EASA AD No.: 2010-0077 

EASA Form 110 Page 1/2

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0077 

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 - General – Change of Life Cycle Counting Method for 

Touch-and-Go and Overshoot 

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

Applicability: All BR700-710A1-10 model engines. 

All BR700-710A2-20 model engines. 

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). 

All BR700-710C4-11 model engines which 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: Analysis of service data carried out by Rolls-Royce Deutschland has 

shown that the effect of touch-and-go and overshoot on life cycle counting 

is higher than anticipated. Therefore, the life cycle counting method for 

touch-and-go and overshoot as defined by the Time Limits Manual needs 

to be changed to reflect this higher effect on life. 

This AD requires a change of the life cycle counting method for touch-andgo and overshoot for all critical parts and the Low Pressure (LP) 

compressor blades as specified in the Rolls-Royce Deutschland Alert 

NMSB-BR700-72-A900504 Revision 1. The chapter 05-00-01 and 05-00-
EASA AD No.: 2010-0077 

EASA Form 110 Page 2/2

02 of the applicable Time Limits Manuals will be revised accordingly. 

Note: An overshoot is the phase of a flight wherein a landing approach of 

an aircraft is not continued to the touch-down point. 

Effective Date: 04 May 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 4 months after the effective date of this AD, the calculation of 

lives for every touch-and-go and overshoot of all critical parts and LP 

compressor blades must be done in accordance with Rolls-Royce 

Deutschland Alert NMSB-BR700-72-A900504 Revision 1, paragraph 

3.A. 

(2) Within 4 months after the effective date of this AD, determine the 

number of touch-and-go’s and overshoots that each individual critical 

part (except the fan shaft and LP turbine rotor shaft) has experienced 

since entry into service in accordance with Rolls-Royce Deutschland 

Alert NMSB-BR700-72-A900504 Revision 1, paragraph 3.B. 

(2.1) If the number of touch-and-go’s and overshoots on an individual 

critical part is less than one percent of the total number of flight 

cycles (FC), no further action is required by this AD, in 

accordance with Rolls-Royce Deutschland Alert NMSB-BR700-

72-A900504 Revision 1, paragraph 3.B. 

(2.2). If the number of touch-and-go’s and overshoots on an 

individual critical part is more than one percent of the total 

number of FC, disregard the previous calculations of life on that 

individual critical part and retrospectively re-calculate the 

accumulated FC of that individual critical part by addition of one 

FC for every touch-and-go and overshoot to the total number of 

FC, in accordance with Rolls-Royce Deutschland Alert NMSBBR700-72-A900504 Revision 1, paragraph 3.B.

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). 

Supplementary Time Limits Manual (TLM) T-710-5BR (710C4-11/10 only) 

Rolls-Rolls-Royce Deutschland Alert NMSB-BR700-72-A900504 Rev. 1. 

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 

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

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