on investment in economic 

development. Written report on 

investments in economic development 

in each State in which the CDC has an 

outstanding 504 loan. 

* * * * * 

■ 9. Amend § 120.835 by revising 

paragraph (c) to read as follows: 

§ 120.835 Application to expand an Area of 

Operations. 

* * * * * 

(c) A CDC seeking to become a MultiState CDC must apply to the SBA 

District Office that services the area 

within each State where the CDC 

intends to locate its principal office for 

that State. A CDC may apply to be a 

Multi-State CDC only if the State the 

CDC seeks to expand into is contiguous 

to the State of the CDC’s incorporation 

and the CDC establishes a loan 

committee in that State meeting the 

requirements of § 120.823. 

§ 120.852 [Removed and Reserved] 

■ 10. Remove and reserve § 120.852. 

■ 11. Amend § 120.882 by revising 

paragraph (a) to read as follows: 

§ 120.882 Eligible Project costs for 504 

loans. 

* * * * * 

(a) Costs directly attributable to the 

Project including expenditures incurred 

by the Borrower (with its own funds or 

from a loan) to acquire land used in the 

Project, or for any other expense directly 

attributable to the Project, prior to 

applying to SBA for the 504 loan; 

* * * * * 

■ 12. Amend § 120.920 by revising 

paragraph (b) to read as follows: 

§ 120.920 Required participation by Third 

Party Lender. 

* * * * * 

(b) Third party loan collateral. The 

504 loan is usually collateralized by a 

second lien on Project Property. The 

Third Party Lender may obtain 

additional collateral or other security for 

the Third Party Loan (‘‘Additional 

Collateral’’) only if in the event of 

liquidation and unless otherwise 

approved in writing by SBA: 

(1) The Third Party Lender liquidates 

or otherwise exhausts all reasonable 

avenues of collection with respect to the 

Additional Collateral no later than the 

disposition of the Project Property, and 

(2) The Third Party Lender applies 

any proceeds received as a result of the 

Additional Collateral to the balance 

outstanding on the Third Party Loan 

prior to the application of proceeds from 

the disposition of the Project Property to 

the Third Party Loan. 

§ 120.925 [Removed and Reserved] 

■ 13. Remove and reserve § 120.925. 

Marianne O’Brien Markowitz, 

Acting Administrator. 

[FR Doc. 2014–06237 Filed 3–20–14; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0796; Directorate 

Identifier 2013–NM–111–AD; Amendment 

39–17802; AD 2014–05–30] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2013–07– 

07 for all The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes. AD 2013–07– 

07 required inspecting to determine the 

part number of the attach pins of the 

horizontal stabilizer rear spar, and 

replacing certain attach pins. This new 

AD clarifies the parts installation 

limitation and prohibition, and adds a 

new requirement for certain airplanes 

on which certain attach pins were 

installed. This AD was prompted by 

inquiries from affected operators 

regarding the parts installation 

limitation and prohibition, and reinstallation of certain attach pins that 

were removed for inspection. We are 

issuing this AD to prevent premature 

failure of the attach pins, which could 

cause reduced structural integrity of the 

horizontal stabilizer to fuselage 

attachment, resulting in loss of control 

of the airplane. 

DATES: This AD is effective April 25, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 20, 2013 (78 FR 22182, April 

15, 2013). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

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15652 Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 

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–2013– 

0796; 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 

Docket 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6440; fax: 

425–917–6590; email: Nancy.Marsh@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, 

April 15, 2013). AD 2013–07–07 applied 

to all The Boeing Company Model 737– 

600, –700, –700C, –800, –900, and 

–900ER series airplanes. The NPRM 

published in the Federal Register on 

September 25, 2013 (78 FR 58982). The 

NPRM was prompted by inquiries from 

affected operators regarding the parts 

installation limitation and prohibition, 

and re-installation of certain attach pins 

that were removed for inspection. The 

NPRM proposed to continue to require 

inspecting to determine the part number 

of the attach pins of the horizontal 

stabilizer rear spar, and replacing 

certain attach pins. The NPRM also 

proposed to clarify the parts installation 

limitation and prohibition, and add a 

new requirement for certain airplanes 

on which certain attach pins were 

installed. We are issuing this AD to 

prevent premature failure of the attach 

pins, which could cause reduced 

structural integrity of the horizontal 

stabilizer to fuselage attachment, 

resulting in loss of control of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal (78 FR 58982, 

September 25, 2013) and the FAA’s 

response to each comment. 

Clarification of Effect of Winglet 

Installation 

Aviation Partners Boeing stated that 

the installation of winglets per 

Supplemental Type Certificate (STC) 

ST00830SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/408E012E008616A78

62578880060456C?Open

Document&Highlight=st00830se) does 

not affect the accomplishment of the 

manufacturer’s service instructions. 

We concur. Paragraph (c)(2) in AD 

2013–07–07, Amendment 39–17411 (78 

FR 22182, April 15, 2013), has been 

restated in this final rule and specifies 

that STC ST00830SE (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/

rgstc.nsf/0/408E012E008616A78625

78880060456C?Open

Document&Highlight=st00830se) does 

not affect the ability to accomplish the 

actions required by this final rule. 

Therefore, for airplanes on which STC 

ST00830SE is installed, a ‘‘change in 

product’’ alternative method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of section 39.17 of the 

Federal Aviation Regulations (14 CFR 

39.17). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

58982, September 25, 2013) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 58982, 

September 25, 2013). 

Costs of Compliance 

We estimate that this AD affects 1,050 

airplanes of U.S. registry. The new 

requirements add no significant 

economic burden over that specified in 

AD 2013–07–07, Amendment 39–17411 

(78 FR 22182, April 15, 2013). Those 

costs are repeated for the convenience of 

affected operators, as follows: 

ESTIMATED COSTS

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

Inspection and attach pin replacement 

[actions retained from AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, 

April 15, 2013)].

39 work-hours × $85 

per hour = $3,315.

Up to $6,312 .......... Up to $9,627 .......... Up to $10,108,350. 

According to the manufacturer, some 

of the costs of this 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 

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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 15653 

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 have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

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 

removing Airworthiness Directive (AD) 

2013–07–07, Amendment 39–17411 (78 

FR 22182, April 15, 2013), and adding 

the following new AD: 

2014–05–30 The Boeing Company: 

Amendment 39–17802; Docket No. 

FAA–2013–0796; Directorate Identifier 

2013–NM–111–AD. 

(a) Effective Date 

This AD is effective April 25, 2014. 

(b) Affected ADs 

(1) This AD supersedes AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, April 

15, 2013). 

(2) This AD affects certain requirements of 

AD 2004–05–19, Amendment 39–13514 (69 

FR 10921, March 9, 2004; corrected April 13, 

2004 (69 FR 19313)). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/408E012E008616A7862

578880060456C?OpenDocument&Highlight=

st00830se) does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST00830SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by inquiries from 

affected operators regarding the parts 

installation limitation and prohibition, and 

re-installation of certain attach pins that were 

removed for inspection. We are issuing this 

AD to prevent premature failure of the attach 

pins, which could cause reduced structural 

integrity of the horizontal stabilizer to 

fuselage attachment, resulting in loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Part Number (P/N) Inspection 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, April 

15, 2013). For airplanes having line numbers 

1 through 3534 inclusive: Before the 

accumulation of 56,000 total flight cycles, or 

within 3,000 flight cycles after May 20, 2013 

(the effective date of AD 2013–07–07), 

whichever occurs later, inspect to determine 

the part number of the attach pins of the 

horizontal stabilizer rear spar. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number of 

the attach pin can be conclusively 

determined from that review. 

(h) Retained Replacement 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, April 

15, 2013). If, during the inspection required 

by paragraph (g) of this AD, any horizontal 

stabilizer rear spar attach pin has P/N 

180A1612–3 or 180A1612–4, prior to the 

accumulation of 56,000 total flight cycles on 

the pin, or within 3,000 flight cycles after 

May 20, 2013 (the effective date of AD 2013– 

07–07), whichever occurs later, replace with 

a new attach pin having P/N 180A1612–7 or 

180A1612–8, respectively, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–55–1093, dated April 9, 2012. 

(i) Retained Parts Installation Prohibition 

This paragraph restates the requirements of 

paragraph (i)(2) of AD 2013–07–07, 

Amendment 39–17411 (78 FR 22182, April 

15, 2013). For airplanes having line numbers 

3535 and subsequent: As of May 20, 2013 

(the effective date of AD 2013–07–07), no 

person may install an attach pin of the 

horizontal stabilizer rear spar having P/N 

180A1612–3 or 180A1612–4 on any airplane. 

(j) Retained Terminating Action for AD 

2004–05–19, Amendment 39–13514 (69 FR 

10921, March 9, 2004; Corrected April 13, 

2004 (69 FR 19313)) 

This paragraph restates the provisions of 

paragraph (j) of AD 2013–07–07, Amendment 

39–17411 (78 FR 22182, April 15, 2013). 

Accomplishment of the actions required by 

paragraphs (g) and (h) of this AD terminates 

the requirements of paragraphs (a), (b), (c), 

(d), and (e) of AD 2004–05–19, Amendment 

39–13514 (69 FR 10921, March 9, 2004; 

corrected April 13, 2004 (69 FR 19313)), for 

the rear spar attach pins only. 

(k) New Parts Installation Limitation 

For airplanes having line numbers 1 

through 3534 inclusive: As of the effective 

date of this AD, an attach pin of the 

horizontal stabilizer rear spar having P/N 

180A1612–3 or 180A1612–4 may be installed 

on an airplane, provided it is replaced with 

an attach pin having P/N 180A1612–7 or 

180A1612–8, as applicable, prior to the 

accumulation of 56,000 total flight cycles on 

the attach pin. The replacement must be 

done in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–55– 

1093, dated April 9, 2012. 

(l) New Attach Pin Replacement 

For airplanes having line numbers 1 

through 3534 inclusive on which an attach 

pin of the horizontal stabilizer rear spar 

having P/N 180A1612–7 or 180A1612–8 has 

been replaced with an attach pin having P/ 

N 180A1612–3 or 180A1612–4 before the 

effective date of this AD: Prior to the 

accumulation of 56,000 total flight cycles on 

the attach pin, or within 1,000 flight cycles 

on the airplane after the effective date of this 

AD, whichever occurs later, replace the 

attach pin having P/N 180A1612–3 or 

180A1612–4 with an attach pin having P/N 

180A1612–7 or 180A1612–8, as applicable, 

in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–55–1093, dated April 9, 

2012. 

(m) 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 (n) of this AD. Information may be 

emailed to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

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15654 Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 

(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. 

(4) AMOCs approved previously for AD 

2013–07–07, Amendment 39–17411 (78 FR 

22182, April 15, 2013), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(n) Related Information 

For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6440; fax: 425–917–6590; 

email: Nancy.Marsh@faa.gov. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on May 20, 2013 (78 FR 

22182, April 15, 2013). 

(i) Boeing Special Attention Service 

Bulletin 737–55–1093, dated April 9, 2012. 

(ii) Reserved. 

(4) For Boeing 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. 

(5) You may view this service information 

at 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. 

(6) You may view this 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/ibrlocations.html. 

Issued in Renton, Washington, on March 3, 

2014. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–05415 Filed 3–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0089; Directorate 

Identifier 2012–NM–166–AD; Amendment 

39–17806; AD 2014–06–02] 

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 certain 

The Boeing Company Model 747–400 

series airplanes. This AD was prompted 

by reports of auxiliary power unit (APU) 

faults due to power feeder cable chafing. 

This AD requires detailed inspections 

for damage of the APU power feeder 

cables; replacing the clamps and 

installing grommets; and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct chafing of the APU 

power feeder cables within a flammable 

fluid leakage zone, which, with arcing, 

could result in fire and structural 

damage. 

DATES: This AD is effective April 25, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 25, 2014. 

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 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–2013– 

0089; 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 

Docket 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: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, Seattle Aircraft Certification 

Office, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6482; fax: 425–917–6590; email: 

georgios.roussos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 747–400 series airplanes. The 

NPRM published in the Federal 

Register on February 7, 2013 (78 FR 

8999). The NPRM was prompted by 

reports of APU faults due to power 

feeder cable chafing. The NPRM 

proposed to require detailed inspections 

for damage of the APU power feeder 

cables; replacing the clamps and 

installing grommets; and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct chafing of the APU 

power feeder cables within a flammable 

fluid leakage zone, which, with arcing, 

could result in fire and structural 

damage. 

Relevant Service Information 

Since we issued the NPRM (78 FR 

8999, February 7, 2013), we reviewed 

Boeing Service Bulletin 747–24A2360, 

Revision 2, dated October 2, 2013. (The 

NPRM referenced Boeing Service 

Bulletin 747–24A2360, Revision 1, 

dated May 2, 2012, as the appropriate 

source of service information for 

accomplishing the required actions.) 

Boeing Service Bulletin 747–24A2360, 

Revision 2, dated October 2, 2013, 

among other things, revises the 

recommended compliance time from 14 

months to 18 months. For information 

on the procedures and compliance 

times, see this service information at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2013– 

0089. 

We have determined that extending 

the compliance time, as recommended 

by the manufacturer, will not adversely 

affect safety. We have revised the 

compliance time in paragraph (g) of this 

AD accordingly. We have also revised 

paragraphs (c), (g), (h), and (i) of this AD 

to refer to Boeing Service Bulletin 747– 

24A2360, Revision 2, dated October 2, 

2013. 

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