Airworthiness directives › 2007-14-07
AD 2007-14-07 Airworthiness Directives; Rolls-Royce plc RB211-524 and -535 Series Turbofan Engines
Applicability*9
This AD applies to the following Rolls-Royce plc (RR) RB211-524 and -535 series turbofan engines: -524B2-19 -524C2-B-19 -524B-02 -524D4X-19 -524B3-02 -524D4X-B-19 -524C2-19 -524G2-19 -524B4-02 -524G3-19 -524B4-D-02 -524H-36 -524D4-19 -524H2-19 -524D4-39 -535E4-37 -524B-B-02 -535E4-B-37 -524B2-B-19 -535E4-C-37 -524D4-B-19 -535E4-B-75 -524D4-B-39 -535C-37 These engines are installed on, but not limited to, Boeing 747, 757, 767 series, Lockheed L-1011 series, and Tupolev Tu204 airplanes.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial and Repetitive Inspections (f) At the next shop visit after the effective date of this AD, perform an initial fluorescent penetrant inspection (FPI) and borescope inspection of the HP compressor stage 1 and 2 discs for cracks. (g) Thereafter, at every engine shop visit, perform repetitive FPIs and borescope inspections of HP compressor stage 1 and 2 rotor discs for cracks. (h) Use paragraphs 3.A.(1) through 3.A.(4)(o) of the Accomplishment Instructions of RR Alert Service Bulletin (ASB) No. RB.211-72-AE359, Revision 1, dated November 17, 2005, to do the inspections. (i) Accept or reject as necessary, HP compressor stage 1 and 2 rotor discs using inspection criteria paragraphs 3.A.(5)(a) through 3.A.(5)(f) of the Accomplishment Instructions of RR ASB No. RB.211-72-AE359, Revision 1, dated November 17, 2005. Definition (j) For the purpose of this AD, an engine shop visit is defined as anytime the HP compressor stage 1 and 2 rotor discs are removed from the HP compressor stage 3 disc. Reporting Requirements (k) Within 10 days, report inspection findings of cracks to the RR local field service office representative. The Office of Management and Budget has approved the reporting requirements specified in paragraph 3.A.(6)(b) of the Accomplishment Instructions of RR ASB No. RB.211-72-AE359, Revision 1, dated November 17, 2005, and assigned OMB control number 2120-0056. Alternative Methods of
Unsafe condition
This AD results from reports of low-cycle fatigue cracks found at overhaul in the interface weld between the high pressure (HP) compressor stage 1 and 2 rotor discs. We are issuing this AD to prevent uncontained engine failure and damage to the airplane.
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