EASA AD No.: 2010-0120 

EASA Form 110 Page 1/3

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0120 

Date: 21 June 2010 

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) : 

A318, A319, A320, and A321 aeroplanes 

TCDS Number : EASA.A.064 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2009-0259 dated 10 December 2009. 

ATA 29 Hydraulic Power – Hamilton Sundstrand Ram Air Turbine Balance 

Weight Screws – Inspection / Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: 

Airbus Model A318-111, A318-112, A318-121, and A318-122 aeroplanes; 

Model A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-

132, and A319-133 aeroplanes; Model A320-211, A320-212, A320-214, A320-

215, A320-216, A320-231, A320-232, and A320-233 aeroplanes, and Model 

A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231 

and A321-232 aeroplanes, that are equipped with a Hamilton Sundstrand Ram 

Air Turbine (RAT) model ERPS08M as identified by Part-Number (P/N) in 

Hamilton Sundstrand Service Bulletin (SB) ERPS08M-29-8 original issue dated 

17 June 2009. 

Reason: 

Hamilton Sundstrand (HS) reported the failure of a balance weight fastening 

screw on the RAT turbine cover during a wind tunnel test. After investigation, it 

has been discovered that a batch of screws, used to attach the balance 

washers of the RAT Turbine assembly, has not received the correct heat 

treatment, making them more subject to a potential fracture. 

This condition, if left uncorrected, could lead to the ejection of screw heads and 

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

would increase RAT vibrations, which could lead to a possible detachment of 

RAT parts and loss of RAT functionality. The loss of the RAT, in combination 

with a double engine failure, or a total loss of normal electrical power 

generation, could result in loss of control of the aeroplane. 

For the reasons described above, EASA AD 2009-0259 was issued in 

December 2009 to require the replacement of all balance weight screws on the 

affected RAT turbine assemblies, or replacement of the RAT, if any balancing 
EASA AD No.: 2010-0120 

EASA Form 110 Page 2/3

washer was found missing. 

This AD retains some of the requirements of AD 2009-0259, which is 

superseded, and corrects its applicability by adding Airbus model A320-215 

and A320-216 aeroplanes which were inadvertently omitted. Also, this AD 

requires the replacement of the set of balance weights screws before the next 

operational or functional check of the RAT assembly.

Effective Date: 05 July 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated. 

(1) Unless previously accomplished before the effective date of this AD: 

 Before the next Ram Air Turbine (RAT) operational/functional check, or 

within 3 000 flight hours (FH) or 12 months after 24 December 2009 (the 

effective date of AD 2009-0259), whichever occurs first, inspect the RAT 

to determine its P/N and serial number (s/n), in accordance with paragraph 

4.3.1 of the Airbus AOT (All Operators Telex) No.A320-29A1150 original 

issue. 

 Instead of inspecting the Ram Air Turbine as required by paragraph (1) of 

this AD, a review of the aeroplane maintenance records along with any 

other applicable data is acceptable, if the P/N and s/n of the RAT 

assembly, installed on the aeroplane, can be positively determined from 

that review. 

(2) If the RAT, identified as required by paragraph (1) of this AD, is listed in 

the Hamilton Sundstrand SB ERPS08M-29-8 original issue, or if its P/N or 

s/n cannot be positively determined, inspect the RAT for missing/broken 

balance weight screw(s) in accordance with the instructions of paragraph 

4.3.1 of the Airbus AOT No.A320-29A1150 original issue. 

(2.1) If any damage is found (missing balancing weight(s), fractured 

screw(s)...): before further flight, accomplish all corrective actions in 

accordance with the instructions of paragraph 4.3.1 of the Airbus 

AOT No.A320-29A1150 original issue. 

Note 1: A single missing balancing weight necessitates the RAT removal for 

new balancing of the assembly after replacing the set of defective balance 

weight screws. 

(2.2) If no damage is found: Before the next RAT operational/functional 

check, or within 3 000 FH or 12 months after 24 December 2009, 

whichever occurs first, replace the balance weight screws in 

accordance with the instructions of paragraph 4.3.1 of the Airbus 

AOT No.A320-29A1150 original issue. 

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

as identified by P/N and s/n in Hamilton Sundstrand SB No.ERPS08M-29-

8 original issue, unless it has been reworked to satisfy the requirements of 

this AD. 

Note 2: RATs that are the subject of this AD, and that have been reworked in 

accordance with the accomplishment instructions of Hamilton Sundstrand 

Service Bulletin No. ERPS08M-29-8, have the symbol ’29-8’ engraved or vibroetched on their identification plate or nameplate. 

Ref. Publications: 

Airbus AOT (All Operators Telex) No.A320-29A1150 original issue. 

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 

Hamilton Sundstrand Service Bulletin No. ERPS08M-29-8 original issue. 

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

Alternative Methods of Compliance for this AD. 
EASA AD No.: 2010-0120 

EASA Form 110 Page 3/3

2. The required actions and the risk allowance have granted the issuance of a 

Final AD with Request for Comments, postponing the public consultation 

process after publication. 

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 – Airworthiness Office – EAS Fax +33 5 61 93 44 51, 

E-mail: account.airworth-eas@airbus.com.