82 FR 13752 - Airworthiness Criteria: Glider Design Criteria for Stemme AG Model Stemme S12 Powered Glider
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 49 (March 15, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 49 (March 15, 2017)
| Page Range | 13752-13752 | |
| FR Document | 2017-05000 |
[Federal Register Volume 82, Number 49 (Wednesday, March 15, 2017)] [Rules and Regulations] [Page 13752] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-05000] ======================================================================= ----------------------------------------------------------------------- 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
![13752 Federal Register / Vol. 82, No. 49 / Wednesday, March 15, 2017 / Rules and Regulations
5. Right of appeal. If FHFA–OIG denies indirect drive shaft, and a fully-foldable, 1. 14 CFR part 21, effective February
your request in whole or in part, you may variable-pitch composite propeller in 1, 1965, including amendments 21–1
appeal the denial by writing directly to the the nose. It is constructed from glass through 21–93 as applicable.
FOIA Officer through electronic mail, U.S. and carbon fiber reinforced composites,
mail, delivery service, or facsimile. The 2. EASA CS–22, initial issue, dated
electronic mail address is: FOIA@fhfaoig.gov.
features a conventional T-type tailplane, November 14, 2003.
For U.S. mail or delivery service, the mailing and has a retractable main landing gear.
address is: Federal Housing Finance Agency, The glider has a maximum weight of 3. EASA Special Condition No. SC–
Office of Inspector General, 400 Seventh 1,984 pounds (900 kilograms) and may A.22.1.01, ‘‘Increase in maximum mass
Street SW., Third Floor, Washington, DC be equipped with an optional dual-axis for sailplanes and powered sailplanes.’’
20219, ATTN: Office of Inspector General— autopilot system. EASA type certificated 4. ‘‘Preliminary Standard for the
FOIA Officer. The facsimile number is: (202) the Stemme S12 under Type Certificate Substantiation of Indirect Drive Shafts
318–8602. When submitting your appeal, Number (No.) EASA.A.054 on March 11,
please mark electronic mail, letters, or in Power Plants of Powered Sailplanes
2016. The associated EASA Type Certified to JAR–22’’ (with a
facsimiles and the subject line, envelope, or
facsimile cover sheet with ‘‘FOIA Appeal.’’
Certificate Data Sheet (TCDS) No. modification for the Stemme AG model
EASA.A.054 defined the certification Stemme S 10), Luftfahrt-Bundesamt
Dated: March 7, 2017. basis Stemme AG submitted to the FAA
Melvin L. Watt,
(LBA) document number (no.) I231–87,
for review and acceptance. issued August 05, 1988.
Director, Federal Housing Finance Agency.
The applicable requirements for glider 5. Installation of a Dual-Axis
[FR Doc. 2017–04910 Filed 3–14–17; 8:45 am] certification in the United States can be
Autopilot System, including—
BILLING CODE 8070–01–P found in FAA Advisory Circular (AC)
21.17–2A, ‘‘Type Certification—Fixed- • EASA CS–VLA (Very Light
Wing Gliders (Sailplanes), Including Aeroplanes) 1309, ‘‘Equipment, systems,
DEPARTMENT OF TRANSPORTATION Powered Gliders,’’ dated February 10, and installations’’; initial issue, dated
1993. AC 21.17–2A has been the basis November 14, 2003; and
Federal Aviation Administration for certification of gliders and powered • EASA CS–23.1329, ‘‘Automatic
gliders in the United States for many pilot system’’, amendment 3, dated July
14 CFR Part 21 years. AC 21.17–2A states that 20, 2012.
[Docket No. FAA–2016–9452] applicants may utilize the Joint Aviation
Requirements (JAR)–22, ‘‘Sailplanes and 6. Drop Testing for Retractable
Airworthiness Criteria: Glider Design Powered Sailplanes’’, or another Landing Gear (EASA equivalent safety
Criteria for Stemme AG Model Stemme accepted airworthiness criteria, or a findings) to include CS–VLA 725,
S12 Powered Glider combination of both, as the accepted ‘‘Limit drop tests’’; CS–VLA 726,
means for showing compliance for ‘‘Ground load dynamic tests’’; and CS–
AGENCY: Federal Aviation VLA 727, ‘‘Reserve energy absorption’’;
glider type certification.
Administration (FAA), DOT. initial issue dated November 14, 2003.
ACTION: Airworthiness design criteria. Type Certification Basis
7. ‘‘Standards for Structural
SUMMARY: These airworthiness criteria The applicant Certification Basis is Substantiation of Sailplane and
are issued for the Stemme AG model based on EASA Certification Powered Sailplane Parts Consisting of
Stemme S12 powered glider. The Specification (CS)–22, ‘‘Sailplanes and Glass or Carbon Fiber Reinforced
Administrator finds the design criteria, Powered Sailplanes’’, initial issue, dated Plastics’’, LBA document no. I4–FVK/
which make up the certification basis November 14, 2003. In addition to CS– 91, issued July 1991.
for the Stemme S12, acceptable. 22 requirements, the applicant will 8. ‘‘Guideline for the analysis of the
DATES: These airworthiness design comply with other requirements from
electrical system for powered
criteria are effective April 14, 2017. the certification basis referenced in
sailplanes’’, LBA document no. I334–
EASA TCDS No. EASA.A.054, including
FOR FURTHER INFORMATION CONTACT: Mr. MS 92, issued September 15, 1992.
special conditions and equivalent safety
Jim Rutherford, Federal Aviation 9. The following kinds of operation
findings.
Administration, Small Airplane are allowed: VFR-Day.
Directorate, Aircraft Certification Discussion of Comments
Service, 901 Locust, Room 301, Kansas 10. Date of application for FAA Type
City, MO 64106, telephone (816) 329– Notice of proposed airworthiness Certificate: January 08, 2016.
4165, facsimile (816) 329–4090. design criteria for the Stemme AG Issued in Kansas City, Missouri on January
SUPPLEMENTARY INFORMATION:
Stemme S12 powered glider was 23, 2017.
published in the Federal Register on
Background Mel Johnson,
November 30, 2016 (81 FR 86296). No
comments were received, therefore Acting Manager, Small Airplane Directorate,
On January 08, 2016, Stemme AG Aircraft Certification Service.
submitted an application for type these airworthiness design criteria are
adopted as proposed. [FR Doc. 2017–05000 Filed 3–14–17; 8:45 am]
validation of the Stemme S12 in
BILLING CODE 4910–13–P
accordance with the Technical The Airworthiness Design Criteria
Implementation Procedures for
Airworthiness and Environmental Accordingly, pursuant to the
Certification Between the FAA and the authority delegated to me by the
rmajette on DSK30RV082PROD with RULES
European Aviation Safety Agency Administrator, the following
(EASA), Revision 5, dated September airworthiness design criteria under the
15, 2015. The Stemme S12 is a two-seat, special class provision of 14 CFR
self-launching, powered glider with a 21.17(b) as part of the type certification
liquid cooled, turbocharged engine basis for the Stemme AG Stemme S12
mounted in the center fuselage, an power glider:
VerDate Sep<11>2014 14:21 Mar 14, 2017 Jkt 241001 PO 00000 Frm 00012 Fmt 4700 Sfmt 9990 E:\FR\FM\15MRR1.SGM 15MRR1](https://thefederalregister.org/doc/82_FR_13801/page/1.svg)
Document Created: 2017-03-15 06:04:44
Document Modified: 2017-03-15 06:04:44
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Airworthiness design criteria. | |
| Dates | These airworthiness design criteria are effective April 14, 2017. | |
| 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. | |
| FR Citation | 82 FR 13752 |
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