FALCON 7X

No 244-R1

JULY 08, 2013

MANDATORY

ATA 27

FLIGHT CONTROLS

OPERATIONAL TEST OF THE SLATS CONTROL

MANIFOLD

FALCON SERVICE BULLETIN

Copyright © 2013 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.

785
FLIGHT CONTROLS

OPERATIONAL TEST OF THE SLATS CONTROL MANIFOLD

Initial issuance February 14, 2013

List of effective pages :

1 to 10

Revision 1 July 08, 2013

List of effective pages :

1 to 10

List of modified pages :

1

REASON:This Service Bulletin becomes mandatory in accordance with an EASA

Airworthiness Directive to be released.

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

this Service Bulletin.

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ATA 27
FLIGHT CONTROLS

OPERATIONAL TEST OF THE SLATS CONTROL MANIFOLD

1. PLANNING INFORMATION

A. EFFECTIVITY

This Service Bulletin is applicable to FALCON 7X aircraft with serial numbers 2 through 101, 105, 106,

108 through 140, 142 through 148, 150, 151, 152, 153, 155, 156, 158, 162, 163, 164, 167, 169 and

173.

B. REASON

Following a quality alert about the slat control manifold P/N 108159-02, the following operational test

allows to determine whether the aircraft is equipped with an affected equipment.

C. DESCRIPTION

This operation consists in performing an operational test of the slats with a circuit breaker disengaged.

Two independent and equivalent procedures can be applied at operator's convenience:

• aircraft with hydraulic systems pressurized with the hydraulic ground power unit,

• aircraft at ground run-up station.

D. COMPLIANCE

Mandatory:

• It is anticipated that this Service Bulletin will be rendered mandatory by an EASA Airworthiness

Directive.

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

E. APPROVAL

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

F. LABOR

Estimated labor-hours:

• Check: 1 hour

• In case of slat control manifold (101CM) replacement: 13 hours

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

other maintenance work which 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

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

If you choose to perform this check with hydraulic supply from a ground power unit:

Aircraft Maintenance Manual:

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

• ENERGIZATION / DE-ENERGIZATION OF THE AIRCRAFT WITH THE ELECTRICAL

GROUND POWER UNIT (GPU) (Refer to TASK 24-00-00-860-805)

• GROUND TEST OF THE FCS (Refer to TASK 27-00-00-700-802)

• FLIGHT CONTROL SYSTEM MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK

27-00-00-910-801)

• REMOVAL / INSTALLATION OF THE SLAT CONTROL MANIFOLD (SCM) (Refer to TASK

27-80-01-900-801)

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DASSAULT AVIATION Proprietary Data
• PRESSURIZATION / DE-PRESSURIZATION OF THE HYDRAULIC SYSTEMS WITH THE

HYDRAULIC GROUND POWER UNIT (GPU) (Refer to TASK 29-00-00-860-803)

If you choose to perform this check with aircraft at a run-up station:

Refer to the Airplane Flight Manual

Aircraft Maintenance Manual:

• FLIGHT CONTROL SYSTEM MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK

27-00-00-910-801)

• POWER PLANT SYSTEM MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK

71-00-00-910-801)

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2. ACCOMPLISHMENT INSTRUCTIONS

A. IF YOU CHOOSE TO PERFORM THIS CHECK WITH HYDRAULIC SUPPLY FROM A GROUND

POWER UNIT

(1) PRELIMINARY STEPS

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

(b) Obey the flight control system maintenance and safety precautions (Refer to TASK

27-00-00-910-801).

(c) Energize the aircraft systems from the electrical GPU (Refer to TASK 24-00-00-860-805).

(d) Make sure that the park brake handle (804GC) is pulled.

(e) Make sure that the slats/flaps control lever (1-fig. 1) of the SFAU (9001CF) is set to “SF 0”.

(f) On maintenance panel (1010TP), set the "TEST E2" switch (L511CZ) and the "TEST E1"

switch (R511CZ) to the ON position (fig. 2).

(g) Pressurize the three hydraulic systems (Refer to TASK 29-00-00-860-803).

(h) Remove the four multi-function probe covers (KPC3-780-45).

(i) On the overhead panel (5000PM), set the "PROBE 1+2" pushbutton (R9810PM), the

"PROBE 3" pushbutton (R9820PM) and the "PROBE 4" pushbutton (R9830PM) to ON (fig.

1).

(j) Wait for one minute to be in the FCS normal mode.

(2) PROCEDURE

(a) On the LH front SPDB (L1000PM), disengage the "SFC LF E3" circuit breaker (213CZ) (fig.

3).

(b) Check that the "FCS: SLATS INB EXTEND FAIL" CAS message is displayed.

(c) Set the slats/flaps control lever (1-fig. 1) of the SFAU (9001CF) to “SF1”.

(d) Check that the middle slats (L9501CM), (L9501CM) and the outboard slats (L9502CM),

(R9502CM) move to the extended position.

(e) Check that the "FCS: SLATS INB EXTEND FAIL" CAS message and "FCS: ALTN LAWS

ACTIVE" CAS message are displayed.

NOTE: An irrelevant "FCS: NO DISPATCH" CAS message is displayed when the "FCS:

ALTN LAWS ACTIVE" appears. It does not need specific monitoring.

(f) Set the back-up slat control switch (2-fig. 1) of the SFAU (9001CF) to the extension position

(guard up).

(g) Make sure that the middle slats (L9501CM), (L9501CM) and the outboard slats (L9502CM),

(R9502CM) stay extended.

NOTE: If the middle and outboard slats are retracted, the test is failed. In this case, stop the

procedure and refer to paragraph 2.A.4.

(h) Check the following CAS messages:

• "FCS: SLATS M+O EXTEND FAIL" is not displayed,

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DASSAULT AVIATION Proprietary Data
• "FCS: SLATS INB EXTEND FAIL" is displayed,

• "FCS: ALTN LAWS ACTIVE" is displayed.

(i) Set the slats/flaps control lever (1-fig. 1) of the SFAU (9001CF) to “SF0”.

(j) Make sure that the middle slats (L9501CM), (L9501CM) and the outboard slats (L9502CM),

(R9502CM) stay extended.

(k) Check the following CAS messages:

• "FCS: SLATS M+O EXTEND FAIL" is not displayed,

• "FCS: SLATS INB EXTEND FAIL" is displayed,

• "FCS: ALTN LAWS ACTIVE" disappears.

(l) Set the back-up slat control switch (2-fig. 1) of the SFAU (9001CF) to the normal position

(guard down).

(m) Make sure that the middle slats (L9501CM), (L9501CM) and the outboard slats (L9502CM),

(R9502CM) move to the retracted position.

(n) Check that the "FCS: SLATS INB EXTEND FAIL" CAS message is displayed.

(o) On the LH front SPDB (L1000PM), engage the "SFC LF E3" circuit breaker (213CZ) (fig. 3).

(p) Check that the "FCS: SLATS INB EXTEND FAIL" CAS message disappears.

(3) FINAL STEPS

(a) Perform a ground test of the FCS (Refer to TASK 27-00-00-700-802).

(4) IN CASE OF TEST FAILURE

(a) Set the back-up slat control switch (2-fig. 1) of the SFAU (9001CF) to the normal position

(guard down).

(b) Set the slats/flaps control lever (1-fig. 1) of the SFAU (9001CF) to “SF0”.

(c) Depressurize the three hydraulic systems (Refer to TASK 29-00-00-860-803).

(d) On the overhead panel (5000PM), set the "PROBE 1+2" pushbutton (R9810PM), the

"PROBE 3" pushbutton (R9820PM) and the "PROBE 4" pushbutton (R9830PM) to OFF (fig.

1).

(e) On maintenance panel (1010TP), set the "TEST E2" switch (L511CZ) and the "TEST E1"

switch (R511CZ) to the OFF position (fig. 2).

(f) On the LH front SPDB (L1000PM), engage the "SFC LF E3" circuit breaker (213CZ) (fig. 3).

(g) De-energize the aircraft systems from the electrical GPU (Refer to TASK 24-00-00-860-805).

(h) Replace the slat control manifold (101CM) (Refer to TASK 27-80-01-900-801).

(i) Perform a new check from paragraph 2.A.1.

B. IF YOU CHOOSE TO PERFORM THIS CHECK WITH AIRCRAFT AT A RUN-UP STATION

(1) PRELIMINARY STEPS

(a) Obey the power plant system maintenance and safety precautions (Refer to TASK

71-00-00-910-801).

(b) Obey the flight control system maintenance and safety precautions (Refer to TASK

27-00-00-910-801).

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DASSAULT AVIATION Proprietary Data
(c) Start up the three engines (refer to the Airplane Flight Manual).

(d) Perform an FCS preflight test (refer to the Airplane Flight Manual, section 4-110-05).

(e) Make sure that the park brake handle (804GC) is pulled.

(f) Make sure that the slats/flaps control lever (1-fig. 1) of the SFAU (9001CF) is set to “SF 0”.

(2) PROCEDURE

(a) On the LH front SPDB (L1000PM), disengage the "SFC LF E3" circuit breaker (213CZ) (fig.

3).

(b) Check that the "FCS: SLATS INB EXTEND FAIL" CAS message is displayed.

(c) Set the slats/flaps control lever (1-fig. 1) of the SFAU (9001CF) to “SF1”.

(d) Check that the middle slats (L9501CM), (L9501CM) and the outboard slats (L9502CM),

(R9502CM) move to the extended position.

(e) Check that the "FCS: SLATS INB EXTEND FAIL" CAS message and "FCS: ALTN LAWS

ACTIVE" CAS message are displayed.

NOTE: An irrelevant "FCS: NO DISPATCH" CAS message is displayed when the "FCS:

ALTN LAWS ACTIVE" appears. It does not need specific monitoring.

(f) Set the back-up slat control switch (2-fig. 1) of the SFAU (9001CF) to the extension position

(guard up).

(g) Make sure that the middle slats (L9501CM), (L9501CM) and the outboard slats (L9502CM),

(R9502CM) stay extended.

NOTE: If the middle and outboard slats are retracted, the test is failed. In this case, stop the

procedure and refer to paragraph 2.B.4.

(h) Check the following CAS messages:

• "FCS: SLATS M+O EXTEND FAIL" is not displayed,

• "FCS: SLATS INB EXTEND FAIL" is displayed,

• "FCS: ALTN LAWS ACTIVE" is displayed.

(i) Set the slats/flaps control lever (1-fig. 1) of the SFAU (9001CF) to “SF0”.

(j) Make sure that the middle slats (L9501CM), (L9501CM) and the outboard slats (L9502CM),

(R9502CM) stay extended.

(k) Check the following CAS messages:

• "FCS: SLATS M+O EXTEND FAIL" is not displayed,

• "FCS: SLATS INB EXTEND FAIL" is displayed,

• "FCS: ALTN LAWS ACTIVE" disappears.

(l) Set the back-up slat control switch (2-fig. 1) of the SFAU (9001CF) to the normal position

(guard down).

(m) Make sure that the middle slats (L9501CM), (L9501CM) and the outboard slats (L9502CM),

(R9502CM) move to the retracted position.

(n) Check that the "FCS: SLATS INB EXTEND FAIL" CAS message is displayed.

(o) On the LH front SPDB (L1000PM), engage the "SFC LF E3" circuit breaker (213CZ) (fig. 3).

(p) Check that the "FCS: SLATS INB EXTEND FAIL" CAS message disappears.

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DASSAULT AVIATION Proprietary Data
(3) FINAL STEPS

(a) Perform a FCS preflight test (refer to the Airplane Flight Manual, section 4-110-05).

(b) Shut-down the three engines (refer to the Airplane Flight Manual).

(4) IN CASE OF TEST FAILURE

(a) Set the back-up slat control switch (2-fig. 1) of the SFAU (9001CF) to the normal position

(guard down).

(b) Set the slats/flaps control lever (1-fig. 1) of the SFAU (9001CF) to “SF0”.

(c) On the LH front SPDB (L1000PM), engage the "SFC LF E3" circuit breaker (213CZ) (fig. 3).

(d) Shut-down the three engines (refer to the Airplane Flight Manual).

(e) Replace the slat control manifold (101CM) (Refer to TASK 27-80-01-900-801).

(f) Perform a new check from paragraph 2.B.1.

C. RECORDING

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

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
Figure 1: LOCATION OF PROBE PUSHBUTTONS AND SFAU

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Figure 2: LOCATION OF TEST E2 AND TEST E1 SWITCHES

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Figure 3: LOCATION OF SFC LF E3 CIRCUIT BREAKER

END OF DOCUMENT

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