# TCDS TC G-2-11: Schweizer Aircraft Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Schweizer Aircraft Corporation
- Revision: 0
- Revised: February 27, 1947
- Product: Aircraft, Glider
- Certification basis: CAR 5
- Data sheet PDF: https://openairdocs.org/files/sha256/18/a4/18a49a1255795163cfda0f3b1e97ebcfa192512696147b1fc21730d3e83f68d2
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/3A7256E8FD1EC9DC85256721006D5F78.0001
- Page: https://openairdocs.org/tcds/TC%20G-2-11

## Models (1)

As the data sheet lists them.

- TG-3A Army

## What the data sheet says

This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers.

```text
MODEIS_: Schweizer Army IG-3A Glider, 2 PCIM
I.C. NUMBER: G-2-11 (Approved 2/27/47)
Type  Class I or Class II
Airspeed limits  Glide or dive - 90 mph True Ind.
Spoilers open - 90 mph True Ind.
Auto-winch tow - 63 mph True Ind.
Airplane tow - 90 mph True Inc.
C.G. range  (+16.5) to (+21.4)
Datum  Wing leading edge at root
Leveling means  Lugs on left of fuselage frame, aft of rear cockpit
Maximum weight  1100 lbs. as Class I
1200 1bs.  as Class II
No. seats  2 (1 at -28 and one at +30)
Baggage
control surface  Down 29 degrees
movements  Elevator trim tab  Up 11 degrees  Down 19 degrees
Aileron  Up 31 degrees  Down 14 degrees
Spoilers (top)  Up 90 degrees  Down 0 degrees
Up 0 degrees  Dowr. 82 degrees
Right 26 degrees  Left  28 degrees
Rudder trim tab  Right 24 degrees  Left 11 degrees
Serial numbers eligible
Required equipment  Items 301, 302, 401
SPECIFICATIONS PERTINENT TO ALL MODELS:
Certification basis  Airworthiness Certificate only (CAR 5.031)
EQUIPMENT:
Landing Gear
301.  Wheel (Goodyear  GH/MBM)  1+27
302-  Tire (Goodyear 6.00-6 4-ply)  1+27
Interior Equipment
401-  Airspeed indicator  (-50)
A weight and balance report including a list of equipment included
in the certificated empty weight must be submitted for each glider with
original inspector's report and each subsequent report covering change
in eguipment.  Each glider must be weighed to determize its weight and
prior to original certification unless satisfactory army weight
and balance report is available.
Prior to certification as a civil aircraft the following must re
Tent, ust be state in view of the pilot?  as determined by the weight and balance
Solo - Use front seat only -
Minimum Weight, Pilot and Parachute
(2) Dual - Front Seat - Minimum
Weight, Pilot and Parachute
Seat - Maximum Weight,
occupant and Parachute
(b) Rudder and elevator trim tab controls must be marked to indicate
direction of rotatior or position of tab.
The manufacturer's serial number and the date of conversion to
certificated status must be includej on the nameplate.
A stop should be installed in the spoiler system in accordance
with Figure 1.
The airspeed pitot head should be located in accordance with Figure 2.
Disconnect electrical system, remove dry batteries and position
of light bulbs.

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```

## ADs (1, in force first)

- [AD 87-02-01](https://openairdocs.org/ad/87-02-01): Tow-Release Installation Inspection · K & L Soaring SGM 2-37, SGS 1-23, SGS 1-23D and 32 more. Effective Jan 21, 1987

## STCs approved under this data sheet (2)

- [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SA01734SE](https://openairdocs.org/stc/SA01734SE): Application of Stewart Systems synthetic fabric covering system to aircraft fuselage, wings, tail surfaces, control surfaces and related parts.. Andrew D. Humphrey

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