Document ID: FAA-2018-0789-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2018-09-10T04:00Z

[Federal Register Volume 83, Number 175 (Monday, September 10, 2018)]
[Rules and Regulations]
[Pages 45550-45554]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19437]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0789; Product Identifier 2018-NM-120-AD; Amendment 
39-19395; AD 2018-18-16]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2018-12-08, 
which applied to certain Airbus SAS Model A330-200 and -300 series 
airplanes, and Model A340-212, -213, -312, and -313 airplanes. AD 2018-
12-08 required repetitive inspections of certain fastener holes, and 
related investigative and corrective actions if necessary. This new AD 
corrects certain compliance time references. This AD was prompted by a 
report of cracking at fastener holes located at a certain frame (FR) on 
the lower shell panel junction. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective September 25, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 22, 
2018 (83 FR 33821, July 18, 2018).
    We must receive comments on this AD by October 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:
     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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this final rule, contact 
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 
2, 31700 Blagnac

[[Page 45551]]

Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; 
email: [email protected]; internet: http://www.airbus.com. You may view this referenced 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-
0789.

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-
0789; 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 AD, the regulatory evaluation, any comments received, and 
other information. The street address for Docket Operations (telephone 
800-647-5527) is listed above. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued AD 2018-12-08, Amendment 39-19312 (83 FR 33821, July 18, 
2018) (``AD 2018-12-08''), which applied to certain Airbus SAS Model 
A330-200 and -300 series airplanes, and Model A340-212, -213, -312, and 
-313 airplanes. AD 2018-12-08 was prompted by a report of cracking at 
fastener holes located at FR40 on the lower shell panel junction. AD 
2018-12-08 required repetitive inspections of certain fastener holes, 
and related investigative and corrective actions if necessary. We 
issued AD 2018-12-08 to address cracking at FR40 on the lower shell 
panel junction; such cracking could lead to reduced structural 
integrity of the fuselage.
    Since we issued AD 2018-12-08, we have determined that it is 
necessary to correct certain service bulletin table references, which 
provide the compliance times for the initial inspection. Table 1 to 
paragraph (g)(1) of AD 2018-12-08 pointed to ``table 1'' of the service 
information for the initial compliance time. However, table 2 and table 
3 in the service bulletins also apply to certain airplanes (those in 
Configuration 1). All airplanes belonging to affected U.S. operators 
are in Configuration 2 or Configuration 3, which use only table 1 in 
the service bulletins. This AD corrects the service bulletin table 
references for the compliance times. We have changed table 1 to 
paragraph (g)(1) of this AD by removing the limitation to ``table 1'' 
of the service bulletins, and instead referring to the compliance times 
in ``paragraph 1.E., `Compliance,' '' of the service bulletins.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0063, dated April 12, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus SAS Model A330-200, 
A330-300, and A340-200 series airplanes, and Model A340-312 and -313 
airplanes. The MCAI states:

    During full scale fatigue test of the Frame (FR) 40 to fuselage 
skin panel junction, fatigue damage was found. Corrective actions 
consisted of in-service installation of an internal reinforcing 
strap on the related junction, as currently required by DGAC 
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France AD 
1999-448-126(B), which refers to Airbus Service Bulletin (SB) A340-
53-4104 Revision 02, and [DGAC] AD 2001-070(B), which refers to 
Airbus SB A330-53-3093 Revision 04; retrofit improvement of internal 
reinforcing strap fatigue life through recommended Airbus SB A330-
53-3145; and introducing a design improvement in production through 
Airbus mod 44360.
    After those actions were implemented, cracks were found on both 
left-hand (LH) and right-hand (RH) sides on internal strap, butt 
strap, keel beam fitting, or forward fitting FR40 flange. These 
findings were made during embodiment of a FR40 web repair on an A330 
aeroplane, and during keel beam replacement on an A340 aeroplane, 
where the internal strap was removed and a special detailed 
inspection (SDI) was performed on several holes.
    This condition, if not detected and corrected, could affect the 
structural integrity of the centre fuselage of the aeroplane.
    Prompted by these findings, Airbus issued SB A330-53-3215 and SB 
A340-53-4215, providing inspection instructions. Consequently, EASA 
issued AD 2014-0136 [which corresponds to FAA AD 2017-07-07, 
Amendment 39-18845 (82 FR 18547, April 20, 2017) (``AD 2017-07-
07'')] to require repetitive SDI (rototest) of 10 fastener holes 
located at the FR40 lower shell panel junction on both LH and RH 
sides and, depending on findings, accomplishment of applicable 
corrective action(s).
    Since that [EASA] AD was issued, prompted by the results of 
complementary fatigue analyses, it was determined that postmod 55792 
aeroplanes could be also affected by crack initiation and 
propagation at this area of the fuselage. These analyses 
demonstrated that post-mod 55792 aeroplanes must follow the same 
maintenance program as aeroplanes in postmod 55306 and pre-mod 55792 
configuration. Consequently, Airbus published SB A330-53-3215 
Revision 02 and SB A340-53-4215 Revision 02 to expand the 
Effectivity accordingly.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0136, which is superseded, which now 
also apply to aeroplanes in post-mod 55792 configuration [the 
applicability identifies airplanes in post-mod 44360 configuration].

    AD 2017-07-07 included Model A340-211 airplanes in its 
applicability. Airbus SAS Model A340-211 airplanes are not identified 
in the applicability of this AD because those airplanes are not 
affected by the identified unsafe condition. All of those airplanes are 
in the pre-Airbus SAS modification 44360 configuration. The MCAI also 
does not include Model A340-211 airplanes in its applicability.
    The compliance time ranges between 20,000 flight cycles or 65,400 
flight hours and 20,800 flight cycles or 68,300 flight hours, depending 
on airplane utilization and configuration. The repetitive inspection 
interval ranges between 14,000 flight cycles or 95,200 flight hours and 
24,600 flight cycles or 98,700 flight hours, depending on airplane 
utilization and configuration.
    You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0789.

Related Service Information Under 1 CFR Part 51

    Airbus SAS has issued Service Bulletin A330-53-3215, Revision 03, 
dated January 22, 2018; and Service Bulletin A340-53-4215, Revision 02, 
dated November 23, 2016. This service information describes procedures 
for repetitive rototest inspections of certain fastener holes, and 
related investigative and corrective actions if necessary. These 
documents are distinct since they apply to different airplane models. 
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 and Requirements of This AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the

[[Page 45552]]

MCAI and service information referenced above. We are issuing this AD 
because we evaluated all pertinent information and determined the 
unsafe condition exists and is likely to exist or develop on other 
products of the same type design.

FAA's Justification and Determination of the Effective Date

    This AD corrects an error that affects compliance for non-U.S.-
registered airplanes only. Therefore, we find good cause that notice 
and opportunity for prior public comment are unnecessary. In addition, 
for the reason 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 we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2018-0789; Product 
Identifier 2018-NM-120-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

    We estimate that this AD affects 99 airplanes of U.S. registry. 
This AD adds no new economic burden. The current costs for this AD are 
repeated for the convenience of affected operators, as follows:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
42 work-hours x $85 per hour = $3,570........................              $0           $3,570         $353,430
----------------------------------------------------------------------------------------------------------------

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

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
46 work-hours x $85 per hour = $3,910.          $2,358           $6,268
------------------------------------------------------------------------

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 and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    We 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 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.

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) 
2018-12-08, Amendment 39-19312 (83 FR 33821, July 18, 2018), and adding 
the following new AD:

2018-18-16 Airbus SAS: Amendment 39-19395; Docket No. FAA-2018-0789; 
Product Identifier 2018-NM-120-AD.

[[Page 45553]]

(a) Effective Date

    This AD is effective September 25, 2018.

(b) Affected ADs

    This AD replaces AD 2018-12-08, Amendment 39-19312 (83 FR 33821, 
July 18, 2018) (``AD 2018-12-08'').

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) and (c)(2) of this AD, all 
manufacturer serial numbers on which Airbus SAS Modification 44360 
has been embodied in production.
    (1) Airbus SAS Model A330-201, -202, -203, -223, -243, -301, -
302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus SAS Model A340-212, -213, -312, and -313 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a report of cracking at fastener holes 
located at frame (FR) 40 on the lower shell panel junction. We are 
issuing this AD to address this cracking, which could lead to 
reduced structural integrity of the fuselage.

(f) Compliance

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

(g) Retained Compliance Times for Paragraph (h) of This AD, With 
Corrected Compliance Time Locations

    This paragraph restates the requirements of paragraph (g) of AD 
2018-12-08, with corrected compliance time locations in table 1 to 
paragraph (g)(1) of this AD. Accomplish the actions required by 
paragraph (h) of this AD at the times specified in paragraphs (g)(1) 
and (g)(2) of this AD, as applicable.
    (1) For airplanes having serial numbers 0176 through 0915 
inclusive: Within the compliance times defined in table 1 to 
paragraph (g)(1) of this AD, and thereafter at intervals not to 
exceed the compliance times defined in Airbus Service Bulletin A330-
53-3215, Revision 03, dated January 22, 2018 (``SB A330-53-
3215R3''); or Airbus Service Bulletin A340-53-4215, Revision 02, 
dated November 23, 2016 (``SB A340-53-4215R2''); as applicable, 
depending on airplane utilization and configuration. As of August 
22, 2108 (the effective date of AD 2018-12-08), where paragraph 
1.E., ``Compliance,'' of SB A330-53-3215R3, specifies weight variant 
(WV) 050 in the condition column of table 1, configuration 003, for 
the purposes of this AD, WV060 and WV080 are also included.
[GRAPHIC] [TIFF OMITTED] TR10SE18.004

    (2) For all airplanes except those identified in paragraph 
(g)(1) of this AD: Before exceeding the applicable compliance time 
``threshold'' defined in paragraph 1.E., ``Compliance,'' of SB A330-
53-3215R3 or SB A340-53-4215R2, as applicable, depending on airplane 
utilization and configuration and to be counted from airplane first 
flight, and, thereafter, at intervals not to exceed the compliance 
times specified in paragraph 1.E., ``Compliance,'' of SB A330-53-
3215R3 or SB A340-53-4215R2, as applicable, depending on airplane 
utilization and configuration. Where paragraph 1.E., ``Compliance,'' 
of SB A330-53-3215R3 specifies weight variant WV050 in the condition 
column of table 1, configuration 003, for the purposes of this AD, 
WV060 and WV080 are also included.

(h) Retained Repetitive Inspections and Related Investigative and 
Corrective Actions, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2018-12-08, with no changes. At the applicable compliance time 
specified in paragraph (g) of this AD: Accomplish a special detailed 
inspection of the 10 fastener holes located at FR40 on the lower 
shell panel junction on both left-hand and right-hand sides, in 
accordance with the Accomplishment Instructions of SB A330-53-3215R3 
or SB A340-53-4215R2, as applicable.
    (1) If, during any inspection required by the introductory text 
of paragraph (h) of this AD, any crack is detected, before further 
flight, accomplish all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of SB A330-53-3215R3 or SB A340-53-4215R2, as 
applicable; except, where SB A330-53-3215R3 or SB A340-53-4215R2 
specifies to contact Airbus SAS for repair instructions, and 
specifies that action as ``RC'' (required for compliance), this AD 
requires repair before further flight using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (2) If, during any inspection required by the introductory text 
of paragraph (h) of this AD, the diameter of a fastener hole is 
found to be outside the tolerances of the transition fit as 
specified in SB A330-53-3215R3 or SB A340-53-4215R2, as applicable, 
and SB A330-53-3215R3 or SB A340-53-4215R2 specifies to contact 
Airbus SAS for repair instructions, and specifies that action as RC, 
before further flight, repair using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Accomplishment of corrective actions, as required by 
paragraph (h)(1) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (h) of this AD.
    (4) Accomplishment of a repair on an airplane, as required by 
paragraph (h)(2) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (h) of this AD for that airplane, unless indicated 
otherwise as specified in the method approved by the Manager, 
International Section, Transport Standards Branch, FAA; or EASA; or 
Airbus SAS's EASA DOA.

[[Page 45554]]

(i) Retained Reporting Provision, With No Changes

    This paragraph restates the provisions of paragraph (i) of AD 
2018-12-08, with no changes. Although SB A330-53-3215R3 and SB A340-
53-4215R2 specify to submit certain information to the manufacturer, 
and specify that action as RC, this AD does not include that 
requirement.

(j) Retained Credit for Previous Actions, With Revised Formatting

    This paragraph restates the provisions of paragraph (j) of AD 
2018-12-08, with a reformatted service bulletin listing. This 
paragraph provides credit for the inspections required by the 
introductory text of paragraph (h) of this AD and the related 
investigative and corrective actions specified by paragraph (h)(1) 
of this AD, if those actions were performed before May 25, 2017 (the 
effective date of AD 2017-07-07), using the applicable service 
information specified in paragraphs (j)(1) through (j)(5) of this 
AD.
    (1) Airbus Service Bulletin A330-53-3215, dated June 21, 2013.
    (2) Airbus Service Bulletin A330-53-3215, Revision 01, dated 
April 17, 2014.
    (3) Airbus Service Bulletin A330-53-3215, Revision 02, dated 
November 23, 2016.
    (4) Airbus Service Bulletin A340-53-4215, dated June 21, 2013.
    (5) Airbus Service Bulletin A340-53-4215, Revision 01, dated 
April 17, 2014.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards 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 International Section, send it to the attention of 
the person identified in paragraph (l)(2) of this AD. Information 
may be emailed to [email protected]. 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.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as specified by 
paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (i) of this AD: If 
any service information contains procedures or tests that are 
identified as RC, those procedures and tests must be done to comply 
with this AD; any procedures or tests that are not identified as RC 
are recommended. Those procedures and tests that are not identified 
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 procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0063, dated April 12, 2017, for related 
information. This MCAI may be found in the AD docket on the internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2018-0789.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax: 206-231-3229.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(4) and (m)(5) of this AD.

(m) 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 this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
August 22, 2018.
    (i) Airbus Service Bulletin A330-53-3215, Revision 03, dated 
January 22, 2018.
    (ii) Airbus Service Bulletin A340-53-4215, Revision 02, dated 
November 23, 2016.
    (4) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 45 80; email: [email protected]; 
internet: http://www.airbus.com.
    (5) 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.
    (6) 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 August 29, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-19437 Filed 9-7-18; 8:45 am]
 BILLING CODE 4910-13-P