EASA AD No.: 2010-0075 

EASA Form 110 Page 1/3

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0075 

Date: 20 April 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 Airworthiness Directive applies, except in accordance with the requirements of that 

Airworthiness Directive 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 : 

Rolls-Royce Deutschland Ltd & Co KG

Type/Model designation(s) : 

BR700-710 engines 

TCDS Number : EASA.E.018 

Foreign AD : Not applicable 

Supersedure : Not applicable 

ATA 72 Engine – High Pressure (HP) Turbine Discs Stage 1 and 2 

Assembly Life Limits – Modification 

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

Applicability: All BR700-710A1-10 model engines if equipped with HP Turbine Discs 

stage 1 or 2 listed in Table 1 or Table 2 of this AD, 

and 

All BR700-710A2-20 model engines if equipped with HP Turbine Discs 

stage 1 or 2 listed in Table 1 or Table 2 of this AD, 

and 

All BR700-710C4-11 model engines which have hardware configuration 

standard 710C4-11 engraved on the engine data plate (Service Bulletin 

SB-BR700-72-101466 standard not incorporated) and if equipped with HP 

Turbine Discs stage 1 or 2 listed in Table 1 or Table 2 of this AD. 

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: Due to manufacturing problems of BR700-710 HP Stage 1 and 2 Turbine 

Discs it was necessary to re-calculate the Declared Safe Cyclic Life 

(DSCL) for all BR700-710 HP Turbine Discs. The analysis concluded that it 

is required to reduce the approved life limits for the HP Turbine Disc Part 

Numbers (P/N) that are listed in Table 1 and Table 2 of this AD. 

Exceeding the revised approved life limits could potentially result in non-
EASA AD No.: 2010-0075 

EASA Form 110 Page 2/3

contained disc failure. 

This AD requires compliance with the new life limits for replacement of the 

affected HP Stage 1 and 2 Turbine Discs, as necessary (at a cyclic life that 

is lower than the one currently applicable in the Time Limits Manuals) and 

introduction of the new DSCL into the applicable aircraft maintenance 

programme. The revised DSCL are given in the Rolls-Royce Deutschland 

Alert Non-Modification Service Bulletin (NMSB) SB-BR700-72-A900497 

initial issue. 

Effective Date: 04 May 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within one month after the effective date of this AD or upon 

accumulating the new DSCL indicated in Table 1 or 2 of this AD, 

whichever occurs later, and thereafter, at intervals not to exceed the 

new DSCL, replace the HP1 Turbine Disc or the HP2 Turbine Disc, 

as applicable, with a serviceable HP1 Turbine Disc or the HP2 

Turbine Disc, as applicable, in accordance with Rolls-Royce 

Deutschland. NMSB SB-BR700-72-A900497 initial issue. 

(2) Compliance with the requirements of paragraph (1) of this AD can be 

demonstrated by: 

(2.1) Revising as follows, unless accomplished previously, the 

approved Aircraft Maintenance Programme from which the 

Operator or the Owner ensures the continuing airworthiness of 

each operated aeroplane: 

Incorporate the new DSCL and associated aircraft 

airworthiness limitations specified in the Rolls-Royce 

Deutschland. NMSB SB-BR700-72-A900497 initial issue. 

and 

(2.2) Complying with the approved Aircraft Maintenance Programme 

as described in paragraph (2.1) of this AD. 

(3) After the effective date of this AD, do not install any HP1 Turbine 

Disc or HP2 Turbine Disc unless in compliance with paragraph (1) of 

this AD. 

Ref. Publications: Time Limits Manual (TLM) T-710-1BR (BR700-710A1-10). 

Time Limits Manual (TLM) T-710-2BR (BR700-710A2-20). 

Time Limits Manual (TLM) T-710-4BR (BR700-710C4-11). 

Rolls-Royce Deutschland Alert NMSB-BR700-72-A900497 initial issue. 

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: 

Rolls-Royce Deutschland Ltd & Co KG 

Eschenweg 11 - 15827 Dahlewitz – Germany 
EASA AD No.: 2010-0075 

EASA Form 110 Page 3/3

Phone: +49 (0) 33 7086 1768 ; Fax: +49 (0) 33 7086 3356 

E-mail: rrd.aog@rolls-royce.com.

Table1: 

Table 2: 

Component Part 

Number 

Engine 

Variant 

Declared Safe Cyclic Life 

(Flight Cycles) 

BRR18291 BR700-710A1-10 9300 

BRR21214 BR700-710A1-10 

BR700-710A2-20 

9600 

BRR22008 

BR700-710A1-10 

BR700-710A2-20 

BR700-710C4-11 

10500 

BRR22009 

BR700-710A1-10 

BR700-710A2-20 

BR700-710C4-11 

10500 

BRR22010 BR700-710A1-10 

BR700-710A2-20 

10500 

HP2 Turbine Disc

BRR22359 BR700-710A1-10 

BR700-710A2-20 

10500 

Component Part 

Number 

Engine 

Variant 

Declared Safe Cyclic Life 

(Flight Cycles) 

BR700-710A1-10 6075 BRR21215 

BR700-710A2-20 5950 

BRR22005 BR700-710A1-10 

BR700-710A2-20 6200 

BRR22006 BR700-710A1-10 

BR700-710A2-20 6200 

BRR22007 BR700-710A1-10 

BR700-710A2-20 6200 

BRR22358 BR700-710A1-10 

BR700-710A2-20 6200 

BRR23864 BR700-710A1-10 

BR700-710A2-20 6200 

BRR23884 BR700-710A1-10 

BR700-710A2-20 6200 

BRR23885 BR700-710A1-10 

BR700-710A2-20 6200 

BRR23952 

BR700-710A1-10 

BR700-710A2-20 

BR700-710C4-11 

6200 

BRR23953 

BR700-710A1-10 

BR700-710A2-20 

BR700-710C4-11 

6200 

HP1 Turbine Disc

BRR23954 BR700-710A1-10 

BR700-710A2-20 6200