[Federal Register Volume 80, Number 59 (Friday, March 27, 2015)]
[Proposed Rules]
[Pages 16321-16324]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-06746]


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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).

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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:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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: 
<a href="/cdn-cgi/l/email-protection#2a594f584004424b585f5e5f44434b446a4c4b4b044d455c"><span class="__cf_email__" data-cfemail="87f4e2f5eda9efe6f5f2f3f2e9eee6e9c7e1e6e6a9e0e8f1">[email protected]</span></a>.

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

[[Page 16322]]

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:
    <bullet> Boeing Service Bulletin DC10-28-256, dated June 24, 2014; 
and
    <bullet> 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:

[[Page 16323]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Installing design features using a      152 work-hours x $85 per        $137,500        $150,420     $51,923,220
 method approved by the FAA [retained    hour = $12,920.
 action from AD 2013[dash]08-23,
 Amendment 39[dash]17441 (78 FR 24037,
 April 24, 2013)].
Installing design features using        98 work-hours x $85 per          109,000         117,330      40,478,850
 service information specified in        hour = $8,330.
 paragraph (h) of this proposed AD
 (including revising the maintenance/
 inspection program) [new option of
 this proposed AD].
----------------------------------------------------------------------------------------------------------------

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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 Boeing-installed 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

[[Page 16324]]

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: <a href="/cdn-cgi/l/email-protection#3d04107c737010717c7c7e72107c70727e106f584c48584e494e7d5b5c5c135a524b"><span class="__cf_email__" data-cfemail="99a0b4d8d7d4b4d5d8d8dad6b4d8d4d6dab4cbfce8ecfceaedead9fff8f8b7fef6ef">[email protected]</span></a>.
    (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: <a href="/cdn-cgi/l/email-protection#0a796f786024626b787f7e7f64636b644a6c6b6b246d657c"><span class="__cf_email__" data-cfemail="146771667e3a7c75666160617a7d757a547275753a737b62">[email protected]</span></a>.
    (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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