EASA

EASA AD No: 2010-0073

AIRWORTHINESS DIRECTIVE

AD No.: 2010-0073

Date: 15 April 2010

Note: This Airworthiness Directive (AD) is issued by EASA, "cling In accordance wit~

Regulation (Ee) No 216/2008 011behalf 01 the European Community, its Member States and

of the ELIrope~n third COUr1lries that participate in the activities of EASA under Article 66 of

that Regulation. I

This AD is issued in a(:cordance with EC 170212003, Part 21A.3B. In a~cOrdarFce with EC 204212003 Annex I, Part M,A,301, lhe

wntinuing airworthiness of an aircr~ft shall be ensured by accomplishing any applicable ADs. COrlseqLJen~y, no person m~y

operate an air<;raft to whiCh an AD applies, except in ~ccordance with lhe~ requirements of that AD unless otherwise specified by the

Agency (EG 204212003 Armex I. Part M,A.303] or ",greed with the Authority of the Slate of Registry lEG 21612008. ArtiCle 14(4)

exemption]. I

Type Approval Holder's Name:

DASSAULT AVIATION

T~pe/Modeldesignation(s) :

F.f\LeON 7X

reDS Number:

Foreign AD.

Supersedure.

ATA24

Manufacturer(s }:

Applicability:

Reason:

EASA Form 112

EASAA155

Not applicable

None

Electrical Power· TransiJnt Voltage Suppressor Diodes -

InspectionfReplacement I

I

Dassault Aviation I

Falcon 7X aeroplanes, all seriall numbers except those on which modification

Dassault Aviation M724 is embrDdied.

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Several in service events relat~d to various electrical systems, have led to the

discovery of a common root leause: a leakage failure mode of Transient

Voltage Suppressor (TVS) diodes used on Power Distribution Control Units

(PDCU) cards or Generator Cbntrol Unit (GCU) cards in the Primary Power

Distribution Boxes (PPDB). Du~ to such TVS diode failure mode, operation of

some electrical circuits is degraded and some control signals are set at

unexpected levels. Further anaiysis indicated that combination of a TVS diode

failure with other systems failur~s could significantly reduce flight safety.

To prevent and correct this cbndition, some Airplane Flight Manual (AFM)

procedures have been modified to reduce the time of exposure to further

failures whenever a TVS diode failure occurs. Additionally, a field tester has

been developed to test all Tvsi diodes installed on the PDCU and GCU cards

for the detection of component~ beyond acceptable tolerances, The criteria for

PDCU or GCU card replacembnt in case of detection of faulty components

have been identified. I

This AD requires the accomplishment of the revised AFM procedures, the

testing and, as necessary. the! replacement of the affected PDCU and GCU

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I Page 1/31
EASAAD No 2010-0073

cards_

Meanwhile, Dassault Aviation is developing a modification (M724), to improve

PDCU and GCU cards, with TVS diodes having reduced susceptibility to the

leakage failure mode.

Effective Date: 29 April 2010

Required Aclion(s) Required as indicated, unless accomplished previously:

and Compliance

Time(s): (1) After the effective date of this AD, amend the F7X AFM sub-section

abnormal procedures and the QUick Reference Handbook 2 (QRH 2) subsections abnormal ELEC and HYD as indicaled below:

0 Upon display of ELEC:BUS MISCONFIG TIED in Crew

Alerting System (Abrlormal procedure 3-190-20), land at

. bl . I

nearest sUita e l:llfPO~

0

~bO~~i~~:Zb~~~,~~~~~e;~~ ~_~~b_~~)~~a~~:~~;~e;tSS

suitable airport

0 Upon display of ELEC:RH ESS PWR LO and ELEC:RH ESS

NO PWR (Abnormal procedure 3-190-45), land at nearest

suitable airport

0 Upon display of HYD:BACKUP PUMP HI TEMP (Abnormal

procedure 3-250-15), set off the pump and if the backup pump

is still rotaling (green) in hydraulic synoptic, descend 10 a safe

altitude or below 15,000 ft

Caution: These temporary amendments take precedence over the same

procedures displayed through the Electronic Check List (ECL) in the

aeroplane.

(2) Pending incorporation of these changes into the next revision of the AFM,

compliance with paragraph (1) of this AD may be demonstrated inserting

a copy of this AD into the AFM, subsection Abnormal Procedures 3-190-

20,3-190-40,3-190-45 and 3-250-15, into the QRH2, subsections

Abnormal ELEC and HYD'I

(3) For the aeroplane serial nur:bers included in the effectivity of Dassault

AViation Falcon 7X Servicli Bulletin (S8) n° 133, wi thin 9 months after

the effective date of this AID inspect the PDCU and GCU cards in

accordance with the instruftions of the SB. In case of detection of faulty

components, before further flight remove and replace the affected PDCU

and GCU cards in accorda'nce with the instructions of Dassault Aviation

S8 n"'l33.

(4) Accomplishment of Goodrich Service Bulletins 80232190-24-01,

80232191-24-01 and 80232192-24-01 is also acceptable to comply with

the requirements of paragraph (3) of this AD.

- F7X AFM DGT105608 Rev 8.

- Dassault Aviation Service Bulletin Falcon 7X n~1 33 original issue.

Ref. Publications: - Goodrich Service Bulletin 80232190-24-01 original issue_

- Goodrich Service Bulletin S0232191-24-01 original issue,

I

- Goodrich Service Bulletin Sq2321 92-24-01 original issue.

EASA Form 112 Page 2/3
EASAAD No: 2010--0073

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

compliance with the requirements of this AD.

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

A1temall,e Melhods of c0r."la"e foc this AD.

2. This AD was posted on 11 March 2010 as PAD 10-022 for consultation

until 08 April 2010. No comments were received during the consultation

period_

3. Enquiries regarding this AD should be referred to the Airworthiness

Directives, Safely Management & Research Section, Certification

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 Technicai Assistance:

• For Europe, Middle E~st and Africa based operators:

Hot Line: (33) 1 47111 3737 {Fax: (33) 1 4711 8949

• For USA, Canada and Mexico based operators:

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

• All other areas:

Help Desk: (1) 201 541 4747 (Fax: (1) 201 541 4740

EASA Form 112

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