[Federal Register Volume 82, Number 164 (Friday, August 25, 2017)]
[Proposed Rules]
[Pages 40511-40514]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17543]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0779; Product Identifier 2017-NM-040-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 adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 787-8 airplanes. This proposed AD was 
prompted by reports of degraded bond-line performance of co-bonded 
upper wing stringer-to-skin joints. This proposed AD would require 
repetitive inspections of certain upper wing stringers for any disbond 
and corrective actions, if necessary; and a terminating preventative 
modification of installing disbond arrestment (DBA) fasteners. This 
proposed AD would also require revising the inspection or maintenance 
program to incorporate an airworthiness limitation. We are proposing 
this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by October 10, 
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-2017-0779.

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-
0779; 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: Allen Rauschendorfer, Aerospace 
Engineer, Airframe Branch, FAA, Seattle ACO Branch, 1601 Lind Avenue 
SW., Renton, WA 98057-3356; phone: 425-917-6487; 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-2017-0779; 
Product Identifier 2017-NM-040-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

    We have received reports of degraded bond-line performance of co-
bonded upper wing stringer-to-skin joints. The co-bonded upper wing 
stringer-to-skin joints were determined to have degraded bond-line 
performance due to the exposure of the bond surface with the use of BMS 
8-308 peel ply to cure times that exceeded 4 hours at a temperature of 
345 degrees Fahrenheit (F) plus or minus 10 F. The upper wing stringer-
to-skin joint disbonding can reduce the structural capability to where 
it cannot sustain limit load, which could adversely affect the 
structural integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    We have reviewed Boeing Alert Service Bulletin B787-81205-SB570030-
00, Issue 001, dated March 17, 2017 (``ASB B787-81205-SB570030-00, 
Issue 001''). This service information describes procedures for 
inspection of certain upper wing stringers for any disbond and repairs; 
and for a preventative modification which consists of, depending on 
airplane configuration, applying copper foil to the upper wing at 
certain stringer and rib bay locations, installing DBA fasteners on the 
upper flanges of the upper wing stringers at the stringer and rib bay 
locations, applying cap seals to the DBA fasteners, and applying edge 
sealant to the stringers at the DBA fastener installation locations.
    We have also reviewed Airworthiness Limitation (AWL) 57-AWL-13, 
``Inspection Requirements for In-Tank Fasteners and Edge Seal near 
Disbond Arrestment (DBA) Fastener Installations of Lightning Zone 2,'' 
of Boeing 787 Special Compliance Items/Airworthiness Limitations, 
D011Z009-03-04, dated February 2017. This service information describes 
tasks for inspecting in-tank fasteners and edge seals near DBA fastener 
installations of lightning zone 2.

[[Page 40512]]

    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 require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' For information on the procedures and compliance times 
in ASB B787-81205-SB570030-00, Issue 001, see this service information 
at http://www.regulations.gov by searching for and locating Docket No. 
FAA-2017-0779.
    This AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections). Compliance with 
these actions is required by 14 CFR 91.403(c). For airplanes that have 
been previously modified, altered, or repaired in the areas addressed 
by this proposed AD, the operator may not be able to accomplish the 
actions described in the revisions. In this situation, to comply with 
14 CFR 91.403(c), the operator must request approval for an alternative 
method of compliance according to paragraph (l) of this proposed AD. 
The request should include a description of changes to the required 
actions that will ensure the continued damage tolerance of the affected 
structure.
    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

    ASB B787-81205-SB570030-00, Issue 001, specifies to contact the 
manufacturer for certain instructions, but this proposed AD would 
require using repair methods, modification deviations, and alteration 
deviations in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Explanation of Applicability

    In the applicability of this proposed AD, we refer to the airplanes 
identified in ASB B787-81205-SB570030-00, Issue 001. In addition, we 
have included line numbers 10, 13, 15, 16, 17, 18, and 19 in the 
applicability of this proposed AD because those line numbers are 
included in the applicability for AWL 57-AWL-13. Those line numbers are 
not listed in ASB B787-81205-SB570030-00, Issue 001, and the actions 
specified in ASB B787-81205-SB570030-00, Issue 001 are not required for 
those line numbers because the actions in the service information were 
completed during production.

Costs of Compliance

    We estimate that this proposed AD affects 24 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
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                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
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Inspection.....................  49 work-hours x $85 per              $0  $4,165 per          $99,960 per
                                  hour = $4,165 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
Modification...................  Up to 352 work-hours x            1,902  Up to $31,822.....  Up to $763,728.
                                  $85 per hour = $29,920.
Maintenance or Inspection        1 work-hour x $85 per                 0  $85...............  $2,040.
 Program Revision.                hour = $85.
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    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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.
    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 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 this 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.

[[Page 40513]]

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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2017-0779; Product Identifier 
2017-NM-040-AD.

(a) Comments Due Date

    We must receive comments by October 10, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin B787-81205-SB570030-00, Issue 001, dated March 17, 2017 
(``ASB B787-81205-SB570030-00, Issue 001''), and line numbers 10, 
13, 15, 16, 17, 18, and 19.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of degraded bond-line 
performance of co-bonded upper wing stringer-to-skin joints. We are 
issuing this AD to prevent upper wing stringer-to-skin joint 
disbonding, which can reduce the structural integrity of the 
airplane.

(f) Compliance

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

(g) Inspections and Corrective Actions

    For airplanes identified in ASB B787-81205-SB570030-00, Issue 
001: Except as specified in paragraph (k)(1) of this AD, at the 
applicable time specified in paragraph 5., ``Compliance,'' of ASB 
B787-81205-SB570030-00, Issue 001: Do an ultrasonic inspection for 
any disbond on the left side and right side upper wing stringers; 
and do all applicable corrective actions; in accordance with the 
Accomplishment Instructions of ASB B787-81205-SB570030-00, Issue 
001, except as specified in paragraph (k)(2) of this AD. Do all 
applicable corrective actions before further flight. Repeat the 
inspection of the upper wing stringers thereafter at the applicable 
intervals specified in paragraph 5., ``Compliance,'' of ASB B787-
81205-SB570030-00, Issue 001 until the actions required by paragraph 
(j) of this AD are done.

(h) Maintenance or Inspection Program Revision

    (1) For airplanes identified in ASB B787-81205-SB570030-00, 
Issue 001: Prior to or concurrently with accomplishing the actions 
required by paragraph (g) of this AD, revise the inspection or 
maintenance program, as applicable, to incorporate Airworthiness 
Limitation (AWL) 57-AWL-13. ``Inspection Requirements for In-Tank 
Fasteners and Edge Seal near Disbond Arrestment (DBA) Fastener 
Installations of Lightning Zone 2,'' of Boeing 787 Special 
Compliance Items/Airworthiness Limitations, D011Z009-03-04, dated 
February 2017. The initial compliance time for accomplishing the 
tasks specified in AWL 57-AWL-13 is within 24,000 flight cycles or 
12 years, whichever occurs first, after accomplishing the actions 
specified in ASB B787-81205-SB570030-00, Issue 001.
    (2) For airplanes having line numbers 10, 13, and 15 through 19 
inclusive: Within 60 days after the effective date of this AD, 
revise the inspection or maintenance program, as applicable, to 
incorporate AWL 57-AWL-13, ``Inspection Requirements for In-Tank 
Fasteners and Edge Seal near Disbond Arrestment (DBA) Fastener 
Installations of Lightning Zone 2,'' of Boeing 787 Special 
Compliance Items/Airworthiness Limitations, D011Z009-03-04, dated 
February 2017. The initial compliance time for accomplishing the 
tasks specified in AWL 57-AWL-13 is prior to the accumulation of 
24,000 total flight cycles or within 12 years after the date of 
issuance of the original airworthiness certificate or date of 
issuance of the original export certificate of airworthiness, 
whichever occurs first.

(i) No Alternative Actions or Intervals

    After the action required by paragraph (h) of this AD has been 
done, no alternative actions (e.g., inspections) or intervals may be 
used unless the actions or intervals are approved as an AMOC in 
accordance with the procedures specified in paragraph (l) of this 
AD.

(j) Inspection and Modification

    For airplanes identified in ASB B787-81205-SB570030-00, Issue 
001, that have not done ``PART 3: PREVENTIVE MODIFICATION'' of the 
Accomplishment Instructions of ASB B787-81205-SB570030-00, Issue 
001, at all of the unrepaired areas of the upper wing stringers: At 
the applicable time specified in paragraph 5., ``Compliance,'' of 
ASB B787-81205-SB570030-00, Issue 001, do the actions specified in 
paragraphs (j)(1) and (j)(2) of this AD, in accordance with the 
Accomplishment Instructions of ASB B787-81205-SB570030-00, Issue 
001, except as specified in paragraph (k)(2) of this AD. Doing the 
actions required by this paragraph terminates the repetitive 
inspections required by paragraph (g) of this AD.
    (1) Do an ultrasonic inspection for any disbond on the left side 
and right side upper wing stringers, and do all applicable 
corrective actions. Do all applicable corrective actions before 
further flight.
    (2) Do the preventative modification in accordance with ``PART 
3: PREVENTIVE MODIFICATION'' of the Accomplishment Instructions of 
ASB B787-81205-SB570030-00, Issue 001.

(k) Exceptions to Service Information

    (1) Where paragraph 5., ``Compliance,'' of ASB B787-81205-
SB570030-00, Issue 001, specifies a compliance time ``after the 
Issue 001 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Although ASB B787-81205-SB570030-00, Issue 001, specifies to 
contact Boeing for repair instructions, and specifies that action as 
``RC'' (Required for Compliance), this AD requires repair before 
further flight using a method approved in accordance with the 
procedures specified in paragraph (l) of this AD.

(l) 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 (m)(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) Except as required by paragraph (k)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (l)(4)(i) and 
(l)(4)(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

[[Page 40514]]

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.

(m) Related Information

    (1) For more information about this AD, contact Allen 
Rauschendorfer, Aerospace Engineer, Airframe Branch, FAA, Seattle 
ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6487; 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 August 9, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-17543 Filed 8-24-17; 8:45 am]
 BILLING CODE 4910-13-P