# TCDS E14EA: Lycoming Engines

- Type: Type certificate data sheet
- Status: Current
- Holder: Lycoming Engines
- Revision: 22
- Revised: May 24, 2012
- Product: Engine
- Certification basis: Part 33, CAR 13
- Registered aircraft: 6,990, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/b7/1f/b71f9830263f6bcda4169d1eb7a35a26b86678ad4ff643e7ebde7fddca320108
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/2E969358B369548B86257A09005118D1.0001
- Page: https://openairdocs.org/tcds/E14EA

## Models (40)

As the data sheet lists them.

- TIO-540-G1A
- LTIO-540-N2BD
- TIO-540-A1A
- TIO-540-AF1B
- TIO-540-T2AD
- TIO-540-A2A
- TIO-540-C1A
- TIO-540-V2AD
- TIO-540-AB1AD
- LTIO-540-F2BD
- TIO-540-J2BD
- TIO-540-J2B
- TIO-540-A2C
- TIO-540-F2BD
- TIO-540-AH1A
- TIO-540-A1B
- TIO-540-AB1BD
- TIO-540-S1AD
- TIO-540-AF1A
- TIO-540-AG1A
- TIO-540-H1A
- TIO-540-N2BD
- TIO-540-AK1A
- TIO-540-U2A
- TIO-540-W2A
- LTIO-540-K1AD
- TIO-540-AA1AD
- TIO-540-R2AD
- TIO-540-A2B
- LTIO-540-V2AD
- TIO-540-A1C
- TIO-540-K1AD
- TIO-540-AJ1A
- LTIO-540-J2B
- LTIO-540-U2A
- TIO-540-E1A
- LTIO-540-W2A
- TIO-540-AE2A
- LTIO-540-J2BD
- LTIO-540-R2AD

## What the data sheet says

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

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 
Rev. No. 22 22 22 22 22 22 22 22 17 16 16 16 16 17 21 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
E14EA 
Revision 22 
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 
May 24, 2012 
 
 
 
TYPE CERTIFICATE DATA SHEET NO. E14EA 
 
 
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 Co rporation transferred TC E14EA to Lycoming Engines, An 
Operating Division of Avco Corporation on December 17, 2003.

2 of 15 E14EA  
 
Model                  Lycoming TIO-540-A1A, -A1B,  
-A2A, -A2B 
TIO-540-A1C, -A2C TIO-540-E1A 
Type 6HOA Direct Drive Turbocharged   
Rating  (See Notes 4 and 13)    
Maximum continuous hp., rpm,  
  in. Hg. at: 
   
 Standard density critical alt. ft . 310-2575-40.2-15,000 310-2575-42.-15,000 260-2575-36.0-15000 
 Standard density sea level alt. ft. 310- 2575-38.6-S.L. 310-2575-40.0- S.L. 260-2575-34.1-S.L. 
Takeoff (5 min.) hp., rpm, in. Hg. at:    
 Standard density critical alt. ft . 310-2575-40.2-15,000 310-2575-41.5-15,000 260-2575-36.0-15000 
 Standard density sea level alt., ft. 310- 2575-38.6-S.L. 310-2575-40.0- S.L. 260-2575-34.1-S.L. 
Fuel (minimum grade aviation  
  gasoline) 
 
100/100LL  - -  - - 
Lubricating oil (lubrication should 
  conform to the specification as listed  
or to subsequent revisions thereto) 
Lycoming Spec. No. 301-F 
Service Instruction  
No. 1014 
 
- - 
 
- - 
Bore and stroke, in. 5.125 X 4.375 - - - - 
Displacement, cu. in. 541.5 - - - - 
Compression ratio See Note 10. - - - - 
Weight (dry) lb. See Note 10. - - - - 
C.G. location (with starter and 
  alternator installed) 
   
 From front face of prop. mounting 
   flange, in. 
 
22.22 
 
- - 
 
19.47 
 Off crankshaft C.L., in. 0.88 below & 0.18 right - - 3.00 below & 0.11 left 
Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - 
Crankshaft dampers (torsional) One 5th order 
One 6th order 
- - 
- - 
- - 
One 6th order (Note 8) 
Fuel injection Note 10 - - - - 
Turbocharger Note 10 - - - - 
Ignition, dual Note 10 - - - - 
Ignition timing  °BTC 20 - - - - 
Spark plugs Note 6 - - - - 
Oil sump capacity, qt. 12 - - - - 
Usable oil, qt. (20° nose up or down)   9 1/4 - - - - 
NOTES  -  as applicable 1-7, 9, 10 1-7, 9, 10 1-10 
 
 
“- -” indicates “same as preceding model.” 
For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070.

3 of 15 E14EA  
 
Model                  Lycoming TIO-540-H1A TIO-540-F2BD 
LTIO-540-F2BD 
TIO-540-J2B, -J2BD, -N2BD, 
LTIO-540-J2B, -J2BD,  
  -N2BD 
Type 6HOA Direct Drive Turbocharged   
Rating  (See Notes 4 and 13)    
Maximum continuous hp., rpm,  
  in. Hg. at: 
   
 Standard density critical alt. ft . 270-2575-37.5-15,000 325-2575-46.0-15000 350-2575-46.0-15000 
 Standard density sea level alt. ft. 270- 2575-35.9-S.L. 325-2575-43.5- S.L. 350-2575-43.0-S.L. 
Takeoff (5 min.) hp., rpm, in. Hg. at:    
 Standard density critical alt. ft . 270-2575-37.5-15,000 325-2575-46.0-15000 350-2575-46.0-15000 
 Standard density sea level alt., ft. 270-2575-35.9-S.L. 325-2575-43.5-S.L. 350-2575-43.0-15000 
Fuel (minimum grade aviation  
  gasoline) 
 
100/100LL  - -  - - 
Lubricating oil (lubrication should 
  conform to the specification as listed  
or to subsequent revisions thereto) 
Lycoming Spec. No. 301-F 
Service Instruction  
No. 1014 
 
- - 
 
- - 
Bore and stroke, in. 5.125 X 4.375 - - - - 
Displacement, cu. in. 541.5 - - - - 
Compression ratio See Note 10. - - - - 
Weight (dry) lb. See Note 10. - - - - 
C.G. location (with starter and 
  alternator installed) 
   
 From front face of prop. mounting 
   flange, in. 
 
19.47 
 
22.19 
 
22.75 
 Off crankshaft C.L., in. 3.00 below & 0.11 left  0.88 below & 0.18 right 0.75 below & 0.16 right 
Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - 
Crankshaft dampers (torsional) One 5th order 
One 6th order (Note 8) 
- - 
One 6th order 
- - 
- -  
Fuel injection Note 10 - - - - 
Turbocharger Note 10 - - - - 
Ignition, dual Note 10 - - - - 
Ignition timing  °BTC 20 - - - - 
Spark plugs Note 6 - - - - 
Oil sump capacity, qt. 12 - - - - 
Usable oil, qt. (20° nose up or down)   9 1/4 - - - - 
NOTES  --  as applicable 1-10 1-7, 9, 10 1-7, 9, 10 
 
“- -” indicates “same as preceding model.” 
For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070.

4 of 15 E14EA  
 
Model                  Lycoming TIO-540-R2AD 
LTIO-540-R2AD 
 
TIO-540-C1A, -G1A 
TIO-540-K1AD 
LTIO-540-K1AD 
Type 6HOA Direct Drive Turbocharged   
Rating  (See Note 4)    
Maximum continuous hp., rpm,  
  in. Hg. at: 
   
 Standard density critical alt. ft. 340-2575-44.0-15000 250-2575-34.0-15000 250-2575-34.0-15000 
 Standard density sea level alt. ft. 350- 2575-44.0-S.L. 250-2575-33.0- S.L. 250-2575-34.0-S.L. 
Takeoff (5 min.) hp., rpm, in. Hg. at:    
 Standard density critical alt. ft. 340-2575-44.0-15000 250-2575-34.0-15000 250-2575-34.0-15000 
 Standard density sea level alt., ft. 350- 2575-44.0-S.L. 250-2575-33.0- S.L. 250-2575-34.0-S.L. 
Fuel (minimum grade aviation  
  gasoline) 
 
100/100LL  - -  - - 
Lubricating oil (lubrication should 
  conform to the specification as listed 
  or to subsequent revisions thereto) 
Lycoming Spec. No. 301-F 
Service Instruction  
No. 1014 
 
- - 
 
- - 
Bore and stroke, in. 5.125 X 4.375 - - - - 
Displacement, cu. in. 541.5 - - - - 
Compression ratio See Note 10. - - - - 
Weight (dry) lb. See Note 10. - - - - 
C.G. location (with starter and 
  alternator installed) 
   
 From front face of prop. mounting 
   flange, in. 
 
22.75 
 
19.27 
 
21.0 
 Off crankshaft C.L., in. 0.75 below & 0.16 right  2.30 below & 0.23 left 0.50 below & 0.31 left 
Propeller shaft flange, SAE A.S. 127 Type 2 modified  - - 
Crankshaft dampers (torsional) One 5th order 
One 6th order 
- - 
One 6th order (Note 8) 
- - 
- -  
Fuel injection Note 10 - - - - 
Turbocharger Note 10 - - - - 
Ignition, dual Note 10 - - - - 
Ignition timing °BTC 20 - - - - 
Spark plugs Note 6 - - - - 
Oil sump capacity, qt. 12 - - 8 
Usable oil, qt. (20° nose up or down)   9 1/4 - - 6 
NOTES  -  as applicable 1-7, 9, 10, 11, 13 1-10 1-10 
 
“- -” indicates “same as preceding model.” 
For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070.

5 of 15 E14EA  
 
Model                  Lycoming  
TIO-540-S1AD 
 
TIO-540-T2AD 
TIO-540-U2A  
LTIO-540-U2A 
Type 6HOA Direct Drive Turbocharged   
Rating  (See Note 4)    
Maximum continuous hp., rpm,  
  in. Hg. at: 
   
 Standard density critical alt. ft. 295-2700-36.0-16000 330-2400-43.0-12000 350-2500-42.2-12000 
 Standard density sea level alt. ft. 300-2700-36.0-S.L. & 
12000 ft. 
330-2400-40.5-S.L. 350-2500-41.2-S.L. 
Takeoff (5 min.) hp., rpm, in. Hg. at:    
 Standard density critical alt. ft. 295-2700-36.0-16000 330-2400-43.0-12000 350-2500-42.2-12000 
 Standard density sea level alt., ft. 300-2700-36.0-S.L. & 
12000 ft. 
330-2400-43.0-S.L. 350-2500-41.2-S.L. 
Fuel (minimum grade aviation  
  gasoline) 
 
100/100LL  - -  - - 
Lubricating oil (lubrication should 
  conform to the specification as listed 
  or to subsequent revisions thereto) 
Lycoming Spec. No. 301-F 
Service Instruction  
No. 1014 
 
- - 
 
- - 
Bore and stroke, in. 5.125 X 4.375 - - - - 
Displacement, cu. in. 541.5 - - - - 
Compression ratio See Note 10. - - - - 
Weight (dry) lb. See Note 10. - - - - 
C.G. location (with starter and 
  alternator installed) 
   
 From front face of prop. mounting 
   flange, in. 
 
18.58 
 
22.75 
 
20.38 
 Off crankshaft C.L., in. 1.31 below & 1.00 right  0.75 below & 0.16 right 1.4 below & 0.25 right 
Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - 
Crankshaft dampers (torsional) One 5th order 
One 6th order (Note 8) 
- - 
- - 
- - 
- -  
Fuel injection Note 10 - - - - 
Turbocharger Note 10 - - - - 
Ignition, dual Note 10 - - - - 
Ignition timing °BTC 20 - - - - 
Spark plugs Note 6 - - - - 
Oil sump capacity, qt. 12 - - - - 
Usable oil, qt. (20° nose up or down)   9 3/4 - - - - 
NOTES  -  as applicable 1-10 1-7, 9. 10 1-7, 9, 10 
 
“- -” indicates “same as preceding model.” 
For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070.

6 of 15 E14EA  
 
Model                  Lycoming TIO-540-V2AD 
LTIO-540-V2AD 
(See Note 14) 
TIO-540-W2A 
LTIO-540-W2A 
(See Note 14) 
TIO-540-AA1AD* 
TIO-540-AB1AD 
TIO-540-AB1BD 
Type 6HOA Direct Drive Turbocharged   
Rating  (See Note 4)    
Maximum continuous hp., rpm,  
  in. Hg. at: 
   
 Standard density critical alt. ft. 340-2600-42.0-18000 350-2600-44.2-15000 250-2575-32.5-15000 
 Standard density sea level alt. ft. 350- 2600-42.0-S.L. 350-2600-44.2- S.L. 250-2575-32.5-S.L. 
Takeoff (5 min.) hp., rpm, in. Hg. at:    
 Standard density critical alt. ft. 340-2600-42.0-18000 350-2600-44.2-15000 250-2575-32.5-15000 
 Standard density sea level alt., ft. 350- 2600-42.0-S.L. 350-2600-44.2- S.L. 250-2575-32.5-S.L. 
Fuel (minimum grade aviation  
  gasoline) 
 
100/100LL  - -  - - 
Lubricating oil (lubrication should 
  conform to the specification as listed  
or to subsequent revisions thereto) 
Lycoming Spec. No. 301-F 
Service Instruction  
No. 1014 
 
- - 
 
- - 
Bore and stroke, in. 5.125 X 4.375 - - - - 
Displacement, cu. in. 541.5 - - - - 
Compression ratio See Note 10. - - - - 
Weight (dry) lb. See Note 10. - - - - 
C.G. location (with starter and 
  alternator installed) 
   
 From front face of prop. mounting 
   flange, in. 
 
23.05 
 
22.10 
 
18.91 
 Off crankshaft C.L., in. 0.59 below & 0.14 right  0.10 below & 0.48 right 2.20 below & 0.67 left 
Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - 
Crankshaft dampers (torsional) One 5th order 
One 6th order  
- - 
- - 
- - 
- - 
Fuel injection Note 10 - - - - 
Turbocharger Note 10 - - - - 
Ignition, dual Note 10 - - - - 
Ignition timing °BTC 20 - - - - 
Spark plugs Note 6 - - - - 
Oil sump capacity, qt. 12 - - - - ** 
Usable oil, qt. (20° nose up or down)   9 1/4 - - - - *** 
NOTES  -  as applicable 1-7, 9, 10,  14 1-7, 9, 10, 14 1-7,  9, 10, 15 
 
“- -” indicates “same as preceding model.” 
For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070. 
 
*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.

7 of 15 E14EA  
 
Model                  Lycoming TIO-540-AE2A TIO-540-AF1A 
TIO-540-AF1B 
TIO-540-AG1A 
Type 6HOA Direct Drive 
Turbocharged 
   
Rating  (See Note 4)    
Maximum continuous hp., rpm, in. 
Hg. at: 
   
 Standard density critical alt. ft. 350-2500-42.0-20000 270-2575-36.5-20000 270 - 2575 - 36.5 -15000 
 Standard density sea level alt. ft. 350-2500- 42.0-S.L. 270-2575-35.0-S.L.  270 - 2575 - 36.5 - SL 
Takeoff (5 min.) hp., rpm, in. Hg. at:    
 Standard density critical alt. ft. 350-2500-42.0-20000 270-2575-36.5-20000 270 - 2575 - 36.5 -15000 
 Standard density sea level alt., ft. 350-2500- 42.0-S.L. 270-2575-35.0-S.L.  270 - 2575 - 36.5 - SL 
Fuel (minimum grade aviation 
gasoline) 
100/100LL - - - - 
Lubricating oil (lubrication should 
conform to the specification as  
listed or to subsequent revisions 
thereto) 
 
Lycoming Spec. No. 301-F 
Service Instruction  
No. 1014 
 
- - 
 
- - 
Bore and stroke, in. 5.125 X 4.375 - - - - 
Displacement, cu. in. 541.5 - - - - 
Compression ratio See Note 10. - - - - 
Weight (dry) lb. See Note 10. - - - - 
C.G. location (with starter and 
alternator installed) 
   
From front face of prop. mounting 
flange, in. 
18.88 18.30 19.00 
Off crankshaft C.L., in. 0.95 below & 0.63 left  2.30 below & 0.64 left 1.75 below & 1.20 left 
Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - 
Crankshaft dampers (torsional) 
 
One 5th order 
One 6th order  
- - 
- - 
- - 
- - 
Fuel injection Note 10 - - - - 
Turbocharger Note 10 - - - - 
Ignition, dual Note 10 - - - - 
Ignition timing °BTC 20 - - - - 
Spark plugs Note 6 - - - - 
Oil sump capacity, qt. 12 10 10 
Usable oil, qt. (20° nose up or down)   9 1/4   7 1/4 5 
NOTES  -  as applicable 1-7, 9, 10, 11 1-7, 9, 10 1-10, 12 
 
“- -” indicates “same as preceding model.” 
For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070.

8 of 15 E14EA  
 
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 critical alt. ft. 300 - 2500 - 38.0 -12000 310 - 2500 - 39.0 – 14000 235 – 2400 – 32.0 -15000 
 Standard density sea level alt. ft. 300 - 2500 - 38.0 - SL 310 - 2500 - 39.0  - SL 235 – 2400 – 32.0 - SL 
Takeoff (5 min.) hp., rpm, in. Hg. at:    
 Standard density critical alt. ft. 300 - 2500 - 38.0 –12000 310 - 2500 - 39.0 – 14000 235 – 2400 – 32.0 -15000 
 Standard density sea level alt., ft. 300 - 2500 - 38.0 - SL 310 - 2500 - 39.0  - SL 235 – 2400 – 32.0 - SL 
Fuel (minimum grade aviation 
gasoline) 
100/100LL - - -- 
Lubricating oil (lubrication should 
conform to the specification as  
listed or to subsequent revisions 
thereto) 
 
Lycoming Spec. No. 301-
F 
Service Instruction  
No. 1014 
- - -- 
Bore and stroke, in. 5.125 - - -- 
Displacement, cu. in. 4.375 - - -- 
Compression ratio See Note 10. - - -- 
Weight (dry) lb. See Note 10. - - -- 
C.G. location (with starter and 
alternator installed) 
   
From front face of prop. mounting 
flange, in. 
18.70 18.50* 18.94* 
Off crankshaft C.L., in. 1.87 below & 1.00 right  0.75 below & 1.13 left* 1.50 below & 1.25 left* 
Propeller shaft flange, SAE A.S. 127 Type 2 modified - - -- 
Crankshaft dampers (torsional) 
 
One 5th order 
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, qt. 12 11 8 
Usable oil, qt. (20° nose up or down)   9 1/4 5 1/2 4 
NOTES  -  as applicable 1-10, 12 - - -- 
 
“- -” indicates “same as preceding model.” 
 
For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070. 
* No alternator installed 
** See Note 16  
*** See Note 17  
 
Certification Basis: 
 Regulations and Amendments    Date Type Certificate 
  Model  Date of Application  E14EA Issued/Revised  
 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

9 of 15 E14EA  
Certification Basis:    (cont’d) 
 Regulations and Amendments    Date Type Certificate 
  Model  Date of Application  E14EA Issued/Revised  
  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 m odels 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 inlet air pressure) 
Minimum 
(p.s.i.) 
Maximum 
(p.s.i.) 
Idle (min 
p.s.i.) 
at inlet to fuel injector  (-A models except -A1C, -A2C) 25 45 12 
at inlet to fuel injector  (-A1C, -A2C , -AJ1A models) 25 55 12 
at inlet to fuel injector  (-C, -E, -G, -H models) 18 45 12 
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 models) 27 65 12 
at inlet to fuel injector  (-W model) 31 65 12 
at inlet to fuel injector  (-AB1AD, -AB1BD models) 20 65 12 
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  models) 24 55 12 
at inlet to fuel injector  (-AG1A, -AK1A  models) 20 55 12

10 of 15 E14EA  
NOTE 2.  (cont’d) 
 
 
Fuel Pressure (p.s.i. above ambient air pressure) 
Minimum 
(p.s.i.) 
Maximum 
(p.s.i.) 
Idle (min 
p.s.i.) 
at inlet to engine fuel pump (-A , -F, -R, -S, -U, -V, -W) -2 65 -- 
 (-J, -N, -T, -AE2A, -AH1A, -AJ1A models)    
at inlet to engine fuel pump (-C, -E, -G, -H, -K -AF1A,) 
                                            (-AF1B, -AG1A, -AK1A models) 
 
-2 
 
55 
 
-- 
 
 
 
Manifold Pressure (cumulative total with altitude adjustment) 
Maximum 
(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, 
 -AH1A  models 
 
38 
  
-AG1A, -AJ1A models 39   
-AK1A model 32   
 
Oil Pressure 
Minimum 
(p.s.i.) 
Maximum 
(p.s.i.) 
 
Normal (all models) 55 95  
Idle (all models) 25 --  
Starting and warm-up (all models) -- 115  
    
Turbocharger exhaust back pressure  0.5

11 of 15 E14EA  
 
 
NOTE 3. The following accessory provisions are available: 
 -A1A, -A1B, 
-A2A, -A2B, 
-A1C, -A2C, 
-C1A, -E1A, 
-G1A, -H1A, 
-J2B, -U2A, 
 
 
 
 
 
AK1A 
  
 
 
 
 
-AF1A 
-F2BD, -J2BD, 
-N2BD, -R2AD, 
-S1AD, -T2AD, 
-U2A, -V2AD, 
-W2A, -J2B, 
-AB1AD, -AA1AD, 
   
 
 
Rotating 
Facing 
Drive Pad 
 
 
 
Speed Ratio 
to 
 
 
 
Maximum 
Torque 
in.  lb. 
 
 
 
Maximum 
Overhang 
Moment 
Accessory -W2A -AJ1A -AE2A -AF1B - AG1A, -AH1A -AB1BD -K1AD TIO LTIO Crankshaft Cont. Static in.-lb. 
Starter * * * * * * * CC C 16.556:1 --- 450 150 
Alternator * -- -- -- * * * C CC   3.200:1 60 120 175 
Alternator - -- * -- - - - C -   3.800:1 60 120 175 
Vacuum pump ** * * * * * * CC C   1.300:1 70 450 25 
Hydraulic pump ** * * * -- -- -- C CC   1.385:1 100 800 40 
Hydraulic pump -- -- -- -- * -- * C CC   1.300:1 100 800 40 
Tachometer * * -- * * * * C CC   0.500:1 7 50 5 
Propeller 
  governor*** 
 
* 
 
-- 
 
-- 
 
-- 
 
-- 
 
-- 
 
* 
 
C 
 
CC 
 
  0.895:1 
 
125 
 
1200 
 
25 
Propeller 
  governor**** 
 
* 
 
* 
 
* 
 
* 
 
* 
 
-- 
 
-- 
 
C 
 
CC 
 
  0.947:1 
 
125 
 
2200 
 
25 
Propeller 
  governor**** 
 
-- 
 
-- 
 
-- 
 
-- 
 
-- 
 
* 
 
-- 
 
C 
 
CC 
 
 1.3000:1 
 
125 
 
2200 
 
25 
Fuel pump - * - - * * * C CC   1.000:1 25 450 25 
Fuel pump * -- * * -- -- -- CC C   1.000:1 25 450 25 
Freon comp. -- -- - - -- -- ** C CC   1.300:1 180 2200 150 
Freon comp. -- -- * * ** * -- C CC   1.462:1***** Limited by belt. 
“C” Clockwise, “CC” Counter Clockwise 
        *Standard 
      **Optional 
     ***Narrow deck engines 
  ****Wide deck engines 
*****With compressor pulley diameter of 6.00 inches.

12 of 15 E14EA  
NOTE 4. The Turbocharger meets the containment requirements of CAR 13.116 and does not require external  
  protection. 
 
  Measure exhaust gas temperature at inlet lo cation 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 presen ted 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 ar e 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 ar e listed in the latest revision of 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 incorpor ating 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 prope ller flange bushings which accommodate either a 
   two-blade or three-blade propeller. 
  TIO-540-A2B Similar to -A1B except has prope ller flange bushings which accommodate either a 
   two-blade or three-blade propeller. 
  TIO-540-A1C Similar to -A1B except BSFC is in creased to .67/bhp-hr and the manifold pressure 
   increased to 40.0 inches Hg. 
  TIO-540-A2C Similar to -A2B except BSFC is in creased to .67/bhp-hr and the manifold pressure 
   increased to 40.0 inches Hg. 
  TIO-540-C1A Differs from -A1A with lower compre ssion ratio, different counterweights, and parallel 
   valve cylinders. 
  TIO-540-E1A Similar to -C1A except rating is incr eased, 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 th at 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 co mpression ratio, dual magneto, pressure controller, 
   provision for cabin bleed air has the turboc harger 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.

13 of 15 E14EA  
  LTIO-540-N2BD Similar to TIO-540-N2BD except th at it has counter-clockwise (reverse) rotation. 
  TIO-540-R2AD Similar to -J2BD except lower rate d 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 m odified 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 exha ust 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 th at it has counter-clockwise (reverse) rotation. 
  TIO-540-W2A Similar to the -V2AD except equi pped with (2) Bendix S-1200 series magnetos, a  
   density differential controller, not e quipped with an induction intercooler nor any 
   provisions for cabin bleed air. 
  LTIO-540-W2A Similar to the TIO-540-W2A except th at 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 pr op 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 fo r 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 i ndividual intercoolers, and a single wastegate 
   modulated by a variable absolute pressu re 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) alternat ors and a different model Garrett turbocharger. 
  TIO-540-AF1B Similar to the TIO-540-AF1A excep t 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 tur bocharger which has been relocated.  
  TIO-540-AH1A Similar to the TIO-540-A except e quipped with (2) Slick pressurized magnetos, 
   down exhaust heads and a different m odel Garrett turbocharger which has been  
   relocated. 
  TIO-540-AJ1A Similar to the TIO-540-W2A excep t 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 us e 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 altern ators approved for use on these engines are listed in the latest revision of 
  Lycoming Service Instruction No. 1154. 
 
NOTE 10. The following tabulation shows turbocharger, fu el injector, weight, compression ratio and ignition. 
 
 
Model 
 
Turbocharger 
 
Fuel Injection 
Weight 
(dry) lb. 
Compression 
Ratio 
 
Ignition, Dual * 
TIO-540-A1A TE0659 RSA-10AD1 509 7.30:1 TCM** S6LN-1208, S6LN-1209 
-A1B TE0659 RSA-10AD1 509 7.30:1  S6LN-1208, S6LN-1209 
-A2A TE0659 RSA-10AD1 509 7.30:1  S6LN-1208, S6LN-1209 
-A2B TE0659 RSA-10AD1 509 7.30:1  S6LN-1208, S6LN-1209 
-A1C TE0659 RSA-10AD1 511 7.30:1  S6LN-1208, S6LN-1209 
-A2C TE0659 RSA-10AD1 511 7.30:1 S6LN-1208, S6LN-1209 
-C1A TE0659 RSA-5AD1 456 7.20:1 S6LN-1208, S6LN-1209

14 of 15 E14EA  
NOTE 10. (cont’d) The following tabulation shows turbocharger , fuel injector, weight, compression ratio and ignition. 
 
Model 
 
Turbocharger 
 
Fuel Injection 
Weight 
(dry) lb. 
Compression 
Ratio 
 
Ignition, Dual * 
-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 RSA-10ED1 514 7.30:1  D6LN-3200, /2230 
-J2B TH08A60 RSA-10ED1 558 7.30:1  S61N-1208, S6LN-1209 
-J2BD TH08A60 RSA-10ED1 518 7.30:1  D6LN-3200, /2230 
-K1AD TE0695 RSA-5AD1 459 8.00:1  D6LN-3200, /2230 
-N2BD TE08A60 RSA-10ED1 518 7.30:1  D6LN-3200, /2230 
-S1AD TE0659 RSA-10ED1 502 7.30:1  D6LN-3000, /2231 
-R2AD TH08A69 RSA-10EB1 524 7.30:1  D6LN-3200, /2230 
-T2AD TH08A60 RSA-10ED1 549 7.30:1  D6LN-3200, /2230 
-U2A 3AU(V)2ME60H3 RSA-10ED1 578 7.30:1  S6LN-1258, S6LN-1259 
-J2B TH08A60 RSA-10ED1 558 7.30:1  S6LN-1208, S6LN-1209 
-V2AD TH08A69 RSA-10DB2 565 7.30:1  D6LN-3200 
-W2A TH08A69 RSA-10ED1 554 7.30:1  S6LN-1208, 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) RSA-10ED1 595 7.30:1  Slick 6263, 6260 (right) 
-AF1A TA0413 RSA-10ED1 473 8.00:1  Slick 6261, 6260 (right) 
-AF1B TA0413 RSA-10ED1 473 8.00:1  Slick 6261, 6260 (right) 
-AG1A TAO413 RSA-5AD1 485 8.00:1  Slick 6361, 6360 (right) 
-AH1A TAO413 RSA-10ED1 or 
FM-250 
542 7.30:1  Slick 6361, 6360 (right) 
-AJ1A TA6102 RSA-10ED1 532 7.30:1  Slick 6361, 6360 (right) 
-AK1A TA0411 RSA-5AD1 464 8.00:1  Slick 6361 (2) 
LTIO-540-
F2BD 
 
TE0659 
 
RSA-10ED1 
 
514 
 
7.30:1 
 
 D6RN-3200, /2230 
-J2BD TH08A60 RSA-10ED1 518 7.30:1  D6RN-3200, /2230 
-K1AD TE0695 RSA-5AD1 459 8.00:1  D6LN-3200, /2230 
-N2BD TH08A60 RSA-10ED1 518 7.30:1  D6RN-3200, /2230 
-U2A 3AU(V)2ME60H3 RSA-10ED1 578 7.30:1  S6LN-1258, S6LN-1259 
-J2B TH08A60 RSA-10ED1 558 7.30:1  S6LN-1208, S6LN-1209 
-V2AD TH08A69 RSA-10DB2 565 7.30:1  D6LN-3200 
-W2A TH08A69 RSA-10ED1 549 7.30:1  S6LN-1208, S6LN-1209 
 
 * For alternate magnetos see latest editi on of Lycoming Service Instruction No. 1443 
 ** TCM formally Bendix 
 
NOTE 11. Air from the compressor of the AiResearch Turboc harger is suitable for cabin pressurization.  The  
  installation must provide for cabin air temperat ure control from 300°F to 20,000 feet hot day condition 
  under maximum engine power.  For cabin air ou tlet flange dimensions see Lycoming Drawing No. 
  63444 for -R2AD model. 
 
  A sonic nozzle must be provided to preclude a ffecting 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. ra ting 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.

15 of 15 E14EA  
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 count erweights for use with a McCauley propeller. 
 
NOTE 16. Engines produced prior to September 25, 2006 may ha ve 20 degree timing. Owners and/or operators should refer 
to the engine dataplate for the correct timing setting. 
NOTE 17. The TIO-540-AHIA has an alternate rating of 40.0 in HG at 2500 rpm and limited to 5000 feet pressure altitude.   
 
 
 
 
.....END.....
```

## ADs (67, first 50, in force first)

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- [AD 97-15-11](https://openairdocs.org/ad/97-15-11): Cylinder kits · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 538 more. Effective Aug 12, 1997
- [AD 97-01-04](https://openairdocs.org/ad/97-01-04): Cylinder assemblies · Lycoming Engines IO-540-M1B5D, LTIO-540-F2BD, LTIO-540-J2B and 10 more. Effective Apr 22, 1997
- [AD 91-21-01 R1](https://openairdocs.org/ad/91-21-01-R1): Exhaust System Flanges · Lycoming Engines TIO-540-S1AD. Effective Jun 27, 1996
- [AD 95-26-02](https://openairdocs.org/ad/95-26-02): Aviation Gasoline · Lycoming Engines IO-320-B1A, IO-320-B1B, IO-320-B1C and 182 more. Effective Jan 24, 1996
- [AD 95-07-01](https://openairdocs.org/ad/95-07-01): Connecting Rod Bolt · Lycoming Engines AEIO-360-A1E, AEIO-360-B1G6, AEIO-360-H1A and 177 more. Effective Apr 12, 1995
- [AD 92-12-05](https://openairdocs.org/ad/92-12-05): Piston Pins · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 532 more. Effective Jul 10, 1992
- [AD 91-10-04](https://openairdocs.org/ad/91-10-04): Exhaust Transition Flange Bolts · Lycoming Engines TIO-540-AE2A. Effective May 21, 1991
- [AD 91-08-07](https://openairdocs.org/ad/91-08-07): Fuel Pump · Lycoming Engines TIO-360-A1A, TIO-360-A1B, TIO-360-A3B6 and 51 more. Effective May 6, 1991
- [AD 89-15-10](https://openairdocs.org/ad/89-15-10): Nozzle Vent Manifold · Lycoming Engines TIO-540-AE2A. Effective Nov 30, 1989
- [AD 87-10-06 R1](https://openairdocs.org/ad/87-10-06-R1): Rocker Arm Assembly · Lycoming Engines IO-360-B4, IVO-360-A1A, O-340-A1A and 243 more. Effective Sep 1, 1989
- [AD 84-19-03 R1](https://openairdocs.org/ad/84-19-03-R1): Cylinder Assemblies · Lycoming Engines LTIO-540-V2AD and TIO-540-V2AD. Effective Sep 20, 1984
- [AD 83-22-04](https://openairdocs.org/ad/83-22-04): Injector Fuel Diaphragm Stem · Lycoming Engines AEIO-540-L1B5D, IO-540-AA1A5, IO-540-G1B5 and 30 more. Effective Nov 4, 1983
- [AD 81-12-06 R1](https://openairdocs.org/ad/81-12-06-R1): Magnetos · Bendix Magnetos, LTIO-540-J2BD and TIO-540-J2BD. Effective Nov 12, 1981
- [AD 80-17-10](https://openairdocs.org/ad/80-17-10): Transition Wastegate Assembly · Lycoming Engines TIO-540-S1AD. Effective Aug 18, 1980
- [AD 79-04-05](https://openairdocs.org/ad/79-04-05): Regulator Diaphragm Stem Assembly · Lycoming Engines AEIO-320-D1B, AEIO-320-E1A, AEIO-320-E1B and 215 more. Effective Sep 26, 1979
- [AD 79-12-07](https://openairdocs.org/ad/79-12-07): Magnetos · Bendix Magnetos, TIO-540-F2BD, TIO-540-N2BD and 3 more. Effective Jun 19, 1979
- [AD 78-23-10](https://openairdocs.org/ad/78-23-10): Center Body Bellows Seal Assembly · Lycoming Engines AEIO-320-D1B, AEIO-320-E1A, AEIO-320-E1B and 218 more. Effective Nov 7, 1978
- [AD 73-23-01](https://openairdocs.org/ad/73-23-01): Piston Pin Assembly · Lycoming Engines AIO-360-A1A, AIO-360-A1B, AIO-360-A2A and 215 more. Effective Jan 13, 1977
- [AD 75-09-15](https://openairdocs.org/ad/75-09-15): Fuel Starvation To The Engine · Lycoming Engines AIO-320-A1A, AIO-320-A1B, AIO-320-A2A and 130 more. Effective Apr 30, 1975
- [AD 73-10-02](https://openairdocs.org/ad/73-10-02): Bendix Fuel Injectors · Bendix Fuel Injectors, AIO-320-A1A, AIO-320-A1B and 88 more. Effective May 16, 1973
- [AD 66-06-03](https://openairdocs.org/ad/66-06-03): Connecting Rod Assemblies · Lycoming Engines GO-435-C2 (O-435-17), GO-435-C2A, GO-435-C2A2 and 317 more. Effective Jan 16, 1969
- [AD 2024-21-02](https://openairdocs.org/ad/2024-21-02) (historical): Engine (Reciprocating) · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 548 more. Effective Dec 5, 2024
- [AD 2012-24-09](https://openairdocs.org/ad/2012-24-09) (historical): Turbocharger turbine wheel · Continental Motors TSIO-360-MB, TSIO-360-RB, TSIO-360-SB and 1 more. Effective Dec 20, 2012
- [AD 2011-26-04](https://openairdocs.org/ad/2011-26-04) (historical): Externally mounted fuel injector fuel lines · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1B and 186 more. Effective Jan 25, 2012

All 67: https://openairdocs.org/tcds/E14EA/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Lycoming TI0-540 series](https://openairdocs.org/engine/lycoming-ti0-540-series): 4,886 aircraft (registry code 41533)
- [Lycoming TIO-540-AJ1A](https://openairdocs.org/engine/lycoming-tio-540-aj1a): 720 aircraft (registry code 42004)
- [Lycoming TIO-540-AK1A](https://openairdocs.org/engine/lycoming-tio-540-ak1a): 508 aircraft (registry code 42005)
- [Lycoming TIO-540-AE2A](https://openairdocs.org/engine/lycoming-tio-540-ae2a): 488 aircraft (registry codes 41999, 40999)
- [Lycoming TIO-540 series](https://openairdocs.org/engine/lycoming-tio-540-series): 191 aircraft (registry codes 41569, 42500)
- [Lycoming TIO-540-AH1A](https://openairdocs.org/engine/lycoming-tio-540-ah1a): 90 aircraft (registry code 42003)
- [Lycoming TIO-540-J2BD](https://openairdocs.org/engine/lycoming-tio-540-j2bd): 24 aircraft (registry code 41977)
- [Lycoming TIO-540-AF1B](https://openairdocs.org/engine/lycoming-tio-540-af1b): 15 aircraft (registry code 42001)
- [Lycoming TIO-540-S1AD](https://openairdocs.org/engine/lycoming-tio-540-s1ad): 13 aircraft (registry code 41988)
- [Lycoming TIO-540-C1A](https://openairdocs.org/engine/lycoming-tio-540-c1a): 10 aircraft (registry code 41984)
- [Lycoming TIO-540-A2C](https://openairdocs.org/engine/lycoming-tio-540-a2c): 6 aircraft (registry code 41971)
- [Lycoming TIO-540-J2B](https://openairdocs.org/engine/lycoming-tio-540-j2b): 6 aircraft (registry code 41976)
- [Lycoming LTIO-540-J2BD](https://openairdocs.org/engine/lycoming-ltio-540-j2bd): 5 aircraft (registry code 41980)
- [Lycoming TIO-540-A1A](https://openairdocs.org/engine/lycoming-tio-540-a1a): 5 aircraft (registry code 41966)
- [Lycoming TIO-540-A2B](https://openairdocs.org/engine/lycoming-tio-540-a2b): 4 aircraft (registry code 41969)
- [Lycoming TIO-540-F2BD](https://openairdocs.org/engine/lycoming-tio-540-f2bd): 4 aircraft (registry code 41974)
- [Lycoming TIO-540-AF1A](https://openairdocs.org/engine/lycoming-tio-540-af1a): 3 aircraft (registry code 42000)
- [Lycoming TIO-540-U2A](https://openairdocs.org/engine/lycoming-tio-540-u2a): 3 aircraft (registry code 41990)
- [Lycoming TIO-540-AA1AD](https://openairdocs.org/engine/lycoming-tio-540-aa1ad): 2 aircraft (registry code 41996)
- [Lycoming TIO-540-V2AD](https://openairdocs.org/engine/lycoming-tio-540-v2ad): 2 aircraft (registry code 41992)
- [Lycoming LTIO-540-F2BD](https://openairdocs.org/engine/lycoming-ltio-540-f2bd): 1 aircraft (registry code 41975)
- [Lycoming TIO-540-AB1BD](https://openairdocs.org/engine/lycoming-tio-540-ab1bd): 1 aircraft (registry code 41998)
- [Lycoming TIO-540-AG1A](https://openairdocs.org/engine/lycoming-tio-540-ag1a): 1 aircraft (registry code 42002)
- [Lycoming TIO-540-K1AD](https://openairdocs.org/engine/lycoming-tio-540-k1ad): 1 aircraft (registry code 41986)
- [Lycoming TIO-540-R2AD](https://openairdocs.org/engine/lycoming-tio-540-r2ad): 1 aircraft (registry code 41982)
- [Lycoming LTIO-540-J2B](https://openairdocs.org/engine/lycoming-ltio-540-j2b): 0 aircraft (registry code 41979)
- [Lycoming LTIO-540-K1AD](https://openairdocs.org/engine/lycoming-ltio-540-k1ad): 0 aircraft (registry code 41987)
- [Lycoming LTIO-540-N2BD](https://openairdocs.org/engine/lycoming-ltio-540-n2bd): 0 aircraft (registry code 41981)
- [Lycoming LTIO-540-R2AD](https://openairdocs.org/engine/lycoming-ltio-540-r2ad): 0 aircraft (registry code 41983)
- [Lycoming LTIO-540-U2A](https://openairdocs.org/engine/lycoming-ltio-540-u2a): 0 aircraft (registry code 41991)
- [Lycoming LTIO-540-V2AD](https://openairdocs.org/engine/lycoming-ltio-540-v2ad): 0 aircraft (registry code 41993)
- [Lycoming LTIO-540-W2A](https://openairdocs.org/engine/lycoming-ltio-540-w2a): 0 aircraft (registry code 41995)
- [Lycoming TIO-540-A1B](https://openairdocs.org/engine/lycoming-tio-540-a1b): 0 aircraft (registry code 41967)
- [Lycoming TIO-540-A1C](https://openairdocs.org/engine/lycoming-tio-540-a1c): 0 aircraft (registry code 41970)
- [Lycoming TIO-540-A2A](https://openairdocs.org/engine/lycoming-tio-540-a2a): 0 aircraft (registry code 41968)
- [Lycoming TIO-540-AB1AD](https://openairdocs.org/engine/lycoming-tio-540-ab1ad): 0 aircraft (registry code 41997)
- [Lycoming TIO-540-E1A](https://openairdocs.org/engine/lycoming-tio-540-e1a): 0 aircraft (registry code 41972)
- [Lycoming TIO-540-G1A](https://openairdocs.org/engine/lycoming-tio-540-g1a): 0 aircraft (registry code 41985)
- [Lycoming TIO-540-H1A](https://openairdocs.org/engine/lycoming-tio-540-h1a): 0 aircraft (registry code 41973)
- [Lycoming TIO-540-N2BD](https://openairdocs.org/engine/lycoming-tio-540-n2bd): 0 aircraft (registry code 41978)
- [Lycoming TIO-540-T2AD](https://openairdocs.org/engine/lycoming-tio-540-t2ad): 0 aircraft (registry code 41989)
- [Lycoming TIO-540-W2A](https://openairdocs.org/engine/lycoming-tio-540-w2a): 0 aircraft (registry code 41994)

## STCs approved under this data sheet (43)

- [STC SE00825WI](https://openairdocs.org/stc/SE00825WI): Installation of Specialty Products Spin-on oil filter on Lycoming Engines.. B & C Specialty Products Inc.
- [STC SE04349CH](https://openairdocs.org/stc/SE04349CH): Installation of SureFly electronic ignition. SureFly Partners Ltd.
- [STC SE01954SE](https://openairdocs.org/stc/SE01954SE): Installation of engine crankcase seal.. Ly-Con Rebuilding Company
- [STC SE02352CH](https://openairdocs.org/stc/SE02352CH): Installation of Challenger cleanable oil filter assembly. Challenger Aviation Products Inc.
- [STC SE00939WI](https://openairdocs.org/stc/SE00939WI): Installation of B&C Specialty Products Model BC 315-( ) Starter on Lycoming engines.. B & C Specialty Products Inc.
- [STC SE2667CE](https://openairdocs.org/stc/SE2667CE): Installation of B&C Specialty Products lightweight (10.2 pounds) engine starter PN BC315-100-2(12 volt) or PN BC315-100-4 (24 volt).. B & C Specialty Products Inc.
- [STC SE03309CH](https://openairdocs.org/stc/SE03309CH): Installation of Engine Preheat Kit, p/n TSP6CYL-2927-115 for 115 volt application. Hartzell Propeller Inc.
- [STC SE01436LA](https://openairdocs.org/stc/SE01436LA): Installation of Firewall Forward Technologies LLC modified camshaft. Centri-lube Technologies LLC
- [STC SE04577CH](https://openairdocs.org/stc/SE04577CH): Install an electronic engine ignition system. Electroair Acquisition Corp
- [STC SE01966WI](https://openairdocs.org/stc/SE01966WI): Use of GAMI G100UL High Octane Unleaded Avgas in spark ignition piston aircraft engines. General Aviation Modifications Inc.
- [STC SE8628SW](https://openairdocs.org/stc/SE8628SW): Installation of oil nozzles for lubrication of cam and filters.. Cygnet Aerospace Corp
- [STC SE04445AT](https://openairdocs.org/stc/SE04445AT): Installation of Continental Motors, Inc. (CMI) S-1200 Series Magnetos (10-349290-1 and 10-349310-1) and associated hardware. Continental Motors Inc.
- [STC SE09445SC](https://openairdocs.org/stc/SE09445SC): Installation of fuel injector nozzles.. General Aviation Modifications Inc.
- [STC SE4408SW](https://openairdocs.org/stc/SE4408SW): Miscellaneous engine cylinder replacement parts.. Continental Motors, Inc.
- [STC SE7503SW](https://openairdocs.org/stc/SE7503SW): Installation of any or all parts listed on Airmotive Engineering Drawing List No. 852-1, Rev. 1, dated 10/4/88, or later FAA approved revision.. Continental Motors, Inc.
- [STC SE7668SW](https://openairdocs.org/stc/SE7668SW): Installation of parts listed on Drawing List 8810-3, Rev 6.. Continental Motors, Inc.
- [STC SE8776SW](https://openairdocs.org/stc/SE8776SW): Installation of coated cylinders and piston rings.. Continental Motors, Inc.
- [STC SE00226NY](https://openairdocs.org/stc/SE00226NY): Replacement of Lycoming starter with SKY-TEC 24-volt starter Models 149-24HT and 122-24HT. Approval limited to 24-volt DC source available to the starter.. Hartzell Engine Technologies, LLC
- [STC SE3329NM](https://openairdocs.org/stc/SE3329NM): Lycoming valve cover gasket. Real Gaskets Tennessee
- [STC SE01211SE](https://openairdocs.org/stc/SE01211SE): Installation of the Merlyn Products Inc. turbocharger system. Merlyn Products Inc.
- [STC SE2569NM](https://openairdocs.org/stc/SE2569NM): Relocation of Turbocharger, intercooler, fuel control unit, and upper engine mounts plus associated changes. Javelin Conversions Inc.
- [STC SE02436AT](https://openairdocs.org/stc/SE02436AT): Installation of 200F series fuel pump assembly.. Kelly Aerospace Energy Systems LLC
- [STC SE02555AT](https://openairdocs.org/stc/SE02555AT): Consolidated Fuel Systems 201F series fuel pump assembly on various Textron Lycoming engine models.. Kelly Aerospace Energy Systems LLC
- [STC SE8193SW](https://openairdocs.org/stc/SE8193SW): Grind nitriden high compression cylinder barrles to plus .010 oversize and install SL75089 P10 piston, SL74242 P10 compression ring, and SL73857 P10 oil ring.. Superior Air Parts Inc.
- [STC SE02599CH](https://openairdocs.org/stc/SE02599CH): SERIAL NUMBERS L-9034-61A and L-1722-68A:  Installation of AIR BP piston engine lubricating oil MDM100-QB2050AD-01 in Textron Lycoming model IO-540-J2BD horizontally opposed reciprocating engine. SERIAL NUMBERS serial numbers L-9034-61A and L-1722-68A. Air BP Atlanta
- [STC SE445GL](https://openairdocs.org/stc/SE445GL): Incorporation of a fuel flow transducer.. Shadin Avionics
- [STC SE01930NY](https://openairdocs.org/stc/SE01930NY): Installation of Casper Labs 90 degree oil filter housing adapter.. Casper Labs Inc
- [STC SE1779NM](https://openairdocs.org/stc/SE1779NM): Installation of Precise Flight, Inc. Standby Vacuum System SVS III. Precise Flight Inc
- [STC SE5743NM](https://openairdocs.org/stc/SE5743NM): Intallation of adapter for externally mounted oil filter.. Aviation Development Corporation
- [STC SE00890LA](https://openairdocs.org/stc/SE00890LA): Installation of Nickson's cylinder barrels on Lycoming reciprocating engine models.. Nickson's Machine Shop Inc
- [STC SE3177NM](https://openairdocs.org/stc/SE3177NM): Installation of Machin, Inc. intercooler & associated systems.. American Aviation Inc
- [STC SE978NW](https://openairdocs.org/stc/SE978NW): Installation of a Garrett AiResearch Model  T18A21 or T18A95 turbocharger with Machen Inc intercooler and associated systems.. Machen Inc
- [STC SE09492SC](https://openairdocs.org/stc/SE09492SC): Installation and usage of Exxon 20W50 multigrade aircraft engine oil conforming to Exxon Oil formulation WS-3013.. Exxon Company USA
- [STC SE00350SE](https://openairdocs.org/stc/SE00350SE): Installation of sump mounted chip detector.. Aviation Development Corporation
- [STC SE7674SW](https://openairdocs.org/stc/SE7674SW): Grind nitrided cylinder barrels plus .010 over size pistons, to .010 and install SL10545P10 SL74241P10 compression rings and SL73857P10 Oil Control rings.. Superior Air Parts, Inc
- [STC SE8023SW](https://openairdocs.org/stc/SE8023SW): Installation and usage of AEROSHELL. Shell Development Co
- [STC SE3762NM](https://openairdocs.org/stc/SE3762NM): Installation of modified oil filter adapter.. Enhance, Inc
- [STC SE452NE](https://openairdocs.org/stc/SE452NE): Installation and usage of 'Mobil AV 1' aviation oil.. Mobil Research & Development Corp
- [STC SE5879SW](https://openairdocs.org/stc/SE5879SW): Use of Phillips X/C II 20W-50 and25W-60 oil (OSS 55875) in all Avco reciprocating aircraft engines from 65 to 450 BHP.. Phillips Petroleum Co
- [STC SE244NE](https://openairdocs.org/stc/SE244NE): Installation of Mattituck plasma flame sprayed cylinder barrels in Teledyne reciprocating engines.. Mattituck Airbase, Inc
- [STC SE80NE](https://openairdocs.org/stc/SE80NE): Installation and usage of Bel-Ray synthetic aviation oil, Bel-Ray Aero 1, (nonsupercharged), horizontally opposed direct drive, aircraft engines of 350 hp. or less.. Bel-Ray Company, Inc
- [STC SE128NE](https://openairdocs.org/stc/SE128NE): Use of AMS/OIL 15W 50 synthetic piston aircraft oil in Avco engines.. AMS/OIL
- [STC SA01436DE](https://openairdocs.org/stc/SA01436DE) (historical): Installation of Firewall Forward Technologies, LLC modified camshaft.. Centri-Lube Technologies LLC

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OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.