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 b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participat e 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 b e ensured by accomplishing any applicable ADs. Cons equently, no person may operate an aircraft to which an Airworthiness D irective applies, except in accordance with the req uirements 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, Ar ticle 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 Me thod for

Touch-and-Go and Overshoot

Manufacturer(s): Rolls-Royce Deutschland Ltd & Co K G
Applicability: All BR700-710A1-10 model engines. All BR700-710A2-20 model engines. All BR700-710C4-11 model engines which have hardwar e 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 hardwar e configuration standard 710C4-11/10 engraved on the engine data pl ate (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 Rol ls-Royce Deutschland has shown that the effect of touch-and-go and overshoot on life cycle counting is higher than anticipated. Therefore, the life cyc le counting method for touch-and-go and overshoot as defined by the Time L imits Manual needs to be changed to reflect this higher effect on life

. This AD requires a change of the life cycle countin g method for touch-andgo and overshoot for all critical parts and the Low Pressure (LP) compressor blades as specified in the Rolls-Royce D eutschland 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 re vised accordingly. Note: An overshoot is the phase of a flight wherein a landing approach of an aircraft is not continued to the touch-down poin t.
Effective Date: 04 May 2010

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 4 months after the effective date of thi s AD, the calculation of lives for every touch-and-go and overshoot of all c ritical parts and LP compressor blades must be done in accordance with R olls-Royce Deutschland Alert NMSB-BR700-72-A900504 Revision 1, paragraph 3.A. (2) Within 4 months after the effective date of thi s AD, determine the number of touch-and-go’s and overshoots that each i ndividual critical part (except the fan shaft and LP turbine rotor sha ft) has experienced since entry into service in accordance with Rolls-R oyce Deutschland Alert NMSB-BR700-72-A900504 Revision 1, paragraph 3 .B. (2.1) If the number of touch-and-go’s and overshoot s 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 overshoo ts on an individual critical part is more than one percent o f the total number of FC, disregard the previous calculations o f life on that individual critical part and retrospectively re-cal culate the accumulated FC of that individual critical part by addition of one FC for every touch-and-go and overshoot to the tota l number of FC, in accordance with Rolls-Royce Deutschland Aler t NMSBBR700-72-A900504 Revision 1, paragraph 3.B.
Ref. Publications: Time Limits Manual (TLM) T-710-1 BR (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 (7 10C4-11/10 only) Rolls-Rolls-Royce Deutschland Alert NMSB-BR700-72-A 900504 Rev. 1. The use of later approved revisions of these docume nts 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. The required actions and the risk allowance have granted the issuance of a Final AD with Request for Comments, p ostponing the public consultation process after publication. 3. Enquiries regarding this AD should be referred t o the Airworthiness Directives, Safety Management & Research Section, C ertification 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: 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



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