Airworthiness directives › 2017-14-08
AD 2017-14-08 Airworthiness Directives; CFM International S.A. Turbofan Engines
Applicability*9
This AD applies to CFM International S.A. (CFM) CFM56-3, -3B, and -3C turbofan engines with steel high-pressure compressor (HPC) stator case, part numbers (P/Ns)1499M30G01, 1499M30G02, 1499M30G03, or 1676M88G01, installed.
Compliance
Comply with this AD within the compliance times specified, unless already done. Within 12 months after the effective date of this AD: (1) Inspect the affected engines to determine if the compressor front stator case is marked with “RP031” adjacent to the part number. If the case is marked with “RP031,” no further action is required. If the case is not marked with “RP031,” follow the remaining steps in paragraph (f) of this AD. (2) Perform an initial pull force check of stage 1, stage 2, and stage 3 of the compressor variable stator vane (VSV) actuation system. (i) If any stage requires more than 100 lb force to move the actuation ring, ream the VSV bores and apply anti-corrosion coating to stages 1, 2, and 3, prior to further flight, or replace with an HPC stator case that is eligible for installation and passes the VSV pull force check with measurements of 75 lb or less. (ii) If any stage requires more than 75 lb, but less than or equal to 100 lb force to move the actuation ring, repeat the inspection within 3 months since last inspection. (iii) If all stages require 75 lb force or less to move the actuation rings, repeat the inspection within 12 months since last inspection. (3) Thereafter, continue to perform repetitive pull force checks of stages 1, 2, and 3 of the compressor VSV actuation system and disposition as specified in paragraphs (2)(i) through (iii) of this AD.
Required actions
Reaming the VSV bores and applying anti-corrosion coating, as specified in paragraph (f)(2)(i) of this AD, is terminating action to the repetitive inspections required by paragraph (f)(3) of this AD.
Unsafe condition
This AD was prompted by a report of dual engine loss of thrust control (LOTC) that resulted in an air turn back. We are issuing this AD to maintain the actuators ability to fully reach commanded position, and prevent LOTC and reduced control of the airplane.
Affected ADs
None.
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