THRUSH TYPE CERTIFICATE DATA

TYPE CERTIFICATE DATA SHEET N EA-2006T02 Type Certificate Holder:

THRUSH AIRCRAFT, INC. P.O. Box 3149 Albany, GA 31706 USA

EA-2006T02-02 Sheet 01

THRUSH AIRCRAFT,

INC.

S2R-T660, S2R-T34, S2R-H80.

03 June 2013 This data sheet, which is part of Type Certificate No. 2006T02, prescribes conditions and limitations under which the product, for which the Type Certificate was issued, meets the airworthiness requirements of the Brazilian Aeronautical Regulations.

I Model S2R-T660 (Restricted Category Only)*, approved 23 August 2006. ENGINE United Aircraft of Canada PT6A-60 AG

Optional Engines: Pratt & Whitney Canada PT6A-65AG, -65B Pratt & Whitney Canada PT6A-67AG eligible on S/N T660-109 & up.

FUEL Jet A, Jet B, JP-4 and JP-5 (If jet fuel is not available, aviation gasoline, MIL-G-

5572, all grades, may be used for a maximum of 150 hours between overhauls).

OIL UACL PT6 Engine Service Bulletin Number 1001, 3001, 4001, 11001, 12002 and 13001

lists approved brands oil. ENGINE LIMITS PT6A-60AG

Takeoff Max. Cont.

Transient Reverse Idle Start Accel.

SHP 1 050 1 020 900 Torque (psi) (2sec) 38.8 37.7 61.0 Trans

ITT - oC 820 775 1 000 Start

(5 sec.) 850 760 750

Ng - ( % ) 104 104 104 104 58

Np (rpm) 1 700 1 700 1870 Trans

(5 sec.) 1 650

Oil Press (Psig) 90 to 135 90 to 135 0 to 200 40 to 200 90 to 135 60 Min. Oil Temp - oC 0 to 110 0 to 110 -40 Min. 0 to 110 0 to 99 -40 to 110

The ratings shown are based on the static sea level standard condition with no external accessory loads and no air bleed.

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ENGINE LIMITS PT6A-65AG/ -65B (Cont.)

Takeoff Max. Cont.

Transient

Reverse Idle Start Accel. SHP 1 300 1 220 900 Torque (psi) (2sec) 48.0 45.1 61 Trans ITT - oC 810 810 1 000 850 Start(5s) 760 750 Ng ( % ) 104 104 104 56 Np (RPM) 1 700 1 700 1 870 Trans(5s) 1 650

Oil Press (Psig) 90 to 135 90 to 135 0 to 200 40 to 200 90 to 135 60 min. Oil Temp - oC 0 to 110 0 to 110 -40 min. -40 to 110 0 to 110 -40 to 110


PT6A-67AG

TakeoffMax. Cont.

Transient Reverse IdleStart Accel.

SHP 1300 1220 900 Torque (psi) (2sec) 48.0 45.1 61 Trans ITT - C 800 800 1000 850 760 750 Ng ( % ) 104 104 104 104 51 Np (RPM) 1700 1700 1870 1650 Oil Press (Psig) 90 to 135 90 to 135 0 to 200 40 to 200 90 to 135 60 min Oil Temp - C 0 to 110 0 to 110 -40 min 0 to 110 10 to 105 -40 to 110


PROPELLER AND PROPELLER LIMITS

PT6A-60AG: Hartzell HC-B5MP-3C propeller, constant speed, feathering and reversing Hub Model HC-B5MP-3C Blade Model M10876ANS or M10876AS. Diameter 2.819m (111.2 in) max., 2.811m (110.7in) min. Pitch (42 in. Sta.) 16.5 low, 79.0 feather, -11.0 reverse

PT6A-65AG, -65B: Hartzell HC-B5MP-3F propeller, constant speed, feathering and reversing Hub Model HC-B5MP-3F Blade Model M11276NS Diameter 2.926m (115.2in) max., 2.913m (114.7 in) min. Pitch (42 in. Sta.) 13.9 low, 83.1 feather, -10.0 reverse

PT6A-67AG: Hartzell HC-B5MA-3D propeller, constant speed, feathering and reversing Hub Model HC-B5MA-3D Blade Model M11276NS. Diameter 2.926m (115.2in) max., 2.913m (114.7 in) min.

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Pitch (42 in. Sta.) 13.9 low, 83.1 feather, -10.0 reverse CERTIFICATION BASIS - FAR 21.25;

- RBHA 23, which endorses the FAR 23 effective 01 February 1965: - RBHA/FAR subpart A, amendment 23-53; - RBHA/FAR subpart B, amendment 23-53; - RBHA/FAR subpart C, amendment 23-53 except 23.423, 23.425,

23.427, 23.441; - RBHA/FAR 23.443, and 23.455 at amendment 23-34; - RBHA/FAR subpart D, Amendment 23-53 except 23.607 at

amendment 23-34; - RBHA/FAR 23.629 at Amendment 23-31 and RBHA/FAR 23.785,

23.807, 23.853, 23.863; - RBHA/FAR 23.865 and 23.867 at Amendment 23-14; - RBHA/FAR Subpart E, Amendment 23-14; - RBHA/FAR Subpart F, Amendment 23-0; - RBHA/FAR Subpart G, Amendment 23-53;

except those regulations found inappropriate for restrict category agricultural airplanes as listed in FAA Advisory Circular 21.25-1, dated 01 December 1997, and compliance with regulations listed in ACE-110 policy memorandum, dated 01 December 1997, demonstrated in accordance with that memorandum.

AIRSPEED VNE (Never Exceed) 191 kt LIMITS (CAS) VP (Maneuvering) 140 kt VNO (Max. Structural

Cruising) 180 kt

VFE (Flap Extended) 126 kt C. G. RANGE Forward limit at 12 500 lb. Is 24 inches aft of datum with straight line

variation to 8 000 lb. At 27 inches aft of datum. Forward limit below 8 000 pounds is 27 inches aft of datum. Aft limit at 12 500 lb. Is 27 inches aft of datum with straight line variation to 8 000 lb. At 30 inches aft of datum. Aft limit below 8 000 lb. Is +30.0 inches aft of datum. Datum is the leading edge of the wing.

MAXIMUM TAKE OFF WEIGHT

12 500 lb.

MAXIMUM LANDING WEIGHT 12.500 lb. MAXIMUM EMPTY WEIGHT 6 100 lb. MAXIMUM OPERATING ALTITUDE 12 000 ft. NUMBER OF SEATS 1 (+89)* MAXIMUM CARGO LOAD Maximum baggage compartment 200 lb. (+112)*

Maximum hopper load, 5 500 lb. (+20.6)* * Distance from CG (inches)

FUEL CAPACITY 225.6 gallons usable, one 115 gallons tank in each wing, tanks interconnected. See NOTE 1 for data on unusable fuel.

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OIL CAPACITY 10 US quarts - usable oil tank capacity 6 quarts. CONTROL SURFACE MOVEMENTS

Elevator Elevator Tab Rudder S/N T660-109 and up Aileron Flaps

Up 27 1 Up 8 1 Left 19 1 Left 22 1 Up 21 1

Down 17 1 Down 22 1 Right 19 1 Right 22 1 Down 17 1 Down 15 1

SERIAL NUMBERS ELIGIBLE

T660-101 and subsequent

REQUIRED EQUIPMENT The basic required equipment as prescribed in the applicable

airworthiness regulations (see certification basis) must be installed in the aircraft for certification. This equipment must include Ayres Corporation Airplane Flight Manual approved 13 March 2000, or later approved version. For S/N T660-109 and up, Thrush Aircraft Inc. Airplane Flight Manual dated March 5, 2004 or later FAA approved revision, is required.

AGRICULTURAL DISPERSAL EQUIPMENT

Standard Spray, Ayres Dwg. No. 95340 Spreader Installation, Ayres Dwg. No. 95370 Transland Hydraulic Fire Door Installation, Ayres Dwg. No. 95385

STRUCTURAL LIMITATIONS

The following parts must be replaced at the times in service indicated: Part Name Rear Spar Doubler, Lower Rear Spar, Inboard, L&R Aft Main Spair Lug, L&R Forward Main Spar Lug, L&E Spar Cap Assy, L&R Steel Doubler Plate

Part Number 95627-3 95623-1/-2 95605-1/-2 95606-1/-2 95603-1/-2 95614-1

Life Limit 20 000 20 000 21 750 20 000 26 625 38 400

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II MODEL S2R-T34 (RESTRICTED CATEGORY ONLY)*, APPROVED 20 JULY 2011. See Note 8 for two-place configuration. See Notes 9 and 10 for options. See Note 7 for life limited parts. ENGINE Pratt & Whitney (United Aircraft of) Canada PT6A-34AG

Optional Engines: Pratt & Whitney Canada PT6A-34 (See NOTE 11). FUEL Jet A, Jet B, JP-4 and JP-5. (If jet fuel is not available, aviation gasoline,

MIL-G-5572, all grades, may be used for a maximum of 150 hours between overhauls.)

OIL UACL PT6 Engine Service Bulletin Number 1001 lists approved brands oil.

ENGINE LIMITS PT6A-34AG/-34: Takeoff and

Max. Cont. Transient Start / Accel. Reverse Idle

SHP 750 Torque (psi) 64.5 68.4 Trans (2sec.) 64.5 ITT - oC 790 1090 Start (2sec.) 790 Ng - ( % ) 101.5 102.6 Trans (2sec.) 101.5 Np (rpm) 2200 2420 Trans (2 sec.) 2100 Oil Press (Psig)

Oil Temp - oC 85 to 105 10 to 99

85 to 105 -40 minimum

85 to 105 0 to 99

40 min. -40 to 99



Hartzell Hub Model HC-B3TN-3C (or HC-B3TN-3D) with Blade Model T-10282, Diameter 102.5 inches maximum, 92.5 inches minimum or optional Blade Model T-10282(N)+4, Diameter 106 inches maximum, 98 inches minimum (See NOTE 12)

AIRSPEED VNE (Never Exceed) 159 mph (138 knots) LIMITS (CAS) VP (Maneuvering) 126 mph (109 knots) VNO (Max.Struct. Cruising) 126 mph (109 knots) VFE (Flap Extended) 123 mph (107 knots)

C. G. RANGE (See NOTE 8 for two-place)

Forward limit at 6,000 lbs., +26.5 inches aft of datum. Forward limit at 4,000 lbs., and below +24.0 inches aft of datum. (Straight line variation in the forward limit between 4,000 and 6,000 lbs.) Aft limit +30.0 inches aft of datum. Datum is the leading edge of the wing.

MAXIMUM WEIGHT

6,000 lbs.

MAXIMUM OPERATING ALTITUDE

12,000 feet

NUMBER OF SEATS

1 (+89) (see NOTE 8)

MAXIMUM CARGO LOAD

See weight and balance data. Maximum baggage compartment, 60 lbs. (+112). (See NOTE 8). Maximum hopper load, 3336 lbs. (+29.9). (See NOTE 13)

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FUEL CAPACITY

104 gallons usable, one 53 gallon tank in each wing, tanks interconnected. See NOTE 1 for data on unusable fuel. Also see NOTE 6.

OIL TANK CAPACITY

11 U.S. quarts - usable oil tank capacity 6 quarts.

CONTROL SURFACE MOVEMENTS

Elevator Up 27+ 1 Elevator Tab Up 13 + 1 Rudder Left 24 + 1 Aileron Up 21 + 1

Down 17 + 1 Down 18 + 1 Right 24 + 1 Down 17 + 1 Flaps Down 15+ 1

SERIAL NUMBERS ELIGIBLE

6000 6049 T34-001 and subsequent.

REQUIRED EQUIPMENT

The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in the aircraft for certification. This equipment must include Ayres Corporation Airplane Flight Manual approved June 23, 1978, and Supplement for Restricted Category Operation approved June 23, 1978, or later approved versions.

AGRICULTURAL DISPERSAL

See NOTE 15 for dispersal systems. CAUTION: For operation with the Micronair Spray Equipment System or the Fire Bomber System, or with any system when an Agavenco pump is installed, the placards for airspeed limitations referred to in NOTE 14(c), 14(a), or 14(b), respectively, for the S2R are applicable.

Model S2R-H80 (Restricted Category Only)*, approved 03 June 2013. ENGINE GE Aviation Czech H80-100. FUEL Jet A per ASTM D1655,

Jet A-1 per ASTM D1655.

OIL Aero Shell Turbine Oil 500 per MIL-L-23699C Aero Shell Turbine Oil 560 per MIL-L-23699C Mobile Jet Oil II per MIL-L-23699C Synthetic oil B3V per TJU 38 101295 85 BPTO 2380 Castrol 599 Royco Turbine Oil Oil purity should be maximum grade 8 in accordance with NAS 1638 standard or maximum grade 11 in accordance with GHOST 17216-71 standard.

ENGINE LIMITS H80-100:

Takeoff (5 min limit)

Max. Cont.

Transient* Reverse IdleStart Accel.

SHP 800 800 Torque

(psi) 100 100 106*

ITT - C 780 750 730 780 710 550 Ng ( % ) 101.5 100.1 102.5* 96 57-60 Np (RPM) 2080 2080 2140* 1900 Oil Press

(Psig) 26 to 39 26 to 39 26 to 39 26 to 39 26 to 39 18 min

Oil Temp C 20 to 85 20 to 85 -20 to 85 20 to 85 20 to 85 20 to 85

*Short term overshoot

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Hartzell HC-B4TW-3/T10282N(S) propeller, constant speed, feathering and reversing; Hub Model HC-B4TW-3 with Blade Model T10282N or T10282NS. Diameter 103 inches maximum, 102 inches minimum. Pitch (30 in. Sta.) 11.0 low, 87.0 feather, -8.0 reverse. Stabilized ground operation is prohibited between 400 & 1100 RPM. Propeller may be operated when feathered at or below 400 RPM.

AIRSPEED LIMITS (IAS) VNE (Never Exceed) 187 mph (162 knots) VP (Maneuvering) 158 mph (137 knots) VNO (Max.Struct. Cruising) 165 mph (143 knots) Vfe (Flap Extended) 157 mph (136 knots) C. G. RANGE Forward Limit at 10,500 lbs. is 28.0 inches aft of datum with straight line

variation to 6,000 lbs. at 25 inches aft of datum. Forward Limit below 6,000 pounds is 25 inches aft of datum. Aft Limit at 10,500 lbs. is 30.5 inches aft of datum with straight line variation to 7,600 lbs. at 31 inches aft of datum. Aft Limit below 7,600 lbs. is +31.0 inches aft of datum. Datum is the leading edge of the wing.

MAXIMUM TAKEOFF WEIGHT

10,500 lbs.

MAXIMUM LANDING WEIGHT

7,600 lbs.

MINIMUM WEIGHT 4,500 lbs. MAXIMUM OPERATING ALTITUDE

12,000 feet

NUMBER OF SEATS 1 (+89) MAXIMUM CARGO LOAD

See weight and balance data. Maximum nose baggage compartment load is 100 lbs.(-14.0). Maximum hopper load is 4,000 lbs.(+29.9).

FUEL CAPACITY 228 gallons usable, one 115 gallon tank in each wing, tanks

interconnected. See NOTE 1 for data on unusable fuel. OIL TANK CAPACITY 11.6 U.S. quarts - usable oil tank capacity 7.4 quarts. CONTROL SURFACE MOVEMENTS Elevator Up 27 1 Down 17 1 Elevator Tab Up 8 1 Down 22 1 Rudder Left 24 1 Right 24 1 Aileron Up 21 1 Down 17 1 Flaps Down 15 1 SERIAL NUMBERS ELIGIBLE

H80-101 and subsequent.

REQUIRED EQUIPMENT

The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in the aircraft for certification. This equipment must include Thrush Aircraft, Inc. Airplane Flight Manual

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REQUIRED EQUIPMENT (CONT)

approved October 9, 2012, or later FAA approved revision.

AGRICULTURAL DISPERSAL EQUIPMENT

Standard Spray System, Thrush Dwg. No. 81071.

STRUCTURAL LIMITATIONS The following parts must be replaced at the times in service indicated: Part Name Part Number Life Limit Wing Lower Spar Cap Assy, L & R 22507T001/T002 60000 Wing Lower Spar Splice Block 22508T001/T002 10000 See Thrush Maintenance Manual H80-1MM airworthiness limitations

section. CERTIFICATION BASIS Brazilian Type Certificate No. 2006T02 Amendment, for inclusion of

S2R-H80 aircraft model, issued on 03 June 2013 based on the RBAC 21.29 and RBAC 23, which endorses the 14 CFR Part 23.

Based on the Model S2R-H80 FAA application date of July 8, 2010, under the provisions of 21.101, the applicable type certification standards for the Model S2R-H80 are as follows: CAR 8 is not part of the certification basis for the S2R-H80. 1) Airworthiness & Environmental Standards for components and areas not affected by the change: RBAC / 14 CFR 21.25(a)(1) for the special purposes of agricultural

aircraft operations, as defined in RBAC / 14 CFR Part 137.3, and aerial dispensing of liquids or other materials for fires.

Civil Air Regulations (CAR) 3, effective May 15, 1956, including Amendments 3-1 through 3-8.

RBAC / 14 CFR Part 23, Subpart C, effective February 1, 1965, Amendments 23-1 through 23-34, only Subpart C regulations

2) Airworthiness and Environmental Standards for components and areas affected by the change: RBAC / 14 CFR 21.25(a)(1), 21.101. Civil Air Regulations (CAR) 3, effective May 15, 1956, including

Amendments 3-1 through 3-8 unless superseded by a later regulation that is specifically listed in this section 2.

RBAC / 14 CFR Part 23, Subpart C, effective February 1, 1965, Amendments 23-1 through 23-34, only Subpart C regulations.

RBAC / 14 CFR Part 23, Subpart G, effective February 1, 1965, Amendments 23-1 through 23-59, only Subpart G regulations.

RBAC / 14 CFR part 23, effective February 1, 1965, Regulations and Amendments as listed below (Note: Dash number in parentheses is amendment level):

23.33 (-50) 23.49 (-50) * 23.65(c) (-21) 23.75 (-7) 23.77(b) (-21) 23.147(c) (-50) 23.173 (-14) 23.175 (-14) 23.177 (-0)

23.905 (-0) 23.907 (-51) 23.929 (-14) 23.933 (-39) 23.937 (-43) 23.939 (-42) 23.943 (-43) 23.951 (-15) 23.954 (-7) *

23.1015 (-15) 23.1017 (-14) 23.1019 (-15) 23.1021 (-43) 23.1027 (-14) 23.1041 (-7) 23.1043 (-7) 23.1045 (-51) 23.1091 (-51)

23.1165 (-34) 23.1181 (-51) 23.1182 (-14) 23.1183 (-51) 23.1191 (-51) 23.1303 (-0) 23.1305 (-52) 23.1308 (-57) 23.1309 (-49)

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23.201 (-50) 23.203 (-50) 23.562 (-50) * 23.629(a)-(e) only (-31) 23.831 (-0) 23.851 (-45) 23.901 (-53) 23.903 (-29)

23.955 (-7) 23.959 (-7) 23.961 (-0) 23.977 (-17) 23.979 (-51) 23.991 (-7) 23.993 (-43) 23.997 (-15) 23.1013 (-15)

23.1093 (-51) * 23.1103 (-43) 23.1107 (-51) 23.1121 (-7) 23.1141 (-51) 23.1143 (-51) 23.1145 (-43) 23.1155 (-7) 23.1163 (-42)

23.1311 (-49) 23.1321 (-49) 23.1322 (-43) 23.1323 (-7) 23.1331 (-43) 23.1337 (-51) 23.1351 (-49) 23.1353 (-49)

*Compliance with the regulation was demonstrated in accordance with ACE-110 policy memorandum, dated December 1, 1997. Unless listed in the table above, compliance with the RBAC / 14 CFR Part 23 regulations listed in FAA Advisory Circular 21.25-1, dated December 1, 1997, Appendix 1, has not been shown and is not required. The Administrator finds these regulations to be inappropriate for restricted category agricultural airplanes as allowed by RBAC / 14 CFR 21.25(a)(1). Equivalent Level of Safety Finding (ELOS) No. ACE-04-05 to RBAC / 14 CFR 23.473(b), dated July 26, 2004, for a landing weight of 7,600 lbs. RBAC / 14 CFR Part 36.1(a)(2) aircraft noise measurement is not required for the S2R-H80 approved special purposes of agricultural aircraft operations, as defined in 14 CFR Part 137.3, or for aerial dispensing of liquids or other materials for fires. Approved for Day-Night VFR operations only.

DATA PERTINENT TO ALL MODELS:

CERTIFICATION BASIS For all models, except S2R-T660 and S2R-H80.

CAR 8 effective October 11, 1950, restricted category.

DATUM Wing leading edge LEVELING MEANS Lower longeron below cockpit. IMPORT ELIGIBILITY A Brazilian Airworthiness Certificate may be issued on the basis of a Export

Certificate of Airworthiness signed by a representative of a local export Civil Aviation Authority containing the following statement: "The airplane covered by this certificate bas been examined, tested and found to conform to the type design approved under ANAC Type Certificate No. 2006T02, and to be in condition for safe operation".

PRODUCTION BASIS Production Certificate Number 5SO.

EMPTY WEIGHT C.G. RANGE None. NUMBER OF PASSENGERS None. NOTES: NOTE 1 Weight and balance: current weight and balance report including list of equipment included in

certificated empty weight, and loading instructions must be provided for each aircraft at the time of original certification and at all times thereafter. The empty weight and corresponding center of gravity location must include the following unusable fuel:

Models S2R-T34 and S2R-H80 all serial numbers

8.16 kg (18 lb) at +97.79 cm (+38.5 in)

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Models S2R-T660 11.97 kg (26.4 lb) at +97.79 cm (+38.5 in) 13.61 kg (30.0 lb) at +97.79 cm (+38.5 in)

NOTE 2

All required placards listed in the limitations Section of the Airplane Flight Manual must be installed in the appropriate locations. All markings and placards for passenger information, external markings for emergency, and load limits in cargo/baggage compartments must be presented in Portuguese or bilingual. For the approved markings and placards translations contact the TC holder or STC holder (as applicable) and/or ANAC at the following address: [email protected].

NOTE 3 Continuing of Airworthiness: Service Bulletins, structural repair manuals, and aircraft flight

manuals which contain a statement that the document is FAA approved are accepted by the ANAC and are considered ANAC approved. These approvals pertain to the type design only. Compliance with the tasks and intervals specified in the "Airworthiness Limitations Section", section of the Maintenance Program listed in Approved Publications, is required to ensure continuing compliance with the type certification basis. Components which are life limited are also listed in the "Airworthiness Limitations Section.

NOTE 4 The ANAC approved type design corresponds to the FAA approved type design plus the

following specific requirements: 1. FAA Approved Brazilian AFM: 2. Markings and placards in Portuguese or bilingual; 3. The international System of units, in accordance with ICAO Annex 5 must be used.

a. Oil quantity - must be in liters and followed by the correspondent amount in gallons, between brackets;

b. Dimensions - must be in meters; c. Weight or mass - must be kilograms; d. Fuel quantity - must be in liters; e. Temperatures - must be in degrees C; f. Altimeter set - must be in millibar or hPa;

4. The weight and balance sheet must be consistent with the modifications required by item 3

above. 5. Night VFR operations are permitted when the airplane is appropriately equipped per RBAC

91.205(c). 6. The use of JP4, JetB as well as AVGAS can only be done having the emergency fuel

pump turned on. ANAC requires the above to be stated in the AFM. 7. Automotive fuels are not approved for aeronautical use.

NOTE 5

The following models and serial numbers have been or are currently produced by Thrush Aircraft, Inc. (originally Ayres Corp.) at its Albany, Georgia, facility. (earlier serial numbers, not listed below, were manufactured prior to July 2003 by Ayres Corp.): Model S2R-T660, S/N T660-109 and up, Model S2R-T34 S/N T34-273 and up.

NOTE 6 The following table summarizes increased fuel capacity limits for the models and serial numbers

listed: Configuration* Model

A. S/N B. S/N

S2R-T34 T34-034 and up T34-080 and up *Configuration: A. Eligible for optional installation -190 gallons usable, one 96 gallon tank in each wing, tanks interconnected; B. Eligible for optional installation -228 gallons usable, one 115 gallon tank in each wing, tanks interconnected.

NOTE 7 Lower Spar Caps, P/Ns 22507T001 and 22507T002, are life limited and must be replaced at 29,000 hours time in service. These P/Ns are installed as original equipment on the following serial numbers:

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T34/41-271 and up.

NOTE 8

For Models S2R-T34 and S2R-T660 with the serial number suffixed with "DC" (Dual Cockpit), the following data apply. All other data listed for these models remain unchanged. Model S2R-T34 Dual Cockpit, 2PCLM C.G. Range (+22.5) to (+27.5) without P/N 19661-1 (elevator down spring) installed. (+22.5) to (+30.0) with P/N 19661-1 (elevator down spring) installed. Number of Seats 1 (+89), 1 (+127 Forward Facing) or (+111 Aft Facing) Maximum Cargo Load Passenger/Cargo compartment, 200 lbs. (+120). Maximum hopper load, 3336 lbs. (+29.9). (See NOTE 13) Control Surface Movements Elevator Tab 8 + 1 up; 22 + 1 down Serial Numbers Eligible T34-033DC and subsequent. Required Equipment This equipment must include Airplane Flight Manual and Supplement for Restricted Category Operation, dated August 25, 1980, or later approved versions. Model S2R-T660 Dual Cockpit, 2PCLM Engine Pratt & Whitney Canada PT6A-65AG, -65B Optional Engine: Pratt & Whitney Canada PT6A-67AG

NOTE 9

For Model S2R-T34, equipped with optional Air Inlet Barrier Filter, P/N 21402, refer to the Airplane Flight Manual Supplement approved February 4, 1991, or later approved revision, for limitations and procedures.

NOTE 10

External pitot type engine air inlet, P/N's 21900-1 and 21900-21, or screened fairing panel, P/N 21922, are approved optional equipment on the following models: Model S/N S2R-T34 T34-150 and up

NOTE 11 NOTE 12

The Pratt & Whitney (United Aircraft of) Canada PT6A-34 engine is approved as an optional engine on Model S2R-T34, S/N T34-084 and up, when installed in accordance with Ayres Dwg. 19870 with the following additions: A. Bleed Air Case Assy. P/N 3029769; Ref. Pratt & Whitney Service Bulletins 1278 & 1279. B. P-3 Air Filter Installation, Ref. Pratt & Whitney Service Bulletins 1253 & 3106. C. Replacement of Compressor Delivery Heated Air Tube by a non-metallic hose, P/N 3026687; Ref. Pratt & Whitney Service Bulletin 1315. Due to the anticipated operating environment, servicing and overhaul interval shall be in accordance with Pratt & Whitney's recommendations for the PT6A-34AG engine. Propeller Pitch Limits Hartzell HC-B3TN-3C and -3D with T10282N+4 blades at 30 inch station: Reverse -8.00.5, Low 18.00.1, Feather 87.01.0 Hartzell HC-B3TN-3C with T10282N blades at 30 inch station: Reverse -11.01.0, Low 16.00.1, Feather 89.01.0 Hartzell HC-B5MP-3C with M10876ANS or M10876AS blades at 42 inch station: Reverse -11.00.5, Low 11.50.1, Feather 79.00.5

NOTE 13

The following table summarizes models and serial numbers eligible for increased hopper load limits - Restricted Category operation only. The certificated maximum take-off gross weight of 6000 pounds applies to these models and serial numbers. Hopper Load Limit 4000 lbs. Model S/N S2R-T34 T34-082 and up

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THRUSH TYPE CERTIFICATE DATA