Airworthiness Directive · Amendment 39-17877 · Rolls-Royce plc Turbofan Engines
Rolls-Royce plc Turbofan Engines
This AD applies to all Rolls-Royce plc (RR) RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan engines, except those that have been reworked in accordance with RR Service Bulletin (SB) No. RB.211-72-G604, dated March 18, 2013.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892- 17, 892B-17, and 895-17 turbofan engines. This AD requires inspection of the affected low-pressure (LP) turbine bearing support and exhaust case assembly and, if necessary, its replacement with a part eligible for installation. This AD was prompted by thin-walled LP turbine bearing support and exhaust case assemblies having been delivered into service. We are issuing this AD to prevent failure of the LP turbine bearing support and exhaust case assembly, which could lead to engine separation and damage to the airplane.
(1) For engines that have an LP turbine bearing support and exhaust case assembly identified by part number (P/N) and serial number (S/N) in Table 1 to paragraph (e) of this AD, installed, at the next engine shop visit after the effective date of this AD, but not later than June 30, 2017, replace the assembly with one that is eligible for installation.
(2) For engines with an LP turbine bearing support and exhaust case assembly not identified by P/N and S/N in Table 1 to paragraph (e) of this AD, installed, at the next piece-part exposure of the LP turbine bearing support and exhaust case assembly after the effective date of AD:
(i) Inspect the hub to conical panel weld line thickness using paragraphs 3.B.(3)(a) through 3.B.(3)(d)(iii) of RR Alert Service Bulletin (ASB) No. RB.211-72-AG644, dated April 30, 2013; and
(ii) Inspect the hub to conical panel flange thickness using paragraphs 3.B.(4)(a) through 3.B.(4)(c)(v) of RR ASB No. RB.211-72-AG644, dated April 30, 2013.
(iii) If the LP turbine bearing support and exhaust case assembly does not pass the inspections required by paragraphs (e)(2)(i) and (e)(2)(ii) of this AD, replace the LP turbine bearing support and exhaust case assembly with one that is eligible for installation.
| P/Ns | S/Ns |
|---|---|
| FK31446 | 118-01 |
| FK31446 | 209-01 |
| FK31446 | 216-01 |
| FK31446 | 232-01 |
| FK32232 | 113-01 |
| FK32085 | 268-01 |
| FK32085 | 269-01 |
| FK31446 | 022-01 |
| FK31446 | 028-01 |
The following definitions apply for the purpose of this AD:
(1) An LP turbine bearing support and exhaust case assembly is eligible for installation if it has passed the inspections of paragraphs (e)(2)(i) and (e)(2)(ii) of this AD; or has been reworked in accordance with RR SB No. RB.211-72-G604, dated March 18, 2013.
(2) “Piece-part exposure” occurs whenever the LP turbine bearing support and exhaust case assembly is sufficiently exposed to do the inspections required by paragraphs (e)(2)(i) and (e)(2)(ii) of this AD.
(3) An “engine shop visit” is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance is not 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.
