Diamond Aircraft 3260 Manuel de référence

SERVICE BULLETIN

Service Bulletin No.: D42L-32-01 Rev 0

Title: CHECK GEAR Annunciation

Date Issued: 09 January 2013

Page: 1 of 8

1. ATA Code: 3260

2. Effectivity: DA42 L360 aircraft with STC SA09-54 installed and the Garmin software

installed that is listed below:

•v1054.01, or

•v1054.02, or

•v1054.03, via Service Bulletin D42L-34-04 Rev 1 (not factory

installed)

3. General: Implementation of this Service Bulletin will provide an amber ‘CHECK

GEAR’ annunciation on the PFD in the event:

•The landing gear is in the retracted position while the flaps

move into the LDG position, or

•The landing gear is in the retracted position while either

throttle lever is moved in a position forward of IDLE, but below

approximately 14 inches of manifold pressure.

4. Reason: To enhance gear position annunciation during the landing phase

assisting with pilot awareness.

5. Compliance: Compliance with this Service Bulletin is Recommended.

6. Approval: Engineering data referenced or contained in this Service Bulletin is

approved as part of the supplemental type design.

7. Labor: Approximately 3 hours will be required to accomplish this Service

Bulletin.

This estimate is for direct labor performed by a technician and it does not include setup,

planning, familiarization, cure time, part fabrication or tool acquisition.

8. Material: Part Number Description Qty

M22759/16-22-9 Wire, 22 AWG, (length: 6100 mm) 1

*3PS-125-2W Label

*Identified as: 31320C22 2

31320B22 2

31320A22 2

920-1/8 BKWH Expando, 1/8” (length: 5100 mm) 1

66105-4 Contact, socket 2

66103-4 Contact, pin 2

36151 Ring Terminal 1

MS3367-5-9 Cable Tie 10

336-00021-00 Contact, pin, high density 1

The above material may be ordered as kit: DA42L-32-01

SERVICE BULLETIN

Service Bulletin No.: D42L-32-01 Rev 0

Title: CHECK GEAR Annunciation

Date Issued: 09 January 2013

Page: 2 of 8

NOTE: A Garmin configuration patch (006-B1669-00) will be required for

this installation. The patch can be obtained via the Dealer

Resource Center portion of the Garmin website www.garmin.com.

9. Special Tools: Daniel Crimpers, Ring Terminal Crimpers

10. References: - DA42 Series Airplane Maintenance Manual, Document # 7.02.01

- DA42 L360 Aircraft Maintenance Manual,

Supplement Document # D42L-AMM-001

- DA42 L360 Aircraft Flight Manual, Document # D42L-AFM-002.

11. Accomplishment Instructions:

11.1 Disconnect the aircraft battery in accordance with the DA42 Airplane

Maintenance Manual (AMM) # 7.02.01 Chapter 24-31.

11.2 Remove the instrument panel cover in accordance with the DA42 AMM

# 7.02.01 Chapter 25-10.

11.3 Remove the ‘Nacelle Cap ECU LH’ access panel. Reference DA42 AMM

# 7.02.01 Chapter 52-40 for panel location

11.4 Remove the pilot seat in accordance with the DA42 AMM # 7.02.01

Chapter 25-10.

11.5 Left Hand Nacelle Section:

11.5.1 Prepare a 3000 mm piece of 22 AWG wire and a 3000 mm piece of

expando with the labels 31320C22 installed, as shown in Figure 1:

SERVICE BULLETIN

Service Bulletin No.: D42L-32-01 Rev 0

Title: CHECK GEAR Annunciation

Date Issued: 09 January 2013

Page: 3 of 8

Figure 1: Nacelle Wire

11.5.2 Remove the GEA71 unit from the rack located in the left hand nacelle

compartment in accordance with the DA42 AMM #D42L-AMM-001

Chapter 31-40.

11.5.3 Remove the GEA71 connector (P702) from the connector backplate.

11.5.4 Insert wire 31320C22 into pin 25 of the P702 connector.

11.5.5 Install the GEA71 connector (P702) into the connector backplate.

11.5.6 Install the GEA71 unit into the rack in accordance with the DA42 AMM

#D42L-AMM-001 Chapter 31-40.

11.5.7 Route wire 31320C22 along the junction box assembly harness and

through the conduit to the left hand fuselage harness J2421 connector,

located under the pilot seat.

11.5.8 Trim wire 31320C22 to the length required for installation into the P2421

connector.

NOTE: Make sure the wire code label is not trimmed off with the excess

wire.

11.5.9 Crimp contact (P/N: 66103-4) onto the end of wire 31320C22 and insert into

pin 52 of the P2421 connector.

SERVICE BULLETIN

Service Bulletin No.: D42L-32-01 Rev 0

Title: CHECK GEAR Annunciation

Date Issued: 09 January 2013

Page: 4 of 8

11.6 Fuselage Section:

11.6.1 Prepare a 2000 mm piece of 22 AWG wire and a 2000 mm piece of

expando with labels 31320B22 installed, as shown in Figure 2:

Figure 2: Fuselage Wire

11.6.2 Insert wire 31320B22 into socket 52 of the J2421 connector.

11.6.3 Route wire 31320B22 along the existing left hand fuselage harness to the

instrument panel P2402 connector.

11.6.4 Trim wire 31320B22 to the length required for installation into the P2402

connector.

NOTE: Make sure that the wire code label is not trimmed off with the

excess wire.

11.6.5 Crimp contact (P/N: 66103-4) onto the end of wire 31320B22 and insert into

the P2402 connector, pin 52.

SERVICE BULLETIN

Service Bulletin No.: D42L-32-01 Rev 0

Title: CHECK GEAR Annunciation

Date Issued: 09 January 2013

Page: 5 of 8

11.7 Instrument Panel Section:

11.7.1 Prepare a 1000 mm piece of 22 AWG wire with the labels 31320A22

installed, as shown in Figure 3:

Figure 3: Instrument Panel Wire

11.7.2 Insert wire 31320A22 into socket 52 of the J2402 connector.

11.7.3 Route wire 31320A22 along the existing instrument panel harness to the

landing gear sonalert, as shown in Figure 4.

11.7.4 Trim wire 31320A22 to the appropriate length for the installation.

NOTE: Make sure that the wire code label is not trimmed off with the

excess wire.

SERVICE BULLETIN

Service Bulletin No.: D42L-32-01 Rev 0

Title: CHECK GEAR Annunciation

Date Issued: 09 January 2013

Page: 6 of 8

Figure 4: Installation of Instrument Panel Wire

11.7.5 Cut the ring terminal off of the existing instrument panel harness wire

32036A22, located at the landing gear sonalert, negative terminal.

11.7.6 Crimp together wires 31320A22 and 32036A22 with supplied ring terminal

(P/N: 36151).

11.7.7 Fasten the crimped wires to the negative terminal of the landing gear

sonalert.

11.7.8 Secure wire 31320A22 to the existing instrument panel harness using the

supplied cable ties (P/N: MS3367-5-9).

11.8 Remove all tools, equipment, and unwanted materials from the work area.

11.9 Ensure all the connectors are plugged in and properly seated.

11.10 Connect the aircraft battery in accordance with the DA42 AMM # 7.02.01

Chapter 24-31.

SERVICE BULLETIN

Service Bulletin No.: D42L-32-01 Rev 0

Title: CHECK GEAR Annunciation

Date Issued: 09 January 2013

Page: 7 of 8

11.11 Obtain the ‘Check Gear’ Patch (006-B1669-00) via the Dealer Resource Center

portion of the Garmin website www.garmin.com.

NOTE: Aircraft with Garmin software v1054.03 installed via Service Bulletin

D42L-32-01 do not require ‘Check Gear’ patch to be installed. Proceed

to Item 11.16.

11.12 Extract the image to an SD card and insert the SD card into the top card slot of

PFD1.

11.13 Press and hold the ENT softkey on the displays, while applying power, to enter

into the configuration mode.

11.14 Go to the “SYSTEM UPLOAD” page in the “SYSTEM” (first) page group and

press the LOAD softkey to apply the configuration update.

11.15 Power down the electrical system.

11.16 Complete the ‘CHECK GEAR’ function test.

11.16.1 Set the ELECT MASTER switch to the ON position.

11.16.2 Press and hold the landing gear TEST button located next to the AV.

MASTER switch and ensure the ‘CHECK GEAR’ message appears on

the PFD screen and the audible landing gear sound is heard.

NOTE: All other information displayed is for reference only.

Landing gear

caution message

SERVICE BULLETIN

Service Bulletin No.: D42L-32-01 Rev 0

Title: CHECK GEAR Annunciation

Date Issued: 09 January 2013

Page: 8 of 8

11.16.3 Set the ELECT MASTER switch to the OFF position.

11.17 Install the pilot seat in accordance with the DA42 AMM # 7.02.01 Chapter 25-1

11.18 Install the left nacelle access panel.

11.19 Install the instrument panel cover in accordance with the DA42 AMM # 7.02.01

Chapter 25-10.

11.20 Make a log book entry that this Service Bulletin has been incorporated.

12. Weight and Balance:

12.1 Make the following adjustments to the aircraft weight and balance.

WEIGHT kg (lbs) ARM m (in)

+0.010 (+0.022) +2.24 (+88.2)

13. Availability: Contact Diamond Aircraft Industries Inc.

14. Electrical Load Data: No impact to the electrical load.

15. Credit: None.

To obtain satisfactory results, procedures specified in this Service Bulletin must be accomplished in accordance with accepted methods

and current government regulations. Diamond Aircraft Industries Inc. cannot be responsible for the quality of work performed in

accomplishing the requirements of this Service Bulletin. Diamond Aircraft reserves the right to void continued warranty coverage in the

area affected by this Service Bulletin if it is not incorporated. If you no longer own the aircraft to which this Service Bulletin applies, please

forward it to the current owner and send the name of the current owner to Diamond Aircraft Industries, Inc., at the address below.

Diamond Aircraft Industries Inc. 1560 Crumlin Sideroad, London, Ontario, Canada N5V 1S2

Customer Support: Phone: (519) 457-4041 Fax: (519) 457-4045 Email: [email protected]

Technical Publications: Phone: (519) 457-4030 Ext. 3173 Email: [email protected]

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