AD 2017-11-14

[Federal Register Volume 82, Number 107 (Tuesday, June 6, 2017)]
[Rules and Regulations]
[Pages 25954-25958]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-11291]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8179; Directorate Identifier 2015-NM-201-AD; 
Amendment 39-18913; AD 2017-11-14]
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) 2011-26-03, 
which applied to certain The Boeing Company Model 777-200, -200LR, -
300, and -300ER series airplanes. AD 2011-26-03 required installing 
Teflon sleeving under the clamps of certain wire bundles routed along 
the fuel tank boundary structure, and cap sealing certain penetrating 
fasteners of the main and center fuel tanks. This AD requires certain 
inspections for certain airplanes, corrective actions if necessary, and 
installation of Teflon sleeves under certain wire bundle clamps. This 
AD was prompted by a report indicating that additional airplanes are 
affected by the identified unsafe condition. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective July 11, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 11, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
20, 2011 (75 FR 78588, December 16, 2010).

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone: 562-797-1717; 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="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
8179.

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-2016-
8179; 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: Tak Kobayashi, Aerospace Engineer, 
Propulsion Branch, ANM-140S, Seattle Aircraft Certification Office 
(ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6499; fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#c7b3a6aca6afaeb4a6e9aca8a5a6bea6b4afae87a1a6a6e9a0a8b1"><span class="__cf_email__" data-cfemail="d0a4b1bbb1b8b9a3b1febbbfb2b1a9b1a3b8b990b6b1b1feb7bfa6">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-26-03, Amendment 39-16893 (76 FR 78138, 
December 16, 2011) (``AD 2011-26-03''). AD 2011-26-03 applied to 
certain The Boeing Company Model 777-200, -200LR, -300, and -300ER 
series airplanes. The NPRM published in the Federal Register on July 
20, 2016 (81 FR 47084). The NPRM was prompted by a report indicating 
that additional airplanes are affected by the identified unsafe 
condition. The NPRM proposed to continue to require installing Teflon 
sleeving under the clamps of certain wire bundles routed along the fuel 
tank boundary structure, and cap sealing certain penetrating fasteners 
of the main and center fuel tanks. The NPRM also proposed to revise the 
applicability by adding The Boeing Company Model 777F series airplanes. 
The NPRM also proposed to add, for certain airplanes, detailed 
inspections of certain wire bundle clamps, certain Teflon sleeves, and 
certain fasteners; corrective actions if necessary; and installation of 
Teflon sleeves under certain wire bundle clamps. We are issuing this AD 
to prevent arcing inside the main and center fuel tanks in the event of 
a fault current or lightning strike, which, in combination with 
flammable fuel vapors, could result in a fuel tank explosion 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 and 
the FAA's response to each comment.

Request To Withdraw the NPRM

    Boeing requested that we withdraw the NPRM. The commenter stated 
that the actions proposed by the NPRM are no longer necessary, since 
the unsafe condition is adequately addressed by repetitive inspections 
required by the electrical wiring interconnection system (EWIS) 
enhanced zonal analysis procedure (EZAP) inspection program required by 
14 CFR part 26. The commenter pointed out that, since the time this 
issue was determined to be a safety issue, the exposure assumed under 
the safety assessment has changed due to the inspection program. The 
commenter stated that the safety concern was that the failure of 
multiple protective design features for wiring installations could be a 
single cascading failure since the exposure was the life of the 
airplane. The commenter stated that since the implementation of the 
EWIS EZAP inspections, where the interval is now 6 years, this is no 
longer considered to be a single failure as the exposure has been 
reduced to where the wiring and installation is not expected to fail in 
this inspection interval and any potential wear would be detected and 
would be repaired or removed and replaced in accordance with 
maintenance activities.
    We disagree to withdraw the NPRM. The EWIS EZAP repetitive 
inspection program is implemented by FAA operating rules (14 CFR 
121.1111 or 14 CFR 129.111), which are applicable only to operators 
that are required to comply with those operating rules. The FAA is 
obligated to advise foreign airworthiness authorities of unsafe 
conditions identified in products manufactured in the United States, 
including Boeing airplanes, in accordance with bilateral airworthiness 
agreements with countries around the world. The issuance of ADs is the 
means by which the FAA satisfies this obligation. Even if the FAA 
agreed that the actions required by 14 CFR 121.1111 and 14 CFR 129.111 
adequately addressed the unsafe condition, the FAA would still issue 
this AD to address airplanes that may

[[Page 25955]]

not be operated in accordance with those requirements. Additionally, 
the FAA does not agree that the EWIS EZAP repetitive inspection program 
has been demonstrated as sufficient to allow a determination that 
chafing through the wire insulation of the unmodified (pre-AD) 
configuration is not a foreseeable single failure. The FAA understands 
that the EWIS EZAP repetitive inspection program interval for this area 
was determined based on a later modified design, and that design has 
additional Teflon sleeving. For these reasons, we have made no change 
to this final rule in this regard.

Request for Clarification of Safety Evaluation Criteria

    Boeing requested that we clarify the use of ``unacceptable 
(failure) experience'' in the Discussion section of the NPRM and that 
was used as a safety evaluation criterion under Special Federal 
Aviation Regulation No. 88 (SFAR 88). The commenter requested better 
definition of ``unacceptable (failure) experience'' or the addition of 
detailed guidance that defines how to identify an ``unacceptable 
(failure) experience.'' The commenter also indicated that Boeing 
airplanes at the time of design approval are intended to meet all 
applicable regulations including 14 CFR 25.601, which specifically 
prohibits hazardous or unreliable features.
    We agree that clarification is necessary. To provide standardized 
policy for determining the need for mandatory action relative to the 
finding from the fuel system safety review required by SFAR 88, the FAA 
issued Memorandum 2003-112-15, SFAR 88--Mandatory Action Decision 
Criteria, dated February 25, 2003. One of the criteria provided in the 
policy memo is that, for any tank (either high or low flammability 
exposure time), all failures identified in service, that result in 
thermal or electrical energy dissipation into the fuel tank system, 
which could create an ignition hazard, or that make fuel tank safety 
protection devices inoperative (e.g., fuel pump canister, wire 
sleeving, bonding lead), are considered unsafe conditions and must be 
addressed by corrective action (i.e., AD). This criterion is 
independent of any compliance showing or finding previously made as 
part of a type certification program. The policy memo criteria are 
mentioned in the Discussion section of each NPRM that resulted from an 
SFAR 88 unsafe condition determination. Additionally, the NPRM 
Discussion is not repeated in the final rule, so no change to this 
final rule is necessary in this regard.

Request for Clarification of Credit for Actions Accomplished Previously

    Boeing requested that we revise paragraph (l) of the proposed AD so 
that it is clear that credit will be given for past work that has 
already been accomplished on other Boeing Model 777 airplanes. No 
justification was provided, however, the commenter stated that the NPRM 
is adding the missing airplanes and it uses the latest service 
information to reset the method of compliance.
    We infer that the commenter is requesting clarification for taking 
credit for actions required by paragraph (g)(l) of this AD using 
earlier revisions of the service information. Paragraph (l)(1) of this 
AD provides credit for actions accomplished before January 20, 2011 
(the effective date of AD 2010-24-12, Amendment 39-16531 (75 FR 78588, 
December 16, 2010) (``AD 2010-24-12'')), using service information 
revisions earlier than Boeing Service Bulletin 777-57A0050, Revision 2, 
dated May 14, 2009, required by paragraph (g)(1) of AD 2010-24-12. 
Accomplishing the actions using Boeing Service Bulletin 777-57A0050, 
Revision 3, dated February 18, 2014, has been approved as an 
alternative method of compliance (AMOC) for paragraph (g)(l) of AD 
2011-26-03, and AMOCs approved previously for AD 2011-26-03 are 
approved as AMOCs for the corresponding provisions of this AD as 
specified in paragraph (m)(4) of this AD. After the effective date of 
this AD, only Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015 is allowed for compliance with paragraph (g)(l) of 
this AD. Paragraphs (i) and (j) of this AD require actions for 
airplanes not covered in paragraph (g)(l) of this AD and also require 
additional actions for those airplanes that accomplished the actions 
required by paragraph (g)(l) of this AD using service bulletin 
revisions earlier than Boeing Service Bulletin 777-57A0050, Revision 4, 
dated September 28, 2015. Therefore, no credit is provided for actions 
required by paragraphs (i) and (j) of this AD using service bulletin 
revisions earlier than Boeing Service Bulletin 777-57A0050, Revision 4, 
dated September 28, 2015. We have not changed this AD in this regard.

Request To Simplify Compliance Implementation Time Frame

    Boeing requested that we revise paragraphs (i), (j), and (k) of the 
proposed AD to simplify the AD compliance implementation time frame. 
The commenter stated that the NPRM sets the requirements to be 
completed within 60 months of different revisions of different 
documents with an exception specified in paragraph (k) of the proposed 
AD, and that the proposed requirements were cumbersome and unclear. The 
commenter did not provide any explanation of how the paragraphs should 
be revised.
    We agree that clarification is necessary. The NPRM proposed to 
supersede AD 2011-26-03 and added new requirements in paragraphs (i) 
and (j) of this AD. Paragraph (k) of this AD provides exceptions to the 
service information. For the new requirements in this AD, the FAA has 
determined that the compliance times are reasonable based on 
consideration of the risk level associated with the unsafe condition 
and the time necessary to perform the work. In addition, the compliance 
times in paragraphs (i) and (j) of this AD do not refer to any service 
documents (both paragraphs refer to Boeing Service Bulletin 777-
57A0050, Revision 4, dated September 28, 2015, as the appropriate 
source of service information for accomplishing the actions in those 
paragraphs). Therefore, we have determined that the requirements of 
this AD are adequate and clear. We have not changed this AD in this 
regard.

Clarification of Service Information Requirement

    Under the ``Differences Between This Proposed AD and the Service 
Information'' section of the NPRM, we noted that the corrections to 
group applicability for ``WORK PACKAGE 21: More Work: Rear Spar Wire 
Bundle Teflon Sleeve Installation,'' Figure 3, and Figure 100 of Boeing 
Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, 
were included in paragraphs (k)(1), (k)(2), and (k)(3) of the proposed 
AD. Paragraph (k)(1) of this AD specifies that WORK PACKAGE 21 applies 
to Groups 5 through 43 (including Configurations 1 and 2) to correct 
the error in Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015, which only identifies Configuration 2 of Groups 5 
through 43 as applicable. Paragraph (k)(1) of this AD, which is 
referenced by paragraph (j) of this AD, is intended to clarify the 
airplanes affected by the requirements specified in paragraph (j) of 
this AD. To further clarify this aspect, we have revised paragraph (j) 
of this AD to specifically reference Groups 5 through 43, 
Configurations 1 and 2 airplanes.
    We have also revised paragraph (m)(4) of this AD to accept AMOCs 
approved previously for AD 2010-24-12 as

[[Page 25956]]

AMOCs for the corresponding provisions of this AD.

Clarification of Unsafe Condition

    We have revised the Discussion section of this final rule and 
paragraph (e) of this AD to clarify that we are issuing this AD to 
address arcing inside the main and center fuel tanks in the event of a 
fault current or lightning strike, which, in combination with flammable 
fuel vapors, could result in a fuel tank explosion and consequent loss 
of the airplane.

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.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015. The service information describes procedures for 
installing Teflon sleeving under the clamps of certain wire bundles 
routed along the fuel tank boundary structure, and cap sealing certain 
penetrating fasteners of the main and center fuel tanks. The service 
information also describes detailed inspections of certain wire bundle 
clamps, certain Teflon sleeves, and certain fasteners; corrective 
actions if necessary; and installation of Teflon sleeves under certain 
wire bundle clamps. 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 182 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
             Action                  Labor cost       Parts cost     Cost per  product   Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Install Teflon sleeving and cap  Up to 358 work-            $2,241  Up to $32,671......  Up to $5,946,122.
 sealing (retained actions from   hours x $85 per
 AD 2011-26-03).                  hour = $30,430.
Detailed inspections and         Up to 53 work-              (\1\)  Up to $4,505.......  Up to $819,910.
 installation of Teflon sleeves   hours x $85 per
 (new actions).                   hour = $4,505.
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide parts cost estimates for the
  installation of Teflon sleeves (new action) specified in this AD.

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified 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

    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

0
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) 
2011-26-03, Amendment 39-16893 (76 FR 78138, December 16, 2011), and 
adding the following new AD:

2017-11-14 The Boeing Company: Amendment 39-18913; Docket No. FAA-
2016-8179; Directorate Identifier 2015-NM-201-AD.

(a) Effective Date

    This AD is effective July 11, 2017.

(b) Affected ADs

    This AD replaces AD 2011-26-03, Amendment 39-16893 (76 FR 78138, 
December 16, 2011) (``AD 2011-26-03'').

(c) Applicability

    This AD applies to The Boeing Company airplanes, certificated in 
any category, as identified in the applicable service information 
specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this 
AD.
    (1) For The Boeing Company Model 777-200, -200LR, -300, -300ER, 
and 777F airplanes: Boeing Service Bulletin 777-57A0050, Revision 4, 
dated September 28, 2015.
    (2) For The Boeing Company Model 777-200 and -300 airplanes: 
Boeing Alert Service Bulletin 777-57A0051, dated May 15, 2006.
    (3) For The Boeing Company Model 777-200, -300, and -300ER 
airplanes: Boeing Alert Service Bulletin 777-57A0057, Revision 1, 
dated August 2, 2007.
    (4) For The Boeing Company Model 777-200, -200LR, -300, and -
300ER airplanes:

[[Page 25957]]

Boeing Alert Service Bulletin 777-57A0059, dated October 30, 2008.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent arcing inside the 
main and center fuel tanks in the event of a fault current or 
lightning strike, which, in combination with flammable fuel vapors, 
could result in a fuel tank explosion and consequent loss of the 
airplane.

(f) Compliance

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

(g) Retained Corrective Actions (Installing Teflon Sleeving, Cap 
Sealing, One-Time Inspection), With Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2011-26-03, with revised service information. Within 60 months after 
January 20, 2011 (the effective date of AD 2010-24-12, Amendment 39-
16531 (75 FR 78588, December 16, 2010) (``AD 2010-24-12'')), do the 
applicable actions specified in paragraph (g)(1), (g)(2), (g)(3), or 
(g)(4) of this AD, except as required by paragraph (k)(2) of this 
AD.
    (1) For airplanes identified in Boeing Service Bulletin 777-
57A0050, Revision 2, dated May 14, 2009: Install Teflon sleeving 
under the clamps of certain wire bundles routed along the fuel tank 
boundary structure, and cap seal certain penetrating fasteners of 
the fuel tanks, in accordance with the Accomplishment Instructions 
of Boeing Service Bulletin 777-57A0050, Revision 2, dated May 14, 
2009; or Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015. As of the effective date of this AD, only Boeing 
Service Bulletin 777-57A0050, Revision 4, dated September 28, 2015, 
may be used to accomplish the actions required by this paragraph.
    (2) For airplanes identified in Boeing Alert Service Bulletin 
777-57A0051, dated May 15, 2006: Cap seal certain penetrating 
fasteners of the fuel tanks, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-57A0051, dated May 
15, 2006.
    (3) For airplanes identified in Boeing Alert Service Bulletin 
777-57A0057, Revision 1, dated August 2, 2007: Do a general visual 
inspection to determine if certain fasteners are cap sealed, and do 
all applicable corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
57A0057, Revision 1, dated August 2, 2007. Do all applicable 
corrective actions before further flight.
    (4) For Model 777-200, -300, and -300ER airplanes identified in 
Boeing Alert Service Bulletin 777-57A0059, dated October 30, 2008: 
Cap seal the fasteners in the center fuel tanks that were not sealed 
during production, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-57A0059, dated 
October 30, 2008.

(h) Retained Cap Sealing the Fasteners, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2011-26-03, with no changes. For Model 777-200LR airplanes 
identified in Boeing Alert Service Bulletin 777-57A0059, dated 
October 30, 2008: Within 60 months after January 3, 2012 (the 
effective date of AD 2011-26-03), cap seal the fasteners in the 
center fuel tanks that were not sealed during production, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 777-57A0059, dated October 30, 2008.

(i) New Detailed Inspection and Corrective Actions

    For Group 1, Configurations 2 through 4 airplanes; Groups 2 
through 4, Configurations 3 through 5 airplanes; Groups 5 through 
43, Configuration 1 airplanes; and Groups 44 and 45 airplanes; as 
identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015: Within 60 months after the effective date of 
this AD, do the applicable actions specified in paragraphs (i)(1), 
(i)(2), and (i)(3) of this AD, except as required by paragraph 
(k)(2) of this AD.
    (1) For Group 1, Configurations 2 through 4 airplanes; Groups 2 
through 4, Configurations 3 through 5 airplanes; Groups 5 through 
43, Configuration 1 airplanes; and Groups 44 and 45 airplanes; as 
identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015: Do a detailed inspection for installation of 
Teflon sleeves under certain wire bundle clamps, as applicable; a 
detailed inspection to determine the type of wire bundle clamp; and 
all applicable corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 777-57A0050, 
Revision 4, dated September 28, 2015. Do all applicable corrective 
actions before further flight.
    (2) For Group 1, Configurations 2 through 4 airplanes; and 
Groups 2 through 4, Configurations 3 through 5 airplanes; as 
identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015: Do a detailed inspection for correct 
installation of certain Teflon sleeves, as applicable; and do all 
applicable corrective actions; in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 777-57A0050, Revision 4, 
dated September 28, 2015. Do all applicable corrective actions 
before further flight.
    (3) For Group 1, Configurations 2 through 4 airplanes; and 
Groups 2 through 4, Configurations 3 through 5 airplanes; as 
identified in Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015: Do a detailed inspection for cap sealing of 
certain fasteners, as applicable; and do all applicable corrective 
actions; in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 
2015. Do all applicable corrective actions before further flight.

(j) New Installation of Teflon Sleeves

    For Group 1, Configurations 2 through 5 airplanes; Groups 2 
through 4, Configurations 3 through 6 airplanes; and Groups 5 
through 43, Configurations 1 and 2 airplanes; as identified in 
Boeing Service Bulletin 777-57A0050, Revision 4, dated September 28, 
2015: Within 60 months after the effective date of this AD, install 
Teflon sleeves under certain wire bundle clamps, as applicable, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 777-57A0050, Revision 4, dated September 28, 2015, except 
as required by paragraphs (k)(1), (k)(2), and (k)(3) of this AD.

(k) Exceptions to the Service Information

    (1) Where ``WORK PACKAGE 21: More Work: Rear Spar Wire Bundle 
Teflon sleeve Installation'' of Boeing Service Bulletin 777-57A0050, 
Revision 4, dated September 28, 2015, specifies ``Groups 5 through 
43, Configuration 2,'' for this AD, ``WORK PACKAGE 21: More Work: 
Rear Spar Wire Bundle Teflon sleeve Installation'' of Boeing Service 
Bulletin 777-57A0050, Revision 4, dated September 28, 2015, applies 
to all configurations of Groups 5 through 43 airplanes.
    (2) Where Figure 3 of Boeing Service Bulletin 777-57A0050, 
Revision 4, dated September 28, 2015, specifies ``Groups 1 through 
7, and 9 through 43,'' for this AD, Figure 3 of Boeing Service 
Bulletin 777-57A0050, Revision 4, dated September 28, 2015, applies 
to Groups 1 through 43 airplanes.
    (3) Where Figure 100 of Boeing Service Bulletin 777-57A0050, 
Revision 4, dated September 28, 2015, specifies ``Groups 5 through 
43, Configuration 2,'' for this AD, Figure 100 of Boeing Service 
Bulletin 777-57A0050, Revision 4, dated September 28, 2015, applies 
to all configurations of Groups 5 through 43 airplanes.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for the actions specified in 
paragraph (g)(1) of this AD, if those actions were performed before 
January 20, 2011 (the effective date of AD 2010-24-12), using Boeing 
Alert Service Bulletin 777-57A0050, dated January 26, 2006; or 
Boeing Alert Service Bulletin 777-57A0050, Revision 1, dated August 
2, 2007; provided that the applicable additional work specified in 
Boeing Service Bulletin 777-57A0050, Revision 2, dated May 14, 2009, 
is done within the compliance time specified in paragraph (g) of 
this AD. The additional work must be done in accordance with Boeing 
Service Bulletin 777-57A0050, Revision 2, dated May 14, 2009.
    (2) This paragraph provides credit for the actions specified in 
paragraph (g)(3) of this AD, if those actions were performed before 
January 20, 2011 (the effective date of AD 2010-24-12), using Boeing 
Alert Service Bulletin 777-57A0057, dated August 7, 2006.

(m) 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

[[Page 25958]]

attention of the person identified in paragraph (n)(1) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#774e5a36393a5a24121603031b125a3634385a363a38345a25120602120403043711161659101801"><span class="__cf_email__" data-cfemail="a69f8be7e8eb8bf5c3c7d2d2cac38be7e5e98be7ebe9e58bf4c3d7d3c3d5d2d5e6c0c7c788c1c9d0">[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 Organization 
Designation Authorization (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.
    (4) AMOCs approved previously for AD 2011-26-03 and AD 2010-24-
12 are approved as AMOCs for the corresponding provisions of this 
AD.

(n) Related Information

    (1) For more information about this AD, contact Tak Kobayashi, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6499; 
fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#b0c4d1dbd1d8d9c3d19edbdfd2d1c9d1c3d8d9f0d6d1d19ed7dfc6"><span class="__cf_email__" data-cfemail="a2d6c3c9c3cacbd1c38cc9cdc0c3dbc3d1cacbe2c4c3c38cc5cdd4">[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 (o)(5) and (o)(6) of this AD.

(o) 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.
    (3) The following service information was approved for IBR on 
July 11, 2017.
    (i) Boeing Service Bulletin 777-57A0050, Revision 4, dated 
September 28, 2015.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
January 20, 2011 (75 FR 78588, December 16, 2010).
    (i) Boeing Alert Service Bulletin 777-57A0051, dated May 15, 
2006.
    (ii) Boeing Alert Service Bulletin 777-57A0057, Revision 1, 
dated August 2, 2007.
    (iii) Boeing Alert Service Bulletin 777-57A0059, dated October 
30, 2008.
    (iv) Boeing Service Bulletin 777-57A0050, Revision 2, dated May 
14, 2009.
    (5) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone: 562-797-1717; Internet: <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (6) You may view this 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.
    (7) 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 May 23, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-11291 Filed 6-5-17; 8:45 am]
 BILLING CODE 4910-13-P