EASA AD No : 2011-0114R2 

EASA Form 110 Page 1/4 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0114R2 

Date: 07 July 2011 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and 

of the European third countries that participate in the activities of EASA under Article 66 of that 

Regulation. 

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Agency 

[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Type Approval Holder’s Name : 

DASSAULT AVIATION 

Type/Model designation(s) : 

Falcon 7X aeroplanes 

TCDS Number : EASA.A.155 

Foreign AD : Not applicable 

Revision : This AD revises EASA AD 2011-0114R1 dated 23 June 2011. EASA AD 2011-

0114R1 revised EASA Emergency AD 2011-0114-E dated 16 June 2011, which 

superseded EASA AD 2011-0102-E dated 26 May 2011. 

ATA 27 Flight Controls - Horizontal Stabilizer Pitch Trim - Modification / 

Operational Limitations 

Manufacturer(s): Dassault Aviation 

Applicability: All Falcon 7X aeroplanes, all serial numbers 

Reason: Recently, a Dassault Aviation Falcon 7X aeroplane experienced an 

uncontrolled pitch trim runaway during descent. The crew succeeded in 

recovering a stable situation and performed an uneventful landing. 

This condition, if occurring again, could lead to a loss of control of the 

aeroplane. 

To address this potential unsafe condition, pending investigations by the 

manufacturer, EASA issued emergency AD 2011-0102-E which prohibited 

further flights from its effective date. 

The initial results of the investigations show that there was a production 

defect in the Horizontal Stabilizer Electronic Control Unit (HSECU) which 

could have contributed to the cause of the event. There are two different 

HSECU part numbers (P/N) in use: P/N 051244-02 is not affected by this 

production defect and P/N 051244-04 is potentially affected by this 

production defect. The aeroplane that experienced the uncontrolled pitch trim 

runaway event was equipped with a HSECU P/N 051244-04. Investigations 

are continuing to confirm this cause. 

In the meantime, to allow re-starting flight operations and providing protection 

against further pitch trim runaway events, Dassault Aviation have developed 

two modifications (M1235 and M1236) which are implemented through 
EASA AD No : 2011-0114R2 

EASA Form 110 Page 2/4 

accomplishment of Dassault Aviation Service Bulletin (SB) F7X-211. 

Furthermore, the flight envelope must be restricted, compared to the original 

certified flight envelope. Dassault Aviation have developed the corresponding 

Aircraft Flight Manual (AFM) limitations and a placard, to be installed in the 

cockpit (part of the instructions of SB F7X-211) to remind the flight crew of 

the limitations. In addition, modified operational procedures have been 

developed for in-flight activation of the new protection. 

A Certification Maintenance Requirement (CMR), to repetitively test the new 

Horizontal Stabilizer Trim Actuator (HSTA) electric motors reversion relays 

(installed with M1235 and M1236), has been developed and must be 

introduced into chapter 5.40 of the Aircraft Maintenance Manual (AMM). 

Additionally, the Master Minimum Equipment List (MMEL) is temporarily 

modified by this AD to prohibit dispatch of the aeroplane with some specific 

identified failures. 

To correct this unsafe condition and allow resumption of flights for aeroplanes 

equipped with HSECU P/N 051244-02, EASA issued AD 2011-0114-E, which 

superseded EASA AD 2011-0102-E, to require: 

1. accomplishing two Dassault Aviation modifications, 

2. amending the AFM and installing a placard in the cockpit, 

3. amending the Minimum Equipment List (MEL), and 

4. implementing an operational test of the HSTA electric motors reversion 

relays. 

For aeroplanes equipped with HSECU P/N 051244-04, the prohibition of 

flights was maintained. 

Since EASA AD 2011-0114-E was issued, Dassault Aviation have issued 

SB F7X-212 which gives instructions, for aeroplanes equipped with HSECU 

P/N 051244-04, to remove the HSECU for verification by Rockwell Collins 

and replace it with an HSECU that has passed the verification, having a 

name plate with a stamped V. After replacement of the HSECU P/N 051244-

04 with a verified HSECU P/N 051244-04 "V", the aeroplane can resume 

flights, provided the requirements of this AD are complied with. 

For the reasons described above, EASA AD 2011-0114R1 was issued to 

allow aeroplanes equipped with HSECU P/N 051244-04 to resume flights 

under the same conditions as those previously established for aeroplanes 

equipped with HSECU P/N 051244-02, provided an HSECU P/N 051244-04 

with stamped "V" is installed. 

Since EASA AD 2011-0114R1 was issued, Dassault Aviation have developed 

a modification of HSECU P/N 051244-04 which corrects the production defect 

found on some of these units inspected during the initial investigation. This 

modified unit has a new P/N 051244-05 and it is eligible for installation on an 

aeroplane. 

For the reasons described above, this revised AD is issued to allow 

aeroplanes equipped with HSECU P/N 051244-05 to resume flights under the 

same conditions as those previously established for aeroplanes equipped 

with HSECU P/N 051244-02 or HSECU P/N 051244-04 with stamped "V". 

This revised AD is still considered to be an interim measure. Pending results 

of the ongoing investigations, further AD action may follow to restore a fully 

certified flight envelope for aeroplanes of this type design. 

Effective Date: Revision 2 : 07 July 2011 

Revision 1 : 23 June 2011 

Original issue : 16 June 2011 

Required Action(s) 

and Compliance 

Required as indicated before next flight, unless previously accomplished: 

(1) Modify the aeroplane as specified in paragraph (1.1) and (1.2) of this AD, 
EASA AD No : 2011-0114R2 

EASA Form 110 Page 3/4 

Time(s): as applicable: 

(1.1) For all aeroplanes, accomplish Dassault Aviation modifications 

M1235 and M1236 in accordance with the instructions of Dassault 

Aviation SB F7X-211. 

(1.2) For aeroplanes equipped with HSECU P/N 051244-04, replace the 

HSECU with an HSECU P/N 051244-02 or verified HSECU P/N 

051244-04 with a stamped V or HSECU P/N 051244-05, in 

accordance with the instructions of Dassault Aviation SB F7X-212. 

(2) Amend the AFM in accordance with Dassault Aviation Change Proposal 

(CP) 055 and CP056 to AFM F7X DGT105608, attached to this AD. 

Inserting a copy of Dassault Aviation CP055 and CP056 is an acceptable 

method to comply with this requirement until publication of the AFM 

revision incorporating these amendments. 

(3) Install a placard in the cockpit, in full view of the pilots, in accordance with 

the instructions of Dassault Aviation SB F7X-211.

(4) Amend the MEL by removing the following items:

- item 34-9 air data systems(ADS) 

- item 30-1 Multi Function Probe (MFP) Heating system 

- item 27-3 ACMU3 and ACMU4 

- item 27-5-(6) LH REAR POWER #3 

- item 27-8 Back-up Mode 

 The result of this removal means that dispatch of the aeroplane is 

prohibited with any of these inoperative conditions. 

 Inserting a copy of this AD in the operator’s Minimum Equipment List is 

an acceptable method to comply with the requirement of paragraph (5) of 

this AD. 

(5) Within 1 850 flight hours (FH) after modification of an aeroplane as 

required by paragraph (1) of this AD and thereafter at intervals not to 

exceed 1 850 FH, accomplish an operational test of the HSTA electric 

motors reversion relays as described in Dassault Aviation document 

CP009 to Chapter 5.40 of F7X AMM.

(6) If during any operational test as required by paragraph (5) of this AD, the 

HSTA electric motors reversion relays fail the test, before next flight, 

contact Dassault Aviation for approved repair instructions and, within the 

time period specified in those instructions, accomplish the repair 

accordingly.

(7) Compliance with the new CMR as required by paragraphs (5) and (6) of 

this AD can be demonstrated by:

(7.1) Revising as follows, the Aircraft Maintenance Programme on the 

basis of which the Operator or the Owner ensures the continuing 

airworthiness of each operated aeroplane: 

 Incorporate the Operational Tests of the HSTA electric motors 

reversion relays as described in CP009 to Chapter 5.40 of F7X 

AMM DGT 107838. Inserting a copy of this AD in the aircraft 

documentation is acceptable until publication of this AMM revision. 

(7.2) Complying with the approved Aircraft Maintenance Program 

described in paragraph (7.1) of this AD. 

Ref. Publications: Dassault Aviation Service Bulletin F7X-211 Revision 1 dated 14 June 2011. 

Dassault Aviation Service Bulletin F7X-212 Revision 1 dated 23 June 2011 or 

Dassault Aviation Service Bulletin F7X-212 Revision 2 dated 07 July 2011. 

Dassault Aviation CP009 to F7X Aircraft Maintenance Manual DGT107838 
EASA AD No : 2011-0114R2 

EASA Form 110 Page 4/4 

chapter 5.40 (Attached to this AD). 

Dassault Aviation CP055 and CP056 to F7X Aircraft Flight Manual 

DGT105608 (Attached to this AD). 

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD. 

Remarks : 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The safety assessment has requested not to implement the full 

consultation process and an immediate publication and notification. 

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical content of the requirements in 

this AD, please contact your Dassault Falcon Technical Assistance: 

- For Europe, Middle East and Africa based operators: 

Hot Line: (33) 1 47 11 37 37 / Fax: (33) 1 47 11 89 49 

- For USA, Canada and Mexico based operators: 

Help Desk: (1) 800-2FALCON (2325266) / Fax: (1) 201 541 4740 

- All other areas: 

Help Desk: (1) 201 541 4747 / Fax: (1) 201 541 4740
EFFECTIVITY : ALL Page 1/1 

« DASSAULT AVIATION Proprietary Data » 10/JUN/2011 

DGT 107838 Revision 1 CP009 - EASA Approved 

FALCON 7X - CHAPTER 5-40-00 after Rev01 

SECTION 5. CMRs AND OTHER ALI THAN FATIGUE and DAMAGE TOLERANCE's 

(scheduled ALI CDCCLs and ALI from qualification tests) 

Before CP009 dated 10/Jun/2011 : 

- No task for OPERATIONAL TEST OF THE HSTA ELECTRIC MOTORS 

REVERSION 

After CP009 dated 10/Jun/2011: 

MPD task Code 

Oper Origin Title Max Limit comment effectivity 

27-40-00-710-801 01 CMR OPERATIONAL TEST OF THE HSTA ELECTRIC MOTORS 

REVERSION 

1850 FH A/C with M 1236 

or with SB 211 

embodied 

09004000804f9dcd - RELEASED - Certification Repository
FALCON 7X 

Airplane 

Flight Manual 

OPERATING TECHNIQUES 

OPERATING TECHNIQUES 

Trim malfunction

2-100-85 

PAGE 1 / 2 

CP055 

DGT 105608

EASA APPROVED

DASSAULT AVIATION Proprietary Data

PITCH TRIM RUNAWAY 

Pitch Trim Runaway 

Possibly: FCS: TRIM LIMIT, FCS: THS DEGRAD, FCS: ALTN LAWS ACTIVE and 

AFCS: AP FAIL messages in CAS. 

 

 Counteract using Side Stick 

 Counteract using the manual pitch trim 

 Emergency panel: TRIM EMERG pushbutton .............................................................................. Push 

 Status light ...................................................................................................... Amber ON 

 FCS: THS DEGRAD, FCS: ALTN LAWS ACTIVE and AFCS: AP FAIL appear 
2-100-85 OPERATING TECHNIQUES 

OPERATING TECHNIQUES

Trim malfunction

FALCON 7X 

Airplane 

Flight Manual

PAGE 2 / 2 

CP055 

DGT 105608

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

INTENTIONALLY LEFT BLANK 
FALCON 

Airplane 

Flight Manual 

Limitations 

AIRSPEED, MACH AND LOAD FACTORS 

Airspeed and Mach

1-150-10 

PAGE 1 / 2 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

MAXIMUM OPERATING LIMIT SPEED: VMO / MMO 

VMO / MMO ENVELOPE 

Unless otherwise specified, limits are expressed in terms of indicated values. 

Instrument error is assumed to be zero. 

 

MAXIMUM OPERATING LIMITS 

MMO = 0.85 

VMO = 320 kt 
1-150-10 Limitations 

AIRSPEED, MACH AND LOAD FACTORS

Airspeed and Mach

FALCON 

Airplane 

Flight Manual

PAGE 2 / 2 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

WARNING 

OVERSPEED PROTECTIONS AND AURAL WARNINGS ARE NOT TRIGGERED AT MMO / VMO. 

 

CAUTION 

The maximum operating limit speed MMO / VMO must not be deliberately exceeded in any 

regime of flight (climb, cruise, descent) unless a higher speed is authorized for flight tests or 

pilot training. 
FALCON 

Airplane 

Flight Manual 

Limitations 

AVIONICS 

Automatic flight control system

1-250-05 

PAGE 1 / 2 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

AUTOMATIC PILOT 

Autopilot must not be engaged for take-off or landing. 

- Minimum height to engage autopilot after take-off ........................................................................ 400 ft 

- Minimum height for autopilot operation except during approach .................................................. 400 ft 

- Minimum height for autopilot operation during approach without path reference ........................ 120 ft 

- Minimum height for autopilot operation during approach 

with vertical path reference (ILS-CAT1) .......................................................................................... 80 ft 

CAUTION 

- Above 35,000ft and airspeed below 230 KIAS 

Do not use airbrakes AB1 position while automatic pilot is in use in roll mode with a bank 

angle above 28. 

- Above 25,000ft and airspeed below 250 KIAS 

Do not use airbrakes AB2 position while automatic pilot is in use. 

 
1-250-05 Limitations 

AVIONICS

Automatic flight control system

FALCON 

Airplane 

Flight Manual

PAGE 2 / 2 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

AUTOTHROTTLE 

The autothrottle must not be engaged for take-off, go-around and landing. 

- Minimum height to engage autothrottle in climb after take-off ...................................................... 400 ft 

- Minimum height to disengage autothrottle at landing ...................................................................... 50 ft 

 
FALCON 

Airplane 

Flight Manual 

Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM 

Flight Management and navigation system

1-400-05 

PAGE 1 / 10 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

OPERATION BARO-SETTING 

Below transition altitude or level, altimeter setting must be set to QNH to use VNAV and VSD. 

FMS 

Barometric VNAV guidance during approach including the approach transition, final approach 

segment, and the missed approach procedure is not temperature compensated. Unless a 

temperature limitation is reflected on the approach chart, operating at uncompensated minimum IFR 

altitudes will not provide expected terrain and obstacle clearance for temperatures below ISA. 

AVIONICS WINDOW 

FMS SPEED TAB 

- AUTO Spd Tab: 

- In descent, the crew must not select “Vmo/Mmo”, 

- Crew must ensure that selected speeds are below 0.85/320 kt. 

FLIGHT MANAGEMENT WINDOW 

- Alt/Spd Tab: 

- If CRZ Spd is in “manual”, the crew must check that selected speeds are below 0.85/320 kt. 

- If CRZ Spd is in “LRC” or “Max End”, the crew must check that selected speeds are below 

0.85/320 kt. 

- The crew must not use “Max Spd”. 

SENSORS WINDOW 

FMS OPERATING MODE 

FMS support synchronous and single-mode operation. Selecting synchronous for an FMS which is in 

single operation will result in the synchronization of that FMS with the Pilot Flying FMS (Master FMS). 

NAVIGATION MODE AND PERFORMANCE 

GPS: GPS, as installed, has been found to comply with the requirements for the use of GPS for IFR 

oceanic, domestic en route, and terminal area operations, as defined in JAA Leaflet No. 3 REV 1, 

when used in conjunction with the Pre-flight Integrity Prediction Software, part number 050-03462-

0003 or later approved prediction program. The statements here-above are valid if there is no FMS 

and/or GPS related failure message/label on the PDU / MDU. 

GPS updating must be disabled when operating in countries whose national airspace is not 

referenced to the WGS-84 reference datum in accordance with the criteria of AC20-130A, unless 

other appropriate procedures are used. 

NAVIGATION 

RNP flight operations are subject to GPS satellite availability and/or navaid coverage for the selected 

route. Navigation based on DME/DME or VOR/DME updating modes is permitted but may be 
1-400-05 Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM

Flight Management and navigation system

FALCON 

Airplane 

Flight Manual

PAGE 2 / 10 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

restricted by the availability or performance of the applicable ground navaids. Crews should deselect 

(NOTAM) ground navaids that are not to be used for navigation. 

NAVIGATION MAP (INAV, VSD) AND LOG (WPT LIST): 

INAV AND VSD DATA LAYERS 

INAV including VSD (obstacle, terrain) are provided for advisory purpose only. 

AIRWAYS layer should be used for flight planning on ground to avoid cluttering INAV display in flight. 

INAV including VSD must not be displayed with amber DGR in HSI or displayed EPU above 15NM. 

GRAPHICAL FLIGHT PLANNING 

Hold dialog box: 

- The FMS does not always take into account the published maximum Holding Pattern speed. Only 

the protection area calculated in accordance with the FAA (7130-3) model is taken into account. 

- Adapt and stabilize the airplane speed 2 minutes prior the airplane over flies the fix for the first time. 

- Check that the FMS message HIGH HOLDING GRD SPD is out when passing the fix. 

CRUISE PERFORMANCE 

FUEL, TIME and SMART PERF prediction information are provided for advisory purpose only and 

must not be used for flight planning. 

SID / STAR / APPROACHES / TERMINAL PROCEDURES 

WARNING 

INSERTING AND ACTIVATING A NEW APPROACH OR A NEW FPLN WILL RESET MINIMUMS 

SELECTIONS. THEREFORE, THEY SHOULD BE VERIFIED AFTER SUCH ACTION. 

CAUTION 

- It is crew responsibility to check the system-proposed VGP angle against the chartpublished descent angle. 

- Once VGP is armed, no pilot intervention should be made to ease the capture. 

Steep App check box must only be used during steep approach operation. 

NOTE 

During holding pattern Flight Director mode may revert from VPATH to PATH mode. 

- It is crew responsibility to check procedures retrieved from data base with SID / STAR / approach 

charts. 
FALCON 

Airplane 

Flight Manual 

Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM 

Flight Management and navigation system

1-400-05 

PAGE 3 / 10 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

- Approach procedures retrieved from data base cannot be modified by the crew. 

- For approach procedures retrieved from data base where only one approach transition (IAF) is 

proposed, this transition will not be automatically selected by the system. It is crew responsibility to 

select this approach transition or not (vector to FAF), depending on the intended trajectory to 

execute the approach. 

- Some approaches and STAR procedures are not in the data base. This is because of the way 

some procedures are defined by the controlling agency and the limitations of the FMS. 
1-400-05 Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM

Flight Management and navigation system

FALCON 

Airplane 

Flight Manual

PAGE 4 / 10 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

FMS-BASED APPROACHES 

The following table describes the approach procedures approved for automatic execution with the 

FMS (i.e. use of LNAV/VNAV flight director guidance, either flown manually or coupled to the 

autopilot). 

FMS navigation mode must be checked prior to IAF. 

Performing a Vertical Direct TO (VDTO) on an altitude constrained FAF will lead to a late activation 

capability, and may result in a steep flight path angle up to minus 10 degrees. 

Whatever the kind of FMS-based approach, following one of the 3 events, the approach must be 

discontinued: 

- UNABLE RNP in FMS message window (I-NAV), 

or 

- Green APPR not displayed prior to FAF (ADI), 

or 

- Amber DGR displayed (HSI). 

Observing the Minimum Safe Altitude and obstacle clearances remains crew responsibility. 

Prior to executing an FMS based approach, the RNP Value on the sensor page shall be set to the 

value indicated in the first column. The FMS navigation and synchronization modes shall be checked 

against the second and third columns. 

Approach 

type and 

RNP 

Approved 

FMS 

navigation 

mode 

Special 

considerations 

Specific events following which 

the approach must be 

discontinued 

NDB or 

NDBDME 

RNP 0.6

(or lower) 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in the 

HSI 

DME-DME Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in the 

HSI 
FALCON 

Airplane 

Flight Manual 

Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM 

Flight Management and navigation system

1-400-05 

PAGE 5 / 10 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

Approach 

type and 

RNP 

Approved 

FMS 

navigation 

mode 

Special 

considerations 

Specific events following which 

the approach must be 

discontinued 

VOR 

RNP 0.5

(or lower) 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

DME-DME Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

VORDME, 

provided 

the 

procedurespecified 

NAVAID 

has DME 

capability 

Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 
1-400-05 Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM

Flight Management and navigation system

FALCON 

Airplane 

Flight Manual

PAGE 6 / 10 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

Approach 

type and 

RNP 

Approved 

FMS 

navigation 

mode 

Special 

considerations 

Specific events following which 

the approach must be 

discontinued 

VORDME or 

TACAN 

RNP 0.5

(or lower) 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

DME-DME Dual FMS 

synchro 

NAV: FMS/GPS 1+2 MONIT

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

VOR-DME Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

RNAV 

RNP 0.3 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS or 

GPS RAIM UNAVAILABLE or 

GPS RAIM ABOVE LIMIT FMS 

message 

DME-DME 

unless 

otherwise 

indicated 

on the 

approach 

chart 

Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS 

GPS 

RNP 0.3 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS or 

GPS RAIM UNAVAILABLE or 

GPS RAIM ABOVE LIMIT FMS 

message 
FALCON 

Airplane 

Flight Manual 

Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM 

Flight Management and navigation system

1-400-05 

PAGE 7 / 10 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

Approach 

type and 

RNP 

Approved 

FMS 

navigation 

mode 

Special 

considerations 

Specific events following which 

the approach must be 

discontinued 

NDB or 

NDBDME 

RNP 0.6

(or lower) 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

DME-DME Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 
1-400-05 Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM

Flight Management and navigation system

FALCON 

Airplane 

Flight Manual

PAGE 8 / 10 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

Approac

h type 

and RNP 

Approved 

FMS 

navigatio

n mode 

Special 

considerations 

Specific events following which 

the approach must be 

discontinued 

VOR 

RNP 0.5

(or lower) 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

DMEDME Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

VORDME 

provided 

the 

procedure 

specified 

NAVAID 

has DME 

capability 

Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 
FALCON 

Airplane 

Flight Manual 

Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM 

Flight Management and navigation system

1-400-05 

PAGE 9 / 10 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

Approac

h type 

and RNP 

Approved 

FMS 

navigatio

n mode 

Special 

considerations 

Specific events following which 

the approach must be 

discontinued 

VORDME or 

TACAN 

RNP 0.5

(or lower) 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

DMEDME Dual FMS 

synchro 

NAV: FMS/GPS 1+2 MONIT

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

VORDME Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

message in CAS 

Single FMS and 

procedurespecified 

NAVAID 

available and 

displayed in HSI 

RNAV 

RNP 0.3 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS or 

GPS RAIM UNAVAILABLE or 

GPS RAIM ABOVE LIMIT FMS 

message 

DMEDME 

unless 

otherwise 

indicated 

on the 

approach 

chart 

Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS 

GPS 

RNP 0.3 

GPS Dual FMS 

synchro 

NAV: FMS..-GPS 1+2 POS MISC

NAV: FMS/GPS 1+2 MONIT

message in CAS or 

GPS RAIM UNAVAILABLE or 

GPS RAIM ABOVE LIMIT FMS 

message 
1-400-05 Limitations 

FLIGHT MANAGEMENT AND NAVIGATION SYSTEM

Flight Management and navigation system

FALCON 

Airplane 

Flight Manual

PAGE 10 / 10 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

LOCALIZER-BASED APPROACHES 

The use of FMS guidance (lateral and vertical) on the final approach segment of a localizer-based 

approach (LOC, LOC-DME, LOC B/C, LDA, SDF, ILS, ILS-DME) is prohibited. 

The final part of these approaches shall be executed on LOC or LOC/GS guidance only (depending 

on the type of procedure). 

However, the FMS LNAV / VNAV can be used up to interception of the localizer. For these phases 

(initial approach and intermediate approach), the limitations associated with the following events 

(UNABLE RNP in FMS message window, amber DGR on HSI, NAV:FMS ..-GPS 1+2 POS MISC

and NAV: FMS/GPS 1+2 MONIT in CAS message) are applicable. 
FALCON 

Airplane 

Flight Manual 

EMERGENCY 

OPERATING TECHNIQUES 

Emergency descent

2-100-50 

PAGE 1 / 2 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

EMERGENCY DESCENT 

CAUTION 

The following procedure assumes structural integrity of the airplane. 

If structural integrity is questioned: 

- Limit airspeed to lowest practicable value, 

- Avoid high maneuvering load factors. 

 FASTEN BELT pushbutton ........................................................................................................... Push 

 Status light ......................................................................................................... Blue ON

 Autopilot ................................................................................................................................. Disconnect 

 Power levers (all 3) ........................................................................................................................... Idle 

 AIRBRAKES ..................................................................................................................................... AB2 

 Descent airspeed: .......................................................................... 0.85 / 320 kt, smooth air conditions 

 ATC transponder .............................................................................................................. Mayday code 
2-100-50 EMERGENCY 

OPERATING TECHNIQUES

Emergency descent

FALCON 

Airplane 

Flight Manual

PAGE 2 / 2 

CP056 

DGT105608 

 EASA APPROVED 

DASSAULT AVIATION Proprietary Data

INTENTIONALLY LEFT BLANK 
FALCON 

Airplane 

Flight Manual 

EMERGENCY 

EMERGENCY PROCEDURES 

Fly by wire(A/C with M566)

2-200-35A 

PAGE 1 / 4 

CP056 

A/C with M566 or SB 7X-100 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

MASTER + gong with 66 FCS: DIRECT LAWS ACTIVE in Crew Alerting System 

"DIRECT LAWS" voice warning 

Loss of protection, autotrims and autopilot. 

 

 Operating technique DIRECT LAWS procedure (section 2-100-15) ................................... Applied

 Maneuver with caution. 

CAUTION 

Loss of protections (low speed, high speed, G load), autotrims, autopilot. 

Loss of airbrakes auto retraction and inboard slats auto retraction. 

Do not use AB 2 in flight while flaps are extended. 

Use autothrottle until Minimum Use Height. 

 Airspeed ...................................................................................................... Below 260 KIAS or MI 0.80 

 Manual trims ..................................................................................................................................... Use 

 FASTEN BELT pushbutton ........................................................................................................... Push 

 Status light ......................................................................................................... Blue ON 

 A/B AUTO EXT. pushbutton ......................................................................................................... Push 

 Status light .................................................................................................... Amber OFF

 Maximum landing crosswind 10 kt. 

 If FCS: BOTH AILERONS FAIL NOT in CAS: 

 If FCS: BOTH ELEVATORS FAIL NOT in CAS: 

 If FCS: MFCC FAULT NOT in CAS: 

Perform a long stabilized approach. 

 APPROACH 

SLATS/FLAPS handle ........................................................................................................ SF 3 

Approach speed (zero wind) ............................................................................................. VREF 

Increase landing distance by 23 % (multiply by 1.23). 

 AT 50 FT 

Reduce progressively flight path angle to approximately minus 1.5° at touch down. 

WARNING 

PILOT MUST MINIMIZE SIDE STICK INPUTS AND TRIM ACTIVITY DURING FLARE. 
2-200-35A EMERGENCY 

EMERGENCY PROCEDURES

Fly by wire(A/C with M566)

FALCON 

Airplane 

Flight Manual

PAGE 2 / 4 

CP056 

DGT105608 

A/C with M566 or SB 7X-100 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

 AIRPLANE ON GROUND 

Manual airbrakes only when nose gear is maintained firmly on ground. 

End of procedure.

 If FCS: MFCC FAULT in CAS: 

Airplane stabilized. 

Wait at least one minute or MFCC 1 or 2 or 3 green lighted in FCS synoptic page. 

 FASTEN BELT pushbutton ................................................................................... Blue ON – Check 

Release pressure on flight controls. 

NORM FCS ENGAGE pushbutton ............................................................................................ Push 

 If blue status light ENGAGE does not light: 

ST-BY FCS ENGAGE pushbutton ........................................................................................ Push 

 If 66 FCS: DIRECT LAWS ACTIVE goes out: 

 A/B AUTO EXT. pushbutton .................................................................................................. Push 

 Status light ................................................................................................ Unlighted - On 

End of procedure. 

 If 66 FCS: DIRECT LAWS ACTIVE remains on: 

Perform a long stabilized approach. 

 APPROACH 

SLATS/FLAPS handle ............................................................................................................. SF 3 

Approach speed (zero wind) ................................................................................................ VREF 

Increase landing distance by 23 % (multiply by 1.23). 

 AT 50 FT 

Reduce progressively flight path angle to approximately minus 1.5° at touch down. 

WARNING 

PILOT MUST MINIMIZE SIDE STICK INPUTS AND TRIM ACTIVITY DURING FLARE. 

 AIRPLANE ON GROUND 

Manual airbrakes only when nose gear is maintained firmly on ground. 

End of procedure. 
FALCON 

Airplane 

Flight Manual 

EMERGENCY 

EMERGENCY PROCEDURES 

Fly by wire(A/C with M566)

2-200-35A 

PAGE 3 / 4 

CP056 

A/C with M566 or SB 7X-100 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

 If FCS: BOTH AILERONS FAIL in CAS: 

CAUTION 

Roll control is accomplished only through rudder pedal inputs. 

Roll trim is inoperative: Use Rudder trim. 

Airplane stabilized. 

 FASTEN BELT pushbutton ................................................................................... Blue ON – Check 

CAUTION 

 Be prepared to counteract roll tendency in case of effective FCS engage. 

Release pressure on flight controls. 

NORM FCS ENGAGE pushbutton ............................................................................................ Push 

 If blue status light ENGAGE does not light: 

ST-BY FCS ENGAGE pushbutton ........................................................................................ Push 

 If 66 FCS: DIRECT LAWS ACTIVE goes out: 

 A/B AUTO EXT. pushbutton .................................................................................................. Push 

 Status light ................................................................................................ Unlighted - On 

End of procedure. 

 If 66 FCS: DIRECT LAWS ACTIVE remains on: 

Perform a long stabilized approach. 

 APPROACH 

SLATS/FLAPS handle ............................................................................................................. SF 3 

Approach speed (zero wind) ................................................................................................. VREF 

Increase landing distance by 23 % (multiply by 1.23). 

 AT 50 FT 

Reduce progressively flight path angle to approximately minus 1.5° at touch down. 

WARNING 

PILOT MUST MINIMIZE SIDE STICK INPUTS AND TRIM ACTIVITY DURING FLARE. 

 AIRPLANE ON GROUND 

Manual airbrakes only when nose gear is maintained firmly on ground. 

End of procedure. 
2-200-35A EMERGENCY 

EMERGENCY PROCEDURES

Fly by wire(A/C with M566)

FALCON 

Airplane 

Flight Manual

PAGE 4 / 4 

CP056 

DGT105608 

A/C with M566 or SB 7X-100 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

 If FCS: BOTH ELEVATORS FAIL in CAS: 

CAUTION 

Pitch control is accomplished only through the manual pitch trim. 

Manual airbrakes only when nose gear is on ground. 

Airplane stabilized. 

 FASTEN BELT pushbutton ................................................................................... Blue ON – Check 

Release pressure on flight controls. 

NORM FCS ENGAGE pushbutton ............................................................................................ Push 

 If blue status light ENGAGE does not light: 

ST-BY FCS ENGAGE pushbutton ........................................................................................ Push 

 If 66 FCS: DIRECT LAWS ACTIVE goes out: 

 A/B AUTO EXT. pushbutton .................................................................................................. Push 

 Status light ................................................................................................ Unlighted - On 

End of procedure. 

 If 66 FCS: DIRECT LAWS ACTIVE remains on: 

Perform a long and flat stabilized approach (path angle approximately minus 1.5°). 

 APPROACH 

SLATS/FLAPS handle ............................................................................................................. SF 3 

Approach speed (zero wind) ...................................................................................... VREF + 20kt 

Increase landing distance by 120 % (multiply by 2.20). 

 AT 50 FT 

Maintain flight path angle until touch down. 

WARNING 

PILOT MUST MINIMIZE SIDE STICK INPUTS AND TRIM ACTIVITY DURING FLARE. 

 AIRPLANE ON GROUND 

Apply brake pressure then manually extend airbrakes at AB 2. 
FALCON 

Airplane 

Flight Manual 

ABNORMAL 

ENGINES 

Airstart(A/C with M566)

3-200-15A 

PAGE 1 / 4 

CP056 

A/C with M566 or SB 7X-100 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

IN FLIGHT RELIGHT ENVELOPE: WINDMILLING 

 

WINDMILLING RELIGHT 

WARNING 

STARTER ASSISTED RELIGHT procedure must be applied before attempting a WINDMILLING 

RELIGHT. 

For corresponding engine: 

 Engine .. FUEL switch ..................................................................................................................... OFF 

 Establish airplane within windmilling envelope. 
3-200-15A ABNORMAL 

ENGINES

Airstart(A/C with M566)

FALCON 

Airplane 

Flight Manual

PAGE 2 / 4 

CP056 

DGT105608 

A/C with M566 or SB 7X-100 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

NOTE 

 Wait for N2 below 45 % before attempting a windmilling relight. 

 BOOST .. status light .........................................................................................Unlighted - On - Check 

 ANTI-ICE: ENG .. and WINGS status lights ....................................................Unlighted - Off - Check 

 BLEED .. status light ............................................................................................ Amber OFF - Check 

 Power lever ......................................................................................................................... Idle - Check 

 Engine .. FUEL switch ....................................................................................................................... ON 

 On PDU .......................................................................... Green START and amber IGN

 Monitor ITT and N2. 

 If engine is relighted (N2 stabilized): 

IGN annunciation ........................................................................................................................... Out 

START annunciation ..................................................................................................................... Out 

Engines parameters ................................................................................................................. Check 

 If engine 2 is operative: 

 BUS TIE pushbutton .............................................................................................................. Push

 Status light .......................................................................................... Unlighted - Untied 

Release pressure on flight controls. 

NORM FCS ENGAGE pushbutton ............................................................................................ Push 

 If blue status light ENGAGE does not flash: 

ST-BY FCS ENGAGE pushbutton ........................................................................................ Push 

 GALLEY MASTER and CABIN MASTER pushbuttons ................................................ As required 

ANTI-ICE: ENG .. and WINGS pushbuttons ................................................................. As required 

TA/RA ........................................................................................................................................ Select 

 BLEED.. pushbutton ................................................................................................... Push to set On 

 Status light ................................................................................................ Unlighted - On 

WINDSHIELD HEAT: LH and RH pushbutton .......................................................... Push to set On 

 Status lights .............................................................................................. Unlighted - On 
FALCON 

Airplane 

Flight Manual 

ABNORMAL 

ENGINES 

Airstart(A/C with M566)

3-200-15A 

PAGE 3 / 4 

CP056 

A/C with M566 or SB 7X-100 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

IN FLIGHT RELIGHT ENVELOPE: STARTER ASSIST 

 

STARTER ASSISTED RELIGHT 

NOTE 

 If possible, wait 1 minute between engine shutdown and engine start. 

 

 BUS TIE pushbutton ...................................................................................................................... Push 

 Status light ................................................................................................... Amber TIED

For corresponding engine: 

 Engine .. FUEL switch ..................................................................................................................... OFF 
3-200-15A ABNORMAL 

ENGINES

Airstart(A/C with M566)

FALCON 

Airplane 

Flight Manual

PAGE 4 / 4 

CP056 

DGT105608 

A/C with M566 or SB 7X-100 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

 Establish airplane within starter assist envelope (below 35,000 ft). 

 BOOST.. status light .........................................................................................Unlighted - On - Check 

 ANTI-ICE: ENG .. and WINGS status lights .....................................................Unlighted - Off - Check 

 BLEED .. status light ............................................................................................ Amber OFF - Check 

 

 Maintain N1 above 70 % on other engines. 

 Engine .. FUEL switch ....................................................................................................................... ON 

 MAN START / MOTORING ENG .. pushbutton ........................................... Push and hold (0.75 sec.) 

 On PDU .......................................................................... Green START and amber IGN

 Monitor ITT and N2. 

 If engine is relighted (N2 stabilized): 

IGN annunciation ........................................................................................................................... Out 

START annunciation .................................................................................................................... Out 

Engines parameters ................................................................................................................. Check 

 If engine 2 is operative: 

 BUS TIE pushbutton .............................................................................................................. Push

 Status light .......................................................................................... Unlighted - Untied 

Release pressure on flight controls. 

NORM FCS ENGAGE pushbutton ............................................................................................ Push 

 If blue status light ENGAGE does not flash: 

ST-BY FCS ENGAGE pushbutton ........................................................................................ Push 

 GALLEY MASTER and CABIN MASTER pushbuttons ................................................ As required 

ANTI-ICE: ENG .. and WINGS pushbuttons .................................................................. As required 

TA/RA ........................................................................................................................................ Select 

 BLEED.. pushbutton ................................................................................................... Push to set On 

 Status light ................................................................................................ Unlighted - On 

WINDSHIELD HEAT: LH and RH pushbutton .......................................................... Push to set On 

 Status lights .............................................................................................. Unlighted - On 

 If engine is not relighted: 

Relight engine with WINDMILLING RELIGHT procedure (section 3-200-15A). 
FALCON 

Airplane 

Flight Manual 

ABNORMAL 

FLIGHT CONTROL 

Sensor or actuator malfunction(A/C with M566)

3-210-10A 

PAGE 1 / 2 

CP056 

A/C with M566 or SB 7X-100 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

MASTER + gong with FCS: THS DEGRAD in Crew Alerting System 

 

FCS: ALTN LAWS ACTIVE and AFCS: AP FAIL messages in CAS. 

 

 Maneuver with caution. 

 Use the manual pitch trim. 

 Airspeed ...................................................................................................... Below 260 KIAS or MI 0.80 

 Emergency Panel: TRIM EMERG pushbutton .............................................................................. Push 

 Status light ...................................................................................................... Amber ON 

 If the manual pitch trim is operative: 

Maximum landing crosswind ....................................................................................................... 15 kt 

End of procedure. 

 If the manual pitch trim is inoperative: 

 CRUISE 

Recover speed for which side stick forces are acceptable. 

CAUTION 

SLATS/FLAPS in clean configuration is forbidden at airspeed below 160 kt. 

 APPROACH 

Maximum landing crosswind ....................................................................................................... 15 kt 

 A/B AUTO EXT. pushbutton ..................................................................................................... Push 

 Status light .................................................................................................... Amber OFF

SLATS/FLAPS handle ................................................................................................................. SF 2 

Airspeed ......................................................................................................................... VREF + 25 kt 

Landing gear handle ................................................................................................................. Down 

 On HSI: GEAR symbols (all 3) .............................................................................. Green 

 If in this configuration airplane has a nose up tendency: 

SLATS/FLAPS handle ............................................................................................................. SF 3 

Approach speed (zero wind) ................................................................................................. VREF 

Increase landing distance by 24 % (multiply by 1.24). 

CAUTION 

Manual airbrakes extension at landing is not authorized. 
3-210-10A ABNORMAL 

FLIGHT CONTROL

Sensor or actuator malfunction(A/C with M566)

FALCON 

Airplane 

Flight Manual

PAGE 2 / 2 

CP056 

DGT105608 

A/C with M566 or SB 7X-100 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

 If in this configuration airplane has a nose down tendency or is steady: 

SLATS/FLAPS handle ............................................................................................................. SF 2 

Approach speed (zero wind) ..................................................................................... VREF + 25 kt 

FMW window: Arrival POF: Landing Config tab .......................................... Select Flaps Override 

Increase landing distance by 120 % (multiply by 2.2). 

CAUTION 

Manual airbrakes extension at landing is not authorized. 

 

CAUTION 

The landing gear not extended aural warning may not sound. 

 NOTE 

This procedure incorporates the procedure for: FCS: ALTN LAWS ACTIVE. 

Do not complete the procedure for FCS: ALTN LAWS ACTIVE. 
FALCON 

Airplane 

Flight Manual 

NORMAL 

BEFORE TAXI 

Before park brake is released

4-110-05 

PAGE 1 / 6 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

BEFORE PARK BRAKE IS RELEASED 

NOTE 

For the first flight of the day COCKPIT CHECK must start from an electrical power off condition. 

Before APU is started, safety area must be verified, nav lights must be turned on. 

Before engines are started, park brake must be set, safety area must be verified, anticol red lights 

must be turned on. 

Before park brake is released, following actions must be performed: 

 Verifications of cabin and cockpit fire extinguishers and smoke hoods. 

 Closure of all doors, 

 Verification of Cargo and loose items, 

 Verification of cockpit lights, including emergency panel. 

 Verification of rain repellent level, 

 Verification of hydraulic, and oxygen quantities, 

 Verification of circuit breaker status, 

 Verification of extinction of all “emergency panel” lights, 

 Verification of tire pressure, 

 Verification of no smoking and fasten seat belts signs, 

 Verification of the accessibility of emergency handles for RAT and gear free fall extension, 

 Verification of crew seat adjustment, rudder pedals and fastening of crew seat belts, 

 Verification of CCD pilot and copilot, outer position must be checked after verification, 

 Test of Fire Control Panel  , 

 Test of hydraulic Backup pump  , 

 Test of RAT  , 

 Test of emergency lights  , 

 Test of windshield heat , 

 Test of cockpit oxygen masks , 

 Test of conditioning system , 

 Test of Anti Ice , 

 Verification that flight controls move freely up to full deflection of the stick, 

NOTE 

Flight controls verification must be done without any other verification in progress and one axis after 

the other. 
4-110-05 NORMAL 

BEFORE TAXI

Before park brake is released

FALCON 

Airplane 

Flight Manual

PAGE 2 / 6 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

 Test of Airbrakes  , 

 Test of TRIM EMERG pushbutton, 

 Test of FCS  , 

 Setting of ELT in AUTO position, 

 Activation of fasten seat belt sign. 

 

MEL when applicable must be checked for all failures indicated by CAS messages in CAS window or 

status page, as well as for failures identified by the crew independently of CAS messages. 

 FIRE CONTROL PANEL TEST 

This test must be performed before starting the APU or the first engine once status page has been 

checked. 

Initial conditions:

- After LH and RH INIT performed, LH and UP DU available. 

Test description:

- 1. Overhead panel: depress FIRE TEST, maintain, and check: 

- white CAS message FIRE: TEST IN PROGRESS is displayed. 

- illumination of all fire control panel and the throttles lights 

- 2. If amber CAS message FIRE: TEST FAIL is displayed: it must be determined which item has 

failed before entering MEL. 

 

 HYDRAULIC BACKUP PUMP TEST 

This test must be performed before each flight. 

Initial conditions:

- 1. Airplane on ground, 

- 2. Engine 1 running. 

Test description:

- 1. Overhead panel: set BACKUP pump to ON , 

- 2. Check hydraulic # B pressure to 2900 PSI 

- 3. If pressure does not increase it must be determined which item has failed before entering 

MEL, 

- 4. Overhead panel: set BACKUP pump to AUTO. 

 

 RAT TEST 

This test must be performed before each flight. 

Initial conditions:

- 1. Electrical initialization completed. 

Test description:

- 1. Synoptic / test page: select RAT soft key until white CAS message 

RAT: TEST IN PROGRESS is displayed. 

- 2. If amber CAS message RAT: TEST FAIL is displayed: it must be determined which item has 

failed before entering MEL. 
FALCON 

Airplane 

Flight Manual 

NORMAL 

BEFORE TAXI 

Before park brake is released

4-110-05 

PAGE 3 / 6 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

 EMERGENCY LIGHTS TEST 

This test must be performed before each flight. 

Initial conditions:

- 1. Always available. 

Test description

- 1. Overhead panel: set EMERG LIGHTS on ON position. 

- 2. Check correct illumination of the emergency lights in the cockpit and the cabin. 

 WINDSHIELD HEAT TEST 

This test must be performed before each flight. 

Initial conditions:

- 1. Airplane on ground 

Test description:

- 1. Synoptic / test page: select WSHIELD soft key until white CAS message 

WSHIELD: TEST IN PROGRESS is displayed 

- 2. If amber CAS message WSHIELD: TEST FAIL is displayed: it must be determined which 

item has failed before entering MEL. 

 COCKPIT OXYGEN MASK TEST 

This test must be performed before each flight. 

Initial conditions:

- 1. Crew stowage box switch must be ON 

- 2. Essential buses must be connected. 

Test description:

- 1. Crew stowage box rotary switch on Normal position then press to test 

- 2. Yellow blinker is displayed within 4 sec. 

- 3. Repeat sequence on EMERG and 100% position 

- 4. If Yellow blinker is not displayed: it must be determined which item has failed before entering 

MEL. 

 CONDITIONING SYSTEM TEST 

This test must be performed before the first take-off of the day. 

Initial conditions:

- 1. Airplane on ground 

- 2. APU running, BLEED auto or 

ENG 1 running, N2 > 60% and 

ENG 2 running, N2 > 60%. 

- 3. Air conditioning mode: NORMAL, or PAX OFF, or CREW OFF. 

Test description:

- 1. Synoptic / test page : select COND soft key until white CAS message 

COND: TEST IN PROGRESS is displayed 

- 2. After 15sec, when white CAS message COND: TEST WAITING EMER is displayed select 

EMERG mode. 
4-110-05 NORMAL 

BEFORE TAXI

Before park brake is released

FALCON 

Airplane 

Flight Manual

PAGE 4 / 6 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

- 3. After 20sec, when white CAS message COND: TEST WAITING NORM is displayed select 

NORMAL mode. 

- 4. If amber CAS message COND: TEST FAILED is displayed: it must be determined which item 

has failed before entering MEL. 

TEST OF ANTI ICE 

This test must be performed before each flight. 

Initial conditions:

- 1. TLA at idle. 

Test description:

- 1. ANTI-ICE: ENG1, ENG2 and ENG3 pushbuttons set to ON, 

- 2. Wait for 20 seconds, 

- 3. Check of absence of any A/I: ENG .. XX PRESS message in crew alerting system, 

- 4. ANTI-ICE: ENG1, ENG2 and ENG3 pushbuttons set to off. 

AIRBRAKES TEST 

This test must be performed before each flight. 

Initial conditions:

- 1. Airplane on ground and after verification of flight controls 

- 2. Hydraulic pressure established. 

Test description:

- 1. Extend airbrakes to AB 1 then AB 2 position then AB 0. 

- 2. Check proper operation of airbrakes and absence of CAS message. 

TRIM EMERG TEST 

This test must be performed before each flight. 

Initial conditions: 

- 1. Airplane on ground, flaps SF0 position, before TRIM EMERG test 

- 2. Park brake is ON 

- 3. All engines running 

- 4.Side stick released. 

Test description: 

- 1. Emergency panel: Set TRIM EMERG pushbutton to ON 

- 2. Select manual pitch trim until amber FCS: THS DEGRAD, FCS: NO DISPATCH, 

FCS: ALTN LAWS ACTIVE, AFCS: AP FAIL CAS messages are displayed. 

- 3. Check in FCS synoptic page that THS can be moved up and down by using manual pitch trim 

control 

- 4. Set THS 0° nose, release the manual pitch trim and check the THS does not move in FCS 

synoptic page. 

- 5. Emergency panel: Set TRIM EMERG pushbutton to OFF 

- 6. Overhead Panel: Select FCS ENGAGE and check amber FCS: THS DEGRAD, 

FCS: NO DISPATCH, FCS: ALTN LAWS ACTIVE, AFCS: AP FAIL CAS messages disappear. 
FALCON 

Airplane 

Flight Manual 

NORMAL 

BEFORE TAXI 

Before park brake is released

4-110-05 

PAGE 5 / 6 

CP056 

DGT105608 

EASA APPROVED

DASSAULT AVIATION Proprietary Data

FCS TEST 

This test must be performed before each flight. 

Initial conditions:

- 1. Airplane on ground, THS at rest, slats not extended and after verification of flight controls and 

test of airbrakes 

- 2. Park brake is On, 

- 3. All engines running, 

- 4. Sidestick released. 

Test description:

- 1. Synoptic / test page: select FCS soft key until white CAS message 

FCS: TEST IN PROGRESS is displayed, 

- 2. Test is completed when white CAS message FCS: TEST IN PROGRESS goes out, 

- 3. If amber CAS message FCS: TEST FAIL is displayed: it must be determined which item has 

failed before entering MEL. 
4-110-05 NORMAL 

BEFORE TAXI

Before park brake is released

FALCON 

Airplane 

Flight Manual

PAGE 6 / 6 

CP056 

DGT105608 

EASA APPROVED 

DASSAULT AVIATION Proprietary Data

INTENTIONALLY LEFT BLANK