Federal Register / Vol. 79, No. 84 / Thursday, May 1, 2014 / Rules and Regulations 24541 

TABLE 2 TO § 217.11—CALCULATION OF MAXIMUM LEVERAGE PAYOUT AMOUNT

Leverage buffer 

Maximum leverage 

payout ratio 

(as a percentage of 

eligible retained 

income) 

Greater than 2.0 percent ......................................................................................................................................................... No payout ratio limitation applies. 

Less than or equal to 2.0 percent, and greater than 1.5 percent ........................................................................................... 60 percent. 

Less than or equal to 1.5 percent, and greater than 1.0 percent ........................................................................................... 40 percent. 

Less than or equal to 1.0 percent, and greater than 0.5 percent ........................................................................................... 20 percent. 

Less than or equal to 0.5 percent ........................................................................................................................................... 0 percent. 

Federal Deposit Insurance Corporation 

12 CFR Chapter III 

Authority and Issuance 

For the reasons stated in the 

preamble, the Federal Deposit Insurance 

Corporation is amending part 324 of 

chapter III of Title 12, Code of Federal 

Regulations as follows: 

PART 324—CAPITAL ADEQUACY OF 

FDIC–SUPERVISED INSTITUTIONS 

■ 10. The authority section for part 324 

continues to read as follows: 

Authority: 12 U.S.C. 1815(a), 1815(b), 

1816, 1818(a), 1818(b), 1818(c), 1818(t), 

1819(Tenth), 1828(c), 1828(d), 1828(i), 

1828(n), 1828(o), 1831o, 1835, 3907, 3909, 

4808; 5371; 5412; Pub. L. 102–233, 105 Stat. 

1761, 1789, 1790 (12 U.S.C. 1831n note); Pub. 

L. 102–242, 105 Stat. 2236, 2355, as amended 

by Pub. L. 103–325, 108 Stat. 2160, 2233 (12 

U.S.C. 1828 note); Pub. L. 102–242, 105 Stat. 

2236, 2386, as amended by Pub. L. 102–550, 

106 Stat. 3672, 4089 (12 U.S.C. 1828 note); 

Pub. L. 111–203, 124 Stat. 1376, 1887 (15 

U.S.C. 78o–7 note). 

■ 11. Revise § 324.403(b)(1)(v) to read as 

follows: 

§ 324.403 Capital measures and capital 

category definitions. 

* * * * * 

(b) * * * 

(1) * * * 

(v) Beginning on January 1, 2018 and 

thereafter, an FDIC-supervised 

institution that is a subsidiary of a 

covered BHC will be deemed to be well 

capitalized if the FDIC-supervised 

institution satisfies paragraphs (b)(1)(i) 

through (iv) of this section and has a 

supplementary leverage ratio of 6.0 

percent or greater. For purposes of this 

paragraph, a covered BHC means a U.S. 

top-tier bank holding company with 

more than $700 billion in total assets as 

reported on the company’s most recent 

Consolidated Financial Statement for 

Bank Holding Companies (FR Y–9C) or 

more than $10 trillion in assets under 

custody as reported on the company’s 

most recent Banking Organization 

Systemic Risk Report (FR Y–15); and 

* * * * * 

Dated: April 8, 2014. 

Thomas J. Curry, 

Comptroller of the Currency. 

By order of the Board of Governors of the 

Federal Reserve System, April 10, 2014. 

Robert deV. Frierson, 

Secretary of the Board. 

Dated at Washington, DC, this 8th day of 

April, 2014. 

By order of the Board of Directors. 

Robert E. Feldman, 

Executive Secretary, Federal Deposit 

Insurance Corporation. 

[FR Doc. 2014–09367 Filed 4–30–14; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1160; Directorate 

Identifier 2010–NM–148–AD; Amendment 

39–17698; AD 2013–25–02] 

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) 2000–11– 

06 for certain The Boeing Company 

Model 767 airplanes. AD 2000–11–06 

required repetitive inspections to detect 

discrepancies of the wiring and 

surrounding Teflon sleeves of the fuel 

tank boost pumps and override/jettison 

pumps; replacement of the sleeves with 

new sleeves, for certain airplanes; and 

repair or replacement of the wiring and 

sleeves with new parts, as necessary. 

This new AD requires reducing the 

initial compliance time and repetitive 

inspection interval in AD 2000–11–06; 

mandates a terminating action for the 

repetitive inspections to eliminate wire 

damage; removes certain airplanes from 

the applicability; and requires revising 

the maintenance program to incorporate 

changes to the airworthiness limitations 

section. This AD was prompted by fleet 

information indicating that the 

repetitive inspection interval in AD 

2000–11–06 is too long, because 

excessive chafing of the sleeving 

continues to occur much earlier than 

expected between scheduled 

inspections. We are issuing this AD to 

detect and correct chafing of the fuel 

pump wire insulation and consequent 

exposure of the electrical conductor, 

which could result in electrical arcing 

between the wires and conduit and 

consequent fire or explosion of the fuel 

tank. 

DATES: This AD is effective June 5, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 5, 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, Washington 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–2010– 

1160; 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 


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24542 Federal Register / Vol. 79, No. 84 / Thursday, May 1, 2014 / Rules and Regulations 

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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6509; fax: 425–917–6590; email: 

rebel.nichols@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a second supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 to supersede 

AD 2000–11–06, Amendment 39–11754 

(65 FR 34928, June 1, 2000; corrected 

August 1, 2000 (65 FR 46862)). AD 

2000–11–06 applied to certain The 

Boeing Company Model 767 airplanes. 

The second SNPRM published in the 

Federal Register on March 8, 2013 (78 

FR 14934). We preceded the second 

SNPRM with a first SNPRM that 

published in the Federal Register on 

July 2, 2012 (77 FR 39188). We preceded 

the first SNPRM with a notice of 

proposed rulemaking (NPRM) that 

published in the Federal Register on 

December 14, 2010 (75 FR 77790). The 

NPRM was prompted by fleet 

information indicating that the 

repetitive inspection interval in AD 

2000–11–06 is too long, because 

excessive chafing of the sleeving 

continues to occur much earlier than 

expected between scheduled 

inspections. The NPRM proposed to 

continue to require repetitive 

inspections to detect discrepancies of 

the wiring and surrounding Teflon 

sleeves of the fuel tank boost pumps and 

override/jettison pumps; replacement of 

the sleeves with new sleeves, for certain 

airplanes; and repair or replacement of 

the wiring and sleeves with new parts, 

as necessary. The NPRM also proposed 

to reduce the initial compliance time 

and repetitive inspection interval in AD 

2000–11–06. The first SNPRM proposed 

to mandate a terminating action for the 

repetitive inspections, to eliminate wire 

damage. In addition, the first SNPRM 

proposed to remove certain airplanes 

from the applicability of AD 2000–11– 

06. The second SNPRM proposed to 

require revising the maintenance 

program to incorporate changes to the 

airworthiness limitations section. We 

are issuing this AD to detect and correct 

chafing of the fuel pump wire insulation 

and consequent exposure of the 

electrical conductor, which could result 

in electrical arcing between the wires 

and conduit and consequent fire or 

explosion of the fuel tank. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the second SNPRM (78 FR 

14934, March 8, 2013) and the FAA’s 

response to each comment. Boeing 

concurred with the content of the 

second SNPRM. 

Request To Allow Using Maintenance 

Manual Procedure for Repetitive 

Inspections 

United Airlines (UAL) asked that 

paragraphs (g), (i)(2)(i)(C), (i)(2)(ii), and 

(k) of the second SNPRM (78 FR 14934, 

March 8, 2013) be changed to allow the 

use of Boeing 767 Airplane Maintenance 

Manual (AMM) 28–22–15/601 when 

accomplishing the repetitive inspections 

required by those paragraphs. UAL 

stated that Boeing has incorporated the 

intent of Boeing Service Bulletin 767– 

28A0053, Revision 3, dated November 

11, 2011, into Boeing 767 AMM 28–22– 

15/601. (Boeing Service Bulletin 767– 

28A0053, Revision 3, dated November 

11, 2011, was cited as an appropriate 

source of service information in the 

second SNPRM.) 

We do not agree to change paragraphs 

(g), (i)(2)(i)(C), (i)(2)(ii), and (k) of this 

final rule to allow using Boeing 767 

AMM 28–22–15/601 for accomplishing 

the required repetitive inspections. The 

procedures specified in that section of 

the AMM are not FAA-approved. In 

addition, it is possible that not all 

operators have a current version of the 

AMM in their maintenance programs; 

therefore, it is not possible for us to 

know which version of the AMM would 

be used for doing the inspections. 

Limiting the requirements to a specific 

AMM procedure and revision level 

would require an operator to get an 

approval of an alternative method of 

compliance (AMOC) for subsequent 

AMM revisions. Therefore, we have not 

changed this final rule in this regard. 

Request To Clarify Certain Errors in the 

Service Information 

UAL asked that the second SNPRM 

(78 FR 14934, March 8, 2013) refer to 

the correct figure callouts (which are 

identified incorrectly in Boeing Alert 

Service Bulletin 767–28A0104, Revision 

1, dated March 2, 2012). UAL stated that 

paragraph (l) of the second SNPRM 

specifies using Boeing Alert Service 

Bulletin 767–28A0104, Revision 1, 

dated March 2, 2012, to perform 

terminating action for the repetitive 

inspections required by paragraphs (g) 

and (k) of the second SNPRM. UAL also 

noted that it made the same request in 

its comments on the first SNPRM (77 FR 

39188, July 2, 1012). UAL added that 

these errors were confirmed by Boeing, 

but no revised service information has 

been issued to address these errors. 

We agree with the commenter that the 

figure callouts are identified incorrectly 

in Boeing Alert Service Bulletin 767– 

28A0104, Revision 1, dated March 2, 

2012; however, as we specified in a 

similar response in the first SNPRM (77 

FR 39188, July 2, 2012), Boeing has not 

yet issued revised service information to 

correct the errors. These errors are 

minor and do not affect accomplishing 

the actions specified in the service 

information. When revised service 

information is issued, operators may 

request approval of an AMOC in 

accordance with the procedures 

specified in paragraph (p) of this AD. 

We have not changed this final rule in 

this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments 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 second SNPRM (78 

FR 14934, March 8, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the second SNPRM (78 FR 

14934, March 8, 2013). 

Costs of Compliance 

We estimate that this AD affects 414 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 79, No. 84 / Thursday, May 1, 2014 / Rules and Regulations 24543 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Actions for airplanes with jettison pumps [retained from AD 2000–11–06, Amendment 39– 

11754 (65 FR 34928, June 1, 2000; corrected 

August 1, 2000 (65 FR 46862)).

7 work-hours × $85 per 

hour = $595 per inspection cycle.

None ........ $595 per inspection 

cycle.

Up to $246,330 per inspection cycle. 

Actions for airplanes without jettison pumps [retained from AD 2000–11–06, Amendment 39– 

11754 (65 FR 34928, June 1, 2000; corrected 

August 1, 2000 (65 FR 46862)).

5 work-hours × $85 per 

hour = $425 per inspection cycle.

None ........ $425 per inspection 

cycle.

Up to $175,950 per inspection cycle. 

New replacement of wire bundles ....................... 42 work–hours × $85 per 

hour = $3,570.

$6,061 ...... $9,631 .......................... $3,987,234. 

New revision to maintenance program ............... 1 work-hour × $85 per hour 

= $85.

None ........ $85 ............................... $35,190. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspections. 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 

Replacement of wire bundle sleeves ................................ 1 work-hour × $85 per hour = $85 .................................. $1,452 $1,537 

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 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) 

2000–11–06, Amendment 39–11754 (65 

FR 34928, June 1, 2000; corrected 

August 1, 2000 (65 FR 46862)), and 

adding the following new AD: 

2013–25–02 The Boeing Company: 

Amendment 39–17698; Docket No. 

FAA–2010–1160; Directorate Identifier 

2010–NM–148–AD. 

(a) Effective Date 

This AD is effective June 5, 2014. 

(b) Affected ADs 

This AD supersedes AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes, certificated in any 

category, as identified in Boeing Service 

Bulletin 767–28A0053, Revision 3, dated 

November 11, 2011. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections). Compliance 

with these actions is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by this AD, the operator 

may not be able to accomplish the actions 

described in the revisions. In this situation, 

to comply with 14 CFR 91.403(c), the 

operator must request approval for an 

alternative method of compliance according 

to paragraph (p) of this AD. The request 

should include a description of changes to 

the required actions that will ensure the 

continued operational safety of the airplane. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Unsafe Condition 

This AD was prompted by fleet 

information indicating that the repetitive 

inspection interval in AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)) is too long because excessive chafing 

of the sleeving continues to occur much 


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24544 Federal Register / Vol. 79, No. 84 / Thursday, May 1, 2014 / Rules and Regulations 

earlier than expected between scheduled 

inspections. We are issuing this AD to detect 

and correct chafing of the fuel pump wire 

insulation and consequent exposure of the 

electrical conductor, which could result in 

electrical arcing between the wires and 

conduit and consequent fire or explosion of 

the fuel tank. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (a) of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), with revised service information. 

Perform a detailed visual inspection to detect 

discrepancies—including the presence of 

cuts, splits, holes, worn areas, and lacing ties 

installed on the outside of the sleeves (except 

at the sleeve ends)—of the Teflon sleeves 

surrounding the wiring of the fuel tank boost 

pumps and override/jettison pumps, at the 

earlier of the times specified in paragraphs 

(g)(1) and (g)(2) of this AD, in accordance 

with Boeing Service Bulletin 767–28A0053, 

Revision 1, dated August 5, 1999; Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. Repeat the 

inspection thereafter at intervals not to 

exceed 60,000 flight hours or 30,000 flight 

cycles, whichever occurs first. As of the 

effective date of this AD, only Boeing Service 

Bulletin 767–28A0053, Revision 3, dated 

November 11, 2011, may be used to do the 

actions required by this paragraph. 

(1) Prior to the accumulation of 50,000 

total flight hours, or within 90 days after July 

6, 2000 (the effective date of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), whichever occurs later. 

(2) Within 18 months after July 6, 2000 (the 

effective date of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)). 

(h) Retained Corrective Actions 

This paragraph restates the requirements of 

paragraph (b) of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), with revised service information. If 

any discrepancy is detected during any 

inspection required by paragraph (g) of this 

AD: Prior to further flight, remove the Teflon 

sleeves and perform a detailed visual 

inspection to detect damage of the wiring, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

28A0053, Revision 1, dated August 5, 1999; 

Boeing Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. As of the effective 

date of this AD, only Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011, may be used to do the actions 

required by this paragraph. 

(1) If no damage to the wiring is detected, 

prior to further flight, install new Teflon 

sleeves, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. As of the effective date of this AD, 

only Boeing Service Bulletin 767–28A0053, 

Revision 3, dated November 11, 2011, may be 

used to do the actions required by this 

paragraph. 

(2) If any damage to the wiring is detected, 

prior to further flight, accomplish the 

requirements of paragraph (i) of this AD. 

(i) Retained Corrective Actions 

This paragraph restates the requirements of 

paragraph (c) of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), with revised service information. If 

any damage to the wiring is detected during 

any inspection required by paragraph (h) of 

this AD: Prior to further flight, perform a 

detailed visual inspection to determine if the 

wiring damage was caused by arcing, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

28A0053, Revision 1, dated August 5, 1999; 

Boeing Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. As of the effective 

date of this AD, only Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011, may be used to do the actions 

required by this paragraph. 

(1) If the wire damage was not caused by 

arcing: Prior to further flight, repair any 

damaged wires or replace the wires with new 

or serviceable wires, as applicable, and 

install new Teflon sleeves, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–28A0053, 

Revision 1, dated August 5, 1999; Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. As of the effective 

date of this AD, only Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011, may be used to do the actions 

required by this paragraph. 

(2) If any damage caused by arcing is 

found: Prior to further flight, perform an 

inspection for signs of fuel inside the conduit 

or on the wires, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. As of the effective date of this AD, 

only Boeing Service Bulletin 767–28A0053, 

Revision 3, dated November 11, 2011, may be 

used to do the actions required by this 

paragraph. 

(i) If no sign of fuel is found, accomplish 

the actions specified in paragraphs 

(i)(2)(i)(A), (i)(2)(i)(B), (i)(2)(i)(C), and 

(i)(2)(i)(D) of this AD. 

(A) Prior to further flight, repair the wires 

or replace the wires with new or serviceable 

wires, as applicable, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. As of the effective date of this AD, 

only Boeing Service Bulletin 767–28A0053, 

Revision 3, dated November 11, 2011, may be 

used to do the actions required by this 

paragraph. 

(B) Prior to further flight, install new 

Teflon sleeves, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. As of the effective date of this AD, 

only Boeing Service Bulletin 767–28A0053, 

Revision 3, dated November 11, 2011, may be 

used to do the actions required by this 

paragraph. 

(C) Repeat the inspection for signs of fuel 

inside the conduit thereafter at intervals not 

to exceed 500 flight hours, until the 

requirements of paragraph (i)(2)(i)(D) of this 

AD have been accomplished. If any fuel is 

found inside the conduit during any 

inspection required by this paragraph, prior 

to further flight, replace the conduit with a 

new or serviceable conduit, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–28A0053, 

Revision 1, dated August 5, 1999; Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. Thereafter, repeat 

the inspection specified in paragraph (g) of 

this AD at intervals not to exceed 60,000 

flight hours or 30,000 flight cycles, 

whichever occurs first. As of the effective 

date of this AD, only Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011, may be used to do the actions 

required by this paragraph. 

(D) Within 6,000 flight hours or 18 months 

after the initial fuel inspection specified by 

paragraph (i)(2) of this AD, whichever occurs 

first, replace the conduit with a new or 

serviceable conduit, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. Such conduit replacement 

constitutes terminating action for the 

repetitive fuel inspections required by 

paragraph (i)(2)(i)(C) of this AD. As of the 

effective date of this AD, only Boeing Service 

Bulletin 767–28A0053, Revision 3, dated 

November 11, 2011, may be used to do the 

actions required by this paragraph. 

(ii) If any fuel is found in the conduit or 

on any wire: Prior to further flight, replace 

the conduit with a new or serviceable 

conduit, replace damaged wires with new or 

serviceable wires, and install new Teflon 

sleeves; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 


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Federal Register / Vol. 79, No. 84 / Thursday, May 1, 2014 / Rules and Regulations 24545 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. Thereafter, repeat the inspection 

specified in paragraph (g) of this AD at 

intervals not to exceed 60,000 flight hours or 

30,000 flight cycles, whichever occurs first. 

As of the effective date of this AD, only 

Boeing Service Bulletin 767–28A0053, 

Revision 3, dated November 11, 2011, may be 

used to do the actions required by this 

paragraph. 

(j) Retained Pump Retest 

This paragraph restates the requirements of 

paragraph (d) of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), with revised service information. 

For any wire bundle removed and reinstalled 

during any inspection required by this AD: 

Prior to further flight after such 

reinstallation, retest the fuel pump, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

28A0053, Revision 1, dated August 5, 1999; 

Boeing Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. As of the effective 

date of this AD, only Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011, may be used to do the actions 

required by this paragraph. 

(k) New Repetitive Inspections With 

Reduced Inspection Intervals 

Do the inspection required by paragraph (g) 

of this AD at the time specified in paragraph 

(k)(1) or (k)(2) of this AD, as applicable, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

28A0053, Revision 3, dated November 11, 

2011. Repeat the inspection thereafter at 

intervals not to exceed 15,000 flight hours. 

Accomplishing the first inspection in this 

paragraph ends the repetitive inspection 

requirements in paragraph (g) of this AD. 

(1) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done as of the effective date of this AD: Do 

the inspection within 15,000 flight hours 

after the most recent inspection, or within 

6,000 flight hours after the effective date of 

this AD, whichever occurs later, but not to 

exceed 60,000 flight hours after the most 

recent inspection required by paragraph (g) of 

this AD. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD has not 

been done as of the effective date of this AD: 

Do the inspection before the accumulation of 

15,000 total flight hours, or within 6,000 

flight hours after the effective date of this AD, 

whichever occurs later. 

(l) New Terminating Action 

Within 60 months after the effective date 

of this AD: Replace the fuel boost pump and 

override/jettison pump wire bundles inside 

the in-tank electrical conduit with a conduit 

liner and new wire bundles, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 767–28A0104, 

Revision 1, dated March 2, 2012. 

Accomplishing the replacement specified in 

this paragraph ends the repetitive inspection 

requirements in paragraphs (g) and (k) of this 

AD. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (l) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 767–28A0104, dated January 

25, 2011, which is not incorporated by 

reference in this AD. 

(n) New Maintenance Program Revision 

Within 180 days after the effective date of 

this AD: Revise the maintenance program to 

incorporate Critical Design Configuration 

Control Limitations (CDCCL) Task 28–AWL– 

29, ‘‘In-Tank AC Fuel Pump Wire Bundles 

with Protective Liner;’’ and CDCCL Task 28– 

AWL–30, ‘‘Fuel Boost Pump Wires in 

Conduit Installation—In Fuel Tank;’’ of 

Section 9, of Boeing 767 Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), of the 

Boeing 767 Maintenance Planning Data 

(MPD) Document, D622T001–9, Revision 

October 2012. 

(o) No Alternative Actions, Intervals, and/or 

CDCCLs 

After accomplishing the revision required 

by paragraph (n) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance in 

accordance with the procedures specified in 

paragraph (p) of this AD. 

(p) 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 (q)(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) AMOCs approved previously for AD 

2000–11–06, Amendment 39–11754 (65 FR 

34928, June 1, 2000; corrected August 1, 2000 

(65 FR 46862)), are approved as AMOCs for 

the corresponding provisions of this AD. 

Compliance time extensions approved 

previously for AD 2000–11–06 are not 

approved as AMOCs for the compliance 

times required by paragraph (k) of this AD. 

(q) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6509; fax: 425–917– 

6590; email: rebel.nichols@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (r)(4) and (r)(5) of this 

AD. 

(r) 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 June 5, 2014. 

(i) Boeing Service Bulletin 767–28A0053, 

Revision 3, dated November 11, 2011. 

(ii) Boeing Alert Service Bulletin 767– 

28A0104, Revision 1, dated March 2, 2012. 

(iii) Section 9, of Boeing 767 Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), of the 

Boeing 767 Maintenance Planning Data 

(MPD) Document, D622T001–9, Revision 

October 2012: 

(A) Critical Design Configuration Control 

Limitations (CDCCL) Task 28–AWL–29, ‘‘InTank AC Fuel Pump Wire Bundles with 

Protective Liner;’’ 

(B) CDCCL Task 28–AWL–30, ‘‘Fuel Boost 

Pump Wires in Conduit Installation—In Fuel 

Tank.’’ 

Note 1 to paragraph (r)(3)(iii) of this AD: 

CDCCL Task 28–AWL–29 and Task 28– 

AWL–30 were not revised in Revision 

October 2012 of Section 9, of Boeing 767 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), of the Boeing 767 Maintenance 

Planning Data (MPD) Document, D622T001– 

9. These tasks were added in Revision May 

2010; therefore, the page date for these tasks 

is May 2010. 

(4) For 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; Internet https://

www.myboeingfleet.com. 

(5) You may view this 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. 

(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 

December 4, 2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–09094 Filed 4–30–14; 8:45 am] 

BILLING CODE 4910–13–P 


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