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 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

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 num bers.

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 unev entful 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 l oss of control of the aeroplane.
To address this unsafe condition, EASA issued emerg ency AD 2011-0102-E which prohibited further flights. Following further technical investigations accomplished by Dassault Aviation, EASA issued AD 2 011-0114, currently at revision 2, which superseded EASA AD 2011-0102-E. F ollowing accomplishment of all the actions as required by EA SA AD 2011-0114R2, all aeroplanes could resume flying with operational lim itations.
Since EASA AD 2011-0114R2 was issued, Dassault Avia tion have developed a modification (M1245 to be embodied thro ugh accomplishment of Dassault Aviation Service Bulletin F7X-214) of the Fly-By-Wire (FBW) current standard which improves the monitoring and reversio n logic of the Horizontal Stabilizer Trim System (HSTS). This modification re sults in earlier failureEASA AD No : 2011-0241

EASA Form 110 Page 2/3 detection and quicker reversion.

Dassault Aviation have issued as well Revision 13 o f the Aircraft Flight Manual (AFM) which incorporates the changes introdu ced in EASA AD 2011-0114R2 (CP55 and 56) as well as the new cha nges resulting from Dassault Aviation M1245 (CP58).
Dassault Aviation have introduced as well operation al tests of the HSTS electric motors reversion relays and of the HSTS tr im emergency command into the Chapter 5.40 of F7X Aircraft Maintenance M anual (CP010).
For the reasons described above, EASA issued AD 201 1-0169 to require:
1. accomplishing Dassault Aviation modification M12 45, 2. amending the AFM, and 3. implementing the operational tests of the HSTS e lectric motors reversion relays and of the HSTS trim emergency command.
Accomplishment of all the above actions restored th e full original certified flight envelope of the aeroplane.
Since EASA AD 2011-0169 was issued, further analyse s 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 sup ersedes 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 accomplishe d:
(1) Within 12 months after having accomplished the actions as specified in EASA AD 2011-0114R2 or within 12 months after 05 Se ptember 2011 [the effective date of EASA AD 2011-0169], whicheve r occurs later, upgrade the Fly-By-Wire system installed in the aer oplane to 2.1.7.3 standard, in accordance with the accomplishment ins tructions of Dassault Aviation Service Bulletin F7X-214 (Dassaul t Aviation modification M1245). Concurrently to the aeroplane modification, amend the AFM to revision 13. After modification of an ae roplane 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 te st with a new threshold and a new interval is now defined in para graph (2) of this AD.
Aeroplanes having Dassault Aviation modification M1 245 embodied in production are compliant with the modification requ irement 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 aerop lane and thereafter at intervals not to exceed 5 050 FH, accomplish an ope rational 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 65 0 FH after embodiment of that modification on that aeroplane and thereaft er at intervals not to exceed 650 FH, accomplish an operational test of th e 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 p aragraphs (2) or (3) of thisEASA AD No : 2011-0241

EASA Form 110 Page 3/3 AD, the HSTA electric motors reversion relays or th e trim emergency command, as applicable, fail the test, before next flight, accomplish the repair in accordance with the applicable Dassault A viation approved repair instructions.
(5) Compliance with the new Certification Maintenan ce 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 th e continuing airworthiness of each operated aeroplane:
Incorporate the Operational Tests of the HSTA elec tric motors reversion relays and the HSTA Trim emergency comman d as described in revision 2 of Chapter 5.40 of F7X AMM DGT 107838.
(5.2) Complying with the approved Aircraft Maintena nce Programme described in paragraph (5.1) of this AD.
(6) For aeroplanes having M1245 embodied, the MEL a mendment as required by paragraph (4) of EASA AD 2011-0114R2 ma y be removed and a copy of CP0019 to Master Minimum Equipment Li st (MMEL) (attached to this AD) may be inserted into the oper ator’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 Bullet in F7X-214 Original dated 30 August 2011.

Dassault Aviation F7X Aircraft Maintenance Manual D GT107838 chapter 5.40 revision 2.
Dassault Aviation F7X Aircraft Flight Manual DGT105 608 Revision 13.
The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

CP 0019 to Dassault Aviation F7X Aircraft Master Mi nimum Equipment List DGT106042 revision 6.

Remarks : 1. If requested and appropriately substantiated, EA SA 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 th e public consultation process after publication.
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 4740CP0019 Page 2 / 10 Impacted Manuals: EASA MMEL: DGT106042 REV6 FAA MMEL: DA-7X REV4 M&O: DGT106044 REV7 FGDA: DGT121502 REV 1 

## FALCON 7XThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced,modified or disclosed withoutits 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 7XThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced,modified or disclosed withoutits 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 7XThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced,modified or disclosed withoutits 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 7XThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced,modified or disclosed withoutits 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 7XThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced,modified or disclosed withoutits 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 7XThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced,modified or disclosed withoutits 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 7XThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced,modified or disclosed withoutits 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 7XThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced,modified or disclosed withoutits 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 7XThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced,modified or disclosed withoutits 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.