DEPARTMENT OF TRANSPORTATION

**FEDERAL AVIATION ADMINISTRATION**

> E14EA
>
> Revision 20
>
> Lycoming Engines
>
> **TIO-540**-A1A, -A1B, -A2A,
>
> -A2B, -A1C, -A2C, -C1A,
>
> -E1A, -F2BD, -G1A, -H1A,
>
> -J2B, -J2BD, -K1AD, -N2BD,
>
> -R2AD, -S1AD, -T2AD, -U2A,
>
> -V2AD, -W2A, -AA1AD,
>
> -AB1AD, -AB1BD -AE2A,
>
> -AF1A, -AF1B, -AG1A,
>
> -AH1A, -AJ1A, AK1A
>
> **LTIO-540-**F2BD-J2B, -J2BD,
>
> -K1AD, -N2BD, -R2AD, -U2A,
>
> -V2AD, -W2A
>
> September 26, 2006

**[TYPE CERTIFICATE DATA SHEET NO. E14EA]{.underline}**

Engines of models described herein conforming with this data sheet
(which is a part of type certificate No. E14EA) and other approved data
on file with the Federal Aviation Administration meet the minimum
standards for use in certification aircraft in accordance with pertinent
aircraft data sheets and applicable portions of the Civil Air
Regulations/Federal Aviation Regulations provided they are installed,
operated, and maintained as prescribed by the approved manufacturer's
manual and other approved instructions.

Type Certificate Holder Lycoming Engines,

An operating Division of Avco Corporation

Williamsport, Pennsylvania 17701

Type Certificate Holder Record Textron Lycoming, AVCO Corporation
transferred TC E14EA to Lycoming Engines, An Operating Division of Avco
Corporation on December 17, 2003.

+--------------------+---------------+---------------+---------------+
| Model Lycoming     | TIO-540-A1A,  | TIO-540-A1C,  | TIO-540-E1A   |
|                    | -A1B,         | -A2C          |               |
|                    |               |               |               |
|                    | -A2A, -A2B    |               |               |
+--------------------+---------------+---------------+---------------+
| Type 6HOA Direct   |               |               |               |
| Drive Turbocharged |               |               |               |
+--------------------+---------------+---------------+---------------+
| Rating (See Notes  |               |               |               |
| 4 and 13)          |               |               |               |
+--------------------+---------------+---------------+---------------+
| Maximum continuous |               |               |               |
| hp., rpm,          |               |               |               |
|                    |               |               |               |
| in. Hg. at:        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 310-257       | 310-25        | 260-25        |
| critical alt. ft.  | 5-40.2-15,000 | 75-42.-15,000 | 75-36.0-15000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 310-2         | 310-2         | 260-2         |
| sea level alt. ft. | 575-38.6-S.L. | 575-40.0-S.L. | 575-34.1-S.L. |
+--------------------+---------------+---------------+---------------+
| Takeoff (5 min.)   |               |               |               |
| hp., rpm, in. Hg.  |               |               |               |
| at:                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 310-257       | 310-257       | 260-25        |
| critical alt. ft.  | 5-40.2-15,000 | 5-41.5-15,000 | 75-36.0-15000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 310-2         | 310-2         | 260-2         |
| sea level alt.,    | 575-38.6-S.L. | 575-40.0-S.L. | 575-34.1-S.L. |
| ft.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Fuel (minimum      | 100/100LL     | \- -          | \- -          |
| grade aviation     |               |               |               |
|                    |               |               |               |
| gasoline)          |               |               |               |
+--------------------+---------------+---------------+---------------+
| Lubricating oil    | Lycoming      | \- -          | \- -          |
| (lubrication       | Spec. No.     |               |               |
| should             | 301-F         |               |               |
|                    |               |               |               |
| conform to the     | Service       |               |               |
| specification as   | Instruction   |               |               |
| listed or to       |               |               |               |
| subsequent         | No. 1014      |               |               |
| revisions thereto) |               |               |               |
+--------------------+---------------+---------------+---------------+
| Bore and stroke,   | 5.125 X 4.375 | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Displacement, cu.  | 541.5         | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Compression ratio  | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Weight (dry) lb.   | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| C.G. location      |               |               |               |
| (with starter and  |               |               |               |
|                    |               |               |               |
| alternator         |               |               |               |
| installed)         |               |               |               |
+--------------------+---------------+---------------+---------------+
| From front face of | 22.22         | \- -          | 19.47         |
| prop. mounting     |               |               |               |
|                    |               |               |               |
| flange, in.        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Off crankshaft     | 0.88 below &  | \- -          | 3.00 below &  |
| C.L., in.          | 0.18 right    |               | 0.11 left     |
+--------------------+---------------+---------------+---------------+
| Propeller shaft    | Type 2        | \- -          | \- -          |
| flange, SAE A.S.   | modified      |               |               |
| 127                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Crankshaft dampers | One 5th order | \- -          | \- -          |
| (torsional)        |               |               |               |
|                    | One 6th order | \- -          | One 6th order |
|                    |               |               | (Note 8)      |
+--------------------+---------------+---------------+---------------+
| Fuel injection     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Turbocharger       | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition, dual     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition timing    | 20            | \- -          | \- -          |
| °BTC               |               |               |               |
+--------------------+---------------+---------------+---------------+
| Spark plugs        | Note 6        | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Oil sump capacity, | 12            | \- -          | \- -          |
| qt.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Usable oil, qt.    | 9 1/4         | \- -          | \- -          |
| (20° nose up or    |               |               |               |
| down)              |               |               |               |
+--------------------+---------------+---------------+---------------+
| NOTES - as         | 1-7, 9, 10    | 1-7, 9, 10    | 1-10          |
| applicable         |               |               |               |
+--------------------+---------------+---------------+---------------+

"- -" indicates "same as preceding model."

+--------------------+---------------+---------------+---------------+
| Model Lycoming     | TIO-540-H1A   | >             | TIO-540-J2B,  |
|                    |               |  TIO-540-F2BD | -J2BD, -N2BD, |
|                    |               | >             | LTIO-540-J2B, |
|                    |               | >             | -J2BD,        |
|                    |               | LTIO-540-F2BD |               |
|                    |               |               | -N2BD         |
+--------------------+---------------+---------------+---------------+
| Type 6HOA Direct   |               |               |               |
| Drive Turbocharged |               |               |               |
+--------------------+---------------+---------------+---------------+
| Rating (See Notes  |               |               |               |
| 4 and 13)          |               |               |               |
+--------------------+---------------+---------------+---------------+
| Maximum continuous |               |               |               |
| hp., rpm,          |               |               |               |
|                    |               |               |               |
| in. Hg. at:        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 270-257       | 325-25        | 350-25        |
| critical alt. ft.  | 5-37.5-15,000 | 75-46.0-15000 | 75-46.0-15000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 270-2         | 325-2         | 350-2         |
| sea level alt. ft. | 575-35.9-S.L. | 575-43.5-S.L. | 575-43.0-S.L. |
+--------------------+---------------+---------------+---------------+
| Takeoff (5 min.)   |               |               |               |
| hp., rpm, in. Hg.  |               |               |               |
| at:                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 270-257       | 325-25        | 350-25        |
| critical alt. ft.  | 5-37.5-15,000 | 75-46.0-15000 | 75-46.0-15000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 270-2         | 325-2         | 350-25        |
| sea level alt.,    | 575-35.9-S.L. | 575-43.5-S.L. | 75-43.0-15000 |
| ft.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Fuel (minimum      | 100/100LL     | \- -          | \- -          |
| grade aviation     |               |               |               |
|                    |               |               |               |
| gasoline)          |               |               |               |
+--------------------+---------------+---------------+---------------+
| Lubricating oil    | Lycoming      | \- -          | \- -          |
| (lubrication       | Spec. No.     |               |               |
| should             | 301-F         |               |               |
|                    |               |               |               |
| conform to the     | Service       |               |               |
| specification as   | Instruction   |               |               |
| listed or to       |               |               |               |
| subsequent         | No. 1014      |               |               |
| revisions thereto) |               |               |               |
+--------------------+---------------+---------------+---------------+
| Bore and stroke,   | 5.125 X 4.375 | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Displacement, cu.  | 541.5         | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Compression ratio  | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Weight (dry) lb.   | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| C.G. location      |               |               |               |
| (with starter and  |               |               |               |
|                    |               |               |               |
| alternator         |               |               |               |
| installed)         |               |               |               |
+--------------------+---------------+---------------+---------------+
| From front face of | 19.47         | 22.19         | 22.75         |
| prop. mounting     |               |               |               |
|                    |               |               |               |
| flange, in.        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Off crankshaft     | 3.00 below &  | 0.88 below &  | 0.75 below &  |
| C.L., in.          | 0.11 left     | 0.18 right    | 0.16 right    |
+--------------------+---------------+---------------+---------------+
| Propeller shaft    | Type 2        | \- -          | \- -          |
| flange, SAE A.S.   | modified      |               |               |
| 127                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Crankshaft dampers | One 5th order | \- -          | \- -          |
| (torsional)        |               |               |               |
|                    | One 6th order | One 6th order | \- -          |
|                    | (Note 8)      |               |               |
+--------------------+---------------+---------------+---------------+
| Fuel injection     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Turbocharger       | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition, dual     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition timing    | 20            | \- -          | \- -          |
| °BTC               |               |               |               |
+--------------------+---------------+---------------+---------------+
| Spark plugs        | Note 6        | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Oil sump capacity, | 12            | \- -          | \- -          |
| qt.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Usable oil, qt.    | 9 1/4         | \- -          | \- -          |
| (20° nose up or    |               |               |               |
| down)              |               |               |               |
+--------------------+---------------+---------------+---------------+
| NOTES \-- as       | 1-10          | 1-7, 9, 10    | 1-7, 9, 10    |
| applicable         |               |               |               |
+--------------------+---------------+---------------+---------------+

"- -" indicates "same as preceding model."

+--------------------+---------------+---------------+---------------+
| Model Lycoming     | TIO-540-R2AD  | >             | TIO-540-K1AD  |
|                    |               |  TIO-540-C1A, |               |
|                    | LTIO-540-R2AD | > -G1A        | LTIO-540-K1AD |
+--------------------+---------------+---------------+---------------+
| Type 6HOA Direct   |               |               |               |
| Drive Turbocharged |               |               |               |
+--------------------+---------------+---------------+---------------+
| Rating (See Note   |               |               |               |
| 4)                 |               |               |               |
+--------------------+---------------+---------------+---------------+
| Maximum continuous |               |               |               |
| hp., rpm,          |               |               |               |
|                    |               |               |               |
| in. Hg. at:        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 340-25        | 250-25        | 250-25        |
| critical alt. ft.  | 75-44.0-15000 | 75-34.0-15000 | 75-34.0-15000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 350-2         | 250-2         | 250-2         |
| sea level alt. ft. | 575-44.0-S.L. | 575-33.0-S.L. | 575-34.0-S.L. |
+--------------------+---------------+---------------+---------------+
| Takeoff (5 min.)   |               |               |               |
| hp., rpm, in. Hg.  |               |               |               |
| at:                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 340-25        | 250-25        | 250-25        |
| critical alt. ft.  | 75-44.0-15000 | 75-34.0-15000 | 75-34.0-15000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 350-2         | 250-2         | 250-2         |
| sea level alt.,    | 575-44.0-S.L. | 575-33.0-S.L. | 575-34.0-S.L. |
| ft.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Fuel (minimum      | 100/100LL     | \- -          | \- -          |
| grade aviation     |               |               |               |
|                    |               |               |               |
| gasoline)          |               |               |               |
+--------------------+---------------+---------------+---------------+
| Lubricating oil    | Lycoming      | \- -          | \- -          |
| (lubrication       | Spec. No.     |               |               |
| should             | 301-F         |               |               |
|                    |               |               |               |
| conform to the     | Service       |               |               |
| specification as   | Instruction   |               |               |
| listed             |               |               |               |
|                    | No. 1014      |               |               |
| or to subsequent   |               |               |               |
| revisions thereto) |               |               |               |
+--------------------+---------------+---------------+---------------+
| Bore and stroke,   | 5.125 X 4.375 | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Displacement, cu.  | 541.5         | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Compression ratio  | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Weight (dry) lb.   | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| C.G. location      |               |               |               |
| (with starter and  |               |               |               |
|                    |               |               |               |
| alternator         |               |               |               |
| installed)         |               |               |               |
+--------------------+---------------+---------------+---------------+
| From front face of | 22.75         | 19.27         | 21.0          |
| prop. mounting     |               |               |               |
|                    |               |               |               |
| flange, in.        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Off crankshaft     | 0.75 below &  | 2.30 below &  | 0.50 below &  |
| C.L., in.          | 0.16 right    | 0.23 left     | 0.31 left     |
+--------------------+---------------+---------------+---------------+
| Propeller shaft    | Type 2        |               | \- -          |
| flange, SAE A.S.   | modified      |               |               |
| 127                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Crankshaft dampers | One 5th order | \- -          | \- -          |
| (torsional)        |               |               |               |
|                    | One 6th order | One 6th order | \- -          |
|                    |               | (Note 8)      |               |
+--------------------+---------------+---------------+---------------+
| Fuel injection     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Turbocharger       | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition, dual     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition timing    | 20            | \- -          | \- -          |
| °BTC               |               |               |               |
+--------------------+---------------+---------------+---------------+
| Spark plugs        | Note 6        | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Oil sump capacity, | 12            | \- -          | 8             |
| qt.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Usable oil, qt.    | 9 1/4         | \- -          | 6             |
| (20° nose up or    |               |               |               |
| down)              |               |               |               |
+--------------------+---------------+---------------+---------------+
| NOTES - as         | 1-7, 9, 10,   | 1-10          | 1-10          |
| applicable         | 11, 13        |               |               |
+--------------------+---------------+---------------+---------------+

"- -" indicates "same as preceding model."

+--------------------+---------------+---------------+---------------+
| Model Lycoming     | TIO-540-S1AD  | >             | TIO-540-U2A   |
|                    |               |  TIO-540-T2AD |               |
|                    |               |               | LTIO-540-U2A  |
+--------------------+---------------+---------------+---------------+
| Type 6HOA Direct   |               |               |               |
| Drive Turbocharged |               |               |               |
+--------------------+---------------+---------------+---------------+
| Rating (See Note   |               |               |               |
| 4)                 |               |               |               |
+--------------------+---------------+---------------+---------------+
| Maximum continuous |               |               |               |
| hp., rpm,          |               |               |               |
|                    |               |               |               |
| in. Hg. at:        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 295-27        | 330-24        | 350-25        |
| critical alt. ft.  | 00-36.0-16000 | 00-43.0-12000 | 00-42.2-12000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 300-2         | 330-2         | 350-2         |
| sea level alt. ft. | 700-36.0-S.L. | 400-40.5-S.L. | 500-41.2-S.L. |
|                    | & 12000 ft.   |               |               |
+--------------------+---------------+---------------+---------------+
| Takeoff (5 min.)   |               |               |               |
| hp., rpm, in. Hg.  |               |               |               |
| at:                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 295-27        | 330-24        | 350-25        |
| critical alt. ft.  | 00-36.0-16000 | 00-43.0-12000 | 00-42.2-12000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 300-2         | 330-2         | 350-2         |
| sea level alt.,    | 700-36.0-S.L. | 400-43.0-S.L. | 500-41.2-S.L. |
| ft.                | & 12000 ft.   |               |               |
+--------------------+---------------+---------------+---------------+
| Fuel (minimum      | 100/100LL     | \- -          | \- -          |
| grade aviation     |               |               |               |
|                    |               |               |               |
| gasoline)          |               |               |               |
+--------------------+---------------+---------------+---------------+
| Lubricating oil    | Lycoming      | \- -          | \- -          |
| (lubrication       | Spec. No.     |               |               |
| should             | 301-F         |               |               |
|                    |               |               |               |
| conform to the     | Service       |               |               |
| specification as   | Instruction   |               |               |
| listed             |               |               |               |
|                    | No. 1014      |               |               |
| or to subsequent   |               |               |               |
| revisions thereto) |               |               |               |
+--------------------+---------------+---------------+---------------+
| Bore and stroke,   | 5.125 X 4.375 | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Displacement, cu.  | 541.5         | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Compression ratio  | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Weight (dry) lb.   | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| C.G. location      |               |               |               |
| (with starter and  |               |               |               |
|                    |               |               |               |
| alternator         |               |               |               |
| installed)         |               |               |               |
+--------------------+---------------+---------------+---------------+
| From front face of | 18.58         | 22.75         | 20.38         |
| prop. mounting     |               |               |               |
|                    |               |               |               |
| flange, in.        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Off crankshaft     | 1.31 below &  | 0.75 below &  | 1.4 below &   |
| C.L., in.          | 1.00 right    | 0.16 right    | 0.25 right    |
+--------------------+---------------+---------------+---------------+
| Propeller shaft    | Type 2        | \- -          | \- -          |
| flange, SAE A.S.   | modified      |               |               |
| 127                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Crankshaft dampers | One 5th order | \- -          | \- -          |
| (torsional)        |               |               |               |
|                    | One 6th order | \- -          | \- -          |
|                    | (Note 8)      |               |               |
+--------------------+---------------+---------------+---------------+
| Fuel injection     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Turbocharger       | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition, dual     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition timing    | 20            | \- -          | \- -          |
| °BTC               |               |               |               |
+--------------------+---------------+---------------+---------------+
| Spark plugs        | Note 6        | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Oil sump capacity, | 12            | \- -          | \- -          |
| qt.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Usable oil, qt.    | 9 3/4         | \- -          | \- -          |
| (20° nose up or    |               |               |               |
| down)              |               |               |               |
+--------------------+---------------+---------------+---------------+
| NOTES - as         | 1-10          | 1-7, 9. 10    | 1-7, 9, 10    |
| applicable         |               |               |               |
+--------------------+---------------+---------------+---------------+

"- -" indicates "same as preceding model."

+--------------------+---------------+---------------+---------------+
| Model Lycoming     | TIO-540-V2AD  | > TIO-540-W2A | TI            |
|                    |               | >             | O-540-AA1AD\* |
|                    | LTIO-540-V2AD | >             |               |
|                    |               |  LTIO-540-W2A | TIO-540-AB1AD |
|                    | (See Note 14) | >             |               |
|                    |               | > (See Note   | TIO-540-AB1BD |
|                    |               | > 14)         |               |
+--------------------+---------------+---------------+---------------+
| Type 6HOA Direct   |               |               |               |
| Drive Turbocharged |               |               |               |
+--------------------+---------------+---------------+---------------+
| Rating (See Note   |               |               |               |
| 4)                 |               |               |               |
+--------------------+---------------+---------------+---------------+
| Maximum continuous |               |               |               |
| hp., rpm,          |               |               |               |
|                    |               |               |               |
| in. Hg. at:        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 340-26        | 350-26        | 250-25        |
| critical alt. ft.  | 00-42.0-18000 | 00-44.2-15000 | 75-32.5-15000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 350-2         | 350-2         | 250-2         |
| sea level alt. ft. | 600-42.0-S.L. | 600-44.2-S.L. | 575-32.5-S.L. |
+--------------------+---------------+---------------+---------------+
| Takeoff (5 min.)   |               |               |               |
| hp., rpm, in. Hg.  |               |               |               |
| at:                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Standard density   | 340-26        | 350-26        | 250-25        |
| critical alt. ft.  | 00-42.0-18000 | 00-44.2-15000 | 75-32.5-15000 |
+--------------------+---------------+---------------+---------------+
| Standard density   | 350-2         | 350-2         | 250-2         |
| sea level alt.,    | 600-42.0-S.L. | 600-44.2-S.L. | 575-32.5-S.L. |
| ft.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Fuel (minimum      | 100/100LL     | \- -          | \- -          |
| grade aviation     |               |               |               |
|                    |               |               |               |
| gasoline)          |               |               |               |
+--------------------+---------------+---------------+---------------+
| Lubricating oil    | Lycoming      | \- -          | \- -          |
| (lubrication       | Spec. No.     |               |               |
| should             | 301-F         |               |               |
|                    |               |               |               |
| conform to the     | Service       |               |               |
| specification as   | Instruction   |               |               |
| listed or to       |               |               |               |
| subsequent         | No. 1014      |               |               |
| revisions thereto) |               |               |               |
+--------------------+---------------+---------------+---------------+
| Bore and stroke,   | 5.125 X 4.375 | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Displacement, cu.  | 541.5         | \- -          | \- -          |
| in.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Compression ratio  | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Weight (dry) lb.   | See Note 10.  | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| C.G. location      |               |               |               |
| (with starter and  |               |               |               |
|                    |               |               |               |
| alternator         |               |               |               |
| installed)         |               |               |               |
+--------------------+---------------+---------------+---------------+
| From front face of | 23.05         | 22.10         | 18.91         |
| prop. mounting     |               |               |               |
|                    |               |               |               |
| flange, in.        |               |               |               |
+--------------------+---------------+---------------+---------------+
| Off crankshaft     | 0.59 below &  | 0.10 below &  | 2.20 below &  |
| C.L., in.          | 0.14 right    | 0.48 right    | 0.67 left     |
+--------------------+---------------+---------------+---------------+
| Propeller shaft    | Type 2        | \- -          | \- -          |
| flange, SAE A.S.   | modified      |               |               |
| 127                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Crankshaft dampers | One 5th order | \- -          | \- -          |
| (torsional)        |               |               |               |
|                    | One 6th order | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Fuel injection     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Turbocharger       | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition, dual     | Note 10       | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Ignition timing    | 20            | \- -          | \- -          |
| °BTC               |               |               |               |
+--------------------+---------------+---------------+---------------+
| Spark plugs        | Note 6        | \- -          | \- -          |
+--------------------+---------------+---------------+---------------+
| Oil sump capacity, | 12            | \- -          | \- - \*\*     |
| qt.                |               |               |               |
+--------------------+---------------+---------------+---------------+
| Usable oil, qt.    | 9 1/4         | \- -          | \- - \*\*\*   |
| (20° nose up or    |               |               |               |
| down)              |               |               |               |
+--------------------+---------------+---------------+---------------+
| NOTES - as         | 1-7, 9, 10,   | 1-7, 9, 10,   | 1-7, 9, 10,   |
| applicable         | 14            | 14            | 15            |
+--------------------+---------------+---------------+---------------+

"- -" indicates "same as preceding model."

\*TIO-540-AA1AD Model is approved with an alternate rating of 270hp/2575
rpm from S.L. to 15,000 ft.

\*\* 10 for AA1AD

\*\*\* 7 1/4 for AA1AD.

+--------------------+----------------+---------------+---------------+
| Model Lycoming     | > TIO-540-AE2A | TIO-540-AF1A  | >             |
|                    |                |               |  TIO-540-AG1A |
|                    |                | TIO-540-AF1B  |               |
+--------------------+----------------+---------------+---------------+
| Type 6HOA Direct   |                |               |               |
| Drive Turbocharged |                |               |               |
+--------------------+----------------+---------------+---------------+
| Rating (See Note   |                |               |               |
| 4)                 |                |               |               |
+--------------------+----------------+---------------+---------------+
| Maximum continuous |                |               |               |
| hp., rpm, in. Hg.  |                |               |               |
| at:                |                |               |               |
+--------------------+----------------+---------------+---------------+
| Standard density   | 350-2          | 270-25        | 270 - 2575 -  |
| critical alt. ft.  | 500-42.0-20000 | 75-36.5-20000 | 36.5 -15000   |
+--------------------+----------------+---------------+---------------+
| Standard density   | 350-           | 270-2         | 270 - 2575 -  |
| sea level alt. ft. | 2500-42.0-S.L. | 575-35.0-S.L. | 36.5 - SL     |
+--------------------+----------------+---------------+---------------+
| Takeoff (5 min.)   |                |               |               |
| hp., rpm, in. Hg.  |                |               |               |
| at:                |                |               |               |
+--------------------+----------------+---------------+---------------+
| Standard density   | 350-2          | 270-25        | 270 - 2575 -  |
| critical alt. ft.  | 500-42.0-20000 | 75-36.5-20000 | 36.5 -15000   |
+--------------------+----------------+---------------+---------------+
| Standard density   | 350-           | 270-2         | 270 - 2575 -  |
| sea level alt.,    | 2500-42.0-S.L. | 575-35.0-S.L. | 36.5 - SL     |
| ft.                |                |               |               |
+--------------------+----------------+---------------+---------------+
| Fuel (minimum      | 100/100LL      | \- -          | \- -          |
| grade aviation     |                |               |               |
| gasoline)          |                |               |               |
+--------------------+----------------+---------------+---------------+
| Lubricating oil    | Lycoming Spec. | \- -          | \- -          |
| (lubrication       | No. 301-F      |               |               |
| should conform to  |                |               |               |
| the specification  | Service        |               |               |
| as                 | Instruction    |               |               |
|                    |                |               |               |
| listed or to       | No. 1014       |               |               |
| subsequent         |                |               |               |
| revisions thereto) |                |               |               |
+--------------------+----------------+---------------+---------------+
| Bore and stroke,   | 5.125 X 4.375  | \- -          | \- -          |
| in.                |                |               |               |
+--------------------+----------------+---------------+---------------+
| Displacement, cu.  | 541.5          | \- -          | \- -          |
| in.                |                |               |               |
+--------------------+----------------+---------------+---------------+
| Compression ratio  | See Note 10.   | \- -          | \- -          |
+--------------------+----------------+---------------+---------------+
| Weight (dry) lb.   | See Note 10.   | \- -          | \- -          |
+--------------------+----------------+---------------+---------------+
| C.G. location      |                |               |               |
| (with starter and  |                |               |               |
| alternator         |                |               |               |
| installed)         |                |               |               |
+--------------------+----------------+---------------+---------------+
| From front face of | 18.88          | 18.30         | 19.00         |
| prop. mounting     |                |               |               |
| flange, in.        |                |               |               |
+--------------------+----------------+---------------+---------------+
| Off crankshaft     | 0.95 below &   | 2.30 below &  | 1.75 below &  |
| C.L., in.          | 0.63 left      | 0.64 left     | 1.20 left     |
+--------------------+----------------+---------------+---------------+
| Propeller shaft    | Type 2         | \- -          | \- -          |
| flange, SAE A.S.   | modified       |               |               |
| 127                |                |               |               |
+--------------------+----------------+---------------+---------------+
| Crankshaft dampers | One 5th order  | \- -          | \- -          |
| (torsional)        |                |               |               |
|                    | One 6th order  | \- -          | \- -          |
+--------------------+----------------+---------------+---------------+
| Fuel injection     | Note 10        | \- -          | \- -          |
+--------------------+----------------+---------------+---------------+
| Turbocharger       | Note 10        | \- -          | \- -          |
+--------------------+----------------+---------------+---------------+
| Ignition, dual     | Note 10        | \- -          | \- -          |
+--------------------+----------------+---------------+---------------+
| Ignition timing    | 20             | \- -          | \- -          |
| °BTC               |                |               |               |
+--------------------+----------------+---------------+---------------+
| Spark plugs        | Note 6         | \- -          | \- -          |
+--------------------+----------------+---------------+---------------+
| Oil sump capacity, | 12             | 10            | 10            |
| qt.                |                |               |               |
+--------------------+----------------+---------------+---------------+
| Usable oil, qt.    | 9 1/4          | 7 1/4         | 5             |
| (20° nose up or    |                |               |               |
| down)              |                |               |               |
+--------------------+----------------+---------------+---------------+
| NOTES - as         | 1-7, 9, 10, 11 | 1-7, 9, 10    | 1-10, 12      |
| applicable         |                |               |               |
+--------------------+----------------+---------------+---------------+

"- -" indicates "same as preceding model."

+----------------------+---------------+---------------+---------------+
| Model Lycoming       | TIO-540-AH1A  | TIO-540-AJ1A  | TIO-540-AK1A  |
+----------------------+---------------+---------------+---------------+
| Type 6HOA Direct     |               |               |               |
| Drive Turbocharged   |               |               |               |
+----------------------+---------------+---------------+---------------+
| Rating (See Note 4)  |               |               |               |
+----------------------+---------------+---------------+---------------+
| Maximum continuous   |               |               |               |
| hp., rpm, in. Hg.    |               |               |               |
| at:                  |               |               |               |
+----------------------+---------------+---------------+---------------+
| Standard density     | 300 - 2500 -  | 310 - 2500 -  | 235 -- 2400   |
| critical alt. ft.    | 38.0 -12000   | 39.0 -- 14000 | -- 32.0       |
|                      |               |               | -15000        |
+----------------------+---------------+---------------+---------------+
| Standard density sea | 300 - 2500 -  | 310 - 2500 -  | 235 -- 2400   |
| level alt. ft.       | 38.0 - SL     | 39.0 - SL     | -- 32.0 - SL  |
+----------------------+---------------+---------------+---------------+
| Takeoff (5 min.)     |               |               |               |
| hp., rpm, in. Hg.    |               |               |               |
| at:                  |               |               |               |
+----------------------+---------------+---------------+---------------+
| Standard density     | 300 - 2500 -  | 310 - 2500 -  | 235 -- 2400   |
| critical alt. ft.    | 38.0 --12000  | 39.0 -- 14000 | -- 32.0       |
|                      |               |               | -15000        |
+----------------------+---------------+---------------+---------------+
| Standard density sea | 300 - 2500 -  | 310 - 2500 -  | 235 -- 2400   |
| level alt., ft.      | 38.0 - SL     | 39.0 - SL     | -- 32.0 - SL  |
+----------------------+---------------+---------------+---------------+
| Fuel (minimum grade  | 100/100LL     | \- -          | \--           |
| aviation gasoline)   |               |               |               |
+----------------------+---------------+---------------+---------------+
| Lubricating oil      | Lycoming      | \- -          | \--           |
| (lubrication should  | Spec. No.     |               |               |
| conform to the       | 301-F         |               |               |
| specification as     |               |               |               |
|                      | Service       |               |               |
| listed or to         | Instruction   |               |               |
| subsequent revisions |               |               |               |
| thereto)             | No. 1014      |               |               |
+----------------------+---------------+---------------+---------------+
| Bore and stroke, in. | 5.125         | \- -          | \--           |
+----------------------+---------------+---------------+---------------+
| Displacement, cu.    | 4.375         | \- -          | \--           |
| in.                  |               |               |               |
+----------------------+---------------+---------------+---------------+
| Compression ratio    | See Note 10.  | \- -          | \--           |
+----------------------+---------------+---------------+---------------+
| Weight (dry) lb.     | See Note 10.  | \- -          | \--           |
+----------------------+---------------+---------------+---------------+
| C.G. location (with  |               |               |               |
| starter and          |               |               |               |
| alternator           |               |               |               |
| installed)           |               |               |               |
+----------------------+---------------+---------------+---------------+
| From front face of   | 18.70         | 18.50\*       | 18.94\*       |
| prop. mounting       |               |               |               |
| flange, in.          |               |               |               |
+----------------------+---------------+---------------+---------------+
| Off crankshaft C.L., | 1.87 below &  | 0.75 below &  | 1.50 below &  |
| in.                  | 1.00 right    | 1.13 left\*   | 1.25 left\*   |
+----------------------+---------------+---------------+---------------+
| Propeller shaft      | Type 2        | \- -          | \--           |
| flange, SAE A.S. 127 | modified      |               |               |
+----------------------+---------------+---------------+---------------+
| Crankshaft dampers   | One 5th order | \- -          | \--           |
| (torsional)          |               |               |               |
|                      | One 6th order |               |               |
+----------------------+---------------+---------------+---------------+
| Fuel injection       | Note 10       | \- -          | \--           |
+----------------------+---------------+---------------+---------------+
| Turbocharger         | Note 10       | \- -          | \--           |
+----------------------+---------------+---------------+---------------+
| Ignition, dual       | Note 10       | \- -          | \--           |
+----------------------+---------------+---------------+---------------+
| Ignition timing °BTC | 20            | \- -          | 23\*\*        |
+----------------------+---------------+---------------+---------------+
| Spark plugs          | Note 6        | \- -          | \--           |
+----------------------+---------------+---------------+---------------+
| Oil sump capacity,   | 12            | 11            | 8             |
| qt.                  |               |               |               |
+----------------------+---------------+---------------+---------------+
| Usable oil, qt. (20° | 9 1/4         | 5 1/2         | 4             |
| nose up or down)     |               |               |               |
+----------------------+---------------+---------------+---------------+
| NOTES - as           | 1-10, 12      | \- -          | \--           |
| applicable           |               |               |               |
+----------------------+---------------+---------------+---------------+

"- -" indicates "same as preceding model."

\* No alternator installed

\*\* See Note 16

Certification Basis:

[Regulations and Amendments]{.underline} Date Type Certificate

[Model]{.underline} [Date of Application]{.underline} [E14EA
Issued/Revised]{.underline}

CAR 13 effective June 15, 1956 TIO-540-A1A May 26, 1964 December 6, 1965

as amended by 13-1, 13-2, 13-3, 13-4 TIO-540-A1B October 6, 1967 October
9, 1967

TIO-540-A2A March 26, 1968 April 1, 1968

TIO-540-A2B March 26, 1968 April 1, 1968

TIO-540-C1A September 7, 1967 June 6, 1968

TIO-540-E1A September 3, 1970 September 18, 1970

TIO-540-G1A September 2, 1970 September 18, 1970

TIO-540-A1C November 17, 1970 January 6, 1971

TIO-540-A2C November 17, 1970 January 6, 1971

TIO-540-H1A April 8, 1971 April 16, 1971

TIO-540-F2BD April 20, 1970 July 23, 1971

Certification Basis: (cont'd)

[Regulations and Amendments]{.underline} Date Type Certificate

[Model]{.underline} [Date of Application]{.underline} [E14EA
Issued/Revised]{.underline}

LTIO-540-F2BD February 9, 1972 February 16, 1972

L/TIO-540-J2BD August 25, 1971 April 7, 1972

L/TIO-540-K1AD December 4, 1973 February 28, 1974

L/TIO-540-N2BD January 29, 1973 February 16, 1973

TIO-540-R2AD April 23, 1975 September 25, 1975

LTIO-540-R2AD October 7, 1977 October 13, 1977

TIO-540-S1AD January 31, 1977 June 14, 1977

TIO-540-T2AD February 17, 1981 March 5, 1981

L/TIO-540-U2A June 2, 1981 February 12, 1982

L/TIO-540-J2B August 20, 1981 September 9, 1981

L/TIO-540-V2AD December 22, 1981 January 31, 1983

L/TIO-540-W2A October 29, 1982 August 17, 1984

TIO-540-AB1AD June 14, 1984 January 16, 1985

TIO-540-AA1AD February 20, 1985 June 25, 1985

TIO-540-AE2A March 9, 1987 August 12, 1988

TIO-540-AF1A September 13, 1988 June 23, 1989

TIO-540-AB1BD May 18, 1993 August 11, 1993

TIO-540-AG1A December 1,1994 June 20, 1995

TIO-540-AF1B December 7, 1995 January 25, 1996

TIO-540-AH1A February 12, 1997 June 25, 1997

TIO-540-AJ1A March 5, 1998 April 30, 1998

TIO-540-AK1A February 22, 2000 February 2, 2001

Production basis: Production Certificate No. 3.

NOTE 1. Maximum permissible temperatures:

Cylinder head (well type thermocouple) 500°F (480°F model - W2A, -V2AD,
-AJ1A)

Cylinder base Note 5

Oil inlet 245°F

Exhaust gas \*1650° F (See Note 4 for turbo inlet location)

Fuel injector inlet air 400°F

Compressor temperature rise Not applicable (see Note 4)

\*TIO-540-AE2A, -AF1A, -AF1B models are approved for 1750°F E.G.T.

model TIO-540-AJ1A approved for 1675°F E.G.T., model TIO-540-AK1A
approved for 1685°F E.G.T.

NOTE 2. Pressure Limits:

+------------------------------------------+--------+--------+--------+
| Fuel pressure (p.s.i. above injector     | M      | M      | Idle   |
| inlet air pressure)                      | inimum | aximum | (min   |
|                                          |        |        |        |
|                                          | (p     | (p     | p      |
|                                          | .s.i.) | .s.i.) | .s.i.) |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-A models     | 25     | 45     | 12     |
| except -A1C, -A2C)                       |        |        |        |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-A1C, -A2C ,  | 25     | 55     | 12     |
| -AJ1A models)                            |        |        |        |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-C, -E, -G,   | 18     | 45     | 12     |
| -H models)                               |        |        |        |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-F model)     | 30     | 65     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-J, -N model) | 34     | 65     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-K model)     | 20     | 45     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-R model)     | 34     | 65     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-S model)     | 25     | 65     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-T model)     | 34     | 65     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-U model)     | 30     | 65     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-V, -AH       | 27     | 65     | 12     |
| models)                                  |        |        |        |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-W model)     | 31     | 65     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-AB1AD,       | 20     | 65     | 12     |
| -AB1BD models)                           |        |        |        |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-AA1AD model) | 20     | 65     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-AE2A model)  | 29     | 65     | 12     |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-AF1A, -AF1B  | 24     | 55     | 12     |
| models)                                  |        |        |        |
+------------------------------------------+--------+--------+--------+
| at inlet to fuel injector (-AG1A, -AK1A  | 20     | 55     | 12     |
| models)                                  |        |        |        |
+------------------------------------------+--------+--------+--------+

NOTE 2. (cont'd)

+------------------------------------------+--------+--------+--------+
| Fuel Pressure (p.s.i. above ambient air  | M      | M      | Idle   |
| pressure)                                | inimum | aximum | (min   |
|                                          |        |        |        |
|                                          | (p     | (p     | p      |
|                                          | .s.i.) | .s.i.) | .s.i.) |
+------------------------------------------+--------+--------+--------+
| at inlet to engine fuel pump (-A, -F,    | -2     | 65     | \--    |
| -R, -S, -U, -V, -W)                      |        |        |        |
+------------------------------------------+--------+--------+--------+
| (-J, -N, -T, -AE2A, -AH1A, -AJ1A models) |        |        |        |
+------------------------------------------+--------+--------+--------+
| at inlet to engine fuel pump (-C, -E,    | -2     | 55     | \--    |
| -G, -H, -K -AF1A,)                       |        |        |        |
|                                          |        |        |        |
| (-AF1B, -AG1A, -AK1A models)             |        |        |        |
+------------------------------------------+--------+--------+--------+

+------------------------------------------+--------+--------+--------+
| Manifold Pressure (cumulative total with | M      |        |        |
| altitude adjustment)                     | aximum |        |        |
|                                          |        |        |        |
|                                          | (in.   |        |        |
|                                          | Hg     |        |        |
|                                          | Abs)   |        |        |
+------------------------------------------+--------+--------+--------+
| -A models (except -A1C, -A2C)            | 45     |        |        |
+------------------------------------------+--------+--------+--------+
| -A1C, -A2C models                        | 46     |        |        |
+------------------------------------------+--------+--------+--------+
| -C, -E, -G models                        | 39.5   |        |        |
+------------------------------------------+--------+--------+--------+
| -H models                                | 40.7   |        |        |
+------------------------------------------+--------+--------+--------+
| -F, -J, -N models                        | 49     |        |        |
+------------------------------------------+--------+--------+--------+
| -K models                                | 34.5   |        |        |
+------------------------------------------+--------+--------+--------+
| -R models                                | 44     |        |        |
+------------------------------------------+--------+--------+--------+
| -S models                                | 36     |        |        |
+------------------------------------------+--------+--------+--------+
| -T models                                | 45.2   |        |        |
+------------------------------------------+--------+--------+--------+
| -U models, AE2A                          | 42.0   |        |        |
+------------------------------------------+--------+--------+--------+
| -W models                                | 50.6   |        |        |
+------------------------------------------+--------+--------+--------+
| -AA1AD, -AB1AD, -AB1BD, -AF1A, -AF1B,    | 38     |        |        |
|                                          |        |        |        |
| -AH1A models                             |        |        |        |
+------------------------------------------+--------+--------+--------+
| -AG1A, -AJ1A models                      | 39     |        |        |
+------------------------------------------+--------+--------+--------+
| -AK1A model                              | 32     |        |        |
+------------------------------------------+--------+--------+--------+
| Oil Pressure                             | M      | M      |        |
|                                          | inimum | aximum |        |
|                                          |        |        |        |
|                                          | (p     | (p     |        |
|                                          | .s.i.) | .s.i.) |        |
+------------------------------------------+--------+--------+--------+
| Normal (all models)                      | > 55   | > 95   |        |
+------------------------------------------+--------+--------+--------+
| Idle (all models)                        | > 25   | > \--  |        |
+------------------------------------------+--------+--------+--------+
| Starting and warm-up (all models)        | > \--  | > 115  |        |
+------------------------------------------+--------+--------+--------+
|                                          |        |        |        |
+------------------------------------------+--------+--------+--------+
| Turbocharger exhaust back pressure       |        | > 0.5  |        |
+------------------------------------------+--------+--------+--------+
|                                          |        |        |        |
+------------------------------------------+--------+--------+--------+

NOTE 3. The following accessory provisions are available:

<table>
<colgroup>
<col style="width: 10%" />
<col style="width: 9%" />
<col style="width: 5%" />
<col style="width: 5%" />
<col style="width: 6%" />
<col style="width: 12%" />
<col style="width: 6%" />
<col style="width: 6%" />
<col style="width: 4%" />
<col style="width: 4%" />
<col style="width: 8%" />
<col style="width: 3%" />
<col style="width: 2%" />
<col style="width: 5%" />
<col style="width: 8%" />
</colgroup>
<tbody>
<tr class="odd">
<td></td>
<td><p>-A1A, -A1B,</p>
<p>-A2A, -A2B,</p>
<p>-A1C, -A2C,</p>
<p>-C1A, -E1A,</p>
<p>-G1A, -H1A,</p>
<p>-J2B, -U2A,</p></td>
<td>AK1A</td>
<td></td>
<td>-AF1A</td>
<td><p>-F2BD, -J2BD,</p>
<p>-N2BD, -R2AD,</p>
<p>-S1AD, -T2AD,</p>
<p>-U2A, -V2AD,</p>
<p>-W2A, -J2B,</p>
<p>-AB1AD, -AA1AD,</p></td>
<td></td>
<td></td>
<td colspan="2"><p>Rotating</p>
<p>Facing</p>
<p>Drive Pad</p></td>
<td><p>Speed Ratio</p>
<p>to</p></td>
<td colspan="3"><p>Maximum</p>
<p>Torque</p>
<p>in. lb.</p></td>
<td><p>Maximum</p>
<p>Overhang</p>
<p>Moment</p></td>
</tr>
<tr class="even">
<td>Accessory</td>
<td>-W2A</td>
<td>-AJ1A</td>
<td>-AE2A</td>
<td>-AF1B</td>
<td>-AG1A, -AH1A</td>
<td>-AB1BD</td>
<td>-K1AD</td>
<td>TIO</td>
<td>LTIO</td>
<td>Crankshaft</td>
<td colspan="2">Cont.</td>
<td>Static</td>
<td>in.-lb.</td>
</tr>
<tr class="odd">
<td>Starter</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>CC</td>
<td>C</td>
<td>16.556:1</td>
<td colspan="2">---</td>
<td>450</td>
<td>150</td>
</tr>
<tr class="even">
<td>Alternator</td>
<td>*</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>C</td>
<td>CC</td>
<td>3.200:1</td>
<td colspan="2">60</td>
<td>120</td>
<td>175</td>
</tr>
<tr class="odd">
<td>Alternator</td>
<td>-</td>
<td>--</td>
<td>*</td>
<td>--</td>
<td>-</td>
<td>-</td>
<td>-</td>
<td>C</td>
<td>-</td>
<td>3.800:1</td>
<td colspan="2">60</td>
<td>120</td>
<td>175</td>
</tr>
<tr class="even">
<td>Vacuum pump</td>
<td>**</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>CC</td>
<td>C</td>
<td>1.300:1</td>
<td colspan="2">70</td>
<td>450</td>
<td>25</td>
</tr>
<tr class="odd">
<td>Hydraulic pump</td>
<td>**</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>C</td>
<td>CC</td>
<td>1.385:1</td>
<td colspan="2">100</td>
<td>800</td>
<td>40</td>
</tr>
<tr class="even">
<td>Hydraulic pump</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>*</td>
<td>--</td>
<td>*</td>
<td>C</td>
<td>CC</td>
<td>1.300:1</td>
<td colspan="2">100</td>
<td>800</td>
<td>40</td>
</tr>
<tr class="odd">
<td>Tachometer</td>
<td>*</td>
<td>*</td>
<td>--</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>C</td>
<td>CC</td>
<td>0.500:1</td>
<td colspan="2">7</td>
<td>50</td>
<td>5</td>
</tr>
<tr class="even">
<td><p>Propeller</p>
<p>governor***</p></td>
<td>*</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>*</td>
<td>C</td>
<td>CC</td>
<td>0.895:1</td>
<td colspan="2">125</td>
<td>1200</td>
<td>25</td>
</tr>
<tr class="odd">
<td><p>Propeller</p>
<p>governor****</p></td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>--</td>
<td>--</td>
<td>C</td>
<td>CC</td>
<td>0.947:1</td>
<td colspan="2">125</td>
<td>2200</td>
<td>25</td>
</tr>
<tr class="even">
<td><p>Propeller</p>
<p>governor****</p></td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>*</td>
<td>--</td>
<td>C</td>
<td>CC</td>
<td>1.3000:1</td>
<td colspan="2">125</td>
<td>2200</td>
<td>25</td>
</tr>
<tr class="odd">
<td>Fuel pump</td>
<td>-</td>
<td>*</td>
<td>-</td>
<td>-</td>
<td>*</td>
<td>*</td>
<td>*</td>
<td>C</td>
<td>CC</td>
<td>1.000:1</td>
<td colspan="2">25</td>
<td>450</td>
<td>25</td>
</tr>
<tr class="even">
<td>Fuel pump</td>
<td>*</td>
<td>--</td>
<td>*</td>
<td>*</td>
<td>--</td>
<td>--</td>
<td>--</td>
<td>CC</td>
<td>C</td>
<td>1.000:1</td>
<td colspan="2">25</td>
<td>450</td>
<td>25</td>
</tr>
<tr class="odd">
<td>Freon comp.</td>
<td>--</td>
<td>--</td>
<td>-</td>
<td>-</td>
<td>--</td>
<td>--</td>
<td>**</td>
<td>C</td>
<td>CC</td>
<td>1.300:1</td>
<td colspan="2">180</td>
<td>2200</td>
<td>150</td>
</tr>
<tr class="even">
<td>Freon comp.</td>
<td>--</td>
<td>--</td>
<td>*</td>
<td>*</td>
<td>**</td>
<td>*</td>
<td>--</td>
<td>C</td>
<td>CC</td>
<td colspan="2">1.462:1*****</td>
<td colspan="3">Limited by belt.</td>
</tr>
</tbody>
</table>

"C" Clockwise, "CC" Counter Clockwise

\*Standard

\*\*Optional

\*\*\*Narrow deck engines

\*\*\*\*Wide deck engines

\*\*\*\*\*With compressor pulley diameter of 6.00 inches.

NOTE 4. The Turbocharger meets the containment requirements of CAR
13.116 and does not require external

protection.

Measure exhaust gas temperature at inlet location shown on Lycoming
Drawing No. 63232(-A1A, -A2A,

-A1B, -A2B, -A1C, -A2C), 63281 (-C1A, -E1A, -G1A, -H1A), 63393 (-F2BD),
63397 (-J2B/D), 63433

(-N2BD), 63416 (K1AD), 63444(-R2AD), 63517 (-T2AD), 63533 (-U2A), 63534
(-V2AD), 63537 (-W2A),

63545 (-AB1AD), 63582 (-AB1BD), 63546 (-AA1AD), 04D63570(-AE2A),
04063573 (-AF1A, -AF1B), 63583 (-AG1A), 63592 (-AH1A), O4D63594 (-AJ1A),
04D63601 (-AK1A).

Performance data for these engines are presented on Lycoming Curves No.
12993 (-A1A, -A2A, -A1B,

-A2B), 13195-B(-A1C, -A2C), 13107-B(-C1A), 13172(-E1A), 13190-A(-G1A),
13208 (-H1A),

13201-A (-F2BD), 13215 (-J2BD, -N2BD), 13257-A (-K1AD), 13296 (-R2AD),
and 13329(-S1AD),

13395 (-T2AD), 13399 (-U2A), 13415 (-V2AD), 13441 (-W2A), 13455 (-AB1AD,
-AB1BD, -AA1AD),

13482(-AE2A), 13491(-AF1A -AF1B), 13509 (-AG1A), 13525 (-AH1A), 13538
(-AJ1A), 13556 (AK1A).

Maximum turbocharger speed is now being governed by manifold pressure
rather than temperature rise.

Maximum manifold pressure versus altitude are presented on Lycoming
Curve Numbers 13166-A (-A1A),

-A2A, -A1B, -A2B), 13196-C (-A1C, -A2C), 13197-A (-C1A, -G1A), 13209
(-H1A), 13202-B (-F2BD),

13216-C (-J2B/D, -N2BD), 13297 (-R2AD), 13263 (-K1AD), 13330 (-S1AD),
13396 (-T2AD), 13416

(-V2AD), 13442 (-W2A), 13456 (-AB1AD, -AB1BD, -AA1AD), 13483 (-AE2A),
13492 (-AF1A,-AF1B), 13510 (-AG1A), 13537 (AH1A), 13540-A (-AJ1A), 13558
(AK1A).

NOTE 5. Cylinder base temperature limits are not applicable to engine
models which incorporate internal piston

cooling oil jets.

NOTE 6. Spark plugs approved for use on these engines are listed in the
latest revision of Textron Lycoming Service

Instruction No. 1042.

NOTE 7. These engines incorporate the following similarities or
differences:

TIO-540-A1A Basic model. Six cylinder, air-cooled, horizontally-opposed,
direct drive, fuel injected,

top exhaust, turbocharged engine incorporating internal piston cooling
oil jets. Uses

two-blade propeller.

TIO-540-A1B Similar to -A1A but has density controller with faster
temperature response.

TIO-540-A2A Similar to -A1A except has propeller flange bushings which
accommodate either a

two-blade or three-blade propeller.

TIO-540-A2B Similar to -A1B except has propeller flange bushings which
accommodate either a

two-blade or three-blade propeller.

TIO-540-A1C Similar to -A1B except BSFC is increased to .67/bhp-hr and
the manifold pressure

increased to 40.0 inches Hg.

TIO-540-A2C Similar to -A2B except BSFC is increased to .67/bhp-hr and
the manifold pressure

increased to 40.0 inches Hg.

TIO-540-C1A Differs from -A1A with lower compression ratio, different
counterweights, and parallel

valve cylinders.

TIO-540-E1A Similar to -C1A except rating is increased, different
turbocharger control setting and uses Bendix S6LN-1227 magneto instead
of S6LN-1208 magneto.

TIO-540-G1A Similar to -C1A except for higher compression ratio.

TIO-540-H1A Similar to -E1A except rating is increased.

TIO-540-F2BD Similar to -A2B except rated power is increased and
incorporates the Bendix Dual

Magneto.

LTIO-540-F2BD Similar to -F2DB except that it has counter-clockwise
(reversed) rotation.

TIO-540-J2BD Similar to TIO-540-F2BD except rated power is increased and
is equipped with an Air

Research Model THO8460 turbocharger.

LTIO-540-H2BD Similar to TIO-540-J2BD except that it has
counter-clockwise (reverse) rotation.

L/TIO-540-J2B Similar to L/TIO-J2BD except for two single Bendix
Magnetos instead of a dual Bendix

Magneto.

TIO-540-K1AD Similar to -E1A except increased compression ratio, dual
magneto, pressure controller,

provision for cabin bleed air has the turbocharger mounted to the rear
of the engine.

LTIO-540-K1AD Similar to TIO-540-K1AD except that it has
counter-clockwise (reverse) rotation.

TIO-540-N2BD Similar to -J2BD except turbocharger is moved 1/2 inch to
the left when viewed from the rear.

LTIO-540-N2BD Similar to TIO-540-N2BD except that it has
counter-clockwise (reverse) rotation.

TIO-540-R2AD Similar to -J2BD except lower rated speed and power,
provision for cabin bleed and type of turbocharger controllers.

LTIO-540-R2AD Similar to TIO-540-R2AD except that it has
counter-clockwise (reverse) rotation.

TIO-540-S1AD Similar to IO-540-M2A5D (1E4) except has a manually
controllable turbocharger, front air inlet, lower compression ratio and
provision for a controllable propeller.

TIO-540-T2AD Similar to TIO-540-J2BD except for modified turbocharger
transition section and lower

rated power.

TIO-540-U2A Similar to IO-540-AA1A5 except has thin wall, high crush
bearings, narrow connecting

rods, an intercooler (remote mounted) and a Rotomaster (Rajay)
turbocharger package.

LTIO-540-U2A Similar to TIO-540-U2A except that it has counter-clockwise
(reverse) rotation.

TIO-540-V2AD Similar to -J2BD except has down exhaust and top intake
cylinder heads, employs an

intercooler and the crankshaft, connecting rods and bearing combination
similar to the

-U2A.

LTIO-540-V2AD Similar to the TIO-540-V2AD except that it has
counter-clockwise (reverse) rotation.

TIO-540-W2A Similar to the -V2AD except equipped with (2) Bendix S-1200
series magnetos, a

density differential controller, not equipped with an induction
intercooler nor any

provisions for cabin bleed air.

LTIO-540-W2A Similar to the TIO-540-W2A except that it has
counter-clockwise (reverse) rotation.

TIO-540-AB1AD Similar to the -K1AD except for the relocation of the
turbocharger and has a density-

differential controller. Also, the dual magneto is equipped with an
impulse coupling

instead of retard breaker.

TIO-540-AB1BD Similar to the -AB1AD except the prop governor is on the
accessory housing, scavenger pump on upper accessory pad and more
effective counterweights.

TIO-540-AA1AD Similar to the model -AB1AD except for a rear mounted prop
governor drive, uses the

-K1AD turbocharger mounting and has no provisions for cabin bleed.

TIO-540-AE2A Similar to the TIO-540-U2A except with (2) Slick retard
breaker, pressurized magnetos,

twin AiResearch turbochargers with individual intercoolers, and a single
wastegate

modulated by a variable absolute pressure controller. Two sonic nozzles
are provided

for cabin pressurization.

TIO-540-AF1A Similar to the TIO-540-AA1AD except equipped with (2) Slick
pressurized magnetos,

an intercooler, drives for (2) alternators and a different model Garrett
turbocharger.

TIO-540-AF1B Similar to the TIO-540-AF1A except incorporates exhaust
valve guide oilers

TIO-540-AG1A Similar to the TIO-540-AA1AD except equipped with (2) Slick
pressurized magnetos,

and a different model Garrett turbocharger which has been relocated.

TIO-540-AH1A Similar to the TIO-540-A except equipped with (2) Slick
pressurized magnetos,

down exhaust heads and a different model Garrett turbocharger which has
been relocated.

TIO-540-AJ1A Similar to the TIO-540-W2A except equipped with a different
model Garrett turbocharger and slope controller.

TIO-540-AK1A Similar to TIO-540-AG1A except that it has a relocated
AiResearch model TAO411 turbocharger, bottom mounted fuel injector and a
lower rating

NOTE 8. The TIO-540-C1A, -E1A, -G1A, -H1A, -K1AD and LTIO-540-K1AD are
equipped with special 5th and 6th

order counterweights making them eligible for use with Hartzell
"compact" propeller. When the

TIO-540-G1A is used with a Hartzell HC-E2YK-2R/8465-7R propeller, the
manifold pressure is limited

in the 2000 rpm speed range to a maximum of 27 inches Hg.

NOTE 9. Starter, generators, and alternators approved for use on these
engines are listed in the latest revision of

Textron Lycoming Service Instruction No. 1154.

NOTE 10. The following tabulation shows turbocharger, fuel injector,
weight, compression ratio and ignition.

+---------+-----------+----------+------+--------+--------------------+
| Model   | Tur       | Fuel     | We   | Compr  | Ignition, Dual \*  |
|         | bocharger | I        | ight | ession |                    |
|         |           | njection |      |        |                    |
|         |           |          | (    | Ratio  |                    |
|         |           |          | dry) |        |                    |
|         |           |          | lb.  |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| TIO-    | TE0659    | R        | 509  | 7.30:1 | TCM\*\* S6LN-1208, |
| 540-A1A |           | SA-10AD1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -A1B    | TE0659    | R        | 509  | 7.30:1 | S6LN-1208,         |
|         |           | SA-10AD1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -A2A    | TE0659    | R        | 509  | 7.30:1 | S6LN-1208,         |
|         |           | SA-10AD1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -A2B    | TE0659    | R        | 509  | 7.30:1 | S6LN-1208,         |
|         |           | SA-10AD1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -A1C    | TE0659    | R        | 511  | 7.30:1 | S6LN-1208,         |
|         |           | SA-10AD1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -A2C    | TE0659    | R        | 511  | 7.30:1 | # S6               |
|         |           | SA-10AD1 |      |        | LN-1208, S6LN-1209 |
+---------+-----------+----------+------+--------+--------------------+
| -C1A    | TE0659    | RSA-5AD1 | 456  | 7.20:1 | > S6LN-1208,       |
|         |           |          |      |        | > S6LN-1209        |
+---------+-----------+----------+------+--------+--------------------+

NOTE 10. (cont'd) The following tabulation shows turbocharger, fuel
injector, weight, compression ratio and ignition.

+---------+-----------+----------+------+--------+--------------------+
| Model   | Tur       | Fuel     | We   | Compr  | Ignition, Dual \*  |
|         | bocharger | I        | ight | ession |                    |
|         |           | njection |      |        |                    |
|         |           |          | (    | Ratio  |                    |
|         |           |          | dry) |        |                    |
|         |           |          | lb.  |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -E1A    | TE0659    | RSA-5AD1 | 453  | 7.20:1 | TCM\*\* S6LN-1227, |
|         |           |          |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -G1A    | TE0659    | RSA-5AD1 | 456  | 8.50:1 | S6LN-1208,         |
|         |           |          |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -H1A    | TE0659    | RSA-5AD1 | 453  | 7.20:1 | S6LN-1227,         |
|         |           |          |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -F2BD   | TE0659    | R        | 514  | 7.30:1 | D6LN-3200, /2230   |
|         |           | SA-10ED1 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -J2B    | TH08A60   | R        | 558  | 7.30:1 | S61N-1208,         |
|         |           | SA-10ED1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -J2BD   | TH08A60   | R        | 518  | 7.30:1 | D6LN-3200, /2230   |
|         |           | SA-10ED1 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -K1AD   | TE0695    | RSA-5AD1 | 459  | 8.00:1 | D6LN-3200, /2230   |
+---------+-----------+----------+------+--------+--------------------+
| -N2BD   | TE08A60   | R        | 518  | 7.30:1 | D6LN-3200, /2230   |
|         |           | SA-10ED1 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -S1AD   | TE0659    | R        | 502  | 7.30:1 | D6LN-3000, /2231   |
|         |           | SA-10ED1 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -R2AD   | TH08A69   | R        | 524  | 7.30:1 | D6LN-3200, /2230   |
|         |           | SA-10EB1 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -T2AD   | TH08A60   | R        | 549  | 7.30:1 | D6LN-3200, /2230   |
|         |           | SA-10ED1 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -U2A    | 3AU(      | R        | 578  | 7.30:1 | S6LN-1258,         |
|         | V)2ME60H3 | SA-10ED1 |      |        | S6LN-1259          |
+---------+-----------+----------+------+--------+--------------------+
| -J2B    | TH08A60   | R        | 558  | 7.30:1 | S6LN-1208,         |
|         |           | SA-10ED1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -V2AD   | TH08A69   | R        | 565  | 7.30:1 | D6LN-3200          |
|         |           | SA-10DB2 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -W2A    | TH08A69   | R        | 554  | 7.30:1 | S6LN-1208,         |
|         |           | SA-10ED1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -AB1AD  | TE0659    | RSA-5AD1 | 474  | 8.00:1 | D6LN-3000          |
+---------+-----------+----------+------+--------+--------------------+
| -AB1BD  | TE0659    | RSA-5AD1 | 474  | 8.00:1 | D6LN-3000          |
+---------+-----------+----------+------+--------+--------------------+
| -AA1AD  | TE0659    | RSA-5AD1 | 483  | 8.00:1 | D6LN-3200          |
+---------+-----------+----------+------+--------+--------------------+
| -AE2A   | TA0411(2) | R        | 595  | 7.30:1 | Slick 6263, 6260   |
|         |           | SA-10ED1 |      |        | (right)            |
+---------+-----------+----------+------+--------+--------------------+
| -AF1A   | TA0413    | R        | 473  | 8.00:1 | Slick 6261, 6260   |
|         |           | SA-10ED1 |      |        | (right)            |
+---------+-----------+----------+------+--------+--------------------+
| -AF1B   | TA0413    | R        | 473  | 8.00:1 | Slick 6261, 6260   |
|         |           | SA-10ED1 |      |        | (right)            |
+---------+-----------+----------+------+--------+--------------------+
| -AG1A   | TAO413    | RSA-5AD1 | 485  | 8.00:1 | Slick 6361, 6360   |
|         |           |          |      |        | (right)            |
+---------+-----------+----------+------+--------+--------------------+
| -AH1A   | TAO413    | R        | 542  | 7.30:1 | Slick 6361, 6360   |
|         |           | SA-10ED1 |      |        | (right)            |
|         |           | or       |      |        |                    |
|         |           | FM-250   |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -AJ1A   | TA6102    | R        | 532  | 7.30:1 | Slick 6361, 6360   |
|         |           | SA-10ED1 |      |        | (right)            |
+---------+-----------+----------+------+--------+--------------------+
| -AK1A   | TA0411    | RSA-5AD1 | 464  | 8.00:1 | Slick 6361 (2)     |
+---------+-----------+----------+------+--------+--------------------+
| LTIO-5  | TE0659    | R        | 514  | 7.30:1 | D6RN-3200, /2230   |
| 40-F2BD |           | SA-10ED1 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -J2BD   | TH08A60   | R        | 518  | 7.30:1 | D6RN-3200, /2230   |
|         |           | SA-10ED1 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -K1AD   | TE0695    | RSA-5AD1 | 459  | 8.00:1 | D6LN-3200, /2230   |
+---------+-----------+----------+------+--------+--------------------+
| -N2BD   | TH08A60   | R        | 518  | 7.30:1 | D6RN-3200, /2230   |
|         |           | SA-10ED1 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -U2A    | 3AU(      | R        | 578  | 7.30:1 | S6LN-1258,         |
|         | V)2ME60H3 | SA-10ED1 |      |        | S6LN-1259          |
+---------+-----------+----------+------+--------+--------------------+
| -J2B    | TH08A60   | R        | 558  | 7.30:1 | S6LN-1208,         |
|         |           | SA-10ED1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+
| -V2AD   | TH08A69   | R        | 565  | 7.30:1 | D6LN-3200          |
|         |           | SA-10DB2 |      |        |                    |
+---------+-----------+----------+------+--------+--------------------+
| -W2A    | TH08A69   | R        | 549  | 7.30:1 | S6LN-1208,         |
|         |           | SA-10ED1 |      |        | S6LN-1209          |
+---------+-----------+----------+------+--------+--------------------+

\* For alternate magnetos see latest edition of Textron Lycoming Service
Instruction No. 1443

\*\* TCM formally Bendix

NOTE 11. Air from the compressor of the AiResearch Turbocharger is
suitable for cabin pressurization. The

installation must provide for cabin air temperature control from 300°F
to 20,000 feet hot day condition

under maximum engine power. For cabin air outlet flange dimensions see
Textron Lycoming Drawing No.

63444 for -R2AD model.

A sonic nozzle must be provided to preclude affecting engine performance
by cabin air bleed.

TIO-540-AE2A model is equipped with two sonic nozzles to supply air for
cabin pressurization,

reference Lycoming Drawing No. 04D63570.

NOTE 12. All models equipped with one impulse coupling magneto may use
two impulse coupling magnetos as

optional equipment.

NOTE 13. TIO-540-R2AD and LTIO-540-R2AD have an alt. rating of 340 hp at
2500 rpm and 44.0 in.Hg at S.L. and

325 hp at 2500 rpm and 44.0 in HG at 15,000 feet.

NOTE 14. The maximum continuous ratings for these engines have been
specified with 10 horsepower extracted at

the accessory drives.

NOTE 15. The TIO-540-AB1BD has more effective counterweights for use
with a McCauley propeller.

NOTE 16. Engines produced prior to September 25, 2006 may have 20 degree
timing. Owners and/or operators should refer to the engine dataplate for
the correct timing setting.

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