AD 2016-21-05

[Federal Register Volume 81, Number 219 (Monday, November 14, 2016)]
[Rules and Regulations]
[Pages 79384-79389]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-25491]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7527; Directorate Identifier 2015-NM-094-AD; 
Amendment 39-18686; AD 2016-21-05]
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 adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 777-200, -200LR, -300, and -300ER series 
airplanes. This AD was prompted by a report indicating that the 
manufacturer discovered locations where the control components and 
wiring of the left and right engine fuel spar valves do not have 
adequate physical separation to meet the redundant system separation 
requirements. This AD requires modifying the wiring, and installing a 
new relay bracket and new location for the relay on the left and right 
engine fuel spar valves. This AD also requires an inspection to 
identify the part number of the motor operated valve (MOV) actuators 
for the left and right engine fuel spar valves; replacement of 
specified MOV actuators with new MOV actuators; certain bonding 
resistance measurements; and applicable corrective actions. We are 
issuing this AD to prevent loss of control of both the left and right 
engine fuel spar valves during a single event, such as local wire 
bundle damage or a wire bundle fire, which could cause both engines to 
shut down or result in the inability to control an engine fire.

DATES: This AD is effective December 19, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 19, 
2016.

ADDRESSES: For service information identified in this final rule, 
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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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

[[Page 79385]]

available on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2015-7527.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
7527; 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: Brendan Shanley, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
telephone: 425-917-6492; fax: 425-917-6590; email: 
<a href="/cdn-cgi/l/email-protection#315343545f55505f1f4259505f5d5448715750501f565e47"><span class="__cf_email__" data-cfemail="385a4a5d565c5956164b505956545d41785e5959165f574e">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 777-200, -200LR, -300, and -300ER series airplanes. The NPRM 
published in the Federal Register on December 23, 2015 (80 FR 79754) 
(``the NPRM''). The NPRM was prompted by a report indicating that the 
manufacturer discovered locations where the control components and 
wiring of the left and right engine fuel spar valves do not have 
adequate physical separation to meet the redundant system separation 
requirements. The NPRM proposed to require modifying the wiring, and 
installing a new relay bracket and new location for the relay on the 
left and right engine fuel spar valves. The NPRM also proposed to 
require an inspection to identify the part number of the MOV actuators 
for the left and right engine fuel spar valves; replacement of 
specified MOV actuators with new MOV actuators; certain bonding 
resistance measurements; and applicable corrective actions. We are 
issuing this AD to prevent loss of control of both the left and right 
engine fuel spar valves during a single event, such as local wire 
bundle damage or a wire bundle fire, which could cause both engines to 
shut down or result in the inability to control an engine fire.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment. Boeing stated that it has reviewed 
the NPRM and concurs with the contents of the NPRM.

Request To Reduce the Compliance Time

    One commenter, Geoffrey Barrance, requested that we reduce the 
compliance time in paragraph (g) of the proposed AD. Mr. Barrance 
stated he is concerned that the timescale proposed for implementing the 
required modification, 60 months after the effective date of the AD, is 
too long. Mr. Barrance commented that the unsafe condition is a common 
failure affecting the continued operation of both engines, and 
therefore is critical to the safe flight and landing of any airplane.
    We disagree with the commenter's request. It is important to note 
that while the commenter has indicated there is currently a common mode 
failure affecting the continued operation of both engines, it is more 
accurate to say that certain airplanes are currently in a configuration 
that makes them vulnerable to a single event causing a common mode 
failure. However, there have been no reports of any events causing this 
condition. This AD is intended to eliminate that condition.
    The compliance time is determined to be appropriate in 
consideration of the risk and the safety implications, the average 
utilization rate of the affected fleet, the practical aspects of an 
orderly modification of the fleet during regular maintenance periods, 
and the availability of required modification parts. In addition to our 
own criteria, we have also considered the manufacturer's safety 
assessment and recommendation for the compliance time. The compliance 
time accounts for the risk to the fleet, availability of parts, and 
other factors. Therefore, we have determined that the compliance time 
is acceptable. We have not changed this AD in this regard.

Request To Remove the Concurrent Requirements

    All Nippon Airways (ANA), Japan Airlines (JAL), and United Airlines 
(UAL) requested that we remove the concurrent requirement for 
accomplishing Boeing Service Bulletin 777-28A0034, Revision 3, dated 
September 25, 2015. JAL and ANA stated that there was no relationship 
between the wiring change and the actuator replacement. ANA, JAL, and 
UAL commented that Boeing Service Bulletin 777-28A0034, Revision 3, 
dated September 25, 2015, is already mandated by AD 2013-05-03, 
Amendment 39-17375 (78 FR 17290, March 21, 2013) (``AD 2013-05-03''), 
and it addressed MOV actuator part number (P/N) MA20A1001-1; therefore, 
it should not be a concurrent requirement. ANA also added that because 
the MOV actuator has been addressed, paragraphs (i)(2) and (i)(3) of 
the proposed AD should not be included.
    We partially agree with the commenters. We agree that the actions 
in Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 
2015, are the same actions that are required by AD 2013-05-03 in 
accordance with Boeing Service Bulletin 777-28A0034, Revision 2, dated 
September 20, 2010, with a compliance date of April 25, 2018. Because 
of the overlap in compliance times, the action required by AD 2013-05-
03 may not be fully completed by the time the requirements of this AD 
become effective. To ensure that the actuator change, in accordance 
with Boeing Service Bulletin 777-28A0034, Revision 3, dated September 
25, 2015, is done prior to the wiring change in accordance with Boeing 
Special Attention Service Bulletin 777-28-0061, Revision 2, dated May 
4, 2015, we have required Boeing Service Bulletin 777-28A0034, Revision 
3, dated September 25, 2015, as a concurrent requirement in this AD. 
Without this concurrent requirement, it is possible that this AD could 
approve certain configurations that are not compliant and safe. The 
concurrent requirement eliminates this possibility. The requirements of 
Boeing Service Bulletin 777-28A0034, Revision 3, dated September 25, 
2015, and related credit for previous actions, will remain as stated. 
We have not changed this AD in this regard.

Request To Use Boeing Information Notice for Completing the 
Requirements in the AD

    ANA requested that we include Boeing Service Bulletin Information 
Notice 777-28-0061, IN 03, dated November 16, 2015, to this AD to allow 
the operators to complete the proposed requirements of the NPRM.
    We partially agree with the commenter's request. We cannot include 
Boeing Service Bulletin Information Notice 777-28-0061, IN 03, dated 
November 16, 2015, as an

[[Page 79386]]

appropriate source of service information in this AD because it is not 
an FAA-approved document. However, we acknowledge that for certain 
airplanes, Figure 22, Sheet 9, of Boeing Special Attention Service 
Bulletin 777-28-0061, Revision 2, dated May 4, 2015, includes an 
editorial error, which shows incorrect wire routing. Boeing Service 
Bulletin Information Notice 777-28-0061, IN 03, dated November 16, 
2015, allows for a modification of Group 2 airplanes that meets the 
requirements of the AD without an additional burden to operators. We 
have included a corrected figure in paragraph (h) of this AD to address 
this issue.
    In addition, Figure 11, Sheet 1, of Boeing Special Attention 
Service Bulletin 777-28-0061, Revision 2, dated May 4, 2015, is 
incorrect in that it shows the cap and stow of an existing wire, W4255-
1002-20, which is terminated at splice SP41201. The correct wire number 
to be capped and stowed is W6251-1002-20, which is terminated at splice 
SP41201. We have clarified this information in paragraph (h)(2) of this 
AD.

Request To Clarify the Terminating Action

    JAL and UAL requested that we clarify the terminating action 
specified in the proposed rule. JAL asked that Boeing Service Bulletin 
777-28A0034 be used as a terminating action for the requirements of the 
proposed rule. UAL stated that since AD 2013-05-03 already addressed 
MOV actuator P/N MA20A2027 and P/N MA30A1001, it contradicts 
airworthiness limitations (AWL) 28-AWL-MOV, which was mandated in AD 
2015-19-01, Amendment 39-18264 (80 FR 55521, dated September 16, 2015) 
(``AD 2015-19-01'').
    We agree that clarification is necessary. We agree that certain 
configurations in Boeing Service Bulletin 777-28A0034, Revision 3, 
dated September 25, 2015, in conjunction with previous airplane 
configurations, alleviate the need to do the AWL task implemented by AD 
2013-05-03 because the configurations are outside the applicability of 
that AWL. However, we disagree with using Boeing Service Bulletin 777-
28A0034, Revision 3, dated September 25, 2015, as a terminating action 
because the requirement of AD 2015-19-01 is to implement the 
airworthiness limitations items (ALI) into an operator's maintenance 
program, and this must be done regardless of the configuration of the 
airplane. Further, certain MOV actuator part numbers can be installed 
that will place an airplane in the applicability of AWL 28-AWL-MOV, 
thus requiring periodic inspections to ensure safe operation. Each 
operator has the option to select a configuration best for its 
circumstances and can evaluate its configurations and determine if AWL 
28-AWL-MOV is applicable to their fleet configuration. We have not 
changed this AD in this regard.

Request To Review the Design and Certification Process

    Geoffrey Barrance requested that we review the design and 
certification process that allowed for the unsafe condition to exist, 
as well as a review of designs in other airplanes with similar unsafe 
conditions. Mr. Barrance commented that the unsafe condition indicated 
a failure has occurred in the design and certification process for the 
airplane type. Mr. Barrance also commented that a review of the 
airplane design is required to prevent the implementation of common 
mode fault exposures for redundant systems.
    We acknowledge the commenter's concerns. We continuously evaluate 
our certification system and procedures and improve them when problems 
are found. If the FAA is made aware of potential design deficiencies 
occurring on a certificated product, we conduct an investigation, 
evaluate the manufacturer's root-cause analysis, and make a 
determination whether or not an unsafe condition exists. We then take 
appropriate action to mitigate the unsafe condition and to identify and 
incorporate certification system process improvements for future 
designs. Furthermore, the manufacturer performs a cross model 
evaluation to determine if the condition exists on other models. We 
agree with the manufacturer's actions in this regard. We have not 
changed this AD regarding this issue.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    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 Boeing Special Attention Service Bulletin 777-28-0061, 
Revision 2, dated May 4, 2015. The service information describes 
procedures for modifying the wiring, and installing a new relay bracket 
and new location for the relay on the left and right engine fuel spar 
valves.
    We have also reviewed Boeing Service Bulletin 777-28A0034, Revision 
3, dated September 25, 2015. The service information describes 
procedures for an inspection of the MOV actuators of the left and right 
engine fuel spar valves for (P/N) MA20A1001-1, replacement of MOV 
actuators, measurement of the electrical resistance of the bond from 
the adapter plate to the airplane structure, and applicable corrective 
actions.
    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 133 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Installation and modification...  119 work-hours x    Up to $3,780        Up to $13,895       Up to $1,848,035
                                   $85 per hour =      depending on        depending on        depending on
                                   $10,115.            airplane            airplane            airplane
                                                       configuration.      configuration.      configuration.
Inspection of MOV actuators       1 work-hour x $85   $0................  $85...............  $11,305.
 [concurrent requirements].        per hour = $85.
----------------------------------------------------------------------------------------------------------------


[[Page 79387]]

    We estimate the following costs to do any necessary replacements 
and bonding resistance measurements that would be required based on the 
results of the inspection. We have no way of determining the number of 
aircraft that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement of MOV actuators for the   Up to 105 work-hours x   Up to $10,954..........  Up to $19,879.
 left and right engine fuel spar        $85 per hour = $8,925.
 valves.
Bonding resistance measurements......  1 work-hour x $85 per    $0.....................  $85.
                                        hour = $85.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data on the costs of the corrective 
actions for the bonding resistance measurement in 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

    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 adding the following new airworthiness 
directive (AD):

2016-21-05 The Boeing Company: Amendment 39-18686; Docket No. FAA-
2015-7527; Directorate Identifier 2015-NM-094-AD.

(a) Effective Date

    This AD is effective December 19, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, and -300ER series airplanes, certificated in any category, as 
identified in Boeing Special Attention Service Bulletin 777-28-0061, 
Revision 2, dated May 4, 2015.

(d) Subject

    Air Transport Association (ATA) of America Code 2822, Fuel Boost 
Pump.

(e) Unsafe Condition

    This AD was prompted by a report indicating that the 
manufacturer discovered locations where the control components and 
wiring of the left and right engine fuel spar valves do not have 
adequate physical separation to meet the redundant system separation 
requirements. We are issuing this AD to prevent loss of control of 
both the left and right engine fuel spar valves during a single 
event, such as local wire bundle damage or a wire bundle fire, which 
could cause both engines to shut down or result in the inability to 
control an engine fire.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Modification

    Within 60 months after the effective date of this AD, modify the 
wiring and install new relay brackets in new locations to allow 
installation of new relays for the left and right engine fuel spar 
valves, in accordance with the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 777-28-0061, Revision 2, dated 
May 4, 2015, except as required by paragraph (h) of this AD.

(h) Exceptions to the Service Information

    (1) Where Boeing Special Attention Service Bulletin 777-28-0061, 
Revision 2, dated May 4, 2015, specifies to use Figure 22, Sheet 9, 
for the wiring installation of the right engine fuel spar valve, 
this AD requires using figure 1 to paragraph (h) of this AD.
    (2) Boeing Special Attention Service Bulletin 777-28-0061, 
Revision 2, dated May 4, 2015, specifies to use Figure 11, Sheet 1, 
for the wiring change at E2-6--Shelf to Disconnect Panel and Splice 
Area. The figure shows the capping and stowing of an existing wire, 
W4255-1002-20, which is terminated at splice SP41201. The wire 
number is incorrect. The correct wire number to cap and stow is 
W6251-1002-20, which is terminated at splice SP41201.

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[GRAPHIC] [TIFF OMITTED] TR14NO16.003

BILLING CODE 4910-13-C

(i) Concurrent Requirements

    (1) Prior to or concurrently with accomplishing the requirements 
of paragraph (g) of this AD: Do an inspection of the motor operated 
valve (MOV) actuators of the left and right engine fuel spar valves 
for part number (P/N) MA20A1001-1, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 777-28A0034, 
Revision 3, dated September 25, 2015. A review of airplane 
maintenance records is acceptable in lieu of this inspection if the 
part number can be conclusively determined from that review.
    (2) If any MOV actuator having P/N MA20A1001-1 is found during 
the inspection required by paragraph (i)(1) of this AD, prior to or 
concurrently with accomplishing the requirements of paragraph (g) of 
this AD, replace the MOV actuator with either a new or serviceable 
MOV actuator having P/N MA30A1001, MA30A1017, MA20A2027, or an MOV 
actuator that meets the criteria specified in paragraphs (i)(2)(i) 
and (i)(2)(ii) of this AD; and, as applicable, measure the 
electrical resistance of the bond from the adapter plate to the 
airplane structure and, before further flight, do all applicable 
corrective actions. All actions specified in this paragraph for the 
left and right engine fuel spar valves must be done in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 777-
28A0034, Revision 3, dated September 25, 2015.
    (i) The replacement MOV actuator must be a Boeing part that is 
approved after the issuance of Boeing Service Bulletin 777-28A0034, 
Revision 3, dated September 25, 2015, by the Manager, Seattle 
Aircraft

[[Page 79389]]

Certification Office (ACO), FAA; or the Boeing Commercial Airplanes 
Organization Designation Authorization (ODA) that has been 
authorized by the Manager, Seattle ACO, to approve the part.
    (ii) The replacement MOV actuator must be fully interchangeable 
with the part specified in Boeing Service Bulletin 777-28A0034, 
Revision 3, dated September 25, 2015.

(j) Credit for Previous Actions

    (1) This paragraph provides credit for the requirements of 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Special Attention Service 
Bulletin 777-28-0061, dated October 25, 2010; or Boeing Special 
Attention Service Bulletin 777-28-0061, Revision 1, dated January 
26, 2012; as applicable. These documents are not incorporated by 
reference in this AD.
    (2) This paragraph provides credit for the requirements of 
paragraph (i) of this AD, if those actions were performed before 
April 25, 2013 (the effective date of AD 2013-05-03, Amendment 39-
17375 (78 FR 17290, March 21, 2013), ``AD 2013-05-03''), using 
Boeing Alert Service Bulletin 777-28A0034, dated August 2, 2007; or 
Boeing Alert Service Bulletin 777-28A0034, Revision 1, dated May 20, 
2010; except that the replacement of MOV actuators of the left and 
right engine fuel spar valves must also include cap sealing the 
bonding jumper, as described in Boeing Service Bulletin 777-28A0034, 
Revision 2, dated September 20, 2010; and provided that the 
replacement is an MOV actuator identified in paragraph (j)(2)(i) or 
(j)(2)(ii) of this AD. Boeing Alert Service Bulletin 777-28A0034, 
dated August 2, 2007, and Boeing Alert Service Bulletin 777-28A0034, 
Revision 1, dated May 20, 2010, are not incorporated by reference in 
this AD. Boeing Service Bulletin 777-28A0034, Revision 2, dated 
September 20, 2010, is incorporated by reference in AD 2013-05-03.
    (i) An MOV actuator that has P/N MA30A1001, MA30A1017, or 
MA20A2027.
    (ii) An MOV actuator that has a part number other than P/N 
MA20A1001-1 and meets the criteria specified in paragraphs (i)(2)(i) 
and (i)(2)(ii) of this AD.
    (3) This paragraph provides credit for the requirements of 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Service Bulletin 777-28A0034, 
Revision 2, dated September 20, 2010, which was incorporated by 
reference in AD 2013-05-03.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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#60594d212e2d4d33050114140c054d21232f4d212d2f234d3205111505131413200601014e070f16"><span class="__cf_email__" data-cfemail="152c38545b5838467074616179703854565a3854585a56384770646070666166557374743b727a63">[email&#160;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, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes ODA that has 
been authorized by the Manager, Seattle ACO, to make those findings. 
To be approved, the repair method, modification deviation, or 
alteration deviation must meet the certification basis of the 
airplane and the approval must specifically refer to this AD.

(l) Related Information

    (1) For more information about this AD, contact Brendan Shanley, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone: 425-917-6492; fax: 425-917-6590; email: 
<a href="/cdn-cgi/l/email-protection#b3d1c1d6ddd7d2dd9dc0dbd2dddfd6caf3d5d2d29dd4dcc5"><span class="__cf_email__" data-cfemail="3a58485f545e5b541449525b54565f437a5c5b5b145d554c">[email&#160;protected]</span></a>.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(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 Special Attention Service Bulletin 777-28-0061, 
Revision 2, dated May 4, 2015.
    (ii) Boeing Service Bulletin 777-28A0034, Revision 3, dated 
September 25, 2015.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet 
<a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (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.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on October 7, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-25491 Filed 11-10-16; 8:45 am]
 BILLING CODE 4910-13-P