EASA AD No : 2009-0260 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0260 

[Correction: 14 December 2009] 

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) : 

A330 and A340 aeroplanes 

TCDS Number : EASA.A.004, EASA.A.015 

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: 

Airbus A330-201, A330-202, A330-203, A330-223, A330-243, A330-301, 

A330-302, A330-303, A330-321, A330-322, A330-323, A330-341, A330-342 

and A330-343 aeroplanes, all manufacturer serial numbers if equipped with a 

Hamilton Sundstrand RAT turbine lower gear box assembly, as identified by 

Part Number (P/N) in Hamilton Sundstrand Service Bulletin (SB) ERPS06G29-6. 

Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313 

aeroplanes, all manufacturer serial numbers if equipped with Hamilton 

Sundstrand RAT turbine lower gear box assembly, as identified by P/N in 

Hamilton Sundstrand SB ERPS06G-29-6. 

Airbus A340-541, A340-542, A340-642 and A340-643 aeroplanes, all 

manufacturer serial numbers if equipped with Hamilton Sundstrand RAT 

turbine lower gear box assembly, as identified by P/N in Hamilton Sundstrand 

SB ERPS33G-29-1. 

Reason: 

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

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

test. After investigation, it has been discovered that a batch of screws, which 

are used to attach the balance washers of the Hamilton Sundstrand RAT 

turbine lower gear box assembly, has not been subject to the correct heat 

treatment and the screws 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 
EASA AD No : 2009-0260 

EASA Form 110 Page 2/3 

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

possible detachment of RAT parts, and thus to damage to the aeroplane and 

risk of injury to persons on the ground. 

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

affected RAT turbine lower gear box assemblies and replacement of all 

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

of the RAT turbine lower gear box assembly. 

This AD has been republished to correct some editorial errors. 

Effective Date: 24 December 2009 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Before the next RAT spin test, or within 3 000 flight hours (FH) or 

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

 - Identify the P/N and serial number (s/n) of the RAT turbine lower gear 

box assembly, and 

 - In case the P/N and s/n of the RAT turbine lower gear box assembly are 

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

inspect the RAT turbine lower gear box assembly in accordance with the 

instructions of Airbus All Operator Telex (AOT) A330-29A3110 or Airbus 

AOT A340-29A4085 or Airbus AOT A340-500/600 29A5015, as applicable 

to aeroplane model: 

(1.1) If all balance screws are fitted on the turbine, within 3 000 FH or 

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

either: 

 - replace the RAT turbine lower gear box assembly, or 

 - replace all balance screws on the RAT turbine lower gear box 

assembly. 

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

washers are still fitted on the RAT turbine lower gear box assembly, 

then 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 lower gear box 

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 lower gear box assembly as identified by P/N in HS SB 

ERPS06G-29-6 or HS SB ERPS33G-29-1, 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 A330-29A3110 at original issue. 

Airbus AOT A340-29A4085 at original issue. 

Airbus AOT A340-500/600-29A5015 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 ERPS06G-29-6. 

Hamilton Sundstrand SB ERPS33G-29-1. 

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

Alternative Methods of Compliance for this AD. 
EASA AD No : 2009-0260 

EASA Form 110 Page 3/3 

2. This AD was posted on 07 October 2009 as PAD 09-122 for consultation 

until 04 November. The Comment Response Document can be found at 

http://ad.easa.europa.eu/. 

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 questions concerning the technical content of the requirements in 

this AD, please contact: AIRBUS – Airworthiness Office – EAL; 

E-mail: A330-A340@airbus.com.