Airworthiness Directive · Amendment 39-21706 · Turbine engine compressor section
Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines
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 (RR) Service Bulletin (SB) Trent 1000 72-J941, Initial Issue, dated December 6, 2016, or Revision 1, dated February 6, 2019.
The FAA is superseding Airworthiness Directive (AD) 2020-15-12 for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000 model turbofan engines. AD 2020-15-12 required initial and repetitive ultrasonic or visual inspections of the intermediate-pressure compressor (IPC) stage 1 rotor blade root (front face), IPC stage 2 rotor blade root (front and rear face), and IPC shaft stage 2 dovetail post (front face), and removal of any cracked parts from service. AD 2020-15-12 also required an inspection after asymmetric power and cabin depressurization events. This AD was prompted by IPC rotor blade separations resulting in engine failures. This AD requires initial and repetitive ultrasonic or visual inspections of certain IPC stage 1 rotor blade root, IPC stage 2 rotor blade root, and IPC shaft stage 2 dovetail posts until replacement of the IPC stage 1 and stage 2 rotor blades with redesigned IPC stage 1 and stage 2 rotor blades in kitted sets. The FAA is issuing this AD to address the unsafe condition on these products.
(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 rotor blade root (front face).
(ii) Thereafter, perform repetitive USIs of the IPC stage 1 rotor 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 rotor blade root (front face) and IPC shaft stage 2 dovetail post (front face).
(ii) Thereafter, perform repetitive visual inspections of the IPC stage 2 rotor 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 rotor blade root (rear face).
(ii) Thereafter, perform repetitive USIs of IPC stage 2 rotor 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) through (3) of this AD.
(ii) Thereafter, perform the repetitive USIs and visual inspections required by paragraphs (g)(1) through (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) through (3) of this AD.
(ii) Thereafter, perform the repetitive USIs and visual inspections required by paragraphs (g)(1) through (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 rotor blade root (front face), IPC stage 2 rotor blade root (front face), or IPC stage 2 rotor 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.
(7) If any IPC shaft stage 2 dovetail post (front face) is found cracked during any inspection required by this AD, replace the IPC drum assembly.
At the next engine shop visit after the effective date of this AD, replace the IPC stage 1 and stage 2 rotor blades with redesigned IPC stage 1 and stage 2 rotor blades introduced by RR SB Trent 1000 72-J941, Revision 1, dated February 6, 2019. Install the blades as kitted sets using the Accomplishment Instructions, paragraph 3.C. (In-Shop), of RR Alert SB Trent 1000 72-AK430, Initial Issue, dated August 17, 2020. This replacement of the IPC stage 1 and stage 2 rotor blades as kitted sets is a terminating action for the initial and repetitive ultrasonic or visual inspection requirements, as applicable, required by paragraphs (g)(1) through (5) of this AD.
(1) For the purpose of this AD, an “asymmetric power condition” is the operation of the airplane at an altitude of less than 28,000 feet, experiencing either single engine take-off, engine fault (reduced power on one engine), or single engine IFSD, which includes execution of any non-normal checklist procedure.
(2) For the purpose of this AD, an “engine shop visit” is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine case flanges, except that the separation of engine flanges solely for the purposes of transportation 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
