EASA AD No : 2011-0232

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0232

Date: 13 December 2011

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption].


### Type Approval Holder’s Name : Rolls-Royce Deutschland Ltd & Co KG Type/Model designation(s) :
BR700-715 engines

TCDS Number : EASA.E.023

Foreign AD : not applicable

Supersedure : None



### ATA 72 Engine – Low Pressure (LP) Compressor Booster Rotor – Inspection / Rework

Manufacturer(s): Rolls-Royce Deutschland Ltd & Co K G

Applicability: BR700-715A1-30, BR700-715B1-30 and B R700-715C1-30 engines, all Serial Numbers. These engines are known to be installed on, but not limited to Boeing 717 aeroplanes.
Reason: Several LP compressor booster rotors have b een found non compliant to original design. The technical investigations carried out by Rolls R oyce Deutschland (RRD) revealed that this discrepancy is due to a manufact uring defect and that only some specific LP compressor booster rotor serial nu mbers are affected. This condition, if not corrected, could lead to an uncontained engine failure, potentially damaging the aeroplane and injuring its occupants, and/or injuring persons on the ground. To address this condition, RRD have developed an in spection programme and a rework for the affected LP compressor booster rot ors. For the reasons described above, depending on engin e type of operations, this AD requires repetitive Fluorescent Penetrant Inspec tions of the LP compressor booster rotor and if any crack is found, replacemen t with a serviceable part. This AD also requires rework of all affected LP com pressor booster rotors.EASA AD No : 2011-0232

EASA Form 110 Page 2/3 Effective Date: 27 December 2011

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) For engines on which LP Compressor Booster Roto rs with part number (P/N) BRH19215 or P/N BRH19871, with serial numbers (S/N) from 118 to 255 inclusive is installed, within the compliance t imes indicated in Table 1 of this AD, depending on engine type of operation, accomplish a Fluorescent Penetrant Inspection (FPI) of the LP co mpressor booster rotor, in accordance with the instructions of RRD N on Modification Service Bulletin (NMSB) SB-BR700-72-A900503 Rev. No. 4. The reafter, at intervals not to exceed the value indicated in Tabl e 1 of this AD, as applicable to the operation (rating) of the engine, repeat the FPI of the LP compressor booster rotor.

Table 1 – Compliance Time(s)

Engine type of operation (rating) Initial FPI (whichever occurs later) Repetitive FPI Interval (not to exceed)

Hawaiian Flight Mission rating only Before accumulating 36 000 Engine Cycles (EC), or within 500 EC after the effective date of this AD 6 000 EC

Any other rating, or combination of ratings Before accumulating 18 000 EC, or within 500 EC after the effective date of this AD 4 000 EC

(2) If a crack is detected during any inspection as required by paragraph (1) of this AD, before next flight, replace the LP compres sor booster rotor with a serviceable part. Note 1: For the purpose of this AD, a serviceable L P compressor booster rotor is: - A LP Compressor booster rotor not having a P/N BR H19215 or a P/N BRH19871, with S/N from 118 to 255 inclusive; - Or a part having a P/N BRH19215 or P/N BRH19871, with S/N from 118 to 255 inclusive and this part is in compliance with the requirements of paragraph (1) of this AD. (3) For engines on which LP Compressor Booster Roto rs with P/N BRH19215 or P/N BRH19871, with S/N from 118 to 255 inclusive is installed, at the next LP compressor booster rotor exposure during sh op visit, but no later than 96 months after the effective date of this AD, rework the LP compressor booster rotor in accordance with the ins tructions of RRD SB-BR700-72-101683. Note 2: Rework of the LP compressor booster rotor c an only be accomplished by RRD maintenance centres. Once the LP compressor booster rotor has been reworked, the part has a new P/N. (4) Replacement on an engine of the LP compressor b ooster rotor with a part not having a P/N BRH19215 or P/N BRH19871, with S/N from 118 to 255 inclusive, constitutes terminating action for the r epetitive inspection requirements of paragraph (1) of this AD for that e ngine. (5) After the effective date of this AD, do not in stall an engine equipped with a LP Compressor Booster Rotor with P/N BRH19215 or P/ N BRH19871, with S/N from 118 to 255 inclusive, unless in compl iance with the requirements of this AD. (6) After the effective date of this AD, do not ins tall a LP Compressor Booster Rotor with P/N BRH19215 or P/N BRH19871, with S/N f rom 118 to 255EASA AD No : 2011-0232

EASA Form 110 Page 3/3 inclusive, on an engine, unless in compliance with the requirements of this AD.

Ref. Publications: RRD NMSB Alert SB-BR700-72-A9005 03 Rev. No.4, dated 16 June 2011. RRD SB-BR700-72-101683, dated 20 September 2010. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 07 November 2011 as PAD 11 -116 for consultation until 05 December 2011. The Comment Response Docume nt can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: Rolls-Royce Deutschland Ltd & Co KG Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany, Telephone : +49 (0) 33 7086 1768; Fax: +49 (0) 33 7 086 3356, Email rrd.aog@rolls-royce.com

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