EASA AD No.: 2010-0188

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0188

Date: 20 September 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 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD unless other wise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption].



### Type Approval Holder’s Name :
Rolls-Royce plc Type/Model designation(s) :

RB211 Trent 800 series engines

TCDS Number : 

### UK CAA 1051

Foreign AD : Not applicable

Supersedure : None



### ATA 73 Engine – Fan Case Low Pressure Fuel Tubes and Clips - Inspection/Replacement

Manufacturer(s): Rolls-Royce plc

Applicability: Models RB211 Trent 895-17, 892-17, 892B-17, 884-17, 884B-17, 877-17 and 875-17. These engines are known to be installed on, but not limited to, Boeing 777 series aeroplanes.

Reason: Fuel leaks from the engine have occurred in -service due to damage to sections of the fan case Low Pressure (LP) fuel tub es which run between the Low Pressure and the High Pressure (HP) fuel pumps. This damage has been caused by frettage between the securing clips and the tube outer surface, which has caused localised thinning of the tube wall thickness. The thinning of the tube wall causes the tube to fractu re and fuel loss to occur. In one case, fuel loss in excess of 10 000 pounds (lbs ) occurred. Fuel leaks, if not detected early enough or if not correctly managed, could lead to potential unsafe conditions such as critica l fuel unbalance or in-flight fuel starvation. Fuel leak detection and the associ ated aeroplanes procedures can be complex, leading to some flight c rews failing to detect and/or address such situations. EASA has initiated reviews of fuel leak management procedures. This AD is issued as a preca utionary measure to mitigate the risk of in-flight fuel starvation iden tified as a result of the existence of a known cause of fuel leaks. This AD requires inspection and, if necessary, repl acement of fan case LP fuel tubes and clips.EASA AD No.: 2010-0188

EASA Form 110 Page 2/2 Effective Date: 04 October 2010

Required Action(s) and Compliance Time(s): Required as indicated: (1) Initial Inspection Inspect and, if necessary, replace the fan case LP fuel tubes (Part Numbers (P/N) FK22617, FK19213 and FK23986) and the relevant associated clips, in accordance with Rolls-Royce NM SB 73-D685 issue 3 before the accumulation of 3 000 hours since new, or 3 000 hours since last inspection accomplished before the effec tive of the effective date of this AD in accordance with Rolls-Royce NMSB 73-D685 issue 3 or within 2 000 hours after the effective date of t his AD, whichever occurs latest. (2) Repetitive Inspection Following accomplishment of the initial inspection in compliance with the requirements of paragraph (1) of this AD, repeat th e inspection at intervals not exceeding 3 000 hours, and, if necess ary, replace the fan case LP fuel tubes (P/N FK22617, FK19213 and FK2398 6) and the relevant associated clips in accordance with. Rolls -Royce NMSB 73- D685 issue 3. (3) Replacement of the fan case LP fuel tubes (P/N FK22617, FK19213 and FK23986) and the relevant associated clips with ser viceable parts does not constitute terminating action for the inspectio n requirements of this AD.

Ref. Publications: Rolls-Royce RB211 Propulsion Sys tem Non Modification Service Bulletin RB211-73-D685 revision 3 dated 18 August 2009. The use of later approved revisions is acceptable f or 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 issued as PAD 10-013 on 21 January 2 010 for consultation until 18 February 2010. This AD has been changed in comparison with the PAD 10-013, introducing less stringent requirem ents. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 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 questions concerning the technical conte nt of the requirements in this AD, please contact: Your designated Rolls-Royce representative or downl oad the publication from your Aeromanager account at www.aeromanager.com . If you do not have a designated representative or Aeromanager account, please contact Corporate Communications at Rolls-Royce plc. PO Box 31, Derby, DE24 8BJ, United Kingdom. Phone: +44 (0) 133 2 242424, or email from http://www.rolls-royce.com/contact/civil_team.jsp identifying the correspondence as being related to Airworthiness Directives

.