Latest Emergency AD:
EASA AD No : 2010-0236-E
EASA Form 111 Page 1/3
EASA EMERGENCY AIRWORTHINESS DIRECTIVE
AD No.: 2010-0236-E
Date: 10 November 2010
Note: This Emergency 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 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].
Type Approval Holder’s Name :
ROLLS-ROYCE PLC
Type/Model designation(s) :
RB211 Trent 900 series engines
TCDS Number : EASA.E.012
Foreign AD : Not applicable
Supersedure : None
ATA 72 Engine – High Pressure / Intermediate Pressure (HP/IP)
Structure – Inspections
Manufacturer(s): Rolls-Royce plc
Applicability: RB211 Trent 900 series engines, variants RB211 Trent 970-84, RB211
Trent 970B-84, RB211 Trent 972-84, RB211 Trent 972B-84, RB211 Trent
977-84, RB211 Trent 977B-84 and RB211 Trent 980-84, all serial
numbers.
These engines are known to be installed on, but not limited to, Airbus
A380 series aeroplanes.
Reason: An uncontained engine failure has recently occurred on a Rolls-Royce
Trent 900 involving release of high energy debris and leading to damage
to the aeroplane.
Analysis of the preliminary elements from the incident investigation shows
that an oil fire in the HP/IP structure cavity may have caused the failure of
the Intermediate Pressure Turbine (IPT) Disc.
This condition, if not detected, could ultimately result in uncontained
engine failure potentially leading to damage to the aeroplane and hazards
to persons or property on the ground.
For the reasons described above and pending conclusion of the incident
investigation, this AD requires repetitive inspections of the Low Pressure
Turbine (LPT) stage 1 blades and case drain, HP/IP structure air buffer
cavity and oil service tubes in order to detect any abnormal oil leakage,
and if any discrepancy is found, to prohibit further engine operation.
The requirements of this AD are considered as interim action. If, as a
EASA AD No : 2010-0236-E
EASA Form 111 Page 2/3
result of the on-going incident investigation, a terminating action is later
identified, further mandatory actions might be considered.
Effective Date: 10 November 2010
Required Action(s)
and Compliance
Time(s):
Required as indicated, unless accomplished previously:
(1) Within the compliance times indicated in Table 1 of this AD,
accomplish the following actions in accordance with Rolls-Royce
Non Modification Service Bulletin (NMSB) 72-AG590, Par 3.
Accomplishment Instructions, 3.A or 3.B as applicable to the engine
configuration:
(1.1) Carry out an extended ground idle run.
(1.2) Inspect the Low Pressure Turbine (LPT) stage 1 blades and
case drain.
(1.3) Inspect the HP/IP structure air buffer cavity and oil service
tubes.
Table 1
Compliance time
Engine
Configuration
Initial Threshold Repetitive Interval
On-wing Within 10 Flight Cycles
(FC) after the effective
date of this AD.
At intervals not exceeding
20 FC.
In-shop After the engine test
procedure and before
next flight.
Not applicable (after
engine installation refer to
on-wing repetitive
inspection intervals).
(2) If any discrepancy is found during the inspections required by
paragraph (1) of this AD, any further engine operation is prohibited.
Within one day after the accomplishment of the inspection, report the
findings to Rolls-Royce.
(3) Inspections accomplished in accordance with the content of NMSB
72-AG590 before the effective date of this AD, are acceptable to
comply with the initial inspections required by this AD.
(4) After the effective date of this AD, do not operate an engine on an
aeroplane unless it has been inspected in accordance with the
requirements of this AD.
Ref. Publications: Rolls-Royce RB211-Trent 900 Alert Non Modification Service Bulletin
72-AG590 dated 10 November 2010.
The use of later approved updates 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 safety assessment has requested not to implement the full
consultation process and an immediate publication and notification.
3. Enquiries regarding this AD should be referred to the Airworthiness
Directives, Safety Management & Research Section, Certification
Directorate, EASA. E-mail
[email protected].
EASA AD No : 2010-0236-E
EASA Form 111 Page 3/3
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
Aeromanager by Rolls-Royce. 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) 1332 242424, or e-mail from
Civil Aerospace - Rolls-Royce identifying the
correspondence as being related to Airworthiness Directives.