81 FR 12806 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 48 (March 11, 2016)

We are superseding Airworthiness Directive (AD) 2013-08-23 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 required adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. This new AD would clarify certain requirements and remove a terminating action. This new AD would also provide an optional method of compliance for the proposed actions. This AD was prompted by a determination that it is necessary to clarify the requirements for the design features and to remove a terminating action for certain inspections. 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.

[Federal Register Volume 81, Number 48 (Friday, March 11, 2016)]
[Rules and Regulations]
[Pages 12806-12810]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-04564]


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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; 
Amendment 39-18410; AD 2016-04-16]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2013-08-23 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 required adding design 
features to detect electrical faults and to detect a pump running in an 
empty fuel tank. This new AD would clarify certain requirements and 
remove a terminating action. This new AD would also provide an optional 
method of compliance for the proposed actions. This AD was prompted by 
a determination that it is necessary to clarify the requirements for 
the design features and to remove a terminating action for certain 
inspections. 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.

DATES: This AD is effective April 15, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 15, 
2016.

ADDRESSES: For service information identified in this final rule, 
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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Serj Harutunian, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5254; fax: 562-627-5210; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2013-08-23, Amendment 39-17441 (78 FR 24037, 
April 24, 2013). AD 2013-08-23 applied 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. 
The NPRM published in the Federal Register on March 27, 2015 (80 FR 
16321). The NPRM was prompted by a determination that it is necessary 
to clarify the requirements for the design features and to remove a 
terminating action for certain inspections. The NPRM proposed to 
clarify certain requirements and remove a terminating action. The NPRM 
also proposed to provide an optional method of compliance for the 
proposed actions. 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 16321, March 27, 2015) and the FAA's response to each comment.

[[Page 12807]]

Support for the NPRM (80 FR 16321, March 27, 2015)

    Boeing stated that it supports the NPRM (80 FR 16321, March 27, 
2015).

Request for Clarification

    FedEx requested that we clarify paragraph (h)(3) of the proposed AD 
(80 FR 16321, March 27, 2015) because it is unclear and confusing.
    FedEx explained that paragraphs (h)(1) and (h)(2) of the proposed 
AD (80 FR 16321, March 27, 2015) propose to mandate compliance with 
Boeing Alert Service Bulletin MD11-28A133, dated June 5, 2014; Boeing 
Service Bulletin MD11-28-137, dated June 24, 2014; Boeing Alert Service 
Bulletin DC10-28A253, dated June 5, 2014; and Boeing Service Bulletin 
DC10-28-256, dated June 24, 2014. This service information, in addition 
to describing procedures for airframe modifications, specifies revising 
Airworthiness Limitation Instructions (ALI) 28-1, Trijet Fuel Pump 
Fault Current Detector Functional Check; ALI 28-2, DC-10/KDC-10 
Uncommanded On Circuit Functional Check; ALI 28-3, MD-10 Uncommanded On 
Circuit Functional Check; and ALI 28-4, MD-11 Uncommanded On Circuit 
Functional Check, Boeing Trijet Special Compliance Item Report MDC-
02K1003, Revision M, dated July 25, 2014. FedEx stated that paragraph 
(h)(3) of the proposed AD creates confusion because Appendixes B and C 
of Boeing Trijet Special Compliance Item Report MDC-02K1003, Revision 
M, dated July 25, 2014, also change/affect Critical Design 
Configuration Control Limitation (CDCCL) 20-9, Trijet Wing Root Area 
Lightning Protection, (Boeing Service Bulletin DC10-28-262, Revision 1, 
dated June 9, 2010, which was mandated by AD 2010-21-13, Amendment 39-
16473 (75 FR 63040, October 14, 2010), and has nothing to do with the 
intent of this NPRM, which supersedes AD 2013-08-23, Amendment 39-17441 
(78 FR 24037, April 24, 2013).
    FedEx also noted that paragraph (h)(3) of the proposed AD (80 FR 
16321, March 27, 2015) states that revising the maintenance or 
inspection program terminates the requirements in paragraphs (g) and 
(h) of AD 2008-06-21 R1, Amendment 39-16100 (74 FR 61504, November 25, 
2009). FedEx requested that we identify the requirements in AD 2008-06-
21 R1 that would be terminated. FedEx reasoned that paragraphs (g) and 
(h) of AD 2008-06-21 R1 cannot be terminated because CDCCLs and ALIs 
are constantly revised or new items added to meet safety requirements, 
so latent failures must be addressed in the fuel system design.
    We agree that clarification is necessary. AD 2010-21-13, Amendment 
39-16473 (75 FR 63040, October 14, 2010), requires installing a support 
bracket and coupler on the left and right wing-to-fuselage transition, 
and metallic overbraid on the left and right leading edge wire assembly 
but it does not require revising the maintenance or inspection program 
to incorporate a corresponding CDCCL. Paragraph (h)(3) of this AD 
includes incorporating CDCCL 20-9, Trijet Wing Root Area Lightning 
Protection, as part of the maintenance or inspection program. 
Notwithstanding any other maintenance or operational requirements, 
components that have been identified as airworthy or installed on the 
affected airplanes before accomplishing the revision of the airplane 
maintenance or inspection program specified in this AD, do not need to 
be reworked in accordance with the CDCCLs. However, once the airplane 
maintenance or inspection program has been revised as required by this 
AD, future maintenance actions on these components must be done in 
accordance with the CDCCLs.
    In regards to FedEx's comment on terminating action, we note that 
AD 2008-06-21 R1, Amendment 39-16100 (74 FR 61504, November 25, 2009) 
requires incorporation of Boeing Trijet Special Compliance Item Report, 
MDC-02K1003, Revision C, dated July 24, 2007. Paragraph (h)(3) of this 
AD requires a revision of the maintenance or inspection program to 
include Boeing Trijet Special Compliance Item (SCI) Report MDC-02K1003, 
Revision M, dated July 25, 2014. We are requiring the actions specified 
in Appendixes B, C, and D of Boeing Trijet Special Compliance Item 
Report MDC-02K1003, Revision M, dated July 25, 2014, because they 
include the latest CDCCLs, ALIs, and short-term extensions. Therefore, 
accomplishing the revision required by paragraph (h)(3) of this AD 
would terminate the requirements in paragraphs (g) and (h) of AD 2008-
06-21 R1. Accomplishing paragraph (h)(3) of this AD would replace the 
existing requirements with updated requirements. We have not changed 
this AD 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 
NPRM (80 FR 16321, March 27, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 16321, March 27, 2015).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information.
     Boeing Alert Service Bulletin DC10-28A253, dated June 5, 
2014; and Boeing Alert Service Bulletin MD11-28A133, dated June 5, 
2014. This service information 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; 
and Boeing Service Bulletin MD11-28-137, dated June 24, 2014; which 
describe procedures for changing the fuel pump control and indication 
system wiring.
     Boeing Trijet Special Compliance Item Report MDC-02K1003, 
Revision M, including Appendices A through D, dated July 25, 2014, 
which includes CDCCLs, ALIs, and short-term extensions in Appendices B, 
C, and D, respectively.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 341 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 12808]]



                                                 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[dash]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      40,009,530
 service information specified in        hour = $8,330.
 paragraph (h) of this AD (including
 revising the maintenance/inspection
 program) [new option of this 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 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

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:

2016-04-16 The Boeing Company: Amendment 39-18410; Docket No. FAA-
2015-0248; Directorate Identifier 2014-NM-143-AD.

(a) Effective Date

    This AD is effective April 15, 2016.

(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 airplanes identified 
in paragraphs (c)(1) and (c)(2) of this AD, certificated in any 
category.
    (1) 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 airplanes.
    (2) Model 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 section 
25.981(a) and (d) of the Federal Aviation Regulations (14 CFR 
25.981(a) and (d), at Amendment 25-125 (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgFAR.nsf/0/339DAEE3E0A6379D862574CF00641951?OpenDocument)). 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 the fault is cleared through maintenance 
action and the pump is verified safe for operation.

[[Page 12809]]

    (2) For airplanes with a 2-person flightcrew: 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 flightcrew 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 flightcrew 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 flightcrew 
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 flightcrew: 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 
to provide an indication to the flightcrew 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 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 Limitation Instructions (ALIs), and short-
term extensions specified in Appendices B, C, and D of Boeing Trijet 
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 the 
maintenance or inspection program required by this paragraph 
terminates the requirements in paragraphs (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 Boeing 
Trijet SCI Report MDC-02K1003, Revision M, dated July 25, 2014, 
except as provided by Appendix D of Boeing Trijet 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, as applicable; 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 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) of this AD. Information may be emailed 
to: [email protected].
    (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

    For more information about this AD, contact Serj Harutunian, 
Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles 
ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5254; fax: 562-627-5210; email: [email protected].

(m) 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.
    (i) Boeing Alert Service Bulletin DC10-28A253, dated June 5, 
2014.
    (ii) Boeing Alert Service Bulletin MD11-28A133, dated June 5, 
2014.
    (iii) Boeing Service Bulletin DC10-28-256, dated June 24, 2014.
    (iv) Boeing Service Bulletin MD11-28-137, dated June 24, 2014.
    (v) Boeing Trijet Special Compliance Item Report MDC-02K1003, 
Revision M, including Appendices A through D, dated July 25, 2014.
    (3) For Boeing 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.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.

[[Page 12810]]

    (5) 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/ibr-locations.html.

    Issued in Renton, Washington, on February 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04564 Filed 3-10-16; 8:45 am]
 BILLING CODE 4910-13-P