UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

Supplemental Type Certificate

Number SR00036SE

 

This certificate, issued to Soloy, LLC

450 Pat Kennedy Way S.W.

Olympia, WA 98501

Certifies that the change in the type design for the following product with the limitations and conditions 

therefore as specified hereon meets the airworthiness requirements of Part * of the * Regulations

* See Pages 13 and 14 of this certificate for Certification Basis

Original ProductType Certificate Number: H2SW

 Make: Bell 

 Model: 206L-1, 206L-3, and 206L-4

Description of the Type Design Change: Installation of two Allison 250-C20R engines and associated systems 

in accordance with sealed Tridair Helicopters, Inc., Master Drawing List No. THI-206-104, dated August 11, 1994, 

or later FAA approved revisions.

Limitations and Conditions: Approval of this change in type design applies to the above model helicopters 

which are otherwise unmodified. This approval should not be extended to other aircraft of this model on which 

other previously approved modifications are incorporated unless it is determined that the relationship between this 

change and any of those other changes in type design will introduce no adverse effect upon the airworthiness of 

that aircraft. A copy of this certificate must be maintained as part of the permanent records for the modified

aircraft.

(See Continuation Sheet Page 3 of 14 Pages)

This certificate and the supporting data which is the basis for approval shall remain in effect until 

surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator of the 

Federal Aviation Administration. 

Date of application: September 30, 1987 Date reissued: January 23, 2014

Date of issuance: November 19, 1993 Date amended: 9/12/94; 10/20/95

 

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 1 OF 15 PAGES

By direction of the Administrator

__________________________________________ (Signature) 

 Manager, Seattle Aircraft Certification Office

(Title)
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Limitations and Conditions continued: 

Model 206L-4

Certain limitations and conditions shown on Type Certificate Data Sheet (TCDS) H2SW for the model 206L-4 

remain applicable. The following list contains those limitations and conditions which have been modified and 

certain unmodified ones which are listed for clarity.

Model: Bell 206L-4 modified by this supplemental type certificate (STC) (Normal Category Rotorcraft)

Engine(s): Allison Model 250-C20R with Bendix gas producer fuel control DP-N2.

Fuel: ASTM Type Jet B (JP-4) or ASTM Type Jet A or A-1 (JP-5). See Tridair 206L-4 Rotorcraft Flight 

Manual Supplement for fuel mixture and fuel temperature limitations (See Note 15)

Engine Limits:

Torque Pressure

Output

Shaft Speed

Turbine

Outlet Temp

Gas Gen

Speed

Takeoff (5 min) 109 PSI (450 SHP) 6016 810° C 105% (N1)

Max Continuous 89.6 PSI (370 SHP) 6016 752° C 105% (N1)

See Rotorcraft Flight Manual Supplement for One Engine Inoperative (OEI) and Transient Limitations. 

(See Note 15)

Transmission Limits:

Main Transmission Combining Gearbox (Co-Box)

With Part Number (P/N) 260-2353-5 Torque Indicator

Takeoff (5 min) torque: 109% (490 SHP) Maximum input torque: 100% (450 SHP)

Max Continuous: 82% (370 SHP)

With P/N 260-2357-5 Torque Indicator

Takeoff (5 min) torque: 100% (490 SHP) Maximum input torque: 91.8% (450 SHP)

Max Continuous: 75.5% (370 SHP)

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 3 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Limitations and Conditions continued: 

Model 206L-4 (Continued):

Rotor Limits

Power Off Power On

Maximum 422 RPM Maximum 398 RPM

(Triple Tach Reading 107% (Triple Tach Reading 101%)

Minimum 355 RPM Minimum 390 RPM

(Triple Tach Reading 90%) (Triple Tach Reading 99%)

Airspeed Limits

Basic VNE is 130 KIAS sea level to 3,000 feet density altitude. Decrease VNE for ambient conditions in 

accordance with Airspeed Limitation Placard in the 206L-4 Rotorcraft Flight Manual.

C.G. Range:

(a) Longitudinal C.G. Limits

(Internal Loading)

Forward Limit

(+118.0) up to 2,800 lbs. changing linearly to (+119.5) at 4,550 lbs.

Aft Limit

(+128.5) up to 2,900 lbs. changing linearly to (+126.3) at 4,500 lbs. (External 

Loading)

(b) Lateral C.G. Limits

Left 4.0 inches up to 4,150 lbs., 1.2 inches above

Right 3.5 inches up to 4,510 lbs., 1.61 inches above

Empty Weight

C.G. Range:

Refer to Section 8 of the Tridair 206L-4 Maintenance Manual Supplement. (See Note 16)

Maximum Weight:

4,550 lbs. (2063 kg) (Internal Loading)

4,550 lbs. (2063 kg) (External Loading)

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 4 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Limitations and Conditions continued: 

Model 206L-4 (Continued):

Altitude Limits:

Maximum altitude at 4,150 lbs. or less is 20,000 feet pressure altitude.

Maximum altitude at 4,151 lbs. to 4,550 lbs., or single engine is 10,000 feet density altitude.

Maximum altitude for takeoff and landing at 4451 lbs. to 4550 lbs. is 3,000 feet density altitude.

Minimum Crew:

1 at (+65.0)

Passengers:

1 at (+65.0), 2 at (+91.0), and 3 at (+129.0). Refer to Tridair 206L-4 Rotorcraft Flight Manual Supplement for 

limitations (See Note 15).

Maximum Cargo:

Refer to Bell Helicopter 206L-4 Rotorcraft Flight Manual for loading schedule (See Note 15).

Fuel Capacity:

115.7 gallons (+132.5): unusable fuel, 5.2 gallons at (+87.3).

Oil Capacity:

12.0 quarts (+109.0) (each engine).

Rotor Blade and Control Movement:

For rigging information refer to the Bell Helicopter 206L-4 Maintenance Manual (See Note 16).

Serial Numbers Eligible:

52001 and subsequent.

Datum:

Station 0 (datum is 1 inch forward of most forward point of fuselage cabin nose section, or 55.16 inches forward 

of jack point centerline).

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 5 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Limitations and Conditions continued: 

Model 206L-4 (Continued):

Leveling Means:

Plumb line from ceiling left rear cabin to index plate on floor.

Model 206L-3

Certain limitations and conditions shown on TCDS H2SW for the Model 206L-3 remain applicable. The following 

list contains those limitations and conditions which have been modified and certain unmodified ones which are 

listed for clarity.

Model: Bell 206L-3 modified by this STC (Normal Category Rotorcraft)

Engine(s): Allison Model 250-C20R with Bendix gas producer fuel control DP-N2

Fuel: ASTM Type Jet B (JB-4) or ASTM Type Jet A or A-1 (JP-5). See Tridair 206L-3 Rotorcraft Flight 

Manual Supplement for fuel mixture and fuel temperature limitations.

Engine Limits:

Torque Pressure

Output

Shaft Speed

Turbine

Outlet Temp

Gas Gen

Speed

Takeoff (5 min) 109 PSI (450 SHP) 6016 810° C 105% (N1)

Max Continuous 89.6 PSI (370 SHP) 6016 752° C 105% (N1)

See Tridair 206L-3 Rotorcraft Flight Manual Supplement for O.E.I. (One Engine Inoperative) and Transient 

Limitations.

Transmission Limits:

Main Transmission Combining Gearbox (Co-Box)

Takeoff (5 min) torque: 100% (450 SHP) Maximum input torque: 100% (450 SHP)

Max Continuous: 82.2% (370 SHP)

Rotor Limits:

Power Off Power On

Maximum 422 RPM Maximum 398 RPM

(Triple Tach Reading 107% (Triple Tach Reading 101%)

Minimum 355 RPM Minimum 390 RPM

(Triple Tach Reading 90%) (Triple Tach Reading 99%)

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 6 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Limitations and Conditions continued: 

Model 206L-3 (Continued):

Airspeed Limits:

Basic VNE is 130 KIAS sea level to 3,000 feet density altitude. Decrease VNE for ambient conditions in 

accordance with Airspeed Limitation Placard in the Bell Helicopter 206L-3 Rotorcraft Flight Manual.

C.G. Range:

(a) Longitudinal C.G. Limits

(Internal Loading)

Forward Limit

(+118.0) up to 2,800 lbs. changing linearly to (+119.2) at 4,250 lbs.

Aft Limit

(+128.5) up to 2,900 lbs. changing linearly to (+126.7) at 4,250 lbs. 

(External Loading)

Forward Limit

(+118.0) up to 2,800 lbs. changing linearly to (+119.2) at 4,250 lbs.

Aft Limit

(+128.5) up to 2,900 lbs. changing linearly to (+126.7) at 4,250 lbs.

(b) Lateral C.G. Limits

Left 4.0 inches up to 4,150 lbs., 1.2 inches above

Right 3.5 inches up to 4,150 lbs., 1.61 inches above

Empty Weight C.G. Range:

Refer to Section 8 of the Tridair 206L-3 Maintenance Manual Supplement.

Maximum Weight:

4,250 lbs. (1927.8 kg) (Internal Loading)

4,250 lbs. (1927.8 kg) (External Loading)

Altitude Limits:

Maximum altitude at 4,150 lbs. or less is 20,000 feet pressure altitude.

Maximum altitude at 4,151 lbs. to 4,250 lbs. is 10,000 feet density altitude.

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 7 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Limitations and Conditions continued: 

Model 206L-3 (Continued):

Minimum Crew:

1 at (+65.0)

Passengers:

1 at (+65.0), 2 at (+91.0), and 3 at (+129.0). Refer to Tridair 206L-3 Rotorcraft Flight Manual Supplement for 

limitations.

Maximum Cargo:

Refer to Bell Helicopter 206L-3 Rotorcraft Flight Manual for loading schedule. 

Fuel Capacity:

115.7 gallons (+132.5): unusable fuel, 5.2 gallons at (+87.3)

Oil Capacity:

12.0 quarts (+109.0) (each engine).

Rotor Blade and Control Movement:

For rigging information refer to the Bell Helicopter 206L-3 Maintenance Manual.

Serial Numbers Eligible:

51001 and subsequent.

Datum:

Station 0 (datum is 1 inch forward of most forward point of fuselage cabin nose section, or 55.16 inches forward 

of jack point centerline).

Leveling Means:

Plumb line from ceiling left rear cabin to index plate on floor.

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 8 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Limitations and Conditions continued: 

Model 206L-1:

Certain limitations and conditions shown on TCDS H2SW for the Model 206L-1 remain applicable. The following 

list contains those limitations and conditions which have been modified and certain unmodified ones which are 

listed for clarity.

Model: Bell 206L-1 modified by this STC (Normal Category Rotorcraft)

Engine(s): Allison Model 250-C20R with Bendix gas producer fuel control DP-N2.

Fuel: ASTM Type Jet B (JP-4) or ASTM Type Jet A or A-1 (JP-5). See Tridair 206L-1 Rotorcraft Flight

Manual Supplement for fuel mixture and fuel temperature limitations 

Engine Limits:

Torque Pressure

Output

Shaft Speed

Turbine

Outlet Temp

Gas Gen

Speed

Takeoff (5 min) 109 PSI (450 SHP) 6016 810° C 105% (N1)

Max Continuous 89.6 PSI (370 SHP) 6016 752° C 105% (N1)

See Tridair 206L-1 Rotorcraft Flight Manual Supplement for One Engine Inoperative (OEI) and Transient

Limitations. 

Transmission Limits:

Main Transmission Combining Gearbox (Co-Box)

Takeoff (5 min) torque: 100% (435 SHP) Maximum input torque: 100% (450 SHP)

OEI Takeoff (5 min) torque 103% (450 SHP)

Max Continuous: 85% (370 SHP)

Rotor Limits:

Power Off Power On

Maximum 422 RPM Maximum 398 RPM

(Triple Tach Reading 107%) (Triple Tach Reading 101%)

Minimum 355 RPM Minimum 390 RPM

(Triple Tach Reading 90%) (Triple Tach Reading 99%)

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 9 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Limitations and Conditions continued: 

Model 206L-1 (Continued):

Airspeed Limits:

Basic VNE is 130 KIAS sea level to 3,000 feet density altitude. Decrease VNE for ambient conditions in 

accordance with Airspeed Limitation Placard in the Bell Helicopter 206L-1 Rotorcraft Flight Manual.

C.G. Range:

(a) Longitudinal C.G. Limits

(Internal Loading)

Forward Limit

(+118.0) up to 2,800 lbs. changing linearly to (+119.2) at 4,250 lbs.

Aft Limit

(+128.5) up to 2,900 lbs. changing linearly to (+126.7) at 4,250 lbs. 

(External Loading)

Forward Limit

(+118.0) up to 2,800 lbs. changing linearly to (+119.5) at 4,250 lbs.

Aft Limit

(+128.5) up to 2,900 lbs. changing linearly to (+126.3) at 4,250 lbs.

(b) Lateral C.G. Limits

Left 4.0 inches up to 4,150 lbs., 1.2 inches above

Right 3.5 inches up to 4,150 lbs., 1.61 inches above

Empty Weight C.G. Range:

Refer to Section 8 of the Tridair 206L-1 Maintenance Manual Supplement.

Maximum Weight:

4,250 lbs. (1927.8 kg) (Internal Loading)

4,250 lbs. (1927.8 kg) (External Loading)

Altitude Limits:

Maximum altitude at 4,150 lbs. or less is 20,000 feet pressure altitude.

Maximum altitude at 4,151 lbs. to 4,250 lbs. is 10,000 feet density altitude.

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 10 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Model 206L-1 (Continued):

Minimum Crew:

1 at (+65.0)

Passengers:

1 at (+65.0), 2 at (+91.0), and 3 at (+129.0). Refer to Tridair 206L-1 Rotorcraft Flight Manual Supplement for 

limitations.

Maximum Cargo:

Refer to Bell Helicopter 206L-1 Rotorcraft Flight Manual for loading schedule. 

Fuel Capacity:

102.9 gallons (+132.5): unusable fuel, 5.2 gallons at (+87.3).

Oil Capacity:

12.0 quarts (+109.0) (each engine).

Rotor Blade and Control Movement:

For rigging information refer to the Bell Helicopter 206L-1 Maintenance Manual (See Note 10).

Serial Numbers Eligible:

45154 thru 45790.

Datum:

Station 0 (datum is 1 inch forward of most forward point of fuselage cabin nose section, or 55.16 inches forward 

of jack point centerline).

Leveling Means:

Plumb line from ceiling left rear cabin to index plate on floor.

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 11 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Certification Basis: 

Applicable to Model 206L-4:

FAR Part 27, dated October 2, 1964, Amendment 27-1 through 27-24, with: Section 27.1545 at Amendment 27-8; 

Section 27.1587 at Amendment 27-14; Section 27.1585 at Amendment 27-16, Section 27.45 at Amendment 27-

20; FAR Part 27, Amendment 27-28, Subpart A except Section 27.1, Subpart B; Subpart C Sections 27.301, 

27.305, 27.307, 27.309, 27.337, 27.351, 27.427, 27.471, 27-479, 27.481, 27.485, 27.501, 27.521, 27.547, 

27.549, 27.561, 27.571, Subpart D Sections 27.601, 27.603, 27.605, 27.607, 27.609, 27.611, 27.613, 27.619, 

27.629, 27.663, 27.674, 27.681, 27.683, 27.685, 27.751, 27.753, 27.771, 27.777, 27.783, 27.807, 27.831, 27.861, 

27.865, Subpart E, Subpart F Sections 27.1301, 27.1305, 27.1307, 27.1309, 27.1321, 27.1337, 27.1351 through 

27.1367, 27.1381, 27.1383, Subpart G except 27.1545; and Sections 27.391, 27.395, 27.397, 27.399, replaced 

by 6.220, 6.225, 6.323 of CAR Part 6, dated December 6, 1956, as amended by Amendments 6-1 through 6-4. 

Exceptions to FAR 27 are the deletion of 27.71, 27.177, 27.562, 27.610, and 27.1322

Far Part 29, through Amendment 29-32, Sections 29.1, 29.53, 29.59, 29.65, 29.67, 29.73, 29.75, 29.77, 29.79, 

29.181, 29.861, 29.903, 27.927, 29.939, 29.953, 29.1045, 29.1047, 29.1189, 29.1191, 29.1195, 29.1203, 

29.1303, 29.1305, 29.1309, 29.1505, 29.1517, 29.1585, and 29.1587.

FAR 36, Appendix J, dated October 7, 1992, and ICAO Annex 16, Volume 1, Chapter 11, as proposed at time of 

testing, April 1993.

Equivalent Safety Findings: Skid Landing Gear (Drop Test) – FAR 27.723, 27.725, and 27.727; Fuel tanks (Drop 

Test) - FAR 27.965(c)(1) and (c)(2).

Exception No. 502 dated March 14, 1989, (Docket No. 25501), as amended by Exemption 5025A.

Applicable to Models 206L-3 and 206L-1:

CAR 6 effective December 20, 1956, as amended by Amendments 6-1 through 6-4 CAR 6.307(b) and 6.637 of 

Amendment 6-5, Special Conditions, “condition establishing compensating factors providing and equivalent level 

of safety under Civil Air Regulations, Section 6.10 for light turbine power helicopters,” dated October 2, 1962, as 

revised February 8, 1966, plus the water/alcohol power augmentation special condition, dated November 14, 

1967, revised September 15, 1975; FAR Part 27, Amendment 27-28, Subpart A except Section 27.1, Subpart B, 

Subpart C Sections 27.301, 27.305, 27.307, 27.309, 27.391, 27.471, 27.479, 27.481, 27.485, 27.501, 27.521, 

27.547, 27.549, 27.561, Subpart D Sections 27.601, 27.603, 27.605, 27.607, 27.609, 27.611, 27.613, 27.619, 

27.681, 27.683, 27.685, 27.751, 27.753, 27.771, 27.777, 27.831, 27.861, Subpart E, Subpart F Sections 27.1301, 

27.1305, 27.1307, 27.1309, 27.1321, 27.1322, 27.1337, 27.1351 through 27.1367, 27.1381, 27.1383, Subpart G 

except 27.1545.

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 12 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Certification Basis Continued: Applicable to Models 206L-3 and 206L-1 Continued:

FAR Part 29, through Amendment 29-32, Sections 29.1, 29.53, 29.59, 29.65, 29.67, 29.73, 29.75, 29.77,

29.79, 29.181, 29.861, 29.903, 29.927, 29.939, 29.953, 29.1045, 29.1047, 29.1189, 29.1191, 29.1195, 29.1203, 

29.1303, 29.1305, 29.1309, 29.1505, 29.1517, 29.1585, and 29.1587.

FAR 36, Appendix J, dated October 7, 1992, and ICAO Annex 16, Volume 1, Chapter 11, as proposed at time of 

testing, April 1993.

Exemption No. 5025, dated 14, 1989, (Docket No. 25501), as amended by Exemption 5025A.

Equipment: (All Models)

The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) 

must be installed in the helicopter for certification.

In addition, the following documents are required:

Tridair Helicopters FAA approved Rotorcraft Flight Manual Supplement No. RFMS-TH-1, dated 

November 19, 1993, for the Bell 206L-4; RFMS-TH-1, dated July 28, 1994, for the Bell 206L-3 and 206L-1, as 

applicable, or later FAA approved revisions (See Note 15).

NOTE 1 Current weight and balance report including list of required equipment and list of equipment 

included in certificated empty weight, and loading instructions when necessary must be 

provided for each helicopter at the time of original certification. The certificate empty weight 

and corresponding C.G. locations must include undrainable oil and unusable fuel for the 

appropriate model.

NOTE 2 The following placard must be displayed in front of and in clear view of the pilot: “THIS 

HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS 

SPECIFIED IN THE APPROVED HELICOPTER FLIGHT MANUAL.” All placards required 

in the approved flight manual must be installed in the appropriate locations.

NOTE 3 The retirement times for critical parts are listed in the FAA approved Chapter Four of Bell 

Helicopters Maintenance Manuals BHTI 206L-4-MM-1, BHTI206L3-MM-1, and 

BHTI206L1-MM-1, and in the FAA approved Chapter Four of Tridair Helicopters Maintenance 

Manual Supplements, THI-206L4-MM-1, THI206L3-MM-1, and THI206L-1-MM-1. (See Note 

16)

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 13 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Certification Basis Continued: NOTE 4 Information essential for proper maintenance of each model is contained in the appropriate 

Bell Helicopters Maintenance Manual and the appropriate Tridair Helicopters Maintenance 

Manual Supplement. (See Note 16)

NOTE 5 Power on rotor and engine output shaft speed limits increase inversely with power. Rotor 

(NR) and engine output shaft (N2) speed limits are shown in Section 1 of the appropriate FAA 

approved Tridair Rotorcraft Manual Supplement. (See Note 15)

NOTE 6 Equipment required to assure satisfactory engine/rotor drive system torsional stability 

(accumulators and doubler check valve) is approved and included as part of the Allison 

Model 250-C20R engine P/N 23059597.

NOTE 7 The engine air induction system and the oil cooler blowing inlet have been substantiated for 

icing, and falling and blowing snow characteristics, as necessary, to demonstrate that ice 

accumulation will not adversely affect engine operation, or cause a serious loss of power 

when the helicopter is operated in icing conditions within the capability of the remainder of 

the helicopter to operate under such conditions.

NOTE 8 Model 206L-4 helicopters equipped with an external cargo hook may operate to 4,550 

pounds gross weight in accordance with the limits of FAA approved Helicopter Flight Manual 

Supplement BHT-206L4-FMS-4, dated October 1992. The retirement times listed in Note 3 

are not changed.

NOTE 9 Model 206L-1 helicopters modified in accordance with this STC must be equipped with P/N 

206-011-149-101 or 206-011-149-105 main rotor yoke.

P/N 206-040-004-101 Transmission

P/N 206-040-014-101 Main Rotor Mast 

P/N 206-011-722-105 T/R Pitch Change Levers (2) 

P/N 206-010-792-101 or -105 Pitch Change Links (2) 

P/N 206-011-794-109 Pitch Change Shaft 

P/N 206-011-820-101 Washer (2)

P/N 206-011-810-125 Tail Rotor Hub 

P/N 206-011-809-107 Pitch Horns (2)

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 14 OF 15 PAGES
UnitedStatesofAmerica

DepartmentofTransportation -FederalAviationAdministration

SupplementalTypeCertificate

(Continuation Sheet)

Number SR00036SE

Soloy, LLC 

Issued: November 19, 1993

Reissued: January 23, 2014

Amended: 9/12/94; 10/20/95

Certification Basis Continued: NOTE 10 Bell 206L-1 helicopters modified in accordance with this STC will incorporate the following 

206L-3 T/R rigging requirements:

Mean blade angle, 23 1⁄4° to 23 3⁄4 ° (was 19° to 19 1⁄2 °) gap between control rod and 

bellcrank, .285” to .315” (was .17” to .23”) 

Refer to Tridair Helicopter Maintenance Manual Supplement Chapter 27 for complete rigging 

details.

NOTE 11 Bell 206L-3 helicopters modified in accordance with this STC must be modified and 

maintained in accordance with the applicable conditions of Bell Service Instruction 

BHT-206-SI-2039 increased power operation. 

NOTE 12 Single engine operation is permitted on converted Models 206L-1, 206L-3, and 206L-4 only. 

Refer to Tridair Single Engine Operation Rotorcraft Flight Manual Supplements Bell 206L-1 

RFMS-TH-6, Bell 206L-3 RFMS-TH-6, and Bell 206L-4 RFMS-TH-6 for complete operation 

procedures.

NOTE 13 Model 206L-3 S/N 51215 and subsequent, and Model 206L-4 S/N 52001 and subsequent are 

manufactured by Bell Helicopter Textron Inc., a Division of Textron Canada Limited, under 

the Canadian Department of Transportation, Manufacturer’s Approval No. 1-86. 

Import Requirement: U.S. Standard Airworthiness Certificate may be issued on the basis of 

the Canadian Department of Transport Certificate of Airworthiness for Export signed by the 

Minister of Transport containing the following statement: “The rotorcraft covered by this 

certificate has been examined, tested, and found to comply with the type design approved 

under Type Certificate H2SW and to be in condition for safe operation.”

NOTE 14 Upon completion of this modification, perform system calibration, functional tests ground 

tests, and flight tests in accordance with Tridair Document No. THI-206-604. 

NOTE 15 Tridair 206L-4 Rotorcraft Flight Manual Supplement No. BELL 206L-4 RFMS-TH-1, and Bell 

Helicopter 206L-4 Flight Manual No. BHT-206L4-FM-1, are superseded by Bell Helicopter 

206L-4T Flight Manual No. BHT-206L4T-FM-1.

NOTE 16 Tridair 206L-4 Rotorcraft Maintenance Manual Supplement No. THI-206L4-MM -1 thru THI206L4-MM-12, and Bell Helicopter 206L-4 Rotorcraft Maintenance Manual No. BHT-206L4-

MM-1 thru BHT-206L4-MM-12, are superseded by Bell Helicopter 206L-4T Maintenance 

Manual No. BHT-206L4T-MM-1 thru BHT-206L4T-MM-13

- END -

Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA FORM 8110-2 (10-68) PAGE 15 OF 15 PAGES