STC SA6088NM

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA6088NM This certificate issued to: Kelowna Flightcraft Ltd.

4401 Saint George Drive Oklahoma City, Oklahoma 73120 Part *Ab of the Bivil Sir Pegulations.

*(See Page 7 of this STC for the Certification Basis) Original Product Type Certificate Number: 6A6 Make: General Dynamics/Convair Model: 340/440 Description of Type Design Change: Conversion of the 6A6 Type Certificated Aircraft into a Model CV 5800 by installation of Allison 501-D22G Engines per STC SA4-1100, Hamilton Standard Propellers per STC SA1825NM and lengthening the fuselage 14 ft. 3.0 inches with all design changes in accordance with Model CV 5800 FAA Sealed Master Drawing List KF580-00000002, Revision No. 44, dated August 4, 1995, or later FAA approved revisions. The Kelowna Flightcraft FAA Approved Airplane Flight Manual Document No. CV 5800, dated December 14, 1993, or later FAA approved revision is required.

Limitations and Conditions: The limitations and conditions are outlined on pages 3 to 12 of this STC.

Applicable to: Model 340, 440, C131E, C131F Propellers - Hamilton Standard 54H60-164

suspended, revoked or a termination date is otherwise established by the Administrator of the Federal Aviation Administration.

Date of Application: July 12, 1984 Date Reissued: December 14, 1993;

Date of Issuance: December 14, 1993 March 2, 2009 FEDERAL AVIATION Date Amended: August 18, 1995 TOMINISTRATO (Signature) Manager, Airframe Branch Los Angeles Aircraft Certification Office

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM Limitations and Conditions:

General Dynamics/Convair 340 or 440 (C131E/C131F) as modified by this STC (CV 5800 configuration) - See Note 6.

Engines Two Allison 501-D22G Fuel Allison Specification EMS-64 (kerosene), ASTM-D-1655 Jet A, Jet A-1 or Jet B, or MIL-T-5624 Grade JP-4. See Note 3 concerning additives, intermixing of fuels and emergency use of aviation gasoline.

Engine ratings Takeoff (5 min.)

Equivalent shaft horsepower 4,593 Shaft horsepower 4,300 Jet thrust (Ibs) 734 Maximum continuous Equivalent shaft horsepower 4,232 Shaft horsepower 3,950 Jet thrust (Ibs) 703 The above ratings are based on static sea level conditions, dry air, 15°C, 29.92 in.

Hg, no external accessory loads, and no air bleed.

Engine limits Power As measured by the torquemeter at maximum rpm:

Takeoff 4,300 shp.

Maximum continuous 3,950 shp.

RPM 13,820 rpm. for all operations (which corresponds to 1,020 propeller rpm).

Turbine inlet Takeoff (5 min.) 1077°C temperature Maximum continuous 1010°C Transient (5 sec.) 1175°C Oil grade Allison Specification EMS-53 Oil inlet Maximum temperature At or below flight idle 100°C Above flight idle for 5 min. 100°C All other operations 85°C Minimum -40°C

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM Propeller and Two Hamilton Standard 54H60-164/A7121 B-2 installed in accordance with propeller STC SA1825NM limits The Hamilton Standard Propeller Model No. 54H60-164 is identical to the Hamilton Standard Propeller Model No. 54H60-77 except for the flight idle (mechanical low pitch stop) which for the 54H60-164 is set at 16.5° + 0.5°.

Refer to the STC SA1825NM for all other installation limitations.

Electrical Systems Maximum load for take-off, climb, approach, and landing.

Two Engine Operation (Each Engine) AC - 5 KVA DC - 110 AMPS (29 percent) Single Engine Operation AC - 10 KVA DC - 215 AMPS (57 percent) Other Pertinent Data Airspeed limits Maximum operating ( MO) Sea level 278 knots (320 mph) IAS 10,000 Ft. 280 knots (322 mph) IAS Reduce 'MO 5 knots per 1,000 ft. above 10,000 ft.

MMO =0.506 Maneuvering (A) and gust penetration ( B)

- See FAA Approved Airplane Flight Manual Flaps extended ('FE) 5° 214 knots (246 mph) IAS 10° 199 knots (229 mph) IAS 15° 187 knots (215 mph) IAS 20° 172 knots (198 mph) IAS 25° 165 knots (190 mph) IAS 30° to 33° 157 knots (181 mph) IAS

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM Landing gear retraction 146 knots (167 mph) IAS ( LO) Landing gear extension 173 knots (200 mph) IAS (LE) Landing light extension, retraction, and extended 200 knots (230 mph) IAS C.G. Range Forward Aft Gross Wt. (Ibs.) • MAC Sta % MAC Sta Landing gear 39,500 or less 8.5 455.6 35 485.9 retracted 63,000 20.5 469.3 35 485.9 Landing gear 39,500 or less 13.0 460.8 34 484.8 extended 63,000 23.3 472.5 34 484.8 Straight line variation between points given.

Datum Same as shown on Aircraft Specification 6A6.

MAC Same as shown on Aircraft Specification 6A6 (114.3 inches).

LE of MAC STA. 445.9 Leveling Same as shown on Aircraft Specification 6A6.

means Maximum weight Takeoff 63,000 lbs.

Landing 58,000 Ibs.

Zero Fuel 55,000 Ibs.

All weight in excess of zero fuel must consist of fuel and oil.

Minimum crew Same as shown on Aircraft Specification 6A6 (pilot + copilot).

Maximum baggage Same as shown on Aircraft Specification 6A6.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM Fuel capacity 1730 U.S. Gallons (6549 Liters), (one 865 U.S. Gallon (3274.5 Liter) tank in each wing at Sta. 492), or * 2032 U.S. Gallons (7692 Liters) (see STC SA4-1242), or * 2058 U. S. Gallons (7790 Liters) (see STC SA4-1114), or * 2908 U.S. Gallons (11008 Liters) (see STC SA4-1249) * See Note 4 (See Note 1 for system fuel) Oil capacity 16.8 U.S. Gallons (63.6 Liters), at Sta. 364.6 (see Note 1 for system oil). Total oil including system oil equals 130 1b (59.0 kg).

Maximum operating 25,000 feet altitude Control surface Same as shown on Aircraft Specification 6A6.

movements Serial numbers 2 and up eligible Applicability/ 1. This STC is a "no passenger and no cargo STC". To obtain the Limitation passenger or cargo configurations, subsequent FAA approved STCs must be installed.

2. The approval of this change in type design is limited to the Basic 340/440 commercial airplanes and the C131E and C131F military versions based on the approved Master Drawing List KF 580-00000002 Rev. 44. Additional military models of the Basic 340/440 will become eligible when subsequent FAA approved Master Drawing Lists incorporating the new designs are submitted.

This change in type design assumes the basic airplanes are otherwise unmodified. This approval should not be extended to other airplanes of these models on which other previously approved modifications are incorporated unless it is determined that the interrelationship between this change and any of those previously approved modifications will introduce no adverse effect upon the airworthiness of those airplanes.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM Certification Part 4b of the Civil Air Regulations effective July 20, 1950, with basis Amendments 4b-1, 4b-3, and 4b-5 thereto Special Civil Air Regulation No. SR-422B, Special Civil Air Regulation No. SR-423, FAR No. 34, FAR No. 36, and Special Condition No. 25-ANM-57 for HIRF and Lightning.

The military to commercial substantiation of the C-131F per GDC-272-0/80-1283 must be accomplished.

Production None. Before an airplane modified in accordance with the provisions basis of this Supplemental Type Certificate is returned to service, a check of flight characteristics must be accomplished by a representative of the FAA.

Export Airplanes modified in accordance with this Supplemental Type eligibility Certificate are eligible for issuance of Export Certificates of Airworthiness under the policies and procedures specified in Chapter 5 of Order 8130.2B, "Airworthiness Certification of Aircraft and Related Approvals".

Equipment The basic required equipment as prescribed in the applicable airworthiness regulations must be installed in the airplane for certification. See Page 10.

An FAA Approved Airplane Flight Manual for the CV 5800 must be NOTES Note 1. A current weight and balance report, including a list of equipment included in the certificate weight empty and, when necessary, loading instructions, must be in each airplane at the time of return to service after modification and at all times thereafter except in the case of operators having an approved weight control system.

The certificated empty weight and corresponding center of gravity locations must include the following:

(a) System oil - 86.8 1b (39.4 kg) at Sta. 356

(b) System fuel - 57.6 1b (26.1 kg) at Sta. 486* * Applies to basic 1730 U.S. Gallons (6549 Liters) capacity configuration.

See appropriate fuel tank modification STC for data on other tank configurations.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM Note 2. The following placard must be displayed in front of and in clear view of the pilot:

'This airplane shall be operated in compliance with the Operating Limitations specified in the FAA Approved Airplane Flight Manual".

Note 3. (a) Aviation gasoline, MIL-G-5572 Grade 115/145 or lower, is approved for limited emergency use. The use of Grade 80/87 (now Grade 80) gasoline is limited to the amount required to operate the engine for 1,000 hours during any overhaul period. The use of grades higher than 80/87 is limited to the amount required to operate the engine for 100 hours during any overhaul period. The average fuel consumption rate may be used to convert the allowable engine operating time to an equivalent gallonage to facilitate record keeping. Gasoline containing tricresyl phosphate, boron, or similar additives shall not be used.

(b) All approved fuels may be used separately or mixed in any proportion without adversely affecting engine operation or power output. No fuel control adjustment or system purging is required when switching fuel types.

(c) Anti-icing additives conforming to MIL-F-27686 may be used in fuels in amounts not to exceed 0.15% by volume.

(d) Shell ASA-3 antistatic additive may be used in a concentration providing no more than 300 conductivity units, which is equivalent to one ppm.

(e) Biocidal fuel additive, Biobor JF, may be used periodically in concentrations that do not exceed 270 ppm. Use of fuel with this additive is limited to one fueling within each engine inspection period specified in the 501-D22 Engine Maintenance Manual.

Note 4. A placard must be installed at or near refueling ports to indicate fuel quantity in both U.S. Gallons and Liters for each of the following:

STC SA4-1242- 2032 U.S. Gallons (7692 Liters) STC SA4-1114- 2058 U.S. Gallons (7790 Liters) STC SA4-1249- 2908 U.S. Gallons (11008 Liters)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM Note 5. In flight use of an auxiliary power unit not installed per this STC is prohibited.

Note 6. Airplanes modified in accordance with this Supplemental Type Certificate are frequently referred to unofficially as CV 5800; however, for official record purposes, these airplanes retain their original Model 340 or 440 identity.

II - Equipment: The basic required equipment as described by applicable Airworthiness Regulations must be installed.

Description of Major Components Weight ARM 1 Propellers

(2) Hamilton Standard 2379.8 307.42 Propellers 59H60-164/A7121 B-2 including spinner 100 Engines

(2) Allison 501-D22G 3648.0 380.52 101 (1) Hydraulic Pump

(a) New York Air Brake 14.0 342.62 P/N 66WH 400

(b) New York Air Brake 14.0 342.62 P/N 66WA 400

(c) New York Air Brake 13.5 342.62 P/N 66WH 300

(d) New York Air Brake 13.5 342.62 P/N 66WA 300

(e) New York Air Brake 13.5 342.62 P/N 66 WAP300

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM II - Equipment: (Cont'd) Weight ARM 102 (2) Starter - Air turbine

(a) Airesearch 46.4 343.52 P/N 355760-1 Model ATS-100-113 103 (1) Cabin Compressor

(a) Airesearch 58.0 347.02 P/N 206230 104 (2) Generator DC

(a) Eclipse Pioneer 128.0 345.52 P/N 30E02-9-G 105 (2) Alternator

(a) General Electric 189.0 346.62 P/N 2CM353 C1F 106 (1) Gas Turbine Compressor

(a) Airesearch 209.4 304.02 P/N 372580 Mod. 85-90-2 Landing Gear 200 (2) Main Gear Shock Strut Assemblies 523.0 503.02 Menasco 528400-501 L.H.

528400-502 R.H.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM Landing Gear: (Con'd) Weight Arm 201 (4) Main Wheel Brakes Assemblies 388.0 503.02 Goodyear Wheel Assembly 9540977/9540977-1 or 9540512/9540512-1

(b) Brake Assy. Loral 9540976-2 Piston Lining 5009106 Amvil Lining 5009107 Brake Disk 9531478 (.750/938) Brake Ring 5001742 Steel 5001037 Aluminum 202 (4) Main Gear Tires 356.0 504.2 (Tubeless 35 x 13 -14 Ply) (Inflation Press = 85 PSI 203 (1) Nose Gear Shock Strut Assemblies 195.5 92.0 Menasco 523500 204 (2) NLG Wheel 33.6 95.0 Goodyear 9531502 205 (2) Nose Wheel Tires (Tubeless 7.5 x 14 - 8 Ply) 58.0 95.0 (Inflation Pressure 63PSI) 206 (2) Anti-Skid System 84.0 503.0 Hytrol MK-1E

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA6088NM II - Equipment: (Cont'd) Weight ARM Electrical Equipment 300 (2) Batteries 155.0 514.0 Exide 6FH-13 (12 Volts) or equivalent 301 Navigation Honeywell E.F.I.S. EDZ-803 115.3 106.1 302 Radar Honeywell 13.0 15.0 P/N 7008470 Interior Equipment 401 FAA Approved Flight Manual - 5.0 90.0 Model CV 5800 402 Auto Pilot - Honeywell 69.8 259.7 SPZ-4500 (Installation) Fuel System 501 Fuel Jettisoning System 46.0 518.5 (STC SA1174WE)

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