E-272
Revision 9
WRIGHT
Double Row Turbo Cyclone
972TC18DA1
(Military R-3350-34, R-3350-91)
972TC18DA2
972TC18DA3
972TC18DA4
December 28, 1983
Engines of models described herein conforming with this data sheet (which is a part of type certificate No. E-272) and other aproved data on file with the Federal Aviation Agency meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Civil Air Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions.
Manufacturer
Curtiss-Wright/Marquette, Inc.
Fountain Inn, South Carolina
| Model : Double Row Turbo Cyclone | 972TC18DA1 (R-3350-34, -91), 972TC18DA2 | 972TC18DA3, 972TC18DA4 |
|---|---|---|
| Type : 18RA with 3 Blow-down exhaust-driven turbines | Reduction gear ratio 16:7 Turbo drive ratio 6.52:1 | - - - - |
| Rating (with low impeller gear ratio) 6.46:1 | ||
| Max. continuous, hp, rpm, in.Hg. at: | ||
| Critical pressure altitude (ft.) | 2650 - 2600 - 45.0 - 6500 | 2750 - 2600 - 47.0 - 5800 |
| Sea level pressure altitude | 2600 - 2600 - 47.5 - S.L. | 2700 - 2600 - 49.0 - S.L. |
| Takeoff (5 min.), hp, rpm, in.Hg. at: | ||
| Critical pressure altitude (ft.) | 3250 - 2900 - 53.0 - 5000 | 3250 - 2900 - 53.5 - 5500 |
| Sea level pressure altitude | 3250 - 2900 - 56.5 - S.L. | 3250 - 2900 - 56.5 - S.L. |
| Rating (with high impeller gear ratio) 8.67:1 | ||
| Max. continuous, hp, rpm, in.Hg. at: | ||
| Critical pressure altitude (ft.) | 2450 - 2600 - 47.0 - 16,400 | - - |
| Low critical pressure altitude (ft.) | 2405 - 2600 - 48.5 - 9550 | 2405 - 2600 - 48.5 - 10,050 |
| Takeoff (5 min.), hp, rpm, in.Hg. at: | ||
| Critical pressure altitude (ft.) | 2550 - 2600 - 49.0 - 15,200 | - - |
| Low critical pressure altitude (ft.) | 2535 - 2600 - 49.5 - 12,800 | 2535 - 2600 - 49.5 - 13,300 |
| Fuel (minimum grade aviation gasoline) | 115/145 | - - |
| Lubricating oil | MIL-L-6082, WAD Spec. 5815 or 5818 | - - |
| Bore and stroke, in. | 6.125 X 6.312 | - - |
| Displacement, cu. in. | 3350 | - - |
| Compression ratio | 6.70:1 | - - |
| Weight (dry), lbs. | 3550 | - - |
| C.G.location (dry) | ||
| Fwd. of mounting flange centerline, in. | 18.22 | - - |
| Left of vertical centerline, viewed from rear, in. | 0.014 | - - |
| Above propeller shaft, in. | 0.133 | - - |
| Propeller shaft, SAFE no. | 60 | - - |
| Fuel injection model | Bendix Stromberg PR-58-S2 master control with two Direct injection pumps | - - |
| Ignition, Dual | Scintilla DLN-9 magneto | - - |
| Timing, °BTC | 25 (30 in cruise) | - - |
| Spark plugs | See Note 10. | - - |
| NOTES | 1,2,3,4,5,6,7,8,9,10 | 1,2,3,4,5,6,7,8,9,10 |
| "- -" indicates "same as preceding model." | ||
| Page No | 1 | 2 | 3 |
|---|---|---|---|
| Rev. No. | 9 | 9 | 9 |
E-272
2
Certification basis
Production basis
Type Certificate No. 272
Production certificate No. 8
NOTE 1. Maximum permissible temperatures are as follows:
| Head (Well Type Thermocouple) | Barrel | Oil Inlet |
|---|---|---|
| 475° (500° for T.O. only) | 350° | 220° |
NOTE 2. Fuel and oil pressure lmits:
Oil pressure (psi) 70 +/-5. Fuel pressure (psi) 25 +/- 2
NOTE 3. The following accessory drives are provided:
| Rotation* | Speed** | Maximum torque (in. lbs.) | Maximum Bending Moment (in. lbs.) | ||
|---|---|---|---|---|---|
| Continuous | Static | ||||
| Starter | C | 1.000 | - | 3600 | 350 |
| Generator and accessory (2) | C | 3.110 | 1500 | 6600 | 400 |
| Fuel pump (2) | CC | 1.000 | 25 | 450 | 15 |
| Hydraulic pump | C | 1.400 | 600 | 2700 | 350 |
| Vacuum pump (2) | C | 1.400 | 250 | 1650 | 75 |
| Tachometer (2) | 1C - 1CC | 0.500 | 22 | 50 | 15 |
| Propeller governor | C | 0.857 | 125 | 825 | 30 |
*"C" - Clockwise viewing drive pad
"CC" - Counter clockwise
**Speed - Times crankshaft rpm
NOTE 4. These engines incorporate torquemeters, provisions for crankcase mounting and double-acting hydraulic propeller provisions.
NOTE 5. The ratings of these engines are based on standard conditions of temperature and barometric pressure (60°F and 29.92 in.Hg. at sea level) and 80% relative humidity. If corrected to dry standard air conditions, the rated powers would be increased approximately 2.5% at sea level to 0.4% at 15,000 ft. for equal manifold pressure settings.
NOTE 6. These engines incorporate 3 blow-down turbines for exhaust gas power recovery. To insure against secondary damage being caused by a turbine blade failure, it is required that each turbine wheel be provided with an approved type of guard prior to use in certificated aircraft. These guards should be capable of at least cushioning the energy effects of a failed blade.
NOTE 7. The military R-3350-34 and R-3350-91 engines are identifical to the 972TC18DA1 and are eligible for use in certificated aircraft; however, when used civilly the engine name plate should be revised to include the corresponding civil model designations and type certificate no.
E-272
3
NOTE 8. The model 972TC18DA2 and DA4 engines are similar to the 972TC18DA1 and DA3 models, respectively, except for installation feature differences.
NOTE 9. These engines are eligible for use with grade 100/130 fuel at the following ratings for all operations including cruise:
| 972TC18DA1 972TC18DA2 | 972TC18DA3 972TC18DA4 | |
|---|---|---|
| With low impeller gear ratio: | ||
| Maximum continuous, hp, rpm, in. Hg. at: | ||
| Critical pressure altitude (ft.) | 2450 - 2600 - 41.0 - 9100 | 2450 - 2600 - 41.5 - 9400 |
| Sea level pressure altitude | 2380 - 2600 - 43.5 - S.L. | 2380 - 2600 - 44.0 - S.L. |
| Takeoff (5 min.), hp, rpm, in.Hg., at: | ||
| Critical pressure altitude (ft.) | 2950 - 2900 - 47.5 - 8100 | 2950 - 2900 - 48.0 - 8500 |
| Sea level pressure altitude | 2880 - 2900 - 53.0 - S.L. | 2880 - 2900 - 53.0 - S.L. |
| With high impeller gear ratio: | ||
| Operation with grade 100/130 fuel not permitted. | ||
NOTE 10.The following spark plugs are approved on these engines:
AC 275, 286A, 288, 298
Champion R103, RHB27P, RHA29E, RHA29N, RHB29E, RHB29N
Lodge RS35R
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