ECLIPSE Service Bulletin

connector (27A03P01) to Flap Position Potentiometer electrical connector (27R01P01). NOTE: Optional step: Wrap the unsleeved wire in teflon tape prior to sleeving through the overbraid. 2. If wire P/N M27500-22SD3T23 can remain in service, cut to fit overbraid sleeving P/N 1233/2 at least 150 inches and sleeve existing wire through overbraid. NOTE: Optional step: Wrap the unsleeved wire in teflon tape prior to sleeving through the overbraid. ECLIPSE Service Bulletin Issued: 24 March 2016 – Rev A SB 500-57-012 © 2016 ECLIPSE AEROSPACE INC. Page 5 of 13 (c) Tie new wire & existing bundle together to existing tie mounts (refer to Figure 1) and no more than 6 inches apart to secure between the attach points using tie straps P/N MS3367-()-0, PLT()-76. (d) At the inboard flap actuator (27A03P01; Figure 2), the overbraid band is removed and the overbraid is pulled back to allow access to the connector. Refer to Wiring Repair Manual, “Band Removal”. One of three methods will be used to re-terminate the overbraid: Method 1 Reattach overbraid to backshell and reband if practical. • Method 1 will be used if the existing overbraid at the inboard flap actuator (27A03P01) is sufficiently long enough to re-band after the new wiring is added. This is the preferred method. Method 2 Wiring Repair Manual, “Shield Support Banding Ring”. • Method 2 requires adding overbraid sleeving P/N 1233/2. Method 3 Wiring Repair Manual, “Unaided Overlap”. • Method 3 requires adding overbraid sleeving P/N 1233/2. (e) Trim to finish length, and terminate at inboard flap actuator connector 27A03P01 using contact P/N M39029/56-351 as follows: Contact / Conductor • P / FCI0220-22 BL • Y / FCI0220-22 OR • X / FCI0220-22 WH • Backshell / FCI0220-22 SH (shield) If overbraid termination method 1 or 2 is used, continue at step (f). If method 3 is used, either step (f) or step (g) can apply. (f) No closer than 1 inch to the backshell, route the wire through the overbraid. This is accomplished using an awl or similar tool to pierce a hole through the overbraid so the wire can be run through it. Attach overbraid to 27A03P01 using banding material PNs A10088, A10089, A31189 or A31089 or equivalent. Continue at step 6. (g) Skip this step if overbraid termination method 1 or 2 is used (step (e)). The wiring may route between the existing overbraid and the added overbraid sleeving before applying the tie straps PN MS3367-()-0, PLT()-76. Attach overbraid to 27A03P01 using banding material PNs A10088, A10089, A31189 or A31089 or equivalent. (h) If overbraid termination method 2 or 3 was used, insure an adequate electrical bond between the two sections of overbraid (no greater than 2.5 mili Ohm). ECLIPSE Service Bulletin Issued: 24 March 2016 – Rev A SB 500-57-012 © 2016 ECLIPSE AEROSPACE INC. Page 6 of 13 NOTE: Instructions are similar for the right side as compared to the left side with exception of the wire numbers. (3) Electrical Harness Rework to Add Overbraid, RH Parts Required: [1] If needed. [2] Part number dependent upon which overbraiding method is used and size desired. (i) Trim to finish length and terminate at flap position potentiometer connector 27R01P01 (Figure 3) using contact P/N 809-002 as follows: Contact / Conductor • B / FCI0220-22 BL • C / FCI0220-22 OR • A / FCI0220-22 WH • Backshell / FCI0220-22 SH (shield) using metal banding material PNs A10088, A10089, A31189 or A31089 or equivalent. NOTE: Finished length is ~143 inches. (j) Apply a 2 inch piece of heat shrink tubing (TAT-125-1/2) over the backshell and metal overbraiding of connector and shrink in place (Figure 4). (k) Slide a second 2 inch piece of heat shrink tubing (tat-125-1/2) past connector (Figure 4). (l) Connect the electrical connector and torque jam nut (15) to 35-45 lbf.in (4.0-5.1 Nm). (m) Position second piece of heat shrink tubing (TAT-125-1/2) over complete connector (19, Figure 4) and shrink in place. (n) Safety the connector (20, Figure 4) to angle bracket with new .020 dia. lockwire (MS20995C20). (o) Seal exposed area of connector (Figure 4) with PRC-Desoto epoxy sealant (PR-2001). (p) Re-dress harness. Refer to Wiring Repair Manual. 39-120497 Electrical Harness Rework Part Number Description Qty M39029/56-351[1] 22 Gauge Socket D38999 3 800-008-06M5-3SN[1] Connector, Series 80 Plug (27R01P01) 1 809-002[1] 22 Gauge Series 80 Socket 3 M27500-22SD3T23[1] 22 Gauge Twisted Triple Wire 13 ft. MS3367-()-0, PLT()-76 Tie Straps (allowed in SWAMP areas) As Required M85049/93-()[1][2] Split Support Ring As Required A10088, A10089, A31189, A31089 or equivalent [2] Metal Banding Material As Required 1233/2[2] Overbraid Sleeving (or alternate overbraid sleeving meeting QQ-W-343E or QQ-B- 575B specifications) As Required ECLIPSE Service Bulletin Issued: 24 March 2016 – Rev A SB 500-57-012 © 2016 ECLIPSE AEROSPACE INC. Page 7 of 13 Refer to Wiring Diagram Manual 27-50-10 for wiring diagram: Sign Off (a) Cut existing tie straps holding existing bundle. (b) Remove the unsleeved wire P/N M27500-22SD3T23 from the 39-120497 wire harness bundle. 1. If the wire is damaged, discard and cut to fit wire P/N M27500-22SD3T23 and overbraid sleeving P/N 1233/2 at least 150 inches, thread wire through overbraid, label FCI0230-22 before routing with existing bundle from inboard flap actuator electrical connector (27A03P01) to Flap Position Potentiometer electrical connector (27R01P01). NOTE: Optional step: Wrap the unsleeved wire in teflon tape prior to sleeving through the overbraid. 2. If wire P/N M27500-22SD3T23 can remain in service, cut to fit overbraid sleeving P/N 1233/2 at least 150 inches and sleeve existing wire through overbraid. NOTE: Optional step: Wrap the unsleeved wire in teflon tape prior to sleeving through the overbraid. (c) Tie new wire & existing bundle together to existing tie mounts (refer to Figure 1) and no more than 6 inches apart to secure between the attach points using tie straps P/N MS3367-()-0, PLT()-76. (d) At the inboard flap actuator (27A04P01), the overbraid band is removed and the overbraid is pulled back to allow access to the connector. Refer to Wiring Repair Manual, “Band Removal”. One of three methods will be used to re-terminate the overbraid: Method 1 Reattach overbraid to backshell and reband if practical. • Method 1 will be used if the existing overbraid at the inboard flap actuator (27A03P01) is sufficiently long enough to re-band after the new wiring is added. This is the preferred method. Method 2 Wiring Repair Manual, “Shield Support Banding Ring”. • Method 2 requires adding overbraid sleeving P/N 1233/2. Method 3 Wiring Repair Manual, “Unaided Overlap”. • Method 3 requires adding overbraid sleeving P/N 1233/2. (e) Trim to finish length, and terminate at inboard flap actuator connector 27A04P01 using contact P/N M39029/56-351 as follows: Contact / Conductor • P / FCI0230-22 BL • Y / FCI0230-22 OR • X / FCI0230-22 WH • Backshell / FCI0230-22 SH (shield) If overbraid termination method 1 or 2 is used, continue at step (f). If method 3 is used, either step (f) or step (g) can apply. ECLIPSE Service Bulletin Issued: 24 March 2016 – Rev A SB 500-57-012 © 2016 ECLIPSE AEROSPACE INC. Page 8 of 13 (f) No closer than 1 inch to the backshell, route the wire through the overbraid. This is accomplished using an awl or similar tool to pierce a hole through the overbraid so the wire can be run through it. Attach overbraid to 27A03P01 using banding material PNs A10088, A10089, A31189 or A31089 or equivalent. Continue at step 6. (g) Skip this step if overbraid termination method 1 or 2 is used (step (e)). The wiring may route between the existing overbraid and the added overbraid sleeving before applying the tie straps PN MS3367-()-0, PLT()-76. Attach overbraid to 27A03P01 using banding material PNs A10088, A10089, A31189 or A31089 or equivalent. (h) If overbraid termination method 2 or 3 was used, insure an adequate electrical bond between the two sections of overbraid (no greater than 2.5 mili Ohm). (i) Trim to finish length and terminate at flap position potentiometer connector 27R01P01 (Figure 3) using contact P/N 809-002 as follows: Contact / Conductor • B / FCI0230-22 BL • C / FCI0230-22 OR • A / FCI0230-22 WH • Backshell / FCI0230-22 SH (shield) using metal banding material PNs A10088, A10089, A31189 or A31089 or equivalent. NOTE: Finished length is ~143 inches. (j) Apply a 2 inch piece of heat shrink tubing (TAT-125-1/2) over the backshell and metal overbraiding of connector and shrink in place (Figure 4). (k) Slide a second 2 inch piece of heat shrink tubing (TAT-125-1/2) past connector (Figure 4). (l) Connect the electrical connector and torque jam nut (15) to 35-45 lbf.in (4.0-5.1 Nm). (m) Position second piece of heat shrink tubing (TAT-125-1/2) over complete connector (19, Figure 4) and shrink in place. (n) Safety the connector (20, Figure 4) to angle bracket with new .020 dia. lockwire (MS20995C20). (o) Seal exposed area of connector (Figure 4) with PRC-Desoto epoxy sealant (PR-2001). (p) Re-dress harness. Refer to Wiring Repair Manual. ECLIPSE Service Bulletin Issued: 24 March 2016 – Rev A SB 500-57-012 © 2016 ECLIPSE AEROSPACE INC. Page 9 of 13 Figure 1. Inboard Flap Actuator & Flap Position Potentiometer Figure 2. Inboard Flap Actuator 5111394A 27A03P01 27R01P01 ROUTE NEW WIRE WITH EXISTING BUNDLE 5111393A 27A03P01 ECLIPSE Service Bulletin Issued: 24 March 2016 – Rev A SB 500-57-012 © 2016 ECLIPSE AEROSPACE INC. Page 10 of 13 Figure 3. Flap Position Potentiometer Figure 4. Heat Shrink and Safety Connector B. Limitations and Procedures N/A C. Parts Disposition N/A 5111392A 27R01P01 ECLIPSE Service Bulletin Issued: 24 March 2016 – Rev A SB 500-57-012 © 2016 ECLIPSE AEROSPACE INC. Page 11 of 13 4. RECORD OF COMPLIANCE Upon completion of this Service Bulletin, make an appropriate maintenance-record entry specifying the Service Bulletin number. 5. NOTIFYING ECLIPSE AEROSPACE On completing this Service Bulletin, the operator/maintainer shall complete the attached Compliance Record and send it to Eclipse Aerospace via regular mail, fax, or e-mail. Mailing Address Eclipse Aerospace Incorporated ATTN: Service Engineering 2503 Clark Carr Loop SE Albuquerque, NM 87106 Fax 1-505-241-8802 E-mail sbcompliance@eclipse.aero ECLIPSE Service Bulletin Issued: 24 March 2016 – Rev A SB 500-57-012 © 2016 ECLIPSE AEROSPACE INC. Page 12 of 13 [Intentionally Blank Page] ECLIPSE Service Bulletin Issued: 24 March 2016 – Rev A SB 500-57-012 © 2016 ECLIPSE AEROSPACE INC. Page 13 of 13 SERVICE BULLETIN COMPLIANCE RECORD MODEL __________ AIRPLANE S/N ____________ REG. NO. __________ TOTAL TIME ______ (HOURS) OWNER NAME: _____________________________________________________________________ ADDRESS: _________________________________________________________________________ _________________________________________________________________________ TELEPHONE NO. (___) _________________________ FAX NO. (___) _________________________ COMPLIANCE WITH SB 500-57-012, Rev A Description of Work Performed (Inspection | Modification | Repair | Option Installation | Defect or Damage Found, if applicable) ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ ___________________________________________________________________________________________ DATE ______________ WORK PERFORMED BY _________________________________________ (PRINTED) _________________________________________ (SIGNATURE) COMPANY _________________________________________________________________________________ ADDRESS _________________________________________________________________________________ __________________________________________________________________________________ TELEPHONE ________________________ FAX ________________________