# TCDS 1A8: Helio Alaska Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Helio Alaska Inc.
- Revision: 38
- Revised: March 30, 2020
- Product: Aircraft, Small Airplane
- Certification basis: Part 3, CAR 3
- Registered aircraft: 122, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/ec/aa/ecaa81ee5e0016592ae8962cf023757203d81452769fa87b267ca50fd88e1819
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/70E8BA9CF78FD0D086258641004DB480.0001
- Page: https://openairdocs.org/tcds/1A8

## Models (9)

As the data sheet lists them.

- H-800
- HT-295
- H-700
- H-395 (USAF L-28A or U-10B)
- H-250
- H-391 (USAF UL-24)
- H-395A
- H-391B
- H-295 (USAF U10D)

## 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 5 6 7 8 9 10 11 12 13 14 
Rev. No. 38 36 36 31 31 31 31 35 31 31 31 34 31 38 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
1A8 
Revision 38 
HELIO  
H-250
      (USAF U-10D) H-295 
HT-295 
     (USAF YL-24) H -391 
H-391B
 (USAF L-28A or U-10B) H-395 
H-395A
H-700
H-800
March 30, 2020 
TYPE CERTIFICATE DATA SHEET NO. 1A8 
This data
 sheet, which is a part of Type Certificate 1A8, prescribes conditions and limitations under which the product for which 
the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations/Federal Aviation Regulations. 
Type Cert
ificate Holder 
(See Note 4 for Holder Record) 
Physical Address:
Helio A
laska, Inc.
20150
 Birchwood Spur Road 
Chugiak AK 99567 
I. Model H-391  (USAF YL-24) (Courier), 4 PCL-SM (Normal Category), approved August 5, 1953
Model H-391B (Courier), 4 P CL-SM (Normal Category), approved June 29, 1954
Model H-391B same  as model H-391 except for engine, propeller, semi-monocoque fuselage, minor fuel system 
changes, minor control system changes, and other miscellaneous minor changes. 
Engine Model
 H-391 - Lycoming GO-435-C2
Model H-391B - Lycoming GO-435-C2B, GO-435-C2B2, GO-435-C2B2-6
Fuel Model H-391 
- 91/98 minimum grade aviation gasoline
Model H-391B - 80/87 minimum grade aviation gasoline with standard
ejector exhaust system 
Engine limits T
akeoff 3400 r.p.m. (260 hp) 
All other operations 3000 r.p.m. (240 hp) 
Propeller a
nd propeller Model H-391 - Hartzell controllable propeller HC12X20-8C, blades
  limits 9333C-0.  Diameter:  not over 93 in., not under 91 in. 
Pitch settings at 30 in. Sta:  low 14° 15′, high 29° 15′ 
Placard re
quired:  "Continuous ground operation 
between 1675 and 2150 r.p.m. prohibited." 
Propeller gove
rnor, Hartzell B-1 or B-3. 
Propeller spinner and mount, Hartzell D-164. 
Model H-391B - Ha
rtzell controllable propeller hub HC82X20-1A or 
HC82X20-1B, blades 10133D.  Diameter:  not over 
101 in., not under 95 in. 
Pitch settings at 30 in. Sta:  Low 13°, high 31° 
S/N 001 through 081, except 075, as delivered by 
manufacturer. 
Mailing Address:
P. O. Box 670641
Chugiak AK 99567

1A8 2 of 14 
I. M odel H-391  (USAF YL-24), Model H-391B     (cont'd)
H- 391B (cont'd) Placard required:  "Avoid continuous operation between 
2600 and 2975 r.p.m."  If engine is modified to 
GO-435-C2B2-6, placard may be removed.  S/N 082 
and up, no placard is required. 
P
ropeller governor, Hartzell B-1 or B-3. 
Propeller spinner, Hartzell C-888 dome with C-807-2 bulkhead. 
A irspeed Limits  LANDPLANE 
M aneuvering (2800 lbs.)   94 m.p.h.  (  82 knots) CAS 
Maneuvering (3000 lbs.)   98 m.p.h.  (  85 knots) CAS 
Maximum structural cruising 150 m.p.h.  (134 knots) CAS 
Never exceed 189 m.p.h.  (164 knots) CAS 
Flaps extended   80 m.p.h.  (  69 knots) CAS 
F LOATPLANE  -  with Edo Model 249-2870 floats (H-391B only) S/N 001 through  
045,  aircraft structural changes required per Helio modifications No. 5A or No. 13.  Float 
installation per Helio modification No. 15.  S/N 046 and up, no structural changes  
required.  Float installation per Helio modification No. 15. 
M
aneuvering   94 m.p.h.  (  82 knots) CAS 
Minimum structural cruising 130 m.p.h.  (113 knots) CAS 
Never exceed 164 m.p.h.  (143 knots) CAS 
Flaps extended   80 m.p.h.  (  70 knots) CAS 
C. G. Range LANDPLANE 
(+ 101.3) to (+106.4) at 3000 lbs. 
(+  99.9) to (+106.4) at 2800 lbs. 
(+  96.5) to (+106.4) at 2200 lbs. or less 
Straight line variation between points given. 
F LOATPLANE 
(+ 101.3) to (+106.4) at 3000 lbs. 
(+  99.1) to (+106.4) at 2700 lbs. 
S KI INSTALLATION 
F ederal installation drawing 11R1241.  Federal AWB-3500A main skis and 
AWT-3500 tailwheel ski including 20 lbs. fixed ballast on tail wheel ski. 
Eligible with hydraulic conversion on ground and in flight.  Weight and  
balance shall be checked with ski in retracted and extended positions. 
(+101.3) to (+104.3) at 3000 lbs. 
(+  99.9) to (+104.3) at 2800 lbs. 
(+  96.5) to (+104.3) at 2200 lbs. or less 
Straight line variation between points given. 
E
mpty Weight C.G. Range None 
M aximum Weight  LANDPLANE  (H-391 and H-391B, S/N 001 through 031) 
2800 l bs. (eligible for 3000 lbs. when incorporating Helio modification 21, 
main landing gear assemblies 391-040-451-12 and -13, and tailwheel 
assembly 391-040-4101.) 
H-391B - S/N 032 and up:  3000 lbs.
F LOATPLANE  (H-391B only, S/N 001 through 031) 
2800 l bs., when Helio modification No. 21 incorporated. 
S/N 032 and up:  3000 lbs. 
N
o. of Seats 4  (2 at +103.5, 2 at +136.  S/N 066 and up eligible for 5th seat at +165)

3 of  14 1A8 
I. Model H-391  (USAF YL-24), Model H-391B     (cont'd)
M aximum Baggage  200 lb.  (+163) 
F
uel Capacity Model H-391 - 60 gal. total, 52.5 gal. usable (two 30 gal. tanks in wings 
 at +113) 
Model H-391B - S/N 001 through 087 (except 075), 61 gal. total, 
58.2 gal. usable two 30 gal. tanks in wings at +113. 
1 gal. header tank in fuselage) 
S/N 088 and up, 60.7 gal. total, 58.2 gal. usable 
(two 30.35 gal. tanks in wing at +113. 
No header tank) 
See NOTE 1 for data on system fuel. 
O
il Capacity Model H-391:  12 qt. (+37).  Model H-391B:  10 qt. (+37) 
Cont rol Surface Movements  LANDPLANE 
S tabilator (trailing edge) Up 19° Down 8° from neutral 
Neutral position is trailing edge down 2.5°. 
Stabilator trim tab (± 2°) Up 36° Down 20° 
Measured from stabilator chord line 
S
tabilator antibalance tab Within ± 2° of neutral - measured from 
stabilator chord line 
A
ileron (± 1°) Up 20° Down 20° 
Rudder (± 1°) 
  S/N 001 through 049 Right 30° Left  30° 
  S/N 050 and up Right 30° Left 25° 
Flaps Down 40° 
FL OATPLANE 
S tabilator (trailing edge) Up 17° Down 8° 
Anti-balance tab  
(trailing edge) Within ± 2° of neutral - measured from 
stabilator chord line 
Rudder Right 30° Left 20° 
S
erial Nos. Eligible Model H-391 - 1 only
Model H-391B - 001 and up
II. Model H-395 (USAF L-28A or U-10B)  (Courier), 5 PCL-SM (Normal Category), approved November 17, 1958
M odel H -395A (Courier), 5 PCL-SM (Normal Category), approved June 29, 1959
E
ngine Model H-395 - Lycoming GO-480-G1D6
Model H-395A - Lycoming GO-435-G2B2-6
Fu
el Model H-395 - 100/130 minimum grade aviation gasoline
Model H-395A - 80/87 minimum grade aviation gasoline
En
gine Limits Model H-395 - Takeoff 3400 r.p.m. (295 hp) 
All other operations 3000 r.p.m. (280 hp) 
Model H-395A - Takeoff 3400 r.p.m. (260 hp) 
All other operations 3000 r.p.m. (240 hp)

1A8 4 of 14 
 
II. Model H-395 (USAF L-28A or U-10B), Model H-395A    (cont'd) 
 Propeller and propeller limits Model H-395 - Hartzell controllable propeller (S/N 075, 502 through 
     514, 516 through 530) hub HC-93Z20-1B1, blades 10151C 
     or 10151C-5 
     Diameter:  not over 101 in., not under 95 in. 
     Pitch settings at 30 in. Sta:  Low 11.8°, high 30.8° 
     Propeller governor, Hartzell B-3 
     Propeller spinner, Hartzell 836-15 
 
     Hartzell controllable propeller (S/N 531 and up) 
     hub HC-B3Z20-1, blades 10151C or 10151C-5 
     Diameter:  not over 101 in., not under 95 in. 
     Pitch settings at 30 in. Sta:  Low 11.8°, high 30.8° 
     Propeller governor, Hartzell B-3 
     Propeller spinner, Hartzell 836-15 
 
  Model H-395A - (S/N 515, 1002 through 1005) Hartzell controllable 
     propeller, hub HC82X20-1A or HC82X20-1B, blades 10133D 
     Diameter:  not over 101 in., not under 95 in. 
     Pitch settings at 30 in. Sta:  Low 13°, high 31° 
     Propeller governor, Hartzell B-1 or B-3 
     Propeller spinner, Hartzell C-888 dome with C-807-2 bulkhead 
 
     (S/N 1006 and up)  Hartzell controllable propeller, 
     hub HC-A2X20-1, blades 10133D 
     Diameter:  not over 101 in., not under 95 n. 
     Pitch settings at 30 in. Sta:  Low 13°, high 31° 
     Propeller governor, Hartzell B-1 or B-3 
     Propeller spinner, Hartzell C-888 dome with C-807-2 bulkhead 
 
 Airspeed Limits LANDPLANE 
  Maneuvering (2800 lbs.)     94 m.p.h. (  82 knots) CAS 
  Maneuvering (3000 lbs.)     98 m.p.h. (  85 knots) CAS 
  Maximum structural cruising  150 m.p.h. (134 knots) CAS 
  Never exceed     189 m.p.h. (164 knots) CAS 
  Flaps extended       80 m.p.h. (  69 knots) CAS 
 
  FLOATPLANE  -  with Edo Model 249-2870 floats 
  H-395A (S/N 515, 1002 and up).  Float installation per Helio modification no. 31. 
 
  Maneuvering       95 m.p.h. (  83 knots) CAS 
  Minimum structural cruising  130 m.p.h. (113 knots) CAS 
  Never exceed     164 m.p.h. (143 knots) CAS 
  Flaps extended       80 m.p.h. (  70 knots) CAS 
 
 C.G. Range LANDPLANE  
  (+101.3) to (+106.4) at 3000 lbs. 
  (+  99.9) to (+106.4) at 2800 lbs. 
  (+  96.5) to (+106.4) at 2200 lbs. or less 
  Straight line variation between points given. 
 
  FLOATPLANE 
  (+101.3) to (+106.4) at 3000 lbs. 
  (+ 99.1) to (+106.4) at 2700 lbs. or less

5 of 14 1A8 
 
II. Model H-395 (USAF L-28A or U-10B), Model H-395A    (cont'd) 
   
  SKI INSTALLATION 
  Federal installation drawing 11R1241.  Federal AWB-3500A main skis and 
  AWT-3500 tailwheel ski including 20 lb. fixed ballast on tailwheel ski.  Eligible 
  with hydraulic conversion on ground and in flight.  Weight and balance shall 
  be checked with ski in retracted and extended positions. 
 
  (+101.4) to (+104.3) at 3000 lbs. 
  (+  99.9) to (+104.3) at 2800 lbs. 
  (+  96.5) to (+104.3) at 2200 lbs. 
  Straight line variation between points given. 
 
 Empty Wt. C.G. Range None 
 
 Maximum Weight LANDPLANE 
  3000 lbs. 
 
  FLOATPLANE    (H-395A only) 
  3000 lbs. 
 
 No. of Seats 5  (2 at +103.5, 2 at +136, 1 at +165) 
 
 Maximum Baggage 200 lbs.  (+163) 
 
 Fuel Capacity 60.7 gal. total, 58.2 gal. usable (two 30.35 gal. tanks in wings at +113). 
  (No header tank) 
  See NOTE 1 for data on system fuel. 
 
 Oil Capacity 10 qt.  (+37) 
 
 Control Surface Movements LANDPLANE 
  Stabilator (trailing edge (±0°)) Up 19°  Down 8° from neutral 
      Neutral position is trailing edge down 2.5°. 
 
  Stabilator trim tab (±2°)  Up 36°  Down 20° 
      Measured from stabilator chord line 
 
  Stabilator anti-balance  Within ±2° of neutral - measured from 
   tab (±2°)    stabilator chord line 
 
  Aileron (±1°)    Up 20°  Down 20° 
  Rudder (±1°)    Right 30°  Left 25° 
  Flaps (±1°)       Down 40° 
 
  FLOATPLANE 
  Stabilator (trailing edge)  Up 17°  Down   8° 
  Anti-balance tab  
   (trailing edge)    Within ±2° of neutral - measured from 
       stabilator chord line 
  Rudder    Right 30°  Left 20° 
 
 Serial Nos. Eligible Model H-395  -  075, 502 through 514, 516 and up 
  Model H-395A  -  515, 1002 and up 
  USAF U-10B airplanes are eligible for a civil airworthiness certificate when 
  converted in accordance with Helio Drawing 395-000-050.

1A8 6 of 14 
III. Model H-250 (Courier), 6 PCL-SM (Normal Category), Approved November 6, 1964
Sam e as Model H -395 except for powerplant installation, increased gross weight, and minor structural changes. 
E
ngine Lycoming O-540-A1A5 
Fuel 100/130 minimum grade aviation gasoline 
Engine limits For all operations, 2575 r.p.m.  (250 hp.) 
P
ropeller and Hartzell controllable propeller, Hub HC-92WK-1D, blades W8847 
  propeller limits Diameter:  not over 88 in., not under 86 in. 
Pitch settings at 30 in. Sta:  Low 12° ± .2°, high 28.5° ± .5° 
Propeller governor, Hartzell F-6-8  (S/N 2501 through 2520), 
Hartzell F-6-8L (S/N 2521 and up).  Propeller spinner, Hartzell C-2513-3. 
A
irspeed limits Maneuvering   94 m.p.h. (  82 knots) CAS 
Maximum structural cruising 150 m.p.h. (134 knots) CAS 
Never exceed 189 m.p.h. (164 knots) CAS 
Flaps extended   80 m.p.h. (  69 knots) CAS 
C. G. Range LANDPLANE 
(+ 105.0) to (+110.0) at 3400 lbs. 
(+  97.5) to (+110.0) at 2150 lbs. or less 
Straight line variation between points given. 
F LOATPLANE  -  with Edo model 582-3430 floats 
S /N 2501, 2506 and up.  Installation per Helio drawing 250-000-015. 
(+
102.5) to (+109.0) at 3400 lbs. 
(+  99.4) to (+109.0) at 2900 lbs. 
(+  97.6) to (+109.0) at 2460 lbs. or less 
Straight line variation between points given. 
E
mpty Wt. C.G. Range None 
Maximum weight 3400 lbs. 
No. of seats 6  (2 at +103.5, 2 at +136, 2 at +162) 
M
aximum baggage 340 lbs. (+162) when 2-passenger aft sling seat is unoccupied 
F
uel capacity 
  standard system 60.7 gal. total, 58.2 gal. usable (two 30.35 gal. tanks in wings at +113) 
O
ptional auxiliary Additional 60 gal. wing installed auxiliary fuel system, Helio P/N 250-080-901 
  fuel system and wing assembly P/N 250-010-050  
See NOTE 1 for data on system fuel. 
O
il capacity 12 qt.  (+22) 
Cont
rol surface movements Stabilator 
  (trailing edge (±1°)) Up 19° Down 10° from neutral 
Neutral position is trailing edge down 2.5°. 
Stabilator trim tab (±2°) Up 36° Down 20° 
Measured from stabilator chord line 
Stabilator anti-balance tab Within ±2° of neutral - measured from  
stabilator chord line 
Aileron   (±1°) Up 20° Down 20° 
Rudder  (±1°) Right 30° Left 25° 
Flaps  (±1°) Down 40° 
S
erial nos. eligible 2501 and up

7 of 14 1A8 
 
IV.  Model H-295 (USAF U10D, (Courier), 6 PCL-SM (Normal Category), approved April 15, 1965 
 Same as Model H-295 except for engine installation. 
 
 Engine Lycoming GO-480-G1D6 - Slow speed (1.250:1) generator drive 
   or Lycoming GO-480-G1A6  -  High speed (2.577:1) generator drive 
 Fuel 100/130 minimum grade aviation gasoline 
 Engine limits Takeoff  3400 r.p.m.  (295 hp) 
  All other operations  3000 r.p.m.  (280 hp) 
   
 Propeller and propeller Hartzell constant speed propeller, Hub HC-B3Z20-1, blades 10151C 
   limits Diameter:  96 in.  (1 in. reduction permitted) 
  Pitch settings at 30 in. Sta:  Low 11.8°, high 30.8° 
  Propeller governor, Hartzell B-3 
  Propeller spinner, Hartzell 836-15R  (supersedes Hartzell 836-15) 
 
 Airspeed limits Maneuvering  103 m.p.h.  (  89 knots) CAS 
  Maximum structural cruising  160 m.p.h.  (140 knots) CAS 
  Never exceed  200 m.p.h.  (174 knots) CAS 
  Flaps extended    80 m.p.h.  (  69 knots) CAS 
 
 C.G. Range LANDPLANE 
  (+103.8) to (+110.0) at 3400 lbs. 
  (+  98.9) to (+110.0) at 2760 lbs. 
  (+  97.0) to +110.0) at 2330 lbs. or less 
  Straight line variation between points given. 
 
  FLOATPLANE 
  Float installation per Helio drawing 250-000-015 
  (+102.0) to (+109.0) at 3400 lbs. 
  (+  98.0) to (+109.0) at 2600 lbs. or less 
  Straight line variation between points given. 
 
 Empty weight C. G. range None 
 Maximum weight 3400 lbs. 
 No. of seats 6  (2 at +103.5, 2 at +136, 2 at +162) 
 Maximum baggage 340 lbs.  (+162) when 2-passenger aft sling seat is unoccupied 
 Fuel capacity standard 60.7 gal., total, 58.2 gal. usable (two 30.35 gal. tanks in wings at +113) 
   system 
 
 Optional auxiliary fuel system Additional 60 gal. wing installed auxiliary fuel system, Helio P/N 250-080-901 
  and wing assembly P/N 250-010-050 
  See NOTE 1 for data on system fuel. 
 
 Oil capacity 12 qt.  (+37) 
 
 Control surface movements Stabilator Up 19° Down 10° from neutral 
    (trailing edge (±1°)) Neutral position is trailing edge down 2.5° 
  Stabilator trim tab (±2°) Up 36° Down 20° 
    Measured from stabilator chord line 
  Stabilator anti-balance tab Within ±2° of neutral - measured from 
    stabilator chord line 
  Aileron  (±1°) Up 20° Down 20° 
  Rudder  (±1°) Right 30° Left 25° 
  Flaps  (+0°, -2°)   Down 40° 
 
 Serial nos. eligible 1201 through 1233, 1278 and up; S/N 1234 through 1277 (USAF 66-14332 
  through 66-14375) eligible when converted in accordance with Helio drawing 
  295-000-020.

1A8 8 of 14 
 
V.  Model HT-295 (Courier), 6 PCLM (Normal Category), approved December 18, 1973  Tricycle Version of Model H-295 
 
 Engine Lycoming GO-480-G1D6 
  Lycoming GO-480-G1A6 
 
 Fuel 100/130 minimum grade aviation gasoline 
 
 Engine limits Takeoff  3400 r.p.m.  (295 hp) 
  All other operations  3000 r.p.m.  (280 hp) 
 
 Propeller and propeller limits Hartzell constant speed propeller, Hub HC-B3Z20-1, blades 10151C 
  Diameter:  96 in. (1 in. reduction permitted) 
  Pitch settings at 30 in. sta:  Low 11.8°, high 30.8° 
  Propeller governor, Hartzell B-3 
  Propeller spinner, Hartzell 836-15R (supersedes Hartzell 836-15) 
   
 Airspeed Limits Maneuvering  103 m.p.h.  (  89 knots) CAS 
  Maximum structural cruising  160 m.p.h.  (140 knots) CAS 
  Never exceed  200 m.p.h.  (174 knots) CAS 
  Flaps extended    80 m.p.h.  (  69 knots) CAS 
 
 C.G. Range LANDPLANE 
  (+103.8) to (+110.0) at 3400 lbs. 
  (+  98.9) to (+110.0) at 2760 lbs. 
  (+  97.0) to (+110.0) at 2330 lbs. or less 
  Straight line variation between points given 
 
 Empty Wt. C.G. Range None 
 
 Maximum weight 3400 lbs. 
 
 No. of seats 6  (2 at +103.5, 2 at +136, 2 at +162) 
 
 Maximum baggage 340 lbs.  (+162) when 2-passenger aft sling seat is unoccupied. 
 
 Fuel capacity 60.7 gal. total, 58.2 gal. usable (two 30.35 gal. tanks in wings at +113) 
  See NOTE 1 for data on system fuel. 
 
 Oil capacity 12 qt.  (+37) 
 
 Control surface movements Stabilator Up 19° Down 10° from neutral 
    (trailing edge (±1°)) Neutral position is trailing edge down 2.5°. 
 
  Stabilator trim tab (±2°) Up 36° Down 20° 
    Measured from stabilator chord line 
 
  Stabilator anti-balance tab Within ±2° of neutral - measured from 
    stabilator chord line 
 
  Aileron (±1°) Up 20° Down 20° 
  Rudder (±1°) Right 30° Left 25° 
  Flaps (+0°, -2°)   Down 40° 
 
 
 Serial Nos. eligible 1701 and up

9 of 14 1A8 
 
VI. Model H-800 (Courier), 4 PCSM  (Normal Category), approved July 19, 1983; 6 PCLM (Normal category), 
 approved September 28, 1983 
 Same as Model HT-295 except for powerplant installation, increased gross weight, structural changes, and 
 miscellaneous minor changes. 
 
 Engine Lycoming IO-720-A1B 
 
 Fuel 100/100LL minimum grade aviation gasoline 
 
 Engine limits 2650 r.p.m.  (400 hp) 
 
 Propeller and propeller limits Hartzell constant speed propeller, Hub HC-C3YR-1RF, blades F8475R 
  Diameter:  86 in. 
  Pitch settings at 30 in. sta:  Low 11.8°, high 30.8° 
  Propeller governor, Hartzell FA-3A 
  Propeller spinner, Hartzell A2295-1 
 
 Airspeed limits (CAS) Maneuvering    93 knots 
  Maximum structural cruising  133 knots 
  Never exceed  168 knots 
  Flaps extended - 40°    83 knots 
  Flaps extended - 15°    96 knots 
 
 C.G. Range LANDPLANE 
  (+102.0) to (+109.0) at 4000 lbs. (max. takeoff weight) 
  (+101.0) to (109.0) at 3800 lbs. (max. landing weight) 
  (+ 98.0) to (+109.0) at 3200 lbs. or less 
  Straight line variation between points given. 
 
  FLOATPLANE 
  Floatplane Model: 
   Edo-Aire 696-3500 
   (+104.0) to (+110.0) at 3888 lbs. 
   (+101.0) to (+110.0) at 3200 lbs. or less 
 
   Edo-Aire 582-3430 
   (+104.0) to (+110.0) at 3800 lbs. 
   (+101.0) to (+110.0) at 3200 lbs. or less 
 
 Empty Weight C.G. Range None 
 
 Maximum Weight LANDPLANE 
  4000 lbs. takeoff 
  3800 lbs. landing 
 
  FLOATPLANE 
  Edo-Aire 696-3500 amphibious 
   Water operations: 
   3888 lb. takeoff 
   3800 lb. landing 
 
   Land operations: 
   3790 lb. takeoff 
   3600 lb. landing 
 
  Edo-Aire 582-3430 
   3800 lb. takeoff and landing

1A8 10 of 14 
 
VI. Model H-800 (Courier)    (cont'd) 
 
 Zero Fuel Weight 3800 lbs. 
 
 No. of Seats LANDPLANE  
  6  (2 at +103.5, 2 at +136.0, 2 at +162.0) 
 
  FLOATPLANE 
  696-3500 amphibious 
   4 (2 at +103.5 and 2 at +136.0, restricted to 306 lb. total weight) 
 
  582-3430 
   4 (2 at +103.5 and 2 at +136.0), restricted to 213 lb. total weight) 
 
 Maximum Baggage LANDPLANE 
  Total load AFT of pilot's seat  -  40 lb. per sq. ft. 
  10 lb. per sq. ft. in luggage compartment 
  See AFM for loadings. 
 
  FLOATPLANE 
  40 lb. per sq. ft. rear seat and cargo area 
  Combined loadings rear passenger seats - 218 lb.  
  See AFM for loadings. 
 
 Fuel Capacity LANDPLANE 
  121.4 gal. total, 120.5 gal. usable (four 30.35 gal. tanks in wing at +113) 
  See NOTE 1 for data on fuel system. 
 
  FLOATPLANE 
  696-3500 amphibious and 582-3430 floats 
   60.7 gal. total, 60.2 gal. usable at +113 
 
 Oil Capacity 19 qt. maximum, 17 qt. normal (+37) 
 
 Control Surface Movements Stabilator  Up 10° Down 21° from neutral 
   Leanding edge (±1°) Neutral position is trailing edge down 2.5°. 
 
  Stabilator trim tab (±2°) Up 30° Down 28°  
    Measured from stabilator chord line 
 
  Stabilator anti-balance tab Within ±2° of neutral - measured from 
    stabilator chord line 
 
  Aileron droop 0.87"  (±.07") 
  Aileron (±1°) Up  20° Down 20° 
  Rudder (±1°) Right 30° Left 25° 
  Flaps (±1°)   Down 40° 
  Interceptor retracted position Below surface of wing, 0.38" to 0.50" 
 
 Serial nos. eligible H-1 and up

11 of 14 1A8 
 
VII. Model H-700 (Courier), 6 PCLM (Normal Category), approved January 24, 1984 
 Same as Model HT-295 except for powerplant installation, increased gross weight, structural changes, and 
 miscellaneous minor change. 
 
 Engine Lycoming TIO-540-J2B 
 Fuel 100/100LL minimum grade aviation gasoline 
 Engine limits 2575 r.p.m.  (350 hp) 
  49 inches M.P. 
 
 Propeller and propeller limits Hartzell constant speed propeller, Hub HC-E3YR-1RF, blades: F9587A-10 
  Diameter:  87 in. 
  Pitch settings at 30 in. sta:  Low 12.7°, high 31.0° 
  Propeller governor,  Hartzell FA-13 
    Serial No. H-7 through H-10 
    Hartzell F4-30 
     Serial No. H-11 and subsequent 
     Service replacement H-7 through H-10 
  Propeller governor, Hartzell A2295-1 
 
 Airspeed limits (CAS) Maneuvering      93 knots 
  Maximum structural cruising  133 knots 
  Never exceed    168 knots 
  Flaps extended - 40°       83 knots 
  Flaps extended - 15°      96 knots 
 
 C.G. Range LANDPLANE 
  (+101.0) to (+108.5) at 3800 lbs. 
  (+  98.0) to (+108.5) at 2600 lbs. or less 
  Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 Maximum weight 3800 lbs. 
 No. of seats LANDPLANE 
  6  (2 at +103.5, 2 at +136.0, 2 at +162.0) 
 
 Maximum Baggage LANDPLANE 
  Total load AFT of pilot's seat - 40 lb. per sq. ft. 
  10 lb. per sq. ft. in luggage compartment.   See AFM for loadings. 
 
 Fuel Capacity LANDPLANE 
  121.4 gal. total, 120.5 gal. usable (four 30.35 gal. tanks in wing at +113). 
  See NOTE 1 for data on fuel system. 
 
 Oil Capacity 12 qt. maximum, 10 qt. normal (+37) 
 
 Control Surface Movements Stabilator   Up 10° Down 21° from neutral 
   Leading edge  (±1°)  Neutral position is trailing edge down 2.5°. 
  Stabilator trim tab  (±2°)  Up 30° Down 28° 
      Measured from stabilator chord line 
  Stabilator anti-balance tab Within ±2° of neutral - measured from 
      stabilator chord line 
  Aileron droop   0.87"  (±.07") 
  Aileron (±1°)   Up  20° Down 20° 
  Rudder (±1°)   Right 30° Left 25° 
  Flaps (±1°)     Down 40° 
  Interceptor retracted position Below surface of wing, 0.38" to 0.50" 
 Serial Nos. Eligible H-1 and up

1A8 12 of 14 
DATA PERTINENT TO ALL MODELS 
Datum 60 in. forward of fuselage station 0.  (Sta. 0 is at upper attachment of engine 
mount to fuselage).  For weight and balance purposes, Station 100.25 is the 
centerline of wing spar (midway between two rows of bolts in wing root 
fitting on bottom side of wing). 
L
eveling Means Model H-391: Plumb line markers at top and bottom of right door 
frame (fuselage station 60). 
Models H-250, H-295, H-391B, H-395A, H-700, H-800:  Two leveling 
studs at lower forward corner of right door frame. 
Ce
rtification Basis Part 3 of the Civil Air Regulations effective November 1, 1949, as amended 
to May 16, 1953.  Type Certificate No. 1A8 issued August 5, 1953.  Application 
for Type Certificate dated May 1, 1951. 
P
roduction Basis None.  Prior to original certification, an FAA representative must perform a detailed 
inspection for workmanship, materials, and conformity with the approved technical data, 
a final inspection of the completed aircraft, and a check of the flight characteristics.  
E
quipment The basic required equipment as prescribed in the applicable airworthiness 
regulations (see Certification Basis) must be installed in the aircraft for 
certification.  The equipment portion of Aircraft Specification 1A8, Revision 18, 
dated July 7, 1969, or the equipment list provided with each airplane should be 
used for equipment references on Helio Models H-391, H-391B, H-395, H-395A, 
H-250, and H-295 (prior to serial number 1458).  Refer to the applicable
equipment list for Model H-295, serial number 1458 and on, Model H-700,
and Model H-800.  In addition, the following FAA approved Airplane Flight
Manuals and Airplane Flight Manual Supplements are required.
(a
) FAA Approved Airplane Flight Manual dated February 9, 1956 (H-391B,
S/N 001 through 031); dated November 3, 1956 (H-391B, S/N 032 and up
and for those S/N 001 through 031 modified oer Helio Modification 21).
(b) F
AA Approved Airplane Flight Manual Supplement dated January 24, 1956
(H-391B, H-395, H-395A) required when Federal AWB-3500A main and
AWT-3500 tailwheel skis are installed.  Federal Installation drawing 11R1241.
(c
) FAA Approved Airplane Flight Manual Supplement dated July 18, 1956
(H-391B, H-395A) required when EDO Model 249-2870 floats are installed.
(d) F
AA Approved Airplane Flight Manual dated November 17, 1958 (H-395).
(e
) FAA Approved Airplane Flight Manual dated June 29, 1959 (H-395A).
(f) F
AA Approved Airplane Flight Manual Supplement dated January 30, 1961,
revised August 20, 1963  (H-391B, H-395, H-395A) required when crosswind
gear lock installed.
(g) F
AA Approved Airplane Flight Manual dated November 6, 1964 (H-250).
(h) F
AA Approved Airplane Flight Manual Supplement No. 1 dated March 22,
1965, (H-250) required when 60 gal. wing installed auxiliary fuel system,
Helio P/N 250-080-901-0 and wing assemblies P/Ns 250-010-050-0 and -1
installed.
(i
) FAA Approved Airplane Flight Manual Supplement No. 2 dated April 16,
1965 (H-250) required when Edo Model 582-3430 floats installed.

13  of 14 1A8 
(j ) FAA Approved Airplane Flight Manual dated April 8, 1965 (H-295 and HT-295).
(k) F
AA Approved Airplane Flight Manual Supplement No. 1 dated April 23, 1965
(H-295 and HT-295) required when 60 gal. wing installed auxiliary fuel
system, Helio P/N 250-080-901-0 and wing assemblies P/Ns 250-010-050-0 and
-1 installed.
(l
) FAA Approved Airplane Flight Manual Supplement No. 2 dated November 24,
1965 (H-295) required when Edo Model 582-3430 floats installed.
(
m) FAA Approved Airplane Flight Manual Supplement No. 3 dated January 19,
1967 (H-295) required when 60 gal. 4 valve wing installed auxiliary fuel
system, Helio drawing 295-080-910 and -911, and wing assemblies
Helio P/Ns 295-010-050-0 and -1 installed.
(n) F
AA Approved Airplane Flight Manual Supplement No. 4 dated January 19,
1968 (H-295 and HT-295) required when alternate static source, Helio
P/N 295-100-900-10 is installed.
(o) F
AA Approved Airplane Flight Manual Supplement No. 5 dated July 26,
1968 (H-295) required when optional electric flaps and trim, Helio
P/N 295-052-900-0 is installed.
(p) F
AA Approved Airplane Flight Manual Supplement (No. 5 for H-250,
No. 6 for H-295 and HT-295) dated December 10, 1968 (H-250, H-295,
H-391B, H-395, H-395A) required for flight with one door removed.
(q) F
AA Approved Airplane Flight Manual Supplement No. 7 dated
October 23, 1969 (H-295) required when optional Goodyear iceguard
kit no. 320-639 (24V) or No. 320-641 (12V) Helio P/Ns 295-066-901-0
(24V) and 295-066-901-2 (12V).
(r) F
AA Approved Airplane Flight Manual Supplement NO. 8 dated April 13,
1970 (H-295 and HT-295) required when optional AK256 Mitchell
stabilizer installed.
(
s) FAA Approved Airplane Flight Manual Supplement No. 8 dated
November 15, 1973 (H-295 and HT-295) required for Electric Flap and
Pitch Trim Tab.
(t
) FAA Approved Airplane Flight Manual dated July 14, 1983, revised
September 27, 1983, or revised January 24, 1984 (H-800 equipped with
Edo 696-3500 amphibian floats, 582-3430 floats, or 39-4000 floats).
(u) F
AA Approved Airplane Flight Manual dated September 27, 1983, or
re vised for 4000 lb. gross weight dated April 11, 1984 (H-800).
(v) F
AA Approved Airplane Flight Manual dated January 18, 1984 (H-700).
NOT
E 1. Current weight and balance report including list of equipment included in certificated empty  
weight, and loading instructions when necessary, must be provided for each aircraft at the 
time of original certification.  The certificated empty weight and corresponding center of 
gravity location must include unusable fuel of 44 lb. at (+113) for H-391, or unusable fuel 
of 16 lb. at (+133) for H-391B, S/N 001 through 087.  H-391B, H-395, H-395A, unusable fuel 
of 15 lb. at (+113).  H-250, H-295, HT-295, with 120 gal., 4 valve fuel system installed, 
unusable fuel of 30 lb. at (+113).  H-800, 2 tank system unusable fuel of 0.5 gal. at (+113), 
H-700/H-800, 4 tank system unusable fuel of 0.9 gal. at (+113).

1A8 14 of 14 
NOTE 2. The following placards must be displayed: 
A. In full  view of the pilot:
(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."
(2) "No acrobatic maneuvers including spins approved."
(3) Deleted December 5, 1955.
(4) Model H-391:  "Continuous ground operation between 1675 and 2150 r.p.m. prohibited."
Model H-391B incorporating Lycoming GO-435-C2B or GO-435-C2B2:
"Avoid continuous operation between 2600 and 2975 r.p.m."  Placard not required
when Lycoming GO-435-C2B2-6 installed (S/N 082 and up).
(5) "One minute limit for takeoff power, full throttle and 3400 r.p.m."
(All models except H-250, H-800, H-700)
(6) "See Flight Manual Supplement for airspeed-altimeter error" (H-295 and HT-295)
when alternate static source, Helio P/N 295-100-900-10, is installed.
(7) "For flight with door removed see aircraft operations limitations with door removed"
(H-250, H-295, HT-295, H-391B, H-395, H-395A) when operating with one door removed.
(8) "This aircraft is not to be flown into known icing conditions"  (H-295 with installation
of Goodyear iceguard kits no. 320-639 (24V) or No. 320-641 (12V), Helio P/Ns
295-066-901-0 (24V) and 295-066-901-2 (12V).
(9) Models H-700, H-800 "Design maneuvering speed 93 kts."
(10) Models H-700, H-800 "Master Switch OFF when A.P.U. is connected."
(11) Models H-700, H-800 "Turn Beacon OFF during IFR"
(12) Models H-700, H-800 "See AFM for ALTERNATE STATIC SOURCE CALIBRATION"
(13) Models H-700, H-800 "No Smoking"
(14) Model H-700 "T.I.T. Limit 1550 F"
(15) Model H-700 "Do not operate at more than 30" MP below 2400 r.p.m."
B. On t he left forward window sill:
(1) "Do not open this window above 80 CAS."  (Not required on Model H-295, HT-295, H-800,
and H-700)
C. Insi de the gascolator box cover (H-391 only):
(1) "Fuel shut-off valves - rear valve L/H, front valve R/H tank.
To open, turn valves counter-clockwise seven turns or more, and safety."
D. Del eted.
E. In proxi mity of fuel transfer pump switches when auxiliary fuel system is installed:
"Caution: Monitor fuel quantity during auxiliary transfer to avoid overflow. 
(Level flight only)." 
F. In vic inity of fuel control valves when 120 gal., 4 valve system is installed:
"Both mains on for takeoff and landing." 
"Left auxiliary level flight only." 
"Right auxiliary level flight only." 
G. In proxim ity of Magnavox FM-622A control (when installed).
"Homing operation unreliable above 50 MHZ." 
NOTE
 3. 
NOTE
 4. 
Airworthiness Limitations for any mandatory retirement life or mandatory inspection are included in the 
Maintenance Manual (Instructions for Continued Airworthiness) for each model. 
Type Certificate Holder Record: 
Reissued to Helio Aircraft Company August 1, 1969 
Reissued to Helio Aircraft Limited November 8, 1976 
Reissued to Helio Inc. August 10, 1984 
Reissued to Helio Aircraft, Inc. August 23, 1984 
Reissued to Helio Enterprises, Inc. August 11, 1994 
Reissued to Alliance Aircraft Group, LLC September 18, 1997 
Reissued to Alliance Aircraft Group, LLC dba Helio Aircraft Company April 10, 2001 
Reissued to Helio Aircraft, LLC July 14, 2005 
Reissued to Helio Alaska, Inc. March 30, 2020  
.....END.....
```

## ADs (17, in force first)

- [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023
- [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 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 2006-03-08](https://openairdocs.org/ad/2006-03-08): Vacuum pumps · Aero Advantage 14-19, 14-19-2, 14-19-3 and 299 more. Effective Mar 10, 2006
- [AD 2005-25-08](https://openairdocs.org/ad/2005-25-08): Electronic Flight Information System (EFIS) · B-N Group BN-2A, 172, 180 and 22 more. Effective Jan 23, 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
- [AD 87-04-09](https://openairdocs.org/ad/87-04-09): Landing Gear Legs · Helio H-700 and H-800. Effective Mar 9, 1987
- [AD 82-16-08](https://openairdocs.org/ad/82-16-08): Left and Right Main Spar Carry-Thru Assembly · Helio H-250, H-295 (USAF U10D), H-391 (USAF UL-24) and 4 more. Effective Aug 3, 1982
- [AD 81-19-04](https://openairdocs.org/ad/81-19-04): Hose Assembly · Rajay Hose Assemblies, 500A, 500B and 87 more. Effective Sep 17, 1981
- [AD 79-07-02](https://openairdocs.org/ad/79-07-02): Batteries · Aircraft Parts & Development A, A-2, A-3 and 149 more. Effective Apr 3, 1979
- [AD 63-18-02](https://openairdocs.org/ad/63-18-02): Engine Breather · Helio H-391B, H-395 (USAF L-28A or U-10B) and H-395A. Effective Sep 1, 1963
- [AD 56-22-02](https://openairdocs.org/ad/56-22-02): Wing Attachment Washers · Helio H-391B
- [AD 57-25-02](https://openairdocs.org/ad/57-25-02): Fin Spar Inspection · Helio H-391B
- [AD 58-01-04](https://openairdocs.org/ad/58-01-04): Aileron Bellcrank Inspection · Helio H-391B
- [AD 58-25-04](https://openairdocs.org/ad/58-25-04): Fin Hinge Attachment · Helio H-391B and H-395 (USAF L-28A or U-10B)
- [AD 59-17-05](https://openairdocs.org/ad/59-17-05): Horizontal Tail Spar Fitting · Helio H-391B and H-395 (USAF L-28A or U-10B)
- [AD 59-17-06](https://openairdocs.org/ad/59-17-06): Pulley Guards · Helio H-391B and H-395 (USAF L-28A or U-10B)

## Registered aircraft by registry model (OpenAirDocs)

- [Helio H-295](https://openairdocs.org/model/helio-h-295): 54 aircraft (registry code 4300802)
- [Helio H-391B](https://openairdocs.org/model/helio-h-391b): 16 aircraft (registry code 4300106)
- [Helio H-395](https://openairdocs.org/model/helio-h-395): 16 aircraft (registry code 4300202)
- [Helio HT-295](https://openairdocs.org/model/helio-ht-295): 13 aircraft (registry code 4300803)
- [Helio H-250](https://openairdocs.org/model/helio-h-250): 11 aircraft (registry code 4300302)
- [Helio H800](https://openairdocs.org/model/helio-h800): 6 aircraft (registry codes 4300500, 4300501)
- [Helio H-700](https://openairdocs.org/model/helio-h-700): 4 aircraft (registry code 4300400)
- [Helio H-391](https://openairdocs.org/model/helio-h-391): 1 aircraft (registry codes 4300102, 4300105)
- [Helio H-395A](https://openairdocs.org/model/helio-h-395a): 1 aircraft (registry code 4300206)
- [Helio-Jungle Avn. & Radio SVC. H-295](https://openairdocs.org/model/helio-jungle-avn-radio-svc-h-295): 0 aircraft (registry code 4300801)

## STCs approved under this data sheet (230, first 50)

- [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 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 SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position  Light System, and applicable associated power supplies. Whelen Aerospace Technologies
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA2261CE](https://openairdocs.org/stc/SA2261CE): Increase gross weight from 3,000 lbs. to 3,800 lbs.. Helio Alaska Inc.
- [STC SA490SW](https://openairdocs.org/stc/SA490SW): Installation of ALCOR turbocharger.. Alcor Aviation LLC
- [STC SA1467CE](https://openairdocs.org/stc/SA1467CE): Increase in maximum gross weight from 3,000 lbs. to 3,300 lbs.. Helio Alaska Inc.
- [STC SA1589CE](https://openairdocs.org/stc/SA1589CE): Increase in maximum gross weight from 3,400 lbs. to 3,800 lbs.. Helio Alaska Inc.
- [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 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 SA1432CE](https://openairdocs.org/stc/SA1432CE): Installation of utility door on left side of airplane. Helio Alaska Inc.
- [STC SA1936CE](https://openairdocs.org/stc/SA1936CE): Installation of Lycoming TIO-540-J2B engine and Hartzell HC-E3YR-IRF/F9587A-10 propeller.. Helio Alaska Inc.
- [STC SA2130CE](https://openairdocs.org/stc/SA2130CE): Installation of window which may be opened inflight, located at forward right side window.. Helio Alaska Inc.
- [STC SA2171CE](https://openairdocs.org/stc/SA2171CE): Replacement of fiberglass main landing gear legs with aluminum parts.. Helio Alaska Inc.
- [STC SA2337CE](https://openairdocs.org/stc/SA2337CE): Repair scheme for main landing gear assemblies. Helio Alaska Inc.
- [STC SA916SO](https://openairdocs.org/stc/SA916SO): Installation of Cessna seat rails and seats.. Helio Alaska Inc.
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [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 SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA125SO](https://openairdocs.org/stc/SA125SO): Installation of Turbocharged Lycoming G0-480- G1D6 engine (STC SE124SO). TALCO Aviation
- [STC SA156SO](https://openairdocs.org/stc/SA156SO): Installation of Turbocharged Lycoming G0-480-G1D6 engine (STC SE124SO) per FAA Sealed Roto-Master (Rajay/Riley) drawing List R0018. FAA approved Flight Manual Supplement, dated November 24, 1965 or later, FAA approved revision and Roto-Master (RAJAY/Riley) Turbo Owner s Manual required with this installation.. TALCO Aviation
- [STC SA1592WE](https://openairdocs.org/stc/SA1592WE): Installation of automatic fuel mixture control.. TALCO Aviation
- [STC SA02576AK](https://openairdocs.org/stc/SA02576AK): Installation of Cleveland and ABI, LLC Wheel and Brake Kits. ABI LLC
- [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc
- [STC SA1686WE](https://openairdocs.org/stc/SA1686WE): Installation of Vibration Isolation Products (VIP) engine mount P/Ns VIP 50525-1 and VIP 50545-1 on various aircraft as shown on FAA Approved Model List (AML) No. SA1686WE.. FTG, Inc.
- [STC SA1845WE](https://openairdocs.org/stc/SA1845WE): Installation of Vibration Isolation Products (VIP) engine mount P/N VIP-50804-20 on various aircraft as shown on FAA Approved Model List (AML) No. SA1845WE.. FTG Inc.
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc.
- [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 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 SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King)
- [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 SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc.
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems
- [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc

All 230: https://openairdocs.org/tcds/1A8/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.