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2020-13-01 DAHER AIRCRAFT DESIGN, LLC (TYPE CERTIFICATE PREVIOUSLY HELD BY QUEST AIRCRAFT DESIGN, LLC) (FAA CORRECTION): Amendment 39-21146; Docket No. FAA-2018-0180; Project Identifier 2017-CE-043-AD.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective August 17, 2020.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This  AD  applies  to Daher  Aircraft  Design,  LLC (type  certificate
    previously  held  by Quest  Aircraft  Design, LLC),  Model  KODIAK 100
    airplanes, all serial numbers, certificated in any category.

(d) SUBJECT

    Joint Aircraft System Component (JASC)/Air Transport Association (ATA)
    of America Code 32, Landing Gear.

(e) UNSAFE CONDITION

    This  AD was  prompted by  reports from  the manufacturer  of  fatigue
    cracks on the nose landing gear (NLG) fork. The FAA is issuing this AD
    to detect  and prevent  fatigue cracking  of the  NLG fork. The unsafe
    condition, if  not corrected,  could result  in separation  of the NLG
    fork  with consequent  reduced control  on landing.  If the  NLG  fork
    separates on an unimproved surface, the risk of the NLG digging in and
    the airplane overturning on the ground increases.

(f) COMPLIANCE

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

(g) INSPECTION FOR TYPE OF NLG FORK

    Within  25  hours time-in-service  (TIS)  after August  17,  2020 (the
    effective date of  this AD), inspect  the airplane to  determine if an
    NLG fork part number  (P/N) 100-410-7001 (type A)  or an NLG fork  P/N
    100-410-7013 (type B) is installed. If you determine that an NLG  fork
    P/N  100-410-7013  (type B)  is  installed during  the  inspection, no
    further action is required by this AD. If a review of the  maintenance
    records can identify the P/N NLG fork that is installed, you may use a
    maintenance  records  review in  lieu  of inspecting  the  airplane to
    determine if an NLG fork P/N 100-410-7001 (type A) or an NLG fork  P/N
    100-410-7013 (type B) is installed.

(h) INSPECTION OF THE NLG FORK FOR CRACKS

(1) If  you  determine  that  an NLG  fork  P/N 100-410-7001  (type  A) is
    installed during the inspection required by paragraph (g) of this  AD,
    within 25 hours TIS after August 17, 2020 (the effective date of  this
    AD) and  thereafter at  intervals not  to exceed  200 hours  TIS, do a
    fluorescent  penetrant,  dye  penetrant,  or  open-hole  eddy  current
    inspection  of  the  NLG  fork  for  cracks  by  following  section 5.
    Instructions  in  Quest Aircraft  Field  Service Instruction  FSI-147,
    Revision 00, Release Date January 29, 2018.

(2) If you find any cracks of the NLG fork during any inspection  required
    by paragraph (h)(1) of this AD, before further flight, replace the NLG
    fork with an  NLG fork P/N  100-410-7013 (type B).  Replacement of the
    NLG fork  with an  NLG fork  P/N 100-410-7013  (type B) terminates the
    repetitive inspections  required by  paragraphs (h)(1)  and (i)(1)  of
    this AD.

(i) INSPECTION OF THE SHIMMY DAMPER BRACKET

(1) If you have not replaced an NLG fork P/N 100-410-7001 (type A) per the
    initial inspection  and replacement  requirements in  paragraph (h) of
    this AD, then within 25 hours TIS after August 17, 2020 (the effective
    date of this AD) and thereafter  at intervals not to exceed 200  hours
    TIS (until the NLG fork is  replaced with a P/N 100-410-7013 (type  B)
    fork), inspect the  shimmy damper bracket  for looseness, and  inspect
    the shimmy  damper system  for damaged  (loose, leaking,  corroded, or
    worn) components, by following pages 32_110 and 32_111, section  3252,
    Shimmy Damper, found  in Chapter 32,  Landing Gear, of  Quest Aircraft
    Company Kodiak 100 Maintenance Manual, Revision No. 21, dated February
    15, 2017.

(2) If  a  loose shimmy  damper  bracket  is found  during any  inspection
    required by  paragraph (i)(1)  of this  AD, rework  the shimmy  damper
    bracket with interference-fit bolts by following Quest Aircraft  Field
    Service Instruction FSI-146, Revision 00, Release Date April 18, 2017.
    Reworking the  shimmy damper  bracket with  the interference-fit bolts
    terminates the repetitive inspections required by paragraph (i)(1)  of
    this AD.

(3) If any other damaged components are found in the shimmy damper  system
    during any inspection required by paragraph (i)(1) of this AD,  before
    further flight, replace the damaged components.

(j) OPTIONAL TERMINATING ACTION

    In lieu of the NLG fork and shimmy damper bracket inspections required
    by paragraphs (h)(1) and  (i)(1) of this AD,  you may replace the  NLG
    fork P/N 100-410-7001 (type A) with an NLG fork P/N 100-410-7013 (type
    B). This  replacement terminates  the inspection  requirements of this
    AD, and no further actions are required.

(k) RESTRICTION OF NLG FORK P/N 100-410-7001 (TYPE A) INSTALLATION

    Once  an  NLG  fork  P/N 100-410-7013  (type  B)  is  installed on  an
    airplane, do not install an NLG fork P/N 100-410-7001 (type A). If  an
    NLG fork P/N  100-410-7013 (type B)  is removed from  the airplane for
    any reason (for example, to install floats), you must reinstall an NLG
    fork P/N 100-410-7013 (type B) when operating with wheels.

(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)  of  this AD.  Information  may also  be
    emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.

(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.

(m) RELATED INFORMATION

    For more information about  this AD, contact Wade  Sullivan, Aerospace
    Engineer,  Aerospace  Engineer,  Airframe  Section,  FAA,  Seattle ACO
    Branch, 2200  South 216th  St., Des  Moines, WA  98198; phone and fax:
    206-231-3530; email: Wade.Sullivan@faa.gov.

(n) MATERIAL INCORPORATED BY REFERENCE

(1) The  Director of  the Federal  Register approved  the incorporation by
    reference 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.

(3) The following service information  was approved for IBR on  August 17,
    2020 (85 FR 41906, July 13, 2020).

(i) Pages  32_110 and  32_111, section  3252, Shimmy  Damper, Chapter  32,
    Landing Gear, of Quest Aircraft Company Kodiak 100 Maintenance Manual,
    Revision No. 21, dated February 15, 2017.

(ii) Quest  Aircraft  Field  Service  Instruction  FSI-146,  Revision  00,
     Release Date April 18, 2017.

NOTE 1 TO PARAGRAPH (N)(2)(II) OF THIS AD: The  Release Date is a pen-and-
ink addition  that appears  only on  the Revision  Notice transmitted with
FSI-146.

(iii) Quest  Aircraft  Field  Service  Instruction  FSI-147,  Revision 00,
      Release Date January 29, 2018.

NOTE 2 TO PARAGRAPH (N)(2)(III) OF THIS AD: The Release Date is a  pen-and
-ink addition that  appears only on  the Revision Notice  transmitted with
FSI-147.

(4) For service information identified in this AD, contact Kodiak Aircraft
    Company,  Inc., 1200  Turbine  Drive,  Sandpoint, Idaho  83864; phone:
    (208)  263-1111  or  1  (866)  263-1112;  email: KodiakCare@daher.com;
    internet: http://Kodiak.aero/support.

(5) You may view this  service information  at the FAA, Airworthiness Pro-
    ducts Section,  Operational Safety  Branch, 901  Locust, Kansas  City,
    Missouri 64106. For information  on the availability of  this material
    at the FAA, call 816-329-4148.

(6) You may view this  service information that is  incorporated by refer-
    ence at the National  Archives and Records Administration  (NARA). For
    information  on  the  availability of  this  material  at NARA,  email
    fedreg.legal@nara.gov,  or   go  to   https://www.archives.gov/federal
    -register/cfr/ibrlocations.html.

Issued on  August 3,  2020. Ross  Landes, Deputy  Director for  Regulatory
Operations, Compliance  & Airworthiness  Division, Aircraft  Certification
Service.

FOR  FURTHER  INFORMATION  CONTACT:  Wade  Sullivan,  Aerospace  Engineer,
Airframe  Section, FAA,  Seattle ACO  Branch, 2200  South 216th  St., Des
Moines,    WA    98198;    phone    and    fax:    206-231-3530;    email:
Wade.Sullivan@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration


14 CFR Part 39

[Docket No. FAA-2018-0180; Project Identifier 2017-CE-043-AD; Amendment
39-21146; AD 2020-13-01]
RIN 2120-AA64

Airworthiness Directives; Daher Aircraft Design, LLC (Type
Certificate Previously Held by Quest Aircraft Design, LLC), Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; correction.

-----------------------------------------------------------------------

SUMMARY: The FAA is correcting an airworthiness directive (AD) that
published in the Federal Register. The AD applies to all Daher Aircraft
Design, LLC (type certificate previously held by Quest Aircraft Design,
LLC), Model KODIAK 100 airplanes. As published, the type certificate
(TC) holder in the regulatory heading that identifies the AD is
incorrect. This document corrects that error. In all other respects,
the original document remains the same; however, for clarity, the FAA
is publishing the entire rule in the Federal Register.

DATES: This correction is effective August 17, 2020. The effective date
of AD 2020-13-01 remains August 17, 2020.

The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 17,
2020 (85 FR 41906, July 13, 2020).

ADDRESSES: For service information identified in this final rule,
contact Kodiak Aircraft Company, Inc., 1200 Turbine Drive, Sandpoint,
Idaho 83864; phone: (208) 263-1111 or 1 (866) 263-1112; email:
KodiakCare@daher.com; internet: http://Kodiak.aero/support. You may
view this referenced service information at the FAA, Airworthiness
Products Section, Operational Safety Branch, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call 816-329-4148. It is also
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2018-0180.

Examining the AD Docket


You may examine the AD docket on the internet at
https://www.regulations.gov; 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, any comments received, and
other information. The address for Docket Operations is Docket
Management Facility, 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: Wade Sullivan, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3530; email:
Wade.Sullivan@faa.gov.

SUPPLEMENTARY INFORMATION: As published, AD 2020-13-01, Amendment 39-
21146 (85 FR 41906, July 13, 2020), applies to all Daher Aircraft
Design, LLC (type certificate previously held by Quest Aircraft Design,
LLC), Model KODIAK 100 airplanes. AD 2020-13-01 requires a one-time
inspection to determine if an affected nose landing gear (NLG) fork is
installed, repetitive inspections of the affected NLG fork for cracks,
repetitive inspections of the shimmy damper bracket for looseness and
of the shimmy damper system for damaged components if an affected NLG
fork is installed, and rework/replacement of parts as necessary.

Need for the Correction


As published, the TC holder in the regulatory heading that
identifies the AD is incorrect. The heading incorrectly identified the
TC holder as "Quest Aircraft Design, LLC." The correct TC holder is
Daher Aircraft Design, LLC (Type Certificate previously held by Quest
Aircraft Design, LLC).

Although no other part of the preamble or regulatory information
has been corrected, for clarity, the FAA is publishing the entire rule
in the Federal Register.

The effective date of this AD remains August 17, 2020.

Related Service Information Under 1 CFR Part 51


The FAA reviewed Quest Aircraft Field Service Instruction FSI-147,
Revision 00, Release Date January 29, 2018, which provides instructions
for inspection and, if necessary, replacement of the NLG fork. The FAA
reviewed pages 32_110 and 32_111, section 3252, Shimmy Damper, Chapter
32, Landing Gear, of Quest Aircraft Company Kodiak 100 Maintenance
Manual, Revision No. 21, dated February 15, 2017, which contains
procedures for inspecting the shimmy damper system. The FAA also
reviewed Quest Aircraft Field Service Instruction FSI-146, Revision 00,
Release Date April 18, 2017, which provides instructions for modifying
the shimmy damper attach bracket. 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.

Good Cause for Adoption Without Prior Notice


Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and
comment procedures for rules when the agency for "good cause" finds
that those procedures are "impracticable, unnecessary, or contrary to
the public interest." Section 553(d)(3) of the APA requires that
agencies publish a rule not less than 30 days before its effective
date, except as otherwise provided by the agency for good cause found
and published with the rule.

Since this action only corrects the TC holder in a regulatory
heading, the FAA finds that notice and public comment under 5 U.S.C.
553(b) is unnecessary. For the same reason, the FAA finds that good
cause exists under 5 U.S.C. 553(d) for making this rule effective in
less than 30 days.

List of Subjects in 14 CFR Part 39


Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Correction


Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Corrected]


2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):