# TCDS A11WE: Aerostar Aircraft Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Aerostar Aircraft Corporation
- Revision: 4
- Revised: October 22, 1992
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23
- Registered aircraft: 1, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/c1/fd/c1fd13e5a633d328e88b8de9d345f86489027d72c54257aa239fa389a0a3b609
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/94B38718EB8EED948525672B00518B55.0001
- Page: https://openairdocs.org/tcds/A11WE

## Models (2)

As the data sheet lists them.

- 400
- 360

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4
Rev. No. 4 - 3 -
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
A11WE
Revision 4
Aerostar
360
400
October 22, 1992
TYPE CERTIFICATE DATA SHEET NO. A11WE
This data sheet which is a part of type certificate No. A11WE 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 Aerostar Aircraft Corporation
South 3608 Davison Blvd
Spokane, Washington  99204-5799
I - Model 360 (Normal Category) Approved May 1, 1967
Engine 2 Lycoming IO-360-E1A
Fuel 100/130 minimum grade aviation gasoline
Engine limits 2700 r.p.m. (180 hp) for all operations
Propeller and 1. Two Hartzell full-feathering propeller installations:
  propeller limits (a) Propellers - Hartzell HC-92WK-2B/W8447-12R
Pitch setting at 30 in. station:
Low 14°, High 84°
Diameter:  not over 72 in., not under 71 in.
(b) Spinners - Hartzell 835-30
(c) Propeller Governor - Woodward #210485
(d) Unfeathering Accumulator installation - Woodward #986250
Airspeed limits Vne - Never exceed 280 mph (243 knots) EAS
Vno - Maximum structural cruising 250 mph (217 knots) EAS
Vp  - Maneuvering 162 mph (141 knots) EAS
Vfe - Flaps extended 150 mph (130 knots) EAS
Vle = Vlo = Max. Landing Gear Operation 180 mph (156 knots) EAS
C.G. range +162.1 to +167.9 (19% MAC to 28% MAC)
Empty weight C.G. range None
Datum F.S. 0.00 @ 150.00 in. forward of wing L.E.
Leveling means Across cabin floor seat tracks.  (Use bubble scale)
Maximum weight 4100 lbs.
No. of seats 5 (2 @ +98, 1 @ +132, 2 @ +165)
Maximum baggage Rear compartment 240 lbs. @ +245
Fuel capacity 111 gal. total (one center fuselage tank +214) (109 gal. usable)
See Note 1 for data on system fuel

A11WE 2
I - Model 360      (cont'd)
Oil capacity 8 qt. each engine (+141), usable 6 qt. ea. engine; total capacity
16 qt.  See Note 1 for data on system oil
Control surface movements Wing Flaps Down 42° + 1°
Main surfaces
Aileron Up 25° + 1° Down 15° + 1°
Elevator Up 30° + 1° Down 10° + 1°
Rudder Right 30° + 1° Left 30° + 1°
Tabs (main surface in neutral)
Elevator Up   5° + 1° Down 25° + 1°
Rudder Right 15° + 1° Left 15° + 1°
Serial Nos. eligible 36-0002 and subsequent
II - Model 400 (Normal Category) Approved October 4, 1967
Engines 2 Lycoming IO-360-D1A
Fuel 100/130 minimum grade aviation gasoline
Engine limits 2700 r.p.m. (200 hp) for all operations
Propeller and 1. Two Hartzell full-feathering propeller installations:
  propeller limits (a) Propellers - Hartzell HC-C3YR-2/C7663-6
Pitch setting at 30 in. station:
Low 10.5°, High 79°
Diameter:  not over 72 in., not under 71 in.
(b) Spinners - Hartzell C-3258
(c) Propeller Governor - Woodward #210485
(d) Unfeathering Accumulator installation - Woodward #986250
Airspeed limits Vne - Never exceed 280 mph (243 knots) EAS
Vno - Maximum structural cruising 250 mph (217 knots) EAS
Vp  - Maneuvering 169 mph (147 knots) EAS
Vfe - Flaps extended 150 mph (130 knots) EAS
Vle = Vlo = Max. Landing Gear Operation 180 mph (156 knots) EAS
C.G. range At 4500 lbs. 16% MAC to 28% MAC (+160.2 to +167.9)
At 4100 lbs. 13% MAC to 28% MAC (+158.3 to +167.9)
Empty weight C.G. range None
Datum F.S. 0.00 @ 150.00 in. forward of wing L.E.
Leveling means Across cabin floor seat tracks.  (Use bubble scale)
Maximum weight 4500 lbs.
No. of seats 5 (2 @ +98, 1 @ +132, 2 @ +165)
Maximum baggage Rear compartment 240 lbs. @ +245
Fuel capacity 111 gal. total (one center fuselage tank +214) (109 gal. usable)
See Note 1 for data on system fuel

3 A11WE
II - Model 400    (cont'd)
Oil capacity 8 qt. each engine (+141), usable 6 qt. ea. engine; total capacity
16 qt.  See Note 1 for data on system oil
Control surface movements Wing Flaps Down 42° + 1°
Main surfaces
Aileron Up 25° + 1° Down 15° + 1°
Elevator Up 30° + 1° Down 10° + 1°
Rudder Right 30° + 1° Left 30° + 1°
Tabs (main surface in neutral)
Elevator Up   5° + 1° Down 30° + 1°
Rudder Right 15° + 1° Left 15° + 1°
Serial Nos. eligible 40-0001 and subsequent
DATA PERTINENT TO ALL MODELS
Certification basis FAR 23 effective February 1, 1965 and Amendments 23-1, 23-2 and 23-3.
No exceptions
Type Certificate No. A11WE issued May 1, 1967
Application for Type Certificate dated December 6, 1965.
Production basis None.  Prior to original certification of each aircraft an FAA representative must perform
a detailed inspection for workmanship, materials, and conformity with the approved
technical data, and a check of the flight characteristics.
Export eligibility Aircraft will be eligible for issuance of an Export Certificate of Airworthiness subject to
compliance with Federal Aviation Regulation Part 21, Subpart L, Sections 21.321 thru
21.339.  The applicable procedures are contained in Advisor Circular 21-2.
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations
(see Certification Basis) must be installed in the aircraft for certification.  Additional
required items of equipment are listed in the FAA Approved Equipment List No. 360-1
for Model 360 and Equipment List No. 400-2 for Model 400.
NOTE 1. Current weight and balance report including list  of equipment included in certificated empty weight, and
loading instructions when necessary, must be in each aircraft at the time of original certification.
The certificated empty weight and corresponding center of gravity locations must include system oil of 7.5 lb.
at (+141) and unusable fuel of 12 lb. at (+214) for Model 360 and Model 400.
NOTE 2. The following placards must be displayed:
(a) L. H. side adjacent to pilots:
(1) "This airplane must be operated as a normal category airplane in compliance with the operating
limitations stated in the form of placards, markings and manuals. No acrobatic maneuvers, including
spins, approved."
(2) "This aircraft is limited to day and night VFR non-icing flight." for Model 360 and "This aircraft
approved for day/night VFR/IFR non-icing flight when equipped in accordance with the airplane
flight manual" for the Model 400.

A11WE 4
(b) On instrument panel above Airspeed Indicator:
(1) "Maximum gear down and operating speed 180 mph"
(2) "Design maneuvering speed 162 mph" for Model 360 and "Design maneuvering speed
169 mph" for the Model 400.
(3) "Demonstrated cross-wind velocity 17 mph" for Model 360 and Model 400.
(c) Above upper door handle on inside:
"Shut off left engine before entering or leaving cabin."
(d) In the center above emergency exit quick release mechanism:
(1) "Emergency exit"
(2) "Pull to release"
(e) On aft baggage floor near lower door jam:
(1) "Maximum capacity 240 lbs."
(2) "Load in accordance with flight manual"
(f) On center line of airplane on contoured (facing aft) edge of glare shield in full view of occupants and on
right side of cabin between +111.0 and +118.5 on window molding, lower edge:
"No Smoking"
(g) On + 176 bulkhead behind electrical equipment cover:
"Notice:  Electrical system has been substantiated for a maximum load of 50 amps only."
.....END.....
```

## ADs (2, in force first)

- [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005

## Registered aircraft by registry model (OpenAirDocs)

- [Smith James G QUICKSILVER GT 400](https://openairdocs.org/model/smith-james-g-quicksilver-gt-400): 1 aircraft (registry code 05903TR)
- [Cessna 360](https://openairdocs.org/model/cessna-360): 0 aircraft (registry code 2076202)
- [Smith Donald H JR QCKSLVR GT 400 DS JR](https://openairdocs.org/model/smith-donald-h-jr-qckslvr-gt-400-ds-jr): 0 aircraft (registry code 05603PX)
- [Smith Donald J LANCAIR 360](https://openairdocs.org/model/smith-donald-j-lancair-360): 0 aircraft (registry code 05626W7)

## STCs approved under this data sheet (41)

- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc.
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine
- [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation
- [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation
- [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation
- [STC SA00780SE](https://openairdocs.org/stc/SA00780SE): Installation of the True Lock Safety Retention Axle Lock Nut System. True Lock LLC
- [STC SA11172SC](https://openairdocs.org/stc/SA11172SC): Installation of an ADS600-B Automatic Dependent Surveillance-Broadcast (ADS-B) Universal Access Transceiver (UAT) and Global Positioning System (GPS) antenna. NavWorx Inc
- [STC SA01229SE PAGE 1](https://openairdocs.org/stc/SA01229SE%20PAGE%201): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc
- [STC SA01933LA-D PAGE 1](https://openairdocs.org/stc/SA01933LA-D%20PAGE%201): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation
System. Garmin International Inc
- [STC SA02717NY PAGE 1](https://openairdocs.org/stc/SA02717NY%20PAGE%201): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC
- [STC SA02825NY PAGE 1](https://openairdocs.org/stc/SA02825NY%20PAGE%201): Installation of Aerospace Logic Aircraft Instruments. Aerospace Logic Inc.
- [STC SA01692SE](https://openairdocs.org/stc/SA01692SE): Installation of a Garmin GMX 200 Multi-Function Display. Garmin International Inc
- [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation
- [STC SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc
- [STC SA02110CH](https://openairdocs.org/stc/SA02110CH): Installation of a Time Trac Data Recorder. P2 Incorporated
- [STC SA02293AK](https://openairdocs.org/stc/SA02293AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Chelton Flight Systems Inc.
- [STC SA563CH](https://openairdocs.org/stc/SA563CH): Authorizes installation of engines equipped w/Unison Limited Authority Spark Advance Regulator (LASAR) ignition system w/Cylinder Head Temp. (CHT) monitoring capability on airframes. engines.. Champion Aerospace LLC
- [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC
- [STC SA01473SE](https://openairdocs.org/stc/SA01473SE): Installation of a GTX 32 (mode C), GTX 33 (mode S), or GTX 33D (mode S with diversity) Remote Transponde. Garmin AT Inc.
- [STC SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc.
- [STC SA01487SE](https://openairdocs.org/stc/SA01487SE): Installation of a GDL 69 or GDL 69A XM Satellite Receiver in accordance with Garmin Supplemental Type Certificate Master Data List, P/N 005-C0217-00, Revision A, dated December 20, 2004, or later FAA approved revision.. Garmin AT Inc.
- [STC SA02217AK](https://openairdocs.org/stc/SA02217AK): Installation of Garmin AT Model GDL90 UAT Data Link System, in accordance with Garmin AT, Inc., GDL 90 UAT Master Data List, P/N 560-0278-01, Revision A, dated November 12, 2004, or later FAA approved revision.. Garmin AT Inc.
- [STC SA00165BO](https://openairdocs.org/stc/SA00165BO): Installation of Avidyne Corporation Datalink Coupler, part number 700-00015-000 per Avidyne Corporation Master Document List, Document No. AVACP-006 dtd 1/2/93 or later FAA-approved revisions.. Avidyne Corporation
- [STC SA5159NM](https://openairdocs.org/stc/SA5159NM): Installation of chip detector system.. Northwest Aircraft Inc
- [STC SA2386SW](https://openairdocs.org/stc/SA2386SW): Installation of S.A.F.E., EGT, CHT Systems.. Avicon Development Corporation
- [STC SA798EA](https://openairdocs.org/stc/SA798EA): Installation of Monitair exhaust gas combustion monitor kit.. Rosemount Engineering Co
- [STC SA00765DE PAGE 1](https://openairdocs.org/stc/SA00765DE%20PAGE%201) (historical): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA02717NY](https://openairdocs.org/stc/SA02717NY) (historical): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC
- [STC SA01933LA](https://openairdocs.org/stc/SA01933LA) (historical): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin AT Inc.
- [STC SA01229SE](https://openairdocs.org/stc/SA01229SE) (historical): Installation of CNX80 GPS WAAS Navigator with integrated VHF Navigation and Communication radios.. UPS Aviation Technologies

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