AD 2018-10-02

[Federal Register Volume 83, Number 92 (Friday, May 11, 2018)]
[Rules and Regulations]
[Pages 21867-21870]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2018-09747]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0398; Product Identifier 2017-NM-113-AD; Amendment 
39-19277; AD 2018-10-02]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 787-8 airplanes. This AD requires inspecting the 
part number of the occupant restraint system on the standard attendant 
seats, and doing additional inspections and corrective actions if 
necessary. This AD was prompted by a report of loose attachment bolts 
on the occupant restraint system on a standard attendant seat due to 
the bolts being over-torqued during production. We are issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective May 29, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 29, 
2018.
    We must receive comments on this AD by June 25, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 final rule, contact 
Boeing

[[Page 21868]]

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="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2018-0398.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2018-
0398; 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 final rule, 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: Julie Moon, Aerospace Engineer, Cabin 
Safety and Environmental Systems Section, Seattle ACO Branch, FAA, 2200 
South 216th St., Des Moines, WA 98198-6547; phone: 206-231-3571; email: 
<a href="/cdn-cgi/l/email-protection#a1cbd4cdc8c48fcccececfe1c7c0c08fc6ced7"><span class="__cf_email__" data-cfemail="b4dec1d8ddd19ad9dbdbdaf4d2d5d59ad3dbc2">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We have received a report of loose attachment bolts on the occupant 
restraint system on a standard attendant seat due to the bolts being 
over-torqued during production. One operator reported that a seat belt 
lower mount helicoil was detached from the seat pan lever while the 
attachment bolt was still threaded into the helicoil. Investigation 
revealed that the attachment bolt was probably over-torqued during 
production. Over-torqueing the attachment bolt could damage the bolt or 
the helicoil installation, and reduce the strength of the restraint 
system. Failure of the restraint system of the attendant seat during 
turbulence or a high-G load event could result in serious injury.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin B787-81205-SB250052-00, Issue 
001, dated January 27, 2014. This service information describes 
procedures for inspecting the part number of the occupant restraint 
system on the standard attendant seats, and doing additional 
inspections and corrective actions if necessary. The additional 
inspections include a general visual inspection for any gap of the 
interface of the lever and spacer, a general visual inspection for any 
flattened or stripped threads, verification that the lap belt bolt 
helicoil in the lever does not protrude beyond the bottom surface of 
the counterbore, and a general visual inspection for a visible metal 
shaving or fragments of the lap belt bolt and lever helicoil. 
Corrective actions include re-torqueing and reworking the bolts and 
lever. 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 issuing 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.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Difference Between this AD and the Service Information.''

Difference Between This AD and the Service Information

    Operators should note that, although the service bulletin 
recommends accomplishing the inspection of the occupant restraint 
system within 50 months (after the release of the service bulletin), 
the FAA has determined that accomplishing the inspection within five 
years after the effective date of this AD is adequate to address the 
identified unsafe condition. In developing an appropriate compliance 
time for this AD, we considered not only the manufacturer's 
recommendation, but the degree of urgency associated with addressing 
the unsafe condition, the average utilization of the affected fleet, 
and the time necessary to perform the inspection (one hour). In light 
of all of these factors, the FAA finds a five-year compliance time for 
completing the inspection is warranted, in that it represents an 
appropriate interval of time for affected airplanes to continue to 
operate without compromising safety. This difference has been 
coordinated with Boeing.

FAA's Justification and Determination of the Effective Date

    There are currently no domestic operators of this product. 
Therefore, we find that notice and opportunity for prior public comment 
are unnecessary and that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number FAA-2018-
0398 and Product Identifier 2017-NM-113-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule because of those comments.
    We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this final rule.

Costs of Compliance

    Currently, there are no affected U.S.-registered airplanes. If an 
affected airplane is imported and placed on the U.S. Register in the 
future, the following cost estimates to comply with this AD would 
apply:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Inspection for part number (P/N)..............  1 work-hour x $85 per hour = $85              $0             $85
Inspection of affected attendant seats........  2 work-hours x $85 per hour =                  0             170
                                                 $170.
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[[Page 21869]]

    We estimate the following costs to do any necessary rework that 
would be required based on the results of the inspections. We have no 
way of determining the number of aircraft that might need this rework:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Rework........................................  2 work-hours x $85 per hour =                 $0            $170
                                                 $170.
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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 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

    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):

2018-10-02 The Boeing Company: Amendment 39-19277; Docket No. FAA-
2018-0398; Product Identifier 2017-NM-113-AD.

(a) Effective Date

    This AD is effective May 29, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 787-8 airplanes, 
certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment/
furnishings.

(e) Unsafe Condition

    This AD was prompted by a report of loose attachment bolts on 
the occupant restraint system on a standard attendant seat due to 
the bolts being over-torqued. We are issuing this AD to address 
potential failure of the restraint system of the attendant seat 
during turbulence or a high-G load event, which could result in 
serious injury.

(f) Compliance

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

(g) Inspection and Applicable Corrective Actions

    Within 5 years after the effective date of this AD: Inspect the 
occupant restraint system on the standard attendant seats for any 
restraint system having a part number identified in the 
Accomplishment Instructions of Boeing Service Bulletin B787-81205-
SB250052-00, Issue 001, dated January 27, 2014.
    (1) For any affected occupant restraint system: Within 5 years 
after the effective date of this AD, inspect the affected attendant 
seat for discrepancies, including a general visual inspection for 
any gap of the interface of the lever and spacer, a general visual 
inspection for any flattened or stripped threads, verification that 
the lap belt bolt helicoil in the lever does not protrude beyond the 
bottom surface of the counterbore, and a general visual inspection 
for visible metal shavings or fragments of the lap belt bolt and 
lever helicoil; and do all applicable torqueing of the lap belt 
bolt, in accordance with the Accomplishment Instructions of Boeing 
Service Bulletin B787-81205-SB250052-00, Issue 001, dated January 
27, 2014.
    (2) For any discrepant attendant seat, before further flight 
rework the attachment bolt, the seat pan lever and bolts, and the 
dampener bolt, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin B787-81205-SB250052-00, Issue 001, dated 
January 27, 2014.

    Note 1 to paragraph (g) of this AD:  Guidance on the inspections 
and rework can be found in Goodrich Service Bulletin 2787-25-009, 
dated June 28, 2013.

(h) Inspection Definition

    For the purposes of this AD, a general visual inspection is: ``A 
visual examination of an interior or exterior area, installation, or 
assembly to detect obvious damage, failure, or irregularity. This 
level of inspection is made from within touching distance unless 
otherwise specified. A mirror may be necessary to ensure visual 
access to all surfaces in the inspection area. This level of 
inspection is made under normally available lighting conditions such 
as daylight, hangar lighting, flashlight, or droplight and may 
require removal or opening of access panels or doors. Stands, 
ladders, or platforms may be required to gain proximity to the area 
being checked.''

(i) Parts Installation Prohibition

    As of the effective date of this AD, no person may install an 
occupant restraint system having a part number identified in the 
Accomplishment Instructions of Boeing Service Bulletin B787-81205-
SB250052-00,

[[Page 21870]]

Issue 001, dated January 27, 2014, on any airplane.

(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 certification office, send it to the attention of the 
person identified in paragraph (k)(1) of this AD. Information may be 
emailed to: <a href="/cdn-cgi/l/email-protection#b78e9af6f9fa9ae4d2d6c3c3dbd29af6f4f89af6faf8f49ae5d2c6c2d2c4c3c4f7d1d6d699d0d8c1"><span class="__cf_email__" data-cfemail="31081c707f7c1c62545045455d541c70727e1c707c7e721c6354404454424542715750501f565e47">[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 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.

(k) Related Information

    (1) For more information about this AD, contact Julie Moon, 
Aerospace Engineer, Cabin Safety and Environmental Systems Section, 
Seattle ACO Branch, FAA, 2200 South 216th St., Des Moines, WA 98198-
6547; phone: 206-231-3571; email: <a href="/cdn-cgi/l/email-protection#f399869f9a96dd9e9c9c9db3959292dd949c85"><span class="__cf_email__" data-cfemail="ed8798818488c380828283ad8b8c8cc38a829b">[email&#160;protected]</span></a>.
    (2) For Goodrich service information identified in this AD, 
contact Goodrich Corporation, Aircraft Interior Products, ATTN: 
Technical Publications, 3414 South Fifth Street, Phoenix, AZ 85040-
1169; telephone 602-243-2200; internet <a href="http://www.goodrich.com/TechPubs">http://www.goodrich.com/TechPubs</a>.

(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 B787-81205-SB250052-00, Issue 001, 
dated January 27, 2014.
    (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, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Des Moines, Washington, on May 1, 2018.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-09747 Filed 5-10-18; 8:45 am]
 BILLING CODE 4910-13-P