Airworthiness Directive · Amendment 39-22537 · Turbine engine compressor section
Rolls-Royce Deutschland Ltd & Co KG Engines
This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) Model BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 engines.
The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model BR700-715A1-30, BR700- 715B1-30, and BR700-715C1-30 engines. This AD was prompted by reports of malformed scallop edge geometry and surface conditions at the front flange scallops of affected low-pressure compressor (LPC) booster rotors. This AD requires repetitive fluorescent penetrant inspections (FPIs) of the front flange scallops of the LPC booster rotor for any cracks, replacement or repair of the LPC booster rotor if necessary and, as an optional terminating action to the repetitive FPIs, a visual inspection for malformed scallop edge geometry and malformed surface conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraphs (h) and (i) of this AD: Perform all required actions within the compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2023-0152, dated July 25, 2023 (EASA AD 2023-0152).
(1) Where EASA AD 2023-0152 requires compliance from its effective date, this AD requires using the effective date of this AD.
(2) This AD does not adopt the compliance times specified for the initial fluorescent penetrant inspection (FPI) in paragraph (1) and Table 1 of EASA AD 2023-0152. Instead, this AD requires the initial FPI within 150 engine flight cycles after the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2023-0152 specifies “in accordance with the instructions of EM task 72-38-12-200-801” this AD requires replacing those words with “in accordance with the instructions of EM task 72-38-18-200-801 or equivalent FAA approved procedures.”
(4) Where paragraphs (2) and (3) of EASA AD 2023-0152 specify to contact RRD for approved corrective action(s) and accomplish those actions accordingly, this AD requires replacement of the LPC booster rotor. In lieu of replacement of the affected LPC booster rotor, operators may repair the affected LPC booster rotor using a method approved by the Manager, International Validation Branch, FAA; or EASA; or RRD's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(5) Where the service information referenced in EASA AD 2023-0152 specifies to reject the engine if a crack is found, this AD requires replacement or repair of the LPC booster rotor.
(6) This AD does not adopt the Remarks paragraph of EASA AD 2023-0152.
Although the service information referenced in EASA AD 2023-0152 specifies to submit the Accomplishment Forms, Parts A and B, to the manufacturer, this AD does not include that requirement. If operators elect to perform the optional terminating action specified in Part C of the service information referenced in EASA AD 2023-0152, this AD requires submission of the Part C Accomplishment Form and photographic information to the manufacturer.
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
