Document ID: FAA-2018-0180-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Quest Aircraft Design, LLC Airplanes
Posted Date: 2018-03-08T05:00Z

[Federal Register Volume 83, Number 46 (Thursday, March 8, 2018)]
[Proposed Rules]
[Pages 9820-9822]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-04650]

[[Page 9820]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0180; Product Identifier 2017-CE-043-AD]
RIN 2120-AA64

Airworthiness Directives; Quest Aircraft Design, LLC Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Quest Aircraft Design, LLC Model KODIAK 100 airplanes. This proposed AD 
was prompted by reports of cracks found in certain nose landing gear 
forks. This proposed AD would require a one-time inspection to 
determine if the affected nose landing gear fork is installed, 
repetitive inspections of the affected nose landing gear fork for 
cracks, repetitive inspections of the shimmy damper bracket for 
looseness if the affected nose landing gear fork is installed, and 
rework/replacement of parts as necessary. We are proposing this AD to 
address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by April 23, 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 NPRM, contact Quest 
Aircraft Company LLC, 1200 Turbine Drive, Sandpoint, Idaho 83864; 
phone: (208) 263-1111 or 1 (866) 263-1112; email: 
[email protected]; internet: http://customercare.questaircraft.com/. You may view this service information 
at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, 
Missouri 64106. For information on the availability of this material at 
the FAA, call (816) 329-4148.

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-
0180; 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 NPRM, 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: Wade Sullivan, Aerospace Engineer, 
Seattle ACO Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057; phone: 
425-917-6430; fax: 425-917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0180; 
Product Identifier 2017-CE-043-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

    We received reports from the manufacturer of fatigue cracks on the 
nose landing gear (NLG) fork on Quest Aircraft Design, LLC Model KODIAK 
100 airplanes. In one report, the NLG fork failed during landing. On 
unimproved surfaces, the NLG shimmy damper system can wear and loosen, 
reducing the resistance of the nose gear to shimmy. Shimmying puts side 
loads on the NLG fork that it was not designed for, which could cause 
fatigue cracks. This condition, if not corrected, could result in 
separation of the fork with consequent reduced control on landing. If 
the fork separates on an unimproved surface, the risk of the NLG 
digging in and the airplane overturning on the ground increases.

Related Service Information Under 1 CFR Part 51

    We reviewed Quest Aircraft Field Service Instruction FSI-147, 
Revision 00 (not dated), which provides instructions for inspection 
and, if necessary, replacement of the NLG fork. We reviewed 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, which describes procedures 
for inspecting the shimmy damper system. We also reviewed Quest 
Aircraft Field Service Instruction FSI-146, Revision 00 (not dated), 
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.

FAA's Determination

    We are proposing 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.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously.

Costs of Compliance

    We estimate that this proposed AD affects 116 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 9821]]

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
             Action                  Labor cost              Parts cost               product        operators
----------------------------------------------------------------------------------------------------------------
Determine if type A or type B    1 work-hour x $85  Not applicable..............             $85          $9,860
 NLG fork is installed.           per hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary additional 
inspections, replacements, and modifications that would be required 
based on the results of the proposed NLG fork type determination. We 
have no way of determining the number of airplanes that might need 
these inspections, replacements, and modifications:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                   Cost per
               Action                      Labor cost                    Parts cost                 product
---------------------------------------------------------------------------------------------------------------
Inspection of the NLG fork for       4 work-hours x $85 per  Not applicable...................            $340
 cracks.                              hour = $340.
Replacement of the NLG fork........  4 work-hours x $85 per  $7,002.36........................        7,342.36
                                      hour = $340.
Inspection of the shimmy damper      1 work-hour x $85 per   Not applicable...................              85
 bracket.                             hour = $85.
Rework of the shimmy damper bracket  4 work-hours x $85 per  $127.33..........................          467.33
                                      hour = $340.
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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 small airplanes, gliders, 
balloons, airships, domestic business jet transport airplanes, and 
associated appliances to the Director of the Policy and Innovation 
Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Quest Aircraft Design, LLC: Docket No. FAA-2018-0180; Product 
Identifier 2017-CE-043-AD.

(a) Comments Due Date

    We must receive comments by April 23, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to 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. We are 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 fork 
with consequent reduced control on landing. If the 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 the effective date 
of this AD, inspect the airplane to determine if a NLG fork part 
number (P/N) 100-410-7001 (type A) or a NLG fork P/N 100-410-7013 
(type B) is installed. If you determine that a NLG 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 
positively identify the P/N NLG fork that is installed, you may use 
a maintenance records review in lieu of

[[Page 9822]]

inspecting the airplane to determine if a NLG fork P/N 100-410-7001 
(type A) or a NLG fork P/N 100-410-7013 (type B) is installed.

(h) Inspection of the NLG Fork for Cracks

    (1) If you determine that a NLG fork P/N 100-410-7001 (type A) 
is installed during the inspection required in paragraph (g) of this 
AD, within 25 hours TIS after the effective date of this AD and 
repetitively thereafter at intervals not to exceed 100 hours TIS, do 
a fluorescent penetrant, dye penetrant, or open-hole eddy current 
inspection of the NLG fork for cracks following section 5. 
Instructions in Quest Aircraft Field Service Instruction FSI-147, 
Revision 00 (not dated).
    (2) If you find any cracks of the NLG fork during any inspection 
required in paragraph (h)(1) of this AD, before further flight, 
replace the NLG fork with a NLG fork P/N 100-410-7013 (type B) 
following section 5. Instructions in Quest Aircraft Field Service 
Instruction FSI-147, Revision 00 (not dated). Replacement of the NLG 
fork with a NLG fork P/N 100-410-7013 (type B) terminates the 
repetitive inspections required in paragraphs (h)(1) and (i)(1) of 
this AD.

(i) Inspection of the Shimmy Damper Bracket

    (1) If you have not replaced a 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 the 
effective date of this AD and repetitively thereafter at intervals 
not to exceed 100 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 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 in paragraph (i)(1) of this AD, rework the 
shimmy damper bracket with interference-fit bolts following Quest 
Aircraft Field Service Instruction FSI-146, Revision 00 (not dated). 
Reworking the shimmy damper bracket with the interference-fit bolts 
terminates the repetitive inspections required in paragraph (i)(1) 
of this AD.
    (3) If any other damaged (loose, leaking, corrosion, worn, etc.) 
components are found in the shimmy damper system during any 
inspection required in paragraph (i)(1) of this AD, before further 
flight, replace damaged components as necessary 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.

(j) Optional Terminating Action

    In lieu of the NLG fork and shimmy damper bracket inspections 
required in paragraphs (h)(1) and (i)(1) of this AD, you may replace 
the NLG fork P/N 100-410-7001 (type A) with a NLG fork P/N 100-410-
7013 (type B) following section 5. Instructions in Quest Aircraft 
Field Service Instruction FSI-147, Revision 00 (not dated). 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 a NLG fork P/N 100-410-7013 (type B) is installed on an 
airplane, do not install a NLG fork P/N 100-410-7001 (type A). If a 
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 a 
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)(1) of this AD. Information may 
also 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.

(m) Related Information

    (1) For more information about this AD, contact Wade Sullivan, 
Aerospace Engineer, Seattle ACO Branch, FAA, 1601 Lind Avenue SW, 
Renton, WA 98057; phone: 425-917-6430; fax: 425-917-6590; email: 
[email protected].
    (2) For service information identified in this AD, contact Quest 
Aircraft Company LLC, 1200 Turbine Drive, Sandpoint, Idaho 83864; 
phone: (208) 263-1111 or 1 (866) 263-1112; email: 
[email protected]; internet: http://customercare.questaircraft.com/. You may view this service 
information at the FAA, Policy and Innovation Division, 901 Locust, 
Kansas City, Missouri 64106. For information on the availability of 
this material at the FAA, call (816) 329-4148.

    Issued in Kansas City, Missouri, on March 1, 2018.
Pat Mullen,
Acting Deputy Director, Policy & Innovation Division, Aircraft 
Certification Service.
[FR Doc. 2018-04650 Filed 3-7-18; 8:45 am]
BILLING CODE 4910-13-P