EASA AD No.: 2014-0249R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0249R1

Date: 18 February 2015

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 EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 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 AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name:

ROLLS-ROYCE plc

Type/Model designation(s):

RB211-535E4 engines

TCDS Number: EASA.E.061

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2014-0249 dated 19 November 2014.

ATA 05, 72 Time Limits / Maintenance Checks – Engine Critical Parts –

Reduction of Cyclic Life Limits

Manufacturer(s): Rolls-Royce plc (RR)

Applicability: RB211-535E4-37, RB211-535E4-B-37 and RB211-535E4-C-37 engines, all 

manufacturer serial numbers.

These engines are known to be installed on, but not limited to, Boeing 757 

aeroplanes.

Reason: An engineering analysis, carried out by RR, of the lives of critical parts of the 

RB211-535E4-37 engine, has resulted in reduced cyclic life limits for certain 

high pressure (HP) turbine discs. The reduced limits are published in the RR

RB211-535E4-37 Time Limits Manual (TLM): 05-10-01-800-000, current 

Revision dated July 2014.

Operation of critical parts beyond these reduced cyclic life limits may result in 

part failure, possibly resulting in the release of high-energy debris, which may 

cause damage to the aeroplane and/or injury to the occupants. 

To address this potential unsafe condition, EASA issued AD 2014-0249 to 

require implementation of the reduced cyclic life limits for the affected critical 

parts, i.e. replacement of each part before the applicable reduced life limit is 

exceeded, and replacement of those critical parts that have already exceeded 

the reduced cyclic life limits.

Since that AD was issued, it was determined that the affected discs are not 

eligible for installation on Model RB211-535C-37 engines. In addition, the AD 

did not explicitly include reference to the necessary recalculation of remaining 

life for a part that has been transferred from one engine Model to another.
EASA AD No.: 2014-0249R1

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For the reasons described above, this AD is revised to remove the Model 

RB211-535C-37 from the Applicability, and to amend paragraph (3) for 

clarification.

Effective Date: Revision 1: 18 February 2015

Original issue: 03 December 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) From 03 December 2014 [the effective date of the original issue of this 

AD], except as specified in paragraphs (2) and (3) of this AD, replace 

each component with a serviceable part before exceeding the applicable 

life limit, as specified in RR RB211-535E4-37 TLM 05-10-01-800-000, 

Revision dated 01 July 2014 (hereafter referred to as ‘the TLM’), as 

applicable to engine Model and configuration.

Note 1: For the purpose of this AD, a serviceable part is one having a P/N as 

listed in the TLM with a total accumulated cyclic life less than the applicable life 

limit as specified in the TLM.

(2) Within 30 days after 03 December 2014 [the effective date of the original 

issue of this AD], determine the Part Number (P/N) of the HP turbine disc 

installed on the engines and the accumulated flight cycles (FC) since new 

for each HP turbine disc.

(3) If, as a result of the determination as required by paragraph (2) 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 the applicable life limit specified in Table 

1 of this AD, as applicable, or within 25 FC after 03 December 2014 [the 

effective date of the original issue of this AD], whichever occurs later, 

replace the affected disc with a serviceable part.

For an affected HP turbine disc, installed on a Model RB211-535E4-B-37 

or RB211-535E4-C-37 engine, which was previously installed on a Model

RB211-535E4-37 engine operated in accordance with flight profile A, task

05-00-01-800-00 of the TLM specifies how the equivalent cycles since 

new must be re-calculated to determine the applicable life limit as 

specified in Table 1 of this AD.

Table 1 – Affected HP Turbine Discs and associated Cyclic Life Limits

P/N Cyclic Life Limit

UL27681 Flight Plan A: 

19 500 FC

Flight Plan B:

UL39767 14 700 FC

(4) Within 12 months after 03 December 2014 [the effective date of the 

original issue of this AD], revise the approved aircraft maintenance 

programme (AMP), on the basis of which the operator or the owner 

ensures the continuing airworthiness of each operated aeroplane, by 

incorporating the limitations, tasks and associated thresholds and 

intervals described in the TLM.

(5) For an AMP that, on 03 December 2014 [the effective date of the original 

issue of this AD], is already updated to incorporate the maintenance tasks 

and life limitations as specified in the RR RB211-535E4-37 TLM 05-10-01-

800-000, Revision dated 01 April 2014, the more restrictive limitations, as 

defined in Table 1 of this AD, must be incorporated into the AMP to 

comply with paragraph (4) of this AD.

(6) Compliance with the requirements of paragraph (4) of this AD constitutes 

compliance with the requirements of paragraphs (1), (2) and (3) of this 

AD. After revising the AMP, as required by paragraph (4) or (5) of this AD,

as applicable, it is not necessary that accomplishment of individual tasks 
EASA AD No.: 2014-0249R1

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is recorded for demonstration of AD compliance on a continued basis.

Note 2: For affected engines installed on aeroplanes registered in Europe, 

complying with the approved AMP as specified in paragraph (3) of this AD is 

required by Commission Regulation (EU) No 1321/2014, Part M.A.301, 

paragraph 3.

Ref. Publications: RR RB211-535E4-37 TLM 05-10-01-800-000, Revision dated 01 July 2014.

The use of later approved variations or revisions of this document 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 original issue of this AD was posted on 20 October 2014 as PAD 14-

152 for consultation until 17 November 2014. No comments were received 

during the consultation period.

3. Enquiries regarding this AD should be referred to the Safety Information 

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 your designated Rolls-Royce representative, or

download 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.,

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.