# TCDS A22NM: Aviat Aircraft Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Aviat Aircraft Inc.
- Revision: 31
- Revised: December 7, 2017
- Product: Aircraft, Small Airplane
- Certification basis: Part 23
- Registered aircraft: 1,076, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/b6/5b/b65bbcab56d07a1d99fd1b55d7eeee6ca6f247239d9ede0591041d35a8051110
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/016931A8621715FD8625878F0053B912.0001
- Page: https://openairdocs.org/tcds/A22NM

## Models (5)

As the data sheet lists them.

- A-1C-180
- A-1C-200
- A-1A
- A-1B
- A-1

## What the data sheet says

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

```text
A-1 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
A22NM 
Revision 31 
Aviat Aircraft, Inc. 
A-1A 
A-1B 
A-1C-180 
A-1C-200 
Dec 7, 2017 
TYPE CERTIFICATE DATA SHEET NO.  A22NM 
This data sheet which is part of Type Certificate No.  A22NM 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 Aviat Aircraft Inc. 
672 South Washington Street 
Afton, Wyoming 83110 
Type Certificate Ownership Record Christen Industries transferred ownership of Type Certificate A22NM to Aviat, Inc. on 
April 4, 1991. 
Aviat, Inc. transferred ownership of Type Certificate A22NM to White International, 
LTD. on December 3, 1992. 
White International, LTD. transferred ownership of Type Certificate A22NM to Sky 
International, Inc. on January 10, 1996. 
Sky International, Inc. transferred ownership to Aviat Aircraft, Inc. On February 27, 
2012 
I - Model A-1, 2PCLM (Normal Category), Approved May 1, 1987 
Engine Lycoming O-360-C1G (180 HP), or 
Lycoming O-360-A1P (180 HP) 
Fuel 100/100LL grade aviation gasoline 
Engine Limits For all operations, 2700 RPM 
Propeller and Propeller Limits Hartzell HC-C2YK-1BF/F7666A (Constant Speed) 
Diameter not over 76 in., not under 72 in. 
(See NOTE 3) 
Pitch settings at 30 in.  station low 
11.7º ± .2°, high 29.0° ± 1.0°, 
(See NOTE 9) 
Hartzell spinner assembly 836-60 (Required). 
Hartzell governor V3-6 or S-1-16 
Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000-2250 
RPM" 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 18 
Rev.  No. 31 25 25 25 26 26 26 26 23 23 23 23 23 25 23 25 27 30 31

A22NM Page 2 of 18 
Rev 25 
I - Model A-1, 2PCLM (Normal Category), Approved May 1, 1987 (cont'd) 
Airspeed Limits (CAS) 
C.G.  Range 
Empty wt.  C.G.  Range 
Datum 
Leveling Means 
Maximum Weight 
No. of Seats 
Maximum baggage 
Fuel Capacity 
Oil Capacity 
Control Surface Movements 
Serial Nos.  Eligible 
Certification Basis 
Production Basis 
Equipment 
Never Exceed 
Maximum Structural Cruising 
Maneuvering 
Flaps Extended 
(+74.5) to (+78.4) at 1800 lb 
(+72.5) to (+78.4) at 1500 lb and below 
Straight line variation between points given 
None 
60 in.  forward of wing leading edge 
Cabin door, lower sill 
1800 lb 
2 (1 at +72.5 and 1 at +99.0) 
50 lb  (at +120.0) 
52 gal.  (two 26 gal.  Tanks in wings at +84.0) 
153 mph (133 knots) 
119 mph (103 knots) 
94 mph (82 knots) 
73 mph (63 knots) 
50 gal usable.  See NOTE 1 for data on unusable fuel. 
8 qts.  (at +25.9) 
Elevator UP 29°±1° DOWN 15°±1° 
Ailerons UP 20° ± 2° DOWN 20° ± 2° 
Rudder LEFT 25° ± 2° RIGHT 25° ± 2° 
Flaps UP 0° DOWN 30° + 0°, -2° 
1001 to 1394 
Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 
thru 23-31 (Normal Category) and FAR 36 amended thru 36-12,. FAR 21 amended thru 
21-57. 
Application for Type Certificate dated November 20, 1985. 
Type Certificate No.  A22NM issued May 1, 1987. 
Production Certificate No.  A22NM 
The basic required equipment as prescribed in the applicable airworthiness regulations 
must be installed in the aircraft for certification.  In addition, the following items of 
equipment are required: 
1. FAA Approved Airplane Flight Manual 
2. Stall Warning indicator. 
3.  Cylinder head temperature gage. 
II - Model A-1A, 2PCLM (Normal Category), Approved January 28, 1998 
The A-1A is a derivative model of the A-1.  The A-1A has a gross weight of 1890 lb  The airframe has been modified 
structurally to accept this higher gross weight. 
Engine Lycoming O-360-A1P (180 HP) 
Fuel 100/100LL grade aviation gasoline 
Engine Limits For all operations, 2700 RPM

A22NM Page 3 of 18 
REV 25 
II - Model A-1A, 2PCLM (cont’d) 
Propeller and 
Propeller Limits 
Airspeed Limits (CAS) 
C.G.  Range 
Empty wt.  C.G.  Range 
Datum 
Leveling Means 
Maximum Weight 
No. of Seats 
Maximum baggage 
Fuel Capacity 
Oil Capacity 
Control Surface Movements 
Serial Nos.  Eligible 
Certification Basis 
Production Basis 
Hartzell HC-C2YK-1BF/F7666A (Constant Speed) 
Diameter not over 76 in., not under 72 in. 
(See NOTE 3) 
Pitch setting at 30 in.  station 
low 11.7° ± .2°, high 29.0° ± 1.0° 
Hartzell governor V3-6 or S-1-16 
Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000-
2250 RPM" 
Never Exceed 153 mph (133 knots) 
Maximum Structural Cruising 119 mph (103 knots) 
Maneuvering 99 mph (86 knots) 
Flaps Extended 
S/N 1395 to 1429 73 mph (73 knots) 
S/N 1430 and up 80 mph (70 knots) 
(see NOTE 15) 
(+74.5) to (+78.4) at 1890 lb 
(+72.5) to (+78.4) at 1500 lb and below 
Straight line variation between points given 
None 
60 in.  forward of wing leading edge. 
Cabin door, lower sill 
1890 lb 
2 (1 at +72.5 and 1 at +99.0) 
50 lb (at +120.0) 
52 gal.  (two 26 gal.  Tanks in wings at +84.0) 
50 gal usable.  See NOTE 1 for data on unusable fuel. 
8 qts.  (at +25.9) 
Elevator UP 29° ± 1° DOWN 15° ± 1° 
Ailerons UP 20° ± 2° DOWN 20° ± 2° 
Rudder LEFT 25° ± 2° RIGHT 25° ± 2° 
Flaps UP 0° DOWN 30° + 0°, -2° 
1395 to 1467 
Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 
thru 23-31 (Normal Category) and FAR 36 amended thru 36-12.  FAR 21 amended thru 
21-57. 
Application for Type Certificate dated August 25, 1997. 
Type Certificate No.  A22NM issued January 28, 1998. 
Production Certificate No.  704NM

A22NM Page 4 of 18 
REV 25 
II - Model A-1A, 2PCLM (cont’d) 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
must be installed in the aircraft for certification.  In addition, the following items of 
equipment are required: 
1. FAA Approved Airplane Flight Manual 
2. Stall Warning indicator 
3.  Cylinder head temperature gage 
III - Model A-1B, 2PCLM  (Normal Category), Approved January 28, 1998 
The A-1B is a derivative model of the A-1.  The A-1B has a gross weight of 2000 lb.  The airframe has been modified 
structurally to accept this higher gross weight.  The C.G.  envelope has been expanded forward and aft.  NOTE: See serial 
numbers eligible under this model. 
(See Engine Option Group Configuration for optional propeller and propeller limits.) 
Engine Lycoming O-360-A1P (180 HP) 
Fuel 100/100LL grade aviation gasoline 
Engine Limits For all operations, 2700 RPM 
Propeller Hartzell HC-C2YK-1BF/F7666A (Constant Speed) 
and Propeller Limits Diameter not over 76 in., not under 72 in.  (See NOTE 3) 
Pitch setting at 30 in.  station 
low 11.7° ± .2°, high 29.0° ± 1.0° 
Hartzell spinner 836-60 (Required). 
Hartzell governor V3-6 or S-1-16 
Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000-2250 
RPM" 
Airspeed Limits (CAS) Never Exceed 153 mph (133 knots) 
Maximum Structural Cruising 119 mph (103 knots) 
Maneuvering 113 mph (98 knots) 
Flaps Extended 80 mph (70 knots) 
(See Engine Option Group Configuration for Airspeed Limits.) 
C.G.  Range (+73.6) to (+80.0) at 2000 lb 
(+71.0) to (+80.0) at 1530 lb and below 
Straight line variation between points given 
Empty wt.  C.G.  Range None 
Datum 60 in.  forward of wing leading edge 
Leveling Means Cabin door, lower sill 
Maximum Weight 2000 lb 
No. of Seats 2 (1 at +72.5 and 1 at +99.0) 
Maximum baggage 50 lb  (at +120.0) 
Fuel Capacity 52 gal.  (two 26 gal.  Tanks in wings at +84.0) 
50 gal usable.  See NOTE 1 for data on unusable fuel. 
Oil Capacity 8 quarts.  (at +25.9)

A22NM Page 5 of 18 
REV 26 
III - Model A-1B, 2PCLM  (cont’d) 
Control Surface Movements 
Serial Nos.  Eligible 
Certification Basis 
Production Basis 
Equipment 
Elevator UP 29° ± 1° DOWN 15° ± 1° 
Ailerons UP 20° ± 2° DOWN 20° ± 2° 
Rudder LEFT 25° ± 2° RIGHT 25° ± 2° 
Flaps UP 0° DOWN 30° + 0°, -2° 
Note: For Model A-1B, serial numbers 2285, 2288, 2289, 2291, and up, 
Aileron UP 15.5° ± 2° DOWN 15.5° ± 2° 
2000 and up 
New optional rear spar material incorporated at S/N 2001.  Was 6061-T6.  Is: 7075-T76. 
(See Engine Option Group Configuration for Serial Nos.  Eligible.) 
Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 
thru 23-31 (Normal Category) and FAR 36 amended thru 36-12,. FAR 21 amended thru 
21-57. 
Application for Type Certificate dated August 25, 1997. 
Type Certificate No.  A22NM issued January 28, 1998. 
Production Certificate No.  704NM 
The basic required equipment as prescribed in the applicable airworthiness regulations 
must be installed in the aircraft for certification.  In addition, the following items of 
equipment are required: 
1. FAA Approved Airplane Flight Manual 
2. Stall Warning indicator. 
3.  Cylinder head temperature gage. 
III.a - Engine Option Group Configuration without Flap (Normal Category), Approved  August 18, 2003 
(The Engine Option Group Configuration without Flap is a model A-1B, 2PCLM) 
Model A-1B, effective serial numbers NF0001 through NF0006, NF0008 and above, are equipped with all of the following 
optional items.   Several of the Notes do not apply to Engine Option Group Configuration.  Note:  A -1B with Engine Option 
Configuration requires Approved Airplane Flight Manual dated August 18, 2003 or later FAA approved revisions. 
Engine Lycoming O-320-D2A (160 HP) 
Type Certificate Data Sheet (TCDS) E-274 
Fuel 100 or 100LL grade aviation gasoline 
Engine Limits For all operations, 2700 RPM 
Propeller Sensenich 74DM6S8-0-58 
Sensenich 
AE C-2367 FWD Bulkhead, AE A1233-5 Doubler Plate 
AE C2347 Spinner Dome, AE C2348 Rear Bulkhead 
Propeller Limits Diameter: Not over 74 in., not under 72 in. 
Static RPM Not over 2350 RPM, not under 2150 RPM 
No additional tolerance permitted. 
Sensenich spinner assembly C2366 (Required). 
Flapless Wing No Flaps or flap control system installed.  Wing tips unique.

A22NM Page 6 of 18 
REV 26 
IIIa - Engine Option Group Configuration without Flap (cont’d) 
Unique Engine Cowl 
Approved main gear tires with 
this option group 
Control Surface Movements 
Certification Basis 
6.00 x 6 4-ply, Type III tube 
8.00 x 6 4-ply, Type III tube 
8.50 x 6 6-ply, Type III tube 
Aircraft with Engine Option Group are approved for Day VFR only.  Aircraft with 
Engine Option Group equipped with Anti-Collision, Taxi/Landing, Position, and 
Instrument Flood Red/White lights are approved for both Day and Night VFR.  Not 
approved for Instrument Flight Rules (IFR) operation under the provisions of § 
91.205(d) of the Federal Aviation Regulations 
Elevator UP 29º ± 1º  DOWN 15° ± 1° 
Ailerons UP 20º ± 2º DOWN 20º ± 2º 
Rudder LEFT 25º ± 2º   RIGHT 25º ± 2º 
Serial Nos.  Eligible NF0001 through NF0006, NF0008 and up 
Part 23 of the Federal Aviation Regulations dated  
February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and  
FAR 36 amended thru 36-24. FAR 21 amended thru 21- 57. 
III.b - Engine Option Group Configuration with Flap (Normal Category), Approved  October 21, 2005 
(The Engine Option Group Configuration with Flap is a model A-1B, 2PCLM) 
Model A-1B, effective serial numbers NF0007, WF0001 and above, are equipped  with all of the following optional items. 
Several of the Notes do not apply to Engine Option Group Configuration.   Note:  A-1B with Engine Option Configuration 
requires Approved Airplane Flight Manual dated September 23, 2005 or later FAA approved revisions. 
Engine 
Fuel 
Engine Limits 
Propeller 
Propeller Limits 
Unique Engine Cowl 
Approved main gear tires with 
this option group 
Lycoming O-320-D2A (160 HP) 
Type Certificate Data Sheet (TCDS) E-274 
100 or 100LL grade aviation gasoline 
For all operations, 2700 RPM 
Sensenich 74DM6S8-0-58 
Sensenich 
AE C-2367 FWD Bulkhead, AE A1233-5 Doubler Plate 
AE C2347 Spinner Dome, AE C2348 Rear Bulkhead 
Diameter: Not over 74 in., not under 72 in. 
Static RPM Not over 2350 RPM, not under 2150 RPM 
No additional tolerance permitted. 
Sensenich spinner assembly C2366 (Required). 
Wing with flaps effective serial numbers NF0007, WF0001 and up are equipped with 
balanced ailerons, without spades, long flaps, flap control system per Engineering 
Report 55-4, Revision D, Appendix A, dated 8-25-05 or later FAA approved revisions. 
6.00 x 6 4-ply, Type III tube 
8.00 x 6 4-ply, Type III tube 
8.50 x 6 6-ply, Type III tube 
.

A22NM Page 7 of 18 
REV 26 
III.b - Engine Option Group Configuration with Flap (Normal Category), Approved  October 21, 2005 (Con’t) 
Aircraft with Engine Option Group are approved for Day VFR only.  Aircraft with 
Engine Option Group equipped with Anti-Collision, Taxi/Landing, Position, and 
Instrument Flood Red/White lights are approved for both Day and Night VFR.  Not 
approved for Instrument Flight Rules (IFR) operation under the provisions of  § 
91.205(d) of the Federal Aviation Regulations. 
Control Surface Movements Elevator UP 29º ± 1º    DOWN 15° ± 1° 
Ailerons UP 15.5º ± 2º  DOWN 15.5º ± 2º 
Rudder LEFT 25º ± 2º  RIGHT 25º ± 2º 
Flaps UP 0º  DOWN 30º  + 0º , -2º     
IIIb - Engine Option Group Configuration with Flap (cont’d) 
Serial Nos.  Eligible NF0007, WF0001 and up 
Certification Basis Part 23 of the Federal Aviation Regulations dated  
February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and  
FAR 36 amended thru 36-24. FAR 21 amended thru 21- 57. 
IV - Model A-1C-180, 2PCLM  (Normal Category), Approved September 24, 2007 
The A-1C-180 is a derivative model of the A-1B.  The A-1C-180 has a gross weight of 2200 lb. 
Structural modifications include updated landing gear per Aviat drawing 45017 (configurations: -501,-502,-503,-504,-505,-
506); and tail wheel configuration using 5-leaf spring or Alaska Bushwheel 3-leaf spring configuration per Aviat drawing 
37340. 
An additional modification to the angle of the leading edge of the horizontal stabilizers down 3/10 of a degree using a new 
stabilizer “H” support tube is also incorporated.  The A-1C-180 aircraft are equipped with the new wing/extended flap and 
spade less ailerons, new sliding windows, and the new wing flap control handle.  The C.G.  envelope has been reduced forward 
and expanded aft.  NOTE: See serial numbers eligible under this model. 
Engine Lycoming O-360-A1P (180 HP) 
Fuel 100/100LL grade aviation gasoline 
Engine Limits Refer to each propeller and propeller limits 
Propeller MTV-15-B/205-58 (includes spinner) (Constant Speed) 
and Propeller Limits Diameter not over 80.7 in., not under 79.9 in. 
Pitch setting at 30 in.  station 
low 7° ± .2°, high 24.0° ± 1.0° 
Takeoff & maximum continuous power 2600 RPM 
(Engine de-rated to 175 HP for noise) 
Hartzell HC-C2YK-1BF/F7666A (Constant Speed) 
Diameter not over 76 in., not under 72 in. 
Pitch setting at 30 in.  station 
low 11.7° ± .2°, high 29.0° ± 1.0 
Takeoff & maximum continuous power 2700 RPM 
Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000-
2250 RPM" 
Hartzell HC-C2YR-1N/F7605 (Constant Speed) 
Diameter not over 76 in., not under 76 in. 
Pitch setting at 30 in.  station 
low 10.5° ± .2°, high 30.0° ± 1.0° 
Takeoff  & maximum continuous power 2700 RPM 
Hartzell HC-C2YR-1BF/F8477-4 (Constant Speed) 
Diameter not over 80 in., not under 78 in.

A22NM Page 8 of 18 
IV - Model A-1C-180, 2PCLM (Normal Category), Approved September 24, 2007 (con’t) 
REV. 26 
Airspeed Limits (CAS) 
C.G.  Range 
Empty wt.  C.G.  Range 
Datum 
Leveling Means 
Maximum Weight 
No. of Seats 
Maximum baggage 
Fuel Capacity 
Oil Capacity 
Control Surface Movements 
Serial Nos.  Eligible 
Certification Basis 
Production Basis 
Equipment 
Pitch setting at 30 in.  station 
low 10.3° ± .2°, high 30.9° ± 1.0 
Takeoff & maximum continuous power 2600 RPM 
(Engine de-rated to 175 HP for noise) 
Hartzell spinner 836-60 or C3568-P (required for Hartzell props) 
Hartzell governor V3-6 or S-1-16 
Never Exceed 153 mph (133 knots) 
Maximum Structural Cruising 119 mph (103 knots) 
Maneuvering 113 mph (98 knots) 
Flaps Extended 80 mph (70 knots) 
(+74.5) to (+81.0) at 2200 lb 
(+72.3) to (+81.0) at 1781 lb and below 
Straight line variation between points given 
None 
60 in.  forward of wing leading edge 
Cabin door, lower sill 
2200 lb 
2 (1 at +72.5 and 1 at +99.0) 
50 lb  (at +120.0) 
52 gal.  (two 26 gal.  Tanks in wings at +84.0) 
50 gal usable.  See NOTE 1 for data on unusable fuel. 
8 quarts.  (at +25.9) 
Elevator UP 29° ± 1° DOWN 15° ± 1° 
Ailerons UP 15.5° ± 2° DOWN 15.5° ± 2° 
Rudder LEFT 25° ± 2° RIGHT 25° ± 2° 
Flaps UP 0° DOWN 30° + 0°, -2° 
3000+ (See NOTE 25) 
Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 
thru 23-31 (Normal Category) and FAR 36 amended thru 36-28.  FAR 21 amended thru 
21-57. 
Application for Type Certificate dated September 26, 2006 
Type Certificate No.  A22NM Reissued: September 24, 2007 
Production Certificate No.  704NM 
The basic required equipment as prescribed in the applicable airworthiness regulations 
must be installed in the aircraft for certification.  In addition, the following items of 
equipment are required: 
1. FAA Approved Airplane Flight Manual 
2. Stall Warning indicator. 
3.  Cylinder head temperature gage.

A22NM Page 9 of 18 
REV 23 
IV.a - Increased Gross Weight Variant, 2PCLM  (Normal Category), Approved January 27, 2012 
(The Increased Gross Weight variant is a model A-1C-180, 2PCLM.) 
Model A-1C-180, effective serial numbers 3000+ are eligible for an increased in max gross weight up to 2,250 lb.  No structural 
modifications are required to accept this higher gross weight. 
The gross weight increase requires the appropriate airspeed indicator (per Aviat Aircraft Drawing No. 35401 or 38401 
incorporating EO Nos. 4507 or 4508 respectively) to be installed; and the Airplane Flight Manual is replaced with the latest 
revision of the A-1C 180 2250 Approved Airplane Flight Manual. 
Engine Lycoming O-360-A1P (180 HP) 
Fuel 100/100LL grade aviation gasoline 
IVa – Increased Gross Weight Variant (cont’d) 
Engine Limits Refer to each propeller and propeller limits 
Propeller MTV-15-B/205-58 (includes spinner) (Constant Speed) 
and Propeller Limits Diameter not over 80.7 in., not under 79.9 in. 
Pitch setting at 30 in. station 
low 7° ± .2°, high 24.0° ± 1.0° 
Takeoff & maximum continuous power 2600 RPM 
(Engine de-rated to 175 HP for noise) 
Hartzell HC-C2YK-1BF/F7666A (Constant Speed) 
Diameter not over 76 in., not under 72 in. 
Pitch setting at 30 in.  station 
low 11.7° ± .2°, high 29.0° ± 1.0 
Takeoff & maximum continuous power 2700 RPM 
Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000-
2250 RPM" 
Hartzell HC-C2YR-1BF/F8477-4 (Constant Speed) 
Diameter not over 80 in., not under 78 in. 
Pitch setting at 30 in.  station 
low 10.3° ± .2°, high 30.9° ± 1.0 
Takeoff & maximum continuous power 2600 RPM 
(Engine de-rated to 175 HP for noise) 
Hartzell spinner 836-60 or C3568-P (required for Hartzell props) 
Hartzell governor V3-6 or S-1-16 
Airspeed Limits (CAS) Never Exceed 145 mph (126 knots) 
Maximum Structural Cruising 115 mph (100 knots) 
Maneuvering 113 mph (98 knots) 
Flaps Extended 81 mph (70 knots) 
C.G.  Range (+74.8) to (+80.0) at 2250 lb 
(+72.3) to (+80.0) at 1781 lb and below 
Straight line variation between points given 
Empty wt.  C.G.  Range None 
Datum 60 in.  forward of wing leading edge 
Leveling Means Cabin door, lower sill

A22NM Page 10 of 18 
REV 23 
IVa – Increased Gross Weight Variant (cont’d) 
Maximum Weight 2250 lb 
No. of Seats 2 (1 at +72.5 and 1 at +99.0) 
Maximum baggage 50 lb  (at +120.0) 
Fuel Capacity 52 gal.  (two 26 gal.  Tanks in wings at +84.0) 
50 gal usable.  See NOTE 1 for data on unusable fuel. 
Oil Capacity 8 quarts.  (at +25.9) 
Control Surface Movements Elevator UP 29° ± 1° DOWN 15° ± 1° 
Ailerons UP 15.5° ± 2° DOWN 15.5° ± 2° 
Rudder LEFT 25° ± 2° RIGHT 25° ± 2° 
Flaps UP 0° DOWN 30° + 0°, -2° 
Serial Nos.  Eligible 3000+ (See NOTE 25) 
Certification Basis Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 
thru 23-31 (Normal Category) and FAR 36 amended thru 36-28.  FAR 21 amended thru 
21-57. 
Application for Type Certificate dated May 7, 2010 
Type Certificate No.  A22NM Reissued: January 27, 2012 
Production Basis Production Certificate No.  704NM 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
must be installed in the aircraft for certification.  In addition, the following items of 
equipment are required: 
1. FAA Approved Airplane Flight Manual 
2. Stall Warning indicator. 
3.  Cylinder head temperature gage. 
V - Model A-1C-200, 2PCLM  (Normal Category), Approved September 24, 2007 
The A-1C-200 is a derivative model of the A-1B.  The A-1C-200 has a gross weight of 2200 lb. 
Structural modifications include updated landing gear per Aviat drawing 45017 (configurations: -501,-502,-503,-504,-505,-
506); and tail wheel configuration using 5-leaf spring or Alaska Bushwheel 3-leaf spring configuration per Aviat drawing 
37340. 
An additional modification to the angle of the leading edge of the horizontal stabilizers down 3/10 of a degree using a new 
stabilizer “H” support tube is also incorporated.  The A-1C-200 aircraft are equipped with Lycoming IO-360-A1D6 engine, new 
wing/extended flap and spade less ailerons, new sliding windows, and the new wing flap control handle.  The C.G.  envelope 
has been reduced forward and expanded aft.  NOTE: See serial numbers eligible under this model. 
Engine Lycoming IO-360-A1D6 (200 HP) 
Fuel 100/100LL grade aviation gasoline 
Engine Limits Refer to each propeller and propeller limits

A22NM Page 11 of 18 
REV 23 
V - Model A-1C-200, 2PCLM (cont’d) 
Propeller 
and Propeller Limits 
Airspeed Limits (CAS) 
C.G.  Range 
Empty wt.  C.G.  Range 
Datum 
Leveling Means 
Maximum Weight 
No. of Seats 
Maximum baggage 
Fuel Capacity 
Oil Capacity 
Control Surface Movements 
Serial Nos.  Eligible 
Certification Basis 
Production Basis 
HC-C2YR-1BF/F8477-4 (Constant Speed) 
Diameter not over 80 in., not under 78.0 in. 
Pitch setting at 30 in. station 
low 10.3° ± .2°, high 30.9° ± 1.0° 
Takeoff & maximum continuous power 2700 RPM 
MTV-15-B/205-58 (includes spinner) (Constant Speed) 
Diameter not over 80.7 in., not under 79.9 in. 
Pitch setting at 30 in. station 
low 7.0° ± .2°, high 24.0° ± 1.0° 
Takeoff & maximum continuous power 2650 RPM 
(Engine de-rated to 196 HP for noise) 
Hartzell spinner assembly 836-60 or C3568-P (Required with Hartzell props) 
Hartzell governor V3-6 or S-1-16 
Never Exceed 153 mph (133 knots) 
Maximum Structural Cruising 119 mph (103 knots) 
Maneuvering 113 mph (98 knots) 
Flaps Extended 80 mph (70 knots) 
(+74.5) to (+81.0) at 2200 lb 
(+72.3) to (+81.0) at 1781 lb and below 
Straight line variation between points given 
None 
60 in. forward of wing leading edge 
Cabin door, lower sill 
2200 lb 
2 (1 at +72.5 and 1 at +99.0) 
50 lb (at +120.0) 
52 gal.  (two 26 gal.  Tanks in wings at +84.0) 
50 gal usable.  See NOTE 1 for data on unusable fuel. 
8 quarts.  (at +25.9) 
Elevator UP 29° ± 1° DOWN 15° ± 1° 
Ailerons UP 15.5° ± 2° DOWN 15.5° ± 2° 
Rudder LEFT 25° ± 2° RIGHT 25° ± 2° 
Flaps UP 0° DOWN 30° + 0°, -2° 
3000+ (See NOTE 25) 
Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 
thru 23-31 (Normal Category) and FAR 36 amended thru 36-28.  FAR 21 amended thru 
21-57. 
Application for Type Certificate dated September 26, 2006 
Type Certificate No.  A22NM Reissued: September 24, 2007. 
Production Certificate No.  704NM

A22NM Page 12 of 18 
REV 23 
V - Model A-1C-200, 2PCLM (cont’d) 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
must be installed in the aircraft for certification.  In addition, the following items of 
equipment are required: 
1. FAA Approved Airplane Flight Manual 
2. Stall Warning indicator. 
3.  Cylinder head temperature gage. 
V.a - Increased Gross Weight Variant, 2PCLM  (Normal Category), Approved January 27, 2012 
(The Increased Gross Weight variant is a model A-1C-200, 2PCLM.) 
Model A-1C-200, effective serial numbers 3000+ are eligible for an increased in max gross weight up to 2,250 lb.  No structural 
modifications are required to accept this higher gross weight. 
The gross weight increase requires the appropriate airspeed indicator (per Aviat Aircraft Drawing No. 35401 or 38401 
incorporating EO Nos. 4507 or 4508 respectively) to be installed; and the Airplane Flight Manual is replaced with the latest 
revision of the A-1C 200 2250 Approved Airplane Flight Manual. 
Engine Lycoming IO-360-A1D6 (200 HP) 
Fuel 100/100LL grade aviation gasoline 
Engine Limits Refer to each propeller and propeller limits 
Propeller HC-C2YR-1BF/F8477-4 (Constant Speed) 
and Propeller Limits Diameter not over 80 in., not under 78.0 in. 
Pitch setting at 30 in. station 
low 10.3° ± .2°, high 30.9° ± 1.0° 
Takeoff & maximum continuous power 2700 RPM 
MTV-15-B/205-58 (includes spinner) (Constant Speed) 
Diameter not over 80.7 in., not under 79.9 in. 
Pitch setting at 30 in. station 
low 7.0° ± .2°, high 24.0° ± 1.0° 
Takeoff & maximum continuous power 2650 RPM 
(Engine de-rated to 196 HP for noise) 
Hartzell spinner assembly 836-60 or C3568-P (Required with Hartzell props) 
Hartzell governor V3-6 or S-1-16 
Airspeed Limits (CAS) Never Exceed 
Maximum Structural Cruising 
Maneuvering 
Flaps Extended 
145 mph (126 knots) 
115 mph (100 knots) 
113 mph (98 knots) 
81 mph (70 knots) 
C.G.  Range (+74.8) to (+80.0) at 2250 lb 
(+72.3) to (+80.0) at 1781 lb and below 
Straight line variation between points given 
Empty wt.  C.G.  Range None 
Datum 60 in. forward of wing leading edge 
Leveling Means Cabin door, lower sill 
Maximum Weight 2250 lb 
No. of Seats 2 (1 at +72.5 and 1 at +99.0) 
Maximum baggage 50 lb (at +120.0)

A22NM Page 13 of 18 
REV 23 
V.a – Increased Gross Weight Variant (cont’d) 
Fuel Capacity 52 gal.  (two 26 gal.  Tanks in wings at +84.0) 
50 gal usable.  See NOTE 1 for data on unusable fuel. 
Oil Capacity 8 quarts.  (at +25.9) 
Control Surface Movements Elevator UP 29° ± 1° DOWN 15° ± 1° 
Ailerons UP 15.5° ± 2° DOWN 15.5° ± 2° 
Rudder LEFT 25° ± 2° RIGHT 25° ± 2° 
Flaps UP 0° DOWN 30° + 0°, -2° 
Serial Nos.  Eligible 3000+ (See NOTE 25) 
Certification Basis Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 
thru 23-31 (Normal Category) and FAR 36 amended thru 36-28.  FAR 21 amended thru 
21-57. 
Application for Type Certificate dated May 7, 2010 
Type Certificate No.  A22NM Reissued: January 27, 2012. 
Production Basis Production Certificate No.  704NM 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
must be installed in the aircraft for certification.  In addition, the following items of 
equipment are required: 
1. FAA Approved Airplane Flight Manual 
2. Stall Warning indicator. 
3.  Cylinder head temperature gage. 
NOTES 
NOTE 1. Current weight and balance report, together with list of equipment included in certificate empty weight must 
be provided for each aircraft at the time of the original certification.  The certified empty weight and 
corresponding center of gravity location must include unusable fuel of 12.0 lb (at  +84.0). 
NOTE 2. All placards specified in the FAA approved Airplane Flight Manual must be displayed in the airplane in the 
appropriate locations. 
NOTE 3. Aircraft Flight Manual Supplement, Revision F, dated October 14, 1988, is required for propeller diameters 
less than 76".  This note does not apply to Engine Option Group Configurations of model A-1B, 2PCLM.  
See note under Engine Option Group Configuration for Airplane Flight Manual applicability. 
This note does not apply to model A-1C-180 and A-1C-200 or their Increased Gross Weight variants. 
NOTE 4. Export aircraft to Germany incorporating the Lycoming 0-360-C1G engine are certified for use with a 72 
inch diameter propeller, VFR day and night only, and 2550 RPM maximum continuous power, with 2700 
RPM maximum take-off power for 5 minutes. 
Export aircraft to Austria, Germany, or Switzerland incorporation the Lycoming 0-360-A1P engine must 
have a 72 inch diameter propeller and be limited to 2400 RPM maximum continuous power and 2700 RPM 
maximum continuous take-off power for 5 minutes.  Aviat Aircraft Inc. Flight Manual Supplement dated 
December 1, 1994 or later FAA approved revision is required. 
This note does not apply to Engine Option Group Configurations of model A-1B, 2PCLM.  
This note does not apply to model A-1C-180 and A-1C-200 or their Increased Gross Weight variants.

A22NM Page 14 of 18 
REV 25 
NOTES (con’t) 
NOTE 5. Model A-1, A-1A, A-1B, are approved for use with Aero Ski Models M1500, M1800, M2000, and M3000H 
installed per Christen Drawing 35569.  Christen Airplane Flight Manual Supplement, dated April 11, 1988, 
or later FAA approved revision for fixed ski operation is required. 
This note does not apply to Engine Option Group Configurations of model A-1B, 2PCLM. 
This note does not apply to model A-1C-180 and A-1C-200 or there increased Gross Weight variants. 
NOTE 6. Deleted 
NOTE 7. The Model A-1 is approved for use with EDO 89-2000 Floats installed in accordance with Christen 
Drawing 35600.  Christen Aircraft Flight Manual Supplement, dated February 28, 1989, or later FAA 
approved revision for the floatplane configuration is required.  The maximum aircraft gross weight with 
EDO 89-2000 floats installed is 1980 pounds. 
This note does not apply to model A-1C-180 and A-1C-200 or their Increased Gross Weight variants. 
NOTE 8. Models A-1, A-1A and A-1B are approved for use with Aero Ski Models R2800 retractable ski installed per 
Christen Drawing 35593.  Christen Airplane Flight Manual Supplement, dated Nov 7, 1989, or later FAA 
approved revision for retractable ski operation is required. 
This note does not apply to Engine Option Group Configurations of model A-1B, 2PCLM. 
This note does not apply to model A-1C-180 and A-1C-200or there increased Gross Weight variants. 
NOTE 9. Aircraft propellers may be reset to the page 1 setting if accomplished by an FAA approved propeller repair 
station.  Serial Numbers 1001 thru 1222 were set to a low pitch setting of 13°, +0°, -.5°. 
This note does not apply to Engine Option Group Configuration of model A-1B, 2PCLM. 
This note does not apply to Model A-1B, serial numbers 2285, 2288, 2289, 2291, and up. 
This note does not apply to model A-1C-180 and A-1C-200 or their Increased Gross Weight variants. 
NOTE 10. Model A-1, A-1A, A-1B, A-1C-180/A-1C-200 are approved for use with optional skylight panel installed in 
accordance with Aviat Aircraft Inc. drawing 35640. 
NOTE 11. Deleted 
NOTE 12. Model A-1 is approved for use with Horizon Instruments Model P-1000 Digital Engine Tachometer.  Aviat 
Aircraft Inc.  Flight Manual Supplement date Dec.  4, 1997 or later FAA approved revision is required. 
NOTE 13. The following main gear tires are approved for use on models A-1, A-1A and A-1B: 
6.00 x 6 4-ply Type III tube 
8.00 x 6 4-ply Type III tube 
8.50 x 6 6-ply Type III tube 
24 x 10-6 Type III Tundra 
26 x 10.5-6 Tundra and 8.50 x 6 tube

A22NM Page 15 of 18 
REV 23 
NOTES (con’t) 
NOTE 14. The following main gear tires are approved for use on models as shown in the table. 
PROPELLER PROPELLER NUMBER TIRE SIZE TUBE 
HARTZELL 76” HC-C2YK-1BF/F7666A 6.00 X 6  4 TO 6 PLY 600 X 6  TYPE III 
(METAL) 8:00 X 6  4 TO 6 PLY 8:00 X 6 TYPE III 
Models & Variants: 8:50 X 6  4 TO 6 PLY 8:50 X 6 TYPE III 
A-1C-180 26 X 10.5 X 6  6 PLY 8:50 X 6 TYPE III 
A-1C-180 2250 lb 26 X 13 X 6 TUBELESS 
29 X 13 X 6 TUBELESS 
31 X 13 X 6 TUBELESS 
HARTZELL 76” HC-C2YR-1N/N7605 8:00 X 6  4 TO 6 PLY 600 X 6  TYPE III 
(COMPOSITE) 8:50 X 6  4 TO 6 PLY 8:00 X 6 TYPE III 
Model: 26 X 10.5 X 6  6 PLY 8:50 X 6 TYPE III 
A-1C-180 26 X 13 X 6 8:50 X 6 TYPE III 
29 X 13 X 6 TUBELESS 
31 X 13 X 6 TUBELESS 
TUBELESS 
HARTZELL 80” HC-C2YR-1BF/F8477-4 8:50 X 6  4 TO 6 PLY 8:50 X 6 TYPE III 
Models & Variants: 26 X 10.5 X 6  6 PLY 8:50 X 6 TYPE III 
A-1C-180 26 X 13 X 6 TUBELESS 
A-1C-200 29 X 13 X 6 TUBELESS 
A-1C-180 2250 lb 
A-1C-200 2250 lb 
31 X 13 X 6 TUBELESS 
MT MTV-15-B/205-58 8:50 X 6  4 TO 6 PLY 8:50 X 6 TYPE III 
(COMPOSITE) 26 X 10.5 X 6 6PLY 8:50 X 6 TYPE III 
Models & Variants: 26 X 13 X 6 TUBELESS 
A-1C-180 29 X 13 X 6 TUBELESS 
A-1C-200 
A-1C-180 2250 lb 
A-1C-200 2250 lb 
31 X 13 X 6 TUBELESS 
This note does not apply to Engine Option Group Configurations of model A-1B, 2PCLM. 
NOTE 15. Model A-1A S/N 1395 to 1429 are eligible for increased flap speed of 80 mph if airspeed indicator P/N 
81714 is installed and Airplane Flight Manual is updated to reflect 80 mph flap speed. 
NOTE 16. Models A-1A and A-1B are approved for use with Baumann Model BF- 2100 Floats installed in accordance 
with Aviat Aircraft Drawing 37600.  The A-1 is float certified at 1980 pounds GW, the A-1A is float 
certified at 2079 pounds GW (1890 lb  for A-1A land plane + 189 lb  for floats), and the A-1B is float 
certified at 2200 pounds GW.  FAA approved Flight Manual Supplement dated August 31, 1998 or later for 
above float plane configurations is required. 
This note does not apply to Engine Option Group Configurations of model A-1B, 2PCLM. 
This note does not apply to model A-1C-180 and A-1C-200 or their Increased Gross Weight variants. 
NOTE 17. Models A-1, A-1A, and A-1B are approved for use with the Alaskan Bushwheel P/N 31136, 31" Diameter 
Tundra tire. 
Model A-1 must have the Aero Ski gear P/N 35017-503 and 35017-504 installed in conjunction with the 31" 
tundra tires P/N 31136. 
The Scott 10" Model L3450 tail wheel must also be installed per Aviat Aircraft Drawing 35340 on the 
model A-1and A-1A or per Aviat Aircraft Drawing 37340 on the Model A-1B.  FAA approved Flight 
Manual Supplement dated September 18, 1998 or later for the Tundra Tire configuration is required. 
This note does not apply to Engine Option Group Configurations of model A-1B, 2PCLM.

A22NM Page 16 of 18 
REV 25 
NOTES (con’t) 
NOTE 18. Models A-1A effective serial numbers 1451 and above, A-1B effective serial numbers 2007 and above, A-
1B with Engine Option Group Configuration effective serial numbers NF0001 and above, and A-1C-180/A-
1C-200 effective serial numbers 3000 and above are equipped for a baggage area access door located below 
the right hand aft side window.  The door is optional for the A-1A, A-1B, A-1C-180/A-1C-200, and A-1C-
180/A-1C-200 Increased Gross Weight variants and is available as a production design change only on the 
serial numbers listed above. 
NOTE 19. Models A-1, A-1A, A-1B, A-1C-180/A-1C-200, and A-1C-180/A-1C-200 Increased Gross Weight variants 
are approved for use with the Vision Microsystems Inc. VM1000 Engine Monitoring System when installed 
in accordance with Aviat Master Drawing List 95-0, dated 25 October 1999.  Operation and maintenance in 
accordance with FAA Approved Airplane Flight Manual Supplement for the Vision Microsystem VM1000 
Engine Monitoring System, dated 18 August 1999 and Supplemental Instructions for Continued 
Airworthiness - VM1000 Engine Monitoring System, dated 5 August 1999, or later revisions, are required. 
This note does not apply to Engine Option Group Configuration of model A-1B, 2PCLM. 
NOTE 20. Models A-1, A-1A, A-1B, A-1C-180/A-1C-200, and A-1C-180/A-1C-200 Increased Gross Weight variants 
are approved for use with the Vision Microsystems Inc.  VM1000 Engine Monitoring System with IFR 
equipment when installed in accordance with Aviat Master Drawing List 95-0, dated 25 October 1999. 
Operation and maintenance in accordance with FAA Approved Airplane Flight Manual Supplement for the 
Vision Microsystem VM1000 Engine Monitoring System, dated 18 August 1999 and Supplemental 
Instructions for Continued Airworthiness - VM1000 Engine Monitoring System, dated 5 August 1999, or 
later revisions, are required. 
This note does not apply to Engine Option Group Configuration of model A-1B, 2PCLM. 
NOTE 21. Models A-1, A-1A, A-1B, A-1C-180/A-1C-200, and A-1C-180/A-1C-200 Increased Gross Weight variants 
are approved for use with the Aviat Aft Stowage Compartment when factory-installed in accordance with 
Aviat Master Drawing List 96-00-00, Revision F dated 5/28/2000, or field installed per Aviat Service 
Bulletin 16, dated 4/19/2000, or later approved revision. 
The approved operating data for the Husky aircraft with the Aft Stowage Compartment installed is 
contained in the approved Airplane Flight Manual appropriate to the aircraft model, the approved Airplane 
Flight Manual Supplement, dated 1/26/2011, and Supplemental Instructions for Continued Airworthiness, 
dated 4/17/2007, or later FAA approved revisions, are required. 
This note does not apply to Engine Option Group Configuration of model A-1B, 2PCLM. 
NOTE 22. Models A-1, A-1A and A-1B are approved for use with the Fluidyne Model C-2200 Retractable Skis when 
installed in accordance with Aviat Husky Service Bulletin 15, Fluidyne C-2200 Retractable Ski Installation 
and Operation; A-1/A-1A Forward CG Expansion, dated 6/14/1999.  Operation and maintenance in 
accordance with FAA Approved Airplane Flight Manual Supplement for Fluidyne Skis, dated 6/25/1999 
and Supplemental Instructions for Continued Airworthiness - Fluidyne C2200 Retractable Skis, dated 
6/25/1999, or later revisions, are required. 
This note does not apply to Engine Option Group Configuration of model A-1B, 2PCLM. 
This note does not apply to model A-1C-180 and A-1C-200or there increased Gross Weight variants. 
NOTE 23. Model A-1B, effective serial numbers 2285, 2288, 2289, 2291, and up are equipped with balanced ailerons, 
without spades, and longer flaps per Master Changed Drawing List Document 2000-200-1, Revision A, 
dated February 15, 2005 or later FAA approved revisions.  Approved Airplane Flight Manual, Revision C, 
dated February 25, 2005, or later FAA approved revision is required. Note 9 does not apply to this 
configuration of Model A-1B. 
NOTE 24. Models A-1, A-1A, A-1B, A-1C-180/A-1C-200, and A-1C-180/A-1C-200 Increased Gross Weight variants 
are approved for flight with both the upper and lower doors open up to Vne.

A22NM Page 17 of 18 
REV 27 
NOTES (con’t) 
NOTE 25. Model A-1C 180 and A-1C 200, S/N 3000+ are eligible for an increased max gross weight of 2,250 lb if 
appropriate airspeed indicator (per Aviat Aircraft Drawing No. 35401 or 38401 incorporating EO Nos. 4507 
or 4508 respectively) is installed. Maintenance and operation compliance is required under Supplemental 
Instructions for Continued Airworthiness document AA-A1C-2250-800 revision A dated 08/26/2011 or 
later FAA accepted revision, and the Airplane Flight Manual Document A-1C-180 document  70467-001 
Revision IR, dated 01/24/2012, or A-1C-200 document 70468-001 Revision  IR, dated 01/20/2012 or later 
FAA approved revision. 
NOTE 26. Models A-1, A-1A, A-1B, and A-1C-180/-200 Increased Gross Weight variants are approved for use with 
glider/banner Tow hook when installed by a certified A&P Mechanic in accordance with Aviat assembly 
drawing 35572-501, Revision C or later FAA approved revision 
This note does not apply to Engine Option Group Configurations of model A-1B, 2PCLM. 
NOTE 27. Model A-1C-180 or A-1C-200, S/N 3000 and up are approved for use with JP Instruments EDM 930, 
Primary Engine Data with Garmin G500 or G600 Primary Flight Display (PFD) with multi function display 
(MFD) when installed at the factory in accordance with Aviat Aircraft Inc. drawing No. 38401 revision E 
dated 02 January 2013 or later FAA approved revision and Flight Manual Supplement document No. AAI-
G500-2009-005 revision IR dated 03/30/2010 or later FAA approved revision. Maintenance compliance is 
required under Aviat Aircraft Inc. Instructions for Continued Airworthiness document No. 70192-006 
revision D dated 7 AUG 2012 or later FAA accepted revision. Garmin G500 PFD/MFD system Instructions 
for Continued Airworthiness document No. 190-01102-00 revision 2 or Garmin G600 PFD/MFD System 
Instructions for Continued Airworthiness document 190-00601-00 revision A or latter FAA accepted 
revision. 
NOTE 28. Model A-1C-180 or A-1C-200, S/N 3085 and 3141 and up are approved for use with rebound damping 
landing gear strut installation. Maintenance and operation compliance is required under Supplemental 
Instructions for Continued Airworthiness document AA-A1C-LG-801 revision A, dated 12/28/2011 or later 
FAA accepted revision, and the Airplane Flight Manual Supplement Document No. AA-A1C-811 Revision 
IR, dated 01/20/2012, or later FAA approved revision. 
NOTE 29. Model A-1, A-1A, A-1B, A-1C-180/200 all serial numbers are approved for installation of VFR short 
instrument panels part numbers 39725-501, 39770-501 or 39770-502, when installed in accordance with 
Master Changed Drawing List document AAI-2015-100-2 rev. D dated 09 SEP 2015. Maintenance and 
operation compliance is required under Instructions for Continued Airworthiness document 70192-006 
revision D dated 07 AUG 2012 or later accepted revision, and the Airplane Flight Manual Supplement 
document AAI-2015-100-4 revision IR, dated 06 JUL 2015, or later FAA approved revision. 
NOTE 30. Model A-1B serial numbers 2285, 2288 and up are eligible for an Increased Gross Weight to 2200Lbs. 
Aviat Aircraft Inc. Service Letter Number 3 rev. B dated 11 JUN 2008 describes the aircraft configurations 
with structural modifications required for each described aircraft configuration. These modifications include 
main landing gear change, tail wheel spring change, tachometer indicing changes, New horizontal stabilizer 
tube, propeller modifications and requirement of new approved flight manuals. A-1B-180 Approved Flight 
Manual document number 70555-004 revision IR dated 29 Feb 2008 and A-1B-200 Approved Flight 
Manual document number 70555-005 revision IR dated 29 Feb 2008. Instructions for Continued 
Airworthiness, revision D dated 05 Oct 2005, or later FAA approved revisions, are required. 
This note does not apply to Engine Option Group Configurations of model A-1B, 2PCLM.

A22NM Page 18 of 18 
REV 31 
NOTE 31 Aviat Fuel Vent Check valve P/N 38266-501 replaces Rapco Fuel Vent Check valve P/N RA1798-00-1.  
Aviat Fuel Vent Check valve P/N 38266-502 can be used to replace Duke Fuel Vent Check valve P/N 1798-
00-1.  Aviat Fuel Vent Check valve installations for P/N 38266-501 and P/N 38266-502 require Husky A-1 
Series – Instructions for Continued Airworthiness Supplement, revision C, dated 16 May 2017 or later FAA 
approved revisions, for maintaining Airworthiness on Aviat Husky A-1 series aircraft. Life limits for Aviat 
Fuel Vent Check valves (P/N 38266-501 and P/N 38266-502) are published in Section 3 of the Husky A-1 
Series – Instruction for Continued Airworthiness Supplement, revision C, dated 16 May 2017, or later FAA 
approved revisions. 
NOTE 32. Models A-1C-180/A-1C-200, and A-1C-180/A-1C-200 Increased Gross Weight variants have incorporated 
a Type Design Change to this model series aircraft to incorporate a new Elevator Trim Tab system design. 
The cockpit controls remain the same, only the Elevator Trim Tab has been incorporated on the RH 
Elevator. Instructions for Continued Airworthiness Supplement, document number AAI-2016-300-008 
revision A, dated 25 July, 2017 or later FAA approved revisions are required with this modification. 
NOTE 33. Models A-1C-180/A-1C-200, and A-1C-180/A-1C-200 Increased Gross Weight variants have incorporated 
a Type Design Change to this model series aircraft to incorporate an optional Extended Landing Gear for 
production aircraft and retrofit. Flight Manual Supplement document AAI-2016-100-008 Revision B, dated 
17 OCT 2017, or later FAA approved revision must be used with this configuration. Also there is a change 
for determination of Weight and Balance for this Type Certificate Amendment. Reference Aircraft Flight 
Manual Supplement document AAI-2016-100-008 Revision B, to determine new Weight and Balance. 
NOTE 34. Models A-1C-180/A-1C-200, and A-1C-180/A-1C-200 Increased Gross Weight variants have incorporated 
a Type Design Change to this model series aircraft for removal of the rear seat to allow for more storage. 
The front seat can be adjusted forward or aft to facilitate occupant height variances and provide the 
occupants with greater ease for ingress and egress. Flight Manual Supplement document AAI-2016-200-
006 Revision IR, dated 22 NOV 2017, or later FAA approved revision must be used with this configuration.  
Also there are specific instructions and information for determination of Weight and Balance when this 
Type Certificate Amendment is configured. Reference Aircraft Flight Manual Supplement document AAI-
2016-100-006 Revision IR, to determine the difference in Weight and Balance with rear seat removed for 
more storage. 
…END…
```

## ADs (7, in force first)

- [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022
- [AD 2020-16-06](https://openairdocs.org/ad/2020-16-06): Horizontal Stabilizer Structure · Aviat A-1, A-1A, A-1B and 2 more. Effective Sep 1, 2020
- [AD 2019-10-06](https://openairdocs.org/ad/2019-10-06): Fuel Distribution · Aviat A-1C-180 and A-1C-200. Effective Jul 22, 2019
- [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 96-09-06](https://openairdocs.org/ad/96-09-06): Air Filter Assemblies · Maule Aerospace Technology 7ACA, 7ECA, 7FC and 180 more. Effective Jun 7, 1996
- [AD 91-23-02](https://openairdocs.org/ad/91-23-02): Carburetor Air Intake Box · Aviat A-1. Effective Dec 10, 1991
- [AD 90-20-05](https://openairdocs.org/ad/90-20-05): Forward Seat Back · Aviat A-1. Effective Oct 15, 1990

## Registered aircraft by registry model (OpenAirDocs)

- [Aviat A-1B](https://openairdocs.org/model/aviat-a-1b): 361 aircraft (registry code 2210406)
- [Aviat A-1C-180](https://openairdocs.org/model/aviat-a-1c-180): 233 aircraft (registry code 2210410)
- [Aviat A-1C-200](https://openairdocs.org/model/aviat-a-1c-200): 186 aircraft (registry code 2210411)
- [Aviat A-1](https://openairdocs.org/model/aviat-a-1): 144 aircraft (registry codes 2210302, 2210400)
- [Christen Industries A-1](https://openairdocs.org/model/christen-industries-a-1): 81 aircraft (registry code 221020X)
- [Aviat A-1A](https://openairdocs.org/model/aviat-a-1a): 58 aircraft (registry code 2210405)
- [Eaglerock A-1](https://openairdocs.org/model/eaglerock-a-1): 8 aircraft (registry code 0400102)
- [American Eagle A-1](https://openairdocs.org/model/american-eagle-a-1): 4 aircraft (registry code 7680102)
- [Christensen Wayne L FLY BABY A1](https://openairdocs.org/model/christensen-wayne-l-fly-baby-a1): 1 aircraft (registry code 056151F)
- [Experimental Aircraft Assn A-1](https://openairdocs.org/model/experimental-aircraft-assn-a-1): 0 aircraft (registry code 3360102)

## STCs approved under this data sheet (156, first 50)

- [STC SA01233SE](https://openairdocs.org/stc/SA01233SE): Fabrication and installation of Alaskan Bushwheel LLC tail wheel and fork assembly. ABI, LLC
- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [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 SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc.
- [STC SA01005DE](https://openairdocs.org/stc/SA01005DE): Installation of a EarthX ETX900-TSO Lithium battery. EarthX Inc.
- [STC SA11177SC](https://openairdocs.org/stc/SA11177SC): Installation of a Hartzell Propeller Inc. model HC-C2YR-IN/NG8301-3 propeller. Hartzell Propeller LLC
- [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA7965SW](https://openairdocs.org/stc/SA7965SW): Application of fabric and polyurethane finishing system.. Shady Aviation LLC
- [STC SA02396AK](https://openairdocs.org/stc/SA02396AK): Replacement of Sky International Inc. landing gear strut assemblies with Floats Alaska, LLC. +3  extended gear, part numbers 45017-501HD-3X and 45017-502HD-3X.. Seaplanes North LLC
- [STC SA02589AK](https://openairdocs.org/stc/SA02589AK): Installation of the Hartzell Model 3C1-R430A1/80C01 Propeller. Momentum Aeronautics Holdings LLC
- [STC SA01240SE](https://openairdocs.org/stc/SA01240SE): Installation of secondary voltage indication system. Visual Instruments LLC
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA02765SE](https://openairdocs.org/stc/SA02765SE): Installation of Acme Stinger tailwheel landing gear shock absorber. Acme Suspensions LLC
- [STC SA39CH](https://openairdocs.org/stc/SA39CH): Installation of an Amphibian Landing Gear Position Advisory System/Laser Gear Advisory System. Wipaire Inc.
- [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics
- [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02576AK](https://openairdocs.org/stc/SA02576AK): Installation of Cleveland and ABI, LLC Wheel and Brake Kits. ABI LLC
- [STC SA01416SE](https://openairdocs.org/stc/SA01416SE): Installation of a butterfly valve in the oil cooler inlet duct. Westview Aviation LLC
- [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA01606CH](https://openairdocs.org/stc/SA01606CH): Installation of alternate electro-hydraulic power pack system for operation of main wheel skis.. F.Atlee Dodge Aircraft Services
- [STC SA02838CH](https://openairdocs.org/stc/SA02838CH): Installation of Wipaire Skis Main Wheel Skis Model C2200. F.Atlee Dodge Aircraft Services
- [STC SA3-423](https://openairdocs.org/stc/SA3-423): Installation of CT-3000 tail ski on airplanes equipped with Scott 3200 or 3400 tail wheels.. F.Atlee Dodge Aircraft Services
- [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation
- [STC SA02023CH](https://openairdocs.org/stc/SA02023CH): Installation of an MT-Propeller model MTV-15-B/210-58 and spinner assembly P-277-B.. McFarlane Aviation LLC
- [STC SA02870CH](https://openairdocs.org/stc/SA02870CH): Installation of MT Propeller, model MTV-9-B/(198-200) -52, MTV-9-B-C-R-M/CR 198-200-52, MTV-15-B-C-R-M/CR 210-58, MTV-15-B/(205-210)-58, MTV-15-B/203-52 and MTV-15-B-C-R-M/CR-203-52, with matching spinner.. McFarlane Aviation LLC
- [STC SA02568AK](https://openairdocs.org/stc/SA02568AK): Installation of Airframes Alaska Aluminum Lift Struts. Airframes Alaska LLC
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc.
- [STC SA01721CH](https://openairdocs.org/stc/SA01721CH): Installation of Baumann Model BF2150A floats per Baumann Drawing List BF-2150A-01, Rev B, dtd 9/19/02 or later FAA approved revisions.. Baumann Floats LLC
- [STC SA96CH](https://openairdocs.org/stc/SA96CH): Installation of Baumann Model BF-2100 floats.. Baumann Floats LLC
- [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA02288AK](https://openairdocs.org/stc/SA02288AK): Installation of Alpha Omega Suspension System (AOSS) in place of original bungees. Burl's Aircraft LLC
- [STC SA02153AK](https://openairdocs.org/stc/SA02153AK): Installation of Burl's Aircraft Rebuild Magnum I tail wheel Penetration ski. Burl's Aircraft Rebuild LLC
- [STC SA03819NY](https://openairdocs.org/stc/SA03819NY): Installation and maintenance of Oratex 6000 Covering and Coating System. Lanitz-Prena Folien Factory GmbH
- [STC SA01015SE](https://openairdocs.org/stc/SA01015SE): Installation of eligible Alaska Bushwheel, Inc. wheels and TSO-C62d tires. ABI LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA02553AK](https://openairdocs.org/stc/SA02553AK): Fabrication and installation of a Tail Wheel Anti-Shimmy Dampener. Keller Engineering Group LLC
- [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA02430SE](https://openairdocs.org/stc/SA02430SE): Fabrication and installation of a camera housing. Airborne Sensor LLC

All 156: https://openairdocs.org/tcds/A22NM/stcs.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.