EASA AD No.: 201 3

- 0246

TE. CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2013

- 0246

Date: 10 October 2013

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 E U 748/2012 , Part 21

. A.3B. In accordan ce 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 ope rate an aircraft to which an AD applies, except in accordance with the requirements of that AD

, 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].



### Design Appr oval Holder’s Name :
ROLLS

- ROYCE plc Type/Model designation(s) :
RB211

- 524 engines

TCDS Number s : United Kingdom 10 46 and 1048

F oreign AD: N ot applicable

Supersedure: N one



### ATA 72 Engine

– High Pressure Compressor Rotor Stage 1 and 2 Disc s
– Re duction of Cyclic Life Limit

Manufacturer(s): Rolls

- Royce plc

Applicability: RB211

- 524G2

- 19, RB211

- 524 G3

- 19, RB211

- 524 H

- 36 and RB211

- 524 H2

- 19 engines, all serial numbers.
These engines are known to be installed on, but not limited to, Boeing 747 and 767 series ae roplanes.

Reason: Rolls

- Royce recently reviewed the cyclic lives of c ritical parts of the RB211

- 524 series engine s , which has resulted in the identification of a reduced cyclic life limit for certain high

- pressure compressor ( HPC ) R otor S tage 1 and 2 Discs

. Operation of c ritical parts beyond the se reduced cyclic life limits could lead to part failure and consequent release of high

- energy debris, possibly resulting in damage to the aeroplane and/or injury to the occupants

. For the reasons described above, t his AD requires replacement of those discs that have already exceeded the reduced cyclic life limit and replacement of all other affected discs before the reduced life limit is exceeded. In addition, this AD requires implementation of the reduced cyclic li fe limit for the affected HPC Rotor Stage 1 and 2 Discs.

Effective Date: 17 October 2013EASA AD No.: 201 3

- 0246

TE. CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 30 days after the effective date of this AD

, determine the Part Number (P/N) of the HPC Rotor Stage 1 and 2 Discs installed on the engines and the accumulated flight cycles ( FC) since new for each HPC Rotor Stage 1 and 2 Disc

.

Table 1

– P/Ns of affected HPC Rotor Stage 1 and 2 Discs

LK70608 UL19877 UL24023
LK76030 UL19878

LK86621 UL19879

(2) If , as a result of the determination as required by paragraph (1) of this AD, a disc is installed with a P/N as listed in Table 1 of this AD, before the accumulated cyclic life exceeds 7 390 FC since new

, or within 25 FC after the effective date of this AD

, whichever occurs later, replace the affected d isc with a serviceable HPC Rotor Stage 1 or 2 Disc , as applicable

. Note: For the purpose of this AD, a serviceable HPC Rotor Stage 1 or 2 Disc is one having a P/N as listed in table 1 of this AD with a total accumulated cyclic life less than 7 390 FC since new , or a HPC Rotor Stage 1 or 2 Disc with another P/N. (3) From the effective date of this AD, each HPC Rotor Stage 1 and Stage 2 Disc having a P/N as listed in Table 1 of this AD must be replaced with a serviceable HPC Rotor Stage 1 or 2 Disc, as applicable, before exceed ing 7 390 FC since new

.

Ref. Public ations: N one.

Remarks: 1. If requested and appropriately substantiated

, EASA can approve Alternative Methods of Compliance for this AD.

2. Based on t he required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments

, postponing the public consultation process until after publication

. 3. Enquiries regarding this A D should be referred to the Safety Information Section, Executive Directorate , EASA. E

- mail : ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirement in this AD, please contact your designated Rolls

- Royce representative, or download the publication from your Aeromanager account at www.aeromanager.com , or contact at Rolls

- Royce plc. Corporat e Communications, P.O. Box 31, Derby, DE24 8BJ, United Kingdom, telephone: +44 (0) 1332 242424, or send an e

- mail through http://www.rolls

- royce.com/contact/civil_team.jsp , identifying the correspondence as being related to Airworthiness Directives

.