EASA AD No : 2011-0241 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0241

Date: 19 December 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 

Supersedure: This AD supersedes EASA AD 2011-0169 dated 02 September 2011. 

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

Operational Test 

Manufacturer(s): Dassault Aviation 

Applicability: Falcon 7X aeroplanes, all serial numbers. 

Reason: In May 2011, 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. 

The results of the investigations showed that there was a production defect in 

the Horizontal Stabilizer Electronic Control Unit (HSECU) which could have 

contributed to the cause of the event. 

This condition, if not corrected, could lead to a loss of control of the 

aeroplane. 

To address this unsafe condition, EASA issued emergency AD 2011-0102-E 

which prohibited further flights. Following further technical investigations 

accomplished by Dassault Aviation, EASA issued AD 2011-0114, currently at 

revision 2, which superseded EASA AD 2011-0102-E. Following 

accomplishment of all the actions as required by EASA AD 2011-0114R2, all 

aeroplanes could resume flying with operational limitations. 

Since EASA AD 2011-0114R2 was issued, Dassault Aviation have 

developed a modification (M1245 to be embodied through accomplishment of 

Dassault Aviation Service Bulletin F7X-214) of the Fly-By-Wire (FBW) current 

standard which improves the monitoring and reversion logic of the Horizontal 

Stabilizer Trim System (HSTS). This modification results in earlier failure 
EASA AD No : 2011-0241 

EASA Form 110 Page 2/3 

detection and quicker reversion. 

Dassault Aviation have issued as well Revision 13 of the Aircraft Flight 

Manual (AFM) which incorporates the changes introduced in EASA 

AD 2011-0114R2 (CP55 and 56) as well as the new changes resulting from 

Dassault Aviation M1245 (CP58). 

Dassault Aviation have introduced as well operational tests of the HSTS 

electric motors reversion relays and of the HSTS trim emergency command 

into the Chapter 5.40 of F7X Aircraft Maintenance Manual (CP010). 

For the reasons described above, EASA issued AD 2011-0169 to require: 

1. accomplishing Dassault Aviation modification M1245, 

2. amending the AFM, and 

3. implementing the operational tests of the HSTS electric motors reversion 

relays and of the HSTS trim emergency command. 

Accomplishment of all the above actions restored the full original certified 

flight envelope of the aeroplane. 

Since EASA AD 2011-0169 was issued, further analyses have demonstrated 

that, once Dassault Aviation modification M1245 is embodied, it is allowed to 

restore the originally certified Minimum Equipment List (MEL) items which 

were removed in accordance with the requirement of paragraph (4) of EASA 

AD 2011-0114R2. 

For the reasons described above, this AD, which supersedes EASA AD 

2011-0169, retaining its requirements, in addition, extends the applicability of 

the AD to all S/Ns and, for aeroplanes fitted with FBW standard 2.1.7.3, 

allows the MEL limitations imposed by EASA AD 2011-0114R2 to be 

removed. 

Effective Date: 02 January 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated unless previously accomplished: 

(1) Within 12 months after having accomplished the actions as specified in 

EASA AD 2011-0114R2 or within 12 months after 05 September 2011 

[the effective date of EASA AD 2011-0169], whichever occurs later, 

upgrade the Fly-By-Wire system installed in the aeroplane to 2.1.7.3 

standard, in accordance with the accomplishment instructions of 

Dassault Aviation Service Bulletin F7X-214 (Dassault Aviation 

modification M1245). Concurrently to the aeroplane modification, amend 

the AFM to revision 13. After modification of an aeroplane as required by 

this AD paragraph, the repetitive operational test of the HSTA electric 

motors reversion relays, as required by paragraph (5) of EASA AD 2011-

0114R2 can be discontinued. The same operational test with a new 

threshold and a new interval is now defined in paragraph (2) of this AD. 

Aeroplanes having Dassault Aviation modification M1245 embodied in 

production are compliant with the modification requirement of this AD 

paragraph and paragraph (5) of EASA AD 2011-0114R2 is not applicable 

to those aeroplanes. 

(2) For aeroplanes having M1245 embodied, within 5 050 flight hours (FH) 

after embodiment of that modification on that aeroplane and thereafter at 

intervals not to exceed 5 050 FH, accomplish an operational test of the 

HSTA electric motors reversion relays as described in Dassault Aviation 

revision 2 to Chapter 5.40 of F7X AMM. 

(3) For aeroplanes having M1245 embodied, within 650 FH after embodiment 

of that modification on that aeroplane and thereafter at intervals not to 

exceed 650 FH, accomplish an operational test of the HSTA trim 

emergency command as described in Dassault Aviation revision 2 to 

Chapter 5.40 of F7X AMM. 

(4) If during any operational test as required by paragraphs (2) or (3) of this 
EASA AD No : 2011-0241 

EASA Form 110 Page 3/3 

AD, the HSTA electric motors reversion relays or the trim emergency 

command, as applicable, fail the test, before next flight, accomplish the 

repair in accordance with the applicable Dassault Aviation approved 

repair instructions. 

(5) Compliance with the new Certification Maintenance Requirements as 

required by paragraphs (2), (3) and (4) of this AD can be demonstrated 

by:

(5.1) 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 and the HSTA Trim emergency command as 

described in revision 2 of Chapter 5.40 of F7X AMM DGT 107838. 

(5.2) Complying with the approved Aircraft Maintenance Programme 

described in paragraph (5.1) of this AD. 

(6) For aeroplanes having M1245 embodied, the MEL amendment as 

required by paragraph (4) of EASA AD 2011-0114R2 may be removed 

and a copy of CP0019 to Master Minimum Equipment List (MMEL) 

(attached to this AD) may be inserted into the operator’s MEL. Inserting 

a copy of CP0019 to MMEL (attached to this AD) into the operator’s 

MEL is an acceptable method to comply with this AD action. 

Ref. Publications: Dassault Aviation Service Bulletin F7X-214 Original dated 30 August 2011. 

Dassault Aviation F7X Aircraft Maintenance Manual DGT107838 chapter 

5.40 revision 2. 

Dassault Aviation F7X Aircraft Flight Manual DGT105608 Revision 13. 

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

compliance with the requirements of this AD. 

CP 0019 to Dassault Aviation F7X Aircraft Master Minimum Equipment List 

DGT106042 revision 6. 

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

Alternative Methods of Compliance for this AD. 

2. The required actions and the risk allowance have granted the issuance of 

a Final AD with Request for Comments, postponing the public 

consultation process after publication. 

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
CP0019 Page 2 / 10 

Impacted Manuals: 

EASA MMEL: DGT106042 REV6 

FAA MMEL: DA-7X REV4 

M&O: DGT106044 REV7 

FGDA: DGT121502 REV 1 

FALCON 7X 

This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data.

MMEL – CP0019

I – CHANGE PROPOSAL TITLE 

M1245 - FCS: FBW 2.1.7.3 Standard 

II – ITEM LIST 

Following items are modified: 

ITEM Rep 

Cat 

Nbr 

Inst

Nbr 

Req REMARKS or EXCEPTIONS 

27 – FLIGHT CONTROLS 

3. Actuator Control and 

Monitoring Units 

(ACMU)

 ⏐

⏐

⏐

(1) ACMU #1 and 

ACMU #2

C 2 1 (O) ACMU #1 or ACMU #2 may be inoperative 

provided: 

- Other ACMU are operative, 

- FCS pre-flight test has been successfully 

performed, 

- No other failure is reported from the Primary 

Flight Control System (PFCS) in any of the 

other PFCS functional lines. 

[OPER 27-1 on section 2-27] 

⏐

⏐

⏐

 (cont'd) ⏐
CP0019 Page 3 / 10 

Impacted Manuals: 

EASA MMEL: DGT106042 REV6 

FAA MMEL: DA-7X REV4 

M&O: DGT106044 REV7 

FGDA: DGT121502 REV 1 

FALCON 7X 

This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data.

MMEL – CP0019

ITEM Rep 

Cat 

Nbr 

Inst

Nbr 

Req REMARKS or EXCEPTIONS 

27 – FLIGHT CONTROLS 

3. Actuator Control and 

Monitoring Units 

(ACMU) (cont'd) 

 ⏐

⏐

⏐

(2) ACMU #3 ⏐

a) A/C without M1245 1 1 ⏐

b) A/C with M1245 C 1 0 (O) ACMU #3 may be inoperative provided: 

- Other ACMU are operative, 

- Selection and Monitoring #3 (SELMON #3) is 

operative, 

- Horizontal Stabilizer Trim Control #3 (THS 

#3) is operative, 

- FCS pre-flight test has been successfully 

performed, 

- No other failure is reported from the Primary 

Flight Control System (PFCS) in any of the 

other PFCS functional lines. 

 [OPER 27-1 on section 2-27]

⏐

⏐

⏐

⏐

⏐

C 1 0 (O) ACMU #3 may be inoperative provided: 

- Other ACMU are operative, 

- Selection and Monitoring #3 (SELMON #3) is 

operative, 

- THS Backup Motor is verified operative, 

 [OPER 27-3 on section 2-27] 

- FCS pre-flight test has been successfully 

performed, 

- No other failure is reported from the Primary 

Flight Control System (PFCS) in any of the 

other PFCS functional lines. 

 [OPER 27-1 on section 2-27] 

- Aircraft speed is limited to 320 KIAS / MI 

0.85.

⏐

⏐

⏐

⏐

⏐

 (cont'd) ⏐
CP0019 Page 4 / 10 

Impacted Manuals: 

EASA MMEL: DGT106042 REV6 

FAA MMEL: DA-7X REV4 

M&O: DGT106044 REV7 

FGDA: DGT121502 REV 1 

FALCON 7X 

This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data.

MMEL – CP0019

ITEM Rep 

Cat 

Nbr 

Inst

Nbr 

Req REMARKS or EXCEPTIONS 

27 – FLIGHT CONTROLS 

3. Actuator Control and 

Monitoring Units 

(ACMU) (cont'd) 

 ⏐

⏐

⏐

(2) ACMU #3 (cont'd) ⏐

b) A/C with M1245 

(cont'd)

A 1 0 (O) ACMU #3 may be inoperative for one flight 

provided: 

- Other ACMU are operative, 

- THS Backup Motor is verified operative, 

 [OPER 27-3 on section 2-27] 

- FCS pre-flight test has been successfully 

performed, 

- No other failure is reported from the Primary 

Flight Control System (PFCS) in any of the 

other PFCS functional lines. 

 [OPER 27-1 on section 2-27] 

- Aircraft speed is limited to 320 KIAS / MI 

0.85.

⏐

⏐

⏐

⏐

⏐

⏐

⏐

 (cont'd) ⏐
CP0019 Page 5 / 10 

Impacted Manuals: 

EASA MMEL: DGT106042 REV6 

FAA MMEL: DA-7X REV4 

M&O: DGT106044 REV7 

FGDA: DGT121502 REV 1 

FALCON 7X 

This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data.

MMEL – CP0019

ITEM Rep 

Cat 

Nbr 

Inst

Nbr 

Req REMARKS or EXCEPTIONS 

27 – FLIGHT CONTROLS 

3. Actuator Control and 

Monitoring Units 

(ACMU) (cont'd) 

 ⏐

⏐

⏐

(3) ACMU #4 ⏐

a) A/C without M1245 1 1 ⏐

b) A/C with M1245 C 1 0 (O) ACMU #4 may be inoperative provided: 

- Other ACMU are operative, 

- Selection and Monitoring #4 (SELMON #4) is 

operative, 

- Horizontal Stabilizer Trim Control #4 (THS 

#4) is operative, 

- FCS pre-flight test has been successfully 

performed, 

- No other failure is reported from the Primary 

Flight Control System (PFCS) in any of the 

other PFCS functional lines. 

 [OPER 27-1 on section 2-27] 

⏐

⏐

⏐

⏐

⏐

C 1 0 (O) ACMU #4 may be inoperative provided: 

- Other ACMU are operative, 

- Selection and Monitoring #4 (SELMON #4) is 

operative, 

- THS Backup Motor is verified operative, 

 [OPER 27-3 on section 2-27] 

- FCS pre-flight test has been successfully 

performed, 

- No other failure is reported from the Primary 

Flight Control System (PFCS) in any of the 

other PFCS functional lines. 

 [OPER 27-1 on section 2-27] 

- Aircraft speed is limited to 320 KIAS / MI 

0.85. 

⏐

⏐

⏐

⏐

⏐

⏐

 
CP0019 Page 6 / 10 

Impacted Manuals: 

EASA MMEL: DGT106042 REV6 

FAA MMEL: DA-7X REV4 

M&O: DGT106044 REV7 

FGDA: DGT121502 REV 1 

FALCON 7X 

This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data.

MMEL – CP0019

ITEM Rep 

Cat 

Nbr 

Inst

Nbr 

Req REMARKS or EXCEPTIONS 

27 – FLIGHT CONTROLS 

5. Front / Rear Rack Power 

Supplies

 

....... 

(6) LH Rear Power #3 ⏐

a) A/C without M1245 1 1 ⏐

b) A/C with M1245 A 1 0 (O) May be inoperative for one flight provided: 

- All other rack power supplies are operative, 

- THS Backup Motor is verified operative, 

 [OPER 27-3 on section 2-27] 

- FCS pre-flight test has been successfully 

performed, 

- No other failure is reported from the Primary 

Flight Control System (PFCS) in any of the 

other PFCS functional lines. 

[OPER 27-1 on section 2-27] 

- Aircraft speed is limited to 320 KIAS / MI 

0.85.

⏐

⏐

⏐

⏐

⏐

....... 

 
CP0019 Page 7 / 10 

Impacted Manuals: 

EASA MMEL: DGT106042 REV6 

FAA MMEL: DA-7X REV4 

M&O: DGT106044 REV7 

FGDA: DGT121502 REV 1 

FALCON 7X 

This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data.

MMEL – CP0019

ITEM Rep 

Cat 

Nbr 

Inst

Nbr 

Req REMARKS or EXCEPTIONS 

27 – FLIGHT CONTROLS 

8. Back-Up Mode ⏐

1) A/C without M1245 1 1 ⏐

2) A/C with M1245 A 1 0 May be inoperative for one flight without 

passenger provided: 

- Primary Flight Control System operated 

spoilers are operative, 

- Primary Flight Control System operated 

Horizontal Stabilizer Trim (THS #3 and THS 

#4) is operative. 

⏐

⏐

⏐

⏐

⏐

⏐

⏐
CP0019 Page 8 / 10 

Impacted Manuals: 

EASA MMEL: DGT106042 REV6 

FAA MMEL: DA-7X REV4 

M&O: DGT106044 REV7 

FGDA: DGT121502 REV 1 

FALCON 7X 

This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data.

MMEL – CP0019

ITEM Rep 

Cat 

Nbr 

Inst

Nbr 

Req REMARKS or EXCEPTIONS 

30 – ICE AND RAIN PROTECTION 

1. Multi-Function Probe 

(MFP) Heating Systems 

 

(1) Primary Heating 

Systems 

 ⏐

⏐

a) A/C without M1245 4 4 ⏐

b) A/C with M1245 B 4 3 (O)(M) One may be inoperative provided: 

- The inoperative MFP primary heating system 

and associated ADS are deactivated and 

secured, 

[MAINT 30-1.1 on section 3-30]

- ADS associated with the non-heatable MFP 

is considered inoperative (refer to item 34-9),

- PF side is on the side-slip compensated 

ADS, 

[OPER 30-1.2 on section 2-30] 

- Approach and landing minima are limited to 

CAT 1 operations, 

- Enroute operations do not require its use, 

[OPER 34-0 on section 2-34] 

- Flight is not conducted into known or forecast 

icing conditions. 

[OPER 30-0 on section 2-30] 

Note: In case of MFP #3 or MFP #4 primary 

heating system inoperative, air data 

parameters displayed on SFD are not 

side-slip compensated. 

⏐

⏐

(2) Secondary Heating 

Systems

 ⏐

⏐

a) A/C without M1245 4 4 ⏐

b) A/C with M1245 C 4 3 One may be inoperative. 

⏐
CP0019 Page 9 / 10 

Impacted Manuals: 

EASA MMEL: DGT106042 REV6 

FAA MMEL: DA-7X REV4 

M&O: DGT106044 REV7 

FGDA: DGT121502 REV 1 

FALCON 7X 

This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data.

MMEL – CP0019

ITEM Rep 

Cat 

Nbr 

Inst

Nbr 

Req REMARKS or EXCEPTIONS 

34 – NAVIGATION 

9. Air Data Systems (ADS) ⏐

1) A/C without M1245 4 4 ⏐

2) A/C with M1245 B 4 3 (O) One may be inoperative provided: 

- Appropriate operative ADS and associated 

IRS are selected, 

[OPER 34-9 on section 2-34] 

- FCS pre-flight test has been successfully 

performed, 

- No other failure is reported from the Primary 

Flight Control System (PFCS) in any of the 

other PFCS functional lines, 

[OPER 27-1 on section 2-27] 

- Crosswind at take-off or landing is limited to 

15 kt. 

⏐

⏐

 
CP0019 Page 10 / 10 

Impacted Manuals: 

EASA MMEL: DGT106042 REV6 

FAA MMEL: DA-7X REV4 

M&O: DGT106044 REV7 

FGDA: DGT121502 REV 1 

FALCON 7X 

This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed without its authorization. DASSAULT AVIATION Proprietary Data.

MMEL – CP0019

III – M&O 

Following paragraphs are added: 

27-3 PREFLIGHT TEST OF THS BACKUP MOTOR 

This test must be performed before park brake is released, before FCS test. 

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 and FCS: ALTN LAWS ACTIVE 

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 and 

FCS: ALTN LAWS ACTIVE CAS messages disappear. 

IV – FGDA 

None.