EASA AD No : 2009-0258 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0258 

Date: 10 December 2009 

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 : 

AIRBUS 

Type/Model designation(s) : 

A310 and A300-600 aeroplanes 

TCDS Number : France TCDS No 145 

Foreign AD : Not applicable 

Supersedure : None 

ATA 29 Hydraulic Power – Ram Air Turbine (RAT) Balance Weight Screws 

– Inspection / Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: 

A310 and A300-600 aeroplanes, all certified models, all manufacturer serial 

numbers, if equipped with a Hamilton Sundstrand RAT Turbine Assembly, as 

identified by Part Number (P/N) in Hamilton Sundstrand Service Bulletin (SB) 

730816-29-15 for A310 aeroplanes, and in Hamilton Sundstrand SB 732365-

29-7 for A300-600 aeroplanes. 

Reason: 

Hamilton Sundstrand (HS), the manufacturer of the RAT, reported the failure 

during a wind tunnel test of a balance weight fastening screw on the RAT 

turbine cover. After investigation, it has been discovered that a batch of 

screws, which are used to attach the balance washers of the HS RAT Turbine 

Assembly, has not been subject to the correct heat treatment and are 

consequently exposed to potential fracture. 

This condition, if not corrected, might lead to the ejection of screw heads and 

consequently to the detachment of the associated balance washers. The loss 

of balance washers could increase RAT vibrations, which might lead to a 

possible detachment of RAT parts and consequent loss of RAT functionality. 

The loss of the RAT, in combination with a total engine flame out, could result 

in loss of control of the aeroplane. 

For the reasons described above, this AD requires the identification of the 

affected RAT turbine assemblies and replacement of all balance weight 

screws or, in case balance washer detachment is found, replacement of the 

RAT turbine assembly. 

Effective Date: 24 December 2009 
EASA AD No : 2009-0258 

EASA Form 110 Page 2/2 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Before the next RAT spin test, or within 1 500 flight hours (FH) or 

9 months after the effective date of this AD, whichever occurs first: 

 - Identify the P/N and s/n of the RAT turbine assembly, and 

 - In case the P/N and s/n of the RAT turbine assembly are listed in the 

applicable HS SB, or if the P/N or s/n cannot be identified, inspect the 

RAT turbine assembly in accordance with the instructions of Airbus All 

Operator Telex (AOT) A300-29A6062 or Airbus AOT A310-29A2098, as 

applicable to aeroplane model: 

(1.1) If all balance screws are fitted on the turbine, within 1 500 FH or 

9 months, whichever occurs first after the effective date of this AD, 

either: 

 - replace the RAT turbine assembly, or 

 - replace all balance screws on the RAT turbine assembly. 

(1.2) If one or more screws are fractured but the associated balance 

washers are still fitted on the RAT turbine assembly, before next 

flight, perform one of the actions as specified in paragraph (1.1) of 

this AD. 

(1.3) If one or more screws are fractured and any balance washer is 

missing, before next flight, replace the RAT turbine assembly. 

(2) Within 10 days after accomplishment of the inspection required by 

paragraph (1) of this AD, report the results, including no findings, to 

Airbus. 

(3) After the effective date of this AD, do not install on an aeroplane a RAT 

turbine assembly as identified by P/N in HS SB 730816-29-15 or HS SB 

732365-29-7, as applicable to aeroplane model, unless it has been 

inspected and, if necessary, corrected in accordance with the 

requirements of this AD. 

Ref. Publications: 

Airbus AOT A300-29A6062 at original issue. 

Airbus AOT A310-29A2098 at original issue. 

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

compliance with the requirements of this AD. 

Hamilton Sundstrand SB 730816-29-15. 

Hamilton Sundstrand SB 732365-29-7. 

Remarks :

1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 07 October 2009 as PAD 09-120 for consultation 

until 04 November. No comments were received during the consultation 

period. 

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

Directives, Safety 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: AIRBUS SAS – EAW (Airworthiness Office, 

Telephone: + 33 5 61 93 36 96, Fax: + 33 5 61 93 44 51).