FEDERAL AVIATION ADMINISTRATION

U.S. DEPARTMENT OF TRANSPORTATION

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| E7EU                                                                  |
|                                                                       |
| TURBOMECA                                                             |
|                                                                       |
| TURMO III C5                                                          |
|                                                                       |
| August 29, 1968                                                       |
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[TYPE CERTIFICATE DATA SHEET E7EU]{.underline}

Engines of models described herein conforming with this data sheet
(which is part of Type Certificate Number E7EU) 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: Turbomeca

64 Bordes, France

<table style="width:100%;">
<colgroup>
<col style="width: 19%" />
<col style="width: 0%" />
<col style="width: 0%" />
<col style="width: 7%" />
<col style="width: 12%" />
<col style="width: 1%" />
<col style="width: 9%" />
<col style="width: 5%" />
<col style="width: 3%" />
<col style="width: 5%" />
<col style="width: 9%" />
<col style="width: 0%" />
<col style="width: 0%" />
<col style="width: 7%" />
<col style="width: 5%" />
<col style="width: 8%" />
<col style="width: 1%" />
<col style="width: 0%" />
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<col style="width: 0%" />
</colgroup>
<tbody>
<tr class="odd">
<td colspan="2">Model</td>
<td colspan="17">TURMO III C5</td>
<td></td>
</tr>
<tr class="even">
<td colspan="2">Type</td>
<td colspan="17">Twin Spool (free turbine)</td>
<td></td>
</tr>
<tr class="odd">
<td colspan="2"></td>
<td colspan="17">Turbo-shaft engine for multi-engined helicopters.</td>
<td></td>
</tr>
<tr class="even">
<td colspan="2"></td>
<td colspan="17"><p>- Single stage axial compressor</p>
<p>- Single stage centrifugal compressor</p>
<p>- Annular combustion chamber with central, rotating, fuel
injection</p>
<p>- Two stages axial turbine for gas generator</p>
<p>- Two stages axial turbine for power output</p>
<p>- One stage reduction gear, ratio 1/3.53659, to output shaft, driving
at 5,915 rpm (nominal)</p></td>
<td></td>
</tr>
<tr class="odd">
<td colspan="2">Rating (See NOTE 5)</td>
<td colspan="18">At nominal power turbine speed of 20,900 rpm (5915
output shaft rpm)</td>
</tr>
<tr class="even">
<td colspan="2"></td>
<td colspan="8">Max. continuous at S.L.; hp.</td>
<td colspan="8">1230</td>
<td colspan="2"></td>
</tr>
<tr class="odd">
<td colspan="2"></td>
<td colspan="8">T.O. (5 min.) at S.L.: hp.</td>
<td colspan="8">1350</td>
<td colspan="2"></td>
</tr>
<tr class="even">
<td colspan="2"></td>
<td colspan="8">30 min. helicopter rating at S.L.; hp.</td>
<td colspan="8">1350</td>
<td colspan="2"></td>
</tr>
<tr class="odd">
<td colspan="2"></td>
<td colspan="8">2 1/2 min. helicopter rating at S.L.; hp.</td>
<td colspan="8">1450</td>
<td colspan="2"></td>
</tr>
<tr class="even">
<td colspan="2">Fuel Control</td>
<td colspan="8"><p>Constant speed (isodromic) fuel flow governor for</p>
<p>generator turbine spool</p></td>
<td colspan="8">Turbomeca 0.064.74.503.0</td>
<td colspan="2"></td>
</tr>
<tr class="odd">
<td colspan="2"></td>
<td colspan="8">Idling fuel flow control unit</td>
<td colspan="8">Turbomeca 0.249.85.885.0</td>
<td colspan="2"></td>
</tr>
<tr class="even">
<td colspan="2"></td>
<td colspan="8">High pressure fuel shut-off cock</td>
<td colspan="8">Semca type 4414/311</td>
<td colspan="2"></td>
</tr>
<tr class="odd">
<td colspan="2"></td>
<td colspan="8"><p>Quick action fuel shut-off solenoid valve (actuated
by</p>
<p>free turbine overspeed sensing device)</p></td>
<td colspan="8">Turbomeca 0.074.15.000.0</td>
<td colspan="2"></td>
</tr>
<tr class="even">
<td colspan="2">Fuel</td>
<td colspan="11">Approved specifications (latest issue)</td>
<td colspan="4"></td>
<td colspan="3"></td>
</tr>
<tr class="odd">
<td colspan="3"></td>
<td colspan="2"><u>U.S.</u></td>
<td colspan="3"><u>U.K.</u></td>
<td colspan="3"><u>France</u></td>
<td colspan="9"></td>
</tr>
<tr class="even">
<td colspan="3"></td>
<td colspan="2">MIL.F.5616 (JP1)</td>
<td colspan="3">DERD 2453/2494</td>
<td colspan="3">AIR 3405 (TR0)</td>
<td colspan="9"></td>
</tr>
<tr class="odd">
<td colspan="3"></td>
<td colspan="2">MIL.J.5624 (JP4)</td>
<td colspan="3">DERD 2486/2454</td>
<td colspan="3">AIR 3407 (TR4)</td>
<td colspan="9"></td>
</tr>
<tr class="even">
<td colspan="3"></td>
<td colspan="2">MIL.J.5624 (JP5)</td>
<td colspan="3">DERD 2488/2498</td>
<td colspan="3">AIR 3404 (TR5)</td>
<td colspan="9"></td>
</tr>
<tr class="odd">
<td colspan="3"></td>
<td colspan="8">The following fuel additives are approved for use:</td>
<td colspan="9"></td>
</tr>
<tr class="even">
<td colspan="3"></td>
<td colspan="12">- Phillips PFA/55 MB, anti-icing additive, in quantity
up to 0.15 percent in volume.</td>
<td colspan="5"></td>
</tr>
<tr class="odd">
<td colspan="3"></td>
<td colspan="12">- Shell ASA-3 antistatic additive, in quantity up to
0.0001 percent in volume.</td>
<td colspan="5"></td>
</tr>
<tr class="even">
<td>Oil</td>
<td colspan="11">Approved Specification (latest amendment) (synthetic
oil)</td>
<td colspan="8"></td>
</tr>
<tr class="odd">
<td></td>
<td colspan="5">- U.S. : MIL.L.7808</td>
<td colspan="10">- France : AIR 3513</td>
<td colspan="4"></td>
</tr>
<tr class="even">
<td>Principal Dimensions</td>
<td colspan="3">Length</td>
<td colspan="3">: 77.80 in.</td>
<td colspan="13"></td>
</tr>
<tr class="odd">
<td></td>
<td colspan="3">Width</td>
<td colspan="3">: 27.60 in.</td>
<td colspan="13"></td>
</tr>
<tr class="even">
<td></td>
<td colspan="3">Height</td>
<td colspan="3">: 27.90 in.</td>
<td colspan="13"></td>
</tr>
<tr class="odd">
<td>Weight</td>
<td colspan="8">Dry, completely equipped, including exhaust pipe</td>
<td colspan="5">: 660 lb.</td>
<td colspan="6"></td>
</tr>
</tbody>
</table>

  --------------- ------------------------------- ----------------- -- -- --
  Center of       Forward of rear engine mount    35.3                    
  Gravity         plane, in.                                              

                  In the horizontal plane of the  3.15                    
                  engine centerline and output                            
                  drive shaft, from centerline on                         
                  drive shaft side, in.                                   

  Ignition        High tension, low energy                                
                  system, comprising:                                     

                  \- Double ignition coil         : Air-Equipment         
                                                  Type 81268/10           

                  \- Two torch igniters           : Turbomeca             
                                                  0.237.30.750.0          

                  \- Two high tension cables      : Turbomeca             
                                                  0.043.05.703.0          

                  \- Ignition fuel micropump      : Turbomeca             
                                                  0.044.61.501.0          

  Starting        Starting generator              : SEB Type 8051         

                  Compressor pressure switch for  : Turbomeca             
                  terminating of starting cycle   0.076.09.500.0          

  Certification   FAR 21.29 and FAR 33, effective                         
  Basis           February 1, 1965, and                                   
                  Amendments 33-1, 33-2, and                              
                  33-3.                                                   

                  Date of Application for Type                            
                  Certificate : January 15, 1968                          
                  Type Certificate E7EU issued                            
                  August 29, 1968.                                        

  Import          Each individually imported                              
  Requirements    engine and replacement part                             
                  must be accomplished by a                               
                  Bureau Veritas \"Certificate of                         
                  Control\" signed by a Bureau                            
                  Veritas inspector.                                      
  --------------- ------------------------------- ----------------- -- -- --

NOTE 1. Maximum Permissible Rotor Speeds, R.P.M.\*

\- Gas generator turbine

2 1/2 min. helicopter rating 33,550

30 min. helicopter rating 33,150

Take-off 33,150

Maximum continuous 32,500

Transient (60 sec. max.) 34,000

*\* Refer to Turbomeca Operation Manual 249.09.932 for required action
if limits are exceeded. Also refer to this Manual for other rpm limits
versus OAT and engine bleed configurations.*

\- Free turbine (expressed in output shaft R.P.M.)

Nominal speed 5915

Maximum speed 6344

Free turbine speed is 3.53569 times output shaft speed.

NOTE 2. Maximum Permissible Temperatures

A. Gas generator turbine exhaust (T4)\*, °C

(measured with two thermocouples on gas generator turbine exhaust
diffuser)

2 1/2 min. helicopter rating 775

30 min. helicopter rating 745

Take-off 745

Max. continuous 720

Starting (30 sec. max.) 750

Transient, for operation

(30 sec. max) 800

Maximum residual before starting 150

*\* Refer to Turbomeca Operation Manual 249.09.932 for required action
if limits are exceeded.*

B. Oil temperature limits (measured in oil tank), °C

\- Max. operating 105

\- Minimum for starting -20

\- Minimum for operation 0

C. Fuel temperature limits, °C

\- Minimum for starting -20

\- Maximum for operation 43

NOTE 3. Fuel and Oil Pressure Limits

Fuel : At engine inlet for starting, P.S.I.G. 4.3 to 11.6

At engine inlet for operation, P.S.I.G. -3.6 to 17.4

Oil : (At engine oil pump outlet)

At ground idle, minimum, P.S.I.G. 14.5

Normal operating range, P.S.I.G. 29 to 58

NOTE 4. Accessory Drive Provisions

The following driven accessories are provided on the engine and are
included in engine weight.

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<col style="width: 18%" />
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<col style="width: 12%" />
<col style="width: 0%" />
<col style="width: 0%" />
<col style="width: 16%" />
<col style="width: 0%" />
<col style="width: 0%" />
<col style="width: 14%" />
<col style="width: 0%" />
<col style="width: 9%" />
<col style="width: 0%" />
<col style="width: 0%" />
<col style="width: 2%" />
<col style="width: 9%" />
</colgroup>
<tbody>
<tr class="odd">
<td colspan="3"></td>
<td></td>
<td colspan="2">Rotation</td>
<td colspan="3"></td>
<td colspan="7"><u>Max. Torque</u></td>
<td colspan="2"></td>
</tr>
<tr class="even">
<td colspan="3">Accessory</td>
<td>Part No.</td>
<td colspan="2"><p>Sense</p>
<p>of Engine</p>
<p>Drive Pad</p></td>
<td colspan="3"><p>Reduction</p>
<p>Ratio</p></td>
<td colspan="4"><p>Continuous</p>
<p>in lb.</p></td>
<td colspan="3"><p>Static</p>
<p>in lb.</p></td>
<td colspan="2"><p>Overhang</p>
<p>in lb.</p></td>
</tr>
<tr class="odd">
<td colspan="18">- on gas generator turbine</td>
</tr>
<tr class="even">
<td colspan="3"><p>Starter</p>
<p>Generator</p></td>
<td><p>SEB Type</p>
<p>8051</p></td>
<td colspan="3">CCW</td>
<td colspan="3">NTG/4.13793</td>
<td colspan="2">130</td>
<td colspan="2">600</td>
<td colspan="4">350</td>
</tr>
<tr class="odd">
<td colspan="3"><p>Tachometer</p>
<p>Transmitter</p></td>
<td><p>JAEGER</p>
<p>Type 545</p>
<p>344</p></td>
<td colspan="3">CCW</td>
<td colspan="3">NTG/7.94482</td>
<td colspan="2">1</td>
<td colspan="2">5</td>
<td colspan="4">18</td>
</tr>
<tr class="even">
<td colspan="3">Free pad available for optional alternator</td>
<td>(not provided)</td>
<td colspan="3">CCW</td>
<td colspan="3">NTG/2.52811</td>
<td colspan="2">80</td>
<td colspan="2">400</td>
<td colspan="4">350</td>
</tr>
<tr class="odd">
<td colspan="18">- on free turbine (output turbine)</td>
</tr>
<tr class="even">
<td colspan="3">Ventilator for oil cooler</td>
<td colspan="2"><p>TURBOMECA</p>
<p>0.249.15.512.0</p></td>
<td colspan="3">CW</td>
<td colspan="3">NTL/.79573</td>
<td colspan="2">32</td>
<td colspan="2">160</td>
<td colspan="3">90</td>
</tr>
<tr class="odd">
<td>CCW</td>
<td>=</td>
<td colspan="15">Counterclockwise looking at accessory drive pad.</td>
<td></td>
</tr>
<tr class="even">
<td>CW</td>
<td>=</td>
<td colspan="15">Clockwise looking at accessory drive pad.</td>
<td></td>
</tr>
<tr class="odd">
<td>NTG</td>
<td>=</td>
<td colspan="15">rpm of the gas generator turbine.</td>
<td></td>
</tr>
<tr class="even">
<td>NTL</td>
<td>=</td>
<td colspan="15">rpm of the free turbine.</td>
<td></td>
</tr>
</tbody>
</table>

NOTE 5. Engine ratings are based on calibrated test stand performance
under the following conditions:

\- Static sea level standard conditions, (15°C, 29.92 in. Hg.)

\- No air bleed.

\- No power off-takes.

The ratings are minimum acceptable final test performance of series and
overhauled engines, measured with:

\- Calibrated test bed air intake, according to Turbomeca dwg No.
6.201.55.721.0

\- Flight exhaust pipe, Turbomeca Part No. 0.249.75.000.0 (which is part
of engine delivery)

NOTE 6. Maximum permissible air bleed (from centrifugal compressor
plenum)

[lb/sec.]{.underline}

\- for aircraft (helicopter) services (including inlet duct anti-icing
when required) 0.330

\- for engine air intake anti-icing 0.220

From gas generator turbine exhaust diffuser

\- for aircraft (helicopter) service

NOTE: When this bleed air is used, centrifugal compressor bleed for
aircraft (helicopter) services must be reduced from 0.330 to 0.165 lb.
sec.

NOTE 7. Air intake anti-icing limits:

\- If OAT is equal or higher than -5°C Gas Generator R.P.M. must be
equal or higher than 26,000

-15°C 27,000

-20°C 28,000

-30°C 30,000

\- Also engine oil temperature must be equal or higher than 30°C

The engine meets FAR 33 requirements for operation in icing conditions
when the above limitations are observed.

NOTE 8. Engine Mechanical Limits:

[Rating]{.underline} [Output Shaft Horsepower]{.underline}

2 1/2 min. helicopter Increases linearly form 1450 at 15°C to 1583 at
5.7°C with flat rating below this temperature

Take-off & 30 min. helicopter Increases linearly from 1350 at 15°C to
1475 at 5.2°C with flat rating below this temperature

Max. continuous Increase linearly from 1230 at 15°C to 1341 at 5°C with
flat rating below this temperature

Maximum allowed output shaft torque is 1555 ft. lbs.

For other limitations VS ambient temperature and bleed conditions, see
Turbomeca Operations Manual 249.09.932.

Operation of gas generator turbine with free turbine stopped is
prohibited with free turbine R.P.M. over 20,000. Limited operation of
the gas generator with the free turbine stopped (helicopter rotor brake
ON) is allowed only when starting in ground conditions with winds over
30 knots. In this case brake release is required when gas generator
speed reaches 19,000 to 19,750 R.P.M.

NOTE 9. The TURMO III C5 has integral oil system including pumps, oil
tank, oil filter, oil cooler with its mechanically driven cooling fan,
all necessary pipes and fittings.

\- Oil pump assembly (lubricating and scavenging pumps) : Turbomeca
0.249.15.762.0

\- Oil cooler with thermostat

(heat rejection approx. 14.0 BTU/Sec) : Jaeger Type 2.2632 A

\- Oil filter

(including cleanable metallic filter-element with 30

microns filtration grade : Softrance Type P.5315 A)

NOTE 10. The engine has no provision for fuel filtering. Fuel supply
from aircraft (helicopter) system must therefore be delivered to engine
with a 10 microns filtration grade.

Maximum fuel flow Approx. 160 U.S. Gallons/hour

NOTE 11. Engine monitoring transmitters:

The engine is equipped with the following transmitter instruments, which
are part of delivery:

\(a\) Tachometer transmitter (gas generator turbine speed) JAEGER Type
545344

\(b\) Oil pressure transmitter JAEGER-AMA Type 1879 SB

\(c\) Oil temperature bulb JAEGER-AMA Type 1982 ZC

\(d\) Thermocouple harness including two chromel-alumel TURBOMECA
0.177.02.000.0

thermocouples

\(e\) Electronic transmitter for free turbine rotational speed ELECMA
Type DV 202 A

NOTE 12. Engine fire detection:

The following spot detectors are installed : - Three l\'Hotellier Type B
232 (front engine zone)

\- Six l\'Hotellier Type B 332 (rear engine zone)

NOTE 13. Electrical Equipment:

27 Volts DC system with all necessary harnesses and Turbomeca
0.177.01.500.0

wirings, including connection box

Automatic starting sequence block Turbomeca 0.077.44.705.0

is approved for use on the engine.

NOTE 14. This engine meets FAR 33 requirements for adequate turbine disc
integrity and rotor blade containment.

\.....END\.....