EASA AD No.: 2012-0243

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0243

[Correction: 13 November 2012]

Date: 12 November 2012

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:

ROLLS-ROYCE plc

Type/Model designation(s):

Viper Mk. 601-22 engines

TCDS Number: United Kingdom 1038

Foreign AD: Not applicable

Supersedure: None

ATA 72 Engine – Critical Parts – Reduction of Cyclic Life Limits

Manufacturer(s): Rolls-Royce plc

Applicability: Viper Mk. 601-22 engines, all serial numbers.

These engines are known to be installed on, but not limited to, Hawker 

Beechcraft (formerly Hawker Siddeley, Beech Aircraft Corporation) BH.125 and 

HS.125 Series 600, 600A and 600B aeroplanes.

Reason: A review, carried out by Rolls-Royce, of the lives of critical parts of the Viper 

Mk. 601-22 engine, has resulted in reduced cyclic life limits for certain critical 

parts.

Operation of critical parts beyond these reduced cyclic life limits may result in 

part failure, possibly resulting in the release of high-energy debris, which may 

cause damage to the aeroplane and/or injury to the occupants.

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

reduced cyclic life limits for the affected critical parts, i.e. replacement of each 

part before the applicable reduced life limit is exceeded, and replacement of 

those critical parts that have already exceeded the reduced cyclic life limits.

This AD has been republished to correct a typographical error (wrong 

applicable Alert Service Bulletin number) in paragraph (3).
EASA AD No.: 2012-0243

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Effective Date: 19 November 2012

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 30 days after the effective date of this AD, determine the 

accumulated flight cycles (FC) since new for each component as identified 

by Part Number (P/N) in Table 1 of this AD.

Table 1: Critical parts reduced cyclic life limit(s)

Component Name P/N(s) Cyclic Life Limit

Compressor Shaft V900766 20 720 FC

Compressor Rear Stubshaft 

(Centre Bearing Hub)

V900007

V900994

9 600 FC

Combustion Chamber Outer 

Casing

V950013

V950331

32 000 FC

(2) If, as a result of the determination as required by paragraph (1) of this AD,

the accumulated cyclic life since new of one or more of the affected 

components is equal to or exceeds the applicable reduced cyclic life limit 

as specified in Table 1 of this AD, before next flight, replace each affected 

component with a serviceable component, in accordance with the 

instructions of Rolls-Royce plc. Alert Service Bulletin (ASB) 72-A206.

(3) After the determination as required by paragraph (1) of this AD, before 

exceeding the reduced cyclic life limit (since new) as specified in Table 1 of 

this AD, replace each component with a serviceable component in 

accordance with the instructions of Rolls-Royce plc. ASB 72-A206 and,

thereafter, each time before exceeding the reduced cyclic life limit (since 

new) as specified in Table 1 of this AD, as applicable to the component, 

replace each component with a serviceable component in accordance with 

the instructions of Rolls-Royce plc. ASB 72-A206.

(4) From the effective date of this AD, do not install a component having a P/N 

listed in Table 1 of this AD on an engine, unless it has been determined 

that the total accumulated cyclic life since new of the component is less 

than the applicable reduced cyclic life limit as specified in in Table 1 of this 

AD.

Ref. Publications: Rolls-Royce plc. ASB 72-A206 dated November 2012.

The use of later approved revisions of this document 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. 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 question concerning the technical content of the requirement in this 

AD, please contact: Defence Aerospace Communications at

Rolls-Royce plc, P.O. Box 3, Gypsy Patch Lane, Filton, Bristol, BS34 

7QE, The United Kingdom, Telephone +44 (0) 117 9791234,

or via the contact form at

http://www.rolls-royce.com/contact/defence_team.jsp identifying the 

correspondence as being related to Airworthiness Directives.