EASA AD No.: 2012-0166

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0166

Date: 30 August 2012

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 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 a nd Stage 2 Life Limitation – Implementation

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

Applicability: BR700-710A1-10 and BR700-710A2-20 en gines, all serial numbers (s/n). BR700-710C4-11 engines, all s/n which (a) have hardware configuration standard 710C4-11 e ngraved on the engine data plate (RRD Service Bulletin (SB) SB-BR700-72-1 01466 standard not incorporated), or (b) have hardware configuration standard 710C4-11/1 0 engraved on the engine data plate (Service Bulletin SB-BR700-72-101 466 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-7 00-1A11 series aeroplanes.

Reason: The results of a recent quality review of h igh pressure turbine (HPT) Stage 1 and Stage 2 discs identified potential for steel in clusions in some production scale of these parts. Further investigation conclud ed that all affected parts were manufactured by Udimet 720i and melted by a certain supplier. Subsequent evaluation concluded that the affected parts life l imitation values declared in the engine Time Limits Manual cannot be supported for d iscs 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

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. BR700-72-A900508 to introduce new life limitations for certain HPT Stage 1 and 2 discs, identified by Part Number (P/N) and se rial number (s/n) to reduce approved life limitations specified in the engine T ime Limits Manuals. For the reasons described above, this AD requires t he 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 previous ly: (1) After the effective date of this AD, before or upon reaching the applicable Declared Safe Cyclic Life (DSCL) limit, in engine f light cycles (EFC) as defined in Table 1 or Table 2 of this AD, as applic able, to allow operation of an engine with installed HPT Stage 1 disc P/N BR R23952 and HPT Stage 2 disc P/N BRR22008, as listed by serial numb ers (S/N) in Table 1 and Table 2 of this AD, replace each HPT Stage 1 an d 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

3 000 EFC 2 300 EFC LDRQA05945

LDRQA05791EASA AD No.: 2012-0166

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. (2) From the effective date of this AD, do not inst all a HPT Stage 1 disc P/N BRR23952 and HPT Stage 2 disc P/N BRR22008, as iden tified by S/N in Tables 1 and 2 of this AD, in the same engine Turbi ne Module. (3) From the effective date of this AD, do not inst all a Turbine Module in an engine and engine on an aeroplane unless in complia nce 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 Mai ntenance Programme (AMP) on the basis of which the operator or the owner ensures the continuing airworthiness of each operated aeroplane: Incorporate the applicable airworthiness limitation s 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 NM SB BR700-72-A900508 at initial issue. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA 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 th e consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: rrd.techhelp@rolls-royce.com 

### , Phone : +49 (0) 337086 1200, Fax : +49 (0) 337086 1 212.