Airworthiness directives › 2004-09-29
AD 2004-09-29 Airworthiness Directives; Honeywell International Inc. (Formerly AlliedSignal Inc., Garrett Turbine Engine Company, and AiResearch Manufacturing Company of Arizona) TPE331-10 and -11 Series Turboprop Engines
Models named: JRB-6, 3N, 3TM, B100, Jetstream 3201 series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company and AiResearch Manufacturing Company of Arizona) TPE331-10-501C, -10-511C, -10-501K, -10-511K, -10-501M, -10-511M, -10AV-511B, -10AV-511M, -10GP-511D, -10GT-511D, -10N-511S, -10N-512S, -10N-513S, -10N-514S, -10N-515S, -10N-531S, -10N-532S, -10N-533S, -10N-534S, -10N-535S, -10P-511D, -10R-501C, -10R-502C, -10R-511C, -10R-512C, -10R-513C, -10T-511D, -10T-511K, -10T-511M, -10T-512K, -10T-513K, -10T-515K, -10T-516K, -10T-517K, -10U-501G, -10U-502G, -10U-511G, -10U-512G, -10U-503G, -10U-513G, -10UA-511G, -10UF-501H, -10UF-511H, -10UF-512H,-10UF-513H, -10UF-514H, -10UF-515H, -10UF-516H, -10UG-513H, -10UG-514H, -10UG-515H, -10UG-516H, -10UGR-513H, -10UGR-514H, -10UGR-516H, -10UR-513H, -10UR-516H, -11U-601G, -11U-602G, -11U-611G, and -11U-612G turboprop engines with first stage turbine disk part number (P/N) 3101520-1 or P/N 3107079-1, with serial numbers (SNs) listed in Table 1 of Honeywell International Inc. Alert Service Bulletin (ASB) TPE331-A72-2102, dated March 28, 2002, installed. These engines are installed on, but not limited to Mitsubishi MU-2B series, Construcciones Aeronauticas S.A. (CASA) C-212 series, Fairchild SA226 series (Swearingen Merlin and Metro series), Twin Commander 680 and 690 series (Jetprop Commander), Dornier 228 series, Beech 18 and 45 series, Beech Models JRB-6, 3N, 3TM, and B100, Cessna Aircraft Company Model 441 Conquest, and Jetstream 3201 series 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 Inspection (f) Perform a fluorescent penetrant inspection (FPI) of first stage turbine disks, P/N 3101520-1, in accordance with 2.A.(4)(a) through 2.A.(4)(d) of Accomplishment Instructions of ASB TPE331-A72-2102, dated March 28, 2002, and the following: (1) For first stage turbine disks with 4,100 cycles-since-new (CSN) or less, inspect at next access, but no later than 4,500 CSN. (2) For first stage turbine disks with more than 4,100 CSN, inspect at next access, but within 400 cycles-in-service (CIS) after the effective date of this AD. (3) First stage turbine disks that pass FPI must be eddy current inspected (ECI) before return to service. Information on procedures for returning disks to Honeywell Engines, Systems, & Services, for ECI, can be found in ASB TPE331-A72-2102, dated March 28, 2002. (4) First stage turbine disks, P/N 3107079-1, do not require initial inspection because they received an initial FPI and ECI at the time of conversion. Repetitive Inspections (g) Perform repetitive FPIs of first stage turbine disks P/N 3101520-1 and P/N 3107079-1, in accordance with 2.B.(3)(a) through 2.B.(3)(d) of Accomplishment Instructions of ASB TPE331-A72-2102, dated March 28, 2002 and the following: (1) FPI first stage turbine disks at each scheduled hot section inspection. (2) First stage turbine disks that pass FPI must be ECI before they are returned to service. Information on procedures for returning disks to Honeywell Engines, Systems, & Services, for ECI, can be found in ASB TPE331-A72-2102, dated March 28, 2002. Optional Terminating Action (h) Replacing a first stage turbine disk, that has a SN specified in this AD, with a disk that does not have a SN specified in this AD, is terminating action for the repetitive inspection requirements specified in paragraphs (g)(1) through (g)(2) of this AD. Definition (i) For the purposes of this AD, next access is when the turbine wheel assembly is removed from the engine or before installation into an engine. Alternative Methods of
Unsafe condition
This AD results from a report of a first stage turbine disk found cracked at the disk bore. We are issuing this AD to prevent cracked first stage turbine disks from causing uncontained disk separation, resulting in engine damage and shutdown and damage to the airplane.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1