Airworthiness Directive · Amendment 39-16103 · General Electric Company (GE) CF34-1A, CF34-3A, and CF34-3B Series Turbofan Engines
General Electric Company (GE) CF34-1A, CF34-3A, and CF34-3B Series Turbofan Engines
Superseded. A later AD replaced this one: AD 2010-01-04. Comply with the one in force.
This AD applies to General Electric Company (GE) CF34-1A, CF34-3A, CF34-3A1, CF34-3A2, CF34-3B, and CF34-3B1 turbofan engines. These engines are installed on, but not limited to, Bombardier Canadair Models CL-600-2A12, CL-600-2B16, and CL-600-2B19 airplanes.
The FAA is adopting a new airworthiness directive (AD) for GE CF34-1A, CF34-3A, and CF34-3B series turbofan engines. This AD requires removing from service certain part number (P/N) and serial number (SN) fan blades within compliance times specified in this AD, inspecting the fan blade abradable rub strip on certain engines for wear, inspecting the fan blades on certain engines for cracks, inspecting the aft actuator head hose fitting for correct position, and, if necessary, repositioning the hose fitting. This AD results from a report of an under-cowl fire and a failed fan blade. We are issuing this AD to prevent failure of certain P/N and SN fan blades and aft actuator head hoses, which could result in an under-cowl fire and subsequent damage to the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For CF34-3A1 engines with fan drive shaft, P/N 6036T78P02, and airworthiness limitation section life limit of 22,000 CSN; and
(g) For CF34-3A1 engines with fan drive shaft, P/N 6036T78P02, and airworthiness limitation section life limit of 15,000 CSN that are in compliance with GE Aircraft Engines (GEAE) Service Bulletin (SB) CF34-AL S/B 72-0147, dated May 21, 2003, Revision 01, dated October 17, 2003, Revision 02, dated August 5, 2004, or Revision 3, dated August 28, 2003; and
(h) For CF34-3B1 engines with fan blades, P/Ns 6018T30P14 or 4923T56G08, that have a fan blade SN listed in Appendix A of GEAE SB CF34-AL S/B 72-0245, Revision 01, dated July 30, 2008;
(i) Do the following for the engines meeting the criteria in paragraph (f), (g), or (h) of this AD, as applicable:
(1) Remove fan blades from service within 4,000 cycles-in-service (CIS) after the effective date of this AD or by December 31, 2010, whichever occurs first.
(2) For fan blades with 1,200 or more cycles-since-new (CSN) on the effective date of this AD, perform an initial visual inspection of the fan blade abradable rub strip for wear within 20 CIS after the effective date of this AD. Use paragraphs 3.A.(1) through 3.A.(2) of the Accomplishment Instructions of GEAE SB CF34-AL S/B 72-0250, Revision 01, dated November 26, 2008, to perform the inspection.
(3) For fan blades with fewer than 1,200 CSN on the effective date of this AD, perform an initial visual inspection of the fan blade abradable rub strip for wear within 1,220 CSN. Use paragraphs 3.A.(1) through 3.A.(2) of the Accomplishment Instructions of GEAE SB CF34-AL S/B 72-0250, Revision 01, dated November 26, 2008, to perform the inspection.
(4) If you find a continuous 360 degree rub indication, before further flight, visually inspect the fan blades using paragraphs 3.A.(2)(a) through 3.A.(2)(b) of the Accomplishment Instructions of GEAE SB CF34-AL S/B 72-0250, Revision 01, dated November 26, 2008.
(5) If you find a crack in the retaining pin holes of the fan blade, remove the blade from service.
(6) Within 75 cycles-since-last inspection (CSLI) or 100 hours-since-last-inspection (HSLI), whichever occurs later, perform a visual inspection of the fan blade abradable rub strip for wear. Use paragraphs 3.A.(1) through 3.A.(2) of the Accomplishment Instructions of GEAE SB CF34-AL S/B 72-0250, Revision 01, dated November 26, 2008, to perform the inspection.
(i) If you find a continuous 360 degree rub indication, before further flight, visually inspect the fan blades using paragraphs 3.A.(2)(a) through 3.A.(2)(b) of the Accomplishment Instructions of GEAE SB CF34-AL S/B 72-0250, Revision 01, dated November 26, 2008.
(ii) If you find a crack in the retaining pin holes of the fan blade, remove the blade from service.
(7) Within 750 hours time-in-service (TIS) after the effective date of this AD, visually inspect and, if necessary, reposition the aft actuator head hose fitting. Use paragraph 3.A of the Accomplishment Instructions of GEAE SB CF34-AL S/B 73-0046, Revision 02, dated August 27, 2008, to perform the inspection.
For CF34-3A1 engines with fan drive shaft, P/N 6036T78P02, and airworthiness limitation section life limit of 15,000 CSN, that are not in compliance with GEAE SB CF34-AL S/B 72-0147, dated May 21, 2003, Revision 01, dated October 17, 2003, Revision 02, dated August 5, 2004, or Revision 3, dated August 28, 2003; and
(k) For CF34-1A, CF34-3A, CF34-3A2, and CF34-3B engines with fan blades, P/N 6018T30P14 or P/N 4923T56G08, that have a fan blade SN listed in Appendix A of GEAE SB CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008;
(l) Do the following for the engines meeting the criteria in paragraph (j) or (k) of this AD as applicable:
(1) Remove fan blades, P/N 6018T30P14, from service within 2,400 CSN.
(2) Remove fan blades, P/N 4923T56G08, from service within 1,200 CIS since the bushing repair of the fan blade hole.
(3) For fan blades, P/N 6018T30P14, with more than 850 CSN, perform an initial eddy current inspection (ECI) of the fan blades for cracks within 350 CIS after the effective date of this AD. Use paragraphs 3.A. or 3.B. of the Accomplishment Instructions of GEAE SB CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008, to perform the inspection.
(4) For fan blades, P/N 6018T30P14, with 850 or fewer CSN on the effective date of this AD, perform an initial ECI of the fan blades for cracks within 1,200 CSN. Use paragraphs 3.A. or 3.B. of the Accomplishment Instructions of GEAE SB CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008, to perform the inspection.
(5) If you find a crack in the retaining pin holes of the fan blade, remove the blade from service.
(6) For fan blades, P/N 6018T30P14, within 600 CSLI, perform an ECI of the fan blades for cracks. Use paragraphs 3.A. or 3.B. of the Accomplishment Instructions of GEAE SB CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008, to perform the inspection.
(7) If you find a crack in the retaining pin holes of the fan blade, remove the blade from service.
(8) For engines with fan blades, P/N 6018T30P14, installed that have a fan blade SN listed in Appendix A of GEAE SB CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008, with 1,200 or more CSN on the effective date of this AD, and that haven't had an ECI of the fan blades for cracks, do the following:
(i) Perform an initial inspection of the fan blade abradable rub strip for wear within 20 CIS after the effective date of this AD. Use paragraph 3.A.(1) of the Accomplishment Instructions of GEAE SB CF34-BJ S/B 72-0231, Revision 02, dated November 26, 2008, to perform the inspection.
(ii) If you find a continuous 360 degree rub indication, before further flight, perform a visual inspection of the fan blades for cracks. Use paragraphs 3.A(2)(a) or 3.A(2)(b) of the Accomplishment Instructions of GEAE SB CF34-BJ S/B 72-0231, Revision 02, dated November 26, 2008, to perform the inspection.
(iii) If you find a crack in the retaining pin holes of the fan blade, remove the blade from service.
(9) For engines with fan blades, P/N 6018T30P14, installed, if you have performed an ECI of the fan blade, you don't need to inspect the fan blade abradable rub strip for wear.
(10) For engines with fan blades, P/N 6018T30P14, installed, within 75 CSLI or 100 HSLI, whichever occurs later, do the following:
(i) Perform a visual inspection of the fan blade abradable rub strip for wear. Use paragraph 3.A.(1) of the Accomplishment Instructions of GEAE SB CF34-BJ S/B 72-0231, Revision 02, dated November 26, 2008, to perform the inspection.
(ii) If you find a continuous 360 degree rub indication, before further flight, visually inspect the fan blades using paragraphs 3.A.(2)(a) through 3.A.(2)(b) of the Accomplishment Instructions of GEAE SB CF34-BJ S/B 72-0231, Revision 02, dated November 26, 2008.
(iii) If you find a crack in the retaining pin holes of the fan blade, remove the blade from service.
(11) For CF34-3A1 engines, within 300 hours TIS after the effective date of this AD, visually inspect and, if necessary, reposition the aft actuator head hose fitting. Use paragraph 3.A of the Accomplishment Instructions of GEAE SB CF34-BJ S/B 73-0062, Revision 02, dated August 27, 2008, to perform the inspection.
(12) For CF34-3B engines, within 400 hours TIS after the effective date of this AD, visually inspect and, if necessary, reposition the aft actuator head hose fitting. Use paragraph 3.A of the Accomplishment Instructions of GEAE SB CF34-BJ S/B 73-0062, Revision 02, dated August 27, 2008, to perform the inspection.
