EASA AD No.: 2010-0196R1 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010–0196R1 

Date: 12 November 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 : 

GE Aviation Systems Ltd, 

 trading as Dowty Propellers 

Type/Model designation(s) :

R321, R324, R333 and R334 propellers 

TCDS Number : United Kingdom (UK) 115, 108 and UK Approval Letters, dated 3 April 1981. 

Foreign AD : Not Applicable 

Supersedure : This AD revises EASA AD 2010-0196 dated 29 September 2010, which 

superseded EASA AD 2009-0147 dated 07 July 2009 and CAA-UK AD 009-05-

2002, 010-05-2002 and 011-05-2002. 

ATA 61 Propellers - Propeller Hub – Inspection / Replacement 

Manufacturer(s): GE Aviation Systems Ltd, trading as Dowty Propellers (formerly Dowty Rotol 

Ltd, Dowty Aerospace Propellers, Dowty Aerospace Gloucester and Dowty 

Propellers) 

Applicability: R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12 and R334/4-82-F/13 

propellers, if fitted with Part Number (P/N) 660709201 hub assemblies. 

These propellers are known to be installed on, but not limited to, M7 

Aerospace (formerly Fairchild Swearingen) SA227-AC, SA227-AT and 

SA227-TT aeroplanes, BAE SYSTEMS Jetstream 31 and 32 aeroplanes, and 

CASA C-212 aeroplanes. 

Reason: Fatigue failure has occurred around the threaded inserts in the rear hub half, 

leading to separation of the R334 propeller on CASA C-212 aeroplanes. 

The affected P/N 660709201 hub is also fitted to propellers installed on BAE 

SYSTEMS Jetstream 31 and 32 aeroplanes, and to those installed on M7 

Aerospace SA227-AC, SA227-AT and SA227-TT aeroplanes. 

This condition, if not detected and corrected, could result in further events of 

propeller separation, possibly resulting in damage to the aeroplane and/or 

injury to person on the ground. 

For the reasons described above, this AD retains the repetitive inspection 

requirements of EASA AD 2009-0147 and CAA UK ADs 009-05-2002, 010-

05-2002 and 011-05-2002, which are superseded, reduces the inspection 

intervals for NDT inspection and introduces an optional terminating action to 
EASA AD No.: 2010-0196R1 

EASA Form 110 Page 2/3 

the inspection requirements of all propellers fitted with hub P/N 660709201. 

This AD has been revised for reasons of standardisation and clarification, to 

confirm that two other CAA UK ADs have been superseded, and to remove 

the flight cycle (FC) inspection requirements for R321, R324 and R333 

propellers. 

Effective Date: Revision 1: 26 November 2010 

Original issue: 13 October 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously. 

(1) Initially, within the time indicated in Table 1 of this AD, as applicable, 

inspect the affected hub assembly P/N 660709201 and, depending on 

findings, accomplish the associated corrective actions, in accordance 

with the instructions of Dowty Alert Service Bulletin (ASB) 61-1119, 61-

A1124, ASB 61-A1125 or ASB 61-A1126, as applicable to propeller 

installation. 

Table 1 

Hub P/N 660709201 Installed on: Compliance Time: 

R334/4-82-F/13 propellers that have not 

been inspected within the last 300 flight 

cycles (FC) or flight hours (FH) prior to 

13 October 2010 [the effective date of 

the original issue of this AD] 

10 FH or 20 days, whichever 

occurs first after 13 October 

2010 [the effective date of the 

original issue of this AD] 

R334/4-82-F/13 propellers, that have 

been inspected within the last 300 FC 

or FH prior to 13 October 2010 [the 

effective date of the original issue of 

this AD] 

300 FH or 300 FC, whichever 

occurs first since the last 

inspection 

R333/4-82-F/12, R321/4-82-F/8 or 

R324/4-82-F/9 propellers, that have not 

been inspected within the last 1 000 FH 

prior to 13 October [the effective date of 

the original issue of this AD] 

50 FH or 60 days, whichever 

occurs first after 13 October 

2010 [the effective date of the 

original issue of this AD] 

R333/4-82-F/12, R321/4-82-F/8 & 

R324/4-82-F/9 propellers, that have 

been inspected within the last 1 000 FH 

prior to 13 October 2010 [the effective 

date of the original issue of this AD] 

1 000 FH since the last 

inspection 

(2) Thereafter, within the intervals specified in Table 2 of this AD, as 

applicable, inspect the affected hub assembly P/N 660709201 and, 

depending on findings, accomplish the associated corrective actions, in 

accordance with the instructions of Dowty Alert Service Bulletin (ASB) 

61-1119, 61-A1124, ASB 61-A1125 or ASB 61-A1126, as applicable to 

propeller installation. 

Table 2 

Propeller installation: Inspection Interval (not to exceed): 

R321/4-82-F/8 

R324/4-82-F/9 

R333/4-82-F/12 

1 000 FH 

R334/4-82-F/13 300 FH or 300 FC, whichever occurs first 
EASA AD No.: 2010-0196R1 

EASA Form 110 Page 3/3 

(3) If, during any inspection as required of this AD, the hub P/N 660709201 

does not meet the criteria for further operation (as defined in the 

applicable Dowty ASB), before next flight, replace the hub with a 

serviceable part. Replacement of a hub as required by paragraph (3) of 

this AD does not constitute terminating action for the repetitive inspection 

requirements of paragraph (2) of this AD. 

(4) From 13 October 2010 [the effective date of the original issue of this AD], 

do not install a hub assembly P/N 660709201 (except zero-time units) on 

any aeroplane, unless it has been inspected and, depending on findings, 

corrected in accordance with the requirements of this AD. 

(5) Modification of an aeroplane by installing new P/N 660717226 hub 

assemblies on both propellers of that aeroplane, in accordance with the 

instructions of the Dowty Service Bulletin (SB) listed in Table 3 of this 

AD, as applicable, constitutes terminating action for the repetitive 

inspection requirements of paragraph (2) of this AD for that aeroplane. 

Table 3 

Propeller installation: Dowty SB: 

R321/4-82-F/8 61-1143 

R324/4-82-F/9 61-1142 

R333/4-82-F/12 61-1144 

R334/4-82-F/13 61-1138 

Ref. Publications: Dowty ASB 61-1119 Revision 5 dated 1 July 2009, and 

Dowty ASB 61-A1124 Revision 2, ASB 61-A1125 Revision 2 and ASB 61-

A1126 Revision 2, all dated 25 August 2010 

Dowty SB 61-1138 dated 8 December 2009, and 

Dowty SB 61-1144, SB 61-1143 and SB 61-1142, all dated 17 May 2010. 

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

compliance with the requirements of this AD. 

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

Alternative Methods of Compliance for this AD. 

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: 

Dowty Propellers, Anson Business Park, Cheltenham Road East, 

Gloucester GL2 9QN, United Kingdom 

Tel +44 (0) 1452 716067 – Fax +44 (0) 1452 716001 

E-mail Mike.Towkan@ge.com