### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

Number SR00036SE

This certificate, issued to Soloy, LLC

450 Pat Kennedy Way S.W.

Olympia, WA 98501



## Certifies t hat 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 Page s 13 and 14 of this c ertificate for Certificati on 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 helic opters

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 thos e 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 F ORM 8110

- 2 (10

- 68) P AGE 1 OF 1 5 P AGES 

## By direction of the Administrator

__________________________________________ (Signature)

Manager, Sea ttle Aircraft Certification Office

(Title)

### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(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 206 L

- 4

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

certain unmodified ones which are listed for clarity.

Model: B ell 206L

- 4 modified by this supplemental type certificate (ST C ) (Normal Category Rot orcraft)

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 f uel mixture and fuel temperature limitati ons ( 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% (N 1 )

Max Continuous 89.6 PSI (370 SHP) 6016 752 ° C 105 % (N 1 )

Se e Roto r craft F light Manua l 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 th is 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 F ORM 8110

- 2 ( 10

- 68) P AGE 3 OF 1 5 PAGES

### United States of

America



# Departmen t

of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(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

B asic V NE is 130 KIAS sea level to 3,000 feet density altitude. Decrease V NE 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 L imit

(+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 F ORM 8110

- 2 ( 10

- 68) P AGE 4 OF 1 5 PAGES

### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(Continuation Sheet)



# Number SR00036SE

Soloy, LLC



## Issued: November 19, 1993



## Reissued: January 23, 2014



## Amended: 9/12/9 4; 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 Supple ment for

limitations ( See Note 15)

.

Maximum Cargo:

Refer to Bell Helicopter 206 L

- 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 f orward 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 tra nsferred in accordance with FAR 21.47.

FAA F ORM 8110

- 2 ( 10

- 68) P AGE 5 OF 1 5 P AGES

### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(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 lim itations 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 modifie d by this S TC (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 mix ture 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% (N 1 )

Max Continuous 89.6 PSI (370 SHP) 6016 752 ° C 105% (N 1 )

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% (4 50 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 bot h.

This certificate may be transferred in accordance with FAR 21.47.

FAA F ORM 8110

- 2 ( 10

- 68) P AGE 6 OF 15 P AGES

### United States o

f America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(Continuation Sheet)



# Number SR00036SE

Soloy, LLC



## Issued: November 19, 1993



## Reissued: January 23, 2014



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



## Limitations and Cond itions continued:

Model 206L

- 3 (Continued):

Airspeed Limits:

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

accordance with Airspeed Limitation Placard in the Bell Helicopter 206L

- 3 Rotorcraft Fl ight 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)

F orward 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 abo ve

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) (Externa l 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 exceedin g $1,000, or imprisonment not exceeding 3 years, or both.

This certificate may be transferred in accordance with FAR 21.47.

FAA F ORM 8110

- 2 ( 10

- 68) P AGE 7 OF 1 5 P AGES

### United States of

America



# Department of Transportation

- Federal Aviation Administrat ion 

# Supplemental Type Certificate

(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 (+6 5.0)

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 Eligibl e:

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 F ORM 8110

- 2 ( 10

- 68) P AGE 8 OF 1 5 P AGES

### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(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 whi ch are

listed for clarity.

Model: Bell 206L

- 1 modified by this S TC (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% (N 1 )

Max Continuous 89.6 PSI (370 SHP) 6016 752 ° C 105% (N 1 )

Se e Tridair 206L

- 1 Roto r craft 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 Read ing 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 F ORM 8110

- 2 ( 10

- 68) P AGE 9 OF 1 5 P AGES

### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(Continuation Sheet)



# Number SR00036SE

Soloy, LL C



## 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 V NE is 130 KIAS sea level to 3,000 feet density altitude. Decrease V NE for ambie nt conditions in

accordance with Airspeed Limitation Placa rd 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 F ORM 8110

- 2 ( 10

- 68) P AG E 1 0 OF 1 5 P AGES

### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(Continuation Sheet)



# Number SR00036SE

Soloy, LLC



## Issued: November 19, 1993



## Reissued: January 23, 2014



## Amended: 9/1 2/94; 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).

Leve ling 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 acc ordance with FAR 21.47.

FAA F ORM 8110

- 2 ( 10

- 68) P AGE 1 1 OF 1 5 P AGES

### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(Continuation Sheet)



# Number SR00036SE

Soloy, LLC



## Issued: Novem ber 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 : S ection 27.1545 at Amendment 27

- 8;

Section 27.1587 at Amendment 27

- 14 ; Secti on 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, 2 7.307, 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, Su bpa rt E, Subpart F Sections 27.1301

, 27.1305, 27.1307, 27.1309, 27.1321, 27.1337, 27.1351 through

27.136 7, 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 a t 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 Ex emption 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 equ ivalent 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 Septem ber 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, Sub part 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 F ORM 8110

- 2 (10

- 68) P AGE 1 2 OF 1 5 P AGES

### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(Continuation Sheet)



# Number SR00036SE

Soloy, LLC



## Issued: November 19, 1993



## Reissued: January 23, 2014



## Amended: 9/12/9 4; 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.

Exemptio n 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 f or 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 approv ed revision s (See N ote 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 appr opriate 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 Hel icopters 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 certifica te may be transferred in accordance with FAR 21.47.

FAA F ORM 8110

- 2 (10

- 68) P AGE 1 3 OF 1 5 P AGES

### United States of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(Continuation Sheet)



# Number SR00036 SE

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

Ma nual Supplement. (See Note 16)

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

(N R ) and engine output shaft (N 2 ) speed limits are shown in Sect ion 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 pa rt 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

accumulati on 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 remaind er of

the helicopter to operate under such conditions.

NOTE 8 Mode l 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.

NO TE 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 F ORM 8110

- 2 (10

- 68) P AGE 1 4 OF 15 P AGES

### United S

tates of

America



# Department of Transportation

- Federal Aviation Administration 

# Supplemental Type Certificate

(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” t o .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 ap plicable 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 Manua l 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 Transpor t 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 Certifica te 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 Ro torcraft 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 S upplement No. THI

- 206L4

- MM

- 1 thru THI

206L4

- 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 F ORM 8110

- 2 (10

- 68) P AGE 15 OF 15 P AGES