FALCON 50

No 481-R1

JANUARY 26, 2015

MANDATORY

ATA 33-21

LIGHTING

EXTERIOR LIGHTING

ELECTRICAL BONDING OF WHELEN FIN TIP ANTICOLLISION LIGHT

FALCON SERVICE BULLETIN

Copyright © 2015 by Dassault Aviation

All rights reserved. No part of this work may be reproduced or copied

in any form or by any means without written permission

of Dassault Aviation.

207
LIGHTING

EXTERIOR LIGHTING

ELECTRICAL BONDING OF WHELEN FIN TIP ANTI-COLLISION LIGHT

Initial issuance August 22, 2007

List of effective pages :

1 to 17

Revision 1 January 26, 2015

List of effective pages :

1 to 18

List of modified pages :

1 to 17

REASON:The Service Bulletin is now rendered mandatory.

This revision is not applicable to aircraft already modified per the initial issuance of

this Service Bulletin.

FALCON 50 F50 -481

F50 -33-21
LIGHTING

EXTERIOR LIGHTING

ELECTRICAL BONDING OF WHELEN FIN TIP ANTI-COLLISION LIGHT

1. PLANNING INFORMATION

A. EFFECTIVITY

This Service Bulletin is applicable to MYSTERE-FALCON 50 aircraft with serial numbers 2 through

352, equipped with a WHELEN fin tip anti-collision light (without SATCOM fairing) per Service Bulletin

F50-241 (M1853).

B. REASON

The investigation conducted on a Falcon 2000 aircraft that had been struck by lightning has shown

that the electrical bonding of the fin tip anti-collision light may not be sufficient under certain

circumstances, potentially resulting in damaging the aircraft wiring.

The purpose of this Service Bulletin is to improve the electrical bonding of the MYSTERE-FALCON 50

fin tip anti-collision light whose installation is similar to the F2000.

C. DESCRIPTION

After removing the fin tip fairing, the operation consists of the following:

• to install an electrical bonding strip in two parts between the anti-collision light and a rib of the

fin,

• to modify the shield connection of the wiring,

• to modify the routing of the wiring.

On some of the fairings, it is required to machine a cutout in the rib.

D. COMPLIANCE

Mandatory:

• This Service Bulletin is rendered mandatory by EASA Airworthiness Directive No. 2015-0006.

• As prescribed by the Airworthiness Authorities of the country of registration of the aircraft.

E. APPROVAL

This Service Bulletin covers DASSAULT AVIATION modification MF50 M3094 that has been approved

under the authority of DOA nr. EASA.21J.051.

The technical content of this document is approved under the authority of DOA nr. EASA.21J.051.

F. LABOR

Estimated labor-hours: Refer to Service Bulletin Commercial Summary.

NOTE: These labor-hours only concern the work described in this Service Bulletin and do not include

other maintenance work that may be performed on this occasion.

G. MATERIAL - PRICE AND AVAILABILITY

The modification kit may be obtained from either address listed below:

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DASSAULT AVIATION Proprietary Data
Western hemisphere: DASSAULT FALCON JET CORP.

SPARES DISTRIBUTION CENTER

200 RISER ROAD

LITTLE FERRY, NJ 07643 U.S.A.

Telephone:

• CANADA and U.S.A.: 1-800-800-4036

• MEXICO: 001-800-800-4036

• Other countries: 1-201-541-4809

Fax:

• CANADA and U.S.A.: 1-800-800-4817

• MEXICO: 001-800-800-4817

• Other countries: 1-201-440-7021

Other continents: DASSAULT AVIATION

Falcon Spares

BOITE POSTALE N°101

AEROPORT DU BOURGET

93350 - LE BOURGET Cedex (FRANCE)

Please contact your Dassault Aviation

Account Representative

Telephone: 33 (0)1.48.35.56.78

Fax: 33 (0)1.48.35.56.00

E/H dafsorder@dassault-aviation.com

Price and availability on request.

H. TOOLING - PRICE AND AVAILABILITY

Normal maintenance tooling.

I. WEIGHT AND BALANCE

Change in weight: None.

Change in balance with respect to 25% MAC: None.

J. REFERENCES

Aircraft Maintenance Manual:

• GENERAL MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK 20-00-00-910-801)

• PRINCIPLES AND CHECK OF THE ELECTRICAL BONDING (Refer to TASK

20-20-00-910-801)

• OPERATIONAL TEST OF THE EXTERIOR LIGHTING (Refer to TASK 33-40-00-710-801)

Illustrated Parts Catalog:

• FIN ANTI-COLLISION LIGHT (Refer to IPC fig. 33-40-10-65)

• FIN TIP RED ANTI-COLLISION LIGHT ASSEMBLY (Refer to IPC fig. 33-40-30-45)

• VERTICAL STABILIZER DOORS,RIB05 TO RIB10C (Refer to IPC fig. 55-30-20-30)

• VERTICAL STABILIZER FIN TIP (Refer to IPC fig. 55-30-40-10)

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DASSAULT AVIATION Proprietary Data
Service Bulletin F50-241 "Lighting - Exterior lighting - Replacement of fin anti-collision light"

K. OTHER PUBLICATIONS AFFECTED

The following publications will be revised at a later date to account for the changes introduced by this

Service Bulletin:

• Illustrated Parts Catalog.

• Maintenance Manual.

• Wiring Manual.

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DASSAULT AVIATION Proprietary Data
2. ACCOMPLISHMENT INSTRUCTIONS

A. PRELIMINARY STEPS

(1) The aircraft must be in the maintenance configuration (Refer to TASK 20-00-00-910-801).

(2) Remove the screws attaching upper fin tip fairing (322A) (Refer to IPC fig. 55-30-40-10 , item 10).

(3) Disengage upper fin tip fairing (322A), disconnect connector (322P) and remove upper fin tip

fairing (322A).

(4) On aircraft S/N 2 through 252 with Service Bulletin F50-241 applied, remove door (323K) (Refer

to IPC fig. 55-30-20-30 , item 210).

(5) Removal of the light unit assembly (Refer to IPC fig. 33-40-10-65), (Refer to IPC fig.

33-40-30-45):

• Remove the PR bead coating the retainer (Refer to IPC fig. 33-40-30-45 , item 200) without

removing the flexible gasket located underneath.

• Remove the retainer, glass cover and seal (Refer to IPC fig. 33-40-30-45 , items 200, 230

and 240).

• Remove the light unit assembly (Refer to IPC fig. 33-40-10-65 , item 10).

NOTE: Remove and discard gasket (Refer to IPC fig. 33-40-30-45 , item 260) if installed.

B. PREPARING FAIRINGS F50B319, (A1), (A2) AND FGFB319, (A1)

NOTE: If not concerned, go to step 2.C.

(1) Remove the contacts from connector (17L).

(2) Extract the wiring from the feedthrough at the upper part of rib 3.

NOTE: The wiring will be re-routed in accordance with the instructions of paragraph 2.F.

(3) Machine the cutout in rib 3 in accordance with fig. 7.

C. ANTI-COLLISION LIGHT ELECTRICAL BONDING

In accordance with fig. 1 or fig. 2 depending on the P/N of the existing fairing.

(1) Cut out the run outs of the compound seal to obtain a plane mounting surface.

(2) Set the mounting-base bonding strip (item 1), equipped with shim (item 8), into place on the

fairing. Attach with two screws.

(3) Fold the tab of the strip to a 90° angle with respect to the fairing’s rib.

(4) Pin the strip assembly (items 2 and 3) to the fairing.

(5) Position the strip assembly (items 2 and 3) in contact against the RH side panel of the fairing and

on strip (item 1). If necessary, rework the shape of the strips to obtain proper contact.

(6) Remove the strip assembly (items 2 and 3).

(7) Install double–sided adhesive tape on the face coming in contact with bonding strip (item 1).

(8) Re-install strip assembly (items 2 and 3). Pin to hold in contact against the fairing.

(9) Install strip (item 1) over the strip assembly, pressing firmly at the contact area).

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DASSAULT AVIATION Proprietary Data
(10) Remove the strip assembly (items 1, 2 and 3).

(11) Counterdrill bonding strip (item 2) to a diameter of 0.1 in (2.5 mm). Disconnect the strips and

discard the adhesive tape, remove all remaining adhesive.

(12) Enlarge the holes drilled in the strips to a diameter of 0.126 in (3.2 mm). Assemble bonding strips

(items 1 and 2) using rivets (item 4). Coat the faces of the strips with covering sealant making a

bead at the contour edge with bead sealant.

(13) Clean the contact surfaces of the light unit assembly, of the strips, and of the fairing using MEK.

(14) Coat the strip assembly (items 2 and 3) with interlaying sealant.

(15) Set the strip assembly and the light unit assembly into place in the fairing without making

electrical connections and attach the light assembly to the fairing. Smooth out the PR in excess

around the strips (items 2 and 3).

(16) Use a shim to wedge strip assembly (items 2 and 3) in contact against the fairing’s wall. Allow to

cure.

(17) Temporarily position the fairing at the fin tip and mark the location of strip (item 3).

(18) Strip the paint off the fin tip rib at the location marked for strip (item 3). Protect the stripped area

with alodine.

D. MODIFYING THE WIRING

Modify the shield connection in accordance with instructions depicted hereafter and using fig. 3 and 

fig. 4 in accordance with lights’ installation on the aircraft.

Dimension A:

• Connector with front extraction: 1.38 in (35 mm).

• Connector with rear extraction: 1.97 in (50 mm).

Self–soldering sleeves must be staggered at the extremity of the wiring assemblies so as to prevent a

bulge on the bundle.

INSTALLING SELF-SOLDERING SLEEVES

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DASSAULT AVIATION Proprietary Data
• After stripping the shielded cable and the ground lead wire, unwind the shielding braid of cable

without overlapping the shielding strands.

• Position the self-soldering sleeve on the stripped part of the cable.

• Insert the stripped part of the ground lead wire on the inside of the solder preform. Make sure

that the ground lead wire is installed against the guide provided for this purpose.

• With hot air or infrared generator equipped with an appropriate reflector, start heating the small

diameter of the self-soldering sleeve, then move up to the solder preform until it melts and flows.

Complete the operation on the large side of the self-soldering sleeve. It is recommended to

position the solder preform at a 90° angle maximum in relation to the heat source. The solder

must always be visible to the operator.

• The insulating sheath of the shielded cable must not be blistered nor burnt.

E. RE-ROUTING THE WIRING WITH WIRING ROUTED OVER RIB 2

In accordance with fig. 5:

(1) Remove the WHELEN light unit assembly.

(2) Drill a 0.19 in (4.9 mm) diameter hole through the rib of the fairing.

(3) Install new clamping stud (item 5) on rib 3.

(4) Unclamp the wiring from rib 2.

(5) Clamp the wiring to rib 3.

(6) Connect connector (4LX) to the WHELEN light.

(7) Attach the light unit assembly to the fairing.

(8) Install the gasket, the glass cover, and the retainer (Refer to IPC fig. 33-40-30-45 , items 200, 230

and 240).

(9) Apply bead sealant around the retainer.

F. RE-ROUTING THE WIRING WITH WIRING ROUTED AROUND THE BACK OF FAIRING

In accordance with fig. 6 (Fairing P/N F50B319BX or FGFB319A2, (A3)) or fig. 7 (Fairing P/N

F50B319, (A1), (A2) or FGFB319, (A1))

(1) Remove the WHELEN light unit assembly.

(2) Drill a 0.19 in (4.9 mm) diameter hole through the rib of the fairing.

(3) Install new clamping stud (item 5) on rib 3.

(4) Remove contacts from connector (17L).

(5) Adjust the wiring length for proper re–routing in accordance with fig. 6.

(6) Fit the cut wires with new contacts and insert them into connector (17L).

(7) Clamp the wiring to rib 3.

(8) Connect connector (17L) to the WHELEN light.

(9) Attach the light unit assembly to the fairing.

(10) Install the gasket, the glass cover, and the retainer (Refer to IPC fig. 33-40-30-45 , items 200, 230

and 240).

(11) Apply bead sealant around the retainer.

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DASSAULT AVIATION Proprietary Data
G. FINAL STEPS

(1) Use a permanent ink pen to record the number of this Service Bulletin on "Service Bulletin

Compliance" label (7-fig. 6).

(2) Use interlaying sealant to bond the "Service Bulletin Compliance" label to the inner skin of the

fairing next to the P/N (7-fig. 7).

(3) Place the fairing on the fin tip, connect connector (322P) and attach the fairing.

(4) Re-install the door (323K) (Refer to IPC fig. 55-30-20-30 , item 210) (aircraft S/N 2 through 252

with Service Bulletin F50-241 applied).

(5) Measure the electrical bonding across the anti–collision light retainer plate and the reference point

located in the mechanic’s servicing compartment (Refer to TASK 20-20-00-910-801).

The measured value must not exceed 2 mΩ

(6) Perform the opperational test of the upper anti-collision light (Refer to TASK 33-40-00-710-801).

H. RECORDING

Record compliance with this Service Bulletin in the appropriate aircraft documents.

Fill out the card located at the end of the Service Bulletin and mail or fax it to Dassault Aviation or

Dassault Falcon Jet, or fill out the electronic Service Bulletin reply form located in the ”Service Bulletin"

page on the Falcon portal.

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DASSAULT AVIATION Proprietary Data
3. MATERIAL INFORMATION

A. MODIFICATION KIT

KIT P/N SBF900EX0285A

APPLICABLE TO AIRCRAFT EQUIPPED WITH FAIRINGS F50B319BX OR FGFB319A2, (A3)

KIT P/N SBF900EX0285A - Mechanical kit

NEW P/N

Q

T

Y

KEY WORD INSTRUCTIONS

DISPOSITION

ITEM

FIG

FGFB319100010 1 Mounting-base bonding

strip Supply already assembled

- (1-fig. 1) -

FGFB319100038 1 Shim - (8-fig. 1) -

FGFB319100036 1 Strip

Supply already assembled

- (2-fig. 1) -

FGFB319100037A1 1 Strip - (3-fig. 1) -

NAS1919M04S02WU 3 Rivet - (4-fig. 1) -

78753 1 Studded support - (5-fig. 5) - (5-fig. 6) -

78750-02 1 Clamp - (6-fig. 5) - (6-fig. 6) -

79160 1 "Service Bulletin

Compliance" label

- (7-fig. 5) - (7-fig. 6) -

KIT P/N SBF900EX0285A - Electrical kit

NEW P/N

Q

T

Y

KEY WORD INSTRUCTIONS

DISPOSITION FIG

01EQTC0S20-05-119-18 1 Lug 322J or 312J - fig. 3 - fig. 4 -

01C0K302-16S01 1 Contact 322J or 312J - fig. 3 - fig. 4 -

01CAN210-1-20 1 #20 gauge wire L= 3.3 ft (1 m) 322J or 312J - fig. 3 - fig. 4 -

01C0A54143FC16 4 Blanking pin 322J/P - fig. 3 - fig. 4 -

01EQTRB23-2R 1 Self-soldering sleeve 4LX or 17L - fig. 3 - fig. 4 -

01CAN210-1-22 1 #22 gauge CF wire L = 1 ft (0.3 m) - See

NOTE 1

4LX - fig. 3 -

01CAN203-1-22Y 1 #22 gauge KZ wire L = 1 ft (0.3 m) - See

NOTE 2

4LX or 17L - fig. 3 - fig. 4 -

01EQTC0S20A03-071-22 1 Lug 4LX or 17L - fig. 3 - fig. 4 -

01C0K345-16S01 2 Contact 4LX or 17L - fig. 3 - fig. 4 -

01EQTEC1-1 1 Insulating sleeve 322P or 312P - fig. 3 - fig. 4 -

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DASSAULT AVIATION Proprietary Data
KIT P/N SBF900EX0285A - Electrical kit

NEW P/N

Q

T

Y

KEY WORD INSTRUCTIONS

DISPOSITION FIG

01EQTEC1-1 4 Insulating sleeve - See NOTE 3 312J/P - fig. 4 -

01EQTPRL08B01 1 Splice - See NOTE 3 SP16L-B - fig. 4 -

GND322J-B 2 Black sleeve with white marking

01PR0TMS3-32BK

322J - fig. 3 -

GND312J-B 2 Black sleeve with white marking

01PR0TMS3-32BK

312J - fig. 4 -

A 1 Black sleeve with white marking

01PR0TMS3-32BK

4LX or 17L - fig. 3 - fig. 4 -

B 1 Black sleeve with white marking

01PR0TMS3-32BK

4LX or 17L - fig. 3 - fig. 4 -

78750-01 5 Clamp 4LX or 17L - fig. 3 - fig. 4 -

NOTE 1: Use on MYSTERE-FALCON 50 S/N 2 through 340.

NOTE 2: Use on FALCON 50 S/N 341 and subsequent.

NOTE 3: Use on FALCON 50 S/N 2 through 252.

KIT P/N SBF50–0481A

APPLICABLE TO AIRCRAFT EQUIPPED WITH FAIRINGS F50B319, (A1), (A2) OR FGFB319, (A1)

KIT P/N SBF50–0481A - Mechanical kit

NEW P/N

Q

T

Y

KEY WORD INSTRUCTIONS

DISPOSITION

ITEM

FIG

FGFB319100010W1 1 Mounting-base bonding strip

Supply already assembled

- (1-fig. 2) -

FGFB319100038 1 Shim - (8-fig. 2) -

FGFB319100036W1 1 Strip

Supply already assembled

- (2-fig. 2) -

FGFB319100037W 1 Strip - (3-fig. 2) -

NAS1919M04S02WU 3 Rivet - (4-fig. 2) -

78753 1 Studded support - (5-fig. 7) -

78750-02 1 Clamp - (6-fig. 7) -

79160 1 "Service Bulletin Compliance" label - (7-fig. 5) - 

(7-fig. 6) - 

(7-fig. 7) -

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DASSAULT AVIATION Proprietary Data
KIT P/N SBF50–0481A - Electricall kit

NEW P/N

Q

T

Y

KEY WORD INSTRUCTIONS

DISPOSITION FIG

01EQTC0S20-05-119-18 1 Lug 322J or 312J - fig. 3 - fig. 4 -

01C0K302-16S01 1 Contact 322J or 312J - fig. 3 - fig. 4 -

01CAN210-1-20 1 #20 gauge wire L= 3.3 ft (1 m) 322J or 312J - fig. 3 - fig. 4 -

01C0A54143FC16 4 Blanking pin 322J/P - fig. 3 - fig. 4 -

01EQTRB23-2R 1 Self-soldering sleeve 4LX or 17L - fig. 3 - fig. 4 -

01CAN210-1-22 1 #22 gauge CF wire L = 1 ft (0.3 m) - See

NOTE 1

4LX or 17L - fig. 3 -

01CAN203-1-22Y 1 #22 gauge KZ wire L = 1 ft (0.3 m) - See

NOTE 2

4LX - fig. 3 - fig. 4 -

01EQTC0S20A03-071-22 1 Lug 4LX or 17L - fig. 3 - fig. 4 -

01C0K345-16S01 2 Contact 4LX or 17L - fig. 3 - fig. 4 -

01EQTEC1-1 1 Insulating sleeve 322P or 312P - fig. 3 - fig. 4 -

01EQTEC1-1 4 Insulating sleeve - See NOTE 3 312J/P - fig. 4 -

01EQTPRL08B01 1 Splice - See NOTE 3 SP16L-B - fig. 4 -

GND322J-B 2 Black sleeve with white marking

01PR0TMS3-32BK

322J - fig. 3 -

GND312J-B 2 Black sleeve with white marking

01PR0TMS3-32BK

312J - fig. 4 -

A 1 Black sleeve with white marking

01PR0TMS3-32BK

4LX or 17L - fig. 3 - fig. 4 -

B 1 Black sleeve with white marking

01PR0TMS3-32BK

4LX or 17L - fig. 3 - fig. 4 -

78750-01 5 Clamp 4LX or 17L - fig. 3 - fig. 4 -

NOTE 1: Use on MYSTERE-FALCON 50 S/N 2 through 340.

NOTE 2: Use on FALCON 50 S/N 341 and subsequent.

NOTE 3: Use on FALCON 50 S/N 2 through 252.

B. LOCAL PROCUREMENT

As indicated in Consumable Products Manual (CPM):

• alodine.

• interlaying sealant.

• bead sealant.

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DASSAULT AVIATION Proprietary Data
• covering sealant.

• MEK or equivalent.

• Green CELOMER varnish 6060B.

• Locking wire.

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DASSAULT AVIATION Proprietary Data
Figure 1: ELECTRICAL BONDING ON AIRCRAFT WITH FAIRINGS F50B319BX AND FGFB319A2 (A3)

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Figure 2: ELECTRICAL BONDING ON AIRCRAFT WITH FAIRINGS P/N F50B319, (A1), (A2) AND FGFB319,

(A1)

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Figure 3: AIRCRAFT S/N 253 AND SUBSEQUENT

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Figure 4: AIRCRAFT S/N 2 THROUGH 252 WITH SB F50-241

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Figure 5: AIRCRAFT WITH WIRING ROUTED OVER RIB 2

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Figure 6: AIRCRAFT WITH WIRING ROUTED AROUND THE BACK OF FAIRING

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Figure 7: OPENING IN RIB 3 ON A/C EQUIPPED WITH FAIRINGS - F50B319, (A1), (A2) AND FGFB319,

(A1)

END OF DOCUMENT

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SERVICE BULLETINS COMPLIANCE FALCON 50 A/C S/N

DASSAULT AVIATION Number ATA Number

F50 481 F50 33 21 Coding: C complete compliance

T partial compliance

Performed by:

Remarks: Revision 1 Date: Signature:

SERVICE BULLETINS COMPLIANCE

Would you be kind enough to inform us that this Service Bulletin is complied with:

- For "Western Hemisphere", mail upper card (No postage necessary if mailed in the U.S.A.) or fax to Dassault Falcon Jet: 1-201-541-4700.

- For "Other Continents", mail card herebelow or fax to Dassault Aviation: 33 (0)1.47.11.65.21.

On the occasion, if other Service Bulletins have been simultaneously complied with could you complete the blank spaces provided for this

purpose.

APPLICATION DE BULLETINS DE SERVICE

Lorsque vous aurez applique ce Bulletin de Service sur votre avion, veuillez avoir l'amabilite de nous en informer:

- Utiliser la carte reponse superieure pour continent americain (Dispensee de timbrage pour postage depuis les U.S.A.) ou le fax pour

Dassault Falcon Jet : 1-201-541-4700.

- Ou la carte reponse inferieure pour autres continents ou le fax pour Dassault Aviation : 33 (0)1.47.11.65.21.

Eventuellement, si d'autres Bulletins de Service ont ete appliques simultanement, vous pouvez les mentionner dans les cases vierges

prevues a cet effet.

APPLICATION DES BULLETINS DE SERVICE

SERVICE BULLETINS COMPLIANCE FALCON 50 A/C S/N

DASSAULT AVIATION Number

Numero DASSAULT AVIATION

ATA Number

Numero ATA

F50 481 F50 33 21 Coding: C

complete compliance

application totale

T

partial compliance

application partielle

Performed by:

Fait par:

Remarks: Revision 1 Date: Signature:

Remarques: Revision 1