DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

 G57EU

 Revision 2

 Burkhart Grob

 Model G 103 C Twin III SL

 March 22, 1993

TYPE CERTIFICATE DATA SHEET No. G57EU

This data sheet which is part of Type Certificate No. G57EU prescribes conditions and limitations under which the product for

which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.

Type Certificate Holder: BURKHART GROB LUFT- UND

RAUMFAHRT GmbH & Co. KG

Am Flugplatz

D-8939 Mattsies

Federal Republic of Germany

I. Model G 103 C TWIN III SL (Utility Category), approved February 13, 1992.

Engine. Bombardier-ROTAX- Type 505A.

Fuel. See Flight Manual Section 2.4.

Engine Limits. Max. power 43 HP (31.6 KW)

Max. permitted RPM 6800 RPM

Max. continuous power 43 HP (31.6 KW)

Max. continuous RPM 6400 RPM (For Propeller 1)

Max. continuous RPM 6800 RPM (For Propeller 2)

Propeller and Propeller Limits. Propeller 1: MT-Propeller-Entwicklung MTV-24-M/158-16

Propeller 2: Technoflug Leichtflugzeugbau KS-1C-158-R-108

Airspeed Limits. (I.A.S.). Maximum Airspeeds

 In Calm Air

 Never exceed (VNE) 134 kts 154 mph 248 km/hr

 In Rough Air (VRA) 94 kts 109 mph 175 km/hr

 Maneuvering (VA) 94 kts 109 mph 175 km/hr

 Aero Tow (VT) 76 kts 87 mph 140 km/hr

 Winch Tow (VW) 76 kts 87 mph 140 km/hr

 Min powerplant extension/

 retraction (VPOMIN) 48 kts 56 mph 90 km/hr

 Max powerplant extension/

 retraction (VPOMAX) 59 kts 68 mph 110 km/hr

C.G. Range. 11.02 in. to 19.29 in. (280 mm to 490 mm) aft of datum.

Empty Weight C.G. See Maintenance Manual Section 7, Page 6.

Page No. 1 2 3 4

Rev. No. 2 1 2 2
G57EU 2

Empty Weight. 1080 lbs (490 kg).

Datum. Wing leading edge at the root rib.

Leveling Means. See Maintenance Manual Section 7, Page 3.

Maximum Weight. 1565 lbs (710 kg).

Minimum Crew. 1 pilot

No. of Seats. 2-fixed seats with Seat 1 located 44.57 in. (1132 mm) forward of datum

and Seat 2 located 1.38 in. (35 mm) behind datum.

Baggage. Maximum 22 lb. (10 kg) at 31.89 in. (810 mm) aft of datum.

Fuel Capacity. Total contents: Fuselage tank 8.7 U.S. gal (33 l)

 Wing tank 12.4 U.S. gal (47 l) *

Non-Useable 0.53 U.S. gal ( 2 l)

* Note: As standard only with Propeller 1.

Control Surface Movements. Aileron Up 2.95 ± 0.31 in. (radius 8.46 in)

Down 1.97 ± 0.20 in.

The radius is the distance measured from the hingeline of

the aileron at the inboard edge of the aileron.

Elevator Up 4.02 ± 0.31 in. (radius 9.45 in.)

Down 2.91 ± 0.24 in.

The radius is the distance measured from the hingeline of

the elevator at the inboard edge of the elevator.

Rudder Right 9.25 ± 0.39 in. (radius 17.72 in.)

Left 7.87 ± 0.20 in.

The radius is the distance measured from the hingeline of

the rudder at the base of the rudder.

Airbrake

 At inner level Up 5.0 in.

Rated Load on Winch and Maximum 935 daN (2061 lbf.).

 Auto Tow (Weak Link).

Serial Nos. Eligible. As of Serial # 35001

Import Requirements. a. To be considered eligible for operation in the United States, each

aircraft manufactured under this type certificate must be accompanied by a

certificate of airworthiness for export or certifying statement endorsed by

the exporting foreign civil airworthiness authority which states (in the

English language): This aircraft conforms to its U.S. type design (type

certificate number G57EU) and is in a condition for safe operation.

b. An airplane maintenance manual in compliance with JAR 22.1529

must be furnished before delivery of the first airplane or issuance of standard

certificate of airworthiness whichever occurs later.
3 G57EU

Certification Basis. 1) 14 CFR Sections 21.29, 21.183(c), and JAR-22 (Joint Airworthiness

Requirements for Sailplanes and Powered Sailplanes), dated 27

June 1989 (Change 4 of the English original edition) including

"Orange Papers" Amendment 22/90/1 dated 12 February 1991 and

Amendment 22/92/1 for propeller 2.

Additional Requirements.

Standards for Structural Substantiation of Sailplane and Powered

Sailplane Components Consisting of Glass or Carbon Fiber

Reinforced Plastics, Issue May 1986.

Standards for the Substantiation of the Electrical System of

Motorgliders, issue 22 November 1990.

Equivalent Level of Safety Findings.

JAR 22.51 (Take-off Speed)

Additional Requirements on Request of the Applicant.

NPA 22G-45, NPA 22D-55

2) Noise Requirements:

Lärmschutzforderungen für Luftfahrzeuge (LSL), Issue 1 January

1991.

3) Section 611(b) of the FAA Act of 1958.

Equipment. The basic required equipment as prescribed in the applicable airworthiness

regulations (see Certification Basis) must be installed in the airplane for

certification.

Service Information. "Service bulletins, structural repair manuals, vendor manuals, aircraft

flight manuals, and overhaul and maintenance manuals, which contain a

statement that the document is (LBA) approved, are accepted by the FAA are

considered FAA approved. These approvals pertain to the type design only."

Available Documents for GROB Model G 103 C TWIN III SL Series:

Flight Manual (POH) G 103 C TWIN III SL, Issue December 1991, and

subsequent revisions, LBA approved.

Maintenance Manual G 103 C TWIN III SL, including "LBA Approved"

Airworthiness Limitation Section.

Repair Manual G 103 C TWIN III SL

For Engine:

• Manual for ROTAX-Engine Type 505A

• Repair Manual for ROTAX-engine Type 501 and 505

• Spare Parts List for ROTAX Engine Type 505 - 505A, No. 744
G57EU 4

Service Information. For Propeller 1:

 (Continued) • Operation- and Installation Manual No. E-309 Mechanical Variable Pitch

 Propeller MTV-24-(),

• Overhaul Manual and Parts List No. E-310 for the Mechanical Variable

 Pitch Propeller

For Propeller 2:

• Operation and Installation Manual No. P3 for the Two Blade Composite

 Propellers with Fixed Pitch KS 1 G ()()(), KS 1 C ()()(), LBA approved.

Operating Manual for Tow Releases Series E-85 Nose Tow Release, LBA

approved.

Operating Manual for Safety Two Releases Series Europa G 88 Safety Tow

Release, LBA approved.

NOTES.

NOTE 1. The placards listed in Section 9 of the Maintenance Manual GROB G 103 C

TWIN III SL must be displayed.

NOTE 2. Service Life Limited components: See Maintenance Manual Section 11.

NOTE 3. All components which are exposed to sunlight (with the exception of the

areas for registration marks and colored warning paint) must have a white

surface.

NOTE 4. Major structural repairs must be accomplished at FAA certified repair stations

rated for composite aircraft structure work, in accordance with GROB repair

methods approved by FAA.

NOTE 5. Motorgliders of this model are certified for flight in accordance with Visual

Flight Rules (VFR day).

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