[Federal Register Volume 83, Number 31 (Wednesday, February 14, 2018)]
[Proposed Rules]
[Pages 6477-6480]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-03026]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0078; Product Identifier 2017-NM-107-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) 2017-01-
02, which applies to certain The Boeing Company Model 787-8 and 787-9 
airplanes. AD 2017-01-02 requires an inspection for discrepant inboard 
and outboard trailing edge flap rotary actuators. Since we issued AD 
2017-01-02, we have determined that it is necessary to revise the 
applicability to include additional airplanes, and to reduce the number 
of affected actuators. This proposed AD would continue to require an 
inspection of the inboard and outboard trailing edge flap rotary 
actuator for any discrepant rotary actuator, and corrective actions if 
necessary. We are proposing this AD to address the unsafe condition on 
these products.

DATES: We must receive comments on this proposed AD by April 2, 2018.

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-

[[Page 6478]]

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 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-2018-0078.

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-2018-
0078; 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 NPRM, 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: Douglas Tsuji, Senior Aerospace 
Engineer, Systems and Equipment Section, FAA, Seattle ACO Branch, 1601 
Lind Avenue SW, Renton, WA 98057-3356; phone: 425-917-6546; fax: 425-
917-6590; email: [email protected].

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-2018-0078; 
Product Identifier 2017-NM-107-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM 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

    We issued AD 2017-01-02, Amendment 39-18769 (82 FR 4775, January 
17, 2017) (``AD 2017-01-02''), for certain The Boeing Company Model 
787-8 and 787-9 airplanes. AD 2017-01-02 requires an inspection for 
discrepant inboard and outboard trailing edge flap rotary actuators. AD 
2017-01-02 resulted from a report that indicated that some rotary 
actuators of the inboard and outboard trailing edge flap may have been 
assembled with an incorrect no-back brake rotor-stator stack sequence 
during manufacturing. We issued AD 2017-01-02 to detect and replace 
incorrectly assembled rotary actuators, which could cause accelerated 
unit wear that will eventually reduce braking performance. This 
degradation could lead to loss of no-back brake function and reduced 
controllability of the airplane.

Actions Since AD 2017-01-02 Was Issued

    Since we issued AD 2017-01-02, we have determined that it is 
necessary to revise the applicability to include additional airplanes, 
and to reduce the number of affected actuators.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin B787-81205-SB270032-00, 
Issue 003, dated July 28, 2017. The service information describes 
procedures for an inspection of the inboard and outboard trailing edge 
flap rotary actuator for any discrepant rotary actuator, and corrective 
actions if necessary. The related investigative action includes a 
functional test of the trailing edge flap no-back brake. The corrective 
actions include replacement of the discrepant rotary actuator with a 
non-discrepant rotary actuator. 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 2017-01-02 and 
add airplanes to the applicability. This proposed AD would require 
accomplishing the 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-2018-0078.
    The phrase ``related investigative actions'' is used in this 
proposed AD. Related investigative actions are follow-on actions that 
(1) are related to the primary action, and (2) further investigate the 
nature of any condition found. Related investigative actions in an AD 
could include, for example, inspections.
    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

    To support operations, many operators have put processes in place 
that, given certain conditions, allow them to rotate or transfer parts 
or equipment within their fleets to different aircraft than what is 
defined in the manufacturer's type design. We have determined that the 
parts or equipment subject to the unsafe condition may have been 
rotated or transferred in this manner, due to similarity with parts or 
equipment not subject to the unsafe condition. Therefore, the 
applicability of this proposed AD is for all The Boeing Company Model 
787 series airplanes.
    The effectivity specified in Boeing Alert Service Bulletin B787-
81205-SB270032-00, Issue 001, dated November 3, 2015, consists of only 
certain Boeing Model 787-8 and 787-9 airplanes. In this proposed AD, 
the actions required by paragraphs (g) and (h) of this AD would be 
accomplished on any The Boeing Company Model 787 series airplane with 
an original Certificate of Airworthiness or an original Export 
Certificate of Airworthiness dated on or before the effective date of 
the final rule. Expanding the applicability of this proposed AD 
addresses the rotability issue of the trailing edge flap rotary 
actuators. We have confirmed with the manufacturer that the 
accomplishment instructions in the following service information are 
applicable to the expanded group of airplanes:

[[Page 6479]]

     Boeing Alert Service Bulletin B787-81205-SB270032-00, 
Issue 001, dated November 3, 2015.
     Boeing Alert Service Bulletin B787-81205-SB270032-00, 
Issue 002, dated November 3, 2016.
     Boeing Alert Service Bulletin B787-81205-SB270032-00, 
Issue 003, dated July 28, 2017.
    The Boeing Company Model 787 series airplanes with an original 
Certificate of Airworthiness or an original Export Certificate of 
Airworthiness dated after the effective date of the final rule are not 
required to complete the actions specified in paragraphs (g) and (h) of 
this AD, but must comply with the parts installation prohibition in 
paragraph (i) of this AD.

Costs of Compliance

    We estimate that this proposed AD affects 89 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection............................  5 work-hours x $85 per                $0            $425         $37,825
                                         hour = $425.
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    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of the proposed 
inspection. We have no way of determining the number of aircraft or the 
number of rotary actuators (up to 8 per shipset) that might need these 
on-condition actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                     Labor cost         Parts cost               Cost per product
----------------------------------------------------------------------------------------------------------------
Check to determine flight cycles    1 work-hour x $85                 $0  $85 per rotary actuator.
 on the rotary actuator.             per hour = $85.
Functional Test per rotary          2 work-hours x $85                 0  $170 per rotary actuator.
 actuator.                           per hour = $170.
Replacement per rotary actuator...  2 work-hours x $85                 0  $170 per rotary actuator.
                                     per hour = $170.
System Test after rotary actuator   24 work-hours x $85                0  $2,040 per airplane.
 replacement(s) per airplane.        per hour = $2,040.
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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 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) 
2017-01-02, Amendment 39-18769 (82 FR 4775, January 17, 2017), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2018-0078; Product Identifier 
2017-NM-107-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by April 2, 
2018.

(b) Affected ADs

    This AD replaces AD 2017-01-02, Amendment 39-18769 (82 FR 4775, 
January 17, 2017) (``AD 2017-01-02'').

(c) Applicability

    This AD applies to all The Boeing Company Model 787 series 
airplanes, certificated in any category.

[[Page 6480]]

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
control systems.

(e) Unsafe Condition

    This AD was prompted by a report indicating that some inboard 
and outboard trailing edge flap rotary actuators may have been 
assembled with an incorrect no-back brake rotor-stator stack 
sequence during manufacturing. We are issuing this AD to detect and 
replace incorrectly assembled rotary actuators, which could cause 
accelerated unit wear that will eventually reduce braking 
performance. This degradation could lead to loss of no-back brake 
function and reduced controllability of the airplane.

(f) Compliance

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

(g) Retained Inspection and Other Actions

    For The Boeing Company Model 787-8 and 787-9 airplanes 
identified in Boeing Alert Service Bulletin B787-81205-SB270032-00, 
Issue 001, dated November 3, 2015: Within 60 months after February 
21, 2017 (the effective date of AD 2017-01-02), do an inspection of 
the inboard and outboard trailing edge flap rotary actuator for any 
discrepant rotary actuator, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin B787-81205-SB270032-
00, Issue 001, dated November 3, 2015; or Boeing Alert Service 
Bulletin B787-81205-SB270032-00, Issue 003, dated July 28, 2017. If 
any discrepant rotary actuator is found, within 60 months after 
February 21, 2017, do the actions specified in paragraph (g)(1) or 
(g)(2) of this AD, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin B787-81205-SB270032-
00, Issue 001, dated November 3, 2015; or Boeing Alert Service 
Bulletin B787-81205-SB270032-00, Issue 003, dated July 28, 2017. 
After the effective date of this AD only Boeing Alert Service 
Bulletin B787-81205-SB270032-00, Issue 003, dated July 28, 2017, may 
be used.
    (1) Replace the discrepant rotary actuator.
    (2) Check the maintenance records to determine the flight cycles 
of each discrepant rotary actuator and, within 60 months after 
February 21, 2017 (the effective date of AD 2017-01-02), do all 
applicable related investigative and corrective actions.

(h) New Requirements: Inspection, Related Investigative and Corrective 
Actions

    For airplanes not identified in Boeing Alert Service Bulletin 
B787-81205-SB270032-00, Issue 001, dated November 3, 2015, which 
have an Original Certificate of Airworthiness or Export Certificate 
of Airworthiness with a date on or before the effective date of this 
AD: Within 60 months after the effective date of this AD, do an 
inspection of the inboard and outboard trailing edge flap rotary 
actuator for any discrepant rotary actuator, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin B787-
81205-SB270032-00, Issue 003, dated July 28, 2017. If any discrepant 
rotary actuator is found, within 60 months after the effective date 
of this AD, do the actions specified in paragraph (h)(1) or (h)(2) 
of this AD, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin B787-81205-SB270032-00, Issue 003, 
dated July 28, 2017.
    (1) Replace the discrepant rotary actuator.
    (2) Check the maintenance records to determine the flight cycles 
of each discrepant rotary actuator and, within 60 months after the 
effective date of this AD, do all applicable related investigative 
and corrective actions.

(i) Parts Installation Limitation

    As of the effective date of this AD, no person may install, on 
any airplane, a rotary actuator with a part number and serial number 
identified in Appendix A of Boeing Alert Service Bulletin B787-
81205-SB270032-00, Issue 003, dated July 28, 2017, unless the 
actuator has been permanently marked in accordance with Task 2 of 
Boeing Alert Service Bulletin B787-81205-SB270032-00, Issue 003, 
dated July 28, 2017, with ``B787-81205-SB270032-00 INCORPORATED.''

(j) Credit for Previous Actions

    (1) 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 Boeing Alert Service Bulletin B787-
81205-SB270032-00, Issue 002, dated November 3, 2016.
    (2) 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 Alert Service Bulletin B787-
81205-SB270032-00, Issue 001, dated November 3, 2015, or Boeing 
Alert Service Bulletin B787-81205-SB270032-00, Issue 002, dated 
November 3, 2016.

(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: [email protected].
    (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 2017-01-02 are approved as 
AMOCs for the corresponding provisions 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 Douglas Tsuji, 
Senior Aerospace Engineer, Systems and Equipment Section, FAA, 
Seattle ACO Branch, 1601 Lind Avenue SW, Renton, WA 98057-3356; 
phone: 425-917-6546; fax: 425-917-6590; email: 
[email protected].
    (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 January 30, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-03026 Filed 2-13-18; 8:45 am]
 BILLING CODE 4910-13-P


