AD 2016-10-02

[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)]
[Rules and Regulations]
[Pages 29119-29123]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-10931]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0247; Directorate Identifier 2014-NM-178-AD; 
Amendment 39-18513; AD 2016-10-02]
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 and -300 series airplanes equipped 
with Rolls-Royce Trent 800 series engines. This AD was prompted by 
reports of heat damage to the strut aft fairing heat shield primary 
seal, as well as heat and wear damage to the heat shield insulation 
blankets. This AD requires repetitive inspections for cracks and heat 
damage to the strut aft fairing lower spar web structure (a flammable 
fluid zone barrier), for wear to the heat shield primary seal, and, as 
applicable, for heat and wear damage to heat shield insulation 
blankets; and related investigative and corrective actions if 
necessary. This AD also provides optional terminating action for the 
repetitive inspections. We are issuing this AD to detect and correct 
cracks and heat damage to the strut aft fairing lower spar web 
structure (a flammable fluid zone barrier), wear to the heat shield 
primary seal, and heat and wear damage to heat shield insulation 
blankets, which could lead to through-cracks in the aft fairing lower 
web structure and heating of the aft fairing lower web structure, and 
consequent uncontrolled fire in the aft fairing, fuel tank ignition or 
possible departure of the engine.

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

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management,

[[Page 29120]]

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 available on the Internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching and locating Docket No. FAA-2015-
0247.

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-
0247; 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: Kevin Nguyen, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6501; fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#a3c8c6d5cacd8dcdc4d6dac6cde3c5c2c28dc4ccd5"><span class="__cf_email__" data-cfemail="acc7c9dac5c282c2cbd9d5c9c2eccacdcd82cbc3da">[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 and -300 series airplanes equipped with Rolls-Royce Trent 
800 series engines. The NPRM published in the Federal Register on March 
12, 2015 (80 FR 12954) (``the NPRM''). The NPRM was prompted by reports 
of heat damage to the strut aft fairing heat shield primary seal, as 
well as heat and wear damage to the heat shield insulation blankets. 
The NPRM proposed to require repetitive inspections for cracks and heat 
damage to the strut aft fairing lower spar web structure (a flammable 
fluid zone barrier), for wear to the heat shield primary seal, and, as 
applicable, for heat and wear damage to heat shield insulation 
blankets; and related investigative and corrective actions if 
necessary. The NPRM also provided optional terminating action for the 
repetitive inspections. We are issuing this AD to detect and correct 
cracks and heat damage to the strut aft fairing lower spar web 
structure (a flammable fluid zone barrier), wear to the heat shield 
primary seal, and heat and wear damage to heat shield insulation 
blankets, which could lead to through-cracks in the aft fairing lower 
web structure and heating of the aft fairing lower web structure, and 
consequent uncontrolled fire in the aft fairing, fuel tank ignition or 
possible departure of the engine.

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. Marc Philippi stated that he 
supports the NPRM.

Request To Clarify Precipitating Event and Unsafe Condition

    Boeing requested that we revise the SUMMARY and parts of the 
Discussion section of the NPRM to clarify that we received reports of 
heat damage to the strut aft fairing heat shield primary seal as well 
as heat and wear damage to the heat shield insulation blankets. Boeing 
also requested that we revise the SUMMARY of the NPRM and paragraph (e) 
of the proposed AD to clarify that the unsafe condition could lead to 
through-cracks in the aft fairing lower web structure and heating of 
the aft fairing lower web structure. Boeing further requested that we 
revise the Discussion section of the NPRM to indicate that the design 
of the strut aft fairing #1 heat shield (a titanium pan casting) and #1 
heat shield insulation blanket allows hot turbulent gas from the 
exhaust nozzle to cause wear and degradation of the front face of the 
#1 insulation blanket, enter the heat shield cavity (the space or 
cavity between the heat shields and insulation blankets), and contact 
the strut aft fairing lower spar web structure. Boeing additionally 
pointed out that continuous exposure to hot turbulent gas further 
damages the primary seal and #1 insulation blanket, increasing the 
temperature in the heat shield cavity, and causes damage to the 
insulation blankets and lower web structure.
    We agree that the requested changes provide clarity about the 
unsafe condition and consistency to the entire AD, and have revised the 
SUMMARY of this final rule and paragraph (e) of this AD accordingly. 
However, the requested revisions to the Discussion section of the NPRM 
are not included since certain paragraphs of the Discussion section of 
NPRMs are not restated in final rules.

Request To Remove References to the Lower Spar Web Structure as a 
Firewall

    Boeing requested that we remove references to the strut aft fairing 
lower spar web structures as a firewall from the preamble of the NPRM 
and paragraph (e) of the proposed AD. Boeing indicated that the strut 
aft fairing lower spar web structure acts as a flammable fluid zone 
barrier, not a firewall. Boeing pointed out that a fire zone is defined 
as a region where flammable fluid and/or vapor leakage can occur where 
there is an ignition source present. Boeing also pointed out that a 
flammable fluid leakage zone is defined as an area in which flammable 
fluid and/or vapor leakage can occur, but where no ignition sources are 
present, and that since there are no ignition sources present in the 
strut aft fairing cavity, The Boeing Company 777 strut fire protection 
document defines the strut aft fairing cavity as a flammable fluid 
leakage zone.
    We agree with the commenter, and have revised the preamble of this 
final rule and paragraph (e) of this AD accordingly.

Request To Include Information Notice in the Final Rule

    Air New Zealand (ANZ) requested that we revise paragraph (h) of the 
proposed AD to include reference to Boeing Information Notice 777-54-
0030 IN 01, dated April 7, 2015. ANZ pointed out that Boeing 
Information Notice 777-54-0030 IN 01, dated April 7, 2015, includes a 
statement to clarify part interchangeability and part intermixability. 
ANZ also pointed out that Boeing Service Bulletin 777-54-0030, dated 
May 27, 2014, does not include the statement to clarify part 
interchangeability and part intermixability and that the modification 
included in the optional terminating action could therefore potentially 
be removed by installing older design parts as specified in Boeing 
Service Bulletin 777-54A0031, Revision 1, dated May 9, 2014. ANZ noted 
that Boeing Information Notice 777-54-0030 IN 01, dated April 7, 2015, 
is not approved by the FAA or any other regulatory authority.
    We acknowledge that Boeing Information Notice 777-54-0030 IN 01, 
dated April 7, 2015, contains the updated part interchangeability and 
part intermixability restriction statement for certain parts (such as 
insulation blankets). Boeing has issued Boeing Service Bulletin 777-54-
0030, Revision

[[Page 29121]]

1, dated September 30, 2015, which contains the information specified 
in Boeing Information Notice 777-54-0030 IN 01, dated April 7, 2015. 
Once an airplane has been modified as specified in Boeing Service 
Bulletin 777-54-0030, dated May 27, 2014, or Boeing Service Bulletin 
777-54-0030, Revision 1, dated September 30, 2015 (optional terminating 
action of installing redesigned or newer insulation blankets, and other 
associated parts), and the operator has shown compliance with paragraph 
(h)(1) of this AD, the modification cannot be removed without 
requesting approval of an Alternative Method of Compliance (AMOC). Any 
change to install the older design parts would invalidate the 
terminating action accomplished as specified in Boeing Service Bulletin 
777-54-0030, dated May 27, 2014, or Boeing Service Bulletin 777-54-
0030, Revision 1, dated September 30, 2015.
    Therefore, we have revised paragraph (h)(1) of this AD to refer to 
Boeing Service Bulletin 777-54-0030, Revision 1, dated September 30, 
2015, and provided credit for actions accomplished using Boeing Service 
Bulletin 777-54-0030, dated May 27, 2014, in paragraph (j)(2) of this 
AD.
    ANZ stated that they believe the AMOC statement in the impending 
Airworthiness Notice should include Boeing Information Notice 777-54-
0030 IN 01, dated April 7, 2015. We infer that ANZ is requesting an 
AMOC for that information notice.
    We disagree with giving AMOC approval for Boeing Information Notice 
777-54-0030 IN 01, dated April 7, 2015, because we are requiring Boeing 
Service Bulletin 777-54-0030, Revision 1, dated September 30, 2015, 
that already includes the information contained in Boeing Information 
Notice 777-54-0030 IN 01, dated April 7, 2015.

Request for Revised Service Information and Credit

    ANZ requested that we revise paragraph (j) of the proposed AD to 
include credit for actions accomplished as specified in Boeing Service 
Bulletin 777-54-0030, dated May 27, 2014. ANZ pointed out that they 
have accomplished the actions required by paragraph (h)(1) of the 
proposed AD, on multiple 777-200 airplanes in their fleet, as specified 
in Boeing Service Bulletin 777-54-0030, dated May 27, 2014. ANZ also 
stated that they believe that credit for accomplishing the actions 
required by paragraph (h)(1) of the proposed AD, as specified in Boeing 
Service Bulletin 777-54-0030, dated May 27, 2014, should be added to 
paragraph (j) of the proposed AD.
    We agree with the request to include actions accomplished as 
specified in Boeing Service Bulletin 777-54-0030, dated May 27, 2014, 
in paragraph (j) of this AD. Therefore, as stated previously, we have 
revised this final rule to provide credit for actions accomplished 
using Boeing Service Bulletin 777-54-0030, dated May 27, 2014, in 
paragraph (j)(2) of this AD.

Request To Correct a Typographical Error

    Boeing requested that we correct a typographical error by inserting 
missing dollar signs in the Cost of Compliance column of the On-
Condition Costs table.
    We agree and have revised this final rule to include the missing 
information.

Clarification of Actions

    Boeing issued Information Notice 777-54A0031 IN 01, dated September 
24, 2015, to clarify access information when removing and installing 
pan casting number 6. Information Notice 777-54A0031 IN 01, dated 
September 24, 2015, specifies that when removing pan casting number 6 
in FIGURE 9 and FIGURE 10 of Boeing Service Bulletin 777-54A0031, 
Revision 1, dated May 9, 2014, it is acceptable to remove and keep the 
bracket attached to the drain lines or remove the P-clamps for access. 
We refer to Boeing Service Bulletin 777-54A0031, Revision 1, dated May 
9, 2014, as the appropriate source of service information for 
accomplishing the actions required by paragraph (g) of this AD. Note 12 
in Paragraph 3.A., ``General Information,'' of Boeing Alert Service 
Bulletin 777-54A0031, dated June 7, 2013; and Revision 1, dated May 9, 
2014; contains statements informing and permitting removal of more 
parts for access when necessary. Also, operators may have been 
performing these same or similar access steps when removing pan casting 
number 6. Thus, the clarification in the information notice is neither 
new nor additional work. Further, this clarification of access 
information is already included in Boeing Service Bulletin 777-54-0030, 
Revision 1, dated September 30, 2015, which is the appropriate source 
of service information for accomplishing the actions required by 
paragraph (h)(1) of this AD. Therefore, we have determined it is not 
necessary to include reference to Information Notice 777-54A0031 IN 01, 
dated September 24, 2015, in the regulatory text of this AD.

Clarification of Credit

    Although the Accomplishment Instructions of Boeing Alert Service 
Bulletin 777-54A0031, dated June 7, 2013, correctly show all nine 
insulation blankets for doing the actions, paragraph 2., ``Material 
Information'' only lists eight insulation blankets and is missing part 
number 313W5421-29. Therefore, we have clarified paragraph (j)(1) of 
this AD to specify that credit for previous actions are acceptable, 
provided that insulation blanket part number 313W5421-29 is inspected 
and reinstalled, or replaced with a new insulation blanket; as 
applicable, as specified in the Accomplishment Instructions of Boeing 
Alert Service Bulletin 777-54A0031, dated June 7, 2013.

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 the following service information:
    <bullet> Boeing Service Bulletin 777-54A0031, Revision 1, dated May 
9, 2014.
    <bullet> Boeing Service Bulletin 777-54-0030, Revision 1, dated 
September 30, 2015.
    The service information describes procedures for repetitive 
inspections for heat damage to the strut aft fairing lower spar web 
structure (a flammable fluid zone barrier) and heat shield primary 
seal, and heat and wear damage to heat shield insulation blankets; and 
related investigative and 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 57 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 29122]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                     Labor cost           Parts cost     Cost per product       operators
----------------------------------------------------------------------------------------------------------------
Inspections....................  40 work-hours x $85 per              $0   $3,400 per          $193,800 per
                                  hour = $3,400 per                         inspection cycle.   inspection cycle
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                 Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Heat shield primary seal replacement.....  10 work-hours x $85 per hour = $850..          $1,940          $2,790
Cracked or damaged parts replacement.....  110 work-hours x $85 per hour =               $52,992         $62,342
                                            $9,350.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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):

2016-10-02 The Boeing Company: Amendment 39-18513; Docket No. FAA-
2015-0247; Directorate Identifier 2014-NM-178-AD.

(a) Effective Date

    This AD is effective June 15, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes equipped with Rolls-Royce Trent 800 series engines, 
certificated in any category, as identified in Boeing Service 
Bulletin 777-54A0031, Revision 1, dated May 9, 2014.

 (d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.

 (e) Unsafe Condition

    This AD was prompted by reports of heat damage to the strut aft 
fairing heat shield primary seal, as well as heat and wear damage to 
the heat shield insulation blankets. We are issuing this AD to 
detect and correct cracks and heat damage to the strut aft fairing 
lower spar web structure (a flammable fluid zone barrier), wear to 
the heat shield primary seal, and heat and wear damage to heat 
shield insulation blankets, which could lead to through-cracks in 
the aft fairing lower web structure and heating of the aft fairing 
lower web structure, and consequent uncontrolled fire in the aft 
fairing, fuel tank ignition or possible departure of the engine.

 (f) Compliance

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

 (g) Repetitive Inspections

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 777-54A0031, Revision 1, 
dated May 9, 2014, except as required by paragraph (i) of this AD: 
Do the inspections specified in paragraphs (g)(1), (g)(2), and 
(g)(3) of this AD, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0031, Revision 1, 
dated May 9, 2014. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspections 
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 777-54A0031, Revision 1, dated May 9, 2014.
    (1) Do a detailed inspection for cracks and heat damage of the 
aft fairing lower spar upper surface.
    (2) Do a conductivity inspection for heat damage of the aft 
fairing lower spar upper surface.
    (3) Do a detailed inspection for wear of the heat shield primary 
seal.

[[Page 29123]]

 (h) Optional Terminating Action

    The concurrent accomplishment of the actions specified in 
paragraphs (h)(1) and (h)(2) of this AD terminates the requirements 
of paragraph (g) of this AD.
    (1) Replacement of all heat shield insulation blankets (rub 
strips, heat shield pan casting, Velcro strips, aft fairing web 
drain sump, drain screen, and drain tubes, as applicable) in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 777-54-0030, Revision 1, dated September 30, 2015.
    (2) A one-time detailed inspection for cracks and heat damage of 
the aft fairing lower spar upper surface, conductivity inspection 
for heat damage of the aft fairing lower spar upper surface, and 
detailed inspection for wear of heat shield primary seal, and all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 777-54A0031, Revision 1, dated May 9, 2014, provided all 
applicable related investigative and corrective actions are done 
before further flight.

 (i) Exception to Service Information Specifications

    Where Boeing Service Bulletin 777-54A0031, Revision 1, dated May 
9, 2014, specifies a compliance time ``After the Original Issue Date 
of this Service Bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.

 (j) Credit for Previous Actions

    (1) This paragraph provides credit for the actions specified in 
paragraphs (g)(1), (g)(2), (g)(3), and (h)(2) of this AD, if those 
actions were performed before the effective date of this AD using 
Boeing Alert Service Bulletin 777-54A0031, dated June 7, 2013, 
provided that insulation blanket part number 313W5421-29 is 
inspected and reinstalled, or replaced with a new insulation 
blanket, as applicable, as specified in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-54A0031, dated 
June 7, 2013. This service information is not incorporated by 
reference in this AD.
    (2) This paragraph provides credit for the actions specified in 
paragraph (h)(1) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 777-54-
0030, dated May 27, 2014. This service information is not 
incorporated by reference in this AD.

 (k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (l)(1) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#1c25315d5251314f797d68687079315d5f53315d51535f314e796d69796f686f5c7a7d7d327b736a"><span class="__cf_email__" data-cfemail="320b1f737c7f1f61575346465e571f73717d1f737f7d711f6057434757414641725453531c555d44">[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 required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle 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.

 (l) Related Information

    (1) For more information about this AD, contact Kevin Nguyen, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6501; 
fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#99f2fceff0f7b7f7feece0fcf7d9fff8f8b7fef6ef"><span class="__cf_email__" data-cfemail="b4dfd1c2ddda9adad3c1cdd1daf4d2d5d59ad3dbc2">[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 Service Bulletin 777-54A0031, Revision 1, dated May 
9, 2014.
    (ii) Boeing Service Bulletin 777-54-0030, Revision 1, dated 
September 30, 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 April 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10931 Filed 5-10-16; 8:45 am]
 BILLING CODE 4910-13-P