AD 2019-22-01

[Federal Register Volume 84, Number 218 (Tuesday, November 12, 2019)]
[Rules and Regulations]
[Pages 60900-60902]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2019-24501]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0583; Product Identifier 2019-NM-063-AD; Amendment 
39-19780; AD 2019-22-01]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain The Boeing Company Model 787-8 airplanes. This AD was prompted 
by a report of an escapement from the wing spar terminal fitting 
supplier indicating that the engineering requirements provided by 
Boeing for controlling machine mismatch were incorrect for part faying 
surfaces, which can result in a reduced fatigue capability at the 
interface of the side of body (SOB) rib. This AD requires repetitive 
inspections for fatigue cracking and applicable on-condition actions 
for the SOB rib webs where fastener locations attach the terminal 
fittings. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective December 17, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 17, 
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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-2019-
0583.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-2019-
0583; 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 information. The address for Docket Operations is 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: Allen Rauschendorfer, Aerospace 
Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th 
St., Des Moines, WA 98198; phone and fax: 206-231-3528; email: 
<a href="/cdn-cgi/l/email-protection#03426f6f666d2d51627670606b666d676c71656671436562622d646c75"><span class="__cf_email__" data-cfemail="5c1d30303932720e3d292f3f34393238332e3a392e1c3a3d3d723b332a">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would

[[Page 60901]]

apply to certain The Boeing Company Model 787-8 airplanes. The NPRM 
published in the Federal Register on August 9, 2019 (84 FR 39239). The 
NPRM was prompted by a report of an escapement from the wing spar 
terminal fitting supplier indicating that the engineering requirements 
provided by Boeing for controlling machine mismatch were incorrect for 
part faying surfaces, which can result in a reduced fatigue capability 
at the interface of the SOB rib. The NPRM proposed to require 
repetitive inspections for fatigue cracking and applicable on-condition 
actions for the SOB rib webs where fastener locations attach the 
terminal fittings.
    The FAA is issuing this AD to address fatigue cracks in the left 
and right SOB rib webs common to the front and rear wing spar terminal 
fittings. Undetected fatigue cracks can grow to weaken primary wing 
structure where it cannot sustain limit load, which could adversely 
affect the structural integrity of the airplane.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA has considered the comment 
received. Boeing indicated its support for the NPRM.

Conclusion

    The FAA reviewed the relevant data, considered the comment 
received, and determined that air safety and the public interest 
require adopting this final rule as proposed, except for minor 
editorial changes. The FAA has determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin B787-81205-
SB570036-00 RB, Issue 001, dated December 14, 2018. The service 
information describes procedures for repetitive high frequency eddy 
current or ultrasonic inspections for fatigue cracking and applicable 
on-condition actions for the SOB rib webs where fastener locations 
attach the terminal fittings. On-condition actions include repair. 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

    The FAA estimates that this AD affects 1 airplane of U.S. registry. 
The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................  Up to 32 work-hours            $960  Up to $3,680 per     Up to $3,680 per
                                    x $85 per hour =                     inspection cycle.    inspection cycle.
                                    Up to $2,720 per
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the on-condition actions specified 
in this AD.
    According to the manufacturer, some or all of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected individuals. The FAA does not control warranty coverage for 
affected individuals. As a result, the FAA has included all known 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.
    The FAA is 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) Will not affect intrastate aviation in Alaska, and
    (3) 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):

2019-22-01 The Boeing Company: Amendment 39-19780; Docket No. FAA-
2019-0583; Product Identifier 2019-NM-063-AD.

[[Page 60902]]

(a) Effective Date

    This AD is effective December 17, 2019.

(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 
Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001, dated 
December 14, 2018.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of an escapement from the wing 
spar terminal fitting supplier indicating that the engineering 
requirements provided by Boeing for controlling machine mismatch 
were incorrect for part faying surfaces, which can result in a 
reduced fatigue capability at the interface of the side of body 
(SOB) rib. The FAA is issuing this AD to address fatigue cracks in 
the left and right SOB rib webs common to the front and rear wing 
spar terminal fittings. Undetected fatigue cracks can grow to weaken 
primary wing structure where it cannot sustain limit load, which 
could adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) Required Actions

    Except as specified by paragraph (h) of this AD: At the 
applicable times specified in the ``Compliance'' paragraph of Boeing 
Alert Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001, 
dated December 14, 2018, do all applicable actions identified in, 
and in accordance with, the Accomplishment Instructions of Boeing 
Alert Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001, 
dated December 14, 2018.

    Note 1 to paragraph (g): Guidance for accomplishing the actions 
required by this AD can be found in Boeing Alert Service Bulletin 
B787-81205-SB570036-00, Issue 001, dated December 14, 2018, which is 
referred to in Boeing Alert Requirements Bulletin B787-81205-
SB570036-00 RB, Issue 001, dated December 14, 2018.

(h) Exception to Service Information Specifications

    Where Boeing Alert Requirements Bulletin B787-81205-SB570036-00 
RB, Issue 001, dated December 14, 2018, specifies contacting Boeing 
for repair instructions: This AD requires doing the repair using a 
method approved in accordance with the procedures specified in 
paragraph (i) of this AD.

(i) 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 (j) of this AD. Information may be 
emailed to: <a href="/cdn-cgi/l/email-protection#c4fde9858a89e997a1a5b0b0a8a1e985878be985898b87e996a1b5b1a1b7b0b784a2a5a5eaa3abb2"><span class="__cf_email__" data-cfemail="b1889cf0fffc9ce2d4d0c5c5ddd49cf0f2fe9cf0fcfef29ce3d4c0c4d4c2c5c2f1d7d0d09fd6dec7">[email&#160;protected]</span></a>.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by The Boeing Company 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.

(j) Related Information

    For more information about this AD, contact Allen 
Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle 
ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and 
fax: 206-231-3528; email: <a href="/cdn-cgi/l/email-protection#195875757c77374b786c6a7a717c777d766b7f7c6b597f7878377e766f"><span class="__cf_email__" data-cfemail="793815151c17572b180c0a1a111c171d160b1f1c0b391f1818571e160f">[email&#160;protected]</span></a>.

(k) 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 Alert Requirements Bulletin B787-81205-SB570036-00 
RB, Issue 001, dated December 14, 2018.
    (ii) [Reserved]
    (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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (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, email <a href="/cdn-cgi/l/email-protection#ccaaa9a8bea9abe2a0a9abada08ca2adbeade2aba3ba"><span class="__cf_email__" data-cfemail="abcdcecfd9cecc85c7cecccac7ebc5cad9ca85ccc4dd">[email&#160;protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Des Moines, Washington, on October 29, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-24501 Filed 11-8-19; 8:45 am]
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