2009-07-01: High Pressure (HP) Turbine

2009-07-01 Rolls-Royce Deutschland Ltd & Co KG (formerly BMW Rolls- Royce GmbH, formerly BMW Rolls-Royce Aero Engines): Amendment 39- 15860. Docket No. FAA-2008-0224; Directorate Identifier 2007-NE-44- AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 27, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. These engines are installed on, but not limited to, McDonnell Douglas Model 717-200 airplanes. Reason (d) It is necessary to change the limits of the High Pressure (HP) Turbine Stage 1 and Stage 2 Rotor Discs. The maximum approved life of these discs is decreased for all flight missions. This Emergency Airworthiness Directive (EAD) has been raised to instruct mandatory decreased maximum approved lives in the BR715 Time Limits Manual (TLM) T-715-3BR for the HP Turbine Stage 1 Rotor Disc forboth Part No. BRH20130 and Part No. BRH20131 and of the High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No. BRH19423 and Part No. BRH19427 for all flight missions. The life limits are decreased by the same proportion for all flight missions, thus back to birth pro-rata calculations due to the life limit changes are not necessary. We are issuing this AD to prevent rotating parts that may have exceeded their low-cycle fatigue life limits from failing, which could result in uncontained engine failure and subsequent damage to the airplane. Actions and Compliance (e) No later than 30 days after the effective date of this AD the following mandatory actions need to be completed for each individual BR700-715 HP Turbine Stage 1 Rotor Disc for both Part No. BRH20130 and Part No. BRH20131 and High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No. BRH19423 and Part No. BRH19427 installed in a BR700-715A1-30, B1-30 or C1-30 engine: (1) Identify the mandatory decreased maximum approved life for the HP Turbine Stage 1 and Stage 2 Rotor Discs listed in the tables below: Declared Safe Cyclic Life, in Flight Cycles High Pressure (HP) Turbine Stage 1 Rotor Disc Engine Thrust Rating Engine Flight Mission Part No. A1-30 Design B1-30 Design C1-30 Design A1-30 Hawaiian C1-30 Tropical C1-30 derated Tropical BRH20130 15971 13324 10500 17647 3794 7941 BRH20131 15971 13324 10500 17647 3794 7941 Declared Safe Cyclic Life, in Flight Cycles High Pressure (HP) Turbine Stage 2 Rotor Disc Engine Thrust Rating Engine Flight Mission Part No. A1-30 Design B1-30 Design C1-30 Design A1-30 Hawaiian C1-30 Tropical C1-30 derated Tropical BRH19423 21165 17800 13372 21165 10893 13461 BRH19427 21165 17800 13372 21165 10893 13461 (2) Record the mandatory maximum approved life in the applicable lifing documentation. It is mandatory to use the values given in the two tables in step (e)(1) of this AD. Alternative Methods of Compliance (AMOCs) (f) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) Refer to EASA Emergency Airworthiness Directive 2007-0152-E (corrected), dated June 1, 2007, for related information. (h) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; telephone (781) 238-7747; fax (781) 238-7199, for more information about this AD. Material Incorporated by Reference (i) None.