# TCDS E6NE: CFS Aeroproducts Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: CFS Aeroproducts Inc.
- Revision: 17
- Revised: January 11, 2023
- Product: Engine
- Certification basis: Part 33
- Registered aircraft: 56, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/94/7d/947d715d29d13bfe0441cb032ee8db7169ebe87c8fa7de32e587100018a53351
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID147831413920230111193707.0001
- Page: https://openairdocs.org/tcds/E6NE

## Models (12)

As the data sheet lists them.

- ALF502L-2C
- LF507-1F
- ALF502R-6
- LF507-1H
- ALF502L-2A
- ALF502L-3
- ALF502R-3
- ALF502R-5
- ALF502R-3A
- ALF502R-4
- ALF502L-2
- ALF502L

## What the data sheet says

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

```text
E6NE 
Revision 17 
CFS AEROPRODUCTS INC. 
ALF502L 
ALF502L-2 
ALF502L-2A 
ALF502L-2C 
ALF502L-3 
ALF502R-3 
ALF502R-3A 
ALF502R-4 
ALF502R-5 
ALF502R-6 
LF507-1H 
LF507-1F 
Date: JANUARY 11, 2023 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
TYPE CERTIFICATE DATA SHEET NO. E6NE 
Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E6NE) and other 
approved data on file with the Federal Aviation Administration (FAA), meet the minimum standards for use in certificated  
aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided 
they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved 
instructions. 
TYPE 
CERTIFICATE (TC) HOLDER: CFS Aeroproducts Inc. 
2133 Aviation Dr. Suite 201 
Upland, CA 91786 
USA 
TYPE CERTIFICATE OWNERSHIP RECORD:  Honeywell International Inc. reissued December 15, 1990 
111 South 14th Street 
Phoenix, AZ 85034 
Allied
Signal reissued December 14, 1999 
Tex
tron Lycoming issued January 31, 1995 
TYPE 
ALF502R-3 High bypass turbofan, geared fan, single-stage supercharger, axial-centrifugal flow high pressure compressor, 
reverse flow annular combustor, two-stage high pressure turbine, two-stage low pressure turbine. 
ALF502R-4 Same as ALF502R-3, but operated at higher thrust. 
ALF502R-5 Same as ALF502R-4, with improved first-stage and second-stage turbine nozzle assemblies. 
ALF502R-3A Same as ALF502R-3, with gas producer turbine improvements, but operated at higher thrust. 
ALF502L High bypass turbofan, geared fan, two-stage supercharger, axial-centrifugal flow high pressure compressor, 
reverse flow annular combustor, two-stage high pressure turbine, two-stage low pressure turbine. 
ALF502L-2 Same as ALF502L with fan blade modification for increased altitude performance. 
ALF502L-3 Same as ALF502L-2 with turbine improvements and automatic power reserve features. 
ALF502L-2A Same as ALF502L-2 with gas producer turbine improvements and automatic power reserve features. 
* 
PAGE 1 2 3 4 5 6 7 8 9 
REV. 16 15 16 14 15 15 15 15 16 
LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
"---" INDICATES "DOES NOT APPLY" 
NOTICE: SIGNIFICANT CHANGES ARE BLACK-LINED

E6NE 2 
ALF502L-2C Mechanically identical to ALF502L-2A, but does not include automatic power reserve . 
ALF502R-6 Similar to ALF502L-2C, but incorporates ALF502R-5 accessory gearbox. 
LF507-1H Mechanically identical to ALF502R-6, but operated at lower, flat-rated thrust. 
LF507-1F Mechanically identical to LF-507-1H, but equipped with a single-channel FADEC with hydromechanical backup. 
RATINGS (SEE NOTE 1) 
I. MODELS: ALF502R-3 ALF502R-4 ALF502R-5 ALF502R- 
3A 
ALF502L ALF502L- 
2 
ALF502L- 
3 
Sea level static thrust, lbs 
Maximum Continuous 
Normal Takeoff (5 min) 
(Note 19) 
Maximum Takeoff (5 min) 
(Note 19) 
6,300 
6,700 
6,700 
6,550 
6,970 
6,970 
- - 
- - 
- - 
- - 
- - 
- - 
7,100 
7,500 
7,500 
- - 
- - 
- - 
- - 
- - 
- - 
II. MODELS: ALF502L- 
2A 
ALF502L- 
2C 
ALF502R-6 LF507-1H LF507-1F 
Sea level static thrust, lbs 
Maximum Continuous 
Normal Takeoff (5 min) 
(Note 19) 
Maximum Takeoff (5 min) 
(Note 19) 
7,100 
7,500 
7,500 
- - 
- - 
- - 
- - 
- - 
- - 
6,545 
7,000 
7,000 
- - 
- - 
- -

3 
COMPONENTS 
Fuel control 
Models ALF502R-3/R-4/R-5/R-3A/R-6 / LF507-1H 
Models ALF502L/L-2/L-3/L-2A/L-2C 
Model LF507-1F 
High pressure fuel pump 
Low pressure fuel pump 
Ignition system (28-volts DC) 
Ignitor plugs 
FUEL (See NOTE 2) 
OIL (See NOTE 3) 
PRINCIPAL DIMENSIONS (nominal, inches) 
Length, nominal, inches 
Models ALF502R-3/R-4/R-5/R-3A 
Models ALF502L/L-2/L-3/L-2A/L-2C/R-6/ LF507-1H/1F 
WEIGHT (dry pounds, maximum) 
Models ALF502L-2A/L2C/L-3 
Models ALF502R-3/R-4/R-5/R-3A 
Models ALF502L/L-2 
Model LF507-1H/ALF502R-6 
Model LF507-1F 
C.G. LOCATION (refer to Engine Installation Instructions)
Model ALF502R-3/R-4/R-5/R-3A
Models ALF502L/L-2/L-3/L-2A/L-2C/R-6/ LF507-1H/-1F 
 
DESCRIPTION 
Hamilton Sundstrand FC 31 -23 
H
amilton Sundstrand FC 31-19 
Triumph Engine Control Systems EMC-32R F ADEC  
Hamilton Sundstrand 025028-110 or 
Triumph Engine Control Systems 774959-1 
2-160-790-08 or equivalent
I
gnition exciter units (Unison or Champion), completely redundant ignition 
s
ystems with additional "continuous-on-demand" ignition compatibility 
Champion spark plug P/N CH34084 or equivalent 
A
STMD1655 Jet A, Jet  A-1, Jet B, MIL-T-5624J 
Grades JP-4, JP-5, and JP-8 or equivalent 
MIL-L-7808 and MIL-L-23699 or equivalent 
LENGTH  HEIGHT WIDTH 
63.657 55.5 47.8 
65.57 54.5 48.6 
Weight includes essential engine accessories but excludes starter, hydraulic pump, 
integrated drive generator and exhaust nozzle. 
1,375 
1,336 
1,375 
1,375 
1,385 
STA B.L. W.L.
105.200 100.000 98.250 
104.8 100.29 98.6 
E6NE

4 
CERTIFICATION BASIS 14 CFR part 33 effective February 1, 1965, as amended by 33-1/-2/-3A/-4 and Special Condition 
Number 33-66-NE-1. 
MODEL 
APPLICATION 
DATE 
TYPE CERTIFICATE 
ISSUED/AMENDED 
TYPE CERTIFICATE 
CANCELED 
ALF502H 
ALF502R 
ALF502L 
ALF502L-2 
ALF502R-3 
ALF502R-4 
ALF502R-5 
ALF502L-3 
ALF502L-2A 
ALF502R-3A 
ALF502L-2C 
ALF502R-6 
LF507-1H 
LF507-1F 
10/09/73 
06/03/76 
02/01/77 
02/11/80 
10/15/78 
10/06/81 
10/06/81 
10/15/81 
10/14/82 
10/14/82 
07/20/83 
06/22/84 
03/25/91 
03/25/91 
06/11/76 
06/11/76 
02/29/80 
02/29/80 
01/16/81 
04/14/82 
07/02/82 
11/30/82 
01/07/83 
01/07/83 
08/24/83 
12/12/84 
10/15/91 
03/20/92 
01/16/81 
01/16/81 
PRODUCTION BASIS None 
NOTES 
NOTE 1. Engine ratings are based on calibrated static test stand performance under the following conditions: 
Static sea level standard condition at 59oF and 29.92 in. Hg. 
No airbleed, no duct losses, no external power extraction. 
Engine primary exhaust and fan bypass exhaust system as specified in Figures 3 and 4 of the 
applicable engine installation instructions. 
NOTE 2. Engines will operate satisfactorily with fuel contaminated to the levels specified in Paragraph 4.4.1 of 
the installation instructions for the LF507-1F engine models, and Paragraph 4.4.3 of the installation 
instructions for the ALF502R, ALF502L and LF507-1H engine models provided the fuel is introduced 
to the engine through a filter satisfying the requirements of the subject paragraph. 
NOTE 3. Mixing of these oils (MIL-L-7808 and MIL-L-23699) is prohibited. 
NOTE 4. Maximum permissible operating speeds for the engine rotors are as follows: 
Low Pressure Rotor 
(N1) RPM 
ALF502 
R-3 
ALF502 
R-4 
ALF502 
R-5 
ALF502 
R-3A 
ALF502 
L 
ALF502 
L-2 
ALF502 
L-3 
ALF502 
L-2A 
ALF502 
L-2C 
Maximum takeoff 
Normal takeoff 
Maximum continuous 
7,300 
7,300 
7,300 
7,350 
7,350 
7,350 
7,374 
7,374 
7,374 
- - 
- - 
- - 
7,300 
7,300 
7,300 
- - 
- - 
- - 
7,374 
7,184 
7,374 
- - 
- - 
- - 
- - 
7,374 
- - 
Low Pressure Rotor 
(N1) RPM 
ALF502 
R-6 
LF507- 
1H 
LF507- 
1F 
Maximum takeoff 
Normal takeoff 
Maximum continuous 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
High Pressure Rotor 
(N2) RPM 
ALF502R 
-3 
ALF502R- 
4 
ALF50 
2R-5 
ALF50 
2R-3A 
ALF502 
L 
ALF502L 
-2 
ALF502 
L-3 
ALF502 
L-2A 
ALF502 
L-2C 
Maximum takeoff 
Normal takeoff 
Maximum continuous 
19,640 
19,640 
19,380 
- - 
- - 
- - 
19,760 
19,760 
- - 
- - 
- - 
- - 
19,640 
19,640 
19,280 
- - 
- - 
- - 
19,700 
19,420 
- - 
- - 
- - 
- - 
19,640 
19,640 
- - 
E6NE

5 
High Pressure Rotor 
(N2) RPM 
ALF502R 
-6 
LF507-1H LF507- 
1F 
Maximum takeoff 
Normal takeoff 
Maximum continuous 
19,760 
19,760 
19,380 
- - 
- - 
- - 
- - 
- - 
- - 
NOTE 5. MAXIMUM PERMISSIBLE TEMPERATURES 
Starting maximum (*) 
Maximum takeoff (5 min) 
Normal takeoff (5 min) 
Maximum continuous 
Transient for acceleration 
Maximum takeoff (**) 
Normal takeoff (**) 
GAS TEMPERATURE (DEGREES FAHRENHEIT) AS MEASURED BY 10 THERMOCOUPLES 
MOUNTED BETWEEN THE THIRD TURBINE NOZZLE VANES 
ALF502 
R-3 
ALF502 
R-4 
ALF502 
R-5 
ALF502 
R-3A 
ALF502 
L 
ALF502 
L-2 
ALF502 
L-3 
ALF502 
L-2A 
ALF502 
L-2C 
1590 
1620 
1620 
1574 
1620 
1620 
- - 
1660 
1660 
1610 
1660 
1660 
- - 
- - 
1620 
1574 
- - 
1620 
- - 
- - 
- - 
- - 
- - 
- - 
1515 
1660 
1660 
1610 
1660 
1660 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
1668 
1593 
1574 
1668 
1593 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
1620 
1620 
- - 
1620 
1620 
(*) Time limit 10 seconds above 1560oF for ALF502R and LF507-1H and 1460oF for 
ALF502L series 
(**) Time limit 15 seconds above takeoff limit 
GAS TEMPERATURE (DEGREES FAHRENHEIT) AS MEASURED BY 10 THERMOCOUPLES 
MOUNTED BETWEEN THE THIRD TURBINE NOZZLE VANES 
ALF502R-6 LF507-1H 
Starting maximum (*) 1590 - - 
Maximum takeoff (5 min) 1660 1660 
Normal takeoff (5 min) - - - - 
Maximum continuous 1574 - - 
Transient for acceleration 
Maximum takeoff (**) 1660 1660 
Normal takeoff (**) - - - - 
(*) 
(**) 
Time limit 10 seconds above 1560oF for ALF502R and LF507-1H and 1460oF for 
ALF502L series 
Time limit 15 seconds above takeoff limit 
EXHAUST GAS TEMPERATURE (DEGREES FAHRENHEIT) AS MEASURED BY 16 
THERMOCOUPLE PROBES 
LF507-1F 
Starting maximum (*) 1,360 
Maximum takeoff (5 min) 1,169 
Normal takeoff (5 min) 1,169 
Maximum continuous 1,136 
Transient for acceleration 
Maximum takeoff (**) 1,169 
Normal takeoff (**) 1,169 
(*) For LF507-1F time limit 10 seconds above 1315oF 
(**) For LF507-1F time limit 15 seconds above takeoff limit 
NOTE 5. MAXIMUM PERMISSIBLE TEMPERATURES (continued) 
E6NE

6 
OIL TEMPERATURES / MAXIMUM / DEGREES FAHRENHEIT 
ALF502 
R-3 
ALF502 
R-4 
ALF502 
R-5 
ALF502 
R-3A 
ALF502 
L 
ALF502 
L-2 
ALF502 
L-3 
ALF502 
L-2A 
ALF502 
L-2C 
271** - - - - - - 290* - - - - - - - - 
* Transient oil temperatures as high as 340oF can be experienced when undergoing a
power reduction. Recovery to acceptable oil inlet temperature should occur after two
minutes steady-state operation.
** Transient oil temperatures as high as 320oF can be experienced when undergoing a
power reduction. Recovery to acceptable oil inlet temperature should occur after two
minutes steady-state operation.
OIL TEMPERATURES / MAXIMUM / DEGREES FAHRENHEIT 
ALF502 
R-6 
LF507- 
1H 
LF507- 
1F 
271** - - - - 
* Transient oil temperatures as high as 340oF can be experienced when undergoing a
power reduction. Recovery to acceptable oil inlet temperature should occur after two
minutes steady-state operation.
** Transient oil temperatures as high as 320oF can be experienced when undergoing a
power reduction. Recovery to acceptable oil inlet temperature should occur after two
minutes steady-state operation.
ACCESSORY TEMPERATURE LIMITS / ALL MODELS 
Additional accessory temperature data are specified in Table III of the LF507-1H engine model 
installation instructions, and Table IV of the applicable installation instructions for other 
ALF502/LF507 engine models. 
AMBIENT OR SURFACE DEGREES 
TEMPERATURE FAHRENHEIT 
Fuel control assembly Ambient 260 
Overspeed fuel shut-off valve Ambient 200 
Ignition unit Ambient 250 
Overspeed control Surface 212 
Fuel manifold Surface 390 
Interstage bleed actuator Ambient 350 
Anti-icing valve Ambient 350 
Fan speed sensor Surface 400 
Electronic control unit Ambient 185 (*) 
(*) The electronic control unit (ECU) can operate continuously in an ambient 
temperature range of minus 65oF to plus 185oF. In addition, the ECU can 
operate for up to 5 minutes at a maximum transient temperature of 212oF. 
E6NE

7 
NOTE 6. FUEL AND OIL PRESSURE LIMITS / ALL MODELS 
ALF502 
R-3 
ALF502 
R-4 
ALF502 
R-5 
ALF502 
R-3A 
ALF502 
L 
ALF502 
L-2 
ALF502 
L-3 
ALF502 
L-2A 
ALF502 
L-2C 
Fuel 
Maximum (psig) 
Minimum (*) 
35 - - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
(*) True fuel vapor pressure plus 5 psi 
Oil (psig) 
Sea level (*) 
Ground idle 
97+10 
25 
- - 
- - 
- - 
- - 
(*) At maximum continuous power and above plus 5 psi 
ALF502 
R-6 
LF507 
1H 
LF507 
1F 
Fuel 
Maximum (psig) 
Minimum (*) 
- - 
- - 
- - 
- - 
- - 
- - 
(*) True fuel vapor pressure plus 5 psi 
Oil (psig) 
Sea level (*) 
Ground idle 
- - 
- - 
- - 
- - 
- - 
- - 
(*) At maximum continuous power and above plus 5 psi 
NOTE 7. 
ACCESSORY DRIVE PROVISIONS 
ALF502L, L-2 / L-3 / L-2A / L-2C / R-3 / R-3A/ R-4 / R-5 / R-6 models 
ALF507-1H / -1F models. 
Maximum accessory power extraction (shp) is shown in installation instructions paragraph 
4.1.2., Figures 12. 
ACCESSORY DRIVES FOR ALF502R-3 / R-4 / R5- / R-3A / R-6 / LF507-1H / -1F 
DRIVE TYPE 
ROTATION 
FACING 
ENGINE 
PAD 
SPEED Tc Ts To Tst Tmt 
MAXIMUM 
OVERHANG 
MOMENT 
(lb-in) 
Starter Special (1) CW 0.8621(2) --- 855 --- 246 --- 200 
Hydraulic Pump AND2000-1X1B (MOD) CCW 0.253(2) 300 --- 855 234 590 150 
IDG/CSD (3) AS970A-13V (MOD) CW 0.458(2) --- --- 1596 505 1200 
(1) Details of pad type and design are available in Table III and in the installation drawings of the applicable engine
installation instructions.
(2) Speed of the drive – is equal to the constant provided multiplied by the engine high pressure rotor (N2) speed.
(3) IDG/CSD pad rating is 96 shp at any engine speed
CW = clockwise 
CCW = counterclockwise 
Tc  = continuous torque rating (lb-in) 
Ts = static torque rating (lb-in) 
To = overload torque rating (5 minutes lb-in) 
Tst = shock torque rating (lb-ft) 
Tmt = normal maximum torque (20 seconds lb-in) 
E6NE

8 
NOTE 7. (CONTINUED) 
ACCESSORY DRIVES FOR ALF502L / L-2 / L-3 / L-2A / L-2C 
DRIVE SPECIFICATION 
(8) 
TYPE 
ROTATION 
FACING 
ENGINE 
PAD 
GEAR 
RATIO 
(6) 
CONT 
(1) EMERGENCY 
IMPACT (5) 
Starter AND20002-XII-D MODIFIED CCW 0.458 1200 (4) - - 4000 
Boost Pump SPECIAL CCW 0.214 70 - - 1000 
Power Takeoff AS970A-13V MODIFIED CW 0.458 (9) 1120 (2) 4000 
1541 (3) 
Hydraulic Pump AND20001-X1-B MODIFIED CCW 0.253 (9) 227 (7) 1250 
(1) Max permissible continuous torque at any engine speed (lb-in) 
(2) Max permissible torque for 10 minutes, (in-lb) 
(3) Max permissible torque for 7 seconds, (in-lb) 
(4) Max peak torque during starting cycle
(5) Max impact torque (in-lb) 
(6) Relative to N2 speed
(7) Maximum permissible torque for 10 minutes (lb-in). Power takeoff pad not to exceed 560 in-lb at this condition.
(8) See specification for overhang moment
(9) Continuous power extraction capability under all operating conditions is as follows:
Power takeoff: 60 shp 
Hydraulic pump pad: 5 shp 
(10) See Installation Drawing
NOTE 8. For in-flight operation in icing conditions, the minimum permissible N2 rpm is 67%.  However, 
momentary N2 excursions down to 60%, not exceeding 60 seconds duration, are permissible within 
300 feet above ground level (AGL) during final approach to landing. 
NOTE 9. Engine starting torque and speed requirements are shown in Figure 7 of the applicable engine 
installation instructions. 
NOTE 10. These engines meet the fire prevention requirements of Special Condition No. 33- 66-NE-1 providing 
the compartment ventilation design requirements of Paragraph 4.6.2, 4.6.2.1, and 4.6.2.2 of the 
applicable engine installation instructions are met. 
NOTE 11. Customer bleed air extraction limits are shown in Paragraph 4.9 of the ALF502L/L-2/L-3/ 
L-2A/L-2C installation instructions and Paragraph 3.1.1 of the ALF502R-3/R-4/R-5/R-3A/
R-6/LF507-1H/-1F installation instructions.
NOTE 12. Fuel venting; emission control is not included on these engines and therefore airframe compliance 
must be provided in accordance with SFAR-27 (superceded by part 34). 
NOTE 13. These engines may use approved type fuels separately or mixed in any proportion.  Fuel control 
adjustments are not required when switching fuel types. Fuel additives and concentrations by volume 
approved for use in fuels for these engines are provided in the applicable engine manual. 
E6NE

9 
NOTE 14. Certain engine parts are life limited.  For ALF502R-3/R-4/R-5/R-3A and R-6, these limits are listed in 
the manufacturer's Service Bulletin No. ALF502-72 -0002. For the ALF502L/L -2/L-3/L-2A and L - 
2C, they are listed in Service Bulletin No. ALF502 -72-0004. For model LF507-1H, they are listed in 
Service Bulletin No. LF507 -1H-72-2. For model LF507- 1F, they are listed in Service Bulletin No. 
LF507-1F-72-2. 
NOTE 15. Overhaul and hot end inspection intervals for models ALF502R -3/R-4/R-5/R-3A and R -6 are  
specified in the manufacturer's Service Bulletin No. ALF502 -72-0001. For models ALF502L/L -2/L- 
3/L-2A and L-2C, they are specified in Service Bulletin No. ALF502 -72-0005. For model LF507-1H, 
they are specified in Service Bulletin LF507 -1H-72-1. For model LF507- 1F, they are specified in 
Service Bulletin LF507-1F-72-1. 
These Time Between Inspection/Time Between Overhaul Service Bulletin Nos. ALF502 -72- 
0001/LF507-1F-72-1/LF507-1H-72-1 do not apply to FA A approved continuous airworthiness 
maintenance programs developed in accordance with FAA Maintenance Review Board procedures; 
e.g. Maintenance Steering Group III Analysis.
NOTE 16. Deleted. 
NOTE 17. The ALF502L, L-2,  L-3,  L-2A,  L-2C, R-3,  R- 4, R-5,  R- 3A, R-6 and LF507-1H and - 1F models 
comply with the windmill test requirement of part 33.92, Amendment 9, up to a N1 of 2,000 rpm and a 
N2 of 3,420 rpm. 
NOTE 18. ALF502L, L-2, L-3, L-2A, L-2C, R-3,  R-4, R-5, R-3A, R-6, and LF507-1H and 1F models comply 
with the instrument connection requirement of part 33.29, Amendment 5. 
NOTE 19. A thrust setting limited to 7,800 lbs. (ALF502L -3 and ALF502L -2A) static thrust at sea level, has  
been established as maximum takeoff thrust rating. A thrust setting limited to 7,500 lbs. (ALF502L-3, 
ALF502L-2A, and ALF502L -2C) static thrust at sea level, has been established as normal takeoff 
thrust rating for normal takeoff operation. 
When the automatic reset mechanism in the fuel control is utilized, operation to the norma l takeoff 
rating operating limits will insure the maximum takeoff rating operating limits are not exceeded when 
the reset mechanism is actuated. 
The time limit at the maximum takeoff rating is five minutes and shall include any time accumulated 
above the normal takeoff rating. 
NOTE 20. For the ALF502R -5 and ALF502R-3A: A thrust setting limited to 6,970 lbs. static thrust at sea level 
flat rated to 71oF with a maximum MGT of 1660 oF has been established as a maximum takeoff thrust 
rating. A thrust setting limited to 6,970 lbs. static thrust as sea level flat rated to 59 oF with a  
maximum MGT of 1620 oF has been established as the normal takeoff rating for normal operation of 
this model. 
For the LF507-1H: A thrust setting limited to 7,000 pounds static thrust  at sea level flat rated to 85 oF 
with a maximum MGT of 1660oF has been established as the maximum takeoff thrust rating.  A thrust 
setting limited to 7,000 pounds static thrust at sea level flat rated to 74 oF with a maximum MGT of 
1620oF has been established as the normal takeoff rating for normal operation of this model. 
For the LF507-1F: A thrust setting limited to 7,000 pounds static thrust at sea level flat rated to 74 oF 
with a maximum EGT of 1169 oF has been established as the normal takeoff rating for normal  
operation of this model. 
E6NE

10 
NOTE 21. The LF507-1F in the manual backup control mode operating configuration is in compliance with the 
Certification Basis defined herein, when operated in accordance with the instructions contained in the 
approved manufacturers operating instructions for Part Number 2-003-040-15. 
….END…. 
E6NE
```

## ADs (28, in force first)

- [AD 2020-18-09](https://openairdocs.org/ad/2020-18-09): Engine (Turbine/Turboprop); Engine Fuel and Control; Engine Emergency Shutdown System · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 9 more. Effective Oct 21, 2020
- [AD 2012-11-07](https://openairdocs.org/ad/2012-11-07): LP turbine blades · Honeywell International ALF502L-2C, ALF502R-3, ALF502R-3A and 3 more. Effective Jul 5, 2012
- [AD 2011-24-11](https://openairdocs.org/ad/2011-24-11): Disc Fracture · Honeywell International ALF502L-2C, ALF502R-3, ALF502R-3A and 3 more. Effective Dec 14, 2011
- [AD 2009-26-06](https://openairdocs.org/ad/2009-26-06): Fuel manifold assemblie · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 9 more. Effective Feb 11, 2010
- [AD 2009-08-07](https://openairdocs.org/ad/2009-08-07): High-pressure compressor (HPC) first stage discs · Honeywell International ALF502L-2 and ALF502L-2C. Effective May 18, 2009
- [AD 2006-09-13](https://openairdocs.org/ad/2006-09-13): Turbofan engines · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 7 more. Effective Jun 13, 2006
- [AD 2003-02-01](https://openairdocs.org/ad/2003-02-01): Drain tube assemblies · Honeywell International ALF502L-2, ALF502L-2C, ALF502R-3 and 1 more. Effective Jan 30, 2003
- [AD 2002-22-12](https://openairdocs.org/ad/2002-22-12): Titeflex hoses · BAE Systems ATP, Avro 146-RJ100A, Avro 146-RJ70A and 122 more. Effective Dec 13, 2002
- [AD 2002-22-06](https://openairdocs.org/ad/2002-22-06): Combustion chamber liner assembly · Honeywell International ALF502R-3, ALF502R-3A, ALF502R-4 and 4 more. Effective Nov 18, 2002
- [AD 2002-12-08](https://openairdocs.org/ad/2002-12-08): Gas Producer Turbine (GPT) Components · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 9 more. Effective Jul 17, 2002
- [AD 2000-11-15](https://openairdocs.org/ad/2000-11-15): Critical Life-Limited Parts · Honeywell International ALF502R-3, ALF502R-3A, ALF502R-4 and 4 more. Effective Jul 10, 2000
- [AD 2000-05-14](https://openairdocs.org/ad/2000-05-14): Bearing Inlet Assembly · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 9 more. Effective Apr 27, 2000
- [AD 99-15-06](https://openairdocs.org/ad/99-15-06): Fan Core Inlet Anti-Ice System · Honeywell International ALF502R-3A and ALF502R-5. Effective Sep 17, 1999
- [AD 96-04-02](https://openairdocs.org/ad/96-04-02): Compressor and Turbine Disks · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 2 more. Effective Apr 29, 1996
- [AD 95-03-15](https://openairdocs.org/ad/95-03-15): Compressor Rotor Disk · Honeywell International ALF502R-3, ALF502R-3A, ALF502R-4 and 2 more. Effective May 8, 1995
- [AD 93-14-13](https://openairdocs.org/ad/93-14-13): Third Stage Turbine Disk · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 7 more. Effective Oct 4, 1993
- [AD 93-10-07](https://openairdocs.org/ad/93-10-07): Third Stage Compressor Disks · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 7 more. Effective Aug 10, 1993
- [AD 92-08-51](https://openairdocs.org/ad/92-08-51): Engine Fuel Control · Honeywell International ALF502R-3, ALF502R-3A, ALF502R-4 and 2 more. Effective Mar 18, 1993
- [AD 91-14-05](https://openairdocs.org/ad/91-14-05): High Compressor Rotor Disks · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 2 more. Effective Jul 15, 1991
- [AD 90-24-01](https://openairdocs.org/ad/90-24-01): High Compressor Disks · Honeywell International ALF502R-3, ALF502R-3A, ALF502R-4 and 2 more. Effective Nov 13, 1990
- [AD 87-15-03](https://openairdocs.org/ad/87-15-03): Gas Producer Turbine Spacer · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 7 more. Effective Jul 24, 1987
- [AD 86-07-13](https://openairdocs.org/ad/86-07-13): Fourth Stage Compressor Vane Assemblies · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 2 more. Effective Apr 11, 1986
- [AD 82-25-10](https://openairdocs.org/ad/82-25-10): First Stage Compressor Stator Vane Airfoils and/or Fourth Stage Turbine Blade Airfoils · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 4 more. Effective Dec 16, 1982
- [AD T83-03-51](https://openairdocs.org/ad/T83-03-51): Fourth Stage Turbine Rotors Assembly · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 7 more
- [AD 97-05-11 R1](https://openairdocs.org/ad/97-05-11-R1) (historical): ALF502L, ALF502L-2, ALF502L-2A and 9 more. Effective Aug 18, 1997
- [AD 97-11-05](https://openairdocs.org/ad/97-11-05) (historical): Fuel Manifold Assemblies · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 9 more. Effective Jul 28, 1997
- [AD 95-04-11](https://openairdocs.org/ad/95-04-11) (historical): Third Stage Turbine Disks · Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 7 more. Effective Apr 3, 1995
- [AD 80-22-53](https://openairdocs.org/ad/80-22-53) (historical): Honeywell International ALF502L, ALF502L-2, ALF502L-2A and 1 more. Effective Dec 31, 1980

## Registered aircraft by registry model (OpenAirDocs)

- [Lycoming ALF-502 SER.](https://openairdocs.org/engine/lycoming-alf-502-ser-series): 25 aircraft (registry code 41580)
- [Alliedsign LF507-1F](https://openairdocs.org/engine/alliedsign-lf507-1f): 13 aircraft (registry code 02503)
- [Honeywell ALF-502 series](https://openairdocs.org/engine/honeywell-alf-502-series): 4 aircraft (registry code 33900)
- [Lycoming ALF502L](https://openairdocs.org/engine/lycoming-alf502l): 4 aircraft (registry code 41589)
- [Lycoming ALF502R-5](https://openairdocs.org/engine/lycoming-alf502r-5): 4 aircraft (registry code 41624)
- [Honeywell ALF502R-5](https://openairdocs.org/engine/honeywell-alf502r-5): 2 aircraft (registry code 33875)
- [Lycoming ALF502L-2C](https://openairdocs.org/engine/lycoming-alf502l-2c): 2 aircraft (registry code 41619)
- [Alliedsign ALF502L-2C](https://openairdocs.org/engine/alliedsign-alf502l-2c): 1 aircraft (registry code 02644)
- [Lycoming ALF502L-2](https://openairdocs.org/engine/lycoming-alf502l-2): 1 aircraft (registry code 41617)
- [Alliedsign ALF502L](https://openairdocs.org/engine/alliedsign-alf502l): 0 aircraft (registry code 02641)
- [Alliedsign ALF502L-2](https://openairdocs.org/engine/alliedsign-alf502l-2): 0 aircraft (registry code 02642)
- [Alliedsign ALF502L-2A](https://openairdocs.org/engine/alliedsign-alf502l-2a): 0 aircraft (registry code 02643)
- [Alliedsign ALF502L-3](https://openairdocs.org/engine/alliedsign-alf502l-3): 0 aircraft (registry code 02645)
- [Alliedsign ALF502R-3](https://openairdocs.org/engine/alliedsign-alf502r-3): 0 aircraft (registry code 02646)
- [Alliedsign ALF502R-3A](https://openairdocs.org/engine/alliedsign-alf502r-3a): 0 aircraft (registry code 02647)
- [Alliedsign ALF502R-4](https://openairdocs.org/engine/alliedsign-alf502r-4): 0 aircraft (registry code 02648)
- [Alliedsign ALF502R-5](https://openairdocs.org/engine/alliedsign-alf502r-5): 0 aircraft (registry code 02649)
- [Alliedsign ALF502R-6](https://openairdocs.org/engine/alliedsign-alf502r-6): 0 aircraft (registry code 02650)
- [Honeywell ALF502L](https://openairdocs.org/engine/honeywell-alf502l): 0 aircraft (registry code 33867)
- [Honeywell ALF502L-2](https://openairdocs.org/engine/honeywell-alf502l-2): 0 aircraft (registry code 33868)
- [Honeywell ALF502L-2A](https://openairdocs.org/engine/honeywell-alf502l-2a): 0 aircraft (registry code 33869)
- [Honeywell ALF502L-2C](https://openairdocs.org/engine/honeywell-alf502l-2c): 0 aircraft (registry code 33870)
- [Honeywell ALF502L-3](https://openairdocs.org/engine/honeywell-alf502l-3): 0 aircraft (registry code 33871)
- [Honeywell ALF502R-3](https://openairdocs.org/engine/honeywell-alf502r-3): 0 aircraft (registry code 33872)
- [Honeywell ALF502R-3A](https://openairdocs.org/engine/honeywell-alf502r-3a): 0 aircraft (registry code 33873)
- [Honeywell ALF502R-4](https://openairdocs.org/engine/honeywell-alf502r-4): 0 aircraft (registry code 33874)
- [Honeywell ALF502R-6](https://openairdocs.org/engine/honeywell-alf502r-6): 0 aircraft (registry code 33876)
- [Lycoming ALF502L-2A](https://openairdocs.org/engine/lycoming-alf502l-2a): 0 aircraft (registry code 41618)
- [Lycoming ALF502L-3](https://openairdocs.org/engine/lycoming-alf502l-3): 0 aircraft (registry code 41620)
- [Lycoming ALF502R-3](https://openairdocs.org/engine/lycoming-alf502r-3): 0 aircraft (registry code 41621)
- [Lycoming ALF502R-3A](https://openairdocs.org/engine/lycoming-alf502r-3a): 0 aircraft (registry code 41622)
- [Lycoming ALF502R-4](https://openairdocs.org/engine/lycoming-alf502r-4): 0 aircraft (registry code 41623)
- [Lycoming ALF502R-6](https://openairdocs.org/engine/lycoming-alf502r-6): 0 aircraft (registry code 41625)

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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.