# TCDS 4H11: Siam Hiller Holdings Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Siam Hiller Holdings Inc.
- Revision: 18
- Revised: January 6, 2010
- Product: Aircraft, Rotorcraft
- Certification basis: Part 21, Part 133, CAR 6
- Registered aircraft: 109, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/c1/11/c111330147d79154e6037461b37954c189e491d38bda238745d5b1eccf4da2e2
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/F9CE682AF6F2F299862576E9004DD718.0001
- Page: https://openairdocs.org/tcds/4H11

## Models (2)

As the data sheet lists them.

- UH-12E ((Army OH-23G)(Army H-23F))
- UH-12E-L

## 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 
Rev. No. 18 16 18 17 18 18 18 18 18 16 17 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
4H11 
Revision 18 
SIAM HILLER 
UH-12E 
UH-12E-L 
(Army OH-23G) 
(Army H-23F) 
January 6, 2010 
 
TYPE CERTIFICATE DATA SHEET NO. 4H11 
This data sheet which is a part of type certificate No. 4H11 prescribes conditions and limitations under which the 
product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. 
  
Type Certificate Holder: Siam Hiller Holdings, Inc. 
925 M. Street 
Firebaugh, California 93622-2234 
Type Certification Ownership  Hiller Aircraft Corporation transferred TC 4H11 to  
Records: Fairchild Industries, Inc. on 10/2/1959 
 Fairchild Industries, Inc. transferred TC 4H11 to  
 Heli-Parts, Inc. on 12/28/1972 
 Heli-Parts, Inc. transferred TC 4H11 to  
 Hiller Aviation on 12/28/1972 
 Hiller Aviation transferred TC 4H11 to  
Rogerson Aircraft Corporation on 6/26/1984 
 Rogerson Aircraft Corporation transferred TC 4H11 to  
Hiller Helicopters, a wholly owned subsidiary of Rogerson Aircraft Corporation 
on 6/29/1984 
 Hiller Helicopters, a wholly owned subsidiary of Rogerson Aircraft Corporation 
transferred TC 4H11 to Rogerson Hiller Corporation on 11/14/1985 
 Rogerson Hiller Corporation transferred TC 4H11 to  
Siam Hiller Holdings, Inc. on 7/14/1994 
I. Model UH-12E, Approved January 6, 1959 (Army OH-23G and H-23F)  
Engine Lycoming VO-540-A1A, VO-540-B1A, VO-540-B1D, VO-540-B1E, VO-540-
C1A, VO-540-C1B, VO-540-B2D, VO-540-C2A, VO-540-B2E, VO-540-C2B, 
or VO-540-C2C.  See Engine TCDS E-304 for more details.  (Refer to 
appropriate Hiller Service Bulletin for requirements for interchanging engine 
models.) 
Fuel 100/100 Low Lead minimum grade aviation gasoline

4H11 2 
Engine Limits for all Operations Maximum rpm:  3200 (305 hp) (All engines) 
 Maximum manifold pressure: 
 VO-540-A1A, -B1A Full Throttle 
 VO-540-B1D, -B1E, -B2D, -B2E 27.2 in. Hg 
 VO-540-C1A, -C1B, -C2A, -C2C 25.2 in. Hg 
 
Rotor Limits and Engine 
Operating  
Power Off (Rotor Tach.) Power On (Engine Tach.) 
Speeds Maximum 395 rpm Maximum 3200 rpm 
 Minimum 314 rpm Minimum (sea level to 5000 ft.) 2900 rpm (above 
5000 ft, increase minimum rpm by 20 rpm for each 
additional 1000 ft of altitude 
 (See NOTE 13 for UH-12E with Main Rotor Blades P/N 53200-03) 
   
Airspeed Limits Configuration V NE (IAS) 
 Skid Gear 96 mph (83 knots) 
 Float Gear 86 mph (74 knots) 
 The above airspeed applies from sea level to 5000 ft.  Decrease V NE 2.5 mph  
(2.2 knots) per 1000 ft of altitude above 5000 ft.  For limits with accessories 
installed, see the FAA-Approved Rotorcraft Flight Manual. 
  (See NOTE 6 for 4-place configurations) 
  
Altitude Limits See FAA-Approved Rotorcraft Flight Manual 
 
C.G. Range (Longitudinal) Configuration  
 Skid Gear Sta. (79.5) to (84.8) 
 Float Gear Sta. (81.0) to (84.8) 
 For range with accessories installed, see the FAA-Approved Rotorcraft Flight 
Manual.  
 See NOTE 6 for 4-place configuration 
See NOTE 13 for UH-12E with Main Rotor Blades P/N 53200-03 
Datum 107.25 in. fwd of tail boom-fuselage upper mounting face 
C.G. Range (Lateral) Left of helicopter centerline, 4.83 in. 
 Right of helicopter centerline, 1.85 in. 
 (See NOTE 13 for UH-12E with Main Rotor Blades P/N 53200-03)  
Leveling Means Top face of flanges under seat 
Maximum Weight 2750 lb (See NOTE 7 or NOTE 13 for increased maximum weight) 
Number of Seats 3 (sta. 53) (See NOTE 6 for 4-place configuration) 
Maximum Baggage See loading instructions in FAA-Approved Rotorcraft Flight Manual 
Fuel Capacity Total 46, 66, or 86 gal.  One main tank 46 gal. (sta. 82.9).  One or two auxiliary 
tanks installed per Hiller Service Bulletin 2008, 20 gal. each (sta. 85.8).   
See NOTE 1 for unusable fuel data. 
Oil Capacity 9.2 qt (sta. 94), or 12.3 qt (sta. 94) with auxiliary fuel tanks installed. 
Other Operating Limitations See FAA-Approved Rotorcraft Flight Manual

3 4H11 
 
Rotor Blade and Control Measured with respect to the mast.   
Note: When the mast is vertical, the helicopter is 1° movement nose up 
Main Blades:  
 Collective Pitch Low setting +1.0 °, total travel 10.5° (Measured at Retention Plate) (Low setting 
is determined as the lowest which will preclude overspeeding in autorotation) 
 Teetering Control rotor ±12°, Main Rotor ±9°  
Wobble Plate: 
 Lateral 7.7 ° to 8.3° 
 Longitudinal Fwd. 8.0 ° to 8.5°, Aft 9.0° to 9.2° 
Control Blades: 
 Neutral ±9° incidence (Rotor hub and wobble plate perpendicular to mast)  
Tail Rotor Blade Flapping +17 ° to -17° 
  
Tail Rotor Pitch Rigging T.R. Gearbox P/N Travel (degrees) 
 25200 +15 to -3 
 25200-3 or -5 +16 to -4 
 25300-5 +20 to -4 
 
Horizontal Stabilizer Setting Configuration(With helicopter level)  
 Skid Gear 0° 
 Float Gear -10° 
  
Float Pressure Differential 8.0 psi maximum 
 (See NOTE 6 for 4-place configuration) 
Serial Nos. Eligible Model UH-12E; 942, 954, 2001 through 2166, 2172 through 2229, 2233 
through 2241,2246 through 2248, 2253 through 2255, 2257 through 2282, 2286 
through 2292, 2294 through 2306, 2309 through 2499, 2518, 5001 and up and 
S/N HA3001 through HA3999 for aircraft built from spare and surplus parts by 
Hiller Aviation.  (See NOTE 12 for additional serial numbers.) 
 Army OH-23G; 1439 through 1760 and 1762 through 1876. 
 Army H-23F; 2167 through 2171, 2230 through 2232, 2242 through 2245, 2249 
through 2252, 2256, 2283 through 2285, 2293, 2307, and 2308.  
 In order for individual OH-23G or H- 23F helicopters procured under military 
cognizance and not having been issued a Form FAA970 "Conformity Certificate 
Military Aircraft", to be eligible for a Standard Airworthiness Certificate as a 
Model UH-12E, it must be determined in each case that the helicopter conforms 
to the Model UH-12E type design per CAR 1.67(d) or FAR 21.183(d).  
Certification basis CAR 6 dated December 20,  1956, including Amendments 6-1 and 6-2, 
Voluntary compliance with Amendment 6-3 has been established.  Type 
Certificate 4H11 issued January 6, 1959.  Date of Application for Type 
Certificate December 13, 1957.

4H11 4 
Production Basis None.  Before original airworthiness certification of each aircraft manufactured 
subsequent to April 23, 2003, an FAA representative must perform a detailed inspection 
for workmanship, materials, conformity with the approved technical data, and a check of 
the flight characteristics.  In the event of an application for a standard airworthiness 
certificate or, if an applicant intends to produce new aircraft under 14 CFR § 21.183 
(d), and the applicant is manufacturing, building, or assembling to another person’s type 
certificate, the applicant must provide written evidence of permission from the type 
certificate holder.  Conduct of such activity without written evidence of permission may 
be a violation of 49 U.S.C. § 44704(a)(3). 
Equipment The basic required equipment as pr escribed in the applicable airworthiness 
regulations (See Certification basis) must be installed in the helicopter for 
certification.  Hiller Report 59-30, "Model UH-12E Master Equipment List," 
contains a list of all required equipment that must be installed as well as optional 
equipment installations approved by FAA.  (See NOTE 6 for 4-place 
configuration.)  
II. Model UH-12E-L, Approved September 18, 1963  
 
Engine Lycoming VO-540-C2A.  See Engine TCDS E-304 for more details.   
Fuel 100/100 Low Lead minimum grade aviation gasoline 
Engine Limits for all Operations Maximum rpm:  3200 (305 hp) 
 Maximum manifold pressure:  26.0 in. Hg at sea level varying linearly to  
25.2 in. Hg at 3000 ft. 
 
Rotor Limits and Engine 
Operating  
Power Off (Rotor Tach.) Power On (Engine Tach.) 
Speeds Maximum 370 rpm Maximum 3200 rpm 
 Minimum 285 rpm Minimum (sea level to 10,000 ft.) 3000 rpm 
(above 10,000 ft, increase minimum rpm by 10 
rpm for each additional 1000 ft of altitude 
 
Airspeed Limits Configuration V NE (IAS) 
 Skid Gear 106 mph (92 knots) 
 The above airspeed applies from sea level to 6000 ft.  Decreases V NE 3 mph  
(2.6 knots) per 1000 ft of altitude above 6000 ft.  (For limits with accessories 
see FAA-Approved Rotorcraft Flight Manual) 
Altitude Limits See FAA-Approved Rotorcraft Flight Manual 
C.G. range (Longitudinal) Configuration 
 Skid Gear Sta. (79.5) to (84.8) 
 (For limits with accessories see FAA- Approved Rotorcraft Flight Manual.) 
Datum 107.25 in. fwd of tail boom-fuselage upper mounting face. 
C.G. Range (Lateral) Left of helicopter centerline, 1.82 in. 
 Right of helicopter centerline, 1.82 in. 
Leveling Means Top face of flanges under seat

5 4H11 
Maximum Weight 3100 lb 
 Gross weights of up to 3500 lb are permitted for Cargo Hook operations in 
accordance with Hiller FAA approved “Model UH-12E-L Helicopter Flight 
Manual 3500 lb Gross Weight Operation with Cargo Hook” dated April 4, 1966 
or later FAA approved revisions.  Operations above 3100 lb gross weights are in 
restricted category under FAR 133.  
Number of Seats 3 (sta. 53) 
Maximum Baggage See loading instructions in Flight Manual. 
Fuel Capacity Total 46, 66, or 86 gal.  One main tank 46 gal. (sta. 82.9) one or two auxiliary 
fuel tanks installed per Hiller Service Bulletin 2008, 20 gal. each (sta. 85.8) 
See NOTE 1 for unusable fuel data.  
Oil Capacity Engine oil - 8 qt (sta. 94) or 11 qt (sta. 94) with auxiliary fuel tanks installed  
Transmission oil - 4.5 qt (sta. 94)  
Other Operating Limitations See FAA-Approved Rotorcraft Flight Manual 
Rotor Blade and Control Measured with respect to the mast.   
Note: When the mast is vertical, the helicopter is 1° movement nose up 
Main Rotor Blade Collective Travel +8 1/2 ° ±0.1° to +20 1/2° ±1/4° 
Wobble Plate: 
 Lateral 7 ° 45' ±1/4° left and 4° 42' ±1/4° right 
 Longitudinal 9 1/4 ° ±1/4° forward and aft 
Tail Rotor Blade Flapping +17 ° to -17° 
 
Tail Rotor Pitch Rigging T.R. Gearbox P/N Travel (degrees) 
 25300-3  +20 to -4 
 25300-5 +16 to -4 
 
Horizontal Stabilizer Setting Configuration (With helicopter level) 
 Skid Gear -4° ±1° 
 
Serial Nos. Eligible Model UH-12E; 942, 954, 2001 through 2166, 2172 through 2229, 2233 
through 2241, 2246 through 2248, 2253 through 2255, 2257 through 2282, 
2286 through 2292, 2294 through 2306, 2309 through 2499 limitations.  
Certification Basis CAR 6 dated December 20, 1956,  including Amendments 6-1, 6-2, and 6-3.  
 Compliance with Amendments 6-4 required for rotor and control systems only.  
Type Certificate 4H11 reissued September 18, 1963.  Date of Application of 
Type Certificate February 28, 1961.  
Production Basis None.  Before original airworthiness certification of each aircraft manufactured 
subsequent to April 23, 2003, an FAA representative must perform a detailed inspection 
for workmanship, materials, conformity with the approved technical data, and a check of 
the flight characteristics.  In the event of an application for a standard airworthiness 
certificate or, if an applicant intends to produce new aircraft under 14 CFR § 21.183 
(d), and the applicant is manufacturing, building, or assembling to another person’s type

4H11 6 
certificate, the applicant must provide written evidence of permission from the type 
certificate holder.  Conduct of such activity without written evidence of permission may 
be a violation of 49 U.S.C. § 44704(a)(3). 
Equipment The basic required equipment as pr escribed in the applicable airworthiness 
regulations (See Certification basis) must be installed in the helicopter for 
certification.  Hiller Report 63-76, "Model UH-12E-L Master Equipment List" 
contains a list of all required equipment that must be installed as well as optional 
equipment installations approved by the FAA.  
Data Pertinent to all Models 
NOTE 1. Current weight and balance report, including list of equipment included in certificated empty 
weight, and loading instructions must be in each helicopter at the time of original certification and 
at all times thereafter (except in the case of operators having an approved weight control system).  
Ballast, when necessary, must be carried in accordance with Loading Instructions in the  
FAA-Approved Rotorcraft Flight Manual. 
 Fuel and Oil capacities as indicated are tota l tank capacities over and above "Trapped Fuel and 
Oil."  The main fuel tank capacity includes "Unusable" fuel of 0.3 gallon, which cannot be used 
safely in all flight attitudes, and which must be included in the empty weight.  Unusable fuel in the 
optional auxiliary fuel tanks is negligible.  
NOTE 2. The following placard must be  installed on the Pilot's Checklist: 
 "This Helicopter must be operated in compliance with the operating limitations specified in 
the FAA-Approved Rotorcraft Flight Manual."  
 For additional placards, see the FAA- Approved Rotorcraft Flight Manual. 
NOTE 3. The retirement times of critical parts are listed in the following tables.  These values of retirement 
or service life cannot be increased without FAA Engineering approval.  
 Life limited components interchanged between UH-12 series models or configurations must be 
restricted to the lowest service life indicated for the models or configurations that the individual 
part has been used on.  If previous service history does not identify the model or configuration, 
the lowest service life of all possible models or configurations must be used.  Life limited 
components removed at retirement are to be destroyed or conspicuously marked to prevent 
inadvertent return to service.  
 
MODEL UH-12E 
FINITE LIFE COMPONENT 
NOMENCLATURE PART NO.  REPLACEMENT  
PERIOD HOURS 
Rotors and Drives 
Blade Assy., main rotor (Parsons) 2253-1101-03 2500  
Blade Assy., main rotor (Parsons) 2253-1101-04 2500 NOTE A 
Blade Assy., main rotor 53200-03 6670 NOTE H 
Shaft Assy., output speed decreaser 25202, -5 5790 
Plate set, main rotor tension-torsion 51430-1, -3, -5 3350 
(component of 51430-1 and -3 assembly) 
Hub Assy., main rotor 51437-9 1540 
(Service Bulletin No. 2014 not complied with) 
Hub Assy., main rotor 51437-9 2500 NOTE B 
(Service Bulletin No. 2014 complied with) 
Hub Assy., main rotor  51437-11, -14, -901, -911 2500

7 4H11 
MODEL UH-12E 
FINITE LIFE COMPONENT (continued) 
NOMENCLATURE PART NO.  REPLACEMENT  
PERIOD HOURS 
Pin, main rotor outboard tension torsion 51452, -1 643 
Fork, main rotor blade root 52110-3 2500 
Drag strut, main rotor blade 52120, -5 2500 
Drag strut, main rotor blade 52120-7 2500 NOTE H 
Bar Assy., tail rotor tension-torsion 55054, -1 12500 
Blade Assy., tail rotor (3-place model) 55073 (All Dash Numbers) 5400 
Blade Assy., tail rotor (4-place model) 55073 (All Dash Numbers) 3240 
Yoke, Tail Rotor 55046 (All Dash Numbers) 2500 NOTE J 
 
Power Plant   
Snubber Assy., engine, longitudinal 63192-7, -11 4650 
Snubber Assy., engine, lateral 63192-5, -9 4650 
Bracket, engine snubber 63197 6160 
Bracket, engine snubber 63197-5 9850 
Attaching bolts, engine snubber AN3 600 
(used to attach P/N 63197 bracket to engine deck and snubber) 
Gimbal outer engine mounting 63309, -3, -9, -11 6300 
Gimbal outer engine mounting 63309, -3, -9, -11 5480 NOTE H 
One way clutch (Borg-Warner) X132591 375 NOTE C 
One way clutch (Borg-Warner) X132815 375 NOTE C 
 
Collective and Cyclic Controls  
Flyweight collective pitch ballast 31197-3 2500 
Bellcrank, collective control 31318 15000 
Tube, collective control 31319, -3 23500 
Shaft, dual collective control 31321 10400 
Block Assy., collective stick 31344, -3, -5, -7, -9 6400 NOTE I  
Push rod, collective control     31365 8150 NOTE H 
Arm, collective pitch blade incidence 31389 14500 NOTE H 
Incidence Arm 31113-13 13400 NOTE H 
(Old style-Includes Fafnir or Shafer Rod Ends) 
Incidence Arm 31333 WA7-75083-S1. 13400 Note H 
(Heim Rod Ends on Condition) 
Arm Assy., collective and throttle controls 31403 21500 
(4-place model) 
Scissor, cyclic control, lower Spar and Blade 34141, -5 275 Note D 
Assy., Control Rotor (all faired Assys.) 
Fairing Blade Assy., Control Rotor 36003, 36129, 36129-25 2500 NOTE F 
Trunion, Control Rotor Hub 36116-4 5150 NOTE E 
Cuff Assy., Control Rotor (used with faired assy.) 36124 5150 NOTE G 
Cuff Assy., Control Rotor (used with unfaired assy.) 36124 6860 NOTE G 
Cuff Assy., Control Rotor (used with unfaired assy.) 36124 5550 NOTE H, G 
 
NOTE A - The replacement period for blade assemb lies S/N 4261 and subsequent is 6670 hours.  The 
replacement period for blade assemblies S/N 3396 through S/N 4260 is extended to 6670 hours if 
these blades are returned to the manufacturer for installation of rolled-thread anti-node bar assembly 
P/N 2253-1124 before 2500 hours time in service. 
NOTE B - The 2500 hour service life total includes service time prior to compliance with Hiller Aviation Service 
Bulletin No. 2014.

4H11 8 
NOTE C - Unlimited life after incorporation of  Hiller Aviation Service Bulletin No. 2027A. 
NOTE D - Any unfaired control rotor blade assembly with an "R" after the part number (reworked per Hiller 
Aviation Service Bulletin 36-1, Revision 2) must be replaced upon attaining 2500 additional operating 
hours after rework.  
NOTE E - 5150 hour limitation applicable to trunions used with control rotor fairing and blade assy. P/N 36003, 
36129, or 36129-25.  
NOTE F - If any of these part numbers are reworked in  accordance with Hiller Aviation Service Bulletin 36-1, 
Revision 3, the part must still be replaced upon attaining a total time of 2500 hours regardless of the 
replacement period shown in Hiller Aviation Service Bulletin 36-1, Revision 3.  
NOTE G - All control rotor cuff assemblies installed with control rotor blade assemblies (both faired and 
unfaired) with an "R" after the part number (reworked per Hiller Aviation Service Bulletin 36-1, 
Revision 3) must be replaced upon attaining the original retirement life, but not to exceed 2500 
additional hours after rework.  
NOTE H - These new or revised replacement periods ar e for the "Hiller Model UH-12E with new main rotor 
blades 53200-03."  (See NOTE 13 for installation of main rotor blade 53200-03.)  
NOTE I - Part number 31344 Collective Stick block asse mbly is a matched set consisting of 31344-3 and 31344-
5.  Part number 31344-7 Collective Stick block assembly is a matched set consisting of 31344-5 and 
31344-9.  Serial number for both lower and upper blocks must be the same.  
NOTE J - Life limited applies only when increased pitch style tail rotor gearbox part number 25300-5 tail rotor 
speed decrease is used. 
 
MODEL UH-12E-L 
FINITE LIFE COMPONENT 
NOMENCLATURE PART NO.  REPLACEMENT  
PERIOD HOURS 
Rotors and Drives   
Main Rotor Blade Assy 53100 9250 
Cuff Assy., main rotor blade 51456 7300 
Rod, drag strut, main rotor blade WS7-125083-14L-20B-083-856-HT 2080 
Terminal, drag strut, main rotor blade 52122-3, -5 2100 
Bolt, drag strut, main rotor blade AN177 710 
Hub Assy., main rotor 51455 6300  
Rod Assy., drag strut 52125 57250 
Terminal, drag strut, main rotor (cuff end) 52122-7 53600 
Terminal, drag strut, main rotor (blade end) 52124-3 63750 
Bolt, drag strut, main rotor (blade end) NAS 1307-24 47600 
Bar Assy., tension-torsion, tail rotor 55054, -1 12500 
Blade Assy., tail rotor 55073 (All Dash Numbers) 5400 
Bolt, drag strut, main rotor (cuff end) NAS 1307-21 46850 
Yoke, tail rotor 55046 (All Dash Numbers) 2500 
 
Power Plant  
Shaft Assy., output 25202, -5 5790 
Engine outer gimbal ring 63309, -3, -9, -11 6360

9 4H11 
MODEL UH-12E-L 
FINITE LIFE COMPONENT (continued) 
NOMENCLATURE PART NO.  REPLACEMENT  
PERIOD HOURS  
Collective and Cyclic Controls   
Bracket Assy., transmission, cyclic controls 33333-5 2120 
Bracket Assy., transmission, cyclic controls 33333-1 150 
Bracket Assy., transmission, cyclic controls 33344-1 150 
Inner Ring Assy., (wobble plate) 34017 77980 
Sleeve Assy., wobble plate cyclic controls 34038 42910 
Gimbal ring, wobble plate 34008 73500 
Yoke Assy., mixing cyclic & collective controls 30034 63850 
Push-Pull Rod Assy., collective 31468 150 
Arm, Mixing Assy., cyclic & collective controls 30036 10940 
Rod end  MDV46-16TMC 150 
Rod end (Conair) 8127 69060 
 
NOTE 4. These helicopters must be serviced and maintained in conformance with  current Hiller Aircraft 
Corporation Instructions for Continued Airworthiness (Inspection Guide), repair handbook, and 
service and overhaul manuals for pertinent model.  
NOTE 5. Deleted May 10, 1960.  
NOTE 6. Model UH-12E 4-Place Conf iguration and 4-Place Modification Kit, Hiller Dwg. No. 10044, 
installed per Hiller Service Bulletin No. 2010.  The following additional limitations apply:  (For 
limits with accessories installed see FAA-Approved Rotorcraft Flight Manual.)  
 
(a) Airspeed limits  Configuration   V NE (IAS) 
  Skid Gear 95 mph (82 knots) 
  Float Gear 86 mph (74 knots) 
   
   
Decrease VNE 2.5 mph (2.2 knots) 
per 1000 ft above 5000 ft 
    
(b) C.G. range Skid Gear Sta. (79.5) to (84.8) 
 (Longitudinal) Float Gear Sta. (81.0) to (84.8) 
    
(c) No. seats 1 (sta. 25), 3 (sta. 53)  
    
(d) Horizontal stabilizer   
 P/N 37027 +3° (Measured with helicopter level) 
    
(e) Equipment   
 The basic required equipment as prescribed in  the applicable airworthiness regulations (See 
Certification Basis) must be installed in the helicopter for certification.  Hiller Report 60-
60 "Model UH-12E (4-place) Master Equipment List" contains a list of all required 
equipment that must be installed as well as optional equipment installations approved by 
the FAA. 
 
NOTE 7. UH-12E, 3- and 4-place configurations are eligible at 2800 pounds maximum weight when items 
specified by Hiller Service Bulletin No. 2031 are installed.  See FAA-Approved Rotorcraft Flight 
Manual for operation limitations.

4H11 10 
NOTE 8. Model UH-12E Helicopters (3 - and 4-place configurations) may be converted to Model UH-12L 
or UH-12L4 by accomplishment of Hiller Service Bulletins No. 2040 (Dwg. 10060) and No. 2045 
(Dwg. 10059) respectively.  
NOTE 9. Model UH-12E Helicopters (3 -place configuration only) may be converted to Model UH-12L by 
accomplishment of Hiller Service Bulletin No. 2039A (Dwg. 10060).  
NOTE 10. The Type Certificate holder has demonstrated compliance with FAR 133.43 for the UH-12E 
Helicopters for Class B (Jettisonable Sling Load) Rotorcraft - Load Combination at a maximum 
overall weight of 3100 pounds and a maximum sling load of 1000 pounds, when modified to 
incorporate cargo hook installation per Hiller Dwg. 91012.  The helicopter weight without sling 
load is not to exceed certificated weight of 2750 pounds (2800 pounds if Hiller Service Bulletin 
No. 2031 has been complied with per NOTE 7. of this document).  For limitations see pertinent 
FAA-Approved Rotorcraft Flight Manual Revision and Rotorcraft-  Load Combination Flight 
Manual to be submitted by applicant for external load operator's certificate in accordance with 
FAR Part 133.  
NOTE 11. The Type Certificate holder has demonstrated compliance with FAR 133.43 for the UH-12E-L 
Helicopters for Class B (Jettison Sling Load) Rotorcraft - Load Combination at a maximum 
overall weight of 3500 pounds and a maximum sling load of 1000 pounds, when modified to 
incorporate cargo hook installation per Hiller Dwg. 91012.  The helicopter weight without sling 
load is not to exceed certificated weight of 3100 pounds.  For limitations see pertinent FAA-
Approved Rotorcraft Flight Manual revision and Rotorcraft - Load Combination Flight Manual to 
be submitted by applicant for external load operator's certificate in accordance with Far 133 
NOTE 12. Certain Model UH-12D helicopters may be c onverted to Model UH-12E in accordance with Hiller 
Drawing No. 10054, Revision B, or subsequent FAA-Approved revisions thereto.  Refer to this 
drawing for serial numbers eligible for such conversion.  
NOTE 13. The main Rotor Blades P/N 53200-03 ma y be installed on Hiller Model UH-12E by 
accomplishment of Hiller Service Bulletins No. 10-2 and No. 51-3.  FAA-Approved Rotorcraft 
Flight Manual "Hiller Model UH-12E Helicopter with 53200-03 Main Rotor Blades" is required.  
The following limitations apply.  (For limits with accessories installed, see FAA-Approved 
Rotorcraft Flight Manual "Hiller UH-12E Helicopter with 53200-03 Main Rotor Blades”.)  
 
(a) Rotor limits and 
engine operating 
speeds 
Power Off (Rotor Tach) Power On (Engine Tach) 
  Maximum 395 rpm Maximum 3200 rpm 
  Maximum 314 rpm Minimum (S.L. to 10,000 ft.) 3000 
rpm (Above 10,000 ft increase 
minimum rpm by 20 rpm for each 
additional 1000 ft of altitude) 
    
(b) Airspeed limits Configurations  V NE (IAS) 
  Skid Gear 2801 to 3100 
pounds 
75 mph (65 knots) decrease VNE 2.5 
mph (2.2 knots) per 1000 ft above 
5000 ft 
    
 
(c) Altitude limits Configuration   
  Skid Gear - 2800 lb S.L. to 15,000 feet 
  Skid Gear-2801 to 3100 
lb 
S.L. to 7400 feet

11 4H11 
 
(d) C.G. Range Configuration   
  Skid Gear  
  2800 pounds Left of helicopter center line, 3.75 in. 
   Right of helicopter center line, 1.85 in. 
  3100 pounds Left of helicopter center line, 3.40 in. 
   Right of helicopter center line, 1.85 in. 
    
  The variation in left lateral C.G. is a straight line interpolation 
between 2801 pounds and 3100 pounds. 
    
(e) C.G. Range Configuration   
 (Longitudinal) Skid Gear Forward: Sta. (79.5) to 7000 feet; 
Sta. (80.1) above 7000 feet.   
Aft:  Sta. (84.8) 
    
(f) Maximum Weight 3100 pounds  
 
NOTE 14. Any changes to the type design of this helicopter by means of an amended type certificate (TC), 
supplemental type certificate (STC), or amended STC, requiring instructions for continued 
airworthiness (ICA's) must be submitted through the project aircraft certification office (ACO) for 
review and acceptance by the Fort Worth -Aircraft Evaluation Group (FTW-AEG) Flight 
Standards District Office (FSDO) prior to the aircraft delivery, or upon issuance of the first 
standard airworthiness certificate for the affected aircraft, whichever occurs later as prescribed by 
Title 14 CFR 21.50.  Type design changes (major repairs or alterations) by means of a FAA Form 
337 (field approval) that require ICA's must have those ICA's reviewed by the field approving 
FSDO. 
...END...
```

## ADs (46, in force first)

- [AD 2025-15-02](https://openairdocs.org/ad/2025-15-02): Main Rotor Mast/Swashplate · Siam Hiller Holdings UH-12E and UH-12E-L. Effective Sep 24, 2025
- [AD 2023-11-07](https://openairdocs.org/ad/2023-11-07): Ground Proximity System · Airbus Helicopters 47, 206, 210 and 237 more. Effective Jun 22, 2023
- [AD 2000-24-21](https://openairdocs.org/ad/2000-24-21): Control System Linkage · Hiller UH-12, UH-12A, UH-12B and 6 more. Effective Jan 10, 2001
- [AD 97-20-15](https://openairdocs.org/ad/97-20-15): Outboard Tension-Torsion Bar Pin · Hiller UH-12A, UH-12B, UH-12C and 2 more. Effective Nov 12, 1997
- [AD 97-10-16](https://openairdocs.org/ad/97-10-16): Blade Spar Tube and Cuff Inspection · Allison 250-C20/250-C20B engine (Siam Hiller Holdings STC SH177WE or SH178WE). Effective Jun 27, 1997
- [AD 90-15-01](https://openairdocs.org/ad/90-15-01): Tail Rotor Blade Assemblies · Hiller UH-12L, UH-12L4, UH-12E and 1 more. Effective Mar 7, 1991
- [AD 86-22-04](https://openairdocs.org/ad/86-22-04): Main Rotor Blades · Hiller UH-12D, UH-12E and UH-12E-L with STC SH177WE or SH178WE. Effective Nov 3, 1986
- [AD 86-17-02](https://openairdocs.org/ad/86-17-02): Main Rotor Blade Fork · Hiller UH-12D, UH-12E and UH-12E-L with STC SH177WE or SH178WE. Effective Aug 22, 1986
- [AD 84-19-08](https://openairdocs.org/ad/84-19-08): Engine Mount · Hiller UH-12D, UH-12E and UH-12E-L with STC SH177WE or SH178WE. Effective Sep 20, 1984
- [AD 83-25-02](https://openairdocs.org/ad/83-25-02): Main Rotor Blade Doublers · Allison 250-C20/250-C20B engine (Siam Hiller Holdings STC SH177WE). Effective Dec 29, 1983
- [AD 82-16-07](https://openairdocs.org/ad/82-16-07): Torsional Coupling Assemblies · Hiller UH-12L, UH-12L4, UH-12E and 1 more. Effective Oct 15, 1982
- [AD 82-13-04 R1](https://openairdocs.org/ad/82-13-04-R1): Torsional Couplings · Hiller UH-12L, UH-12L4, UH-12E and 1 more. Effective Sep 13, 1982
- [AD 82-15-02](https://openairdocs.org/ad/82-15-02): Main And Tail Rotors · Hiller UH-12D, UH-12L, UH-12L4 and 2 more. Effective Jul 16, 1982
- [AD 81-18-02](https://openairdocs.org/ad/81-18-02): Tail Rotor Skin Cracks · Hiller UH-12, UH-12A, UH-12B and 6 more. Effective Sep 10, 1981
- [AD 81-17-03](https://openairdocs.org/ad/81-17-03): Main Transmission · Hiller UH-12, UH-12A, UH-12B and 6 more. Effective Aug 24, 1981
- [AD 81-09-08](https://openairdocs.org/ad/81-09-08): Main Rotor Blade · Hiller UH-12D and UH-12E with STC SH177WE or SH178WE. Effective Jun 25, 1981
- [AD 81-04-01](https://openairdocs.org/ad/81-04-01): Rudder Cable Assembly · Hiller UH-12D, UH-12L and UH-12E. Effective Feb 9, 1981
- [AD 80-23-02](https://openairdocs.org/ad/80-23-02): Turbine Power Conversions · Allison 250-C20/250-C20B engine (Siam Hiller Holdings STC SH177WE or 2 others). Effective Nov 20, 1980
- [AD 80-19-02](https://openairdocs.org/ad/80-19-02): Turbine Power - Soloy Conversions · Hiller UH-12D and UH-12E with STC SH177WE or SH178WE. Effective Oct 11, 1980
- [AD 80-07-04](https://openairdocs.org/ad/80-07-04): Main Rotor Blade Anti-Node Bars · Hiller UH-12, UH-12D and UH-12E. Effective Mar 31, 1980
- [AD 79-03-07](https://openairdocs.org/ad/79-03-07): Main Rotor Tachometer Generator · Hiller UH-12D and UH-12E with STC SH177WE or SH178WE. Effective Feb 21, 1979
- [AD 78-23-07](https://openairdocs.org/ad/78-23-07): Finite Life Components Listed in AD · Hiller UH-12D and UH-12E. Effective Dec 14, 1978
- [AD 78-22-08](https://openairdocs.org/ad/78-22-08): Flight/Engine Control · Hiller UH-12D and UH-12E with STC SH177WE or SH178WE. Effective Nov 30, 1978
- [AD 78-22-02](https://openairdocs.org/ad/78-22-02): Rotor Blade Retention System · Hiller UH-12D and UH-12E. Effective Oct 27, 1978
- [AD 78-18-03](https://openairdocs.org/ad/78-18-03): Drive Shaft · Hiller UH-12D and UH-12E with STC SH177WE or SH178WE. Effective Oct 6, 1978
- [AD 77-24-03](https://openairdocs.org/ad/77-24-03): Fuel Control Valve · Hiller UH-12C, UH-12D, UH-12L and 3 more. Effective Jan 6, 1978
- [AD 75-10-01](https://openairdocs.org/ad/75-10-01): Rotor Drive System · Hiller UH-12D, UH-12L, UH-12L4 and 2 more. Effective May 8, 1975
- [AD 61-05-04](https://openairdocs.org/ad/61-05-04): Main Transmission · Hiller UH-12D and UH-12E. Effective Jun 4, 1974
- [AD 74-04-03](https://openairdocs.org/ad/74-04-03): Main Rotor Drag Struts · Hiller UH-12D and UH-12E. Effective Feb 18, 1974
- [AD 73-20-03](https://openairdocs.org/ad/73-20-03): Main Rotor Hub · Hiller UH-12, UH-12A, UH-12B and 4 more. Effective Oct 30, 1973
- [AD 72-13-08](https://openairdocs.org/ad/72-13-08): Main Rotor Blades · Hiller UH-12L, UH-12L4 and UH-12E-L. Effective Oct 19, 1972
- [AD 71-25-08](https://openairdocs.org/ad/71-25-08): Inspect Main Rotor Blades · Hiller UH-12, UH-12A, UH-12B and 6 more. Effective Dec 14, 1971
- [AD 69-13-07](https://openairdocs.org/ad/69-13-07): Collective Yoke Support Brackets · Hiller UH-12D, UH-12L, UH-12L4 and 2 more. Effective Apr 30, 1970
- [AD 69-08-08](https://openairdocs.org/ad/69-08-08): Tail Rotor Yoke · Hiller UH-12D, UH-12L, UH-12L4 and 2 more. Effective Apr 23, 1969
- [AD 67-08-03](https://openairdocs.org/ad/67-08-03): Cyclic Control Bracket · Hiller UH-12D and UH-12E. Effective Mar 9, 1967
- [AD 66-22-04](https://openairdocs.org/ad/66-22-04): Mercury Clutches · Hiller UH-12D, UH-12L, UH-12L4 and 2 more. Effective Sep 2, 1966
- [AD 64-11-02](https://openairdocs.org/ad/64-11-02): Tail Rotor Pinion Gears · Siam Hiller Holdings UH-12E and UH-12E-L. Effective May 16, 1964
- [AD 2015-20-51](https://openairdocs.org/ad/2015-20-51): Hiller UH-12, UH-12A, UH-12B and 6 more
- [AD 59-05-05](https://openairdocs.org/ad/59-05-05): Cyclic Control Scissor Casting · Hiller UH-12, UH-12A, UH-12B and 3 more
- [AD 59-25-03](https://openairdocs.org/ad/59-25-03): Wobble Plate Screws · Hiller UH-12, UH-12A, UH-12B and 3 more
- [AD 62-06-03](https://openairdocs.org/ad/62-06-03): Transmission & Lubrication System Modification · Hiller UH-12D and UH-12E
- [AD 63-21-03](https://openairdocs.org/ad/63-21-03): Main Rotor Blades · Hiller UH-12D and UH-12E
- [AD 76-20-06](https://openairdocs.org/ad/76-20-06): Cable Freezing Control · Hiller UH-12D and UH-12E with STC SH177WE or SH178WE
- [AD 2021-23-13](https://openairdocs.org/ad/2021-23-13) (historical): Ground Proximity System · Airbus Helicopters K-225, K-190A, K-240 and 237 more. Effective Dec 9, 2021
- [AD 77-07-05](https://openairdocs.org/ad/77-07-05) (historical): Control Rotor Blade Spar Tube and Cuff · Hiller UH-12, UH-12A, UH-12B and 3 more. Effective Jun 20, 1977
- [AD 77-07-05 R1](https://openairdocs.org/ad/77-07-05-R1) (historical): Control Rotor Blade Spar Tube and Cuff · Hiller UH-12, UH-12A, UH-12B and 3 more. Effective Jun 20, 1977

## Registered aircraft by registry model (OpenAirDocs)

- [Hiller UH-12E](https://openairdocs.org/model/hiller-uh-12e): 103 aircraft (registry codes 4360122, 4360137)
- [Hiller OH-23G](https://openairdocs.org/model/hiller-oh-23g): 4 aircraft (registry code 4360121)
- [Hiller UH-12E-L](https://openairdocs.org/model/hiller-uh-12e-l): 1 aircraft (registry code 4360124)
- [Hiller-Rogerson Helicopter UH12E](https://openairdocs.org/model/hiller-rogerson-helicopter-uh12e): 1 aircraft (registry code 4361101)
- [Hiller-Fisher UH-12E](https://openairdocs.org/model/hiller-fisher-uh-12e): 0 aircraft (registry code 4360601)
- [Hiller-Miller UH-12E](https://openairdocs.org/model/hiller-miller-uh-12e): 0 aircraft (registry code 4361201)
- [Rogerson Hiller UH-12E](https://openairdocs.org/model/rogerson-hiller-uh-12e): 0 aircraft (registry code 4366001)
- [Rogerson Hiller UH-12E-L](https://openairdocs.org/model/rogerson-hiller-uh-12e-l): 0 aircraft (registry code 4366003)

## STCs approved under this data sheet (75, first 50)

- [STC SR04637CH](https://openairdocs.org/stc/SR04637CH): Replacement of existing main ship battery with Lithium Ion Battery and installation of Annunciator Control
Panel. Airwolf Aerospace LLC
- [STC SH3319NM](https://openairdocs.org/stc/SH3319NM): Installation of Precise Flight Pulselite Control Unit in the
Landing /Taxi Recognition Visual Control Light system,. Precise Flight Inc
- [STC SH1152NW](https://openairdocs.org/stc/SH1152NW): Installation of the Automatic Flagman Model 135 Control Stick Grip. Air Products & Parts LLC
- [STC SR02704SE](https://openairdocs.org/stc/SR02704SE): Installation and maintenance of the Sunspot 36 and 46 series lights. AeroLED's Holdings LLC
- [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SR01845SE](https://openairdocs.org/stc/SR01845SE): Installation of a barrier air filtration system. Cascade Flying Service LLC
- [STC SR00420NY](https://openairdocs.org/stc/SR00420NY): Installation of Airwolf remote mounted engine oil filter Model AFC-600. Airwolf Filter, Corp
- [STC SR01802WI](https://openairdocs.org/stc/SR01802WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel per ASTM D7547.. Swift Fuels LLC
- [STC SR02394AK](https://openairdocs.org/stc/SR02394AK): Replacement of existing landing and/or hover light bulbs with Light Emitting Diode (LED) lighting system. Seaplanes North LLC
- [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc.
- [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc.
- [STC SH381NW](https://openairdocs.org/stc/SH381NW): Installation and maintenance of engine auto reignition system. (UH-12E modified per STC SH178WE). Siam Hiller Holdings Inc
- [STC SH476NW](https://openairdocs.org/stc/SH476NW): Installation of an agricultural spray system.. Siam Hiller Holdings Inc
- [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC
- [STC SA02033AT](https://openairdocs.org/stc/SA02033AT): Modification to install an air-oil separator to prevent oil from being aspirated from the engine breather line.. M-20 Oil Separators LLC
- [STC SH178WE](https://openairdocs.org/stc/SH178WE): Installation of Allison 250-C20/250-C20B engine and related changes. (UH-12E-L (4 place)). Siam Hiller Holdings Inc
- [STC SH248NW](https://openairdocs.org/stc/SH248NW): Installation and maintenance of exhaust ejector engine oil cooler system. (UH-12E modified per STC SH178WE). Siam Hiller Holdings Inc
- [STC SH288NW](https://openairdocs.org/stc/SH288NW): Installation of Hiller landing gear float kit No. 44012. (UH-12E modified per STC SH178WE). Siam Hiller Holdings Inc
- [STC SH296NW](https://openairdocs.org/stc/SH296NW): Installation of Hiller auxiliary fuel tanks kit No. 72041. (UH-12E modified per STC SH178WE). Siam Hiller Holdings Inc
- [STC SH298NW](https://openairdocs.org/stc/SH298NW): Installation and maintenance of a cabin heater system. (UH-12E modified per STC SH178WE). Siam Hiller Holdings Inc
- [STC SH300NW](https://openairdocs.org/stc/SH300NW): Installation of Soloy cargo racks.. Siam Hiller Holdings Inc
- [STC SH322NW](https://openairdocs.org/stc/SH322NW): Installation of a Bendix fuel control/power governor system on the Allison 250-C20 turbine powered Hiller UH-12E rotorcraft. (UH-12E modified per STC SH178WE). Siam Hiller Holdings Inc
- [STC SH339NW](https://openairdocs.org/stc/SH339NW): Installation of transmission oil cooling system on the Allison250-C20 turbine powered Hiller UH-12E rotorcraft. (UH-12E modified per STC SH178WE). Siam Hiller Holdings Inc
- [STC SH506NW](https://openairdocs.org/stc/SH506NW): Installation of cargo release pedal.. Siam Hiller Holdings Inc
- [STC SH560NW](https://openairdocs.org/stc/SH560NW): Installation and maintenance of engine inlet air cleaner system.. Siam Hiller Holdings Inc
- [STC SH634NW](https://openairdocs.org/stc/SH634NW): Installation of Tundra Pads.. Siam Hiller Holdings Inc
- [STC SA01258SE](https://openairdocs.org/stc/SA01258SE): Installation of the Automatic Flagman Dispenser Models in accordance with Automatic Flagman Master Drawing Lists specified in attached AML, or later FAA approved revision.This STC supercedes several existing STC s as listed in the notes on the attached AML.. R-S Sales Inc.
- [STC SA02520AT](https://openairdocs.org/stc/SA02520AT): Installation of M-20 Oil Separator, model 600-WP.. M-20 Oil Separators LLC
- [STC SH849NW](https://openairdocs.org/stc/SH849NW): Installation of North American Industries, Inc., Model No. 5 Automatic Flagman. R-S Sales Inc.
- [STC SH201WE](https://openairdocs.org/stc/SH201WE): Installation of stirrup assemblies to directional control pedals for operation by handicapped pilot. (US ARMY OH-13E 205A). Dallwig Barry C
- [STC SA2687NM](https://openairdocs.org/stc/SA2687NM): Installation of Truboplus/ Electronics Int'l gauges and switches.. Aero Manufacturing Inc.
- [STC SH12CE](https://openairdocs.org/stc/SH12CE): Replace existing engine induction air filter with AC Spark Plug Filter.. Brackett Aero Filters Inc.
- [STC SH767NW](https://openairdocs.org/stc/SH767NW): Installation of Chadwick Model C-512S spray system.. Tower Aerospace, Inc
- [STC SR00135LA](https://openairdocs.org/stc/SR00135LA): Installation of Yehnert Tail Rotor Blades YH-278 as replacements for Hiller Tail Rotor Blades 55073.. Yehnert Helicopters, Inc
- [STC SA1626NM PAGE 1](https://openairdocs.org/stc/SA1626NM%20PAGE%201): Installation of Electronics Int'l Digital EGT/CHT Instruments and accessories. (201 Series). Electronics International
- [STC SH5729NM](https://openairdocs.org/stc/SH5729NM): Full flow oil filter system. Grogan Don
- [STC SA2350NM PAGE 1](https://openairdocs.org/stc/SA2350NM%20PAGE%201): Installation of Electronics International Inc digital carburetor/outside air temperature gauges. Electronics International
- [STC SH300GL](https://openairdocs.org/stc/SH300GL): Installation of Facet Enterprises engine lubrication system scavenge filter.. Facet Filter Products
- [STC SH2763SO](https://openairdocs.org/stc/SH2763SO): Installation of control rotor safety cable.. JAARS Inc.
- [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International
- [STC SH2611SO](https://openairdocs.org/stc/SH2611SO): Installation of cargo rack.. JAARS Inc.
- [STC SA3862NM PAGE 1](https://openairdocs.org/stc/SA3862NM%20PAGE%201): Installation of Electronics International Primary TIT/EGT/CHT instruments, remote switches and associated accessories.. Electronics International
- [STC SH4173NM](https://openairdocs.org/stc/SH4173NM): Installation of Simplex Model 7600 modular electrical system. (US ARMY OH-13E M74A). Simplex Manufacturing Company
- [STC SH3362NM](https://openairdocs.org/stc/SH3362NM): Installation of a Tail Rotor Blade Protective Coating. Columbia Helicopters Inc
- [STC SA2190NM PAGE 1](https://openairdocs.org/stc/SA2190NM%20PAGE%201): Installation of electronics International Digital Volt/Amp Gauges and Accessories.. Electronics International
- [STC SH4997SW](https://openairdocs.org/stc/SH4997SW): Installation of Lycoming TIVO-540-A2A engine. Craig Helicopters
- [STC SH302NM](https://openairdocs.org/stc/SH302NM): Installation of two Albany Int. dispersion pads, Drawing No. 21940 or 21961.. Albany International
- [STC SH1014NW](https://openairdocs.org/stc/SH1014NW): Simplex Model 4600 spray system. Simplex Manufacturing Co
- [STC SH1147NW](https://openairdocs.org/stc/SH1147NW): Installation of a Chadwick Spray System. Helicopter Maintenance Corp.
- [STC SH887NW](https://openairdocs.org/stc/SH887NW): Simplex Model 4650 spray system - agricultural.. Simplex Manufacturing Co

All 75: https://openairdocs.org/tcds/4H11/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.