Document ID: FAA-2017-0246-0009
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2018-12-14T05:00Z

[Federal Register Volume 83, Number 240 (Friday, December 14, 2018)]
[Rules and Regulations]
[Pages 64233-64239]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-26532]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0246; Product Identifier 2017-NM-011-AD; Amendment 
39-19522; AD 2018-25-11]
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 Model RB211-Trent 800 engines. This AD was prompted by 
reports of inadequate clearance between the thermal protection system 
(TPS) insulation blankets and the electronic engine control (EEC) 
wiring, which resulted in damaged wires. This AD requires repetitive 
inspections of the EEC wire bundles and clips, and corrective actions 
if necessary. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective January 18, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 18, 
2019.

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 https://www.myboeingfleet.com. You may view this service information at the 
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, call 
206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0246.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0246; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other

[[Page 64234]]

information. The address for Docket Operations (phone: 800-647-5527) is 
Docket Operations, 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 Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des 
Moines, WA 98198; phone and fax: 206-231-3555; email: 
kevin.nguyen@faa.gov.

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 Model 
RB211-Trent 800 engines. The NPRM published in the Federal Register on 
April 10, 2017 (82 FR 17154). The NPRM was prompted by reports of 
inadequate clearance between the TPS insulation blankets and the EEC 
wiring, which resulted in damaged wires. The NPRM proposed to require 
repetitive inspections of the EEC wire bundles and clips, and 
corrective actions if necessary.
    We are issuing this AD to address damaged wires, which could result 
in in-flight shutdown of the engine, or the inability to properly 
control thrust, and consequent reduced controllability of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment.

Support for the Proposed Rule

    The Air Line Pilots Association, International (ALPA), Boeing, and 
Rolls-Royce all supported the NPRM.

Request To Include Additional Service Information

    Air New Zealand (ANZ) suggested that paragraph (g) of the proposed 
AD could be complied with using either Boeing Special Attention Service 
Bulletin 777-78-0071; or Boeing Service Bulletin 777-78-0082; because 
certain configurations of thrust reversers (T/Rs) are not covered by 
Boeing Service Bulletin 777-78-0082, but are covered by Boeing Special 
Attention Service Bulletin 777-78-0071. ANZ noted that paragraph (h) of 
the proposed AD provided credit for previous actions if the previous 
inspections were performed in accordance with either Boeing Special 
Attention Service Bulletin 777-78-0071; or Boeing Service Bulletin 777-
78-0082.
    American Airlines (AAL) explained that Boeing Service Bulletin 777-
78-0082, Revision 1, dated June 15, 2015, is not effective to its fleet 
configuration and requested that paragraph (g) of the proposed AD be 
revised to include Boeing Special Attention Service Bulletin 777-78-
0071, Revision 2, dated July 23, 2013, as an additional method of 
compliance for those airplanes that are identified in Boeing Special 
Attention Service Bulletin 777-78-0071, Revision 2, dated July 23, 
2013, but not affected by Boeing Service Bulletin 777-78-0082, Revision 
1, dated June 15, 2015. AAL also provided the definitions for a general 
visual inspection and detailed inspection from Boeing Special Attention 
Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013, to 
support its justification that a general visual inspection would 
identify damage to components within the inspection area identified in 
the service information and therefore offers an equivalent level of 
safety to that of a detailed inspection.
    Delta Air Lines (DAL) explained that Boeing Service Bulletin 777-
78-0082, Revision 1, dated June 15, 2015, is not applicable to all the 
T/Rs affected by the proposed AD, and suggested that paragraph (g) of 
the proposed AD follow the same structure as AD 2016-11-16, Amendment 
39-18543 (81 FR 39547, June 17, 2016) (``AD 2016-11-16''), which allows 
for the use of Boeing Special Attention Service Bulletin 777-78-0071, 
Revision 2, dated July 23, 2013, in paragraph (k)(1) of AD 2016-11-16 
or Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 
2015, in paragraph (k)(2) of AD 2016-11-16, according to airplane 
effectivity. DAL observed that the referenced service information was 
acknowledged in AD 2016-11-16 to provide the same acceptable level of 
safety, and DAL would prefer that either service bulletin be allowed as 
an acceptable method of compliance for the inspections required by 
paragraph (g) of this AD.
    We do not agree with the commenter's request to include additional 
service information as an additional method of compliance for the 
inspections required by paragraph (g) of this AD. Boeing Special 
Attention Service Bulletin 777-78-0071, Revision 2, dated July 23, 
2013; and Boeing Service Bulletin 777-78-0082, dated November 9, 2011; 
do not provide inspection requirements for engine configurations that 
have incorporated Rolls-Royce Service Bulletin RR.211-71-H824, dated 
July 30, 2014. Only Boeing Service Bulletin 777-78-0082, Revision 1, 
dated June 15, 2015, contains detailed inspection requirements and 
instructions that are applicable to engine configurations that either 
have or have not incorporated Rolls-Royce Service Bulletin RR.211-71-
H824, dated July 30, 2014. As a result, the EEC wire bundle inspections 
specified by Boeing Service Bulletin 777-78-0082, Revision 1, dated 
June 15, 2015, are applicable to the ANZ, AAL, and DAL fleet 
configurations that are identified in Boeing Special Attention Service 
Bulletin 777-78-0071, Revision 2, dated July 23, 2013.
    Consistent with the requirements of paragraph (k) of AD 2016-11-16, 
we determined that a general visual inspection as specified in Boeing 
Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 
23, 2013; and Boeing Service Bulletin 777-78-0082, dated November 9, 
2011; accomplished prior to the effective date of this AD is acceptable 
when looking for damage of the EEC wire bundle and clips. On or after 
the effective date of this AD, a detailed inspection is required as 
specified in Boeing Service Bulletin 777-78-0082, Revision 1, dated 
June 15, 2015. We have not changed the AD in this regard.

Request To Clarify Paragraph (c) Applicability of the Proposed AD

    DAL found the ``and/or'' construction of paragraphs (c)(1) and 
(c)(2) of the proposed AD confusing, and requested clarification 
regarding the applicability of airplanes that meet one of the two 
conditions or both conditions specified in paragraphs (c)(1) and (c)(2) 
of the proposed AD.
    We agree with DAL's request to clarify the applicability of this 
AD. We have revised paragraph (c) of this AD to include airplanes that 
have incorporated Boeing Alert Service Bulletin 777-78A0094, dated July 
29, 2014, and the condition specified in paragraph (c)(1) or (c)(2) of 
this AD is met on any engine, or both conditions specified in (c)(1) 
and (c)(2) of this AD are met on any engine.

Request To Clarify the Intent of the Proposed AD

    DAL requested that we clarify that the intent of the proposed AD is 
to maintain the EEC wire bundles inspections described in paragraph (k) 
of AD 2016-11-16 until all three of the following terminating actions 
have been completed: (1) Incorporating Boeing Alert Service Bulletin 
777-78A0094, dated July 29, 2014; (2) incorporating Work Package 7 of 
Boeing Special Attention Service Bulletin 777-78-0071, Revision 2, 
dated July 23, 2013; or

[[Page 64235]]

Part 8 or Part 9 of Boeing Service Bulletin 777-78-0082, Revision 1, 
dated June 15, 2015; as applicable; and (3) incorporating Rolls-Royce 
Service Bulletin RR.211-71-H824, dated July 30, 2014.
    We agree to clarify that the intent of this AD is to maintain the 
EEC wire bundles repetitive inspections described in paragraph (k) of 
AD 2016-11-16 for certain airplanes. The repetitive inspections 
required by paragraph (g) of this AD are no longer required after re-
contoured insulation blankets part numbers (P/N) 315W5115-60, -62, and 
-64 are installed on the right T/R half by accomplishing either Boeing 
Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 
23, 2013; or Boeing Service Bulletin 777-78-0082, Revision 1, dated 
June 15, 2015; and the EEC wire bundle and clip are re-routed on the 
engine by accomplishing Rolls-Royce Service Bulletin RR.211-71-H824, 
dated July 30, 2014. No change to this AD is needed in this regard.

Request To Revise Paragraph (c) Applicability of the Proposed AD

    AAL requested that paragraph (c) of the proposed AD be revised to 
exclude airplanes with the following configuration combinations from 
the applicability of paragraph (g) of the proposed AD:
     Engines with or without incorporation of Rolls-Royce 
Service Bulletin RR.211-71-H824, dated July 30, 2014; T/R halves that 
incorporated Boeing Alert Service Bulletin 777-78A0094, dated July 29, 
2014; installed re-contoured insulation blankets (P/N 315W5115-60, -62, 
and -64 for the right half and P/N 315W5115-63, -59, and -61 for the 
left half) by incorporating Work Package 7 of Boeing Special Attention 
Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013; and 
accomplishment of EEC wire bundle and clip inspection using Work 
Package 6 of Boeing Special Attention Service Bulletin 777-78-0071, 
Revision 2, dated July 23, 2013, when that T/R was installed.
     Engines with incorporation of Rolls-Royce Service Bulletin 
RR.211-71-H824, dated July 30, 2014, regardless of T/R half insulation 
blanket standards (re-contoured or non-re-contoured insulation 
blankets).
    AAL provided the following justifications for their request. We 
have included our response to those justifications.
    AAL explained that insulation blanket P/N 315W5115-60, -62, and -64 
are optional re-contoured insulation blankets introduced by Boeing 
Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 
23, 2013, to replace original P/N 315W5115-2, -6, or -20 non-re-
contoured insulation blankets that caused the initial potential EEC 
wire bundle and clip frettage condition. AAL noted that the optional 
re-contoured insulation blankets were designed with the addition of 
rulon frettage protection on the insulation blanket face sheet to 
prevent potential EEC wire bundle and clip frettage at the inspection 
area of paragraph (g) of the proposed AD. AAL stated that the 
installation of the re-contoured insulation blankets therefore provides 
an equivalent level of safety to the repetitive EEC wire bundle and 
clip inspections.
    AAL reasoned that Rolls-Royce Service Bulletin RR.211-71-H824, 
dated July 30, 2014, changes the EEC wire bundle routing to provide 
additional clearance with the T/R non-re-contoured insulation blankets 
to eliminate the potential frettage in the area of inspection as 
specified in paragraph (g) of the proposed AD and provides an 
equivalent level of safety to the repetitive EEC wire bundle and clip 
inspections. AAL added that any existing harness damage will be or has 
been addressed during incorporation of this service bulletin during an 
engine shop visit.
    We agree to clarify. We have determined that after accomplishing 
the work instructions in Boeing Alert Service Bulletin 777-78A0094, 
dated July 29, 2014, there is still not sufficient clearance between 
the insulation blankets and EEC wire bundle W0800 and its associated 
clip. The EEC wire bundle and clip could still be damaged from making 
contact with insulation blankets when one or both of the following 
conditions exist:
     The EEC wire and clip are not re-routed on the engine (did 
not incorporate Rolls-Royce Service Bulletin RR.211-71-H824, dated July 
30, 2014); or
     Non-re-contoured insulation blankets (P/N 315W5115-2, -6, 
and -20) are installed on the right T/R half.
    We have determined that in order to have proper clearance between 
the insulation blankets and the EEC wiring, and to prevent damage, 
Rolls-Royce Service Bulletin RR.211-71-H824, dated July 30, 2014, must 
be incorporated to re-route the EEC wire bundle and clip on the engine; 
and re-contoured insulation blankets P/N 315W5115-60, -62, and -64 must 
be installed on the right T/R half by accomplishing either Boeing 
Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 
23, 2013; or Boeing Service Bulletin 777-78-0082, Revision 1, dated 
June 15, 2015.
    AAL pointed out that the insulation blankets have repetitive 
airworthiness limitation inspection requirements as specified by Boeing 
Maintenance Planning Document (MPD) D622W001-9, Section 9, 
Airworthiness Limitations (AWLs) and Certification Maintenance 
Requirements (CMRs), Airworthiness Limitation Item (ALI) 78-AWL-01 that 
maintain the blanket rulon material condition. AAL noted that T/Rs that 
incorporate Work Package 7 of Boeing Special Attention Service Bulletin 
777-78-0071, Revision 2, dated July 23, 2013, for installing re-
contoured insulation blankets no longer have a T/R configuration 
specified by Boeing Special Attention Service Bulletin 777-78-0071, 
dated November 25, 2009; or Boeing Special Attention Service Bulletin 
777-78-0071, Revision 1, dated September 8, 2010; and are not 
applicable to the EEC wire bundle and clip inspection as specified in 
Work Package 6 of Boeing Special Attention Service Bulletin 777-78-
0071, Revision 2, dated July 23, 2013.
    AAL also noted that Rolls-Royce Model RB211-Trent 800 engine EEC 
wire runs already receive repetitive zonal general visual inspections 
as specified by Boeing MPD D622W001, Section 3, Zonal Inspection 
Program, item 71-864-01 and item 71-878-02, and receive repetitive 
detailed inspections as specified by Boeing MPD D622W001, Section 1, 
System Maintenance Program, item 20-540-01 and item 20-540-02, as part 
of a Lightning/High Intensity Radiated Fields maintenance program. AAL 
stated that these inspections are regulated by the 14 CFR 121.1111 
required electrical wiring interconnection systems (EWIS) maintenance 
program requirements.
    In regards to AAL's reference to Boeing MPD D622W001-9, Section 9, 
AWLs and CMRs, ALI 78-AWL-01, we note that Boeing MPD D622W001-9, 
Section 9, AWLs and CMRs, ALI 78-AWL-01 has requirements to inspect the 
insulation blankets for damage, but it does not directly inspect the 
EEC wire bundle and clip for damage. The intent of this AD is to 
specifically inspect the EEC wire bundle and clip for damage. We agree 
with AAL's justification that T/Rs with re-contoured insulation 
blankets installed no longer have a T/R configuration as specified by 
Boeing Special Attention Service Bulletin 777-78-0071, November 25, 
2009; or Boeing Special Attention Service Bulletin 777-78-0071, 
Revision 1, dated September 8, 2010. Boeing Special Attention Service 
Bulletin 777-78-0071, Revision 2, dated

[[Page 64236]]

July 23, 2013, does not have clear information and instructions to do a 
detailed EEC inspection for T/R halves with re-contoured blankets. 
However, as explained by Boeing and Boeing Service Bulletin 777-78-
0082, Revision 1, dated June 15, 2015, instructions, and reinforced by 
the requirements in this AD, EEC wire bundles and clips are to be 
inspected when one or both of the previously described conditions 
exists where the EEC wire bundle and clip could still be damaged from 
making contact with insulation blankets. We note that this AD mandates 
the use of Boeing Service Bulletin 777-78-0082, Revision 1, dated June 
15, 2015, to do the EEC wire bundle and clip detailed inspections, 
which is applicable to airplanes in a configuration specified in Boeing 
Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 
23, 2013.
    We infer that AAL is suggesting that the existing inspections in 
Boeing MPD D622W001, Section 3, Zonal Inspection Program, item 71-864-
01 and item 71-878-02, and detailed inspections in Boeing MPD D622W001, 
Section 1, System Maintenance Program, item 20-540-01 and item 20-540-
02 provide an equivalent level of safety to the repetitive wire bundle 
and clip inspections. We disagree with that suggestion. We note that 
part of the EWIS maintenance program requirement for operators is to 
maintain continued airworthiness of the electrical wiring 
interconnection systems on the airplane, including the engine. The EWIS 
maintenance program requirement is based on the assumption that the 
type design is compliant and is not expected to create wiring problems 
if the original configuration is maintained. This AD was proposed 
because the existing design was found to have details that are expected 
to lead to a wiring chafing problem on at least some airplanes. 
Therefore, we determined that more frequent and detailed inspections 
are necessary to address this unsafe condition. The inspections in 
Boeing MPD D622W001, Section 3, Zonal Inspection Program, item 71-864-
01 and item 71-878-02; and Boeing MPD D622W001, Section 1, System 
Maintenance Program, item 20-540-01 and item 20-540-02; are not 
sufficient to address the identified unsafe condition of this AD. The 
repetitive inspection intervals for Boeing MPD D622W001, Section 1, 
System Maintenance Program, item 20-540-01 and item 20-540-02; and 
Boeing MPD D622W001, Section 3, Zonal Inspection Program, item 71-864-
01 and item 71-878-02; are longer than the 2,000 flight-hour repetitive 
inspection interval specified in paragraph (g) of this AD, and they can 
be escalated to a longer interval without FAA ACO Branch approval. In 
accordance with 14 CFR part 39 (Sec.  39.5 and Sec.  39.13), this AD is 
issued to address the unsafe condition identified in paragraph (e) of 
this AD.
    Therefore, we do not agree to revise paragraph (c) of this AD as 
proposed by the commenter. We did not change the AD in this regard.

Request To Include Terminating Action

    DAL requested that we include terminating action for airplanes that 
accomplish the modification in paragraphs (c)(1) and (c)(2) of the 
proposed AD. DAL explained that paragraph (c) of the proposed AD states 
that if airplanes with Rolls-Royce engines, which have accomplished the 
action in Boeing Alert Service Bulletin 777-78A0094, dated July 29, 
2014, have neither the condition in paragraph (c)(1) of the proposed AD 
nor the condition in paragraph (c)(2) of the proposed AD, that the rule 
is not applicable. DAL noted that there is no terminating action 
paragraph in the proposed AD.
    We agree to clarify the requirements of this AD. As discussed in 
the above comments: For any affected airplane on which the modification 
specified in paragraph (c)(2) of this AD, and the replacement of all 
affected parts (non-re-contoured insulation blankets) identified in 
paragraph (c)(1) of this AD with non-affected parts (re-contoured 
insulation blankets) have been accomplished on both engines, that 
airplane is no longer affected by this AD. For clarity, we have added 
paragraph (i) to this AD to specify terminating actions for the 
repetitive inspections required by paragraph (g) of this AD and 
redesignated subsequent paragraphs accordingly.

Request To Extend the Compliance Time

    AAL requested that for engines that have not incorporated Rolls-
Royce Service Bulletin RR.211-71-H824, dated July 30, 2014, the 
inspection required by paragraph (g) of this AD be required within 
2,000 flight hours, rather than 500 flight hours, after the effective 
date of the AD, if re-contoured insulation blankets (P/N 315W5115-60, -
62, -64) were installed on the T/R by Work Package 7 of Boeing Special 
Attention Service Bulletin 777-78-0071, Revision 2, dated July 23, 
2013, and, during installation of the insulation blanket on the T/R 
halves, the EEC wire bundle inspection was accomplished on the engine 
in accordance with Work Package 6 of Boeing Special Attention Service 
Bulletin 777-78-0071, Revision 2, dated July 23, 2013.
    We do not agree with the commenter's request because we have 
determined that both the EEC wiring modification specified in Rolls-
Royce Service Bulletin RR.211-71-H824, dated July 30, 2014, and 
installation of the re-contoured insulation blankets specified in Work 
Package 7 of Boeing Special Attention Service Bulletin 777-78-0071, 
Revision 2, dated July 23, 2013, are necessary to prevent the chafing 
condition that is the subject of this AD. In the absence of both of 
those modifications, we have determined that a 2,000 flight hour 
inspection interval is necessary. The 500 flight hours is meant to be a 
grace period for those airplanes on which the interval has lapsed (due 
to inspections being terminated in AD 2016-11-16), as well as airplanes 
that are nearing the end of the inspection interval. AAL did not 
provide adequate justification for a longer grace period. We did not 
change this AD in this regard.

Request To Clarify the Requirements of Paragraph (g) of the Proposed AD 
for a Certain Repaired Wire Condition

    For engines which require inspections as specified in paragraph (g) 
of this AD, AAL requested clarification that the inspection of the wire 
bundle can be accomplished without removal of any harness 
polytetrafluoroethylene (PTFE) tape protection applied to the wire 
bundle, provided that the PTFE tape protection is not damaged, and 
provided the wire bundle had received an inspection and was repaired if 
damaged prior to application of the protective tape wrap. AAL explained 
that it had already identified the potential wire bundle interference 
condition through its continuous airworthiness maintenance program 
(CAMP) prior to release of Boeing Special Attention Service Bulletin 
777-78-0071, Revision 2, dated July 23, 2013. As a result, AAL 
accomplished a fleet-wide general visual inspection of the EEC wire 
bundle W0800 for damage in the inspection area, accomplished any 
required repairs, and then wrapped the W0800 harness with PTFE tape in 
accordance with the approved procedures in its CAMP.
    We do not agree with the commenter's request because we do not have 
sufficient information in the AAL request to clarify nor expand 
paragraph (g) of this AD for wire bundles that have been modified by 
AAL's CAMP. We do not consider it appropriate to include various 
provisions in an AD applicable only to individual airplane 
configurations or to a single operator's

[[Page 64237]]

unique use of an affected airplane. However, AAL and others may request 
an alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (j) of this AD, provided sufficient 
data are submitted to substantiate that the AMOC would provide an 
acceptable level of safety. We did not change this AD in this regard.

Request To Clarify Requirements of Paragraph (g) of the Proposed AD for 
Engine Inspection in the Shop

    AAL requested clarification to paragraph (g) of the proposed AD to 
confirm that after the effective date of this AD, installation of an 
engine that had a shop visit meets the requirements of an inspection, 
and in that case, that the next inspection is required within 2,000 
hours of engine installation.
    We agree to clarify paragraph (g) of this AD. If, during a shop 
visit, an EEC wire bundle and clamp inspection was done as specified in 
Boeing Special Attention Service Bulletin 777-78-0071, Revision 2, 
dated July 23, 2013; or Boeing Service Bulletin 777-78-0082, dated 
November 9, 2011; or Boeing Service Bulletin 777-78-0082, Revision 1, 
dated June 15, 2015; then the next inspection can be done within 2,000 
flight hours from the last inspection done in the shop. However, if an 
inspection other than the one specified in Boeing Special Attention 
Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013; or 
Boeing Service Bulletin 777-78-0082, dated November 9, 2011; or Boeing 
Service Bulletin 777-78-0082, Revision 1, dated June 15, 2015; was 
done, operators must request an AMOC in accordance with the procedures 
specified in paragraph (j) of this AD. No change to this AD is needed.

Request To Modify Relationship to Affected ADs

    DAL requested that AD 2005-07-24, Amendment 39-14049 (70 FR 18285, 
April 11, 2005) (``AD 2005-07-24'') and AD 2016-11-16 be added to 
paragraph (b) of the proposed AD. DAL also requested that the proposed 
AD be incorporated as a revision to AD 2016-11-16 or a supersedure to 
AD 2016-11-16 in order to provide a clear relationship between the 
actions required. DAL observed that paragraph (b) of the proposed AD 
states that no ADs are affected by this rule, but paragraph (l) of AD 
2016-11-16 states that accomplishment of Boeing Alert Service Bulletin 
777-78A0094, dated July 29, 2014, will terminate paragraph (k) of AD 
2016-11-16. DAL also submitted that paragraph (k) of AD 2016-11-16 
pertains to the EEC wire bundle inspections that are described in the 
``Discussion'' section of the proposed rule. DAL stated that paragraph 
(q) of AD 2016-11-16 describes accomplishments that are terminating 
actions to AD 2005-07-24, which include the EEC wire bundle inspections 
as described in paragraph (k) of AD 2016-11-16. DAL contended that the 
proposed rule reinstates these inspections and therefore affects the 
requirements of AD 2005-07-24 as described in paragraph (q) of AD 2016-
11-16.
    We do not agree with the commenter's request because this AD is a 
stand-alone AD and does not impact nor change the requirements of AD 
2005-07-24 or AD 2016-11-16. The T/R inner wall and TPS configuration, 
and certain engine configurations affected by the actions in this AD 
are not configurations affected by AD 2005-07-24 or AD 2016-11-16. This 
AD is only applicable to airplanes with certain T/R halves on which the 
actions in Boeing Alert Service Bulletin 777-78A0094, dated July 29, 
2014, have been accomplished, and the condition specified in paragraph 
(c)(1) or (c)(2) of this AD is met on any engine, or both conditions 
specified in (c)(1) and (c)(2) of this AD are met on any engine. This 
AD is not applicable to airplanes with T/R halves of certain inner wall 
and TPS configurations specified in AD 2005-07-24 and AD 2016-11-16 on 
which the actions specified in Boeing Alert Service Bulletin 777-
78A0094, dated July 29, 2014, have not been accomplished. Therefore, 
this AD has no direct relationship to and does not change the 
requirements of AD 2005-07-24 or AD 2016-11-16.
    After accomplishing paragraph (l) of AD 2016-11-16 to install 
serviceable thrust reverser halves (by accomplishing Boeing Alert 
Service Bulletin 777-78A0094, dated July 29, 2014), and paragraph (n) 
of AD 2016-11-16 to revise the maintenance or inspection program, the 
repetitive inspection requirements of AD 2016-11-16 are terminated. 
However, Boeing and the FAA have determined that inadequate clearance 
between the TPS non-re-contoured insulation blankets and the EEC wiring 
still exists after completing the actions required by AD 2016-11-16, 
which will result in damaged wires, and an unsafe condition still 
exists.
    We have determined not to revise or supersede AD 2016-11-16 because 
of the high rate of inner wall failures and the urgency of the safety 
issue. We have also determined that the required actions must be 
accomplished to ensure continued safety. Revising this AD as requested 
would necessitate (under the provisions of the Administrative Procedure 
Act) reissuing the notice, reopening the period for public comment, 
considering additional comments subsequently received, and eventually 
issuing a final rule. In light of this, and in consideration of the 
unsafe condition, we have determined that further delay of this AD is 
not appropriate. We have not changed this AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the change described previously and minor 
editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     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 final 
rule.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin 777-78-0082, Revision 1, dated 
June 15, 2015. The service information describes, among other things, 
procedures for repetitive inspections of the EEC wire bundles and 
clips, and corrective actions if necessary.
    We also reviewed Boeing Special Attention Service Bulletin 777-78-
0071, Revision 2, dated July 23, 2013. This service information 
describes, among other things, procedures for installing re-contoured 
insulation blankets on the right T/R halves and performing an EEC wire 
bundle and clip inspection.
    We also reviewed Rolls-Royce Service Bulletin RR.211-71-H824, dated 
July 30, 2014. This service information describes procedures for 
modifying the engine by rerouting the EEC wire bundle and clip.
    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 55 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

[[Page 64238]]

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
          Action                 Labor cost          Parts cost       Cost per product           operators
----------------------------------------------------------------------------------------------------------------
Inspection...............  Up to 6 work-hours x                $0  Up to $510 per          Up to $28,050 per
                            $85 per hour = $510                     inspection cycle.       inspection cycle.
                            per inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the repairs specified in this AD. We estimate the 
following costs to do any necessary replacements 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 repairs or replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of EEC wire harness...............  1 work-hour x $85 per hour = $85          $8,500          $8,585
----------------------------------------------------------------------------------------------------------------

    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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

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):

2018-25-11 The Boeing Company: Amendment 39-19522; Docket No. FAA-
2017-0246; Product Identifier 2017-NM-011-AD.

(a) Effective Date

    This AD is effective January 18, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes, certificated in any category, equipped with Rolls-
Royce Model RB211-Trent 800 engines, on which the actions specified 
in Boeing Alert Service Bulletin 777-78A0094 have been incorporated, 
and the condition specified in paragraph (c)(1) or (c)(2) of this AD 
is met on any engine, or both conditions specified in (c)(1) and 
(c)(2) of this AD are met on any engine.
    (1) Thermal protection system (TPS) non-re-contoured insulation 
blankets having part numbers (P/N) 315W5115-2, -6, or -20 are 
installed on the thrust reverser (T/R) inner wall.
    (2) Rolls-Royce Service Bulletin RR.211-71-H824, dated July 30, 
2014, has not been incorporated on the engine.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine 
exhaust.

(e) Unsafe Condition

    This AD was prompted by reports of inadequate clearance between 
the TPS insulation blankets and the electronic engine control (EEC) 
wiring, which resulted in damaged wires. We are issuing this AD to 
address damaged wires, which could result in in-flight shutdown of 
the engine, or the inability to properly control thrust, and 
consequent reduced controllability of the airplane.

(f) Compliance

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

[[Page 64239]]

(g) Repetitive EEC Wire Bundle Inspection

    Within 2,000 flight hours since the most recent EEC wire bundle 
inspection done as specified in Boeing Special Attention Service 
Bulletin 777-78-0071; or Boeing Service Bulletin 777-78-0082; or 
within 500 flight hours after the effective date of this AD, 
whichever occurs later: Do a detailed inspection for damage of the 
EEC wire bundles and clips, and do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 
2015. Do all applicable corrective actions before further flight. 
Repeat the inspection thereafter at intervals not to exceed 2,000 
flight hours.

(h) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the service information specified in 
paragraph (h)(1) or (h)(2) of this AD.
    (1) Boeing Special Attention Service Bulletin 777-78-0071, 
Revision 2, dated July 23, 2013.
    (2) Boeing Service Bulletin 777-78-0082, dated November 9, 2011.

(i) Optional Terminating Action

    Accomplishing the actions in paragraph (i)(1) and (i)(2) of this 
AD terminates the repetitive inspections required by paragraph (g) 
of this AD for the modified engine installation only.
    (1) Installing re-contoured insulation blankets P/N 315W5115-60, 
-62, and -64 on the right T/R halves in accordance with the 
Accomplishment Instructions of either Boeing Special Attention 
Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013; or 
Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 
2015.
    (2) Modifying an engine in accordance with the Accomplishment 
Instructions of Rolls-Royce Service Bulletin RR.211-71-H824, dated 
July 30, 2014.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, 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 (k)(1) of this AD. Information may be 
emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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 Branch, FAA, 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.

(k) Related Information

    (1) For more information about this AD, contact Kevin Nguyen, 
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3555; email: kevin.nguyen@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) of this AD.

(l) 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 777-78-0082, Revision 1, dated June 
15, 2015.
    (ii) Boeing Special Attention Service Bulletin 777-78-0071, 
Revision 2, dated July 23, 2013.
    (iii) Rolls-Royce Service Bulletin RR.211-71-H824, dated July 
30, 2014.
    (3) 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 https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on November 29, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-26532 Filed 12-13-18; 8:45 am]
 BILLING CODE 4910-13-P