Document ID: FAA-2017-0771-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2017-08-15T04:00Z

[Federal Register Volume 82, Number 156 (Tuesday, August 15, 2017)]
[Proposed Rules]
[Pages 38629-38632]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16666]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0771; Product Identifier 2016-NM-212-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-09-
07, which applies to all The Boeing Company Model 787 airplanes. AD 
2015-09-07 requires a repetitive maintenance task for electrical power 
deactivation. Since we issued AD 2015-09-07, Boeing has developed new 
software for the generator control unit (GCU) that addresses the 
software counter overflow anomaly that prompted the issuance of AD 
2015-09-07. This proposed AD would require installing the new GCU 
software. This proposed AD would also remove certain airplanes from the 
applicability. We are proposing this AD to address the unsafe condition 
on these products.

DATES: We must receive comments on this proposed AD by September 29, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 referenced service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on 
the availability of this material at the FAA, call 425-227-1221. It is 
also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2017-0771.

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-
0771; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Stephen Oshiro, Aerospace Engineer, 
Systems and Equipment Section, FAA, Seattle ACO Branch, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; phone: 425-917-6480; fax: 425-917-
6590; email: Stephen.Oshiro@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0771; 
Product Identifier 2016-NM-212-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On April 23, 2015, we issued AD 2015-09-07, Amendment 39-18153 (80 
FR 24789, May 1, 2015) (``AD 2015-09-07''), for all The Boeing Company 
Model 787 airplanes. AD 2015-09-07 requires a repetitive maintenance 
task for electrical power deactivation on Model 787 airplanes. AD 2015-
09-07 resulted from the determination that a Model 787 airplane that 
has been powered continuously for 248 days can lose all alternating 
current (AC) electrical power due to the GCUs simultaneously going into 
failsafe mode. This condition is caused by a software counter internal 
to the GCUs that will overflow after 248 days of continuous power. We 
issued AD 2015-09-07 to prevent loss of all AC electrical power, which 
could result in loss of control of the airplane.

Actions Since AD 2015-09-07 Was Issued

    The preamble to AD 2015-09-07 specifies that we consider the 
requirements ``interim action'' and that the manufacturer is developing 
a modification to address the unsafe condition. That AD explains that 
we might consider further rulemaking if a modification is developed, 
approved, and available. Since we issued AD 2015-09-07, Boeing has 
developed new software for the Model 787 GCU that addresses the 
software counter overflow anomaly that prompted the issuance of AD 
2015-09-07. Installation of the new software eliminates the need for 
performing the repetitive maintenance

[[Page 38630]]

actions (i.e., repetitive electrical power deactivations) that were 
mandated by AD 2015-09-07 as a means of mitigating the GCU software 
counter overflow anomaly.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information.
     Boeing Service Bulletin B787-81205-SB240063-00, Issue 002, 
dated June 7, 2016, which describes procedures for installing 
operational program software (OPS) into each of the six GCUs and doing 
a software check. This service information specifies to concurrently 
accomplish the following two service bulletins:
     Boeing Service Bulletin B787-81205-SB280018-00, Issue 001, 
dated April 17, 2014, which describes procedures for installing fuel 
quantity management program software and doing a software check.
     Boeing Service Bulletin B787-81205-SB420006-00, Issue 003, 
dated October 15, 2015, which describes procedures for installing 
common interface control document 9.3 software and doing a software 
check.
     Boeing Multi Operator Message MOM-MOM-15-0248-01B, dated 
April 19, 2015; and Boeing Multi Operator Message MOM-MOM-15-0248-
01B(R1), dated April 20, 2015. This service information describes 
procedures for electrical power deactivation of Model 787 airplanes. 
These documents are distinct due to editorial revisions.
    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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2015-09-07. 
However, this proposed AD removes certain airplanes from the 
applicability of AD 2015-09-07, which affects all Model 787 airplanes. 
The new software specified in Boeing Service Bulletin B787-81205-
SB240063-00, Issue 002, dated June 7, 2016, has already been installed 
on airplanes having line numbers 4, 5, 10, 12-19, 22, 369, 371, 373, 
and 375-552 and will be installed in production on line numbers 553 and 
subsequent. Line numbers 1, 2, and 3 are no longer in service. 
Therefore, this proposed AD only affects airplanes identified in Boeing 
Service Bulletin B787-81205-SB240063-00, Issue 002, dated June 7, 2016.
    This proposed AD would also require installing the new software and 
accomplishing applicable corrective actions specified in the service 
information described previously. For information on the procedures and 
compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0771.
    The phrase ``corrective actions'' is used in this proposed AD. 
Corrective actions correct or address any condition found. Corrective 
actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    Boeing Service Bulletin B787-81205-SB240063-00, Issue 002, dated 
June 7, 2016, states that this revision has no effect on airplanes on 
which Issue 001 was previously done. However, this proposed AD will 
require additional action for Group 2 airplanes. Operators of Group 2 
airplanes will be required to accomplish the actions in Boeing Service 
Bulletin B787-81205-SB420006-00, issue 003, dated October 15, 2015, on 
those airplanes.

Costs of Compliance

    We estimate that this proposed AD affects 47 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on  U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Electrical power deactivation      1 work-hour x $85              $0  $85 per deactivation  $3,995 per
 (actions retained from AD 2015-    per hour = $85 per                 cycle.                deactivation cycle.
 09-07).                            deactivation cycle.
Software installation (new         5 work-hours x $85             $0  $425................  $19,975.
 proposed action).                  per hour = 425.
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                                     Estimated Costs for Concurrent Actions
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost        Cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
Install fuel quantity management       1 work-hour x $85 per    \1\....................  Up to $3,995.
 program software.                      hour = $85.
Install common interface control       Up to 15 work-hours X    \1\....................  Up to $59,925.
 document 9.3 software.                 $85 per hour = $1,275.
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\1\ We have received no definitive data that would enable us to provide parts cost estimates for the concurrent
  actions specified in this proposed AD.

    According to the manufacturer, some of the costs of this proposed 
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 available 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,

[[Page 38631]]

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 proposed 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 to the Director of the System Oversight 
Division.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 
2015-09-07, Amendment 39-18153 (80 FR 24789, May 1, 2015), and adding 
the following new AD:

The Boeing Company: Docket No. FAA-2017-0771; Product Identifier 
2016-NM-212-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by September 29, 
2017.

(b) Affected ADs

    This AD replaces AD 2015-09-07, Amendment 39-18153 (80 FR 24789, 
May 1, 2015) (``AD 2015-09-07'').

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 and 787-9 
airplanes, certificated in any category, as identified in Boeing 
Service Bulletin B787-81205-SB240063-00, Issue 002, dated June 7, 
2016.

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
power.

(e) Unsafe Condition

    This AD was prompted by the determination that a Model 787 
airplane that has been powered continuously for 248 days can lose 
all alternating current (AC) electrical power due to the generator 
control units (GCUs) simultaneously going into failsafe mode. This 
condition is caused by a software counter internal to the GCUs that 
will overflow after 248 days of continuous power. We are issuing 
this AD to prevent loss of all AC electrical power, which could 
result in loss of control of the airplane.

(f) Compliance

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

(g) Retained Repetitive Maintenance Task: Electrical Power Deactivation 
With a New Reference To Terminating Action

    This paragraph restates the actions required by paragraph (g) of 
AD 2015-09-07, with a new reference to terminating action. At the 
latest of the times specified in paragraphs (g)(1), (g)(2), and 
(g)(3) of this AD, accomplish electrical power deactivation on the 
airplane, in accordance with step 2) in ``DESIRED ACTION'' of Boeing 
Multi Operator Message MOM-MOM-15-0248-01B, dated April 19, 2015; or 
Boeing Multi Operator Message MOM-MOM-15-0248-01B(R1), dated April 
20, 2015. The main and auxiliary power unit (APU) batteries do not 
need to be disconnected when performing the electrical power 
deactivation. Repeat the electrical power deactivation thereafter at 
intervals not to exceed 120 days until the software installation 
required by paragraph (h) of this AD is done.
    (1) Within 120 days after the last electrical power deactivation 
in accordance with step 2) in ``DESIRED ACTION'' of Boeing Multi 
Operator Message MOM-MOM-15-0248-01B, dated April 19, 2015; or 
Boeing Multi Operator Message MOM-MOM-15-0248-01B(R1), dated April 
20, 2015.
    (2) Within 120 days after the date of issuance of the original 
certificate of airworthiness or the date of issuance of the original 
export certificate of airworthiness.
    (3) Within 7 days after May 1, 2015 (the effective date of AD 
2015-09-07).

(h) New Requirement of This AD: Software Installation

    Within 12 months after the effective date of this AD: Install 
new operational program software (OPS) into each of the six GCUs, do 
a software check, and do all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin B787-81205-SB240063-00, Issue 002, dated June 7, 2016. Do 
all applicable corrective actions before further flight. 
Accomplishment of the actions required by this paragraph on all six 
GCUs on an airplane terminates the requirements of paragraph (g) of 
this AD for that airplane.

(i) New Requirement of This AD: Concurrent Actions

    (1) For Group 1 airplanes as identified in Boeing Service 
Bulletin B787-81205-SB240063-00, Issue 002, dated June 7, 2016: 
Prior to or concurrently with accomplishing the actions required by 
paragraph (h) of this AD, do the actions specified in paragraph 
(i)(1)(i) and (i)(1)(ii) of this AD.
    (i) Install new fuel quantity management program software and do 
a software check, in accordance with the Accomplishment Instructions 
of Boeing Service Bulletin B787-81205-SB280018-00, Issue 001, dated 
April 17, 2014. If any software check fails, before further flight, 
do corrective actions, repeat the check, and do applicable 
corrective actions until the software passes the check.
    (ii) Install new common interface control document 9.3 software 
and do software checks, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin B787-81205-SB420006-00, 
Issue 003, dated October 15, 2015. If any software check fails, 
before further flight, do corrective actions, repeat the check, and 
do applicable corrective actions until the software passes the 
check.
    (2) For Group 2 airplanes as identified in Boeing Service 
Bulletin B787-81205-SB240063-00, Issue 002, dated June 7, 2016: 
Prior to or concurrently with accomplishing the actions required by 
paragraph (h) of this AD, install new common interface control 
document 9.3 software and do software checks, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin B787-81205-
SB420006-00, Issue 003, dated October 15, 2015. If any software 
check fails, before further flight, do corrective actions, repeat 
the check, and do applicable corrective actions until the software 
passes the check.

(j) Credit for Previous Actions

    (1) For Group 1 and Group 3 airplanes as identified in Boeing 
Service Bulletin B787-81205-SB240063-00, Issue 001, dated December 
22, 2015: This paragraph provides credit for the actions specified 
in paragraph

[[Page 38632]]

(h) of this AD, if those actions were performed before the effective 
date of this AD using Boeing Service Bulletin B787-81205-SB240063-
00, Issue 001, dated December 22, 2015.
    (2) For Group 2 airplanes as identified in Boeing Service 
Bulletin B787-81205-SB240063-00, Issue 001, dated December 22, 2015: 
This paragraph provides credit for the actions specified in 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Service Bulletin B787-81205-
SB240063-00, Issue 001, dated December 22, 2015, and provided the 
actions specified in Boeing Service Bulletin B787-81205-SB420006-00, 
Issue 003, dated October 15, 2015, are done within 12 months after 
the effective date of this AD.

(k) 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 certification office, send it to the attention of the 
person identified in paragraph (l)(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, 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 2015-09-07 are approved as 
AMOCs for the corresponding provisions of paragraph (g) of this AD.
    (5) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(k)(5)(i) and (k)(5)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(l) Related Information

    (1) For more information about this AD, contact Stephen Oshiro, 
Aerospace Engineer, Systems and Equipment Section, FAA, Seattle ACO 
Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6480; fax: 425-917-6590; email: Stephen.Oshiro@faa.gov.
    (2) 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. You may view this referenced service 
information at the FAA, Transport Standards Branch, 1601 Lind Avenue 
SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 28, 2017.
John P. Piccola, Jr.,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-16666 Filed 8-14-17; 8:45 am]
 BILLING CODE 4910-13-P