## EASA EASA AD No: 2010-0019 

## AIRWORTHINESS DIRECTIVE AD No,: 

### 2010·0019

Date: OSFebruary 2010 Note: This Airworthiness Directive (AD) isissued by EASA, acting inaccordance with Regulation (Eel No21612008on behalf 0,1 the European Community, its MemberStales and ofthe Europe"n third countries that participate intheactivities 01EASAunder Article 66

### orthal Regulation. This AD is issued in accordance wiHl EC 170212003,P"rt 21A,38, In accordance with EC 204212003Annex I, Part M.A.301, the continuing airvvorthiflSSS of anaircraft shall beensured byaccomplishing any~pplic8ble ADs, Consequently, noperson mayoperate an aircraft 10which an AD applies. except inaccord~nce with the requiremsnts ofthatAD unless otherwise specified bythe Agency IEC 2042/2003 Annex I, Part M,A.303] oragreed withtheAuthority oftheSlale orRegislry [EC216/2008, Arlicle 14(4)exemption]. 

### Type Approval Holder's Name; AIRBUS 1;ype/Model designation(s) : 

### .l\300aeroplanes TCDS Number Foreign AD. Supersedure:



### ATA27
Manufacturer(s): Applicability:

Reason:

Effective Date:
EASA Form 110 France N°145 Not applicable None 

### Flight Controls ~ Trimmabla Horizontal Stabilizer Actuator (THSA) Upper Attachment - Inspection

Airbus (formerly Airbus Industrie) Airbus A300 aeroplanes, all models, all serial numbers. In accordance with design regulation, the THSA has afailsafe design. lis upper attachment to the aeroplane has two load paths, a Primary Load Path (PLP) and a Secondary Load Path (SLP), which is only engaged in case of PLP failure, Following the design intent, engagement of the SLP leads tojam the THSA, indicating the failu~e of the PLP.I Tests carried out under the ioads-measured during representative flights have demonstrated that, when the S~P isengaged, itdoes not systematically jam the THSA. In addition, laboratory te~ts have confirmed that the SLP will only withstand the loads for a limitedjperiod of time. This condition of PLP failure dur1ingan extended period of lime, ifnot detected and corrected, would lead to the rupture ofthe THSA upper attachment and consequent THSA loss of comrr\and, resulting in reduced control of the aeroplane. Forthe reasons staled above, this AD requires repetitive inspections to detect if damage exists to the THSA uppkr attachment and ifthe SLP has been engaged and corrective actions, dependi7g on findings. 19 February 2010 Page 1/2EASAAD No 2010·0019 Required as indic1ted, unless accomplished previously: (1) Within 2 500 IFII9ht Hours (FH) after the effective date ofthis AD and thereafter at intervals nol to exceed 2 500 FH, perform adetailed visual inspection ofIthe THSA upper allachment and screw shaft in accordance with the instructlons of Airbus Service Bulletin (5B) A300-27-0203, as Required Action(s) applicable tolaeroPlane model. and Compliance (2) If, during any inspection as required by paragraph (1) of this AD, metallic Time(s): particles are found orthe inspection result reveals cracks, scratches or missing mat~rial, before next flight, contact Airbus 10obtain approved corrective aclion instructions and accomplish those instructions accordingly. (3) AccomPlish~ent of corrective actions as required by paragraph (2) of this AD does not bonstitute terminating action for the repetitive inspection requirementsiof this AD. Airbus Service B~lIetin A300-27·0203 original issue. Ref. Publications: The use of later a~proved revisions ofthis document is acceptable for compliance with rfquirements of this AD. 1. If requested 1nd appropriately substantiated, EASA can approve Alternative Methods of ~omPliance for this AD. 2 This AD was posted on 04 January 2010 as PAD 10-001 for consultation until 01 February 2010. No comments were received during the consultation Remarks. 3. period. 

# I Enquiries regarding this AD should be referred to the Airworthiness Directives, S~fety Management & Research Section, Certification Directorate, EA5A. E-maii ADs@easa.europa.eu. 4 For any qUeS~iOnconcerning the technicai content of the requirements in this AD, pleake contact: AIRBUS SA$ - EAW (Airworthiness Office, Telephone: 133 5 61 933696, Fax: +33 5 61 934451).

EASA Form 110 Page2/2