Airworthiness Criteria: Glider Design Criteria for Stemme AG Model Stemme S12 Powered Glider, 13752 [2017-05000]
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Federal Register / Vol. 82, No. 49 / Wednesday, March 15, 2017 / Rules and Regulations
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[FR Doc. 2017–04910 Filed 3–14–17; 8:45 am]
BILLING CODE 8070–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 21
[Docket No. FAA–2016–9452]
Airworthiness Criteria: Glider Design
Criteria for Stemme AG Model Stemme
S12 Powered Glider
Federal Aviation
Administration (FAA), DOT.
ACTION: Airworthiness design criteria.
AGENCY:
Type Certification Basis
These airworthiness criteria
are issued for the Stemme AG model
Stemme S12 powered glider. The
Administrator finds the design criteria,
which make up the certification basis
for the Stemme S12, acceptable.
DATES: These airworthiness design
criteria are effective April 14, 2017.
FOR FURTHER INFORMATION CONTACT: Mr.
Jim Rutherford, Federal Aviation
Administration, Small Airplane
Directorate, Aircraft Certification
Service, 901 Locust, Room 301, Kansas
City, MO 64106, telephone (816) 329–
4165, facsimile (816) 329–4090.
SUPPLEMENTARY INFORMATION:
SUMMARY:
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Background
On January 08, 2016, Stemme AG
submitted an application for type
validation of the Stemme S12 in
accordance with the Technical
Implementation Procedures for
Airworthiness and Environmental
Certification Between the FAA and the
European Aviation Safety Agency
(EASA), Revision 5, dated September
15, 2015. The Stemme S12 is a two-seat,
self-launching, powered glider with a
liquid cooled, turbocharged engine
mounted in the center fuselage, an
VerDate Sep<11>2014
14:21 Mar 14, 2017
Jkt 241001
indirect drive shaft, and a fully-foldable,
variable-pitch composite propeller in
the nose. It is constructed from glass
and carbon fiber reinforced composites,
features a conventional T-type tailplane,
and has a retractable main landing gear.
The glider has a maximum weight of
1,984 pounds (900 kilograms) and may
be equipped with an optional dual-axis
autopilot system. EASA type certificated
the Stemme S12 under Type Certificate
Number (No.) EASA.A.054 on March 11,
2016. The associated EASA Type
Certificate Data Sheet (TCDS) No.
EASA.A.054 defined the certification
basis Stemme AG submitted to the FAA
for review and acceptance.
The applicable requirements for glider
certification in the United States can be
found in FAA Advisory Circular (AC)
21.17–2A, ‘‘Type Certification—FixedWing Gliders (Sailplanes), Including
Powered Gliders,’’ dated February 10,
1993. AC 21.17–2A has been the basis
for certification of gliders and powered
gliders in the United States for many
years. AC 21.17–2A states that
applicants may utilize the Joint Aviation
Requirements (JAR)–22, ‘‘Sailplanes and
Powered Sailplanes’’, or another
accepted airworthiness criteria, or a
combination of both, as the accepted
means for showing compliance for
glider type certification.
The applicant Certification Basis is
based on EASA Certification
Specification (CS)–22, ‘‘Sailplanes and
Powered Sailplanes’’, initial issue, dated
November 14, 2003. In addition to CS–
22 requirements, the applicant will
comply with other requirements from
the certification basis referenced in
EASA TCDS No. EASA.A.054, including
special conditions and equivalent safety
findings.
Discussion of Comments
Notice of proposed airworthiness
design criteria for the Stemme AG
Stemme S12 powered glider was
published in the Federal Register on
November 30, 2016 (81 FR 86296). No
comments were received, therefore
these airworthiness design criteria are
adopted as proposed.
The Airworthiness Design Criteria
1. 14 CFR part 21, effective February
1, 1965, including amendments 21–1
through 21–93 as applicable.
2. EASA CS–22, initial issue, dated
November 14, 2003.
3. EASA Special Condition No. SC–
A.22.1.01, ‘‘Increase in maximum mass
for sailplanes and powered sailplanes.’’
4. ‘‘Preliminary Standard for the
Substantiation of Indirect Drive Shafts
in Power Plants of Powered Sailplanes
Certified to JAR–22’’ (with a
modification for the Stemme AG model
Stemme S 10), Luftfahrt-Bundesamt
(LBA) document number (no.) I231–87,
issued August 05, 1988.
5. Installation of a Dual-Axis
Autopilot System, including—
• EASA CS–VLA (Very Light
Aeroplanes) 1309, ‘‘Equipment, systems,
and installations’’; initial issue, dated
November 14, 2003; and
• EASA CS–23.1329, ‘‘Automatic
pilot system’’, amendment 3, dated July
20, 2012.
6. Drop Testing for Retractable
Landing Gear (EASA equivalent safety
findings) to include CS–VLA 725,
‘‘Limit drop tests’’; CS–VLA 726,
‘‘Ground load dynamic tests’’; and CS–
VLA 727, ‘‘Reserve energy absorption’’;
initial issue dated November 14, 2003.
7. ‘‘Standards for Structural
Substantiation of Sailplane and
Powered Sailplane Parts Consisting of
Glass or Carbon Fiber Reinforced
Plastics’’, LBA document no. I4–FVK/
91, issued July 1991.
8. ‘‘Guideline for the analysis of the
electrical system for powered
sailplanes’’, LBA document no. I334–
MS 92, issued September 15, 1992.
9. The following kinds of operation
are allowed: VFR-Day.
10. Date of application for FAA Type
Certificate: January 08, 2016.
Issued in Kansas City, Missouri on January
23, 2017.
Mel Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–05000 Filed 3–14–17; 8:45 am]
BILLING CODE 4910–13–P
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the following
airworthiness design criteria under the
special class provision of 14 CFR
21.17(b) as part of the type certification
basis for the Stemme AG Stemme S12
power glider:
PO 00000
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15MRR1
]]>Agencies
[Federal Register Volume 82, Number 49 (Wednesday, March 15, 2017)]
[Rules and Regulations]
[Page 13752]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-05000]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 21
[Docket No. FAA-2016-9452]
Airworthiness Criteria: Glider Design Criteria for Stemme AG
Model Stemme S12 Powered Glider
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Airworthiness design criteria.
-----------------------------------------------------------------------
SUMMARY: These airworthiness criteria are issued for the Stemme AG
model Stemme S12 powered glider. The Administrator finds the design
criteria, which make up the certification basis for the Stemme S12,
acceptable.
DATES: These airworthiness design criteria are effective April 14,
2017.
FOR FURTHER INFORMATION CONTACT: Mr. Jim Rutherford, Federal Aviation
Administration, Small Airplane Directorate, Aircraft Certification
Service, 901 Locust, Room 301, Kansas City, MO 64106, telephone (816)
329-4165, facsimile (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Background
On January 08, 2016, Stemme AG submitted an application for type
validation of the Stemme S12 in accordance with the Technical
Implementation Procedures for Airworthiness and Environmental
Certification Between the FAA and the European Aviation Safety Agency
(EASA), Revision 5, dated September 15, 2015. The Stemme S12 is a two-
seat, self-launching, powered glider with a liquid cooled, turbocharged
engine mounted in the center fuselage, an indirect drive shaft, and a
fully-foldable, variable-pitch composite propeller in the nose. It is
constructed from glass and carbon fiber reinforced composites, features
a conventional T-type tailplane, and has a retractable main landing
gear. The glider has a maximum weight of 1,984 pounds (900 kilograms)
and may be equipped with an optional dual-axis autopilot system. EASA
type certificated the Stemme S12 under Type Certificate Number (No.)
EASA.A.054 on March 11, 2016. The associated EASA Type Certificate Data
Sheet (TCDS) No. EASA.A.054 defined the certification basis Stemme AG
submitted to the FAA for review and acceptance.
The applicable requirements for glider certification in the United
States can be found in FAA Advisory Circular (AC) 21.17-2A, ``Type
Certification--Fixed-Wing Gliders (Sailplanes), Including Powered
Gliders,'' dated February 10, 1993. AC 21.17-2A has been the basis for
certification of gliders and powered gliders in the United States for
many years. AC 21.17-2A states that applicants may utilize the Joint
Aviation Requirements (JAR)-22, ``Sailplanes and Powered Sailplanes'',
or another accepted airworthiness criteria, or a combination of both,
as the accepted means for showing compliance for glider type
certification.
Type Certification Basis
The applicant Certification Basis is based on EASA Certification
Specification (CS)-22, ``Sailplanes and Powered Sailplanes'', initial
issue, dated November 14, 2003. In addition to CS-22 requirements, the
applicant will comply with other requirements from the certification
basis referenced in EASA TCDS No. EASA.A.054, including special
conditions and equivalent safety findings.
Discussion of Comments
Notice of proposed airworthiness design criteria for the Stemme AG
Stemme S12 powered glider was published in the Federal Register on
November 30, 2016 (81 FR 86296). No comments were received, therefore
these airworthiness design criteria are adopted as proposed.
The Airworthiness Design Criteria
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following airworthiness design criteria under the
special class provision of 14 CFR 21.17(b) as part of the type
certification basis for the Stemme AG Stemme S12 power glider:
1. 14 CFR part 21, effective February 1, 1965, including amendments
21-1 through 21-93 as applicable.
2. EASA CS-22, initial issue, dated November 14, 2003.
3. EASA Special Condition No. SC-A.22.1.01, ``Increase in maximum
mass for sailplanes and powered sailplanes.''
4. ``Preliminary Standard for the Substantiation of Indirect Drive
Shafts in Power Plants of Powered Sailplanes Certified to JAR-22''
(with a modification for the Stemme AG model Stemme S 10), Luftfahrt-
Bundesamt (LBA) document number (no.) I231-87, issued August 05, 1988.
5. Installation of a Dual-Axis Autopilot System, including--
EASA CS-VLA (Very Light Aeroplanes) 1309, ``Equipment,
systems, and installations''; initial issue, dated November 14, 2003;
and
EASA CS-23.1329, ``Automatic pilot system'', amendment 3,
dated July 20, 2012.
6. Drop Testing for Retractable Landing Gear (EASA equivalent
safety findings) to include CS-VLA 725, ``Limit drop tests''; CS-VLA
726, ``Ground load dynamic tests''; and CS-VLA 727, ``Reserve energy
absorption''; initial issue dated November 14, 2003.
7. ``Standards for Structural Substantiation of Sailplane and
Powered Sailplane Parts Consisting of Glass or Carbon Fiber Reinforced
Plastics'', LBA document no. I4-FVK/91, issued July 1991.
8. ``Guideline for the analysis of the electrical system for
powered sailplanes'', LBA document no. I334-MS 92, issued September 15,
1992.
9. The following kinds of operation are allowed: VFR-Day.
10. Date of application for FAA Type Certificate: January 08, 2016.
Issued in Kansas City, Missouri on January 23, 2017.
Mel Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-05000 Filed 3-14-17; 8:45 am]
BILLING CODE 4910-13-P
