Airworthiness directives › 2016-22-11
AD 2016-22-11 Airworthiness Directives; Engine Alliance Turbofan Engines
Applicability*9
This AD applies to all Engine Alliance GP7270 and GP7277 turbofan engines with a high-pressure turbine (HPT) stage 2 nozzle segment, part number (P/N) 2101M24G01, 2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05, or 2101M24G06, installed.
Compliance
Replace HPT stage 2 nozzle segments, P/N 2101M24G01, 2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05, and 2101M24G06, at the next piece-part exposure, with parts eligible for installation.
Required actions
For the purpose of this AD, piece-part exposure is when the HPT stage 2 nozzle is removed from the engine and completely disassembled.
Unsafe condition
Comply with this AD within the compliance times specified, unless already done. (1) Perform a 360 degree borescope inspection of the HPT stage 1 shroud and stage 2 nozzle as follows: (i) For engines with nozzles installed at a shop visit that did not include full engine overhaul, borescope inspect the HPT stage 1 shroud and stage 2 nozzle as follows: (A) If the nozzle has fewer than 1,050 cycles-since-new (CSN) or cycles-since-repair (CSR) on the effective date of this AD, before the nozzle has accumulated 1,100 CSN or CSR. (B) If the nozzle has 1,050 or more CSN or CSR on the effective date of this AD, within the next 50 cycles. (ii) For all other engines, borescope inspect the HPT stage 1 shroud and HPT stage 2 nozzle as follows: (A) If the nozzle has fewer than 1,450 CSN or CSR on the effective date of this AD, before the nozzle has accumulated 1,500 CSN or CSR. (B) If the nozzle has 1,450 or more CSN or CSR on the effective date of this AD, within the next 50 cycles. (iii) Thereafter, repetitively borescope inspect the HPT stage 1 shroud and stage 2 nozzle as follows: (A) For engines with HPT stage 2 nozzle segments, P/N 2101M24G01, 2101M24G02, or 2101M24G03, within every 150 additional cycles-in-service (CIS). (B) For engines with HPT stage 2 nozzle segments, P/N 2101M24G04, 2101M24G05, or 2101M24G06, within every 300 additional CIS. (2) If any burn holes are detected through the surface of the nozzle or if the shroud is distorted radially inward with evidence of blade tip rubs, remove the HPT stage 1 shroud and HPT stage 2 nozzle from service before further flight.
Affected ADs
This AD replaces AD 2013-02-06, Amendment 39-17327 (78 FR 5710, January 28, 2013).
Read the original on the Federal Register →
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