Airworthiness directives › 2018-22-01
AD 2018-22-01 Airworthiness Directives; Honeywell International Inc. Turboprop Engines
Applicability*9
This AD applies to Honeywell International Inc. (Honeywell) TPE331-8, -10, -10N, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U turboprop engines with second stage turbine rotor assemblies, part number (P/Ns) 3102106-1, -6, and -8 or P/N 3101514-1, -10 and -12, installed.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) Remove from service the applicable second stage turbine rotor assembly, P/Ns 3102106-1, -6 and -8, according to the schedule in Table 1 to Paragraph (g)(1) of this AD: Table 1 to Paragraph ( g )(1) of This AD—Removal of Second Stage Rotor, P/Ns 3102106-1, -6 and -8 Second stage turbine rotor cycles since new (CSN) on the effective date of the AD Removal schedule 0 to 2,600 Prior to 3,000 CSN. 2,601 to 3,300 Within 400 cycles-in-service (CIS) after the effective date of this AD or 3,600 CSN, or at next access, whichever occurs first. 3,301 to 4,000 Within 200 cycles-in-service after the effective date of this AD or 4,100 CSN, or at next access, whichever occurs first. 4,001 to 4,800 Within 100 cycles-in-service after the effective date of this AD or 4,800 CSN, or at next access, whichever occurs first. (2) Remove from service the applicable second stage turbine rotor assembly, P/Ns 3101514-1, -10 and -12, per the schedule in Table 2 to Paragraph (g)(2) of this AD: Table 2 to Paragraph ( g )(2) of This AD—Removal of Second Stage Rotors, P/Ns 3101514-1, -10 and -12 Second stage turbine rotor CSN on the effective date of the AD Removal schedule 0 to 2,600 Prior to 3,000 CSN. 2,601 to 3,200 Within 400 CIS after the effective date of this AD or 3,600 CSN, or at next access, whichever occurs first. 3,201 to 3,800 Within 200 CIS after the effective date of this AD or 4,100 CSN, or at next access, whichever occurs first. 3,801 to 4,400 Within 100 CIS after the effective date of this AD or 4,400 CSN, or at next access, whichever occurs first.
Unsafe condition
This AD was prompted by a report that a TPE331-11U engine installed on an M7 Aerospace LP SA227 airplane experienced an uncontained rotor separation and the discovery of cracks in the bore of the second stage turbine rotor assembly after publication of AD 88-12-10. We are issuing this AD to prevent failure of the second stage turbine rotor. The unsafe condition, if not addressed, could result in uncontained release of the second stage turbine rotor, damage to the engine, and damage to the airplane.
Affected ADs
This AD replaces AD 88-12-10, Amendment 39-5910 (53 FR 19766, May 31, 1988).
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