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EASA AIRWORTHINESS DIRECTIVE 

AD No : 2007-0310 R1 

Date: 08 January 2008

No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the 

requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.

Type Approval Holder’s Name : 

Rolls-Royce plc 

Type/Model designation(s) : 

RB211-22B and -524 Series Engines 

TCDS Number: United Kingdom Engine TCDS No. 1039 and 1043 

Foreign AD: Not applicable 

Revision: This Airworthiness Directive (AD) revises and replaces AD 2007-0310 dated 19 December 2007. 

ATA 72 Engine – Low Pressure Turbine (LPT) Shaft – Inspection / Replacement 

Manufacturer(s): Rolls-Royce plc 

Applicability: RB211-22B series engines, all models, all serial numbers; and 

RB211-524B4-D-02, RB211-524D4-19, RB211-524D4-39, RB211-524D4-B-19, 

RB211-524D4-B39, RB211-524D4X-19 and RB211-524D4X-B-19 engines, all serial 

numbers. These engines are known to be installed on, but not limited to, Boeing 747 

series aircraft; and Lockheed L-1011 series aircraft. 

Note: Some RB211-524 series engines and all RB211-535 series Engines, although 

listed in the referenced Rolls-Royce Non Modification Service Bulletin (NMSB), are 

not affected by the same unsafe condition and therefore this AD does not apply to 

those engines. 

Reason: Several low pressure turbine (LPT) shafts have been found with cracks originating 

from the rear cooling air holes. The cracks were found at normal component 

overhaul, by the standard Magnetic Particle Inspection (MPI) technique defined in 

the associated engine manual. The cracks have been found to initiate from 

corrosion pits. Propagation of a crack from the rear cooling air holes may result in 

shaft failure and subsequently in an uncontained Low Pressure Turbine failure. 

For the reasons stated above, this AD requires the inspection of the affected 

engines’ LPT shafts and replacement of the shaft, as necessary. 

This AD has been revised to delete Model RB211-524B4-02 engines from the 

Applicability and Compliance as it is not affected by the same unsafe condition. 

Effective Date: 02 January 2008 
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Compliance: Required as indicated, unless accomplished previously: 

1. Initial Inspection Requirements 

(a) If on the effective date of this AD, the engine is undergoing a shop visit 

where the LPT shaft has been completely disassembled to piece-part level 

in accordance with the appropriate disassembly procedures contained in 

the Engine Manual and the LPT shaft has not been re-protected with 

corrosion resistant coating then, before installing the engine on an aircraft, 

the LPT shaft must be inspected in accordance with the accomplishment 

instructions of Rolls-Royce NMSB 72-AF336; 

(b) For all other engines, at the next engine shop visit after the effective date of 

this AD when the LPT shaft is completely disassembled to piece-part level 

in accordance with the appropriate disassembly procedures contained in 

the Engine Manual, inspect the LPT Shaft in accordance with the 

accomplishment instructions of Rolls-Royce NMSB 72-AF336. 

 

2. Repetitive Inspection Requirements – following initial inspection of an LPT 

shaft in accordance with paragraph 1 of this AD, the LPT shaft must be reinspected in accordance with the accomplishment instructions of Rolls-Royce 

NMSB 72-AF336 and in accordance with the following schedule: 

Engine Model Maximum Time Between 

Inspections (engine cycles) 

RB211-22B Series, all models 3 500 

RB211-524B4-D-02 4 000 

RB211-524D4-19, RB211-524D4-39, 

RB211-524D4-B-19, RB211-524D4-B39, 

RB211-524D4X-19 and RB211-524D4XB-19 

normal shop visit interval 

3. All LPT shafts inspected according to the schedule above and found to be 

cracked must be replaced with serviceable LPT shafts before installing the 

engine on an aircraft. 

Ref. Publications: Rolls-Royce RB211 Propulsion System Non Modification Service Bulletin No. 

RB211-72-AF336 original issue. 

The use of later approved revisions of this document is acceptable for compliance 

with the requirements of this AD. 

Remarks : 1. If requested and appropriately substantiated, EASA can accept Alternative 

Methods of Compliance for this AD. 

2. The original issue of this AD was posted on 20 November 2007 as PAD 07-212 

for consultation until 18 December 2007. No comments were received during the 

consultation period. 

3. Enquiries regarding this AD should be referred to the AD Focal Point - 

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: 

Rolls-Royce plc, Publication Services, P.O. Box 31, Derby, DE24 8BJ, United 

Kingdom; Telephone: +44 (0) 1332 242424, Fax: +44 (0) 1332 249936; 

Email: tech.help@rolls-royce.com or download the publication from 

https://www.aeromanager.com/