Airworthiness Directive · Amendment 39-18899 · Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines
Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines
This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) Spey 506-14A, Spey 555-15, Spey 555-15H, Spey 555-15N, and Spey 555-15P turbofan engines with high-pressure compressor (HPC) stage 12 rotor disks, part number (P/N) EU25917, P/N EU56963, P/N JR10242, or P/N JR18449, installed.
We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) model Spey 506-14A, Spey 555- 15, Spey 555-15H, Spey 555-15N, and Spey 555-15P turbofan engines. This AD requires reducing the maximum approved life limits for certain high- pressure compressor (HPC) stage 12 rotor disks. We are issuing this AD to correct the unsafe condition on these products.
(1) Within 30 days after the effective date of this AD, determine if:
(i) The affected part was ever operated in a Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engine model, or
(ii) the affected part was operated soley in a Spey 506-14A engine.
(2) If the affected part was operated solely in a Spey 506-14A engine with no history of operating in a Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engine, no further action is required.
(3) If the affected part was operated in in both Spey 506-14A and Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engine models, or solely in Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engines, re-calculate the consumed cyclic life (and remaining service life) using the Maximum Approved Life for each engine model and take-off monitoring procedure as defined in Figures 1 and 2 to paragraph (g) of this AD.
(4) After the effective date of this AD, the Maximum Approved Lives for the affected parts are as defined in Figure 2 to paragraph (g) of this AD. Calculate the consumed cyclic life (and remaining service life) using the Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P Maximum Approved Lives in Figure 2 to paragraph (g) of this AD.
(5) For Spey 506-14A engines with an affected part installed, that do not have an engine shop visit after the effective date of this AD before the re-calculated consumed cyclic life of the affected part exceeds 14,700 flight cycles (FC), remove the affected part from service before the re-calculated consumed cyclic life exceeds 14,700 FC, or 50 FC or 30 days after the effective date of this AD, whichever occurs later.
(6) For Spey 555-15, Spey 555-15H, Spey 555-15N, or Spey 555-15P engines with an affected part installed, that do not have an engine shop visit after the effective date of this AD before the re-calculated consumed cyclic life of the affected part exceeds the Maximum Approved Lives in Figure 2 to paragraph (g) of this AD, remove the affected part from service before the re-calculated consumed cyclic life exceeds the later of the following:
(i) Maximum Approved Lives in Figure 2 to paragraph (g) of this AD, or
(ii) 200 FC or 90 days after the effective date of this AD, or before exceeding the In-Service Replacement Limits defined in Figure 3 to paragraph (g) of this AD, whichever occurs first.
| Flight cycles | |
|---|---|
| HPC stage 12 rotor disk, P/N EU25917, EU56963, and JR10242 | 14,700 |
| Take-off monitoring procedure | Maximum approved lives (flight cycles) |
|---|---|
| (A) With no high-pressure (HP) revolutions per minute (RPM) monitoring | 11,500 |
| HP RPM monitoring; stated RPM not exceeded on more than 15% of occasions: | |
| (B) 100% N2 | 13,600 |
| (C) 99% N2 | 17,100 |
| (D) 98% N2 | 19,300 |
| (E) 97% N2 | 20,500 |
| (F) No HP RPM monitoring required Datum (Average N2 at 99.5%) | 16,800 |
| Take-off monitoring procedure | In-service replacement limits (flight cycles) |
|---|---|
| (A) With no HP RPM monitoring | 13,800 |
| HP RPM monitoring; stated RPM not exceeded on more than 15% of occasions: | |
| (B) 100% N2 | 15,600 |
| (C) 99% N2 | 17,600 |
| (D) 98% N2 | 19,700 |
| (E) 97% N2 | 22,100 |
| (F) No HP RPM monitoring required Datum (Average N2 at 99.5%) | 17,300 |
After the effective date of this AD, installation of a serviceable spare engine or release to service of an engine after any shop visit is allowed, provided the affected part has not exceeded the Maximum Approved Lives in Figures 1 or 2 to paragraph (g) of this AD.
For the purpose of this AD, a shop visit is the induction of an engine into the shop for maintenance or overhaul. The separation of engine flanges solely for the purpose of transporting the engine without subsequent engine maintenance does not constitute an engine shop visit.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Engines
