P68 SERIES SERVICE INSTRUCTION

Transcription

1 vulcanair spa via g. pascoli, casoria (na) italia Tel Fax info@vulcanair.com P68 SERIES SERVICE INSTRUCTION No. 61 Rev. 1 SUBJECT: NEW EGT INDICATOR SYSTEM INDICATOR P/N NOR C (ALCOR P/N 46198) PROBE P/N NOR B (ALCOR P/N 86255) The purpose of Rev.1 to this Service Instruction is to eliminate the process of revising the P68, P68B, P68R Flight Manuals. Therefore the Equipment List of the afore mentioned Flight Manuals will be manually updated as laid out in instruction 20 of paragraph GENERAL 1.1 AIRCRAFT AFFECTED P68 P68B P68R P68 OBSERVER P68C and P68 OBSERVER 2 up to S/N 400 inclusive 1.2 PURPOSE The purpose of this Service Instruction is to provide the installation procedure for the replacement of previously installed EGT Indicator Systems with the new Indicator P/N OR C (ALCOR P/N 46198) and relative Probe P/N NOR (ALCOR P/N 86255), as supplied with kit SI DESCRIPTION The new EGT Indicator is interchangeable with previous systems and installation does not require any mechanical changes. Correct installation instructions are reported herein. First issue : Page. 1 of 7

2 1. GENERAL (Cont.) 1.4 MANHOURS Application time for this Service Instruction is estimated as 12 man-hours, including the time necessary to access the components and return the aircraft to an airworthy condition. 1.5 SPECIAL TOOLS No special tools are required 1.6 VARIATIONS IN WEIGHT AND BALANCE Negligible. 1.7 ELECTRICAL SYSTEM LOAD Not Applicable. 1.8 REFERENCE DOCUMENTS ALCOR Instruction Sheets (included with each component): EGT Indicator Installation P/N (Latest Revision) Probe Installation P/N (Latest Revision) Lead Wire Installation P/N (Latest Revision) 1.9 PUBLICATIONS AFFECTED Flight Manual (only for P68, P68B and P68R aircraft) Parts Catalogue 1.10 MODIFICATION TO BE CARRIED OUT BY: An authorised Maintenance Facility certified to carry out work to the required level. 2. WORK PROCEDURE Referring to Figure 1, install Modification Kit SI61 in accordance with the following instructions: 1. Position all electrical switches to OFF and disconnect the battery cables; 2. Remove lateral engine cowlings; 3. Remove the inspection covers on the internal leading edge of the wing; 4. Disconnect and remove the existing EGT Probe from the wing wiring harness; 5. Install the new Probe P/N NOR B (ALCOR P/N 86255) onto the N 4 cylinder exhaust pipe as per the original installation, and torque the retaining clip to inch pounds, as per Instruction Sheet ALCOR P/N (Refer to Fig. 1); Excessive torque values may reduce the service life of the retaining clip on the probe. 6. Repeat steps 2 through 5 for the second engine; First Issue : Page. 2 of 7

3 2. WORK PROCEDURE (Cont.) 7. To access the rear of the instrument panel on the P68, P68B, P68R and P68C aircraft, remove inspection panels between frame numbers 1 and 2 on the nose of the aircraft. For P68 Observer aircraft, remove the instrument panel cover. 8. Remove the existing EGT Indicator and disconnect cables; If the EGT Indicator installed is the electrically operated one P/N (NOR ) manufactured by B & D Instruments, refer to Figure 2 and carry out the following additional steps: a. Tag the +28 VDC wire assigned to connector pin A ; b. Tag the earthing wire assigned to connector pin C ; c. Remove the MS3106A-14S-5S connector from the wiring; d. Remove the previously tagged earthing wire; e. Insulate the previously tagged +28 VDC wire, and indelibly mark it for future identification. Roll up the wire and anchor it to a suitable part of the aircraft structure (Particular care should be taken in the insulation and identification of this wire since the +28VDC supply runs through it). 9. Access the EGT Indicator wire by following the cable run and removing relative inspection and/or cabin panels. Disconnect and remove wiring from the existing EGT Indicator System; 10. Install new wiring in the cable run and use the existing cable ties or supports. The new wiring consists of: N 2 ALCOR Cables P/N 42551" for the wing ; N 2 ALCOR Cables P/N for the fuselage; 11. Connect and secure the wing wire to the fuselage wire as indicated in Figure 3; 12. Before installing the insulation sleeve included in the kit to the wiring, connect the new Probes to the new wiring using the screws, lockwashers and nuts also included in the kit. Install the insulation sleeve over the connections and anchor the sleeve in place with ties strap. 13. Referring to Figure 3 for correct instructions, connect the new Indicator to the new wiring; 14. Install the new EGT Indicator as per the original installation; 15. Reconnect battery cables; 16. Prepare aircraft for an engine test; 17. Carry out an engine run on both engines at max RPM and referring to the table below, verify that the EGT Indicator functions correctly : Parameter Maximum RPM Manifold Pressure (I.S.A. s.l.) Fuel Flow Oil Temperature Oil Pressure Cylinder Head Temperature (CHT) Exhaust Gas Temperature (EGT) Nominal Value 2680 RPM Hg (I.S.A. s.l.) gal/hr 245 F Max PSI (generally 85 psi) 475 F Max 700 C Max First Issue : Page. 3 of 7

4 2. WORK PROCEDURE (Cont.) If there is no indication on the instrument, carry out system TROUBLESHOOTING as per the latest revision of the ALCOR Instruction Sheet P/N supplied with the instrument. 18. Shut down engines; 19. Reinstall engine cowlings and all previously removed inspection panels and/or internal cabin panels; 20. Update the Equipment List of the a/c Flight Manual manually, inserting the new component installation according to the following tables (P68, P68B and P68R aircraft only). P68 Item Dual EGT Indicator Per Vulcanair Drwg NOR Weight (Lbs) Arm (inches) P68B e P68R Item Dual EGT Indicator Per Vulcanair Drwg NOR Weight (Lbs) Arm (inches) MATERIALS REQUIRED FOR THE MODIFICATION Kit SI61 Item P/N Description Qty 1 NOR C EGT Indicator ( ALCOR P/N 46198) 1 2 NOR B EGT Probe ( ALCOR P/N 86255) 2 3 ALCOR Wing wiring 2 4 ALCOR Fuselage wiring 2 First Issue : Page. 4 of 7

5 NEW EGT INDICATING SYSTEM BLOCK DIAGRAM Fig. 1 First Issue : Page. 5 of 7

6 PRE-MODIFICATION EGT INDICATOR SYSTEM DIAGRAM P/N NOR (B&D P/N ) Fig. 2 First Issue : Page. 6 of 7

7 CORRECT WIRING CONNECTION INFORMATION Fig. 3 First Issue : Page. 7 of 7