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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2006 – 0181 

Date: 26 June 2006 

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 series engines (all marks) 

TCDS No: UK-CAA Engine No. 1039 

Foreign AD : N/A 

Supersedure: N/A 

ATA 72; 41; 51 High Pressure Turbine (HPT) – Inspection of Disc Rim Cooling 

Air Holes for Cracks from Scoring Damage 

Manufacturer(s): Rolls-Royce plc 

Applicability: RB211-22B series engines (all marks) installed on, but not limited to, 

Lockheed L-1011 aircraft 

Reason: HPT Discs recently inspected in accordance with the Engine Manual have 

exhibited cracks in the disc rim. The discs have failed to meet the inspection 

acceptance criteria and have been returned to Rolls-Royce for engineering 

investigation. 

This investigation has concluded that the cracks have resulted from scores 

within the cooling air holes in the disc rim that could have been introduced 

during new part manufacture or during overhaul of the disc. The engineering 

investigation has also concluded that if this cracking was undetected then it 

could result in uncontained disc failure. 

Effective Date: 10 July 2006 

Compliance: Carry out an Eddy Current Inspection (ECI), as defined in Section 3., 

Accomplishment Instructions of Rolls-Royce NMSB 72-AE969 or later EASA 

approved revision on the HP turbine discs identified in Section 1.A.(4) of 

Rolls-Royce NMSB 72-AE969 or later EASA approved revision in 

accordance with the following schedule: 

1. Initial Inspection Requirements- inspect the HP Turbine disc by whichever 

is the soonest of the following conditions: 
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1A. If HP turbine disc cycles since new is greater than 9500 cycles on the 

effective date of this Airworthiness Directive, then inspect the disc by 

whichever is the soonest of the following conditions: 

 (a) Within 500 cycles from the effective date of this Airworthiness 

Directive 

 (b) At next shop visit where the HP turbine rotor is removed from the 

Combustor Outer Case 

1B. If 

 -the HP turbine disc cycles since new is greater than 9500 cycles on 

the effective date of this Airworthiness Directive 

 and 

 -the HP turbine rotor is currently undergoing a shop visit 

 and 

 has been removed from the Combustion Outer Case and it has 

not yet been reinstalled into the Combustion Outer Case, 

then the HP turbine disc must be inspected in accordance with the 

requirements of this Airworthiness Directive. 

1C. If HP turbine disc cycles since new is less than 9500 cycles on the 

effective date of this Airworthiness Directive, then inspect the disc by 

whichever is the soonest of the following conditions: 

 (a) Prior to reaching 10000 cycles since new. 

 (b) At next shop visit where the HP turbine rotor is removed from the 

Combustor Outer Case and the HP turbine disc cycles since new is 

greater than 2750 cycles. 

1D. If 

 -the HP turbine disc cycles since new is greater than 2750 cycles 

and less than 9500 cycles on the effective date of this 

Airworthiness Directive 

 and 

 -the HP turbine rotor is currently undergoing a shop visit 

 and 

 ,has been removed from the Combustion Outer Case and it has 

not yet been reinstalled into the Combustion Outer Case, 

then the HP turbine disc must be inspected in accordance with the 

requirements of this Airworthiness Directive. 

2. Further Inspection Requirements- repeat the inspection detailed above at 

every subsequent shop visit where the HP turbine blades have been 

removed from the HP turbine disc. 

3. If a HP turbine disc has previously passed inspection to the Eddy Current 

Inspection procedure as defined in Rolls-Royce TSD594-J Overhaul Process 

Manual Task 70-00-00-200-223 and at a disc life above 2750 cycles since 

new that meets the criteria of section 1. above, then that inspection satisfies 

the requirements stated in section 1. of this Airworthiness Directive. 
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Ref. Publications: Rolls-Royce RB211 Propulsion System Non-Modification Service 

Bulletin Mod No: 72-AE969 or later approved revisions. 

Remarks: 1. If requested and appropriately substantiated the responsible EASA 

manager for the related product has the authority to accept Alternative 

Method of Compliance (AMOCs) for this AD. 

2. This AD was posted as PAD 06-131 for consultation on 24 May 2006 

with a comment period until 16 June 2006. The comment Response 

Document can be found at http://ad.easa.eu.int/ . 

3. Enquiries regarding this Airworthiness Directive should be referred to 

Mr. M. Capaccio, Airworthiness Directive Focal Point - Certification 

Directorate, EASA. E-mail: ADs@easa.europa.eu

4. For any questions concerning the technical content of the 

requirements in this AD, please contact Rolls-Royce plc. PO Box 31, 

Derby, DE24 8BJ, United Kingdom. 

Phone: +44 (0) 1332 242424, Fax: +44 (0) 1332 249936.