# TCDS H13WE: Midwest Aerospace TC LLC

- Type: Type certificate data sheet
- Status: Current
- Holder: Midwest Aerospace TC LLC
- Revision: 14
- Revised: February 8, 2023
- Product: Aircraft, Rotorcraft
- Certification basis: Part 21
- Registered aircraft: 12, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/50/f9/50f94b79e7cf6b70aea69c2eff5b5aa104f7c09a350cbfef6ec43fe2d965a5c4
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID175579896320230629180759.0001
- Page: https://openairdocs.org/tcds/H13WE

## Models (2)

As the data sheet lists them.

- UH-1H
- UH-1B

## What the data sheet says

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

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
H13WE 
Revision 14 
Midwest Aerospace TC. 
UH-1B 
UH-1H 
February 8, 2023 
 
TYPE CERTIFICATE DATA SHEET NO. H13WE 
 
This data sheet, which is part of Type Certificate No. H13WE, prescribes conditions a nd limitations under which the 
product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation 
Regulations. 
 
Type Certificate Holder: Midwest Aerospace TC LLC 
9465 Joliet Street 
St. John, IN 46373 
  
Type Certificate Holder Record:  Rotorcraft Development Corporation transferred to Midwest Aerospace TC 
LLC., on February 8, 2023. 
 
Garlick Helicopter Corporation transferred to Rotorcraft Development 
Corporation on September 6, 2012. 
 
Garlick Helicopter Corporation transferred TC H13WE to Rotorcraft 
Development Corporation on November 17, 2008. 
 
Garlick Helicopter, Inc. transferred TC H13WE to Garlick Helicopter 
Corporation on June 29, 2007.  
 
I - Model UH-1B, 9PCLHL (Utility Helicopter Restricted Category) approved: March 4, 1981 
 
Engine:   Lycoming T-53-L-11D    (See note 8 for approved alternate engines) 
 
Fuel:   Mil-T-5624, Grade JP-4; alternate fuel 
   Mil-T-5624, Grade JP-5; See TM 55-1520-219-10 for substitute and emergency fuels. 
 
Engine Limits:  Torque 
Pressure 
(PSI) 
 Output 
RPM 
 Exhaust Gas 
Temperature (Deg. C) 
 Takeoff (5 min.) 47.5 (1100 HP)  6600  610 
 Max. Continuous 39.0 (900 HP)  6400  590 
 See NOTES 11, 12, & 13 
 
Rotor Limits:  Power Off   Power On 
   Maximum 339 r.p.m.  Maximum 324 r.p.m. 
   Minimum 295 r.p.m.  Minimum 294  r.p.m. 
   Continuous operations   294-324 r. p. m.. 
 
Airspeed Limits:  Never Exceed 120 knots (138 mph,) up to and including 6600 lbs. G.W. 
   sea level to 2000 feet. 
 
   Never Exceed 112 knots (129 mph.) up to 7200 lbs. G.W. sea level to 2000 feet. (See Note 2 
for specific operating airspeed limitations.) 
 
Page No. 1 2 3 4 5 6 7 8 9 
Rev No. 14 11 11 11 11 12 12 11 13

H13WE Page 2 of 9 
  
I - Model UH-1B, 9PCLHL (cont’d) 
 
Other Limits:   Flight Hours are counted from takeoff to landing. 
 
The helicopters approved under this type certificate are done so under the concept of 
limited exposure associated with escape from inadvertent ice encounters, and are 
prohibited against flight into known icing.  The helicopters must be re-evaluated if 
certification to the General Ice protection Airworthiness Regulations is requested.  
 
C. G. Range:  Longitudinal C.G. Limits: 
   (+125.0) to (+136.0) to 6600 lbs. and above  
   (+125.0) to (+136.4) to 6500 lbs. 
   (+125.0) to (+137.3) to 6250 lbs. 
   (+125.0) to (+138.0) to 6000 lbs. or less. 
   See TM 55-1520-219-10, Center of Gravity Charts for specific loads/weights. 
 
Empty Weight C.G. (+125.0) to (+138.0) 
Range: 
 
Maximum Weight: 8500 lbs. 
 
Minimum Crew:  1 (pilot) 
 
Maximum Passengers: See Note 18 
 
Maximum Baggage: 200 lb. (150 lbs./sq. ft. deck loading maximum.) 
 
Fuel Capacity Usable: 163 U.S. gals if Crashworthy Fuel System is installed. 
   168 U.S. gals if Crashworthy Fuel System is not installed.   
 
Oil Capacity:  3.25 gals. (+157) 
 
Rotor Blade and  For rigging information, refer to Technical Manual: 
Control Movement: 55-1520-219-20. 
 
Approved Serial No’s: Surplus UH-1 B helicopters as identified in FAA Approved Garlick Helicopters Report No. 
GHI-TC-01, dated April 7, 1995 or later approved revision. 
 
II - Model UH-1H, 15PCLM (Utility Helicopter Restricted Category) approved: December 14, 1992  
 
Engine:   Lycoming T-53-L-13B   (See notes 8 & 17 for approved alternate engines) 
 
Fuel:   Mil-T-5624, Grade JP-4; alternate fuel 
   Mil-T-5624, Grade JP-5; See TM 55-1520-228-10 for substitute and emergency fuels. 
 
Engine Limits:  Torque 
Pressure 
(PSI) 
 Output 
RPM 
 Exhaust Gas 
Temperature (Deg. C) 
 Takeoff (5 min.) 50.0 (1100 HP)  6600  610-625 
 Max. Continuous 50.0 (1100 HP)  6600  400-610 
 
Rotor Limits:  Power Off   Power On 
   Maximum 339 r.p.m.  Maximum 324 r.p.m. 
   Minimum 294 r.p.m.  Minimum 294 r.p.m. 
   Continuous operation 294-324 r.p.m. 
   Maximum for auto rotation is 339 r.p.m. 
 
Airspeed Limits:  Never Exceed 124 knots (143 m.p.h.) up to and including 7500 lbs.

H13WE Page 3 of 9 
 
II - Model UH-1H, 15PCLM (cont’d) 
 
   Roof-mounted G.W. sea level to 2000 feet. 
   pitot static Never Exceed 113 knots (132 m.p.h.) at 9500 lbs. 
     G.W. sea level to 2000 feet.  
     (See Note 2 for specific operating airspeed limitations.) 
   Nose-mounted Never Exceed 119 knots (137 mph) up to and including 
   pitot static 7500 lbs. G.W. sea level to 2000 ft. 
     Never Exceed 108 knots (124 mph) at 9500 lbs. G.W. 
     sea level to 2000 ft.  
     (See Note 2 for specific operating airspeed limitations) 
 
Other Limits:  Flight Hours are counted from takeoff to landing. 
 
The helicopters approved under this type certificate are done so under the concept of 
limited exposure associated with escape from inadvertent ice encounters, and are 
prohibited against flight into known icing.  The helicopters must be re-evaluated if 
certification to the General Ice protection Airworthiness Regulations is requested.  
 
C. G. Range:  Longitudinal C.G. Limits: (+130.0) to (+144.0), at 3600 lbs. or less. 
   Lateral C.G. Limits: Plus or minus 7.5 inches 
   See TM 55-1520-210-10, Center of Gravity Charts for specific loads/weights. 
 
Empty Weight C.G. (+130.0) to (+144.0) 
Range: 
 
Maximum Weight: 9500 lbs. 
 
Minimum Crew:  1 (Pilot) 
 
Maximum Passengers: See Note 18 
 
Maximum Baggage: 100 lbs/sq. ft. cargo area (See TM 55-1520-210-10). 
 
Fuel Capacity Useable: 206.5 U.S. gals (+151.6) Crashworthy system. 
 
Oil Capacity:  3.25 gals. (+173.0) 
 
Rotor Blade and  For rigging information, refer to Technical Manual 55-1520-210-23.  
Control Movements: 
 
Approved Serial No’s: Surplus UH-1 H helicopters as identified in FAA Approved Garlick Helicopters Report 
No. GHI-TC-01, dated April 7, 1995 or later approved revision. 
 
DATA PERTINENT TO ALL MODELS 
 
Datum:   7.6” aft of aircraft nose. 
 
Leveling Means:  Plumb line from top of left main door frame. 
 
Certification Basis: FAR 21.25(a)(2) effective February 1, 1965. 
   Type Certificate No. H13WE issued for the purpose of: 
   1. Agricultural under FAR 21.25 (b)(1) 
   2. Forest and Wildlife Conservation under FAR 21.25 (b)(2)  
   3. Aerial Surveying Operations under FAR 21.25 (b)(3) 
   4. Patrolling Operations under FAR 21.25 (b)(4) 
   5. External Cargo Operations under FAR 21.25 (b)(7)

H13WE Page 4 of 9 
 
DATA PERTINENT TO ALL MODELS (cont’d) 
 
Note: In accordance with FAR 36.1(a)(4), compliance with the noise requirements has 
been shown for Garlick Models UH-1B and UH-1H.  No determination has been made by 
the Federal Aviation Administration that the noise levels of this aircraft are or should be 
acceptable or unacceptable for operation at, into, or out of, any airport. 
 
Any alteration to the helicopter for Special Purposes not identified above require further 
FAA approval and in addition, may require additional noise and/or flight testing.  
 
UH-1B 
General Note:  Any subsequent modifications to the helicopter type certified under this 
Type Certificate are to have the certification basis for that modification established under 
14 CFR 21.101 published June 7, 2000 which became effective June 10, 2003.  
Otherwise non-significant modifications are to meet the requirements of CAR 7 
airworthiness standards, including Amendment 7-5, effective May 1962, plus special 
conditions for turbine engine installations and 14 CFR 29.1529, Instructions for 
continued airworthiness, Amendment 20, effective September 11, 1980.  Also should 
consider that military installed crashworthy fuel systems in some of these aircraft and 
should require that to be maintained. 
 
UH-1H 
General Note:  Any subsequent modifications to the helicopters type certified under this 
Type Certificate are to have the certification basis for that modification established under 
14 CFR 21.101 published June 7, 2000, which became effective June 10, 2003.  
Otherwise non-significant modifications are to meet the requirements of 14 CFR 29 
airworthiness standards, transport category, Amendment 1, effective August 12, 1965, 
plus special conditions for turbine engine installations and 14 CFR 29.1529, Instructions 
for Continued Airworthiness, Amendment 20, effective September 11, 1980.  
 
Production Basis:  None. No helicopter may be produced under this approval. (See Note 4)  Prior to adding 
serial numbers to this Type Certificate, each candidate helicopter must undergo a 
conformity inspection.  The conformity inspection will be conducted in accordance with 
a Type Inspection Authorization, Part 1, or request for conformity that will include as a 
minimum, the inspections contained in the FAA Rotorcraft Directorate Restricted 
Category Conformity document dated September 25, 2001 or later FAA approved 
revisions. 
 
Equipment:  The basic required equipment as prescribed in the applicable airworthiness regulations 
(see certificate basis) must be installed in each helicopter for certification. In addition, the 
following are required: 
 
UH-1B 
   U.S. Army TM 55-1520-219-10 Operator's Manual UH-1 B. 
 
UH-1H  
1)  U.S. Army TM 55-1520-210-10, Operator's Manual UH-1H. 
2)  Standard U.S. Army cargo suspension installation 204-072-024-1; 205-070-900-5;  
205-070-900-7; or 205-070-900-19 I/A/W TM 55-1520-210-23P (Parts Manual) installed 
and maintained I/A/W TM 55-1520-210-23 (Maintenance Manual) and operated I/A/W 
TM 55-1520-210-10 (Operator's Manual) for all external cargo operations. Refer to Note 
12 for operating limitations. 
 
   All external equipment and its attachments installed on this aircraft, (other than that  
   equipment necessary to conduct the Special Purpose Operations for FAR Part 21.25   
   (b)(7) “External Cargo Operations”, operating under FAR Part 133) must be FAA   
   Approved.

H13WE Page 5 of 9 
 
NOTES 
 
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 time of original airworthiness 
certification and at all times thereafter.  
  
UH-1B Only 
Refer to pages 12-4a and 12-4b of Operator's Manual (TM 55-1520-219-10) or Appendix D of 
Maintenance Manual (TM 55-1520-219-20) for CG determination and use of ballast if required. 
 
NOTE 2. The following placards must be prominently displayed in the cockpit in full view of the pilot (on 
the instrument panel): 
 
  UH-1B  
     (a) OPERATING LIMITS 
 
DENSITY CALIBRATED AIR SPEED – KNOTS 
ALTITUDE 6600 LBS OR LESS 7200 LB 8000 LB 8500 LB 
RPM   6400             6600 6400             6600 6400             6600 6400             6600 
SEA LEVEL TO 
2000 FT 120 120  109  112   95   101  86  95 
 116 116  105  108   92    97  82  92 
 102 106   92   97   77    86  68  80 
  90  94   79   86   65    76  ---- ---- 
  77  84   66   75  ----   ----  ---- ---- 
  64  72   ----  ----  ----   ----  ---- ---- 
  51  61   ----  ----  ----   ----  ---- ---- 
 
 From 0 to 70 knots use 6000 to 6600 RPM range. 
 From 70 to 120 knots use 6400 to 6600 RPM range. 
 
EXTERNAL LOAD OPERATION:  VNE will be determined for each proposed external load  application. 
  
 REDUCE AIR SPEED WHEN VIBRATION IS EXCESSIVE. 
 
 (b) This helicopter must be operated in accordance with the Restricted Category operating limitations 
of 91.313 and with the limitations noted in U.S. ARMY TM 55-1520-219-10. 
 
UH-1H  
(a) OPERATING LIMITS         MODEL UH-1 H  
With Roof-mounted pitot static tube 
CALIBRATED AIR SPEED - KNOTS 
 
GROSS WEIGHT 6600 LB 7500 LB 8500 LB 9500 LB 
SL    2000 FT 
        3000 FT 
        6000 FT 
        9000 FT 
      12000 FT 
      15000 FT 
      18000 FT 
124 
121 
112 
102 
92 
81 
69 
 
124 
121 
112 
102 
92 
81 
69 
 
119 
116 
107 
97 
87 
76 
65 
114 
111 
102 
92 
83 
— 
— 
 
 
Up to 7500 Ibs G.W. use 6000 to 6600 RPM Range. 
Over 7500 Ibs G.W. use 6400 to 6600 RPM Range. 
 
 EXTERNAL LOAD OPERATION:  VNE will be determined for each proposed load application.

H13WE Page 6 of 9 
 
NOTE 2 (cont’d) 
 
REDUCE AIR SPEED WHEN VIBRATION IS EXCESSIVE. 
 
 MODEL UH-1H 
 With Nose-mounted Pitot Static tube 
Limits                  
Aircraft      
Weight / KIAS 
Density 
 Alt (ft) 
 
To 7500 lb 
 
8500 lb 
 
9500 lb 
SL-2000 
3000 
6000 
9000 
12000 
15000 
18000 
112 
109 
100 
91 
82 
70 
58 
107 
104 
95 
86 
77 
65 
— 
103 
100 
91 
82 
73 
— 
— 
Under 7500 lb 
6000-6600 RPM 
 Over 7500 lb 
6400- 6600 RPM 
 
Power off 294 to       339 RPM   
   Decrease Airspeed if Vibration Excessive. 
 
b) This helicopter must be operated in accordance with the Restricted Category operating limitations of FAR   
       91.313 and within the limitations noted in U.S. ARMY TM 55-1520-210-10. 
 
 
NOTE 3.  UH-1B  
  Continued airworthiness of UH-1B helicopters certificated under this Type Certificate H13WE is 
contingent upon compliance with Garlick Helicopters Inc. report GH -H13WE-CA1B, compliance 
with applicable FAA Airworthiness Directives, and compliance with all applicable Garlick 
Helicopters Inc. Alert Service Bulletins. 
 
  UH-1H  
  Continued airworthiness of UH-1H series helicopters certificated under this Type Certificate 
H13WE  is contingent upon compliance with Garlick Helicopters Inc. report GH -H13WE-CA1H 
dated 5-3-2002 or later revision, compliance with applicable FAA Airworthiness Directives, and 
compliance with all applicable Garlick Helicopters Inc. Alert Service Bulletins.  
 
NOTE 4. In addition to the standard helicopter requirements, the following additional data and/or helicopter 
configuration requirements must be met for each individual model UH-1B or UH-1H helicopter 
upon application for an original Special Airworthiness Certificate:  
 
 UH-1B 
a) A completed application for airworthiness certificate, FAA Form 8130-6 that has correctly 
identified the type certificate holders helicopter and its intended special purpose(s). 
 
b) Written confirmation from the certifying office that the affected serial number has been added 
to Type Certificate H13WE. NOTE: See the most current FAA Approved Revision of 
Type Certificte Data Sheet H13WE, Serial Number List Report No. RDC-TC-01. 
 
c) The application for airworthiness certification and the helicopter’s registration certification 
match the information on Garlick Helicopter, Inc. data plate. 
 
d) Garlick Helicopters Report GH 80, Part One, dated September 29, 1980, must be complied 
with.  
 
e) The battery may be relocated in accordance with Garlick Helicopters Report GH 80 921 & 
921-1, Part Two, dated September 30, 1980.

H13WE Page 7 of 9 
 
NOTE 4 (cont’d) 
 
f) All UH-1B series aircraft and Lycoming/Honeywell engine T53-L-11 series FAA 
Airworthiness Directives must be reviewed for applicability and complied with accordingly.  
 
g) FAA Airworthiness Directives as called out in Garlick Helicopters Inc. UH -1 Airworthiness 
Directive review list dated 5-14-2001 or later edition must be reviewed for applicability and 
complied with accordingly. 
 
h) The Helicopter(s) must be serviced, maintained, inspected, repaired and overhauled in 
accordance with the documents specified in Garlick Helicopters Inc. Instructions for 
Continued Airworthiness report GH-H13WE-CA1B dated 5-24-02 or later accepted revision. 
   
UH-1H 
a) A completed application for airworthiness certificate, FAA Form 8130-6 that has correctly 
identified the type certificate holders helicopter and its intended special purpose(s).  
 
b) Written confirmation from the certifying office that the affected serial number has been added 
to Type Certificate H13WE. NOTE: See the most current FAA Approved Revision of 
Type Certificte Data Sheet H13WE, Serial Number List Report No. RDC -TC-01. 
 
c) The application for airworthiness certification and the helicopter’s registration certification 
match the information on Garlick Helicopter, Inc. data plate. 
 
d) Garlick Helicopters Report GH 80, Part One, dated September 29, 1980, must be complied 
with. 
 
e) Battery may be re-located in accordance with Garlick Helicopter Report GH 80-921 and 
921-1, Part Two, dated September 30, 1980. 
 
f) All UH-1H series aircraft and Lycoming/Honeywell engine T53-L-13 series FAA 
Airworthiness Directives must be reviewed for applicability and complied with accordingly. 
 
g) FAA Airworthiness Directives as called out in Garlick Helicopters Inc. UH -1 Airworthiness 
Directive review list dated 5-14-2001 or later edition must be reviewed for applicability and 
complied with accordingly. 
 
h) The Helicopter(s) must be serviced, maintained, inspected, repaired and overhauled in 
accordance with the documents specified in Garlick Helicopters Inc. report 
GH-H13WE-CA1H dated 5-3-2002 or later revision. 
 
i) This model helicopter must be operated in compliance with TM 55-1520-210-10. 
 
NOTE 5. This helicopter is prohibited from carrying cargo for compensation or hire.  Carriage of cargo is 
limited to such cargo that is incidental to the helicopter owner’s/operator’s business, which is 
other than air transportation. 
 
NOTE 6. A restricted category helicopter may not be operated in a foreign country without the express 
written approval of that country. 
 
NOTE 7. This helicopter has not been shown to meet the requirements of the applicable comprehensive and 
detailed Airworthiness Code as provided by Annex 8, to the Convention of the International Civil 
Aviation Organization.

H13WE Page 8 of 9 
 
NOTES (cont’d) 
 
NOTE 8. UH-1B Only 
Lycoming engine models T53-L-11 (s/n suffix "A"), T53-L-11B and T53-L-11C are approved for 
use as alternate engines under this Type Certificate.  Engines Identified in this note will be 
maintained on a 1200 hr. (T53-L-11C, 1800 hr.) overhaul schedule and in accordance with the 
applicable U.S Army Maintenance, Overhaul and Parts Manuals, applicable to that engine.   
 
UH-1H Only 
  Lycoming engine models T53-L-13, T53-L-13A, T53-L-13BA and the commercial T5313B are 
  approved for use as alternate engines under this Type Certificate.  Military engines Identified in  
  this note will be maintained on a 2400 hr. overhaul schedule and in accordance with the  
  applicable U.S Army Maintenance, Overhaul and Parts Manuals, applicable to that engine. For  
T5313B overhaul schedule, ref: Garlick Helicopters report GH-H13WE-CA1H Dated 5-3-02 or later 
approved revision. 
 
NOTE 9. Type Certificate (TC) and Type Certificate Data Sheet reissued to clearly state that Bell Helicopter 
Textron, Inc., has no involvement with this TC and that Garlick Helicopters or later specified 
owner(s) , (See Page 1), are the original holder of TC No. H13WE. Authority, AWS-100 Memo 
dated February 22, 1985. 
 
NOTE 10. Torque pressure output by the engine torque sensing system varies with individual engines. A 
calibration of this value is required of each engine and the value corresponding to take -off power 
is stamped on the engine data plate. 
 
NOTE 11. Gas producer speed, as shown under "Engine Limits" are maximum permissible speeds. The gas 
producer speed for rated power outputs varies with individual engines and must be determined 
during engine calibration and stamped on the engine data plate, The rated gas producer speed 
shown on the temperature limit placard installed on the instrument panel must correspond to the 
engine data plate gas producer speed. Gas producer speed limits also vary with OAT in accordance 
with the schedule as shown on the Temperature Limit (GO-NO-GO TAKE-OFF) placard on the 
instrument panel. 
 
NOTE 12. Maximum permissible exhaust gas temperature varies with ambient temperature as described in 
the Operators Manual.  Check engine EGT by use of Health Indicator Test (HIT) prior to take-off 
(see TM 55-1520-219-10 and HIT EGT Log for aircraft). 
 
NOTE 13. Aircraft certified under this Type Certificate are eligible for flight with Pilot-in-command located in the 
left seat position during FAR Part 133 external load operations with Approved Flight Manual Supplement 
providing they are modified to extend cargo hook manual release capabilities to the left seat position 
I/A/W Garlick Helicopters, Inc. drawing no. GHI 72290-2. Instruments required for safety of flight must 
be clearly readable from the left seat position or may be relocated as necessary.  Instrument relocation 
must be FAA approved. 
 
NOTE 14. Garlick Helicopters, Inc. Technical Bulletin No. UHI-93-01 provides information to 
  operators on parts interchangeability and replacement parts.  
 
NOTE 15. Avionics Specialties Power Analyzer and Recorder (PAR) System may be installed in  
  accordance with GHI Technical Bulletin UH1-98-07 dated 7-7-98 or later revision.  
 
NOTE 16. Military to Civil or Military to Military engine changes are allowed, provided the replacement 
engine is of the same make and model as identified in this TCDS.  The military or civil 
replacement engine must have proper military or civil records and have the applicable FAA 
Airworthiness Inspection accomplished and is in an airworthy condition.

H13WE Page 9 of 9 
 
NOTES (cont’d): 
 
NOTE 17. Any Alteration to the type design of this aircraft may require Instructions for Continued 
Airworthiness (ICA’s). Changes to the Type Design by means of a Supplemental Type Ce rtificate 
(STC) requiring ICA’s or changes to existing ICA’s must be submitted and reviewed by the Fort 
Worth Aircraft Evaluation Group (FTW-AEG). Type Design Changes by means of a Field 
Approval that require ICA’s must have those ICA’s reviewed by the Flight Standards District 
Office (FSDO) managing the Field Approval or the FTW-AEG. 
 
NOTE 18. No person may be carried in this helicopter during flight unless that person is essential to the 
purpose of the flight. 
 
NOTE 19. Helicopter is not approved for IFR operation or flight into known icing conditions. 
 
NOTE 20. UH-1H Only 
 Aircraft must be modified I/A/W Garlick Helicopters, Inc. Report No. GH -UHI-MOD dated 7- 
  7-98 or later approved revision to conduct the Special Purposes of Aerial Survey Operations un der FAR 
  21.25(b)(3) and Patrolling Operations under FAR 21.25(b)(4). 
 
NOTE 21. UH-1H Only 
Standard U. S. Army Cargo Suspension Installation 204-072-024-1; 205-070-900-5;  205-070-900-7; or   
  205-070-900-19 I/A/W TM 55-1520-210-23P (Parts Manual) installed and maintained I/A/W TM   
  55-1520-210-23; and operated I/A/W TM 55-1520-210-10 (Operator's Manual). 
 
…END…
```

## ADs

None name its models.

## Registered aircraft by registry model (OpenAirDocs)

- [Garlick Helicopters UH-1H](https://openairdocs.org/model/garlick-helicopters-uh-1h): 7 aircraft (registry code 3740005)
- [Garlick Helicopters UH-1B](https://openairdocs.org/model/garlick-helicopters-uh-1b): 3 aircraft (registry code 3740001)
- [Rotorcraft Development UH-1H](https://openairdocs.org/model/rotorcraft-development-uh-1h): 2 aircraft (registry code 3741202)

## STCs approved under this data sheet (52, first 50)

- [STC SR02796SE](https://openairdocs.org/stc/SR02796SE): Installation of Human External Cargo (HEC) system. Boost Systems LLC
- [STC SH8609SW](https://openairdocs.org/stc/SH8609SW): Fabrication of Isolair Eliminator II Model 4600-205 fire fighting system.. Isolair Inc.
- [STC SR01776SE](https://openairdocs.org/stc/SR01776SE): Fabrication, installation, and maintenance of the Isolair Helicopters, Inc., Model 9002 High Cross tubes. Isolair Inc.
- [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 SH3744NM](https://openairdocs.org/stc/SH3744NM): Dual Battery Installation. WSH, LLC
- [STC SR00026DE](https://openairdocs.org/stc/SR00026DE): Installation of tailboom 24 inch plug extension, commercial style main rotor blades, and rotorhead.. Midwest Aerospace TC LLC
- [STC SR00073DE](https://openairdocs.org/stc/SR00073DE): Replacement of Lycoming T53-L-13 series powerplant. Midwest Aerospace TC LLC
- [STC SR00119DE](https://openairdocs.org/stc/SR00119DE): Installation of an upgraded 42 degree Tail Rotor gearbox, P/N 212-040-003, and Control Cables. Midwest Aerospace TC LLC
- [STC SR00143DE](https://openairdocs.org/stc/SR00143DE): Installation of an upgraded 42 degree Tail Rotor gearbox, P/N 212-040-003. Midwest Aerospace TC LLC
- [STC SR09167RC](https://openairdocs.org/stc/SR09167RC): Replacement of tail rotor control roller chain.. Midwest Aerospace TC LLC
- [STC SR09176RC](https://openairdocs.org/stc/SR09176RC): Modification of the vertical fin spar. Midwest Aerospace TC LLC
- [STC SR09177RC](https://openairdocs.org/stc/SR09177RC): Modification of the vertical fin spar. Midwest Aerospace TC LLC
- [STC SR09224RC](https://openairdocs.org/stc/SR09224RC): Modification of the lift beam on the Model UH-1H. Midwest Aerospace TC LLC
- [STC SR02761LA](https://openairdocs.org/stc/SR02761LA): Installation of UH-1H composite main rotor blades on the UH-1B helicopters. Northern X-Treme Helicopters
- [STC SR00713SE](https://openairdocs.org/stc/SR00713SE): Installation of Onboard Systems International Cargo Hook Kit. Onboard Systems International
- [STC SH5690NM](https://openairdocs.org/stc/SH5690NM): Installation of Advanced Technology Aircraft Co. engine barrier filter.. WSH, LLC
- [STC SH5707NM](https://openairdocs.org/stc/SH5707NM): Fabrication of Onboard Systems Model 200-088-03 or 200-088-04 (without Load Weight) or 200-089-03, -04, -05 or -06 (with Load Weight) cargo hook suspension systems. Onboard Systems International
- [STC SH5737NM](https://openairdocs.org/stc/SH5737NM): Replacement of Bell magnesium cargo hook bumper and ring Part Nos. 204-072-901-1 or -3, and 204-072-905-3, respectively, with Onboard bumper ring kit No. 210-092-00. Fabrication of Onboard Systems Model 210-092-00 bumper ring kit. Onboard Systems International
- [STC SH5758NM](https://openairdocs.org/stc/SH5758NM): Fabrication of the Onboard Model 200-095-00 Multi-Channel Electrical Slip-Ring Kit. Onboard Systems International
- [STC SR02475SE](https://openairdocs.org/stc/SR02475SE): Installation of a Tailboom Motion Detection System. Aircraft Structural Repair Inc.
- [STC SR02492LA](https://openairdocs.org/stc/SR02492LA): Installation of a Helicopter Technology Company main rotor blade assembly. Helicopter Technology Co
- [STC SR02641SE](https://openairdocs.org/stc/SR02641SE): Installation of a Service Deck. Northwest Heli-Structures Inc
- [STC SR02070SE](https://openairdocs.org/stc/SR02070SE): Fabrication of Dart D205-770-011 Replacement Engine Mount Kit. Dart Aerospace USA Inc.
- [STC SR00929SE](https://openairdocs.org/stc/SR00929SE): Fabrication of tail boom mounted strakes.. BLR Aerospace LLC.
- [STC SR01039SE](https://openairdocs.org/stc/SR01039SE): Fabrication of tail boom mounted strakes in accordance with Master Drawing List Number BL-UH1H-01, Revision D, dated September 10, 2001, or later Federal Aviation Administration (FAA)-approved revision; and installation of this strake system. BLR Aerospace LLC.
- [STC SR01470SE](https://openairdocs.org/stc/SR01470SE): Fabrication and Installation of  Fast Fin System.. BLR Aerospace LLC.
- [STC SR03408CH](https://openairdocs.org/stc/SR03408CH): Install Airwolf Aerospace, LLC Tension-Torsion Strap Assemblies, P/N AA-204-310-101-101 or AA-204-310-101-103. Airwolf Aerospace LLC
- [STC SR02413LA](https://openairdocs.org/stc/SR02413LA): Installation of an AKV, Inc Exceedence and Trend Monitoring System kit P/N ETM1000. AKV Inc.
- [STC ST04270AT](https://openairdocs.org/stc/ST04270AT): Install the VTOL ASSALT  V3 Windscreen Laminate Kit. VTOL LLC
- [STC SR00767SE](https://openairdocs.org/stc/SR00767SE): Fabrication of Helipro spar replacement system. Vector Aerospace Helicopter Services USA Inc.
- [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 SR01742NY](https://openairdocs.org/stc/SR01742NY): Installation of extended height landing gear.. Dart Aerospace Limited
- [STC SR01196LA](https://openairdocs.org/stc/SR01196LA): Installation of Honeywell (Lycoming) T53-L-703 engine to replace Honeywell (Lycoming) T53-L-13/13B/-13BA engine. Responsible ACO is Los Angeles, NM-L.. Minuteman Aviation Inc.
- [STC SR02051LA](https://openairdocs.org/stc/SR02051LA): Installation of a VAn Horn Aviation Tail Rotor Blade.. Van Horn Aviation LLC
- [STC SR01946SE](https://openairdocs.org/stc/SR01946SE): Installation of the Mechanical Specialties, Model UH606. Mechanical Specialties Inc
- [STC SR09257RC](https://openairdocs.org/stc/SR09257RC): Fabrication, modification, and installation of a new vertical fin spar in accordance with Global Helicopter Technology, Inc., Drawing number VTF-030-800, Revision D, dated March 26, 2001, or later FAA approved revision.. Global Spar LLC
- [STC SR09313RC](https://openairdocs.org/stc/SR09313RC): Fabrication, modification, and installation of a new vertical fin spar in accordance with Global Helicopter Technology, Inc., Drawing number VTF-030-802, Revision B, dated April 5, 2001, or later FAA approved revision.. Global Spar LLC
- [STC SR09316RC](https://openairdocs.org/stc/SR09316RC): Fabrication, modification, and installation of a new vertical fin spar in accordance with Global Helicopter Technology, Inc., Drawing number VTF-030-801, Revision B, dated April 5, 2001, or later FAA approved revision.. Global Spar LLC
- [STC SR01497AT](https://openairdocs.org/stc/SR01497AT): Manufacture of Windows in accordance with Aeronautical Accessories, Inc. Drawing List Report No. AA-97115, no revision, dated August 20, 1997, or later FAA approved revisions, and installation per Installation Instructions  listed in that report.. Bell Helicopter Textron Inc.
- [STC SR01812AT](https://openairdocs.org/stc/SR01812AT): Manufacture of Flitestep in accordance with Aeronautical Accessories, Inc. Drawing List Report No. AA-97166, no revision, dated December 19, 1997, or later FAA approved revisions, and installation per Aeronautical Accessories, Inc. Report AA-97087, Revision B, dated December 18, 1997, or later FAA approved revisions.. Bell Helicopter Textron Inc.
- [STC SR01922AT](https://openairdocs.org/stc/SR01922AT): Manufacture of Locking Door Handle.. Bell Helicopter Textron Inc.
- [STC SR01923AT](https://openairdocs.org/stc/SR01923AT): Manufacture of Air Deflector.. Bell Helicopter Textron Inc.
- [STC SR01924AT](https://openairdocs.org/stc/SR01924AT): Manufacture of Low Skid or High Skid Landing Gear.. Bell Helicopter Textron Inc.
- [STC SR02545AT](https://openairdocs.org/stc/SR02545AT): Manufacture of Fast Rope Kit in accordance with Aeronautical Accessories, Inc. Drawing List Report No. AA-99126-4Rev A dated June 14, 2001, or later FAA approved revision, and installation (structural provisions only) per Aeronautical Accessories, Inc. Report No. AA-98167-Rev E dated May 1, 2001, or later approved revision.. Bell Helicopter Textron Inc.
- [STC SR00103SE](https://openairdocs.org/stc/SR00103SE): Installation of Aviation Development Corporation oil filter. Aviation Development Corporation
- [STC SR01298NY](https://openairdocs.org/stc/SR01298NY): Installation of replacement crosstubes P/N D212-664.. Dart Aerospace Limited
- [STC SR00563NY](https://openairdocs.org/stc/SR00563NY): Installation of Skidtubes and associated saddles. Dart Aerospace Limited
- [STC SR00332NY](https://openairdocs.org/stc/SR00332NY): Installation of Avionics Specialties power analyzer and recorder no. SL17009 and SL17061.. Aerosonic Corporation
- [STC SR01395NY](https://openairdocs.org/stc/SR01395NY): Installation of adjustable engine mount.. Dart Aerospace Limited
- [STC SR01218AT](https://openairdocs.org/stc/SR01218AT): Manufacture of Flitestep.. Aeronautical Accessories, Inc.

All 52: https://openairdocs.org/tcds/H13WE/stcs.md

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