EASA AD No.: 2012-0166

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0166 

Date: 30 August 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 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]. 

Design Approval Holder’s Name: 

Rolls-Royce Deutschland Ltd & Co KG 

Type/Model designation(s): 

BR700-710 engines

TCDS Number: EASA.E.018 

Foreign AD: Not applicable 

Supersedure: None 

ATA 72 Engine – High Pressure Turbine Rotor Disc Stage 1 and Stage 2 

Life Limitation – Implementation 

Manufacturer(s): Rolls-Royce Deutschland Ltd & Co KG (RRD) 

Applicability: BR700-710A1-10 and BR700-710A2-20 engines, all serial numbers (s/n). 

BR700-710C4-11 engines, all s/n which 

(a) have hardware configuration standard 710C4-11 engraved on the engine 

data plate (RRD Service Bulletin (SB) SB-BR700-72-101466 standard not 

incorporated), or 

(b) have hardware configuration standard 710C4-11/10 engraved on the 

engine data plate (Service Bulletin SB-BR700-72-101466 standard 

incorporated). 

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

GV-SP (G500, G550) and Bombardier BD-700-1A10, BD-700-1A11 series 

aeroplanes. 

Reason: The results of a recent quality review of high pressure turbine (HPT) Stage 1 

and Stage 2 discs identified potential for steel inclusions in some production 

scale of these parts. Further investigation concluded that all affected parts were 

manufactured by Udimet 720i and melted by a certain supplier. Subsequent 

evaluation concluded that the affected parts life limitation values declared in the 

engine Time Limits Manual cannot be supported for discs with potential steel 

inclusion. 

This condition, if not corrected, could lead to an uncontained HPT disc failure, 

potentially resulting in damage to, and/or reduced control of the aeroplane. 

To address this unsafe condition, RRD issued Alert Non-Modification SB-
EASA AD No.: 2012-0166

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BR700-72-A900508 to introduce new life limitations for certain HPT Stage 1 

and 2 discs, identified by Part Number (P/N) and serial number (s/n) to reduce 

approved life limitations specified in the engine Time Limits Manuals. 

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

restrictive life limits for the affected parts. 

Effective Date: 13 September 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) After the effective date of this AD, before or upon reaching the applicable 

Declared Safe Cyclic Life (DSCL) limit, in engine flight cycles (EFC) as 

defined in Table 1 or Table 2 of this AD, as applicable, to allow operation 

of an engine with installed HPT Stage 1 disc P/N BRR23952 and HPT 

Stage 2 disc P/N BRR22008, as listed by serial numbers (S/N) in Table 1 

and Table 2 of this AD, replace each HPT Stage 1 and HPT Stage 2 

discs with serviceable parts in accordance with the instructions of RRD 

SB-BR700-72-A900508: 

Table 1 – HPT Stage 1 disc P/N BRR23952 

s/n 

DSCL Limit when installed in A1-

10, A2-20 and 

C4-11(without Mod 72-101466) 

engine models 

DSCL Limit when 

installed in C4-11 

with Mod 72-

101466 

LDRQA05841

3 000 EFC 2 300 EFC 

LDRQA05719

LDRQA05720

LDRQA05727

LDRQA05722

LDRQA05723

LDRQA05726

LDRQA05721

LDRQA05842

LDRQA05724

Table 2 - HPT Stage 2 P/N BRR22008 

s/n 

DSCL Limit when installed in 

A1-10, A2-20 and C4-11(without 

Mod 72-101466) engine models 

DSCL Limit when 

installed in C4-11 

with Mod 72-

101466 

LDRQA05944

LDRQA05945 3 000 EFC 2 300 EFC 

LDRQA05791
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(2) From the effective date of this AD, do not install a HPT Stage 1 disc P/N 

BRR23952 and HPT Stage 2 disc P/N BRR22008, as identified by S/N in 

Tables 1 and 2 of this AD, in the same engine Turbine Module. 

(3) From the effective date of this AD, do not install a Turbine Module in an 

engine and engine on an aeroplane unless in compliance with 

requirements of this AD. 

(4) Compliance with the requirements of paragraphs (1), (2) and (3) of this 

 AD can be demonstrated by: 

(4.1) Revising as follows the approved Aircraft Maintenance 

Programme (AMP) on the basis of which the operator or the 

owner ensures the continuing airworthiness of each operated 

aeroplane: 

Incorporate the applicable airworthiness limitations as specified 

by this AD 

and 

(4.2) Complying with the approved AMP described in paragraph (4.1) 

of this AD. 

Ref. Publications: Rolls-Royce Deutschland Alert NMSB BR700-72-A900508 at initial issue. 

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. This AD was posted on 31 July 2012 as PAD 12-101 for consultation until 

31 August 2012. No comments were received during the consultation 

period. 

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 requirements in 

this AD, please contact: rrd.techhelp@rolls-royce.com, 

Phone : +49 (0) 337086 1200, Fax : +49 (0) 337086 1212.