# TCDS E10CE: Rolls-Royce Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Rolls-Royce Corporation
- Revision: 15
- Revised: September 1, 2000
- Product: Engine
- Certification basis: Part 33, Part 34
- Registered aircraft: 67, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/f1/ad/f1adcbcfd89c05af522d2c03b07107737ab2044a02ada934f127539e8cd83891
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A58C282A51E805E0862575B4004D8821.0001
- Page: https://openairdocs.org/tcds/E10CE

## Models (11)

As the data sheet lists them.

- 250-B17F
- 250-B17F/1
- 250-B17B
- 250-B17F/2
- 250-B15G
- 250-B17E
- 250-B17C
- 250-B15E
- 250-B17D
- 250-B17
- 250-B15A

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6
Rev. No. 15 13 15 13 15 15
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
E10CE
Revision 15
Rolls-Royce Corporation
250-B15A 250-B17D
250-B15E 250-B17E
250-B15G 250-B17F
250-B17 250-B17F/1
250-B17B 250-B17F/2
250-B17C
September 1, 2000
TYPE CERTIFICATE DATA SHEET NO. E10CE
Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E10CE), and other
approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in
accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations provided they are
installed, operated and maintained as prescribed by the approved manufacturer's manuals and other approved instructions.
Type Certificate Holder Rolls-Royce Corporation
P.O. Box 420
Indianapolis, Indiana  46206-0420
Model 250-B15A, -B15E, -B15G 250-B17 250-B17B 250-B17C
Type Free turbine – turboprop; Axial centrifugal compressor, 2 stage gas producer turbine, 2 stage power turbine,
single combustion chamber
Prop drive ratio 17.284:1 16.399:1 - - - -
Ratings (see NOTE 3)
  Max. continuous
    s.hp. at sea level 270 385 - - 420
    Prop drive r.p.m. 2025 2030 - - - -
Measured gas temp. 1280°F (693°C) 1430°F (777°C) 1406°F (763°C) 1464°F (795°C)
Takeoff s. hp. 317 400 - - 420
  5 min. at sea level
  Prop drive r.p.m. 2025 2030 - - - -
Measured gas temp. 1380°F (749°C) 1460°F (793°C) 1445°F (785°C) 1464°F (795°C)
Takeoff (augmented)
  at sea level, 95°F
  ambient temperature
    s.hp., 5 min. — — — 420
    Prop drive r.p.m. — — — 2030
    Measured gas temp — — — 1490°F (810°C)
      (see NOTE 15)
Prop drive Flange 4" bolt circle - - - - - -

E10CE 2
Control system
  (see NOTE 18)
Bendix gas producer
fuel control DP-M1;
Woodward combination
power turbine and
propeller governor control
8210-010; Woodward
propeller overspeed
governor 8210-011
Bendix gas producer fuel
control DP-P1;
Woodward combination
power turbine and
propeller governor
control 8210-018;
Woodward propeller
overspeed governor
8210-011
Bendix gas producer fuel
control DP-P2;
Woodward combination
power turbine and
propeller governor
control 8210-018;
Woodward propeller
overspeed governor
8210-011
- -
"- -" indicates same as preceding model.
"" indicates not applicable.

3 E10CE
Model 250-B17D 250-B17E 250-B17F, -B17F/1, -B17F/2
Type Free turbine – turboprop; Axial centrifugal compressor, 2 stage gas producer turbine,
2 stage power turbine, single combustion chamber
Prop drive ratio 16.399:1 - - - -
Ratings (see NOTE 3)
  Max. continuous
    s.hp. at sea level 420 - - 450
    Prop drive r.p.m. 2030 - - - -
Measured gas temp. 1464°F (795°C) 1448°F (787°C) 1430°F (777°C)
Takeoff s. hp. 420 - - 450
  5 min. at sea level
  Prop drive r.p.m. 2030 - - - -
Measured gas temp. 1464°F (795°C) 1448°F (787°C) 1430°F (777°C)
Takeoff (augmented)
  at sea level, 95°F
  ambient temperature
    s.hp., 5 min.  420 —
    Prop drive r.p.m. — 2030 —
    Measured gas temp — 1490 °F (810 °C) —
      (see NOTE 15)
Prop drive Flange 4" bolt circle - - - -
Control system
  (see NOTE 18)
Bendix gas producer
fuel control DP-P2;
Woodward combination
power turbine and
propeller governor control
8210-018; Woodward
propeller overspeed
governor 8210-011
- - Bendix gas producer
fuel control DP-P2;
Woodward combination
power turbine and
propeller governor
control 8210-011;
Woodward propeller
overspeed governor 8210-
085
Model 250-B15A, -B15E,
-B15G
250-B17, -B17B 250-B17C, -B17D,
-B17E
250-B17F, B17F/2 250-B17F/1
Fuel pump and filter Sundstrand single element 024918 or 5002395 or TRW pump model 386500    (All models)
Fuel MIL-T-5624, Grade JP-4 or JP-5; Aviation Turbine Fuels ASTM D1655 Jet A or A-1 (or Allison Spec.
EMS-64) or Jet B; MIL-T-83133, Grade JP-8 (for other fuel and limitations see NOTE 8.)  (All models)
Lubricating oil MIL-L-7808G or MIL-L-23699 and subsequent revisions.  (All models)
Principal dimensions:
  Length, overall, in. 44.642 44.834 44.92 44.924 - -
  Width, in. 19.06 19.006 18.78 18.784 - -
  Height, in. 22.53 22.53 22.60 22.596 - -
C.G. Location, aft of
  gear box side mount
  centerline, in.   2.72   2.70 - -   2.54   2.48
Lateral C.G. 0.36 to right of
gear box centerline
(looking fwd.- in.)
0.26 to left of
engine centerline
(looking fwd. - in.)
- - 0.42 (text)
of - -
    - -
.32 (text)
of - -
    - -

E10CE 4
C.G. Vertical - above
  engine centerline
  (see NOTE 10)
  2.72   3.13 - - 2.68 - -

5 E10CE
Model     (cont'd) 250-B15A, -B15E,
-B15G
250-B17, -B17B 250-B17C, -B17D,
-B17E
250-B17F, B17F/2 250-B17F/1
Weight (dry), lb. 250-B15A  171 195 - - 212 215
  Includes basic engine 250-B15E  171
  fuel pump and filter, 250-B15G  180
  ignition and fuel
  control system
Ignition system Capacitor discharge,
low tension exciter
type Simmons
Precision (GLA) P/N
41820 or P/N 43765
Bendix Scintilla P/N
10-369950-2 or
P/N 10-374440-1
Champion spark
igniter P/N FHE 161
or
AC P/N 5611071
(Type YB 63) (AC
P/N 5611588) or
Auburn P/N 0270486
Capacitor discharge, low
tension exciter type
Simmonds Precision
(GLA) P/N 43754 or
P/N 49522
Bendix-Scintilla P/N
10-387150 1
Champion spark igniter
P/N FHE 161-9 or CH
34168 or (AC P/N
5611071) (Type YB
63) or (AC P/N
5611588) (Type YB
63-1) or Auburn P/N
0270486
- - - - - -
"- -" indicates same as preceding model.
"" indicates does not apply.
Certification basis Part 33 of the Federal Aviation Regulations effective February 1, 1965, as amended by 33-2 and 33-3,
and Exemption No. 754 from FAR 33-69, Regulatory Docket 8338 dated November 30, 1967.
Application for Type Certificate dated June 12, 1967.  Type Certificate No. E10CE issued March 27,
1969, for Model 250-B15A, 250-B15E, and 250-B15G.  Model 250-B17 added April 7, 1971.  Model
250-B17B added July 5, 1974.  Model 250-B17C added May 11, 1979.  Model 250-B17D added
November 14, 1983.  Model 250-B17E added May 17, 1985.  Model 250-B17F dated May 6, 1988.
14 CFR Part 34, effective September 10, 1990 including Amendments 34-1 through 34-3
Production basis Production Certificate No. 310.
NOTE 1. Maximum Permissible Temperature:
Measured Gas Temperatures
Takeoff 1490°F.  (810°C.) for Models 250-B17B, -B17C, -B17D, -B17E, and -B17F, F/1, F/2
1380°F.  (749°C.) for Model 250-B15G
1460°F.  (793°C.) for Model 250-B17
Maximum continuous 1280°F.  (693°C.) for Model 250-B15G
1430°F.  (777°C.) for Model 250-B17
1490°F.  (810°C.) for Models 250-B17B, -B17C, -B17D, -B17E, and -B17F, F/1, F/2
Maximum transient
(not to exceed 1550°F.  (843°C.) for Models 250-B15G, 250-B17, -B17B, -B17C, -B17D, -B17E, 250-
6 seconds) B17F, F/1, F/2.  Ten seconds maximum between 1380°F.  (749°C.) to 1700°F.
250-B17D, and 250-B17E.  Ten seconds maximum between 1380°F.  (749°C.) to 1700°F.
(927°C.) for Model 250-B15G, ten seconds maximum between 1460°F.  (793°C.) to
1700°F.  (927°C) for Model 250-B17 and ten seconds maximum between 1490°F.
(810°C.) to 1700°F.  (927°C.) for Models 250-B17B, -B17C, -B17D, -B17E, and -B17F,
F/1, F/2.
Maximum transient
(6 not to exceed 1490°F.  (810°C.) to 1650°F.  (899°C.) for Model 250-B17F/1
12 seconds) (maximum of three occurrences per life of each turbine wheel).

E10CE 6
Oil inlet temperatures Minus 65°F.  to 180°F. for MIL-L-7808 and  minus 40°F. to 180°F. for MIL-L-23699 for
Models 250-B15G, 250-B17, 250-B17B, -B17C, -B17E, and 250-B17F, F/1, F/2.
Temperatures up to 225°F. are permitted for the 250-B17, -B17B, -B17C, -B17D,
-B17E, and -B17F, F/1, F/2 when operating at powers not in excess of 165 hp.
Temperatures up to 225°F. are allowed for five minutes when operating at powers in
excess of 165 hp. for models 250-B17, -B17B, -B17D, -B17E, and -B17F, F/1, F/2.

7 E10CE
Note 2. Fuel inlet and oil pressure limits are as follows:
Fuel: (Appl icable to MIL-T-5624, ASTM-D1655 Jet A, A-1 or B), minimum at fuel connection to
engine:  not less than ambient pressure minus 9.0 in. Hg at sea level, ambient minus 5.5 in. Hg at
6000 feet, ambient minus 3.3 in. Hg at 10,000 feet, ambient minus 0.8 in. Hg at 15,000 feet, ambient
plus 1.5 in. Hg at 20,000 feet, ambient plus 3.0 in. Hg at 25,000 feet.  No fuel inlet depression
permitted with MIL-G-5572 fuel.  Maximum pressure 25 p.s.i.g.
Oil: Model 250-B15 Series:
Operating oil gauge pressure at 48,053 r.p.m. (94.0 percent) gas producer speed and above is 110 to
130 p.s.i.g.
43,452 r.p.m. (85.0 percent) to 48,053 r.p.m. gas producer speed, 90 to 130 p.s.i.g.
Below 43,452 r.p.m. gas producer speed 50 to 130 p.s.i.g.
Oil pump inlet pressure 5 in. Hg absolute minimum when operating in the Beta range (propeller
operating below selected governor r.p.m.), the above minimum oil pressure limits are reduced by 15
p.s.i.g.
Models 250-B17, 250-B17B, 250-B17C, 250-B17D, 250-B17E, and 250-B17F, F/1, F/2:
Operating oil gauge pressure at 47,912 r.p.m. (94.0 percent) gas producer speed and above is 110 to
130 p.s.i.g. for all models except -B17F, 1, 2, which is 120-130 p.s.i.g.
43,325 r.p.m. (85.0 percent) to 47,912 r.p.m. gas pro ducer speed is 90 to 130 p.s.i.g.
Below 43,325 r.p.m. gas producer speed 50 to 130 p.s.i.g.
Oil pump inlet pressure 5 in. Hg absolute minimum
When operating in the Beta range (propeller operating below selected governor r.p.m.), the above
minimum oil pressure limits are reduced by 15 p.s.i.g.
NOTE 3. The engine ratings, unless otherwise specified, are based on static sea level standard conditions.  Compressor inlet
air (dry) 59°F., 29.92 in. Hg.  Compressor inlet bell attached to provide suitable air approach conditions.   No
external accessory loads and no customer air bleed.  Measured rated gas temperature as indicated by average of the 4
gas temperature thermocouples.
NOTE 4. The following accessory drive or mounting provisions are available:
(Models 250-B15G, 250-B17, 250-B17B, 250-B17C, 250-B17D, 250-B17E, and 250-B17F)
Driven by Gas *Direction Speed Ratio   Max. Torque (in. -lb.) Maximum Overhang
Producer Turbine    or Rotation          to Turbine             Continuous          Static         Moment (in. lb.)        
Spare C 0.0728 35 75 25
Tachometer CC 0.0824 7 50 4
Starter-Generator C 0.2361 ** 550 94
Driven by
Power Turbine
***Power takeoff-rear C 0.1807 4611 8000 100
Tachometer CC 0.1197 7 50 4
(250-B15)
0.1262
                                                            (250-B17, B17B, C, D, E, F, F/1, F/2)                             
   *C - Clockwise viewed drive pad; CC- Counterclockwise.

E10CE 8
 **The maximum generator load is 150 amperes (9.3 hp.).
***Not provided on 250-B15G.  The sum of the torque extracted in any combination from the front and rear power
output drives shall not exceed the torque values specified in NOTE 6.  The values given in above table represent
the 5 minute and maximum continuous limited total torque.

9 E10CE
NOTE 5. External air bleed may not exceed 4.0 percent for the 250-B15G and 4.5% for the 250-B17, -B17B, -B17C, -B17D, -
B17F, and -B17F, F/1, F/2.
NOTE 6. Model 250-B15 Series:
The maximum allowable torque as measured by the torquemeter for below standard inlet air temperature and/or ram
conditions is 948 ft.-lb. for 10 seconds; 869 ft.-lb. for takeoff and 737 ft.-lb. for maximum continuous.
Models 250-B17 and -B17B:
The maximum allowable torque as measured by the torquemeter for below standards inlet air temperature and/or ram
conditions is 1165 lb.-ft. for 10 seconds; 1087 lb.-ft. for takeoff and 996 lb.-ft. for maximum continuous.
Models 250-B17C, -B17D, and -B17E:
The maximum allowable torque as measured by the torquemeter for below standard inlet air temperature and/or ram
conditions is 1165 lb.-ft. for 10 seconds; 1138 lb.-ft. for takeoff and maximum continuous.
Model 250-B17F, -B17F/1, and -B17F/2
The maximum allowable torque as measured by the torquemeter for below standard inlet air temperature and/or ram
conditions is 1218 lb.-ft. for 10 seconds; 1185 lb.-ft. for takeoff and maximum continuous.
NOTE 7. Gas producer speeds up to 105 percent are permissible for 15 seconds and up to 104 percent speed continuously
for the 250-B15 and 250-B17, and up to 106  percent for 15 seconds and up to 105 percent speed continuously for
the 250-B17B, -B17C, -B17D, -B17E and -B17F, F/1, F/2.  Power turbine speeds up to 110 percent are permissible
for 15 seconds and up to 104 percent continuously for 250-B15 and 105 percent for 250-B17, -B17B,  -B17C, -
B17D, -B17E and -B17F, F/1, F/2.  The power turbine governor provides propeller overspeed protection.  100
percent gas producer speed is defined as 51,120 r.p.m. for 250-B15, and 50,970 r.p.m. for 250-B17, -B17B, -B17C,
-B17D,
-B17E, and -B17F, F/1, F/2.  100 percent turbine speed is defined as 35,000 r.p.m. for the 250-B15 and 33,290 for
the 250-B17, -B17B, -B17C, -B17D, -B17E, and -B17F, F/1, F/2.
NOTE 8. Emergency use of aviation gasoline MIL-G-5572, grades 115/145 and lower, is limited to amount of fuel required to
operate the engine for not over 6 hours during an overhaul period except that a mixture consisting of 1/3 by volume
of aviation gasoline MIL-G-5572 grade 80/87, and 2/3 by volume of MIL-T-5624, grade JP-5, or aviation turbine
fuels ASTM-D1655 Jet A or A-1 or Allison Spec. EMS-64 may be used for unrestricted periods of time.  Fuels
containing Tri-Cresyl-Phosphate additives shall not be used.  It is not necessary to purge the unused fuel from the
system before refueling with different type fuels.  No fuel control adjustment is required when switching these fuel
types.  Anti-icing additives conforming to MIL-I-27686 are approved for use in fuels in amounts not to exceed 0.15
percent by volume.  Shell anti-static additive is approved for use at a concentration that will not exceed fuel
conductivity of 300 picomhos per meter.  The 250-B15 and –B17 series engines are approved for use with fuel
meeting Chinese specification GB6537-94 RP-3.
NOTE 9. The 250-B15A is similar to the 250-B15G except no provision for coordinator.
The 250-B15E is similar to the 250-B15G except no provision for coordinator and propeller brake.
The 250-B17 is similar to the 250-B15G except increased ratings, larger diameter first stage compressor wheel and
larger diameter power turbine wheels.
The 250-B17B is similar to 250-B17 except for turbine changes for improved hot day performance.
The 250-B17C is similar to 250-B17B except for increased ratings and deleted propeller brake.
The 250-B17D is similar to 250-B17C except for propeller reduction gearbox changes to accommodate aerobatic
maneuvers.
The 250-B17E is similar to 250-B17C except the guaranteed performance ratings are accomplished at reduced rated
measured gas temperatures.
The 250-B17F is similar to the 250-B17D except for increased performance, a new compressor, and incorporates an
on-speed #1 wheel internal energy absorbing ring.
The 250-B17F/1 is similar to the 250-B17F except it incorporates an electronic power turbine (N2) overspeed
detection system and it does not incorporate propeller reduction gearbox changes to accommodate aerobatic
maneuvers.

E10CE 10
The 250-B17F/2 is similar to the 250-B17F except it does not incorporate propeller reduction gearbox changes to
accommodate aerobatic maneuvers.
NOTE 10. For the 250-B15A and 250-B15E models the CG location aft of gear box side mount centerline moves to 2.74 in.
The lateral CG moves to 1.01 inches to the right of gear box centerline (looking forward) and the vertical CG moves
to 2.96 inches above the engine centerline.
NOTE 11. These engines are approved for both tractor and pusher applications.

11 E10CE
NOTE 12. Life limits established for critical components are published in the corresponding Operations and Maintenance
Manual.  Distributor Information Letters (DIL) 190 and 202 establish acceptable crack limits suitable for return to
 service of first stage and second stage turbine wheels, respectively, in time continued (repair) engines.
NOTE 13. Engines produced under this type certificate except the model 250-B17F, are approved for operation with
unprotected inlets having been tested in accordance with Group I and Group II Foreign Object Ingestion Criteria of
FAA Advisory Circular AC 33-1B.  The model 250-B17F is approved for operation with an unprotected inlet
having been tested in accordance with Foreign Object Ingestion Criteria of FAR 33-10, Section 33.77 with the
exception that Advisory Circular 20-73 criteria of 60-second delay, instead of 2-minutes, was used in actuating the
anti-icing system.
NOTE 14. Engine equipment, which is aircraft mounted, includes two water-alcohol injection nozzles for the 250-B17C
(optional) and 250-B17E (optional).
NOTE 15. Operation with water-alcohol injection is limited to ambient temperatures above 40°F.
The augmented takeoff rating is based on water-alcohol flow rate of 1.25 g.p.m. delivered to the injection nozzles at
a pressure differential of 50 p.s.i. across each nozzle.  The water-alcohol solution, nozzle location and system
installation must be in accordance with the FAA approved installation Design Handbook requirements.
NOTE 16. A magnetic oil drain plug (chip detector) indicator lamp is an installation requirement.
NOTE 17. A 3 to 25 micron absolute external seavenge oil filter is an installation requirement for the model 250-B17F, F/1, F/2
engines.
NOTE 18. Control system component part numbers approved for each engine mode are listed in the applicable parts catalog.
... END...
```

## ADs (18, in force first)

- [AD 2006-16-04](https://openairdocs.org/ad/2006-16-04): Inspection of the fuel nozzle screen · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 43 more. Effective Sep 7, 2006
- [AD 2006-13-06](https://openairdocs.org/ad/2006-13-06): Gas producer rotor assembly tie bolts · Rolls-Royce 250-B17, 250-B17B, 250-B17C and 16 more. Effective Jul 26, 2006
- [AD 2005-10-13](https://openairdocs.org/ad/2005-10-13): Turbine energy absorbing ring · Rolls-Royce 250-B17B, 250-B17C, 250-B17D and 7 more. Effective Jun 22, 2005
- [AD 2004-26-09](https://openairdocs.org/ad/2004-26-09): Compressor Adaptor Couplings · Rolls-Royce 250-B17, 250-B17B, 250-B17C and 8 more. Effective Feb 8, 2005
- [AD 2001-24-12](https://openairdocs.org/ad/2001-24-12): Helical Torquemeter Gearshaft Assembly · Rolls-Royce 250-B17, 250-B17C, 250-B17D and 13 more. Effective Dec 19, 2001
- [AD 98-24-28](https://openairdocs.org/ad/98-24-28): Main Fuel Control Bellows · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 36 more. Effective Jan 7, 1999
- [AD 96-19-01](https://openairdocs.org/ad/96-19-01): Superior Air Parts Manufacture Approval (PMA) Bearings · Rolls-Royce 250-B15G, 250-B17F, 250-B17F/1 and 17 more. Effective Sep 26, 1996
- [AD 88-17-01](https://openairdocs.org/ad/88-17-01): Fuel Controls · Rolls-Royce 250-B17, 250-B17B, 250-B17C and 26 more. Effective Mar 1, 1989
- [AD 83-03-02 R1](https://openairdocs.org/ad/83-03-02-R1): Slotted Third Stage Turbine Wheels · Rolls-Royce 250-B17, 250-B17B, 250-B17C and 5 more. Effective Feb 28, 1984
- [AD 82-24-05](https://openairdocs.org/ad/82-24-05): Control Assembly and Power Turbine Governor Assembly · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 43 more. Effective Nov 26, 1982
- [AD 82-12-04](https://openairdocs.org/ad/82-12-04): Combined Power Turbine and Propeller Governor Assembly · Cessna 401, 401A, 401B and 11 more. Effective Jun 7, 1982
- [AD 79-21-01 R1](https://openairdocs.org/ad/79-21-01-R1): Third Stage Turbine Wheel Blade · Rolls-Royce 250-B17, 250-B17B, 250-B17C and 3 more. Effective Jun 3, 1981
- [AD 77-15-12](https://openairdocs.org/ad/77-15-12): Power Turbine Coupling Nut · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 23 more. Effective Sep 23, 1977
- [AD 77-09-08](https://openairdocs.org/ad/77-09-08): Bleed Valve Diaphragm · Rolls-Royce 250-B17, 250-B17B, 250-C20 and 2 more. Effective Jul 18, 1977
- [AD 72-03-06](https://openairdocs.org/ad/72-03-06): Turbine Wheels · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 9 more. Effective Feb 8, 1972
- [AD 2015-02-22](https://openairdocs.org/ad/2015-02-22) (historical): Repetitive visual inspections · Rolls-Royce 250-B17, 250-B17B, 250-B17C and 15 more. Effective Mar 9, 2015
- [AD 2004-24-09](https://openairdocs.org/ad/2004-24-09) (historical): Fuel nozzle · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 40 more. Effective Jan 5, 2005
- [AD 2001-20-51](https://openairdocs.org/ad/2001-20-51) (historical): Helical Torquemeter Gearshaft Assembly · 250-B17, 250-B17C, 250-B17D and 12 more

## Registered aircraft by registry model (OpenAirDocs)

- [Allison 250-B17 series](https://openairdocs.org/engine/allison-250-b17-series): 14 aircraft (registry codes 03017, 03018)
- [Allison 250-B15G](https://openairdocs.org/engine/allison-250-b15g): 12 aircraft (registry code 03064)
- [Rolls-Royce 250-B17F](https://openairdocs.org/engine/rolls-royce-250-b17f): 10 aircraft (registry code 54586)
- [Rolls-Royce 250-B17F/2](https://openairdocs.org/engine/rolls-royce-250-b17f-2): 8 aircraft (registry code 54033)
- [Allison 250-B17C](https://openairdocs.org/engine/allison-250-b17c): 6 aircraft (registry code 03067)
- [Rolls-Royce 250-B17C](https://openairdocs.org/engine/rolls-royce-250-b17c): 6 aircraft (registry code 54029)
- [Allison 250-B17D](https://openairdocs.org/engine/allison-250-b17d): 4 aircraft (registry code 03068)
- [Allison 250-B17F/2](https://openairdocs.org/engine/allison-250-b17f-2): 3 aircraft (registry code 03072)
- [Rolls-Royce 250-B17D](https://openairdocs.org/engine/rolls-royce-250-b17d): 2 aircraft (registry code 54030)
- [Allison 250-B17E](https://openairdocs.org/engine/allison-250-b17e): 1 aircraft (registry code 03069)
- [Rolls-Royce 250-B15G](https://openairdocs.org/engine/rolls-royce-250-b15g): 1 aircraft (registry code 54026)
- [Allison 250-B15A](https://openairdocs.org/engine/allison-250-b15a): 0 aircraft (registry code 03062)
- [Allison 250-B15E](https://openairdocs.org/engine/allison-250-b15e): 0 aircraft (registry code 03063)
- [Allison 250-B17](https://openairdocs.org/engine/allison-250-b17): 0 aircraft (registry code 03065)
- [Allison 250-B17B](https://openairdocs.org/engine/allison-250-b17b): 0 aircraft (registry code 03066)
- [Allison 250-B17F](https://openairdocs.org/engine/allison-250-b17f): 0 aircraft (registry code 03070)
- [Allison 250-B17F/1](https://openairdocs.org/engine/allison-250-b17f-1): 0 aircraft (registry code 03071)
- [Rolls-Royce 250-B15A](https://openairdocs.org/engine/rolls-royce-250-b15a): 0 aircraft (registry code 54024)
- [Rolls-Royce 250-B15E](https://openairdocs.org/engine/rolls-royce-250-b15e): 0 aircraft (registry code 54025)
- [Rolls-Royce 250-B17](https://openairdocs.org/engine/rolls-royce-250-b17): 0 aircraft (registry code 54027)
- [Rolls-Royce 250-B17B](https://openairdocs.org/engine/rolls-royce-250-b17b): 0 aircraft (registry code 54028)
- [Rolls-Royce 250-B17E](https://openairdocs.org/engine/rolls-royce-250-b17e): 0 aircraft (registry code 54031)
- [Rolls-Royce 250-B17F/1](https://openairdocs.org/engine/rolls-royce-250-b17f-1): 0 aircraft (registry code 54032)

## STCs approved under this data sheet (3)

- [STC SE00327AT](https://openairdocs.org/stc/SE00327AT): Installation of PC Safety Valve Kit.. Bell Helicopter Textron Inc.
- [STC ST00037AT](https://openairdocs.org/stc/ST00037AT): Unison igniter plugs, P/N 9044400-1.. Unison Industries
- [STC SQ00338AT](https://openairdocs.org/stc/SQ00338AT): Unison igniter leads, P/N9048222-101, 102, 103, 104, 105, 106.. Unison Industries

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