Wiring Diagram for Cessna 310F

Transducer Identification: Transducer Identification: Transducer Identification: Transducer Identification: Transducer Identification: FT-60 - Red Cube. FT-90 - Gold Cube. FT-180 - Black Cube. If your aircraft is not covered on our STC (found at the back of this manual), you must you must you must you must you must perform the flow and pressure tests in FAA document A.C. 23-16 (Powerplant Guide perform the flow and pressure tests in FAA document A.C. 23-16 (Powerplant Guide perform the flow and pressure tests in FAA document A.C. 23-16 (Powerplant Guide perform the flow and pressure tests in FAA document A.C. 23-16 (Powerplant Guide perform the flow and pressure tests in FAA document A.C. 23-16 (Powerplant Guide for Certification of Part 23 Airplanes) to insure safe and proper operation. for Certification of Part 23 Airplanes) to insure safe and proper operation. for Certification of Part 23 Airplanes) to insure safe and proper operation. for Certification of Part 23 Airplanes) to insure safe and proper operation. for Certification of Part 23 Airplanes) to insure safe and proper operation. Installation of the FP-5 on an aircraft with a fuel return line from the Pressure Carburetor requires a FFDM-1 Differential Module (see price sheet). The placard "Do Not Rely on Fuel Flow Instrument to Determine Fuel Levels in Tanks" must be mounted on the aircraft instrument panel near the FP-5/FP-5L. If the aircraft is equipped with a primary fuel flow and/or pressure instrument, the following placard must be mounted on the aircraft instrument panel near the FP-5/FP-5L: "Refer to Original Fuel Flow/Pressure Instrumentation for Primary Information." Contents Contents Contents Contents Contents Warranty ............................................................................................. Warranty ............................................................................................. Warranty ............................................................................................. Warranty ............................................................................................. Warranty ............................................................................................. 22222 1. Important Information and Initial Check Out .................................... 1. Important Information and Initial Check Out .................................... 1. Important Information and Initial Check Out .................................... 1. Important Information and Initial Check Out .................................... 1. Important Information and Initial Check Out .................................... 33333 2. Install the Fuel Flow Transducer ...................................................... 2. Install the Fuel Flow Transducer ...................................................... 2. Install the Fuel Flow Transducer ...................................................... 2. Install the Fuel Flow Transducer ...................................................... 2. Install the Fuel Flow Transducer ...................................................... 44444 3. Install the Circular Connector ......................................................... 3. Install the Circular Connector ......................................................... 3. Install the Circular Connector ......................................................... 3. Install the Circular Connector ......................................................... 3. Install the Circular Connector ......................................................... 55555 4. Route the Power and Ground Wires ................................................ 4. Route the Power and Ground Wires ................................................ 4. Route the Power and Ground Wires ................................................ 4. Route the Power and Ground Wires ................................................ 4. Route the Power and Ground Wires ................................................ 55555 5. Route the Backlight Wires ............................................................... 5. Route the Backlight Wires ............................................................... 5. Route the Backlight Wires ............................................................... 5. Route the Backlight Wires ............................................................... 5. Route the Backlight Wires ............................................................... 66666 6. Route the (Optional) External Warning Control Line ....................... 6. Route the (Optional) External Warning Control Line ....................... 6. Route the (Optional) External Warning Control Line ....................... 6. Route the (Optional) External Warning Control Line ....................... 6. Route the (Optional) External Warning Control Line ....................... 66666 7. Route the Fuel Flow Transducer Wires ........................................... 7. Route the Fuel Flow Transducer Wires ........................................... 7. Route the Fuel Flow Transducer Wires ........................................... 7. Route the Fuel Flow Transducer Wires ........................................... 7. Route the Fuel Flow Transducer Wires ........................................... 66666 8. Install A Functional Module ............................................................ ............................................................ ............................................................ ............................................................ ............................................................ 77777 9. (FP-5L Only) Connect the RS-232/422 Input Lines ............................. 9. (FP-5L Only) Connect the RS-232/422 Input Lines ............................. 9. (FP-5L Only) Connect the RS-232/422 Input Lines ............................. 9. (FP-5L Only) Connect the RS-232/422 Input Lines ............................. 9. (FP-5L Only) Connect the RS-232/422 Input Lines ............................. 77777 10. (FP-5L Only) Connect the RS-232 Output Line ................................ 10. (FP-5L Only) Connect the RS-232 Output Line ................................ 10. (FP-5L Only) Connect the RS-232 Output Line ................................ 10. (FP-5L Only) Connect the RS-232 Output Line ................................ 10. (FP-5L Only) Connect the RS-232 Output Line ................................ 77777 11. Install the Fuel Flow Differential Module (FFDM-1) ......................... 11. Install the Fuel Flow Differential Module (FFDM-1) ......................... 11. Install the Fuel Flow Differential Module (FFDM-1) ......................... 11. Install the Fuel Flow Differential Module (FFDM-1) ......................... 11. Install the Fuel Flow Differential Module (FFDM-1) ......................... 88888 12. Install the Instrument in the Panel ................................................... 12. Install the Instrument in the Panel ................................................... 12. Install the Instrument in the Panel ................................................... 12. Install the Instrument in the Panel ................................................... 12. Install the Instrument in the Panel ................................................... 88888 13. Connect the Circular Connector to the Instrument .......................... 13. Connect the Circular Connector to the Instrument .......................... 13. Connect the Circular Connector to the Instrument .......................... 13. Connect the Circular Connector to the Instrument .......................... 13. Connect the Circular Connector to the Instrument .......................... 99999 14. System Check-out ........................................................................... 14. System Check-out ........................................................................... 14. System Check-out ........................................................................... 14. System Check-out ........................................................................... 14. System Check-out ........................................................................... 99999 15. Initial Programming ........................................................................ 15. Initial Programming ........................................................................ 15. Initial Programming ........................................................................ 15. Initial Programming ........................................................................ 15. Initial Programming ........................................................................ 1 0 1 0 1 0 1 0 1 0 Wiring Diagrams .................................................................................. Wiring Diagrams .................................................................................. Wiring Diagrams .................................................................................. Wiring Diagrams .................................................................................. Wiring Diagrams .................................................................................. 11-12 11-12 11-12 11-12 11-12 Circular Connectors ............................................................................. Circular Connectors ............................................................................. Circular Connectors ............................................................................. Circular Connectors ............................................................................. Circular Connectors ............................................................................. 13-14 13-14 13-14 13-14 13-14 Specifications and Operating Features ................................................... Specifications and Operating Features ................................................... Specifications and Operating Features ................................................... Specifications and Operating Features ................................................... Specifications and Operating Features ................................................... 15-16 15-16 15-16 15-16 15-16 Fuel Flow Transducer Installation Drawings ......................................... Fuel Flow Transducer Installation Drawings ......................................... Fuel Flow Transducer Installation Drawings ......................................... Fuel Flow Transducer Installation Drawings ......................................... Fuel Flow Transducer Installation Drawings ......................................... 17-20 17-20 17-20 17-20 17-20 STC Information ................................................................................. Appendix STC Information ................................................................................. Appendix STC Information ................................................................................. Appendix STC Information ................................................................................. Appendix STC Information ................................................................................. Appendix 1 2 W W W W War ar ar ar arranty / ranty / ranty / ranty / ranty / Agr Agr Agr Agr Agreement eement eement eement eement Electronics International Inc. (E.I. inc.) warrants this instrument and system components to be free from defects in materials and workmanship for a period of one year from the user invoice date. Fuel Flow and Pressure Transducers are NOT covered under this warranty Fuel Flow and Pressure Transducers are NOT covered under this warranty Fuel Flow and Pressure Transducers are NOT covered under this warranty Fuel Flow and Pressure Transducers are NOT covered under this warranty Fuel Flow and Pressure Transducers are NOT covered under this warranty. They are covered by the original equipment manufacturer. Electronics International Inc. will repair or replace any item, at its sole discretion, covered under the terms of this Warranty provided the item is returned to the factory prepaid. 1. This Warranty shall not apply to any product that has been repaired or altered by any person other than Electronics International Inc., or that has been subjected to misuse, accident, incorrect wiring, negligence, improper or unprofes- sional assembly or improper installation by any person. This warranty does not cover any reimbursement for This warranty does not cover any reimbursement for This warranty does not cover any reimbursement for This warranty does not cover any reimbursement for This warranty does not cover any reimbursement for any person’s time for installation, removal, assembly or repair. any person’s time for installation, removal, assembly or repair. any person’s time for installation, removal, assembly or repair. any person’s time for installation, removal, assembly or repair. any person’s time for installation, removal, assembly or repair. Electronics International retains the right to determine the reason or cause for warranty repair. 2. This Warranty does not extend to any machine, vehicle, boat, aircraft or any other device to which the Electronics International Inc. product may be connected, attached, interconnected or used in conjunction with in any way. 3. The obligation assumed by Electronics International Inc. under this Warranty is limited to repair, replacement or refund of the product, at the sole discretion of Electronics International Inc. 4. Electronics International Inc. is not liable for expenses incurred by the customer or installer due to factory updates, modifications, improvements, upgrades, changes, or any other alterations to the product that may affect the form, fit, function or operation of the product. 5. Personal injury or property damage due to misinterpretation or lack of understanding of this product is solely the pilot's responsibility. The pilot must must must must must understand the operation of this product before flying the aircraft. Do not allow anyone to operate the aircraft that does not know the operation of this product. Keep the Operating Manual in the aircraft at all times. 6. E. I. Inc. is not responsible for shipping charges or damages incurred under this Warranty. 7. No representative is authorized to assume any other liability for Electronics International Inc. in connection with the sale of Electronics International Inc. products. 8. If you do not agree to and accept the terms of this Warranty, you may return the product for a If you do not agree to and accept the terms of this Warranty, you may return the product for a If you do not agree to and accept the terms of this Warranty, you may return the product for a If you do not agree to and accept the terms of this Warranty, you may return the product for a If you do not agree to and accept the terms of this Warranty, you may return the product for a r e f u n d . r e f u n d . r e f u n d . r e f u n d . r e f u n d . This Warranty is made only to the original user. THIS WARRANTY IS IN LIEU OF ALL OTHER WARRAN- THIS WARRANTY IS IN LIEU OF ALL OTHER WARRAN- THIS WARRANTY IS IN LIEU OF ALL OTHER WARRAN- THIS WARRANTY IS IN LIEU OF ALL OTHER WARRAN- THIS WARRANTY IS IN LIEU OF ALL OTHER WARRAN- TIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY DISCLAIMS TIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY DISCLAIMS TIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY DISCLAIMS TIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY DISCLAIMS TIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY DISCLAIMS ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PUR- ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PUR- ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PUR- ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PUR- ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PUR- POSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFACTURER BE LIABLE FOR POSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFACTURER BE LIABLE FOR POSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFACTURER BE LIABLE FOR POSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFACTURER BE LIABLE FOR POSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFACTURER BE LIABLE FOR SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, INCLUDING LOST PROFITS OR LOSS SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, INCLUDING LOST PROFITS OR LOSS SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, INCLUDING LOST PROFITS OR LOSS SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, INCLUDING LOST PROFITS OR LOSS SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, INCLUDING LOST PROFITS OR LOSS OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS EXPRESSLY PROVIDED HEREIN, MANUFAC- OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS EXPRESSLY PROVIDED HEREIN, MANUFAC- OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS EXPRESSLY PROVIDED HEREIN, MANUFAC- OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS EXPRESSLY PROVIDED HEREIN, MANUFAC- OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS EXPRESSLY PROVIDED HEREIN, MANUFAC- TURER DISCLAIMS ALL OTHER LIABILITY TO PURCHASER OR ANY OTHER PERSON IN CON- TURER DISCLAIMS ALL OTHER LIABILITY TO PURCHASER OR ANY OTHER PERSON IN CON- TURER DISCLAIMS ALL OTHER LIABILITY TO PURCHASER OR ANY OTHER PERSON IN CON- TURER DISCLAIMS ALL OTHER LIABILITY TO PURCHASER OR ANY OTHER PERSON IN CON- TURER DISCLAIMS ALL OTHER LIABILITY TO PURCHASER OR ANY OTHER PERSON IN CON- NECTION WITH THE USE OR PERFORMANCE OF MANUFACTURER’S PRODUCTS, INCLUDING NECTION WITH THE USE OR PERFORMANCE OF MANUFACTURER’S PRODUCTS, INCLUDING NECTION WITH THE USE OR PERFORMANCE OF MANUFACTURER’S PRODUCTS, INCLUDING NECTION WITH THE USE OR PERFORMANCE OF MANUFACTURER’S PRODUCTS, INCLUDING NECTION WITH THE USE OR PERFORMANCE OF MANUFACTURER’S PRODUCTS, INCLUDING SPECIFICALLY LIABILITY IN TORT. SPECIFICALLY LIABILITY IN TORT. SPECIFICALLY LIABILITY IN TORT. SPECIFICALLY LIABILITY IN TORT. SPECIFICALLY LIABILITY IN TORT. FP-5 and FP-5L FP-5 and FP-5L FP-5 and FP-5L FP-5 and FP-5L FP-5 and FP-5L Installation Instr Installation Instr Installation Instr Installation Instr Installation Instructions uctions uctions uctions uctions 1. 1. 1. 1. 1. Important Information and Initial Check Out Important Information and Initial Check Out Important Information and Initial Check Out Important Information and Initial Check Out Important Information and Initial Check Out A. The installer and aircraft owner must read the Warranty before starting the installation. There is information in the Warranty that may alter your decision to install this instrument. If you do not accept the terms of the Warranty, do not install this instrument. B. If you are not an FAA Certified Aircraft Mechanic familiar with the issues of installing aircraft fuel flow and pressure instruments, Do Not attempt to install this instrument. The installer should use current aircraft standards and practices to install this instrument (refer to AC 43.13). C. Check that any necessary FAA Approvals (STCs, etc.) are available for your aircraft before starting the installation. The FAA Approved Model List (AML) is located at the back of this manual. Resolve any issues you may have before starting the installation. D. Before starting installation, read the entire Installation Instructions and resolve any installation, operating and performance issues you may have before starting the installation. E. THIS INSTALLATION WILL REQUIRE SOME PARTS UNIQUE TO YOUR AIRCRAFT THAT ARE NOT SUP- PLIED IN THE KIT (including, but not limited to hoses and fittings). Acquire all the parts necessary to install this instrument before starting the installation. F. Check that the instrument and flow transducer make and model are correct before starting the installation (check your invoice and the markings on the side of the instrument). The FT-60 flow transducer is intended to be used on aircraft equipped with fuel pumps with engines rated below 350 H.P. A gravity feed fuel system or any engine rated over 350 H.P. must use an FT-90 flow transduer; an engine rated over 550 HP must use the FT-180 flow transducer. A pressure carbureted engine with a fuel return line requires an FFDM-l (see price sheet). Transducer Identification: FT-60 - Red Cube FT-90 - Gold Cube FT-180 - Black Cube. G. Before starting the installation make sure the unit will fit in the location you intend to install it without obstruct- ing the operation of any controls. H. If this instrument is to replace an existing unit in the aircraft, it is the installer's responsibility to move or replace any existing instruments or components in accordance with FAA approved methods and procedures. The follow- ing Installation Instructions do not cover moving or the removal of any existing instruments or components. 33333 4 2. 2. 2. 2. 2. Install the Fuel Flo Install the Fuel Flo Install the Fuel Flo Install the Fuel Flo Install the Fuel Flow w w w w T T T T Transducer ransducer ransducer ransducer ransducer Mount the Fuel Flow Transducer using the appropriate drawing at the back of this manual. The instructions listed below must be followed when installing a Fuel Flow Transducer. The instructions listed below must be followed when installing a Fuel Flow Transducer. The instructions listed below must be followed when installing a Fuel Flow Transducer. The instructions listed below must be followed when installing a Fuel Flow Transducer. The instructions listed below must be followed when installing a Fuel Flow Transducer. Note: Note: Note: Note: Note: If your engine is equipped with a Pressure Carburetor with a fuel return line from the carburetor back to the fuel tank, you will need to install two flow transducers: one in the feed line from the fuel pump to the carburetor and one in the return line from the carburetor back to the fuel tank. Also, a Fuel Flow Differential Module (FFDM-1) will need to be installed. See drawings 1229932 and 1015941 at the back of this manual. A. The transducer output port should be mounted lower, even or no more than 4" per foot higher than the carburetor inlet port (or fuel servo on a fuel injected engine). If this is not possible, a loop should be put in the fuel line between the Fuel Flow Transducer and the carburetor or fuel servo (see diagram below). Fuel Flow Transducer 1/4" NPT • Mount the transducer with the wires pointing up or the cap with five bolts up or the output up or any combina- tion thereof. Note: • The direction of the flow of fuel through the transducer is marked on the transducer. End View End View End View End View End View Side View Side View Side View Side View Side View If the transducer is more than 4" per foot higher than the carburetor or fuel servo port, put a loop in the fuel line between the transducer and the carburetor or fuel servo. This will allow bubbles to vacate the Flow Transducer. B. Do not remove the yellow caps on the flow transducer until the fuel hoses are ready to be installed. C. The flow of fuel through the transducer must follow the direction marked on the transducer. Fuel Flow Transducer Carburetor or Fuel Servo  —      g  —  ™ e 5    —  h  — €      —        ™   p FA    ™  v   @          P Q W W P P I I Q W W P P I U I  V I        —       ™   p FA—   g   @       I R W S I R H H P      — %   %   —        ˜— g F    P Q W W P P I I Q W W P P I U I  V I   —   — %   %   —        ˜— g FA  w I E w h p p  —   * @     P Q W W P P I   — DI Q W W P P I I R W S I H I W I   — DU I  V I       — —        ˜— g FA ™     — „  p H W E „ p  —   * @      P Q W W P P I I Q W W P P I U I  V I OUT 5 D. The flow transducer must be mounted so the wires exiting the transducer are pointing up or the cap with five bolts are pointing up or the output port is pointing up or any combination thereof.. E. Before connecting any hoses, thoroughly clean them and insure they are free of any loose material. High air pressure may be used, however, however, however, however, however, do not allow high air pressure to pass through the flow trans- do not allow high air pressure to pass through the flow trans- do not allow high air pressure to pass through the flow trans- do not allow high air pressure to pass through the flow trans- do not allow high air pressure to pass through the flow trans- d u c e r . d u c e r . d u c e r . d u c e r . d u c e r . F. When mounting a Fuel Flow Transducer make provisions for the Fuel Pressure Transducer as necessary. You may want to consider using some Fittings and Hoses shown below. Note: DO NOT EXCEED a torque of 15 ft. DO NOT EXCEED a torque of 15 ft. DO NOT EXCEED a torque of 15 ft. DO NOT EXCEED a torque of 15 ft. DO NOT EXCEED a torque of 15 ft. lbs. or screw the fittings tighter than two full turns past hand tight, whichever happens first. lbs. or screw the fittings tighter than two full turns past hand tight, whichever happens first. lbs. or screw the fittings tighter than two full turns past hand tight, whichever happens first. lbs. or screw the fittings tighter than two full turns past hand tight, whichever happens first. lbs. or screw the fittings tighter than two full turns past hand tight, whichever happens first. F i t t i n g s : F i t t i n g s : F i t t i n g s : F i t t i n g s : F i t t i n g s : #4 Straight - AN816-4- B or C #6 Straight - AN816-6 B or C #8 Straight - AN816-7 B or C #6 45° - MS20823-6 B or C 1/4" NPT 1/4" NPT 1/4" NPT 1/4" NPT 1/4" NPT F l a r e F l a r e F l a r e F l a r e F l a r e Hose Fittings: Hose Fittings: Hose Fittings: Hose Fittings: Hose Fittings: Straight - MS24587-XX, Stratoflex 300-, Aeroquip 400- 45° - MS27226-XX, Stratoflex 646- and 640, Aeroquip 980006 NOTE: NOTE: NOTE: NOTE: NOTE: The Stratoflex teflon hose can be much more flexible and easier to route than most existing hoses. If you have a hard to fit installation, consider this hose. F l a r e F l a r e F l a r e F l a r e F l a r e H o s e H o s e H o s e H o s e H o s e 3. 3. 3. 3. 3. Install the Circular Connector Install the Circular Connector Install the Circular Connector Install the Circular Connector Install the Circular Connector Starting from under the instrument panel, route the circular connector wire harness up to the instrument mounting location. (See the Wiring Diagram at the back of this manual). Place the circular connector about 8 inches back from the panel. Tie wrap the harness in place approximately 1 foot back from the circular connector. This will allow the harness to be flexible and accommodate varying lengths in instrument wires. Be sure these wires do not obstruct Be sure these wires do not obstruct Be sure these wires do not obstruct Be sure these wires do not obstruct Be sure these wires do not obstruct the freedom of travel of any controls. the freedom of travel of any controls. the freedom of travel of any controls. the freedom of travel of any controls. the freedom of travel of any controls. 4. 4. 4. 4. 4. Route the P Route the P Route the P Route the P Route the Po o o o ow w w w wer and Gr er and Gr er and Gr er and Gr er and Ground ound ound ound ound Wir Wir Wir Wir Wires es es es es In the wire harness are two sets of red and black 6' wire bundles used for the fuel pressure transducer and the fuel flow transducer. Also, there are red and black 3' wires used for instrument power and ground. Route the 3' red wire in the harness to the aircraft’s 12 or 24 volt main or emergency bus as applicable via an independent circuit breaker (five amps or less). An alternate method would be to route the red lead to the bus via a one amp in-line fuse. With this With this With this With this With this method a spare fuse must be kept in the aircraft. method a spare fuse must be kept in the aircraft. method a spare fuse must be kept in the aircraft. method a spare fuse must be kept in the aircraft. method a spare fuse must be kept in the aircraft. Route the 3' black wire in the harness to a good ground . Tie Tie Tie Tie Tie wrap these wires so they do not obstruct the freedom of travel of any controls. wrap these wires so they do not obstruct the freedom of travel of any controls. wrap these wires so they do not obstruct the freedom of travel of any controls. wrap these wires so they do not obstruct the freedom of travel of any controls. wrap these wires so they do not obstruct the freedom of travel of any controls. 6 5. 5. 5. 5. 5. Route the Backlight Route the Backlight Route the Backlight Route the Backlight Route the Backlight Wir Wir Wir Wir Wires es es es es Connect the backlight wires as follows: A. A. A. A. A. It is recommended to permanently power up the digital display backlight, although, you can connect the appropriate wires to a panel light rheostat. 1) For a 12-volt system connect the white/brown wire to the bus (or rheostat) and connect the white/red wire to ground (see Wiring Diagram). 2) For a 24-volt system leave the white/brown wire open and connect the white/red wire to the bus (or rheostat) (see Wiring Diagram). B. B. B. B. B. Connect the white/orange wire to the panel light rheostat. This wire will dim the Display Mode Indicator LEDs for night operation when the panel lights are turned on. If this line is left open, the Display Mode Indicator LEDs will remain at full intensity at all times. Also, if the voltage on this line drops below 11.5 volts, the analog LEDs will be displayed at full intensity. Tie wrap all wires so they do not obstruct the Tie wrap all wires so they do not obstruct the Tie wrap all wires so they do not obstruct the Tie wrap all wires so they do not obstruct the Tie wrap all wires so they do not obstruct the freedom of travel of any controls. freedom of travel of any controls. freedom of travel of any controls. freedom of travel of any controls. freedom of travel of any controls. Note: This line may be connected to the CP-1 Intensity Control Pot (see price sheet). 6. 6. 6. 6. 6. Route the (Optional) External Route the (Optional) External Route the (Optional) External Route the (Optional) External Route the (Optional) External W W W W Warning Contr arning Contr arning Contr arning Contr arning Control Line ol Line ol Line ol Line ol Line The white/yellow wire can be connected to E.I.'s external light (model AL-1), buzzer (model ATG-1), voice annun- ciator (model AV-17), a relay, etc. This wire grounds when the red warning light is on. The current in this line must be limited to 2/10 of an amp maximum. Exceeding this limit will damage the instrument. If this feature is not used, leave this line open. Tie wrap this wire so it does not obstruct the freedom of travel of any controls. Tie wrap this wire so it does not obstruct the freedom of travel of any controls. Tie wrap this wire so it does not obstruct the freedom of travel of any controls. Tie wrap this wire so it does not obstruct the freedom of travel of any controls. Tie wrap this wire so it does not obstruct the freedom of travel of any controls. 7. 7. 7. 7. 7. Route the Fuel Flo Route the Fuel Flo Route the Fuel Flo Route the Fuel Flo Route the Fuel Flow w w w w T T T T Transducer ransducer ransducer ransducer ransducer Wir Wir Wir Wir Wires es es es es The wire harness includes 6' cable with red, black and white wires. Route and connect these 6' wires to the fuel flow transducer using the OLC-1 Overlap Connectors supplied with the transducer. See OLC-1 Instructions for details. If your engine is equipped with a fuel return line from the carburetor back to the fuel tank, route these wires to the Fuel Flow Differential Module (FFDM-1). See the appropriate drawing at the back of this manual. Any excess wires can be rolled up and tie wrapped under the instrument panel. Tie wrap these wires so they Tie wrap these wires so they Tie wrap these wires so they Tie wrap these wires so they Tie wrap these wires so they do not obstruct the freedom of travel of any controls. do not obstruct the freedom of travel of any controls. do not obstruct the freedom of travel of any controls. do not obstruct the freedom of travel of any controls. do not obstruct the freedom of travel of any controls. You may decide to cut these wires to a specific length prior to connecting to the fuel flow transducer with the OLC-1 connectors. 8. 8. 8. 8. 8. Install Install Install Install Install A Functional Module A Functional Module A Functional Module A Functional Module A Functional Module If the Aux channel on the FP-5 is to be used to monitor a function (EGT, TIT, Fuel Pressure, Oil Pressure, etc.) an appropriate Functional Module must be installed. A Functional Module is a small box with circuitry used to convert Temperature, Pressure, Voltage, Amps, etc. to an appropriate signal the FP-5 can display on the Aux channel. These modules are small and light and are tie wrapped under the instrument panel. They come with a Circular Connector so they may be installed and removed easily. Install any Functional Modules at this time. Installation Instructions for the various Functional Modules come with the modules and are supplements to this installation manual. 9. 9. 9. 9. 9. (FP-5L Only) Connect the RS-232/422 Input Lines (FP-5L Only) Connect the RS-232/422 Input Lines (FP-5L Only) Connect the RS-232/422 Input Lines (FP-5L Only) Connect the RS-232/422 Input Lines (FP-5L Only) Connect the RS-232/422 Input Lines Connecting the FP-5L Input Lines to a compatible GPS unit allows the FP-5L to display Fuel to Destination, Fuel Reserve, Nautical Miles per Gallon and Statute Miles per Gallon information. The FP-5L has three GPS Receive Formats: 1. "In1" for all panel mount GPS units (9600 baud); 2. "In2" for Northstar (1200 baud); 3. "In3" for hand held GPS units (NMEA at 4800 baud). The protocol is 1 start bit, 8 data bits and 1 stop bit and the RS-232 update time of the GPS unit should be 1 to 2 seconds. The GPS unit may require some setup. You may want to contact a knowledgeable instrument shop or the GPS factory to help with the hookup and setup of the GPS unit. See the "Power-Up Program- mable Settings" section in the FP-5(L) Operating Instructions to configure the FP-5L RS-232 input. 7      „   E   r v S E € p    ™     g ƒ € q    ™     g P Q P E ƒ ‚  s P Q P E ƒ ‚ A    ˜G   @   y P Q P E ƒ ‚   P P R E ƒ ‚ T V R E ƒ ‚  s P Q P E ƒ ‚ A    ˜G   @   y E   y C A  y E  —   y C    ˜       H P I — ™  ™@ F  $  ˜     %  „ F v S E € p         ƒ € q % — ™  ™    h X   x 10. 10. 10. 10. 10. (FP-5L Only) Connect the RS-232 Output Line (FP-5L Only) Connect the RS-232 Output Line (FP-5L Only) Connect the RS-232 Output Line (FP-5L Only) Connect the RS-232 Output Line (FP-5L Only) Connect the RS-232 Output Line Connecting the FP-5L Output Line to a compatible GPS unit allows the GPS unit to use the fuel data transmited by the FP-5L. The FP-5L has three GPS Transmit Formats: 1. "Ot1" outputs older Shadin fuel flow data (for Arnav, King and newer Garmin GPS units); 2. "Ot2" outputs the Shadin fuel flow sentence (for Garmin and other GPS units); 3. "Ot3" outputs a modified Shadin Fuel/Airdata sentence (for UPS GPS units). The GPS unit may require some setup. You may want to contact a knowledgeable instrument shop or the GPS factory to help with the hookup and setup of the GPS unit. See the "Power-Up Programmable Settings" section in the FP-5(L) Operating Instructions to configure the FP-5L RS-232 output. Connect the FP-5L RS-232 Output Line (White/Green Wire) to the GPS RS-232 Input Line. Do not connect any GPS shield wires to the FP-5L. They should be left open. 8 11. 11. 11. 11. 11. Install the Fuel Flow Differential Module (FFDM-1) Install the Fuel Flow Differential Module (FFDM-1) Install the Fuel Flow Differential Module (FFDM-1) Install the Fuel Flow Differential Module (FFDM-1) Install the Fuel Flow Differential Module (FFDM-1) If your engine is equipped with a fuel return line from the carburetor back to the fuel tank, install the FFDM-1 in the aircraft as oulined below (see diagram at the back of this manual). Otherwise, omit this step. A. Connect the circular connector to the FFDM-1. B. Install the FFDM-1 under the instrument panel using two tie wraps on each end of the module to support it to a wire bundle or bracket. C. Route and connect the 3' red power lead to the 12 or 24 volt bus via a 1 amp fuse. D. Route and connect the 3' black ground lead to the same ground used for the FP-5. E. Route and connect the 6' red, black and white leads marked "Feed" to the flow transducer installed in the fuel line from the fuel pump to the carburetor using OLC-1 Overlap Connectors supplied with the transducer. See OLC-1 Installation Instructions for details. F. Route and connect the 6' red, black and white leads marked "Return" to the flow transducer installed in the return fuel line from the carburetor to the fuel tank using OLC-1 Overlap Connectors supplied with the transducer. See OLC-1 Installation Instructions for details. G. Connect the 1' red, black and white leads to the same color 6' leads from the FP-5. H. Any excess wires can be rolled up and tie wrapped under the instrument panel. Tie wrap these wires so Tie wrap these wires so Tie wrap these wires so Tie wrap these wires so Tie wrap these wires so they do not obstruct the freedom of travel of any controls. they do not obstruct the freedom of travel of any controls. they do not obstruct the freedom of travel of any controls. they do not obstruct the freedom of travel of any controls. they do not obstruct the freedom of travel of any controls. You may decide to cut the transducer wires to a specific length prior to connecting to the fuel flow transducer with the OLC-1 connectors. Note: Note: Note: Note: Note: The flow transducers for the FFDM-1 and the FP-5 MUST MUST MUST MUST MUST be of the same model (i.e., if the FP-5 uses an FT-60 flow transducer, then the FFDM-1 must use a FT-60 flow transducer). 12. 12. 12. 12. 12. Install the Instrument in the Panel Install the Instrument in the Panel Install the Instrument in the Panel Install the Instrument in the Panel Install the Instrument in the Panel Install the instrument from behind the instrument panel using 6 x 32 screws. These screws must not be any longer than 1/2". Tie wrap any loose wires as needed. Make sure the instrument and wire do not obstruct the operation of any controls. Mount the placard "Do Not Rely on Fuel Flow Instrument to Determine Fuel Levels in Tanks" Mount the placard "Do Not Rely on Fuel Flow Instrument to Determine Fuel Levels in Tanks" Mount the placard "Do Not Rely on Fuel Flow Instrument to Determine Fuel Levels in Tanks" Mount the placard "Do Not Rely on Fuel Flow Instrument to Determine Fuel Levels in Tanks" Mount the placard "Do Not Rely on Fuel Flow Instrument to Determine Fuel Levels in Tanks" on the aircraft instrument panel near the FP-5. on the aircraft instrument panel near the FP-5. on the aircraft instrument panel near the FP-5. on the aircraft instrument panel near the FP-5. on the aircraft instrument panel near the FP-5. If the aircraft is equipped with a primary fuel flow and/or pressure instrument, the following If the aircraft is equipped with a primary fuel flow and/or pressure instrument, the following If the aircraft is equipped with a primary fuel flow and/or pressure instrument, the following If the aircraft is equipped with a primary fuel flow and/or pressure instrument, the following If the aircraft is equipped with a primary fuel flow and/or pressure instrument, the following placard must be mounted on the aircraft instrument panel near the FP-5: "Refer to Original Fuel placard must be mounted on the aircraft instrument panel near the FP-5: "Refer to Original Fuel placard must be mounted on the aircraft instrument panel near the FP-5: "Refer to Original Fuel placard must be mounted on the aircraft instrument panel near the FP-5: "Refer to Original Fuel placard must be mounted on the aircraft instrument panel near the FP-5: "Refer to Original Fuel Flow/Pressure Instrumentation for Primary Information". Flow/Pressure Instrumentation for Primary Information". Flow/Pressure Instrumentation for Primary Information". Flow/Pressure Instrumentation for Primary Information". Flow/Pressure Instrumentation for Primary Information". 9 13. 13. 13. 13. 13. Connect the Circular Connector to the Instrument Connect the Circular Connector to the Instrument Connect the Circular Connector to the Instrument Connect the Circular Connector to the Instrument Connect the Circular Connector to the Instrument A. Push the two mating connectors together and twist them until they snap into position. B. Turn the locking ring on the instrument connector clockwise (1 1/2 turns) until it locks into position. 14. 14. 14. 14. 14. System Check-out System Check-out System Check-out System Check-out System Check-out Check instrument operation as follows: A. Turn the aircraft master switch on (engine off) and verify that the red warning LED's on the FP-5 flash and the green "REM" mode LED is blinking. A problem at this step could be caused by poor connections on the red or black power and ground leads. B. Set the instrument toggle switch to "FLOW" and check for a digital fuel flow reading of "000." A problem at this step could be caused by a poor connection or crossed flow transducer wires. The voltage on the flow trans- ducer wires (with the transducer removed from the instrument) should measure as follows: Red Wire - +9 to 14 Volts Black Wire - 0 Volts White Wire - 0 or 5 Volts (pulsed when fuel is flowing) C. Check the digital display backlight. With high or medium ambient light it is hard to see the digital display backlight (it is only required during low ambient light conditions but should be on at all times). D. If the Display Mode Indicator LED dimming wire has been connected, turn the panel light rheostat up and look for the Display Mode Indicator LEDs to dim. E. With the engine running, check the "FLOW" Display Mode to read properly. If there is a problem at this point see step B above for troubleshooting information. To see if the instrument is receiving pulses from the flow transducer, disconnect the white wire from the transducer and short it rapidly (white wire to the instrument) to ground. A reading should appear on the display. 10 FP-5L Display Comments Off The FP-5L is not receiving serial data. Check Connections and the setup of the Loran/GPS unit. ' on (note the bar) The FP-5L is receiving serial data but it does not have the proper protocol. Check connections the Loran/GPS Interface settings on the FP-5L. on The FP-5L is receiving RS-232 data but the Speed and/or Distance data is missing. Check the setup of the Loran/GPS unit. F. (FP-5L Only) Check the FP-5L display to read a number when the "F. to D." (Fuel to Destination) button is pushed. You may have to fly the aircraft before the GPS unit will output data. If the "F. to D." function is not working properly, use the following chart to help find your problem. G. After running the engine, check the fuel hoses, transducers and fittings for leaks. After running the engine, check the fuel hoses, transducers and fittings for leaks. After running the engine, check the fuel hoses, transducers and fittings for leaks. After running the engine, check the fuel hoses, transducers and fittings for leaks. After running the engine, check the fuel hoses, transducers and fittings for leaks. 15. 15. 15. 15. 15. Initial Programming Initial Programming Initial Programming Initial Programming Initial Programming The Power-Up Programmable Settings for the FP-5(L) must be set up for your aircraft. See the Power-Up Programmable Setting section in the Operating Instruction manual for set up information. Fuel Flo Fuel Flo Fuel Flo Fuel Flo Fuel Flow/Pr w/Pr w/Pr w/Pr w/Pressur essur essur essur essure (FP-5 and FP-5L) e (FP-5 and FP-5L) e (FP-5 and FP-5L) e (FP-5 and FP-5L) e (FP-5 and FP-5L) Wiring Diagram Wiring Diagram Wiring Diagram Wiring Diagram Wiring Diagram 11 6' Red Wire 6' Black Wire 6' White Wire R e d B l a c k White AUX Channel Input Lines. See the Installation Instructions for the approprIate Functional Module. White/Red Wire White/Yel Wire White Wire Circular Connector 3' Display Mode Indicator LED Dimming Line, connects to Panel Light Rheostat. 12/24 volts dims the Display Mode LEDs. 3' (Optional) External Warning Control Line. Can be connected to a relay to control an external light, buzzer, etc. Grounds when Red Warning Light is on. Current must be limited to 2/10 amp maximum. 3' Backlight Control Line, connects to 24 Volt Bus. Connect to ground for 12 Volt System. 3' Backlight Control Line, connects to 12 Volt Bus. 12 volts turns on the digital display backlight. 3' Ground Lead, connects to Ground. 3' Power Lead, connects to 12 or 24 Volt Bus. White/Yel B l a c k Red White/Brwn White/Red White/ Orng Do not use screws Do not use screws Do not use screws Do not use screws Do not use screws longer than 1/2" (4 ea.). longer than 1/2" (4 ea.). longer than 1/2" (4 ea.). longer than 1/2" (4 ea.). longer than 1/2" (4 ea.). 2ea - 3' (FP-5L Only) RS-232/422 Serial Lines. See the FP-5 and FP-5L Circular Connector data on page 14. Wire Harness Connect the same color of 6' wires from the unit to the Fuel Flow Transducer. Fuel Flow Transducer Note: For a Note: For a Note: For a Note: For a Note: For a c a r b u r e t o r c a r b u r e t o r c a r b u r e t o r c a r b u r e t o r c a r b u r e t o r with a fuel with a fuel with a fuel with a fuel with a fuel return line see return line see return line see return line see return line see next page. next page. next page. next page. next page. Wht/Grn Wht/Blu FP-5(L) / FFDM-1 Inter FP-5(L) / FFDM-1 Inter FP-5(L) / FFDM-1 Inter FP-5(L) / FFDM-1 Inter FP-5(L) / FFDM-1 Interconnect connect connect connect connect Wiring Diagram Wiring Diagram Wiring Diagram Wiring Diagram Wiring Diagram 12 Circular Connector 6' Red Wire 6' Black Wire 6' White Wire R e d B l a c k White Fuel Flow Differential Module (FFDM-1). Used with the FP-5(L) for carbureted engines with a fuel return line. Partial wiring diagram for the FP-5 or FP-5L. B l a c k R e d B l a c k White R e d B l a c k White 6' Red Wire 6' Black Wire 6' White Wire 6' Red Wire 6' Black Wire 6' White Wire Red Wire bundle marked Wire bundle marked Wire bundle marked Wire bundle marked Wire bundle marked "Return" "Return" "Return" "Return" "Return" Wire bundle marked Wire bundle marked Wire bundle marked Wire bundle marked Wire bundle marked "Feed" "Feed" "Feed" "Feed" "Feed" Circular Connector 3' Ground Lead, connects to same ground as FP-5(L). 3' Power Lead, connects to 12 or 24 Volt Bus Via 1 amp fuse. Fuel Flow Transducer mounted in the fuel line from the Fuel Pump to the Carburetor. Fuel Flow Transducer mounted in the fuel return line from the Carburetor to the fuel tank. W A R N I N G ! W A R N I N G ! W A R N I N G ! W A R N I N G ! W A R N I N G ! Electronics International Inc. Electronics International Inc. Electronics International Inc. Electronics International Inc. Electronics International Inc. only authorizes the installation of only authorizes the installation of only authorizes the installation of only authorizes the installation of only authorizes the installation of the FFDM-1 with the FP-5 or FP- the FFDM-1 with the FP-5 or FP- the FFDM-1 with the FP-5 or FP- the FFDM-1 with the FP-5 or FP- the FFDM-1 with the FP-5 or FP- 5L. Installing the FFDM-1 with 5L. Installing the FFDM-1 with 5L. Installing the FFDM-1 with 5L. Installing the FFDM-1 with 5L. Installing the FFDM-1 with any other manufacturer's instru- any other manufacturer's instru- any other manufacturer's instru- any other manufacturer's instru- any other manufacturer's instru- ment may seriously jeopardize ment may seriously jeopardize ment may seriously jeopardize ment may seriously jeopardize ment may seriously jeopardize the safety of the aircraft. the safety of the aircraft. the safety of the aircraft. the safety of the aircraft. the safety of the aircraft. 13 FP-5 and FP-5L FP-5 and FP-5L FP-5 and FP-5L FP-5 and FP-5L FP-5 and FP-5L Circular Connector Circular Connector Circular Connector Circular Connector Circular Connector 1 and 2 connect to power and ground. 6 3 7 10 11 14 15 16 2 1 Blk Red W/ Yel W/ Brn W/ Red W/ Org W/ Red WhtW/ Yel Wht Blk Red 7 through 9 connects to the Fuel Flow Trans- ducer. 3 through 6 are for back- light, LED dimming and external warning. Note: See Wiring Diagram for hookup information. Connecting Cable Harness, Back View (wire side) Connecting Cable Harness, Back View (wire side) Connecting Cable Harness, Back View (wire side) Connecting Cable Harness, Back View (wire side) Connecting Cable Harness, Back View (wire side) or Instrument Connector, Front View Instrument Connector, Front View Instrument Connector, Front View Instrument Connector, Front View Instrument Connector, Front View 12 through 14 connects to a Functional Module W/ Grn W/ Blu RS-232 Output (FP-5L Only) RS-232/422 Input (FP-5L Only) 3 1 4 7 9 6 Connecting Cable Harness, Back View (wire side) Connecting Cable Harness, Back View (wire side) Connecting Cable Harness, Back View (wire side) Connecting Cable Harness, Back View (wire side) Connecting Cable Harness, Back View (wire side) Module Connector, Front View Module Connector, Front View Module Connector, Front View Module Connector, Front View Module Connector, Front View o r Blk Red W/ Blk W/ Red 14 FFDM-1 Circular Connector FFDM-1 Circular Connector FFDM-1 Circular Connector FFDM-1 Circular Connector FFDM-1 Circular Connector Note: See Wiring Diagram for hook up information. Power and Ground Wires To Feed Transducer To Return Transducer Wht W/ Blk W/ Red Wht 15 Specif Specif Specif Specif Specifications and Operating F ications and Operating F ications and Operating F ications and Operating F ications and Operating Features eatures eatures eatures eatures Model: FP-5 and FP-5L (Fuel Flow/Pressure Instrument) Case Dimensions: 2.5" x 2.5" x 3.65" depth, 2 1/4" Bezel. Weight: Instrument Only: 11 Oz. Flow Transducer FT-60, FT-90 or FT-180: 6 Oz. Environmental: Meets TSO C44a/C47 Power Requirements: 7.5 to 35 Volts, 1/10 Amp. Green Display Mode Indicator LEDs: The intensity of these LEDs is controlled by the dimming wire. 12 or 24 volts on this wire will dim the LEDs for night operation. Red Low Fuel Warning LED: This LED will blink any time the programmed First or Second Low Fuel limit, Time to Empty Limit or Reoccur- ring Alarm is violated. The Low Fuel Warning LED is always displayed at full intensity and will flash on power- up. Red H/L AUX Warning LED: This LED will blink any time the programmed High or Low AUX limit is violated. The H/L AUX Warning LED is always displayed at full intensity and will flash on power-up. Digital Display: LCD (viewable in direct sunlight), with 12 and 24 volt backlight control wires for night operation. Displays "8888" on power up. External Warning Control Line: Grounds when any Red Warning LED is on or blinking. Current should be limited to 2/10 amp. Accuracy: Flow: 2% or better in accordance with TSO C44a. Aux Channel: 2% in accordance with TSO. Resolution: Fuel Flow: 0.1 Gal. or 1 Lb. or 1 Ltr. Fuel Remaining: 0.1 Gal. up to 99.9 Gal or 1 Lb. or 1 Ltr. Fuel Used: 0.1 Gal. up to 99.9 Gal or 1 Lb. or 1 Ltr. Time to Empty: 1 minute Aux: 1 or 0.1 (programmable). Max Displayed Range (Unit Only): Fuel Flow: 199.9 Gals/Hr or 162.0 br Gal/Hr or 1199 Lbs/Hr or 749 Ltr/Hr. Fuel Remaining: 999 Gals. or 811 br Gal. or 1999 Lbs. or 1999 Ltr. Fuel Used: 999 Gals. or 811 br Gal. or 1999 Lbs. or 1999 Ltr. Time to Empty: 19 hours 59 minutes AUX: +/- 1999 RS-232/422 Input Ports (FP-5L Only) Single Line Receive Method: RS-232C or RS-423 Dual Line Receive Method: RS-422 or RS-485 (with 120 ohm external resistor) Protocol: 1 Start bit, 8 Data bits, 1 Stop bit. Baud Rate: 1200, 4800, 9600 Receive Format: Moving Map, Northstar or NMEA. RS-232/422 Output Port (FP-5L Only) Transmit Method: RS-232C Single Line. Protocol: 1 Start bit, 8 Data bits, 1 Stop bit. Baud Rate: 9600 (Receive Format must be set to Moving Map). Transmit Format: King KLN88, Garmin, or UPS. Fuel Flow Transducer, Standard (FT-60) Range: 0.6 to 70+ GPH Linearity: 1% over an engines normal operating range. K Factor: Approx. 68,000 Pressure Drop: 0.5 PSI at 28 GPH 2.0 PSI at 56 GPH Working Press: 1000 PSI Min. Burst Press: 4000 PSI Temp. Range: -65° C to 125° C Fuel Ports: 1/4" Female NPT Fuel Flow Transducer, Special (FT-90) Range: 2 to 125+ GPH K Factor: Approx. 33,800 Pressure Drop: 0.5 PSI at 63 GPH 2.0 PSI at 127 GPH Working Press: 1000 PSI Min. Burst Press: 4000 PSI Temp. Range: -65° C to 125° C Fuel Ports: 1/4" Female NPT Fuel Flow Transducer, Special (FT-180) Range: 2 to 250 GPH K Factor: Approx. 22,400 Pressure Drop: 0.5 PSI at 88 GPH 2.0 PSI at 176 GPH Working Press: 1000 PSI Min. Burst Press: 4000 PSI Temp. Range: -65° C to 125° C Fuel Ports: 1/4" Female NPT with #8 Female Flare Fitting 16 Drawn By: Electronics International Inc. Approved By: Scale: Material: Next Assembly: P/N: Date: Rev: D/N: 12/29/93 1229931 R.R. R.R. None Installation of a Fuel Flow Transducer on the Fire Installation of a Fuel Flow Transducer on the Fire Installation of a Fuel Flow Transducer on the Fire Installation of a Fuel Flow Transducer on the Fire Installation of a Fuel Flow Transducer on the Fire Wall and in the fuel line Wall and in the fuel line Wall and in the fuel line Wall and in the fuel line Wall and in the fuel line from the fuel pump to the from the fuel pump to the from the fuel pump to the from the fuel pump to the from the fuel pump to the carburetor or fuel servo carburetor or fuel servo carburetor or fuel servo carburetor or fuel servo carburetor or fuel servo..... Note: Note: Note: Note: Note: Not applicable Not applicable Not applicable Not applicable Not applicable for a fuel injected engine with a for a fuel injected engine with a for a fuel injected engine with a for a fuel injected engine with a for a fuel injected engine with a fuel return line (see D/N 0415941). fuel return line (see D/N 0415941). fuel return line (see D/N 0415941). fuel return line (see D/N 0415941). fuel return line (see D/N 0415941). D: 7/2/02 (OUT) (IN) Fuel Flow Transducer Bracket To the Carburetor (or Fuel Servo) Adapter, (1/4 NPT to Fuel Hose) Adapter, (1/4" NPT to Fuel Hose) From the Fuel Pump (or Fuel Filter on a gravity feed system). Mounting Procedure 1. Find a convenient location on the fire wall (away from any hot exhaust pipes) and mount a bracket for the Fuel Flow Transducer. Check both sides of the fire wall for clearance before drilling any holes. 2. Mount the Fuel Flow Transducer onto the Bracket. You must use the FT-90 (Gold Cube) Fuel Flow Transducer on a gravity feed system or for any engine over 350 H.P. You must use the FT-180 (Black Cube) for any engine over 550 H.P. If the Transducer is mounted within 6" of an exhaust pipe, the Flow Transducer must be wrapped with Fire Sleeving. 3. Remove the fuel hose which goes from the Fuel Pump (or the Fuel Filter on a gravity feed system) to the Carburetor (or Fuel Servo). 4. Purchase two new hoses, one from the fuel pump (or the Fuel Filter) to the Fuel Flow Transducer (making provisions for the fuel pressure transducer as necessary) and the other from the Fuel Flow Transducer to the carburetor (or Fuel Servo). There must be flexible hose in and out of the Transducer. The hoses must meet TSO-C53a Type C or D FAA specification. The new hoses must be the same size as the current hoses in the aircraft. A source of fittings and fabricated hoses is: Sacramento Sky Ranch Inc. (916) 421-7672 (800) 433-3564 Fax: (916) 421-5719 Varga Enterprises Inc. (480) 963-6936 (800) 966-6936 FAX: (480) 899-0324 OR 5. Read the Installation Instructions for important installation considerations. 17 OR Hoses Unlimited Inc. (510) 483-8521 Fax: (510) 483-8524 Drawn By: Electronics International Inc. Approved By: Scale: Material: Next Assembly: P/N: Date: Rev: D/N: 12/29/93 R.R. R.R. None Installation of a Fuel Flow Transducer suspended in Installation of a Fuel Flow Transducer suspended in Installation of a Fuel Flow Transducer suspended in Installation of a Fuel Flow Transducer suspended in Installation of a Fuel Flow Transducer suspended in the fuel line the fuel line the fuel line the fuel line the fuel line from the fuel pump to the carburetor or from the fuel pump to the carburetor or from the fuel pump to the carburetor or from the fuel pump to the carburetor or from the fuel pump to the carburetor or fuel servo fuel servo fuel servo fuel servo fuel servo..... Note: Note: Note: Note: Note: Not applicable Not applicable Not applicable Not applicable Not applicable for a fuel injected engine with for a fuel injected engine with for a fuel injected engine with for a fuel injected engine with for a fuel injected engine with a fuel return line (see D/N 0415941). a fuel return line (see D/N 0415941). a fuel return line (see D/N 0415941). a fuel return line (see D/N 0415941). a fuel return line (see D/N 0415941). (IN) (OUT) From the Fuel Pump (or Fuel Filter on a gravity feed system) To the Carburetor (or Fuel Servo) Fuel Flow Transducer Adapter, (1/4" NPT to Fuel Hose) 6" Maximum from support or fitting Mounting Procedure 1. Find a convenient location within 6" of a hose support or fitting and away from any hot exhaust pipes to suspend the Fuel Flow Transducer. The hose support or fitting may be on the input or output line of the Flow Transducer. 2. Remove the fuel hose which goes from the Fuel Pump (or the Fuel Fliter on a gravity feed system) to the Carburetor (or Fuel Servo). 3. Purchase two new hoses: one to be used from the fuel pump (or the Fuel Filter) to the Fuel Flow Trans- ducer and the other to be used from the Fuel Flow Transducer to the carburetor (or Fuel Servo). There must be flexible hose in and out of the Transducer. The hoses must meet TSO-C53a Type C or D FAA specification. The new hoses must be the same size as the current hoses in the aircraft. A source of fittings and fabricated hoses is: 4. Mount the Fuel Flow Transducer in the fuel line. You must use the FT-90 (Gold Cube) Fuel Flow Transducer on a gravity feed system or for any engine over 350 H.P. You must use the FT-180 (Black Cube) for any engine over 550 H.P. If the Transducer is mounted within 6" of an exhaust pipe, the Flow Transducer must be wrapped with Fire Sleeving. 5. Read the Installation Instructions for important installation considerations. D: 7/2/02 122993218 Sacramento Sky Ranch Inc. (916) 421-7672 (800) 433-3564 Fax: (916) 421-5719 Varga Enterprises Inc. (480) 963-6936 (800) 966-6936 FAX: (480) 899-0324 O R O R Hoses Unlimited Inc. (510) 483-8521 Fax: (510) 483-8524 Drawn By: Electronics International Inc. Approved By: Scale: Material: Next Assembly: P/N: Date: Rev: D/N: 10/15/94 R.R. R.R. None Installation of a Fuel Flow Transducer suspended in Installation of a Fuel Flow Transducer suspended in Installation of a Fuel Flow Transducer suspended in Installation of a Fuel Flow Transducer suspended in Installation of a Fuel Flow Transducer suspended in the the the the the fuel return line fuel return line fuel return line fuel return line fuel return line from the carburetor to the fuel from the carburetor to the fuel from the carburetor to the fuel from the carburetor to the fuel from the carburetor to the fuel t a n k . t a n k . t a n k . t a n k . t a n k . Note: Note: Note: Note: Note: Only applicable Only applicable Only applicable Only applicable Only applicable for installation on aircraft for installation on aircraft for installation on aircraft for installation on aircraft for installation on aircraft with a fuel return line from the with a fuel return line from the with a fuel return line from the with a fuel return line from the with a fuel return line from the Carburetor. Carburetor. Carburetor. Carburetor. Carburetor. (IN) (OUT) Fuel Flow Transducer Adapter, (1/4" NPT to Fuel Hose) 6" Maximum from support or fitting Mounting Procedure 1. Find a convenient location within 6" of a hose support or fitting and away from any hot exhaust pipes to suspend the Fuel Flow Transducer. The hose support or fitting may be on the input or output line of the Flow Transducer. 2. Remove the return fuel hose which goes from the Carburetor to the Fuel Tank. 3. Purchase two new hoses: one to be used from the Carburetor to the Fuel Flow Transducer and the other to be used from the Fuel Flow Transducer to the Fuel Tank. There must be flexible hose in and out of the Transducer. The hoses must meet TSO-C53a Type C or D FAA specification. The new hoses must be the same size as the current hose in the aircraft. A source of fittings and fabricated hoses is: 1015941 To the Fuel Tank Fuel return line from the Carburetor 19 4. Mount the Fuel Flow Transducer in the fuel return line. You must use the FT-90 (Gold Cube Fuel Flow Transducer on any engine that has over 350 H.P. You must use the FT-180 (Black Cube) for any engine over 550 H.P. If the Transducer is mounted within 6" of an exhaust pipe, the Flow Transducer must be wrapped with Fire Sleeving. 5. Read the Installation Instructions for important installation considerations. A: 7/2/02 Sacramento Sky Ranch Inc. (916) 421-7672 (800) 433-3564 Fax: (916) 421-5719 Varga Enterprises Inc. (480) 963-6936 (800) 966-6936 FAX: (480) 899-0324 O R O R Hoses Unlimited Inc. (510) 483-8521 Fax: (510) 483-8524 Drawn By: Electronics International Inc. Approved By: Scale: Material: Next Assembly: P/N: Date: Rev: D/N: 4/15/94 R. R. R.R. None Installation of the Fuel Flow Transducer suspended Installation of the Fuel Flow Transducer suspended Installation of the Fuel Flow Transducer suspended Installation of the Fuel Flow Transducer suspended Installation of the Fuel Flow Transducer suspended in the fuel line in the fuel line in the fuel line in the fuel line in the fuel line between the Fuel Servo and the Flow between the Fuel Servo and the Flow between the Fuel Servo and the Flow between the Fuel Servo and the Flow between the Fuel Servo and the Flow D i v i d e r D i v i d e r D i v i d e r D i v i d e r D i v i d e r ..... Note: Note: Note: Note: Note: Only applicable Only applicable Only applicable Only applicable Only applicable for installation on aircraft for installation on aircraft for installation on aircraft for installation on aircraft for installation on aircraft with a fuel return line from the Fuel Servo. with a fuel return line from the Fuel Servo. with a fuel return line from the Fuel Servo. with a fuel return line from the Fuel Servo. with a fuel return line from the Fuel Servo. 0415941 Mounting Procedure 1. Find a convenient location between the Fuel Servo and Flow Divider and away from any hot exhaust pipes to suspend the Fuel Flow Transducer. 2. Remove the fuel hose which goes from the Fuel Servo to the Flow Divider. 3. Purchase two new hoses: one to be used from the Fuel Servo to the Fuel Flow Transducer and the other to be used from the Fuel Flow Transducer to the Flow Divider. There must be flexible hose in and out of the Fuel Transducer. The hoses must meet TSO-C53a Type C or D FAA specification. The new hoses must be the same size as the current hose in the aircraft. A source of fittings and fabricated hoses is: Adapter, (1/4" NPT to Fuel Hose) (IN) (OUT) From the Fuel Servo To the Flow Divider 4. Mount the Fuel Flow Transducer in the fuel line. You must use the FT-90 (Gold Cube) Fuel Flow Transducer on any engine over 350 H.P. You must use the FT-180 (Black Cube) for any engine over 550 H.P. If the Transducer is mounted within 6" of an exhaust pipe, the Flow Transducer must be wrapped with Fire Sleeving. 5. Read the Installation Instructions for important installation considerations. 20 B: 7/2/02 Sacramento Sky Ranch Inc. (916) 421-7672 (800) 433-3564 Fax: (916) 421-5719 Varga Enterprises Inc. (480) 963-6936 (800) 966-6936 FAX: (480) 899-0324 O R O R Hoses Unlimited Inc. (510) 483-8521 Fax: (510) 483-8524 1\abhls.,.__ llqmmmt of ~llim-lFO>md ·""- ~ .§uppletntutal wuve <!rertifinrtt Dupleate Orig.,al lo ret:~liiiiQe lo$1 STC ,A/;ntk SA00068SE :?I.:J~ ~k.· E1eetronles lntomational, Inc. 63296 Powell Butte Highway B end, OR 9770 1 t>Ed~~,..G,.,fh~.wa, {H-iW-Ffod,pA;w4p~-u~.~& ~'1~-J--w~ ~--~/-<-t---c.u.~,.,.-"/'.9lm . -/d. ·EJP.~. ~~.1--/T.tfN ~.,..-f"-.(....· •See attached FAA Ap,:~rcwed Model Ust (,t.ML) .A'~.· No SAOOO&SSE for a 11&1 ot approved airplane 9J,~.y'M., ~9~ ~.. Eleettonie:s lnternOltioOnal fuel nowlpressute instrumtf1 manufactured and installed in accordance v.;th the drawings and installation instructiOns specified on the FAA AMl of thiS $TC, or latet FAA appro~ revisioo. P.'OTE The instrument 3PD'Oved by this STC is to be used as a &eCOndatY inMrumont oNy. TN& approval does not alow the removal of any original equ.xnent lnscrumenta~ lon. See the C()(l(inl.lation Sheet for req~,~ired plae.rds .?-r&<I'<M.~ ..,_t~II.M.l.· Approval of this change in ~pe deSign applies to the airplanes and factory installed or STC'd Al>at ooml:l&nabOns listed on the AMl only. This f9Proval sho1.1ld not be extended to other wcratt ol these models on \\t.c:h other pre\liously approved modrllcatiOOS are inOOtJ)Orated unless it is de;ermined by the r.&taner thai the relationship between this change and any of those other previ01.1Siy approved modlflea1Jons, Including Changes in 1ype de~n . Wil introduce no ac:Mtrs.e eff6ct 1.1pon the airworthiness of that aircraft. A oopy of this Certificate, Continuation Sheet, and AML must be maintained as part ot the pennanent ttcOI'ds fOt the moddied aiiC:tafl. If the holder agrees to permit another person to use this certi'ficate to alter the product, the holder shall give the other pel'$on writt en evidence of thlt permission (Sec Conbnuation Sl'leel p.-,;c 3 ) .9L-.~.....rytuwU~btJ~~.rW.. -tJ~JbtJtl..mfo.,_..........~~~~-r./~ ~~.-.t~-.. ~-~iltii~JWJ~~""'~"-tN.Ytk Y~Jlf~Jlf~IM.. !i..ll--.1- OC!obe! 15, 2002 Mwet'l31. 1994 ......tl.,_ ~ ot h>o!•rtO J"llml ,__ ~ &uppltmtutal WtWt <!rertificatt UKlrMic1 lttr.m~~ MNI, Iiiii... A~ Octcw t 5. 2002 ~Hill Ck:IOW 15. 2002 ((!lontinuatilm &lyutl The "o.IO...W~&~ ~fnlltl bt loe;lled Oil !he tMtr.Jmenl panel .editeM tO._. E_TI[IICII'r.II'IIC:I lnlemaliOolll.ltl now.~,. m~~Unent •wove<~ tly"" src· For ;.II t»V~'I ~ ·oo NOT-YOft FUEL FLOW I NS'IRUI~T TO OETE RM!N£ n.JEl. LEVElS INTANt<l!5 • For alrtrilll\ OlfVINifv ~IIPI*d..t~ntwt !\ow ilno'or p-c:s.s~n tnetNme"IJ 'ft£FER TOOA>GNAL FUB. FlOW..,.ESSURE INSTRWEHTAnON ~ PRIUAAY INFORt.tATION . e.o ,._~-·"'·~··_.... .._,~_. ..,,. FAA APPROVED MOD EL LIST (AML) SA00068SE FOR - AIRCAAFT MAKE t AUOco...A.Notllt j'Y(IIMitJ 2 AIROHCA INC. (AIIo See AMenrcM Cll~} 3 AEROMOT • AIJIOIPATW.E $AGCAT~ IAilltnt~INC 7 AUJANC:l .-..CAAI'l GIU)t.. (HetoEf'llllei'Pfl&e6! I ALOfll t AMlltiCAN BuMP COMPANY tO AMIRICAN CIHAM!l'tON {AMine" e.a.rg T~ It AMatiCAN GEHEftAL. AIACftN"l 12 AUGUSTMit ..C. IV~•> ELECTRONICS INTERNATIONAL, INC. FUEL FLOW/PRESSURE INSTRUMENTS AIRCRAn MOOEL tO, 1~ 100 100A 100.180 !!0-l !0-U\ 86-<A, e&<.B 1SAC StSAC C.3. PC-) ORIGIHAL ISSUE DATE March 3 1 199-4 OfttGINAL CERTIFICATION FAA SEALED DRAWltoiGS INSTAl..l.AllOH AMl TC BASIS FOR ---.,.------.....:IHS~T~RUCT::::;;.:'ONS=::....- AM.-o I NUMBER ALTER.AT K>N NUfieP I ftfVISIOH NUMeP: AEVliiON DATE TOttXI92 1 1A21 CARS A-702 CAR <A M02 CARS A-381 8Ul7A 00606931 107~..2002 cwl.atetFAA ....,_ - 02·11·2003 02·1t-2003 10.1$.18$7 10·20-2010 AMT.tOO AMT-.200 AWT·200S.AUT..)()() TGOOQOCAT CfR21 02·U--2003 s..-. ......0.184 G164A. 01&18 G1&4C ~t..O tAte CARl 02-11~3 G-t&48otST, G-1&48-34T, G-t&4S.T 1AI8 CARl 02·11-2003 AT·HO AT·300 ·301 .)02 ..eocl . ..tOGA AiSW rAR2t 10·20-~tO AT-401 AT-401A,AT..t01B AT-'02, AT· A17SW F'AR21 t0.2'0o2010 .t02A _AT.-.028 AT-601 AT·502 AT·502A. AT.eo2B AT~ AT· At7SW FAR21 1Q.2().20t0 500A. AT·504 AT-It» AT-ICJ2A, ,t.T.f102 A19SW FAR2) 10.20-2010 H·2MI K-29S KT·29$ 1AI CARS 02-tt-2003 H-3918 H·396 H3~ 1AO CARl 1Q.17-te94 H·$91 1AI CAR S 02-11 2001 H-700. H-800 1AO CARJ 10.17·1994 s...- 02·11·2003 A.&l . ......,. A$1 ... FAR2t 10.t6-t~7 A-1-50 S00002SC fAR21 10.16-1997 1N:; 1'8CM, 70C 870C ...,.. CAR <A 02· 1 1-2003 7N:;A, S1AC 78CM (f..-1M) ...,.. CAR4A 1~ t0 1CCM $7CCM A· 75e CAR4A 02· 1 t-2003 tf"C. 7.1C ?EC. S7EC 70C. 7HC TI<C ...,5t CAR <A 10-20-2010 7GCA. 7GC8 7GCM., 7KCA8 7ECA. ...,.. CAR4A 02·1l·2003 7GCIC TKCAB L·1~ l-168 ...,5t CAR4A 02-11·2003 7GCI!A ..,.. CARt 02·11·2003 II<CAil IIOCIC A21CE FAR23 02·1 t-2003 11 AC.11 BC St1AC.S11BC A-761 CAR4A 02·U·2003 ttCC S11CC ...,. CARl 02--lt·200l S.. ~Arntn~C*t 02·1 1-2003 21$0 2t50A- 2180 <A10 CARJ 02·11·2003 P.t0tt01t1 1- AIRCRAFT MAKE 13 AVlAT INC. (- . S<y, Chii<J F Ooyle) (Christon~$) (WhiM kttel'ltatio.ltal) 1• BEECH AIRCilAFl CORP. AIRCRAFT MAKE 1 5 BEU. HEUCOf"TER Beu. HEUCOf''TER tC<wr.) 16 BeiJ..ANCA AIRCRAFT CORJIORATION (See Amencano Cbe~nJ t7 BOEING AIRCRAFT 18 BRANT\.Y tt CUSHAAfRCIU1T~. AIRCRAFT MODEl A·1 . A-1A.A-18 A-1C- t 60, A ·tC.200 S · 1S, S · 1T &-2 S·2A. S·2S. S·2B, S·2C 18A. $18A 180 At61A A180. SA18A. $AI 80 19A, 819, M19A, 2 3, A23, A23A, A23--24, C23. 823 A24, A24A. 924R. C24R. A23-HI 35, 35A.. A35. 835. C3-5, 036, E35 F35 G35 H3~. J3~. 1(35. M3S. N35. P3.5, $35. V3.5, V35A, V3SB, 35-33 35-AJJ, 35·833. 3S.C33. 3S.C33A. £33. E33A, E3'3C. F33. F33A f33C, G33, 36, A36,A36'TC, 836TC •s (YT·34). M~ (T-34A, 8-4$), 045 (T:l48) 50, 850. CSO, OM. 050A. 0509. OSOC 060E 050E-6m. E$0, F$0, 050. H50, JSO A55. 655. 9559. CM. C55A. 055, 05~ E55, E55A 56TC. A56TC $$.58A 58P, 58PA, 58TC, 58TCA 60. A60, B60 65. GS-$0. GS-A80. 6$-88, 6$.881(), A$5, A6S.8200 70 60-$0. 6$.-00. $$.A90 6S.A9Q.1 (JU•21o\. RU·21A, RU·21D, RU· 2 1H., U·21A. U.21G) 6s.A90-2 (RU-219). 6~ (RU-2 1C) 6S.A9Q..4 (RU-21E, RU-21H), 85-880. 70, A65, A-6S.8200. 890 C90.C90A C90GT, C90GTi.UO H90 (l....,A) ,.n 95, 895, B9SA. 095A, E95, 95-55, 96- A$5 ~856 95-BSSA. ~558. 95-C55. 95-C55A. AIRCRAFT MODEL ORIGINAL TC NUMBER A22t<U A22HM A8SO AOSO GOO ·- A ICE At(;£ A·777 3A\S 3AI$ 3A1S 5113 ..... 5M 3AI$ 3A16 3AI$ A23CE A12CE 3A20 3A20 3A20 3A20 3A20 3Po20 A29CE A30CE ~I$ ~~· ORIGINAL TC I NUMBER 47. 478. •70.4101. 47E. 47G, 470·2. HI .,.., 2H1 47J. 47K, 47J.2 , 47J· 2A, 2H1 8-2 , B-2A. B-28, 2H2 47G·2A. 4 70·2A·1. 47G-3, 470.38 41G· 2H3 3(1.1 470~. 4TG-4A. 47GS, 47G-3B-2. •70· 2H3 5A.. 47G-38-2A 17 ·30A, 17-31A A\8CE 17 ·3 1ATC A18CE OW· I MNW 14·13. 14- 13--2. 14·13-3. 14-13-JW A-TT3 14· 19 14-19·2. 14-19-3. 14·19-31\, 17--30, IA3 11·31 . 17-31TC 7Sil1ou E7S, ATSJI. A7~300. AT911 tlw AoT43 E75N1, 1B7SA 8-2. 8-lA. 8-28 2H2 47 4 78, •70. 4701. 47£, HI 47G, •7G·2. 47H·1 HI 47G-2A. 47G·2A·1 . 2Hl 4 7<>-3, 4TG-3B 47G-3$.1.47G-38-2, 2H3 47G-3S.2.A 4?G-4. 4TG-4A 2H3 47(;.6, 470.~ 2H3 120, ·~ A-768 C·145. C·165 A-101 150 tnru 1 50U, A15CI<, A150L. A150M, 3A\9 152, A152 170 thru t ?00 ...,.. 172 ttlru 1 720 3A\2 172R. 172S 3AI2 t72RG """ P1 720 :lAIT R172E lhN RtnK 3AIT 175 ttlru t 75C 3AIT t?7 thru 1779 A\:>C€ 177RG A20CE 180 t:hru t 80K •M 182 t:hru 182$. tSZT 3A\3 R182, T182., l182T, TR182 3AI3 ORIGINAL ISSUE DATE· March 31 1994 CERTIFICATION FAA SEALED DRAWINGS INSTAU.ATION AML BASIS FOR INSTRUCTIONS AMENDED ALTERATION HUMBER R!VISIOH NUMetR R!VI$10frl DATE FAA23 . . . . 02·11·2003 FAR2:3 . . . . 10.20·20 1() FAR23 " . . . 02-11·2003 FAA23 . . . . 02· 11 ·2003 9UL7A . . . . 02·1 1-2003 BUL7A . . . . 02·11·2003 CAR3 . . . . Nono CAR3 . . . . 02· t 1-2003 CAR3 . . . . Nono CAR3 . . . . 02·11 ·2003 CAR3 . . . . 02-11-2003 CAR3 . . . . ..... CAR3 . . . . 1().20-2010 CAR3 . . . . 02· 11-2003 CAR3 . . . . 02·11·2003 CAR3 . . . . None CAR3 . . . . ..,. CAR3 . . . . 02· 11-2003 FAR23 . . . . Noooo FAR23 . . . . None CAR3 . . . . 02·11·2003 CAR3 . . . . 1().20-2010 CAR3 . . . . 1().20-2010 CAR3 . . . . 1().2().2010 CAR3 . . . . 1().20-2010 CAR3 . . . 10.20-20'10 FAR23 . . . Nooe FAR23 . . . Nono CAR3 . . ....CAR3 . . .... ORtGI NALISSUE DATE March 31, 1994 CERTIFICATION FAA SEALED DRAWINGS INSTALLAllOH AML BASIS FOR ----r-------~I:;N::_ST:.:;"""':::;:~I;:ONS:::,_ _,. AMENDED ALTERATII()N NUMIU I REVIS*!»! HUMBER REVISION DATE CAR$ CAR& CAR6 CAR$ CAR$ FAA23 FAR23 FAR21 CAR <A CAR3 CAR4A CAR6 CAR$ CAR& CAR6 CAR6 CAR$ CAR6 CAA<A CAA 4A CAR3 CAR3 CAR 3 FAA23 CAR3 CAR3 CAR3 CAR3 FAR23 FAA23 CAR3 CAR3 CAR3 <n-1 1-2'003 None None Noo>e None None None 02·11 ·2003 02-1 1·2003 02·1 1·2003 02·11·2003 tn·11·2003 02·11..2003 02·11-2003 02·11·2003 02·11·2003 02·11·2003 02·11·2003 02·11·2003 02·11·2003 10.20·20 10 02-11-2003 02·11·2003 02·11·2003 02:·11·2003 10-20·20 10 02·11·2003 10.16-1997 02-11-2003 02·11·2003 02:·11 · 2003 10·20-.201 0 10.20·2010 ••• AIRCRAFT MAKE AIRCRA" M ODEL CUSNA AIRC#t.AFT CORP. t¢ovf.J 185. 18SA.. 1858 185C, 1850, 185E, A185E.A185F 18$, 1$8A. 1$88 Al88, A188A. A1888, T188C 190, 195, 19SA, 1958 206, 206ft P206 thru P206E, T206H TP206A'hN TP206E U2<l6 ttliV U20&G TU2<l6A thru TU206G 207, 207A, T207, T207A 210, 210A, 2108, 210C, 2 100, 210E 210F, 2tOK. 210R 210-5 ( 205). 21().5A (205A) T2 10F, 2100, T210G, 210H, 2 10J Tl1011, Tl' lOJ, T21(llr<;, ~10M. .t 101\, <0! 101.. l2 t 0l. T2tOF T2t0M, 210N P2tOH. P21M., T2 10R T210N T300 305A. 306C, 3050, 305F 3058 JOOE 310, 31C)A, 3100, 310C, 3100, 310E, 310f, 310K, E310H 3101, 3t0J. E3t0J, 3tt»<, 3HJl 310N, 3 10P, 310R T310P, T3 10R T3100 3100 320, 320A, 3208, 320C 3200, 320E, 320F 32 1 336 337, 337A, 3378 337£. 3J7C T3379 T337E. T337C 3370, P3378,. F337F M3378, 337H T3J70, 1'33nt 340, 340A 40 1, 401A. 4018 · - AIRCRAFT M AKE A IRCRAFT MODEL CESSNA AIRCRAFT CORP. {Co!tr.t 402. 402A, 40'28 402C ...406 411. 411A 414 414A A21. 42-lA. 4219 421C 425 S-4A (Stibel) 20 CHlO, OOVLE F, SMAWat 21 CHRISTEN INDUSTRIES SeeAviat 22 CIRRUS DESIGN CORPORAnoH SR20 SA:22 & SA.22T 23 Cl.AAA 1000 12 2A C0MMAHOER AIRCRAFT 112. 112TC, 1128, 112TCA 114, tl ~ 500, 500-A. S00.8, 500.5. 500-U. 520. 560, 560-A. 560-E 560-F. 680. 880-E. $80.F. &eOFL. $80T, 680V, 6roN, 68 t. 685 690A chru 8900, 6$1S, 6$$A.. 6$$9 700 COMMANDER AIRCRAFT (¢oo.'T, 72<l 1 148. 11ATC 0t HAV..LANO Mt.CRNT OHC·2 INC. I, DHC-2 Mk. II. OHC· 2 J.a: . Ill ,. COMPANY, LTD. OHC·3 OHC·1B·2·S3, OHC· 1B·2 ·S5 OH02A 0H82A Oe HAVI.l.ANO AlltCR»T OH.C1, 21 , 22, 22A COMPANY, L TD . (COfrot.l L-20A Z6 OIAMONO AIRCRAFT INOUSliii:IU OA 20-A1, DA 20.C1 OA40, DA40F 27 OMNI!R·WERK! 00270.$ 0028A ·I, 0028S.1 00280 00280. 1 ORIGINAl ISSUE DATE· ORIGINAL CE1mFICAOON FAA S EALEO DRAWlNG$ INSTALLATION TC BASIS FOR I NSTRUCOONS NUMBER ALTERATION NUMetlt RI!!VI $11)N NUMBER Rf.VISION 3A24 CARl 3A24 CARl A9CE FAR23 A9CE FAR 2) A-790 CARl A4CE CARl A4CE CARl A4CE CARl At 6CE FARZl 3A21 CARl lA21 CARl lA21 CARl ""' CAA~ 3A21 CARl 3A21 CARl A3ACE FAR 2:) 5A5 CARl 3A t4 CARl 3A 10 CARl 3A10 CAR3 lAIO CAR3 3A10 CAR 3 JAIO CAR3 3A25 CAR3 3A25 CAR3 3A11 CAR3 I\2CE CAR3 Ae<:E CAR3 A5CE CAR3 MCE CAR3 Ae<:E CAR3 A5CE CAR3 A5CE CARJ 3A25 CAR3 A7CE CAR3 ORIGINAL ISSUE 0ATE ORIGINAL I CERTIFtCATION FAA SEALED DRAWINGS INSTALLATION TC BAStS FOR INSTRUCOONS NUMBER A L T ERAnoN 1 NUMBER REV1$10N NUMBER RE\IlsiON A7CE CAR3 A7CE CAR3 A>&:E FAR23 A2SCE FAR23 A7CE CAR3 A7CE CARl A7CE CARl A7CE CARl IH2 CAR& A00009CH FAR23 2A& CAR& 2A 12 CAR$ A12SO FAR 23 A12SO FAR23 ...., CAR3 2A4 CARl 2A4 CAR3 A I2SW FARZ3 2A4 CARl A12$0 FAR>J A ·806 CARlO A.$ 15 CARlO A26NM CARlO A5PC FAR21 A8EU FAA21 A44EU FAA2 1 AR-33 CAR$ TA4CO< FAA21 AA7CE FAR21 A81N CAR10 7A13 CARlO A16EU FAR>J March 31, 1994 AML AM ENDED DATE 02·1t·2003 ....02· 11 ·2003 1().2().2010 1().2().2010 02· 11 ·2003 02·11·2003 None 02· 11 ·2003 10.20-2010 02·11·2003 ....l ~~;t\) 1(1 1().20-2010 None 02-U-2003 02 ·1 1· 2003 02·11-2003 02·1 1· 2003 02·11·2003 ()2. t 1-2003 None No"' None 02-t l-2003 02-11-2003 02-11-2003 02·l1·2003 02·1 1o2003 02·1 1·2003 02- 11·2003 02·1 1o2003 02·11·2003 02· 11-2003 02·1 1·2003 March 31 . 1~4 AML ' AMENDED DATE 02·1 1-2003 0 2-H -2003 02·1 1·2003 02·1t-2003 02·1t·2003 02·1 1-2003 02·11·2003 ....02·11·2003 02·1 1·2003 02-11 -2003 10.20-2010 02·1 1·2003 02·11·2003 1)4..2().1994 04·20-1994 1().2().20 10 02-11-2003 10. 16- 1997 02-tl-2003 02- 11-2003 10.20..2010 U)-20-2010 10.16·1997 02-11-2003 02· 11 · 200) 02· 11 ·2003 02·11-2003 02·11·2003 02·11·2003 10· 20-20 10 02·11·2003 02·11·2003 02· 11-2003 ORIGINAL I SSUE DATE M h 31 1994 arc ORIGI NAL CERTIFICATION FAA SEALED D RAWINGS INSTALLATION A M L ·~· AIRCRAFT MAKE AIRCRAFT MODEL T C B ASIS FOR I NSTRUCTIONS AMENDED NUMBER ALTERATION NUMB'flt 1 RfVISION l NUMBER RfVtSIOH DATE OCIRNIER•WERI<E !CCWI'.) 228-100,228-101, 228-200. 228-201 . A16E.V FAR2l . . . . 02·U·2003 228-202,228-212 28 EHSTROM F-28, F·2aA, F·28C, F·28F H1CE CAR6 . . . - 02-11 ·2003 280. 2toe. TH-28, .t80, 2.80F, F-28FX HICE CAR6 . . . - 02·11·2003 29 ERCO SN!Jnlv.w -- --- -- -- -- -- 02·11·2003 30 EXTRA flUG.UUG8AU EA-300, EA.-lOOS, EA 3001'200, 300l A87EU FAR23 . . . - 02·11-2003 3t FAIRCHILD 24R9, 24R9S, 24R40. 24R40S, 24R48, A-106 CAR4A . . . - 02·11·2003 24R46A, 2-4R46S 24\V.$, 24W.9S 24W-40, 24W..4QS, 24W- >.707 CAR4A . . . - 02-11-2003 41 , 24W.o41A 24W-41AS, 24W-41S, 24W~. 24W-46$ A·707 CAR4A . . . - 02·11-2003 M62A. U62.A.-3. M62A-4, M$28, M$2(:, ~ A·724 CAR4A . . . . 02-11-2003 ., z• cec. z• cecs A·535 8Ul7A . . . - 02·11·2003 M-BA·C A-2-599 CAR <A . . . - 02·11-%003 J.2 FOfi:HfY see tkl•v&r -- -- -- -- -- --- 02-11 ·2003 l3 FUJI FA·2~160, 180, 180AO MPC CAR 10 . . . - 02·11-2003 34 GLOBE (SvriffJ OC.lA, Gc.-18 A-766 CA~4A . . . . 02-11-200) 35 GOOOY'tNt GI<·22A 1A12 CAR> . . . . 02-11-2003 GA.·2, GA.-28 A·784 CAR4A . . . - 02· 11·2003 36 GAOB G-1t$. t1M. 1 168 11$C. 11$C2. 11SO. A-57EU FAR2t . . . - 02-11·2003 115D2 37 GULF$Tli£AIIt Alllllt«:AN CI)IW. ~1!$ 1At7 CAR<8 . .. - None (Arne(iean Genera') G-1159 At2EA. CAR48 . . - None (GiuF)VI")BnAifCr'8ttl AA·1, M·1A.AA·18 At 1EA FAR2> . .. - Noooo trl9f'f Aircta~ AA·tC A11EA FAR>J . . - None AA-5, AA·SA, AA.SB, AG-58 A 1$EA FAR2> . . - 02·11·2000 38 HfUCOf'TEft TfCHHIIC FJ Sky·Ttae H5EU FAR27 . . - 02-11-2003 31 HEUTECH CO.. H-$-tN H12WE FAR21 . . - 02· 11 · 2003 40 HEUOA.II't:ta~ 1St't,20 ll\3 CIII\1A . . . 1Q-16-19i7 41 HIU.'A UH· 12, IJH..12A 6H1 CAR6 . . . 02-11· 2003 UH-128. UH·12C 6H2 CAR6 . . - 02· 11 -2000 HIUER(~ .) UH-120 4H 10 CAR6 . . - 02·11·2000 UH-12E UH-12E-L A.H 11 CAR6 . . - 02·11·2000 UH·12l HlWE CAR6 . . - 02-11-2003 42 HOWARD OOA-3 ~Army UC·70C) 6 12 BUL7A . . - 10·20..2010 00A·9(Army UC-100), OGA-12 (Army ... SUL 7A .. . - 10-20-20t0 UC·70A) DGA-11 072 9UL7A . . - 10..20..2010 ORIGINAL I SSUE DATE· March 31 1994 O~VGINAL CERTIFtc.AnON FAA SEALED DRAWINGS INSTALLATION A ML ·- AIRCRAFT M AKE AIRC RAFT MODEL I TC BASIS FOR INSTRUCTIONS AMENDED NUMBER ALTERAnON HUMBER A:f.VISION NUM&at 1\EVISION DATE HQwAAO tCoo11 ,) DGA· 15P (Army UC·70, tQvyGH-1 . GK- A· 717 CAR4A . . . . 11).2().2010 2. GH-3, NH·1) OOA-1$..1 (Nmy UC-700). OGA-1SW A-711 CA~<A . . . 10.20-2010 00Ao18, QGA.t 8K 7:)9 CAR <A . . . 10.20-2010 43 INTE:RCEPTOit Se& PlOp-Jets --- --- --·- --- ---- ---- 02-11-2003 JOOEL 0-14(1-9 AJIN C ARlO . . . 02·11-2003 OA.-1060 MIN CAA 10 . . . 02 ·11·2003 0.1190 A10tN CARlO . . . 02·11· 2003 150 A1MN CARlO . . . 02·11·2003 44 LAKE (Rf'VO) C-1, C-2, LA,., LA·<lA, l.Ao4P L.A,.4.200, 1A13 CAR> . .. . 02-11-2003 2SO 45 lU$Ca.!: 8A ltlru 8F. T-8F M94 CAR <A .. . . 10.16-1997 q MARCHETTI $206-18/f. ·18/R A9EU FAR21 . . . 02-11-2003, (&:o StAI) $205-20/F. ·20/R A9EU FAR21 . . . 02·1 1· 2003 sm-221R A9EU FAA21 . . . 02·11·2003 S208, S208A A9EU FAR21 . . . 02·11·2003 F2EO. FZ&IB-F A10EU CAR> . . . 02-1 1-2003, $211A ABOEU FAR23 . . . . 02· t1· 2003 47 MNA.E M-4 M-4C. M,.$,M-•tl, M-4-180C. M.A. ,.,, CAR> . . .. 02-11·2003 180$, M-4 ~180T M_.·210, U-4-210C. M-4-210$ M-4-210T ,.,, CAR> . . . 02·11-2003 M-4·220, Mo4·220C M..·220S Mo4· 220T :lA23 CAR 3 . . . . 02·11·2003 M-5-180C, M-5-200, M-5-210C, M-6- ,.,, CAR3 . . . . Nono 210TC M-5-220C, M-5-235C :W3 CAR3 . . . None ~180. M-6-235 ,.,, CAR3 . . . 10.17-19$4 MX -7-180 MX ·7-160C, MXT-7- 160 ,.,, CAR3 . . . 02·11·2003 M·7·180, MX-7- 180A.11'W\1 MX·7·180C, ,.,, CAR3 . . 02-11-2003 MX-7-180AC MXT· 7· 180, MXT· 7·180A ,.,, CAR 3 .. . 02·11·2003 M-7·235, M·7·235A ltlru M-7·235C, MT·7· ,.,, CAR3 . . . 02·11-2003 235. MX-7-235 M-7~60. M·7·260C, IM· 7· 260 :lA2> CAR3 . . 02·11·2003 MAULl! (Co.n.) M-7.. 20AC, MJH-420, MXT-7-420, M-3- ,.,, CAR3 . . 02·11-2003 235 4$ ME$SERSC...vrT B0-209-150 FV &RV A27EU FAR21 . . 02-11-2003 80-200.1&0 FV & Rv AV'EU FAR21 . . 02-11-2003 B0209· 150FF A27EU FAR 21 . . 02·11·2003 49 MEYERS Se&Mre.roe,:~tor --- --·-- ---· --- ---- ---- 02-11-2003 .... A I RCRAFT MAKE SO MOONEY .AIRCRAFt 51 M OAAVAN &2: NAVION 6l PARTtNAV\A 54 PWlGIO 5$ PILAT\15 S6 PIPER AIRCRAFT CO . .... A IRC RAFT MAKE PIP~R AIRCRAFT CO. (COOit,J 57 "'"" 68 PROP-JETS (~ (Aero Cotntn&ndef .s MeyefS} 5t QuEsT 60 Revo 61 ROCKWElL 62 SIAl M ARCHETTI 63 SfABll! 64 SIKOR.SKY 85 SKY EnTERPRISES ($o38o.J 66 SKY INTlRNATION.AL 67 SOCA.TA GROUP CAfrospatl<lfeJ A IRC RAFT MODEL M.18C M· 18C$5, M· 18L.t.t.181.A M20, M20A thru M20M M20R. M20S, M20TN M22 Z lin 5261. Zlin Z 242l, 143l s.. )')""' """" P_., P.$88, P.-C, P-&&TC P-68C-TC P ·166, P·166B, P ·166C, P- 136-l. P-1J&.l.1, P·t36· L2 PC-$ Pc.$.H 1• PC-6-H2. PC..et350. PC.fii35().H1, PC~H2 PC-6/A. PC-6/A.fi1, PC-6/A.fi2, PC.&'Bo tQ, PC-$.!81-H2 PCo&'B2-K2, Pc.6182· H4, PC~H2 . PC-6o'C1·H2 PC-7 PC.12, PC· 12/45, PC·12/47, PC-121-47E PA-1 1. PA-11$., JJC-40, JJC.50, J3C· 5DS, J3Co85. J3C-655 PA· 12 PA-12$. PA-1-4 PA·1 5 PA· 16 , PA·16S. PA- 11 PA-18 . PA· 1SA.. PA-18A5 PA-185, PA- 10 PA-195 PA-20. PA- 20$ PM2 , PM2S PA-23, PA-23-160 PA·23-23S, PA-23-250 PA-24, PA-24-250. PA-24-2$0. PA-24-400 PA-25, PA-25-235. PA-2~260 PA·28· 140, PA--28-150, PA·28-t5 1. PA- 28- 160. PA.-28$-160 PA,28· 16 t, PA--28-180, PA·28R· 180, PA- 28·181, PA-28R·200 PA-.28R-201, PA-28-201T PA-28R-201T, PA-28·235 PAM28-236 A I RCRAFT MODEL PA·28RT· 201. PA·28RT·20 1T, PA-28S· 180 PA.:JO PA..J1,PA-31o300, PA.-3 1·325, PA-31-350 PA..J1P, PA..J1T, PA..JtT1, PA..J1T2. PA· 31T). PA-31P-350 PA.-32-260. PA·32·300, PA·32R·300. PA- 32RT.JOOT, PA·32·301 PA-32-301T PA-32R-301. PA-32R-301T P~OO . PA-34-'200T, PA-34-220T PA-36a85, PA-38-300. PA-36-375 PA-3&-1 12 PA-39,PA-40 PA-44-180 PA-«-18()T PA~ tOP, PA.o46-350P PA-48·350T PA-60600 (Aetostar 600), PA~1 (AttODf 801) PA 60601P (Act-or 601P ~. PA-60 ~p ~rODr602P) PA-6o.700P (Aerostar 700P} SHA1~ 200. - - 2009. 200C, 2000. 400 Kodiak 100 S..'-"<• SH Commltneitr AIICI'{I, S205-181F, ·18/R $20~~~. -'20JR $205-~2/R S208, S208A F2$0, r2608-F $21tA ORIGINAL I SSUE DATE' March 31 1994 ORIGINAL CERTIFtCAnOH FAA SEALED DRAWINGS INSTALLATION AML lNSTRUCllOHS I AMENDED TC BASIS FOR NUMBER ALTERAnON NUMBER I REVISION NUM8~R """""" DATE A-80\1 CAR3 . . . 02·1 1·2003 w CAR3 . . . ....,. w CAR3 . . . . 10.20-2010 MSW CAR3 . . . .....A:l<lEU FAR2 1 . . . 02·11 ·2003 AreEU FAR2 t . . . 02-11 ·2003 --- ---- --- --- ---- --- .....A31EU FAR2 1 . . . 02· 11 -2003 1M CARlO . . . 0 2"· 11 ·2003 A·813 CARlO . . . 02-1 1·2003 7A15 CAR 10 . . . 02·11·2003 ? Al$ CAR3, 10 . . . 02· 1t ·2003 7A1S CAR3, 10 . . . 10.20-2010 7A1S CAR3, 10 . . . 1().2().2010 ASOEU FAR 23 . . . 10.20-20"10 A78EU FAR23 . . . . 1().20-2010 A... I CAR4A . . . . 02·11·2003 A·780 CARl . . . . 02·1 1· 2003 A·797 CARl . . . . 02· 11 · 2003 A-800 CARl . . . . 02-11·2003 lAI CARl . . . . 02- t 1-2003 MIOS CARl . . . . 02·1 1· 2003 IA2 CARl . . . . 02-11-2003 IA4 CARl . . . . None lAG CAR3 . . . . 02·1 1·1003 1A10 CARl . . . . Nooe 1A15 CARl . . . . 0'2· 11 ·2003 2A$ CAR 3 . . . . 02·11·2003 2A13 CARl . . . . None 2A13 CARl . . . . None 2A13 CAR3 . . . . None ORIGINAL I SSUE DATE' March 31 , 1994 ORIGINAL ICERTIFICATtOH FAA SEALED DRAWINGS TC BASIS FOA 1 NUMBER A L TERATION INSTALLATION AML -------=--=---=-_,,_._ l:N~S~TR~U~C~TIO ~N~s~.., AM ENOEO DATE 2Ail CARl A lEA CARl A2050 CARl ASEA CAR3 AlSO CARl AlSO CARl A1S0 ~AR23 A9SO FAR23 A18SO FAR23 A lEA CARl A19SO FAR23 A25SO FAR23 AI 1WE FAR23 AI 1WE FAR23 AI1WE FAR2l 3A18 CARl A00007SE FAR2J ASEU FAR21 A9EU ~AA21 A9EU ~AR21 A!leU FAR21 A10EU CARl A86EU FAA23 A.-593 BUL7A A-1~ CARl A51EU CAR3 A51EU CARl A1750 FAR23 NUMBER REVISION NUMBER RE-VISION 02·1 1·2003 02-tt-'2003 02-11 -2003 02·11·2003 None .........,. None .....02-lt-2003 ....,. 10·20.2010 1!>-20-2010 10.20-2010 10.20-2010 02·11·2003 10.16-1097 ... AIRCRAFT MAKE 68 SllNSON .......(_ 10 TA'f't.ORCRNT 71 THOMPSC»> (NiiWOfl. /tii:IMtAit~tt~CJMJ 72 TI«USH AIRCRAFT, INI';. IA1"NC<q/ ,_.c:o...._, 73 nGER ARc:RAFl 14T'OY1V< 7$\Jfii\'Mt~f (A/on £too. Fomey ltlt:IOney) 1-1 .... AIRCRAFT MAKE 76 VAAGA 71 WSK· "PZL·Mift.JEC'" OBR 78 ZEMAIR AIRCRAFT MODEL MS 1108 MS 88! lot$ 492AotSO, MS 112E-t50 YS893A MS 89lE US 894A.- MS ~E R~ltye 1008 A..,. I!IOST Ralye 150T Rlllye 23M;,~ 236E SHurw..t OC.tA QC.tl 1$_ FHI, f21. F2tA. F21 8 F22. F22A. F229 F22C A ec acs. 8C-6s, BCS-6s 8Ct2-$5 8CSt2-65 BC12..Q 8CS12.0 ICU:-Dt. IC:$12-0t 8Ct20-M 9CS120-85,8C12D+M SC$120-A-85 IF 8f$.8f-t0,8FI-e0 BF45.8FS-e. Bf 12-8$ BL Bt.S, Bl..-65 Bl$.$5, 81.1 2.$5, Bl$12-65 DCe5, DF..&S 01.--6$ DC046 N...-.ot~,N8'n01'1 A,B.C. O E .F . G H L-17A ~·178 L• I7C 800&20, s.2R S2R-TS4 S2R-T1$_ S2R· R3S. SZR·T11, S2R·T65 S2AHG-TI$ S2R·RI)e(l, S2R-Rt820 S2A-T45, 52R..c& S2R.Q10 S2ft..G$.~G.T34 S2R-GI. S2R· ,... 800$.20 S2R S2R·T3<t, ~-T115, S2A- Tt \. S2R·R3S S2R.R134() S>A $.28 S4C JI00.$2C see- Gu.f.stn!lam Atl:wlc:an SN A"***' at.,..., 10$ t~t 101-2 101-3 1C&S v.n 1.-6. L·58 1.·5C. 1.6-0 L5-E u..l· 1, L.$-0 1QA.. 109 415-C 41 $-CO 415-0 E.G '·'·'·1AA-2.A2-A. M-1 0 lm-7$ AIRCRAFT MOOEL SH A~Jf}USU~ir InC PZI. M2003 CH2000 ORIGINAL ISSU£ OAT£ Men:ll3 1, 1~ INSTALLATION ORIGINAL CERTFtCATIOH FAA SEALED DRAWINGS IN$TRUCTlONS AML TC BASIS FOA ---------~~~:2:.~- AMI!NOt!O NUMBER ALTERATIOH ~R REVI.SION HUMBP A:fVISION DATE 7AI4 7A 14 7A14 ....'lte IA9 M43 ,_ A- ...... -~ ....700 A-7'"' A-782 ...7112 AASoN MSIV "'""l<lSW w >A7 A.-787 A-m ,..,,. A-73$ A-718 A-187 A-709 ORIGINAl TC I NUMBER AMEU TASCH CNIIO CNIIO CARlO CAll <A CN13 BIA.1A CNI4 CAll< CAll< CAR< CAR<A CNI<A CARJ CAR3 CARB CN18 CN18 CNI3 CAR 1 tO(el(t) CAR 1 tO(e)(t) CN13 CNI<A CAA<A CAR <A CAR <A CAR3 CAR <A CE.RnFICAOON F AA S EALED 0 AAW1NOS BASIS FOR ALTERATION NU M8~ 1 R!.VISION FAR21 FAR21 10.20-2010 10.20-2010 10-2'0-2010 ......10.16--t etl 02· 11·2003 02·11·2003 02·11·2003 02·11·2003 02·11 ·2003 02· 1·2003 02·11·200) 02-11--200) 10.21).2010 -· 1Q.20.2010 11).20.2010 10-20-2010 10.20-2010 11).-20-2010 10.2'0-2010 02·11·2003 02-11·200) 1~16-1 997 02·11-2003 CXMt~003 02·11-2003 <X2·1t·2003 0:2-11~003 <X2·11·2003 ORIGINAl. I SSUE DATE : March 31, 1994 INSTALLATION INSTRUCTIONS NUMB<R REVISION AML AMENDED DATE 02 ·1 1·2003 0'2·11·2003 10·16-1997 FAA A PPROVED: AMENDED: April20. 1994: October 17 1994· October 16 1997· July 19 2002· February 11 2003· October 20. 2010 REI SSUED: