Airworthiness directives › 2023-02-05
AD 2023-02-05 Airworthiness Directives; General Electric Company Turbofan Engines
Applicability*9
This AD applies to General Electric Company (GE) CF34-8C1, CF34-8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1 model turbofan engines, including engine models marked on engine data plate as CF34-8C5/B, CF34-8C5/M, CF34-8C5A1/B, CF34-8C5A1/M, CF34-8C5B1/B, CF34-8C5A2/B, and CF34-8C5A2/M.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Within 90 days after the effective date of this AD, revise the airworthiness limitations section (ALS) of the existing engine manual (EM) and the operator's existing approved maintenance or inspection program, as applicable, to incorporate the following requirements for fluorescent penetrant inspections of the combustion chamber assembly aft flange. (1) For combustion chamber assemblies with part numbers (P/Ns) 4145T11G08, 4145T11G09, 4180T27G01, or 4180T27G03 installed on GE CF34-8E model turbofan engines: (i) Replace Table 801, Static Structures—Life Limits (Table 801), with the revised Table 801 in TASK 05-11-05-200-801, dated March 4, 2021, from ESM 05-11-05 Static Structures—Life Limits (TASK 05-11-05-200-801), of GE CF34-8E EM GEK112031, Rev 43, dated April 1, 2022 (GE CF34-8E EM GEK112031), and (ii) Add TASK 05-21-03-200-801, dated April 1, 2019, from ESM 05-21-03 Airworthiness Limitations—Mandatory Inspection 001 (TASK 05-21-03-200-801), of GE CF34-8E EM GEK112031. Where the notes to Tables 801 and 802, included in TASK 05-21-03-200-801 of GE CF34-8E EM GEK112031, specify to perform the inspection within 2,200 cycles from the issuance date of the temporary revision (TR), this AD requires performing the inspection within 2,200 cycles from the effective date of this AD. (2) For combustion chamber assemblies with P/Ns 4126T87G04, 4126T87G05, 4126T87G07, 4126T87G08, 4180T27G04, 4923T82G01, or 4923T82G02 installed on GE CF34-8C1 model turbofan engines, or with P/Ns 4145T11G08, 4145T11G10, 4180T27G02, 4180T27G04, or 4923T82G02 installed on GE CF34-8C5, CF34-8C5/M, CF34-8C5A1, CF34-8C5A1/M, CF34-8C5A2, CF34-8C5A2/M, CF34-8C5A3, or CF34-8C5B1 model turbofan engines: (i) Replace Tables 801 (for -8C1) and 802 (for -8C5) Static Structures—Life Limits (Table 801 and Table 802), with the revised Tables 801 and 802 in TASK 05-11-05-200-801, dated March 4, 2021, from ESM 05-11- 05 Static Structures—Life Limits (TASK 05-11-05-200-801), of GE CF34-8C EM GEK105091, Rev 51, dated April 1, 2022 (GE CF34-8C EM GEK105091); and (ii) Add TASK 05-21-03-200-801, dated April 1, 2019, from ESM 05-21-03 Airworthiness Limitations—Mandatory Inspection 001 (TASK 05-21-03-200-801), of GE CF34-8C EM GEK105091. Where the notes to Tables 801, 802, 803, 804, and 805, included in TASK 05-21-03-200-801 of GE CF34-8C EM GEK105091, specify to perform the inspection within 2,200 cycles from the issuance date of the TR, this AD requires performing the inspection within 2,200 cycles from the effective date of this AD. (3) For combustion chamber assemblies with P/Ns 4145T11G08, 4145T11G10, 4180T27G02, 4180T27G04, or 4923T82G02 installed on GE CF34-8C5B1/B, CF34-8C5/B, CF34-8C5A1/B, or CF34-8C5A2/B model turbofan engines: (i) Replace Table 801 (for/B -8C5) Static Structures—Life Limits with the revised Table 801 in TASK 05-11-25-200-801, of GE CF34-8C EM GEK105091; and (ii) Add TASK-05-21-03-200-801, of GE CF34-8C EM GEK105091. Where the notes to Tables 801, 802, 803, 804, and 805, included in TASK 05-21-03-200-801 of GE CF34-8C EM GEK105091, specify to perform the inspection within 2,200 cycles from the issuance date of the TR, this AD requires performing the inspection within 2,200 cycles from the effective date of this AD. (4) After performing the actions required by paragraphs (g)(1) through (3) of this AD, except as provided in paragraph (i) of this AD, no alternative life limits may be approved.
Unsafe condition
This AD was prompted by a predicted reduction in the cyclic life of the combustion chamber assembly aft flange. The FAA is issuing this AD to prevent failure of the combustion chamber assembly. The unsafe condition, if not addressed, could result in combustion chamber assemblies failing before reaching their published life limit, uncontained release of the combustion chamber assembly, damage to the engine, and damage to the airplane.
Affected ADs
None.
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