Airworthiness Directive · Amendment 39-19100 · Compressor bleed governor
General Electric Company Turbofan Engines
Superseded. A later AD replaced this one: AD 2019-22-05. Comply with the one in force.
This AD applies to General Electric Company (GE) CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34-8C5B1 engines with serial numbers: 965101 through 965670 inclusive; 194101 through 194999 inclusive; and 195101 through 195653 inclusive.
We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34- 8C5B1 engines. This AD requires an inspection of the bleed air manifold link rod assemblies and the supply, return, and drain fuel fittings on the operability bleed valve (OBV). This AD was prompted by an engine fire that occurred as a result of malfunctions related to the OBV. We are issuing this AD to address the unsafe condition on these products.
(1) Inspect the bleed air manifold link rod assemblies and the OBV supply, return, and drain fuel fittings within 500 flight hours after the effective date of this AD.
(2) Use the Accomplishment Instructions, paragraph 3.B., in GE Service Bulletin (SB) CF34-8C-AL S/B 75-0019 Revision 01, dated October 24, 2017, to do the inspection. Replace parts that fail this inspection according to the following criteria:
(i) Replace any OBV that fails the inspection with a part eligible for installation before further flight.
(ii) Replace any additional hardware that fails inspection within 50 flight cycles. The engine can be returned to service each day for up to the 50 flight cycles if the OBV rosan rings and fittings are examined each day for fuel leaks and looseness based on the criteria in Table 1 of GE SB CF34-8C-AL S/B 75-0019 Revision 01, dated October 24, 2017.
(3) The reporting instructions in paragraphs 3.B.(3), 3.B.(5)(e), 3.B.(6)(e), and 3.B.(8) of GE SB CF34-8C-AL S/B 75-0019 Revision 01, dated October 24, 2017, are not required by this AD.
