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 b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD unless other wise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, 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 dat ed 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0114R1 revised EASA Emergency AD 2011-0114-E dated 16 June 2011, which superseded EASA AD 2011-0102-E dated 26 May 2011.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 seri al numbers
Reason: Recently, a Dassault Aviation Falcon 7X aer oplane experienced an uncontrolled pitch trim runaway during descent. The crew succeeded in recovering a stable situation and performed an unev entful 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 Cont rol Unit (HSECU) which could have contributed to the cause of the event. T here are two different HSECU part numbers (P/N) in use: P/N 051244-02 is n ot affected by this production defect and P/N 051244-04 is potentially affected by this production defect. The aeroplane that experienced t he 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 operat ions and providing protection against further pitch trim runaway events, Dassault Aviation have developed two modifications (M1235 and M1236) which are imple mented throughEASA AD No : 2011-0114R2

EASA Form 110 Page 2/4 accomplishment of Dassault Aviation Service Bulleti n (SB) F7X-211. Furthermore, the flight envelope must be restricted , compared to the original certified flight envelope. Dassault Aviation have d eveloped the corresponding Aircraft Flight Manual (AFM) limitations and a plac ard, 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 prote ction. A Certification Maintenance Requirement (CMR), to r epetitively test the new Horizontal Stabilizer Trim Actuator (HSTA) electric motors reversion relays (installed with M1235 and M1236), has been develope d and must be introduced into chapter 5.40 of the Aircraft Mainte nance Manual (AMM). Additionally, the Master Minimum Equipment List (MM EL) is temporarily modified by this AD to prohibit dispatch of the aer oplane with some specific identified failures. To correct this unsafe condition and allow resumpti on of flights for aeroplanes equipped with HSECU P/N 051244-02, EASA issued AD 2 011-0114-E, which superseded EASA AD 2011-0102-E, to require: 1. accomplishing two Dassault Aviation modification s, 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 ele ctric motors reversion relays. For aeroplanes equipped with HSECU P/N 051244-04, t he prohibition of flights was maintained. Since EASA AD 2011-0114-E was issued, Dassault Avia tion 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 ve rification, having a name plate with a stamped V. After replacement of t he HSECU P/N 051244- 04 with a verified HSECU P/N 051244-04 "V", the aer oplane can resume flights, provided the requirements of this AD are c omplied with. For the reasons described above, EASA AD 2011-0114R 1 was issued to allow aeroplanes equipped with HSECU P/N 051244-04 to resume flights under the same conditions as those previously estab lished for aeroplanes equipped with HSECU P/N 051244-02, provided an HSEC U P/N 051244-04 with stamped "V" is installed. Since EASA AD 2011-0114R1 was issued, Dassault Avia tion have developed a modification of HSECU P/N 051244-04 which correct s the production defect found on some of these units inspected during the i nitial investigation. This modified unit has a new P/N 051244-05 and it is eli gible 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 res ume flights under the same conditions as those previously established for aeroplanes equipped with HSECU P/N 051244-02 or HSECU P/N 051244-04 wit h stamped "V". This revised AD is still considered to be an interi m measure. Pending results of the ongoing investigations, further AD action ma y follow to restore a fully certified flight envelope for aeroplanes of this ty pe 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 pr eviously 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 Aviat ion 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 Aviati on SB F7X-212. (2) Amend the AFM in accordance with Dassault Aviat ion Change Proposal (CP) 055 and CP056 to AFM F7X DGT105608, attached t o this AD. Inserting a copy of Dassault Aviation CP055 and CP0 56 is an acceptable method to comply with this requirement until public ation 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 syst em - 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 Mini mum 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 modificati on 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 Av iation document CP009 to Chapter 5.40 of F7X AMM. (6) If during any operational test as required by p aragraph (5) of this AD, the HSTA electric motors reversion relays fail the test , before next flight, contact Dassault Aviation for approved repair instr uctions and, within the time period specified in those instructions, accomp lish the repair accordingly. (7) Compliance with the new CMR as required by para graphs (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 th e continuing airworthiness of each operated aeroplane: Incorporate the Operational Tests of the HSTA elec tric 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 th is AMM revision. (7.2) Complying with the approved Aircraft Maintena nce Program described in paragraph (7.1) of this AD.

Ref. Publications: Dassault Aviation Service Bullet in 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 DGT107838EASA 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 F light Manual DGT105608 (Attached to this AD). The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The safety assessment has requested not to imple ment the full consultation process and an immediate publication a nd notification. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact your Dassault Falcon Techni cal Assistance: - For Europe, Middle East and Africa based operator s: 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 Proprie tary Data » 10/JUN/2011 DGT 107838 Revision 1 CP009 - EASA Approved 

## FALCON 7X - CHAPTE R 5-40-00 after Rev01
SECTION 5. CMRs AND OTHER ALI THAN FATIGUE and DAMAGE TOLERANCE's (scheduled ALI CDCCLs and AL I 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 TH E HSTA ELECTRIC MOTORS REVERSION 1850 FH A/C with M 1236 or with SB 211

embodied09004000804f9dcd - RELEASED - Certification Repository

### FALCON 7X Airplane Flight Manual OPERATING TECHNIQUES OPERATING TECHNIQUES Trim malfunction 

### 2-100-85 PAGE 1 / 2

CP055

DGT 105608 EASA APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT AVIATION Proprietary Data 

### AUTOMATIC PILOT
Autopilot must not be engaged for take-off or landing. - Minimum height to engage autopilot after take-off ........................................................................ 40 0 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 i ncluding 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 cr ew 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 th e 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 In tegrity Prediction Softwar e, 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 av ailability 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 APPROVEDDASSAULT AVIATION Proprietary Data restricted by the availability or performance of the app licable ground nava ids. 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 gr ound 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 th e 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 pi lot 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 APPROVEDDASSAULT 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 w ill 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 APPROVEDDASSAULT AVIATION Proprietary Data 

### FMS-BASED APPROACHES
The following table describes the approach procedur es approved for automatic execution with the FMS (i.e. use of LNAV/VNAV flight director gui dance, 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 alti tude constrained FAF will lead to a late activation capability, and may result in a steep f light 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 obst acle 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 orNDBDME

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 andprocedurespecified NAVAID available and displayed in the HSI DME-DME Dual FMS synchro NAV: FMS..-GPS 1+2 POS MISC message in CAS Single FMS andprocedurespecified 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 APPROVEDDASSAULT 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 andprocedurespecified NAVAID available and displayed in HSI DME-DME Dual FMS synchro NAV: FMS..-GPS 1+2 POS MISC message in CAS Single FMS andprocedurespecified NAVAID available and displayed in HSIVORDME, provided theprocedurespecified NAVAID has DME capability Dual FMS synchro NAV: FMS..-GPS 1+2 POS MISC message in CAS Single FMS andprocedurespecified 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 APPROVEDDASSAULT 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 andprocedurespecified NAVAID available and displayed in HSI DME-DME Dual FMS synchro NAV: FMS/GPS 1+2 MONIT message in CAS Single FMS andprocedurespecified NAVAID available and displayed in HSI VOR-DME Dual FMS synchro NAV: FMS..-GPS 1+2 POS MISC message in CAS Single FMS andprocedurespecified 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 APPROVEDDASSAULT AVIATION Proprietary Data Approach type and RNP Approved FMS navigation mode Special considerations Specific events following which the approach must be discontinued

NDB orNDBDME

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 andprocedurespecified NAVAID available and displayed in HSI DME-DME Dual FMS synchro NAV: FMS..-GPS 1+2 POS MISC message in CAS Single FMS andprocedurespecified 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 APPROVEDDASSAULT 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 andprocedurespecified NAVAID available and displayed in HSIDMEDME Dual FMS synchro NAV: FMS..-GPS 1+2 POS MISC message in CAS Single FMS andprocedurespecified NAVAID available and displayed in HSIVORDME provided the procedure specified NAVAID has DME capability Dual FMS synchro NAV: FMS..-GPS 1+2 POS MISC message in CAS Single FMS andprocedurespecified 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 APPROVEDDASSAULT 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 andprocedurespecified NAVAID available and displayed in HSIDMEDME Dual FMS synchro NAV: FMS/GPS 1+2 MONIT message in CAS Single FMS andprocedurespecified NAVAID available and displayed in HSIVORDME Dual FMS synchro NAV: FMS..-GPS 1+2 POS MISC message in CAS Single FMS andprocedurespecified 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 messageDMEDME 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 conditi ons

 ATC transponder ............................................................................................................. . Mayday code

### 2-100-50 EMERGENCY OPERATING TECHNIQUES Emergency descent 

### FALCON Airplane Flight Manual PAGE 2 / 2

CP056

DGT105608 EASA APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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) ................................................................................................ VR EF

 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 APPROVEDDASSAULT 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 tenden cy 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) ................................................................................................. VR EF

 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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) ................................................................................................. VR EF

 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 APPROVEDDASSAULT AVIATION Proprietary Data  If in this configuration airplane ha s 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 APPROVEDDASSAULT 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 fa stening 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT 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 APPROVEDDASSAULT AVIATION Proprietary Data  FCS TEST This test must be performed before each flight. Initial conditions: - 1. Airplane on ground, THS at rest, slats not ex tended 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 APPROVEDDASSAULT AVIATION Proprietary Data

INTENTIONALLY LEFT BLANK