Airworthiness directives › 2020-25-04
AD 2020-25-04 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines
Applicability*9
This AD applies to all Rolls-Royce Deutschland Ltd. & Co KG (RRD) (Type Certificate previously held by Rolls-Royce plc) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 model turbofan engines.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) Within 7,500 engine flight hours (FHs) since new or since the last inspection or within 150 flight cycles (FCs) after January 5, 2017 (the effective date of AD 2016-24-08), whichever occurs later, inspect the engine upper bifurcation nose fairing assembly for cracks or missing material. Use paragraph (g)(3) of this AD to perform the inspection. (2) Repeat the inspection required by paragraph (g)(1) of this AD within every 7,500 engine FHs since the last inspection. (3) Inspect the engine upper bifurcation nose fairing assembly as follows. Note 1 to Paragraph (g)(3): Figure 1 of Rolls-Royce plc (RR) Alert Non-Modification Service Bulletin (NMSB) RB.211-72-AJ165, Revision 2, dated August 21, 2018, provides guidance on the engine upper bifurcation nose fairing assembly inspection locations. (i) Visually inspect upper bifurcation fairing seal face 22, seal support 23, and Zone A for any cracks or material loss on the right side. (A) If fairing seal face 22 is found to have released material, repair or replace the fairing before further flight. (B) If there is a single crack found on fairing seal face 22, shorter than 6 mm, repair or replace the fairing within 100 engine FCs, or at the next engine shop visit, whichever occurs first. (C) If there is a single crack, longer than 6 mm, found on fairing seal face 22, repair or replace the fairing within 15 engine FCs or at the next engine shop visit, whichever occurs first. (D) If there are two or more cracks found on fairing seal face 22, replace the fairing within 15 engine FCs or at the next engine shop visit, whichever occurs first. (E) If there is any cracking or material loss found on seal support 23, replace the fairing within 15 engine FCs or at the next engine shop visit, whichever occurs first. (ii) If the visual inspection required by paragraph (g)(3)(i) of this AD does not detect any cracks, fluorescent penetrant inspect Zone A. (A) If a crack shorter than 6 mm is detected, repair or replace the fairing within 100 engine FCs, or at the next engine shop visit, whichever occurs first. (B) If a crack longer than 6 mm is detected, repair or replace the fairing within 15 engine FCs or at the next engine shop visit, whichever occurs first. Note 2 to Paragraph (g)(3)(ii): AMM TASK 70-20-02, Water Washable Fluorescent Penetrant Inspection (Maintenance Process 213), and OMat 632, high sensitivity fluorescent penetrant inspection, provides guidance on performing a fluorescent penetrant inspection.
Unsafe condition
This AD was prompted by RRD developing a modification of the engine upper bifurcation nose fairing assembly as a result of reports of cracking and material release from an engine upper bifurcation fairing. The FAA is issuing this AD to prevent failure of the engine fire control system. The unsafe condition, if not addressed could result in engine fire and damage to the airplane.
Affected ADs
This AD replaces AD 2016-24-08, Amendment 39-18725 (81 FR 86567, December 1, 2016).
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