CIRRUSservicecenters.cirrusdesign.com/tech_pubs/SR2X/pdf/SB/SR2X...CIRRUS SERVICE BULLETIN MODEL SR2X SERIES SB2X-95-24R1 Page 2 See Effectivity Section, Page 1 EFFECTIVITY: 06 Nov

C I R R U S SR2X Service Bulletin

SB2X-95-24R1Number:

SNS SUBJECT: 95-00 SPECIAL PURPOSE EQUIPMENT - CAPS Rocket Shelf Ground Wire

10 Oct 2017Issued:06 Nov 2017Revised:

1. COMPLIANCE

Mandatory: Cirrus Aircraft considers this Service Bulletin to be MANDATORY. Accomplish this Service Bulletin at next annual inspection. Compliance time begins upon receipt of this Service Bulletin.

This bulletin was revised to remove accomplishment restrictions, update affected publications, correct a specification number, and clarify ground wire routing.

2. EFFECTIVITY

SR20 Serials 20-1005 thru 20-1267 after SB2X-95-20, 20-1268 thru 20-1422 after SB2X-95-17, 20-1423 & subs w/o Perspective after SB2X-95-18, 20-1907 thru 20-2227 w/ Perspective after SB2X-95-19, 20-2228 thru 20-2368.

SR22 Serials 22-0002 thru 22-0820 after SB2X-95-17, 22-0821 & subs w/o Perspective after SB2X-95-18, 22-2487 thru 22-3914 w/ Perspective after SB2X-95-19, 22-3915 thru 22-4523.

SR22T Serials 22T-0001 thru 22T-0441 after SB2X-95-19, 22T-0442 thru 22T-1596.

3. APPROVAL

FAA approval has been obtained on all technical data in this Service Bulletin that affects type design.

For aircraft not operating under FAA requirements and regulatory oversight, it is the operator's responsibil-ity to ensure that installation of this Service Bulletin has been accepted by the local airworthiness authority.

4. PURPOSE

It has been discovered that aircraft with the CAPS electric ignition could possibly be vulnerable to inadver-tent activation due to certain highly abnormal electrostatic surge effects. An incident recently occurred on an unoccupied customer aircraft parked on the ramp during a lightning storm where an electrostatic surge caused by a proximate lightning strike activated the CAPS rocket and parachute deployment.

Based on Cirrus' investigation of this incident, the probability of the exact electrostatic conditions for an air-craft on the ground to experience an uncommanded CAPS deployment is extremely improbable. Neverthe-less, it has been determined that the addition of the rocket shelf ground wire will further mitigate against the rare possibility of an uncommanded CAPS deployment.

The inspection determined that this is a ground-based remote possibility only and not an in-flight risk.

5. DESCRIPTION

This Service Bulletin contains instructions to install the rocket shelf ground wire.

6. WARRANTY INFORMATION

For aircraft under warranty at the issue date of this Service Bulletin, Cirrus will cover all parts and labor costs for this Service Bulletin if the work is accomplished within the Compliance time period and the work is performed at an authorized Cirrus Service Center.

7. MANPOWER REQUIREMENTS

3.5 man-hours

SB2X-95-24R1Page 1See Effectivity Section, Page 1

EFFECTIVITY:

C I R R U S S E R V I C E B U L L E T I N M O D E L S R 2 X S E R I E S

8. OTHER PUBLICATIONS AFFECTED

SR20 Wiring Manual (p/n 12129-001, p/n 12129-002)SR20 Component Maintenance Manual (p/n 12128-001)SR22 / SR22T Wiring Manual (p/n 13775-001, p/n 13775-002)SR22 / SR22T Component Maintenance Manual (p/n 15994-001)

9. WEIGHT AND BALANCE

10. MATERIAL INFORMATION

The following parts are required to comply with this Service Bulletin. Parts can be obtained from an Autho-rized Cirrus Service Center or Parts Distributor.

Reference Kit 70572-001 or order the following parts.

11. ACCOMPLISHMENT INSTRUCTIONS

A. Acquire necessary tools, equipment, and supplies.

CAUTION: The airplane must be grounded to earth prior to performing any maintenance.

Use personal ESD precautions including wrist or ankle grounding strap to aircraft.

B. Attach static ground cable to engine tailpipe and suitable earth ground.

C. Remove CAPS handle access cover and install safety pin.

D. Remove key from ignition.

Component Weight Arm

Electrical Wiring Modifications 0.1 lb 116.0 inches

Item No. Description P/N or Spec. Supplier Quantity

1 Ground Wire Assembly 70572-101 Cirrus 1

2 Terminal Ring MS25036-103 Cirrus 1

3 Tape, Sheet, 20” × 9” 70572-102 Cirrus 1

Description P/N or Spec. Supplier Purpose

Static Ground Cable - Any Source Ground airplane.

Drop Cloth - Any Source Protect empennage from debris.

Vacuum - Any Source Remove debris.

Fish Tape, Nylon - Any Source Route ground wire.

Crimp Tool - Any Source Crimp terminal ring.

Heat Gun - Any Source Heat shrink sleeve.

Ohmmeter - Any Source Check continuity.

Petroleum Jelly VV-P-236 Any Source Prevent battery terminal corrosion.

Cable Ties MS3367-4-9 Any Source Secure ground wire.

Tape, 2-inch 051141-84802 3M Company Insulate CB7 access panel.

Utility Knife - Any Source Cut tape.


EFFECTIVITY:

06 Nov 2017


E. Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.

F. Pull BAT 2 circuit breakers (CB880 and CB881).

G. Near battery 2, disconnect battery 2 connector (J/P1169).

H. Disconnect battery 1 at both positive and negative terminals.

WARNING: All electrical circuits must be off, prior to disconnecting battery cables. Always remove the negative battery cable first, then the positive cable. Insulate cable ends and battery terminals to prevent accidental re-connection.

Remove all jewelry before servicing the battery. Metal objects may fuse to electri-cal connections and cause severe burns. Wear face shield and protective clothing when servicing battery and/or handling electrolyte. Neutralize electrolyte spills with a solution of baking soda and water, then rinse with clean water.

(1) Remove upper engine cowling. (Refer to AMM 71-10)

CAUTION: After battery disconnection, insulate cable ends and battery terminals to prevent accidental connection.

(2) Remove negative battery cable from battery terminal.(3) Remove positive battery cable from battery terminal.(4) Insulate cable ends and battery terminals.

I. SR20 Serials w/ CAPS battery: Disconnect CAPS battery at J/P2702 connectors.

J. Serials w/ Iridium Weather System: Remove Iridium GSR 56 mounting shelf. (Refer to AMM 34-50)

K. Remove crew and passenger seats. (Refer to AMM 25-10)

L. Remove RH mid console trim. (Refer to AMM 25-10)

M. Remove cabin floor covering. (Refer to AMM 25-10)

N. Remove BH 222 trim panel. (Refer to AMM 25-10)

O. Remove access panels CF1L, CF2L, CF3L, CF4L, CF5, CB6, and CB7. (Refer to AMM 06-00)

P. To prevent debris and components from falling into bottom of empennage, place catch cloth below CAPS compartment.

Q. Install ground wire (item 1) at rocket shelf. (See Figure 01)

(1) At rocket shelf, remove and retain indicated screw and washer. Discard existing safety wire.(2) Secure ground wire TR2712 to rocket shelf using existing washer and screw.

Note: For accessibility and time-saving gains, it is permissible to use safety cable instead of safety wire.

(3) Install safety wire to screws securing shelf assembly to rocket motor. (Refer to AMM 20-50)

WARNING: To ensure ground wire does not contact the battery 2 shelf, route ground wire as follows:

Serials w/ factory installation: Route aft of CAPS diagnostic wire harness upper length, downward along harness, and forward of lower harness bend. Use cable ties as required to maintain routing. (See Figure 02)

Serials after SB2X-95-17, SB2X-95-18, SB2X-95-19, or SB2X-95-20: Route aft of and along CAPS diagnostic wire harness. Use cable ties as required to maintain routing away from the battery 2 shelf. (See Figure 02)

(4) Route ground wire along with existing wiring exiting CAPS compartment.

R. Route ground wire (item 1). (See Figure 02)

(1) Route ground wire approximately as shown following the battery 2 harness and the engine mon-itoring harness forward of the J/P847 connectors. (Refer to WM 20-10)

(2) Secure ground wire to existing tie downs with cable ties.


EFFECTIVITY:

06 Nov 2017


S. Install ground wire (item 1) at RH mid console. (See Figure 03)

(1) At ground wire, slide heat shrink sleeve onto end of ground wire and crimp terminal ring (item 2) onto ground wire. (Refer to WM 20-10)

(2) Apply heat using a heat gun to heat shrink sleeve. (Refer to WM 20-10)(3) Label end of ground wire as “TR2713”.(4) Serials w/o Perspective or Perspective+: Secure ground wire (item 1).

(a) Acquire necessary tools, equipment, and supplies.

(b) At RH mid console, measure 2.5 inches (6.4 cm) forward from forward edge of console panel opening, and mark.

(c) Measure 2.8 inches (7.1 cm) down from upper edge of console panel and mark intersec-tion with previous mark.Note: If measured location for intersection conflicts with an existing installation,

contact Cirrus for disposition.(d) Using #7 drill bit, drill Ø 0.201±0.005 inch (5.105±0.127 mm) hole approximately at

marked intersection.(e) Deburr and solvent clean installation hole. (Refer to AMM 20-30)(f) Apply Alodine to installation hole.(g) Position and secure ground wire TR2713 to ground at console with bolt, washer, and nut.

(5) Serials w/ Perspective or Perspective+: Secure ground wire (item 1).(a) At RH mid console, remove nut, washer, and screw securing TR2050 to ground at console.(b) Position and secure ground wire TR2713 and TR2050 to ground at console with screw,

washer, and nut.

T. Check continuity between rocket shelf and aircraft ground.

(1) Position ohmmeter lead to rocket shelf and other lead to suitable aircraft ground (firewall or tailpipe).(2) If resistance from rocket shelf to aircraft ground is less than 2 ohms, the rocket shelf is ade-

quately grounded and no further steps are necessary.(3) If resistance from rocket shelf to aircraft ground is greater than 2 ohms, contact Cirrus for disposition.

U. Install tape onto access panel CB7. (See Figure 04)

Note: Overlap tape seams 0.5 inch (1.3 cm) minimum.

Ensure 2-inch tape is centered onto upper edge of CB7 access panel prior to wrap-over.

(1) Using 2-inch tape, center tape along entire upper edge of access panel CB7 so that tape ends extend 1 inch (2.54 cm) before and after edge.

Description P/N or Spec. Supplier Purpose

Permanent Marker - Any Source Mark installation hole.

Drill Bit, #7 0.201 inch Any Source Drill installation hole.

Deburring Tool - Any Source Deburr installation hole.

Cotton Cloth (clean, white, lint free)

- Any Source Clean installation hole.

Isopropyl Alcohol TT-I-735 Grade A or B Any Source Clean installation hole.

Touch-N-Prep Pen Alodine 1132 Henkel Protect from corrosion.

Bolt AN3-3A Any Source Secure ground wire.

Washer NAS1149D0332J Any Source Secure ground wire.

Nut MS21044N3 Any Source Secure ground wire.


EFFECTIVITY:

06 Nov 2017


(2) Fold tape over edge and adhere to panel and itself at ends.(3) Serials 20-1005 thru 20-1422, 22-0002 thru 22-0820: On aft side of access panel CB7, install

tape sheet (item 3) over entire surface.(4) Serials 20-1423 thru 20-2368, 22-0821 thru 22-4523, 22T-0001 thru 22T-1596: On aft LH side of

access panel CB7, install tape sheet (item 3) from upper to lower edge of panel, extending 9 inches (23 cm) minimum from LH edge.

Note: Do not trim overlapped 2-inch tape ends installed at upper edge of access panel.

(5) Use utility knife to trim any excess from lower portion of tape sheet (item 3).

V. SR20 Serials w/ CAPS battery: Perform Inspection/Check - Cirrus Airplane Parachute System. (Refer to AMM 95-00)

Note: SR20 Serials w/ CAPS battery: It is not necessary to perform Electric Ignition Checkout Procedure, as defined in AMM 95-00.

W. Remove drop cloth from CAPS compartment.

X. Using vacuum cleaner, remove all debris from baggage floor, CAPS compartment, and fuselage belly below the CAPS compartment.

Y. Visually inspect CAPS compartment for security, leaks, loose or missing hardware, moisture, and gen-eral condition.

Z. Install access panels CF1L, CF2L, CF3L, CF4L, CF5, CB6, and CB7. (Refer to AMM 06-00)

AA. Install BH 222 trim panel. (Refer to AMM 25-10)

AB. Install cabin floor covering. (Refer to AMM 25-10)

AC. Install RH mid console trim. (Refer to AMM 25-10)

AD. Install crew and passenger seats. (Refer to AMM 25-10)

AE. Serials w/ Iridium Weather System: Install Iridium GSR 56 mounting shelf. (Refer to AMM 34-50)

AF. SR20 Serials w/ CAPS battery: Connect CAPS battery at J/P2702 connectors.

AG.Connect battery 1 at both positive and negative terminals.

CAUTION: Connecting cables in reverse (positive to negative and negative to positive) can cause serious damage to the electrical system. Connect the negative cable last.

(1) Connect positive battery cable to positive terminal.(2) Connect negative battery cable to negative terminal.(3) To prevent corrosion, apply petroleum jelly to battery terminals.(4) Install upper engine cowling. (Refer to AMM 71-10)

AH.Near battery 2, connect battery 2 connector (J/P1169).

AI. Reset BAT 2 circuit breakers (CB880 and CB881).

AJ. Remove ground from aircraft at engine tailpipe.

AK. Using recorded aircraft weight, calculate and record new weight and center of gravity values on the Weight & Balance Record of the POH.

AL. Complete airplane records by noting compliance with SB2X-95-24R1 in Aircraft Logbook.

To submit a Technical Publication change request, visit:http://servicecenters.cirrusdesign.com/tech_pubs/SR2X/serviceloopform.aspor contact us by email at [email protected].


EFFECTIVITY:

06 Nov 2017

http://servicecenters.cirrusdesign.com/tech_pubs/SR2X/serviceloopform.asp

mailto:[email protected]


Figure 01CAPS Rocket Shelf Ground Wire Connection

SR2_SB95_1620A1

NOTE

Route ground wire along with existing wiring exiting CAPS compartment.

ADETAIL LEGEND 1 . Screw 2 . Washer 3 . Braided Sleeving 4. TR2712

BULKHEAD 222(REF)

3

CAPS ROCKET SHELF(REF)

1

2

4

A

SHIELD(REF)

CAPSCOMPARTMENT

(REF)

3

SHIELD(REF)

Serials after SB2X-95-17, SB2X-95-18, SB2X-95-19, or SB2X-95-20.

1

1

1

CAPS IGNITION HARNESS

(REF)

1

CAPS IGNITION HARNESS

(REF)

CAPSCOMPARTMENT

(REF)


EFFECTIVITY:

06 Nov 2017


Figure 02CAPS Ground Wire Routing (1 of 3)

AB

C

LEGEND 1 . Ground Wire

TR2713J/P847

CONNECTOR (REF)

BATTERY 2 HARNESS

(REF)ENGINE

MONITORINGHARNESS

(REF)BULKHEAD 222(REF)

BATTERY 2 (REF)

SPAR TUNNEL(REF)

SR2_SB95_1619B

1

NOTE

Route ground wire approximately as shown following the battery 2harness and the engine monitoring harness forward of the J/P847 connectors.

1

TR2713J/P847

CONNECTOR (REF)

BATTERY 2 HARNESS

(REF)

A

ENGINE MONITORING

HARNESS (REF)

SPAR TUNNEL(REF)

AFT FLOOR(REF)

BULKHEAD 222(REF)

BATTERY 2 (REF)

CAPS COMPARTMENT

(REF)

BA

A

AB

C

G

1

1

1

B


EFFECTIVITY:

06 Nov 2017



BATTERY 2SHELF(REF)

SECTION A

Due to aircraft configurations, the battery 2 shelf may vary from illustration.

NOTE

1

1

1

To ensure ground wire does not contact the battery 2 shelf, route ground wire aft of CAPS diagnostic wire harness upper length, downward along harness, and forward of lower harness bend. Use cable ties as required to maintain routing.

2

2

2

A1

A1

VIEW A1

1

SR2_SB95_1624A

CAPS DIAGNOSTIC

WIRE HARNESS(REF)

BULKHEAD 222(REF)

CAPS ACTIVATION

CABLE(REF)

ANTENNAIF INSTALLED

(REF)

1

BATTERY 2SHELF(REF)

BULKHEAD 222

(REF)

FUSELAGE(REF)


EFFECTIVITY:

06 Nov 2017



BATTERY 2SHELF(REF)

SECTION B

Due to aircraft configurations, the battery 2 shelf may vary from illustration.

NOTE

1

1

B1

B1

VIEW B1

1

To ensure ground wire does not contact the battery 2 shelf, route ground wire aft of and along CAPS diagnostic wire harness. Use cable ties as required to maintain routing away from the battery 2 shelf.

2

CAPS DIAGNOSTIC

WIRE HARNESS(REF)

2

1

Serials after SB2X-95-17, SB2X-95-18, SB2X-95-19, or SB2X-95-20.

SR2_SB95_1626

BULKHEAD 222(REF)

CAPS ACTIVATION

CABLE(REF)

1

BATTERY 2SHELF(REF)

BULKHEAD 222

(REF)

FUSELAGE(REF)


EFFECTIVITY:

06 Nov 2017


Figure 03RH Mid Console Ground Wire Connection - Serials w/o Perspective or Perspective+ (1 of 2)

LEGEND 1 . Bolt 2 . TR2713 3 . Washer 4. Nut

SIDE PANELRIGHT MID CONSOLE

(REF)

1

SR2_SB95_1623

2

43

TO CAPS ROCKET SHELF

(REF)

BA

Serials w/o Perspective or Perspective+ Avionics.

2.5 inches(6.4 cm)

2.8 inches(7.1 cm)


(REF)


EFFECTIVITY:

06 Nov 2017


Figure 03RH Mid Console Ground Wire Connection - Serials w/ Perspective or Perspective+ (2 of 2)

LEGEND 1 . Screw 2 . TR2713 3 . Washer 4. Nut


(REF)

1

SR2_SB95_1621

2

43

TO CAPS ROCKET SHELF

(REF)

TR2050(REF)

TVS(REF)

Serials w/ Perspective or Perspective+ Avionics.

BDETAIL


EFFECTIVITY:

06 Nov 2017


Figure 04Tape Installation on Access Panel CB7

52

9.0 inches(23.0 cm)

3 4

1.0 inch(2.5 cm)

1.0 inch(2.5 cm)

TAPE SHEET

(REF)

1

1.0 inch(2.5 cm)

1

1

ROCKET FACINGSURFACE

(REF)

ADETAIL

1

NOTE

Ensure tape wraps over upper edge of CB7 access panel.

2 Overlap tape seams 0.5 inch (1.3 cm) minimum.

Serials 20-1005 thru 20-1422, 22-0002 thru 22-0820 (not shown): On aft side of access panel CB7, install sheet over entire surface.

Serials 20-1423 thru 20-2368, 22-0821 thru 22-4523, 22T-0001 thru 22-1596 (as shown): On aft LH side of access panel CB7, install sheet from upper to lower edge of panel, extending 9.0 inches (23.0 cm) minimum from LH edge.

4

3

5 Use utility knife to trim any excess from lower portion of tape sheet. Do not trim overlapped 2-inch tape ends installed at upper edge of access panel. SR2_SB95_1622B

LEGEND 1. Access Panel CB7


EFFECTIVITY:

06 Nov 2017

Documents

CIRRUSservicecenters.cirrusdesign.com/tech_pubs/SR2X/pdf/SB/SR2X...CIRRUS SERVICE BULLETIN MODEL SR2X SERIES SB2X-95-24R1 Page 2 See Effectivity Section, Page 1 EFFECTIVITY: 06 Nov