Federal Register / Vol. 80, No. 59 / Friday, March 27, 2015 / Proposed Rules 16321 

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 (j)(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 for AD 2005–18–18, 

Amendment 39–14258 (70 FR 53554, 

September 9, 2005), are approved as AMOCs 

for paragraph (g) of this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Christopher Baker, Aerospace 

Engineer, Propulsion Branch, ANM–140S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6498; fax: 425–917–6590; email: 

christopher.r.baker@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Ave. SW., Renton WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on March 

12, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–06782 Filed 3–26–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0248; Directorate 

Identifier 2014–NM–143–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–08– 

23, which applies to all The Boeing 

Company Model DC–10–10, DC–10– 

10F, DC–10–15, DC–10–30, DC–10–30F 

(KC–10A and KDC–10), DC–10–40, DC– 

10–40F, MD–10–10F, MD–10–30F, MD– 

11, and MD–11F airplanes. AD 2013– 

08–23 currently requires adding design 

features to detect electrical faults and to 

detect a pump running in an empty fuel 

tank. Since we issued AD 2013–08–23, 

we have determined that it is necessary 

to clarify the requirements for the 

design features and to remove a 

terminating action for certain 

inspections. This proposed AD would 

clarify certain requirements and remove 

a terminating action. This proposed AD 

would also provide an optional method 

of compliance for the proposed actions. 

We are proposing this AD to reduce the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 11, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0248. 

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–2015– 

0248; 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: Serj 

Harutunian, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

phone: 562–627–5254; fax: 562–627– 

5210; email: serj.harutunian@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0248; Directorate Identifier 

2014–NM–143–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 

On April 10, 2013, we issued AD 

2013–08–23, Amendment 39–17441 (78 

FR 24037, April 24, 2013), for all The 

Boeing Company Model DC–10–10, DC– 

10–10F, DC–10–15, DC–10–30, DC–10– 

30F (KC–10A and KDC–10), DC–10–40, 

DC–10–40F, MD–10–10F, MD–10–30F, 

MD–11, and MD–11F airplanes. AD 

2013–08–23 requires adding design 

features to detect electrical faults and to 

detect a pump running in an empty fuel 

tank. AD 2013–08–23 resulted from fuel 

system reviews conducted by the 

manufacturer. We issued AD 2013–08– 

23 to reduce the potential of ignition 

sources inside fuel tanks, which, in 

combination with flammable fuel 

vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

Actions Since AD 2013–08–23, 

Amendment 39–17441 (78 FR 24037, 

April 24, 2013), Was Issued 

Since we issued AD 2013–08–23, 

Amendment 39–17441 (78 FR 24037, 

April 24, 2013), we have determined 


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that it is necessary to clarify the 

requirements for the design features and 

to remove a terminating action for 

certain inspections. In addition, The 

Boeing Company has issued new service 

information, which provides optional 

alternative methods of compliance for 

the actions required by AD 2013–08–23. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information, which describes 

procedures for changing the fuel pump 

control and indication system wiring: 

• Boeing Service Bulletin DC10–28– 

256, dated June 24, 2014; and 

• Boeing Service Bulletin MD11–28– 

137, dated June 24, 2014. 

We have also reviewed Appendixes B, 

C, and D of Boeing Special Compliance 

Item Report MDC–02K1003, Revision M, 

dated July 25, 2014, which include 

Critical Design Configuration Control 

Limitations (CDCCLs), Airworthiness 

Limitations Instructions (ALIs), and 

short-term extensions. 

Boeing Service Bulletin MD11–28– 

137, dated June 24, 2014, specifies prior 

or concurrent accomplishment of 

Boeing Alert Service Bulletin MD11– 

28A133, dated June 5, 2014. Boeing 

Alert Service Bulletin MD11–28A133, 

dated June 5, 2014, describes 

procedures for replacing the fuel pump 

control relays with fault current 

detectors and changing the fuel tank 

boost/transfer pump wire termination. 

Boeing Service Bulletin DC10–28– 

256, dated June 24, 2014, specifies prior 

or concurrent accomplishment of 

Boeing Alert Service Bulletin DC10– 

28A253, dated June 5, 2014. Boeing 

Alert Service Bulletin DC10–28A253, 

dated June 5, 2014, describes 

procedures for replacing the fuel pump 

control relays with fault current 

detectors and changing the fuel tank 

boost/transfer pump wire termination. 

This service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

Clarification of the Requirements for 

the Design Features 

In the introductory text of paragraph 

(g) of this proposed AD, we have added 

the text ‘‘for the auxiliary fuel tank’’ to 

the last sentence to clarify that, for 

airplanes on which Boeing-installed 

auxiliary fuel tanks are removed, only 

the actions specified in this AD for the 

auxiliary fuel tanks are not required. 

In paragraph (g)(1) of this proposed 

AD, we have added the text ‘‘and each 

pump that is partially covered by a 

lowering fuel level’’ and ‘‘main tanks’’ 

to the first sentence to clarify the pumps 

that must have a protective device 

installed. 

Removal of a Terminating Action for 

Certain Actions 

Paragraph (h) of AD 2013–08–23, 

Amendment 39–17441 (78 FR 24037, 

April 24, 2013), specifies, in part, that 

accomplishing the actions required by 

paragraph (g)(1) of that AD terminates 

certain inspections and tests required by 

paragraph (a) of AD 2002–13–10, 

Amendment 39–12798 (67 FR 45053, 

July 8, 2002), and repetitive inspections 

required by paragraph (j) of AD 2011– 

11–05, Amendment 39–16704 (76 FR 

31462, June 1, 2011), for pumps affected 

by those ADs. However, we have 

determined that accomplishing the 

actions required by paragraph (g)(1) of 

AD 2013–08–23 (which is restated in 

paragraph (g)(1) of this proposed AD) 

does not terminate those actions and, 

therefore, we have not retained the 

terminating action in this proposed AD. 

The actions specified in paragraph (h) of 

this proposed AD (i.e., a new optional 

method of compliance in lieu of 

paragraph (g) of this proposed AD) 

would extend the compliance times for 

certain inspections and tests required by 

paragraph (a) of AD 2002–13–10, and 

repetitive inspections required by 

paragraph (j) of AD 2011–11–05, from 

18-month intervals to 24-month 

intervals. We have added paragraph (j) 

to this proposed AD to specify that 

accomplishing the actions in paragraph 

(h) of this proposed AD would extend 

certain repetitive intervals. 

Revised Compliance Time 

We have determined that it is 

appropriate to allow additional time to 

accomplish the design features and 

requirements specified in this proposed 

AD. Therefore, we have added a 

compliance time ‘‘as of 48 months after 

the effective date of this AD’’ to 

paragraph (g) of this proposed AD. We 

have determined that this extension of 

the compliance time will provide an 

acceptable level of safety. 

Related AD 

On November 12, 2009, we issued AD 

2008–06–21 R1, Amendment 39–16100 

(74 FR 61504, November 25, 2009), for 

all McDonnell Douglas Corporation 

Model DC–10–10 and DC–10–10F 

airplanes, Model DC–10–15 airplanes, 

Model DC–10–30 and DC–10–30F (KC– 

10A and KDC–10) airplanes, Model DC– 

10–40 and DC–10–40F airplanes, Model 

MD–10–10F and MD–10–30F airplanes, 

and Model MD–11 and MD–11F 

airplanes. AD 2008–06–21 R1 requires 

revising the maintenance program or the 

Airworthiness Limitations (AWLs) 

section of the Instructions for Continued 

Airworthiness to incorporate 

inspections and CDCCLs. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Proposed AD Requirements 

This proposed AD would retain 

certain requirements of AD 2013–08–23, 

Amendment 39–17441 (78 FR 24037, 

April 24, 2013), clarify certain 

requirements, and remove a certain 

terminating action. This proposed AD 

would also provide a new optional 

method of compliance for the actions 

required by AD 2013–08–23. 

This proposed AD specifies to revise 

certain operator maintenance 

documents to include new actions (e.g., 

inspections) and Critical Design 

Configuration Control Limitations 

(CDCCLs). Compliance with these 

actions and CDCCLs is required by 14 

CFR 91.403(c). For airplanes that have 

been previously modified, altered, or 

repaired in the areas addressed by this 

proposed 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 (k) of this 

proposed AD. The request should 

include a description of changes to the 

required actions and CDCCLs that will 

ensure the continued operational safety 

of the airplane. 

Costs of Compliance 

We estimate that this proposed AD 

affects 341 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


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ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Installing design features using a method approved by the 

FAA [retained action from AD 2013-08–23, Amendment 

39-17441 (78 FR 24037, April 24, 2013)].

152 work-hours × $85 per 

hour = $12,920.

$137,500 $150,420 $51,923,220 

Installing design features using service information specified 

in paragraph (h) of this proposed AD (including revising 

the maintenance/inspection program) [new option of this 

proposed AD].

98 work-hours × $85 per hour 

= $8,330.

109,000 117,330 40,478,850 

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 

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 that the 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 

removing Airworthiness Directive (AD) 

2013–08–23, Amendment 39–17441 (78 

FR 24037, April 24, 2013), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2015–0248; Directorate Identifier 2014– 

NM–143–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by May 11, 2015. 

(b) Affected ADs 

(1) This AD replaces AD 2013–08–23, 

Amendment 39–17441 (78 FR 24037, April 

24, 2013). 

(2) This AD affects AD 2008–06–21 R1, 

Amendment 39–16100 (74 FR 61504, 

November 25, 2009). 

(3) This AD affects AD 2002–13–10, 

Amendment 39–12798 (67 FR 45053, July 8, 

2002). 

(4) This AD affects AD 2011–11–05, 

Amendment 39–16704 (76 FR 31462, June 1, 

2011). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model airplanes identified in 

paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) DC–10–10, DC–10–10F, DC–10–15, DC– 

10–30, DC–10–30F (KC–10A and KDC–10), 

DC–10–40, DC–10–40F airplanes. 

(2) MD–10–10F, MD–10–30F, MD–11, and 

MD–11F airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by a fuel system 

review conducted by the manufacturer. We 

are issuing this AD to reduce the potential of 

ignition sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Criteria for Operation, With 

Clarifications and New Compliance Time 

This paragraph restates the actions 

required by paragraph (g) of AD 2013–08–23, 

Amendment 39–17441 (78 FR 24037, April 

24, 2013), with clarification of actions for 

airplanes with auxiliary fuel tanks removed, 

clarification of the pumps that must have a 

protective device installed, and a new 

compliance time. Except as provided by 

paragraph (h) of this AD: As of 48 months 

after the effective date of this AD, no person 

may operate any airplane affected by this AD 

unless an amended type certificate or 

supplemental type certificate that 

incorporates the design features and 

requirements described in paragraphs (g)(1) 

through (g)(4) of this AD has been approved 

by the Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, and those 

design features are installed on the airplane 

to meet the criteria specified in 14 CFR 

Section 25.981(a) and (d), at Amendment 

level 25–125. For airplanes on which Boeinginstalled auxiliary fuel tanks are removed, 

the actions specified in this AD for the 

auxiliary fuel tanks are not required. 

(1) For all airplanes: Each electrically 

powered alternating current (AC) fuel pump 

installed in any fuel tank that normally 

empties during flight and each pump that is 

partially covered by a lowering fuel level— 

such as main tanks, center wing tanks, 

auxiliary fuel tanks installed by the airplane 

manufacturer, and tail tanks—must have a 

protective device installed to detect electrical 

faults that can cause arcing and burn through 

of the fuel pump housing and pump 

electrical connector. The same device must 

shut off the pump by automatically removing 

electrical power from the pump when such 

faults are detected. When a fuel pump is shut 

off resulting from detection of an electrical 

fault, the device must stay latched off, until 


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the fault is cleared through maintenance 

action and the pump is verified safe for 

operation. 

(2) For airplanes with a 2-person flight 

crew: Additional design features, if not 

originally installed by the airplane 

manufacturer, must be installed to meet 3 

criteria: To detect a running fuel pump in a 

tank that is normally emptied during flight, 

to provide an indication to the flight crew 

that the tank is empty, and to automatically 

shut off that fuel pump. The prospective 

pump indication and shutoff system must 

automatically shut off each pump in case the 

flight crew does not shut off a pump running 

dry in an empty tank within 60 seconds after 

each fuel tank is emptied. An airplane flight 

manual supplement (AFMS) that includes 

flight crew manual pump shutoff procedures 

in the Limitations Section of the AFMS must 

be submitted to the Los Angeles ACO, FAA, 

for approval. 

(3) For airplanes with a 3-person flight 

crew: Additional design features, if not 

originally installed by the airplane 

manufacturer, must be installed to detect 

when a fuel pump in a tank that is normally 

emptied during flight is running in an empty 

fuel tank, and provide an indication to the 

flight crew that the tank is empty. The flight 

engineer must manually shut off each pump 

running dry in an empty tank within 60 

seconds after the tank is emptied. The AFMS 

Limitations section must be revised to 

specify that this pump shutoff must be done 

by the flight engineer. 

(4) For all airplanes with tanks that 

normally empty during flight: Separate 

means must be provided to detect and shut 

off a pump that was previously commanded 

to be shut off automatically or manually but 

remained running in an empty tank during 

flight. 

(h) New Optional Method of Compliance 

In lieu of doing the requirements of 

paragraph (g) of this AD, do the applicable 

actions specified in paragraphs (h)(1), (h)(2), 

and (h)(3) of this AD. 

(1) For MD–11 and MD–11F airplanes: Do 

the actions specified in paragraphs (h)(1)(i) 

and (h)(1)(ii) of this AD. 

(i) As of 48 months after the effective date 

of this AD, change the fuel pump control and 

indication system wiring, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin MD11–28–137, dated 

June 24, 2014. 

(ii) Prior to or concurrently with 

accomplishing the actions specified in 

paragraph (h)(1)(i) of this AD: Replace the 

fuel pump control relays with fault current 

detectors, and change the fuel tank boost/

transfer pump wire termination, in 

accordance with Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD11–28A133, dated June 5, 2014. 

(2) For Model DC–10–10, DC–10–10F, DC– 

10–15, DC–10–30, DC–10–30F (KC–10A and 

KDC–10), DC–10–40, DC–10–40F, MD–10– 

10F, and MD–10–30F airplanes: Do the 

actions specified in paragraphs (h)(2)(i) and 

(h)(2)(ii) of this AD. 

(i) As of 48 months after the effective date 

of this AD, change the fuel pump control and 

indication system wiring, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin DC10–28–256, dated June 

24, 2014. 

(ii) Prior to or concurrently with 

accomplishing the actions specified in 

paragraph (h)(2)(i) of this AD: Replace the 

fuel pump control relays with fault current 

detectors, and change the fuel tank boost/

transfer pump wire termination, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

DC10–28A253, dated June 5, 2014. 

(3) For all airplanes: Within 30 days after 

accomplishing the actions required by 

paragraph (h)(1) or (h)(2) of this AD, or 

within 30 days after the effective date of this 

AD, whichever occurs later, revise the 

maintenance or inspection program, as 

applicable, to incorporate the Critical Design 

Configuration Control Limitations (CDCCLs), 

Airworthiness Limitations Instructions 

(ALIs), and short-term extensions specified in 

Appendix B, C, and D of Special Compliance 

Item (SCI) Report MDC–02K1003, Revision 

M, dated July 25, 2014. The initial 

compliance time for accomplishing the 

actions specified in the ALIs is at the later 

of the times specified in paragraphs (h)(3)(i) 

and (h)(3)(ii) of this AD. Revising of the 

maintenance or inspection program required 

by this paragraph terminates the 

requirements in paragraph (g) and (h) of AD 

2008–06–21 R1, Amendment 39–16100 (74 

FR 61504, November 25, 2009). 

(i) At the applicable time specified in 

Appendix C of SCI Report MDC–02K1003, 

Revision M, dated July 25, 2014, except as 

provided by Appendix D of SCI Report MDC– 

02K1003, Revision M, dated July 25, 2014. 

(ii) Within 30 days after accomplishing the 

actions required by paragraph (h)(1) or (h)(2) 

of this AD, or within 30 days after the 

effective date of this AD, whichever occurs 

later. 

(i) No Alternative Actions, Intervals, or 

CDCCLs 

If the option in paragraph (h)(3) of this AD 

is accomplished: After the maintenance or 

inspection program has been revised, as 

provided by paragraph (h)(3) of this AD, no 

alternative actions (e.g., inspections), 

intervals, or CDCCLs may be used unless the 

actions, intervals, or CDCCLs are approved as 

an alternative method of compliance (AMOC) 

in accordance with the procedures specified 

in paragraph (k) of this AD. 

(j) Compliance Time Extension in Related 

ADs 

Accomplishment of the actions specified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD, as applicable, extends the 18-month 

repetitive inspections and tests required by 

paragraph (a) of AD 2002–13–10, 

Amendment 39–12798 (67 FR 45053, July 8, 

2002), and the 18-month repetitive 

inspections required by paragraph (j) of AD 

2011–11–05, Amendment 39–16704 (76 FR 

31462, June 1, 2011), to 24-month intervals 

for pumps affected by those ADs, regardless 

if the pump is installed in a tank that 

normally empties, provided the remaining 

actions required by those two ADs have been 

accomplished. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-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, Los Angeles 

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 for AD 2013–08–23, 

Amendment 39–17441 (78 FR 24037, April 

24, 2013), are approved as AMOCs for the 

corresponding provisions of this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Serj Harutunian, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: 562–627– 

5254; fax: 562–627–5210; email: 

serj.harutunian@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; fax 

206–766–5683; Internet https://

www.myboeingfleet.com. You may view this 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–06746 Filed 3–26–15; 8:45 am] 

BILLING CODE 4910–13–P 


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