Airworthiness Directive · Amendment 39-16315 · Turbomeca Astazou XIV B and XIV H Turboshaft Engines
Turbomeca Astazou XIV B and XIV H Turboshaft Engines
Superseded. A later AD replaced this one: AD 2016-12-07. Comply with the one in force.
This AD applies to Turbomeca Astazou XIV B and XIV H turboshaft engines with the following part number (P/N) third stage turbine wheels that incorporate modification AB 173 (Turbomeca Service Bulletin (SB) No. 283 72 0091) or modification AB 208 (Turbomeca SB No. 283 72 0117), but that do not incorporate Turbomeca SB No. 283 72 805:
(1) Third stage turbine wheels P/N 0265257000, all serial numbers (S/Ns);
(2) Third stage turbine wheels P/N 0265257020, all S/Ns;
(3) Third stage turbine wheels P/N 0265257060, all S/Ns;
(4) Third stage turbine wheels P/N 0265257050, of the S/Ns listed in Appendix 1 of Turbomeca Mandatory Service Bulletin (MSB) No. 283 72 0804, Version C, dated October 23, 2009.
(5) These engines are installed on, but not limited to, single-engine Aerospatiale AS319B “Alouette III” and AS342J “Gazelle” helicopters.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions.
(1) For any affected third stage turbine wheel that on the effective date of this AD has accumulated fewer than 500 cycles-since-last-overhaul or repair, or since-new if the engine has never been overhauled or repaired:
(i) Within 300 additional cycles, perform a dye penetrant inspection on the rear face of the third stage turbine wheel.
(ii) Use Section 2, Instructions to Be Incorporated, of Turbomeca MSB No. 283 72 0804, Version C, dated October 23, 2009, to do the inspection.
(iii) Perform a second dye penetrant inspection when the engine has accumulated between 450 and 550 cycles from the first inspection.
(2) For any affected third stage turbine wheel that on the effective date of this AD, has accumulated 500 or more but fewer than 700 cycles-since-last-overhaul or repair, or since-new if the engine has never been overhauled or repaired:
(i) Within 200 additional cycles, perform a dye penetrant inspection on the rear face of the third stage turbine wheel.
(ii) Use Section 2, Instructions to Be Incorporated, of Turbomeca MSB No. 283 72 0804, Version C, dated October 23, 2009, to do the inspection.
(3) For any affected third stage turbine wheel that on the effective date of this AD, has accumulated 700 or more but fewer than 1,200 cycles-since-last-overhaul or repair, or since-new if the engine has never been overhauled or repaired:
(i) Within 150 additional cycles, perform a dye penetrant inspection on the rear face of the third stage turbine wheel.
(ii) Use Section 2, Instructions to Be Incorporated, of Turbomeca MSB No. 283 72 0804, Version C, dated October 23, 2009, to do the inspection.
(4) If any crack indication is found, then before further flight, remove the third stage turbine wheel from service.
(5) For any affected third stage turbine wheel that on the effective date of this AD has accumulated 1,200 or more cycles-since-last-overhaul or repair, or since-new if the engine has never been overhauled or repaired, no action is required.
This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) and or service information as follows:
(1) EASA AD 2010-0004, dated January 5, 2010, requires removing the engine from service before further flight if a third stage turbine wheel is found cracked.
(2) This AD requires removing the third stage turbine wheel from service before further flight if a third stage turbine wheel is found cracked.
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
