EASA AD No.: 2007-0223R4

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2007-0223R4

Date: 30 September 2013

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 EU 748/2012, Part 21.A.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].

Design Approval Holder’s Name:

GE Aviation Systems,

trading as DOWTY PROPELLERS

Type/Model designation(s):

R408 propellers

TCDS Number: EASA P.002

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2007-0223R3 dated 19 September 2013.

ATA 61 Propellers – Blades Metallic Leading Edge Guard – Inspection

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

Ltd, Dowty Aerospace Propellers, Dowty Aerospace Gloucester or Dowty 

Propellers)

Applicability: All R408/6-123-F/17 propellers, all serial numbers, if equipped with blade 

assemblies Part Number (P/N) 697071200-18, P/N 697071210-18, P/N 

697071227-18, P/N 697071240-18, P/N 697071245-18, or

P/N 697071257-18.

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

Inc. (formerly de Havilland Canada) Models DHC-8-400, DHC-8-401 and 

DHC-8-402 aeroplanes.

Reason: Three in-service occurrences have been reported where the propeller 

blades lost the metallic leading edge (L/E) guard. The investigation results 

showed that these events were caused by deterioration of the bonding 

between blade and leading edge guard.

This condition, if not detected and corrected, could lead to additional events 

of in-flight loss of the L/E guard, possibly resulting in damage to the 

aeroplane, or injury to occupants or persons on the ground.

To address this potential unsafe condition, EASA issued Emergency AD 

2007-0223-E to require repetitive inspections of the blade L/E guards for 

correct bonding until they accumulate more than 1 200 flight hours (FH) time 

in service.
EASA AD No.: 2007-0223R4

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Revision 1 of this AD was issued to clarify the required inspections and 

follow-up actions depending on findings and to make reference to the latest 

Dowty Alert Service Bulletin (ASB) revision. Revision 2 was issued to 

specify that blades repaired at the tip are only allowed to continue up to 500 

hours in service after repair. This limitation was already in the original Dowty 

ASB and a Note was added to ‘Required Action(s)’ section to avoid the 

impression that the AD does not impose the same limitation.

Revision 3 of this AD is issued to introduce an optional terminating action for 

the repetitive inspection requirements of this AD.

Revision 4 of this AD is issued to highlight that accomplishment of the 

optional termination action in accordance with the instructions of Dowty SB

D8400-61-70 or SB D8400-61-83 at a previous revision is acceptable.

Effective Date: Revision 4: 30 September 2013

Revision 3: 19 September 2013

Original issue, R1 and R2: 17 August 2007

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the next 50 FH or within 1 month after 17 August 2007 [the 

effective date of the original issue of this AD], whichever occurs first, 

inspect each affected blade assembly where the bonded metallic L/E 

guard has accumulated 1 200 FH or less since installation, in 

accordance with the instructions of Dowty Propellers ASB No. D8400-

61-A69.

(2) Within 50 FH or 1 month after installing a replacement blade, inspect 

the affected blade assembly where the bonded metallic L/E guard has 

accumulated 1 200 FH or less since installation, in accordance with the 

instructions of Dowty Propellers ASB No. D8400-61-A69.

(3) After the inspection as required by paragraph (1) or (2) of this AD, as 

applicable, at intervals not to exceed 100 FH, repeat the inspection of 

each affected blade assembly in accordance with the instructions of 

Dowty Propellers ASB No. D8400-61-A69.

When the bonded blade L/E guard of an affected blade assembly has 

accumulated more than 1 200 FH since installation, no further 

inspections are required on that blade assembly.

(4) When, during any of the inspections as required by paragraph (1), (2) or 

(3) of this AD, disbonding is found, apply the criteria as indicated in 

Appendix A of Dowty Propellers ASB No. D8400-61-A69 Revision 1 

and, depending on findings, within the applicable time period, repair or 

replace the affected blade assembly, in accordance with the instructions 

of Dowty Propellers ASB No. D8400-61-A69 Revision 1.

Note: Blades that have been repaired within the first 101,6 mm (4.0 inches) 

of the tip of the blade as specified in Appendix D of the referenced ASB are 

allowed to continue in service for another 500 FH after accomplishment of 

the repair. Repair does not terminate the repetitive inspection requirements 

of paragraph (3) of this directive.

(5) Modification of an affected propeller in accordance with Dowty 

Propellers Service Bulletin (SB) D8400-61-70, or in accordance with 

Dowty Propellers SB D8400-61-83, as applicable, constitutes 

terminating action for the repetitive inspections required by paragraph 

(3) of this AD for that propeller.

Ref. Publications: Dowty Propellers ASB D8400-61-A69, initial issue dated 15 August 2007, or 

Revision 1 dated 18 September 2007.

Dowty Propellers SB D8400-61-70 Original issue dated 07 September 2007, 
EASA AD No.: 2007-0223R4

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Revision 1 dated 08 October 2007, Revision 2 dated 01 November 2012, 

Revision 3 dated 03 June 2013.

Dowty Propellers SB D8400-61-83 Original Issue dated 19 February 2009, 

Revision 1 dated 15 June 2009, Revision 2 dated 25 January 2010, 

Revision 3 dated 01 November 2012, Revision 4 dated 03 June 2013.

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 accept 

Alternative Methods of Compliance for this AD.

2. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication

3 Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any questions 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.