[Federal Register Volume 80, Number 188 (Tuesday, September 29, 2015)]
[Rules and Regulations]
[Pages 58354-58357]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-24249]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2207; Directorate Identifier 2015-CE-003-AD; 
Amendment 39-18272; AD 2015-19-10]
RIN 2120-AA64


Airworthiness Directives; M7 Aerospace LLC Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 97-02-02 for 
certain Models SA26-AT, SA26-T, SA226-AT, SA226-T, SA226-T(B), SA226-
TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC 
(C-26B), and SA227-TT airplanes. AD 97-02-02 required applying torque 
to the control column pitch bearing attaching nuts, inspecting the 
bearing assembly, inspecting the elevator control rod end bearing 
retainer/dust seals, and replacing or installing new parts as 
necessary. This new AD requires inspecting for movement and correct 
torque of the elevator control pivot bearing, inspecting the elevator 
control rod for damage and correct configuration, and replacing parts 
as necessary. This AD also requires a 10,000-hour time-in-service (TIS) 
repetitive replacement of the control column pivot bearing and elevator 
control rod bolt and requires replacement of the control column pivot 
bearing with the improved design by 35,000 hours TIS. This AD was 
prompted by loss of elevator control due to failure of the bolt 
attaching the elevator control rod to the elevator walking beam under 
the cockpit floor. We are issuing this AD to correct the unsafe 
condition on these products.

DATES: This AD is effective November 3, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 3, 
2015.

ADDRESSES: For service information identified in this AD, contact M7 
Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: 
(210) 824-9421; fax: (210) 804-7766; Internet: http://www.elbitsystems-us.com; email: [email protected]. You may view this referenced 
service information at the FAA, Small Airplane Directorate, 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 http://www.regulations.gov by searching for Docket No. 
FAA-2015-2207.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2015-
2207; 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 address for the Docket Office (phone: 800-647-
5527) is Document 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: Andrew McAnaul, Aerospace Engineer, 
FAA, ASW-143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, 
San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370; 
email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 97-02-02, Amendment 39-9886 (62 FR 2552, 
January 17, 1997), (``AD 97-02-02''). AD 97-02-02 applied to certain M7 
Aerospace LLC Models SA26-AT, SA26-T, SA226-AT, SA226-T, SA226-T(B), 
SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, 
SA227-DC (C-26B), and SA227-TT airplanes. The NPRM published in the 
Federal Register on June 16, 2015 (80 FR 34326). The NPRM was prompted 
by an operator experiencing complete loss of elevator control due to 
failure of the bolt attaching the elevator control rod to the elevator 
walking beam under the cockpit floor. A follow-on inspection of the 
operator's fleet revealed a variety of hardware installed. Some 
hardware matched the illustrated parts catalog (IPC), some matched the 
AD 97-02-02 configuration, and some matched neither of those 
configurations.
    When AD 97-02-02 was issued, the IPC was never revised to match the 
hardware configuration called out in AD 97-02-02 or in the service 
information associated with that AD. Because of the conflict between 
the AD and the IPC configurations, an airplane that was in compliance 
with the requirements of AD 97-02-02 could have had an incorrect 
hardware configuration installed during routine maintenance after 
complying with the AD. The IPC has been updated and corrected by M7 
Aerospace, LLC.
    Also, since we issued AD 97-02-02, the manufacturer developed an 
improved design for the control column pivot bearing and support 
structure that terminates the repetitive torque check and replacement 
of control column pivot bearings.
    The manufacturer also issued new service information that adds the 
10,000-hour TIS repetitive replacement of the control column pivot 
bearing that is in the airworthiness limitations section (ALS) of the 
airplane maintenance manual (AMM) and (if this revision is mandated) 
requires the replacement of the pivot bearing with the improved design 
by 35,000 hours TIS that is in the supplemental inspections document 
(SID). Issuance of

[[Page 58355]]

the new service information, the revised IPC, and this AD will 
eliminate the conflicts between AD 97-02-02, the service information, 
the IPC, the ALS, and the SID.
    The NPRM (80 FR 34326, June 16, 2015) proposed to require 
inspecting for movement and correct torque of the elevator control 
pivot bearing, inspecting the elevator control rod for damage and 
correct configuration, and replacing parts as necessary. The NPRM also 
proposed to require a 10,000-hour TIS repetitive replacement of the 
control column pivot bearing and elevator control rod bolt and require 
replacement of the control column pivot bearing with the improved 
design by 35,000 hours TIS. Replacing the original control column pivot 
bearing with the improved design terminates the requirement to 
repetitively replace the original control column pivot bearing every 
10,000 hours. We are issuing this AD to correct the unsafe condition on 
these products.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 34326, June 16, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 34326, June 16, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 34326, June 16, 2015).

Relevant Service Information Under 1 CFR 51

    We reviewed M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014; Fairchild Aircraft SA26 Series Service 
Bulletin No. 26-27-30-047, dated June 16, 1997; M7 Aerospace SA226 
Series Service Bulletin No. 226-27-060 R2, dated December 5, 2014; 
Fairchild Aerospace SA226 Series Service Bulletin No. 226-27-061, dated 
June 16, 1997; M7 Aerospace SA227 Series Service Bulletin, No. 227-27-
041 R2, dated December 5, 2014; Fairchild Aircraft SA227 Series Service 
Bulletin No. 227-27-042, dated June 16, 1997; M7 Aerospace LLC SA227 
Series Commuter Category Service Bulletin No. CC7-27-010 R2, dated 
December 5, 2014; and Fairchild Aircraft SA227 Series Commuter Category 
Service Bulletin No. CC7-27-011, dated June 16, 1997. The service 
information describes procedures for inspecting for movement and 
correct torque of the elevator control pivot bearing, inspecting the 
elevator control rod for damage, and replacing parts as necessary. The 
service information also adds a repetitive replacement of the control 
column pivot bearings at 10,000 hours TIS and requires replacement of 
the control column pivot bearing with the improved design within 35,000 
hours TIS. This 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 of this 
AD.

Costs of Compliance

    We estimate that this AD affects 360 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
              Action                    Labor cost              Parts cost            product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of torque on the        2 work-hours x $85    Not applicable.........            $170         $61,200
 control column pivot bearing.      per hour = $170.
Control column pivot bearing       8 work-hours x $85    $300...................             980         352,800
 replacement.                       per hour = $680.
New designed control column pivot  20 work-hours x $85   $2,450.................           4,150       1,494,000
 bearing replacement.               per hour = $1,700.
Elevator rod end bolt replacement  4 work-hours x $85    $10....................             350         126,000
                                    per hour = $340.
----------------------------------------------------------------------------------------------------------------

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.

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.

[[Page 58356]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
97-02-02, Amendment 39-9886 (62 FR 2552, January 17, 1997), and adding 
the following new AD:

2015-19-10 M7 Aerospace: Amendment 39-18272; Docket No. FAA-2015-
2207; Directorate Identifier 2015-CE-003-AD.

(a) Effective Date

    This AD is effective November 3, 2015.

(b) Affected ADs

    This AD supersedes AD 97-02-02, Amendment 39-9886 (62 FR 2552, 
January 17, 1997).

(c) Applicability

    This AD applies to M7 Aerospace LLC Models SA26-AT, SA26-T, 
SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, 
SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), SA227-TT, all serial 
numbers, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

    AD 97-02-02 (62 FR 2552, January 17, 1997) (``AD 97-02-02'') 
resulted from reports of Fairchild SA227 series airplanes losing 
pitch control in-flight. This supersedure was prompted by an 
operator experiencing complete loss of elevator control because of 
failure of the bolt attaching the elevator control rod to the 
elevator walking beam under the cockpit floor. We are issuing this 
AD to prevent loss of pitch control, which if not corrected, could 
result in loss of airplane control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done. Models SA227-CC and SA227-DC, serial numbers 
892, 893, and 895 and up, have the revised (modified) configuration. 
Since those airplanes are already in compliance, they do not have to 
do the actions in paragraphs (h) or (i) of this AD, including all 
subparagraphs. Those airplanes must still do the actions required in 
paragraph (j) of this AD, including all subparagraphs.

(g) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    This AD allows credit for the control column pivot bearing 
torque check and initial replacement required in paragraph (i)(2) of 
this AD and the elevator rod bolt inspection and initial replacement 
required in paragraphs (j)(1) and (j)(3)(i) of this AD, if done 
before November 3, 2015 (the effective date of this AD), following 
the procedures specified in the Accomplishment Instructions of the 
applicable service information listed in paragraphs (g)(1) through 
(g)(4) of this AD:
    (1) M7 Aerospace SA227 Commuter Category Service Bulletin No. 
CC7-27-010, original issue or revision 1.
    (2) M7 Aerospace SA227 Series Service Bulletin No. 227-27-041, 
original issue or revision 1.
    (3) M7 Aerospace SA226 Series Service Bulletin No. 226-27-060, 
original issue or revision 1.
    (4) M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-046, 
original issue or revision 1.

(h) Control Column Pivot Bearing Revised (Modified) Configuration

    (1) On or before the airplane accumulates a total of 35,000 
hours time-in-service (TIS) or within the next 1,000 hours TIS after 
November 3, 2015 (the effective date of this AD), whichever occurs 
later, you must revise (modify) the control column pivot bearing 
configuration with the improved design. Use the applicable service 
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of 
this AD. Revising (modifying) the configuration of the control 
column pivot bearing with the improved design terminates the actions 
for paragraph (i) of this AD, including all subparagraphs, but you 
must still complete the required actions in paragraph (j) of this 
AD, including all subparagraphs.
    (i) Fairchild Aircraft SA26 Series Service Bulletin No. 26-27-
30-047, dated June 16, 1997;
    (ii) Fairchild Aircraft SA226 Series Service Bulletin No. 226-
27-061, dated June 16, 1997;
    (iii) Fairchild Aircraft SA227 Series Service Bulletin No. 227-
27-042, dated June 16, 1997; or
    (iv) Fairchild Aircraft SA227 Series Commuter Category No. CC7-
27-011, dated June 16, 1997.
    (2) You may at any time before 35,000 hours TIS revise (modify) 
the control column pivot bearing configuration with the improved 
design to terminate the repetitive replacement of the original 
control column pivot bearing using the applicable service 
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of 
this AD. This action terminates the requirements of paragraph (i) of 
this AD, including all subparagraphs, but you must still complete 
the required actions in paragraph (j) of this AD, including all 
subparagraphs.

(i) Torque Check or Replacement of the Control Column Pivot Bearing

    (1) Use the service information, as applicable, listed in 
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD to do a control 
column pivot bearing torque check or replacement at the applicable 
compliance times in paragraph (i)(2) or (i)(3) of this AD, including 
all subparagraphs:
    (i) M7 Aerospace LLC SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014;
    (ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226-27-
060 R2, dated December 5, 2014;
    (iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227-27-
041 R2, dated December 5, 2014; or
    (iv) M7 Aerospace LLC SA227 Series Commuter Category Service 
Bulletin No. CC7-27-010 R2, December 5, 2014.
    (2) For airplanes where the control column pivot bearing has 
been torque checked or replaced within the last 10,000 hours TIS 
before November 3, 2015 (the effective date of this AD) using the 
applicable service information listed in paragraph (g)(1) through 
(g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, do one of the 
following actions:
    (i) Within the next 10,000 hours TIS after the last control 
column pivot bearing replacement or within the next 1,000 hours TIS 
after November 3, 2015 (the effective date of this AD), whichever 
occurs later, and repetitively thereafter every 10,000 hours TIS, 
replace the control column pivot bearing following paragraph 2.B. of 
the Accomplishment Instructions of the applicable service 
information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of 
this AD; or
    (ii) Within the next 10,000 hours TIS after the last control 
column pivot bearing replacement or within the next 1,000 hours TIS 
after November 3, 2015 (the effective date of this AD), whichever 
occurs later, revise (modify) the control column pivot bearing 
configuration with the improved design using the applicable service 
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of 
this AD. Revising (modifying) the configuration of the control 
column pivot bearing with the improved design terminates the 
repetitive replacement of the original control column pivot bearing. 
No other actions are required for paragraph (i) of this AD, 
including all subparagraphs, but you must still complete the actions 
in paragraph (j) of this AD, including all subparagraphs.
    (3) For airplanes where the control column pivot bearing has not 
been torque checked or replaced within the last 10,000 hours TIS 
before November 3, 2015 (the effective date of this AD) using the 
applicable service information listed in paragraphs (g)(1) through 
(g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, within the next 
200 hours TIS after November 3, 2015 (the effective date of this 
AD), torque check the control column pivot bearing following 
paragraph 2.A. of the service information listed in paragraphs 
(i)(1)(i) through (i)(1)(iv) of this AD.
    (4) If nut movement occurs during the torque check required in 
paragraph (i)(3) of this AD, do one of the following actions:
    (i) Before further flight and repetitively thereafter at 
intervals not to exceed every 10,000 hours TIS, replace the control 
column pivot bearing following paragraph 2.B. of the Accomplishment 
Instructions of the applicable service information listed in 
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or
    (ii) Before further flight, revise (modify) the control column 
pivot bearing configuration with the improved design using the 
applicable service information listed in paragraphs (h)(1)(i) 
through (h)(1)(iv) of this AD. Revising (modifying) the 
configuration of the control column pivot bearing with the improved 
design terminates the repetitive replacement of the original control 
column pivot bearing. No other actions are required for paragraph 
(i) of this AD, including all

[[Page 58357]]

subparagraphs, but you must still complete the actions in paragraph 
(j) of this AD, including all subparagraphs.
    (5) If no nut movement occurs during the torque check required 
in paragraph (i)(3) of this AD, do one of the following actions:
    (i) Within the next 1,000 hours TIS after November 3, 2015 (the 
effective date of this AD), replace the control column pivot bearing 
following paragraph 2.B. of the Accomplishment Instructions of the 
applicable service information listed in paragraphs (i)(1)(i) 
through (i)(1)(iv) of this AD; or
    (ii) Within the next 1,000 hours TIS after November 3, 2015 (the 
effective date of this AD), revise (modify) the control column pivot 
bearing configuration with the improved design using the applicable 
service information listed in paragraphs (h)(1)(i) through 
(h)(1)(iv) of this AD. Revising (modifying) the configuration of the 
control column pivot bearing with the improved design terminates the 
repetitive replacement of the original control column pivot bearing.

(j) Inspect the Elevator Control Rod Ends and Hardware

    (1) Within the next 200 hours TIS after November 3, 2015 (the 
effective date of this AD), inspect the elevator control rod ends 
and hardware for wear, creasing, or other damage and verify the 
elevator rod bolt and attachment hardware for correct configuration 
following paragraph 2.D. of the Accomplishment Instructions of the 
applicable service information listed in paragraphs (i)(1)(i) 
through (i)(1)(iv) of this AD.
    (2) If any damage is found during the inspection required in 
paragraph (j)(1) of this AD or the elevator rod bolt and attachment 
hardware does not match the correct configuration, before further 
flight, replace the elevator rod bolt, rod ends, and associated 
hardware following paragraph 2.D. of the Accomplishment Instructions 
of the applicable service information listed in paragraphs (i)(1)(i) 
through (i)(1)(iv) of this AD.
    (3) Replace the elevator rod end bolt and associated hardware 
following paragraph 2.D. of the Accomplishment Instructions of the 
applicable service information listed in paragraphs (i)(1)(i) 
through (i)(1)(iv) of this AD at whichever of the following 
compliance times applies and repetitively thereafter at intervals 
not to exceed 10,000 hours TIS:
    (i) For airplanes where the elevator rod bolt has been replaced: 
Within the next 10,000 hours TIS after the last elevator rod bolt 
replacement or within the next 1,000 hours TIS after November 3, 
2015 (the effective date of this AD), whichever occurs later; or
    (ii) For airplanes where the elevator rod bolt has never been 
replaced: Within the next 200 hours TIS after November 3, 2015 (the 
effective date of this AD).

 (k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Fort Worth Airplane Certification Office, 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 ACO, send it to the attention of the 
person identified in paragraph (l)(1) of this AD.
    (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.

(l) Related Information

    (1) For more information about this AD, contact Andrew McAnaul, 
Aerospace Engineer, FAA, ASW-143 (c/o San Antonio MIDO), 10100 
Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 
308-3365; fax: (210) 308-3370; email: [email protected].

(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 the AD specifies otherwise.
    (i) M7 Aerospace LLC SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014.
    (ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226-27-
060 R2, dated December 5, 2014.
    (iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227-27-
041 R2, dated December 5, 2014.
    (iv) M7 Aerospace LLC SA227 Series Commuter Category Service 
Bulletin No. CC7-27-010 R2, December 5, 2014.
    (v) Fairchild Aircraft SA26 Series Service Bulletin No. 26-27-
30-047, dated June 16, 1997.
    (vi) Fairchild Aircraft SA226 Series Service Bulletin No. 226-
27-061, dated June 16, 1997.
    (vii) Fairchild Aircraft SA227 Series Service Bulletin No. 227-
27-042, dated June 16, 1997.
    (viii) Fairchild Aircraft SA227 Series Commuter Category No. 
CC7-27-011, dated June 16, 1997.
    (3) For service information identified in this AD, contact M7 
Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; 
phone: (210) 824-9421; fax: (210) 804-7766; Internet: http://www.elbitsystems-us.com; email: [email protected].
    (4) You may view this service information at FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
816-329-4148.
    (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 Kansas City, Missouri, on September 17, 2015.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-24249 Filed 9-28-15; 8:45 am]
 BILLING CODE 4910-13-P