Airworthiness directives › 2020-15-12
AD 2020-15-12 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines
Applicability*9
This AD applies to Rolls-Royce Deutschland Ltd & Co KG (Type Certificate previously held by Rolls-Royce plc) Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 model turbofan engines, except those that have the redesigned intermediate-pressure compressor (IPC) stage 1 and stage 2 rotor blades introduced by Rolls-Royce plc (RR) Service Bulletin (SB) Trent 1000 72-J941, Revision 1, dated February 6, 2019.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) After the effective date of this AD, before exceeding the initial inspection thresholds and repeat inspection intervals specified in Table 1 of RR Alert Non-Modification Service Bulletin (NMSB) Trent 1000 72-AK313, Revision 1, dated August 22, 2019 (“RR NMSB Trent 1000 72-AK313, R1”): (i) Perform initial ultrasonic inspections (USIs) of the IPC stage 1 blade root (front face). (ii) Thereafter, perform repetitive USIs of the IPC stage 1 blade root (front face). (iii) Use the Accomplishment Instructions, paragraph 3.A.(1)(a) (on-wing) or 3.A.(2)(a) and (b) (in-shop) of RR NMSB Trent 1000 72-AK313, R1 to perform the inspections. (2) After the effective date of this AD, before exceeding the initial inspection thresholds and repeat inspection intervals specified in Table 2 of RR NMSB Trent 1000 72-AK313, R1: (i) Perform initial visual inspections of the IPC stage 2 blade root (front face) and IPC shaft stage 2 dovetail post (front face). (ii) Thereafter, perform repetitive visual inspections of the IPC stage 2 blade root (front face) and IPC shaft stage 2 dovetail post (front face). (iii) Use the Accomplishment Instructions, paragraph 3.B.(1)(a) (on-wing) or 3.B.(2)(b) (in-shop) of RR NMSB Trent 1000 72-AK313, R1 to perform the inspections. (3) After the effective date of this AD, before exceeding the initial inspection threshold and repeat inspection intervals specified in Table 2 of RR NMSB Trent 1000 72-AK313, R1: (i) Perform initial USIs of IPC stage 2 blade root (rear face). (ii) Thereafter, perform repetitive USIs of IPC stage 2 blade root (rear face). (iii) Use the Accomplishment Instructions, paragraph 3.C.(1)(a) (on-wing) or 3.C.(2)(a) (in-shop) of RR NMSB Trent 1000 72-AK313, R1 to perform the inspections. (4) After the effective date of this AD, within 5 engine flight cycles (FCs) after each occurrence in which any engine operates in asymmetric power conditions at an altitude of less than 28,000 feet, perform the following inspections on the engine not affected by the power reduction or in-flight shutdown (IFSD): (i) Perform initial USIs and visual inspections required by paragraphs (g)(1), (2), and (3) of this AD. (ii) Thereafter, perform the repetitive USIs and visual inspections required by paragraphs (g)(1), (2), and (3) of this AD. (iii) Use the service information and repetitive inspection thresholds required by paragraphs (g)(1)(iii), (2)(iii), and (3)(iii) to perform the inspections, as applicable. (5) After the effective date of this AD, within 5 engine FCs following a cabin depressurization event, perform the following inspections on both engines installed on the airplane: (i) Perform initial USIs and visual inspections required by paragraphs (g)(1), (2), and (3) of this AD. (ii) Thereafter, perform the repetitive USIs and visual inspections required by paragraphs (g)(1), (2), and (3) of this AD. (iii) Use the service information and repetitive inspection thresholds required by paragraphs (g)(1)(iii), (2)(iii), and (3)(iii) to perform the inspections, as applicable. (6) If any IPC stage 1 blade root (front face), IPC stage 2 blade root (front face), IPC shaft stage 2 dovetail post (front face), or IPC stage 2 blade root (rear face) is found cracked during any inspection required by this AD, replace the part with a part eligible for installation before further flight.
Unsafe condition
This AD was prompted by IPC blade separations resulting in engine failures. Subsequently, the manufacturer identified cracking of parts in-service resulting in the need to require new inspections using new inspection thresholds and intervals. The manufacturer also determined the need to add an optional terminating action, amend the asymmetric power condition for engine inspection, and require an inspection after a cabin depressurization event. The FAA is issuing this AD to prevent failure of the IPC. The unsafe condition, if not addressed, could result in failure of one or more engines, loss of thrust control, and loss of the airplane.
Affected ADs
This AD replaces AD 2018-08-02, Amendment 39-19255 (83 FR 17746, April 24, 2018).
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