[Federal Register Volume 83, Number 95 (Wednesday, May 16, 2018)]
[Rules and Regulations]
[Pages 22589-22592]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-10413]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0413; Product Identifier 2018-NM-061-AD; Amendment 
39-19283; AD 2018-10-08]
RIN 2120-AA64


Airworthiness Directives; Boeing Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2016-09-05, 
which applied to certain The Boeing Company Model 717-200 airplanes. AD 
2016-09-05 required a detailed inspection for distress of the vertical

[[Page 22590]]

stabilizer leading edge skin, and related investigative and corrective 
actions if necessary. It also required, for certain airplanes, 
repetitive inspections of the front spar cap for any loose or missing 
fasteners, or any cracking, and related investigative and corrective 
actions if necessary. This AD requires repetitive inspections for 
distress, cracking, and loose or missing fasteners in the vertical 
stabilizer leading edge skin and front spar cap, with new compliance 
times for certain airplanes. This AD was prompted by reports of 
cracking in the leading edge of the vertical stabilizer and front spar 
web. We are issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective May 31, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 31, 
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-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 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 https://www.myboeingfleet.com. 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 http://www.regulations.gov by searching 
for and locating Docket No. FAA-2018-0413.

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-
0413; 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 street address for Docket Operations (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Muoi Vuong, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5205; fax: 562-627-
5210; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued AD 2016-09-05, Amendment 39-18503 (81 FR 26673, May 4, 
2016) (``AD 2016-09-05''), for certain The Boeing Company Model 717-200 
airplanes. AD 2016-09-05 required a detailed inspection for any 
distress of the vertical stabilizer leading edge skin, and related 
investigative and corrective actions if necessary. It also required, 
for certain airplanes, repetitive detailed inspections of the front 
spar cap for any loose or missing fasteners, repetitive eddy current 
testing high frequency (ETHF) and radiographic testing (RT) inspections 
of the front spar cap for any crack, and related investigative and 
corrective actions if necessary. AD 2016-09-05 resulted from reports of 
10 cases of elongated fastener holes in the vertical stabilizer leading 
edge. We issued AD 2016-09-05 to address cracking in the vertical 
stabilizer leading edge and front spar cap, which may result in the 
structure becoming unable to support limit load, and may lead to the 
loss of the vertical stabilizer.

Actions Since AD 2016-09-05 Was Issued

    Since we issued AD 2016-09-05, four cases of elongated fastener 
holes in the vertical stabilizer leading edge and nine cases of front 
spar cap damage or cracks were reported. Seven of the nine cases 
involved small cracks of approximately 0.3 inch in the front spar cap. 
Two of the nine cases involved a severed front spar cap and front spar 
web cracking, and one also involved skin cracking. The longest cracks, 
4.5 inches in length, were discovered in the left skin of the vertical 
stabilizer leading edge and the front spar web of a Boeing Model 717-
200 airplane during an initial inspection required by AD 2016-09-05. We 
determined that for airplanes on which an initial inspection has not 
been done as specified in AD 2016-09-05, a revised compliance time is 
needed. We are issuing this AD to address the unsafe condition on these 
products.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 717-55A0012, Revision 1, 
dated April 11, 2018. The service information describes procedures for 
doing detailed inspections of the front spar cap for any loose or 
missing fasteners, ETHF or RT inspections for distress and for cracking 
in the vertical stabilizer leading edge and front spar cap at the 
splice at station Zfs=52.267, and applicable on-condition actions. 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

    Although this AD does not explicitly restate the requirements of AD 
2016-09-05, this AD would retain the requirements of AD 2016-09-05, 
with revised compliance times for airplanes that have not completed the 
requirements of AD 2016-09-05. The requirements of AD 2016-09-05 are 
referenced in the service information identified previously, which, in 
turn, is referenced in paragraph (g) of this AD.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comment prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because cracks in the vertical stabilizer leading edge and front spar 
cap could result in the structure becoming unable to support limit 
load, and may lead to the loss of the vertical stabilizer. Therefore, 
we find good cause that notice and opportunity for prior public comment 
are impracticable. In addition, for the reason(s) stated above, we find 
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

[[Page 22591]]

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-2018-0413 and Product Identifier 2018-NM-061-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 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 final rule.

Costs of Compliance

    We estimate that this AD affects 106 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
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                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections for distress         11 work-hours x $85 per              $0  $935 per            $99,110 per
 (retained actions from AD 2016-  hour = $935 per                          inspection cycle.   inspection cycle.
 09-05).                          inspection cycle.
Repetitive inspections for       7 work-hours x $85 per                0  $595 per            $63,070 per
 cracking and loose or missing    hour = $595 per                          inspection cycle.   inspection cycle.
 fasteners (retained actions      inspection cycle.
 from AD 2016-09-05).
----------------------------------------------------------------------------------------------------------------

    The new requirements of this AD add no additional economic burden.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this 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 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 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 removing Airworthiness Directive (AD) 
2016-09-05, Amendment 39-18503 (81 FR 26673, May 4, 2016), and adding 
the following new AD:

2018-10-08 The Boeing Company: Amendment 39-19283; Docket No. FAA-
2018-0413; Product Identifier 2018-NM-061-AD.

(a) Effective Date

    This Airworthiness Directive (AD)is effective May 31, 2018.

(b) Affected ADs

    This AD replaces AD 2016-09-05, Amendment 39-18503 (81 FR 26673, 
May 4, 2016) (``AD 2016-09-05'').

(c) Applicability

    This AD applies to The Boeing Company Model 717-200 airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin 717-55A0012, Revision 1, dated April 11, 2018.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by multiple reports of the vertical 
stabilizer leading edge showing signs of fastener distress, multiple 
cracked or severed front spar caps, and cracks in the left skin of 
the vertical stabilizer leading edge and in the front spar web, 
discovered during initial inspections required by AD 2016-09-05. We 
have determined that a revised compliance time is needed for 
airplanes on which the initial inspection has not been done as 
specified in AD 2016-09-05. We are issuing this AD to address 
cracking in the vertical stabilizer leading edge and front spar cap, 
which may result in the structure becoming unable to support limit 
load, and may lead to loss of the vertical stabilizer.

(f) Compliance

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

[[Page 22592]]

(g) Required Actions

    Except as required by paragraph (h) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 717-55A0012, Revision 1, dated April 
11, 2018, do all applicable actions identified as ``RC'' (required 
for compliance) in, and in accordance with, the Accomplishment 
Instructions of Boeing Alert Service Bulletin 717-55A0012, Revision 
1, dated April 11, 2018.

(h) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements 
of this AD: Where Boeing Alert Service Bulletin 717-55A0012, 
Revision 1, dated April 11, 2018, uses the phrase ``the Revision 1 
issue date of this service bulletin,'' this AD requires using the 
effective date of this AD.
    (2) Where Boeing Alert Service Bulletin 717-55A0012, Revision 1, 
dated April 11, 2018, specifies contacting Boeing, and specifies 
that action as RC: This AD requires repair using a method approved 
in accordance with the procedures specified in paragraph (j) of this 
AD.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the initial inspection 
specified in paragraph (g) of this AD, if that inspection was 
performed before June 8, 2016 (the effective date of AD 2016-09-05), 
using Boeing MOM-MOM-14-0437-01B(R1), dated July 3, 2014. This 
service information is not incorporated by reference in this AD.
    (2) 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 717-
55A0012, dated June 12, 2015. This service information was 
incorporated by reference in AD 2016-09-05.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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: [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, Los Angeles 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 2016-09-05 are approved as 
AMOCs for the corresponding provisions of Boeing Alert Service 
Bulletin 717-55A0012, Revision 1, dated April 11, 2018, that are 
required by paragraph (g) of this AD.
    (5) Except as required by paragraph (h)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (j)(5)(i) and 
(j)(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.

(k) Related Information

    (1) For more information about this AD, contact: Muoi Vuong, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5205; fax: 562-627-5210; email: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) of this AD.

(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 Alert Service Bulletin 717-55A0012, Revision 1, dated 
April 11, 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 https://www.myboeingfleet.com.
    (4) You may view this service information at 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Des Moines, Washington, on May 8, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-10413 Filed 5-15-18; 8:45 am]
 BILLING CODE 4910-13-P


