[Federal Register Volume 82, Number 214 (Tuesday, November 7, 2017)]
[Rules and Regulations]
[Page 51549]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-24102]



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 Rules and Regulations
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  Federal Register / Vol. 82, No. 214 / Tuesday, November 7, 2017 / 
Rules and Regulations  

[[Page 51549]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 21

[Docket No. FAA-2017-0863]


Airworthiness Criteria: Glider Design Criteria for Alexander 
Schleicher GmbH & Co. Models ASG 32 & ASG 32 Mi Gliders

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Airworthiness design criteria.

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

SUMMARY: These airworthiness design criteria for the Alexander 
Schleicher GmbH & Co. models ASG 32 & ASG 32 Mi gliders. The 
administrator finds the design criteria, which make up the 
certification basis for the ASG 32 & ASG 32 Mi gliders, acceptable.

DATES: These airworthiness design criteria are effective December 7, 
2017.

FOR FURTHER INFORMATION CONTACT: Mr. Jim Rutherford, AIR-692, Federal 
Aviation Administration, Policy & Innovation Division, Small Airplane 
Standards Branch, 901 Locust, Room 301, Kansas City, MO 64106, 
telephone (816) 329-4165, facsimile (816) 329-4090.

SUPPLEMENTARY INFORMATION: 

Background

    On August 23, 2016, Alexander Schleicher GmbH & Co. submitted an 
application for type validation of the ASG 32 glider and ASG 32 Mi 
powered glider 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. Both models will be documented on a single 
type certificate. The model ASG 32 is a two-seat, mid-wing, glider 
constructed from carbon-, glass-, and synthetic-fiber reinforced 
plastic and features a 65.6 foot (20 meter) wingspan with flaps, 
double-panel Schempp-Hirth airbrakes on the upper wing surface, 
winglets, water ballast tanks in the wing, and optional tanks in the 
fuselage. The glider also features a retractable landing gear with 
hydraulic disc brakes and a conventional T-type tailplane. The model 
ASG 32 Mi adds a retractable engine and fixed pitch propeller mounted 
in the center fuselage behind the cockpit which allows the glider to be 
self-launching. Both glider versions have a maximum weight of 1,874 
pounds (850 kilograms). The EASA type certificated the ASG 32 and ASG 
32 Mi gliders under Type Certificate Number (No.) EASA.A.599 on 
February 11, 2016. The associated EASA Type Certificate Data Sheet 
(TCDS) No. EASA.A.599 defined the certification basis Alexander 
Schleicher GmbH & Co. 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 certification basis is based on EASA Certification 
Specification (CS)-22, ``Sailplanes and Powered Sailplanes'', amendment 
2, dated March 05, 2009. In addition to CS-22 requirements, the 
applicant will comply with other requirements from the certification 
basis referenced in EASA TCDS No. EASA.A.599, including special 
conditions and equivalent safety findings.

Discussion of Comments

    Notice of proposed airworthiness design criteria for the Alexander 
Schleicher GmbH & Co. models ASG 32 & ASG 32 Mi gliders was published 
in the Federal Register on September 6, 2017 (82 FR 42049). No comments 
were received; therefore, these airworthiness design criteria are 
adopted as proposed.

The Airworthiness Design Criteria

    Applicable Airworthiness Criteria under Sec.  21.17(b).
    Based on the Special Class provisions of Sec.  21.17(b), the 
following airworthiness requirements form the FAA Certification Basis 
for this design:
    1. 14 CFR part 21, effective February 1, 1965, including amendments 
21-1 through 21-98 as applicable.
    2. EASA CS-22, amendment 2, dated March 05, 2009.
    3. EASA Special Condition No. SC-A.22.1.01, ``Increase in maximum 
mass for sailplanes and powered sailplanes.''
    4. EASA Equivalent Safety Finding to CS-22.335(f)--Alternate method 
to calculate the Design Maximum Speed (VD) using the 
Organisation Scientifique et Technique Internationale du Vol [aacute] 
Voile (OSTIV), Airworthiness Standards for Sailplanes, dated July 1997.
    5. EASA Equivalent Safety Finding to CS-22.585(a)--Alternate basis 
for lower towing loads and subsequent lower lauching hook attachment 
loads.
    6. ``Standards for Structural Substantiation of Sailplane and 
Powered Sailplane Parts Consisting of Glass or Carbon Fiber Reinforced 
Plastics,'' Luftfahrt-Bundesamt (LBA) document no. I4-FVK/91, issued 
July 1991.
    7. ``Guideline for the analysis of the electrical system for 
powered sailplanes,'' LBA document no. I334-MS 92, issued September 15, 
1992.
    8. Operations allowed: VFR-Day
    9. EASA Type Certificate Data Sheet No. EASA.A.599, Issue 02, dated 
March 17, 2016.
    10. Date of application for FAA Type Certificate: August 23, 2016.

    Issued in Kansas City, Missouri on October 31, 2017.
Pat Mullen,
Manager, Small Airplane Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-24102 Filed 11-6-17; 8:45 am]
 BILLING CODE 4910-13-P


