Airworthiness Directive · Amendment 39-16161 · 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
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 superseding an existing airworthiness directive (AD) for GE CF34-1A, CF34-3A, and CF34-3B series turbofan engines. That AD currently requires removing from service certain part number (P/N) and serial number (S/N) fan blades within compliance times specified in the 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 supersedure requires the same actions but corrects the effectivity for certain fan blades requiring corrective actions and changes the effective date of the current AD. This AD supersedure results from the FAA discovering that the existing AD has an incorrect effectivity for certain fan blades requiring corrective actions, and 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 S/N 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 that meet all of the following criteria, perform the actions specified in paragraph (i) of this AD:
(1) Fan drive shaft, P/N 6036T78P02, installed; and
(2) Airworthiness limitation section fan drive shaft life limit of 22,000 cycles-since-new (CSN); and
(3) Installed fan blades, P/Ns 6018T30P14 or 4923T56G08, that have any fan blade S/Ns listed in Appendix A of General Electric Aircraft Engines (GEAE) SB No. CF34-AL S/B 72-0245, Revision 01, dated July 30, 2008.
(g) For CF34-3A1 engines that meet all of the following criteria, perform the actions specified in paragraph (i) of this AD:
(1) Fan drive shaft, P/N 6036T78P02, installed; and
(2) Airworthiness limitation section fan drive shaft life limit of 15,000 CSN; and
(3) In compliance with GEAE SB No. 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
(4) Installed fan blades, P/Ns 6018T30P14 or 4923T56G08, that have any fan blade S/Ns listed in Appendix A of GEAE SB No. CF34-AL S/B 72-0245, Revision 01, dated July 30, 2008.
(h) For CF34-3B1 engines that meet all of the following criteria, perform the actions specified in paragraph (i) of this AD:
(1) Installed fan blades, P/Ns 6018T30P14 or 4923T56G08; and
(2) With any fan blade S/Ns listed in Appendix A of GEAE SB No. 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 listed 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 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 No. 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 No. 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 No. 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 No. 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 No. 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 No. CF34-AL S/B 73-0046, Revision 02, dated August 27, 2008, to perform the inspection.
For CF34-3A1 engines that meet all of the following criteria, perform the actions specified in paragraph (l) of this AD:
(1) Fan drive shaft, P/N 6036T78P02, installed; and
(2) Airworthiness limitation section fan drive shaft life limit of 15,000 CSN that are not in compliance with GEAE SB No. CF34-AL S/B 72-0147, dated May 21, 2003, Revision 01, dated October 17, 2003, Revision 02, dated August 5, 2004, or Revision 03, dated August 28, 2003; and
(3) With fan blades, P/Ns 6018T30P14 or 4923T56G08, that have any fan blade S/Ns listed in Appendix A of GEAE SB No. CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008.
(k) For CF34-1A, CF34-3A, CF34-3A2, and CF34-3B engines that meet all of the following criteria, perform the actions specified in paragraph (l) of this AD:
(1) Installed fan blades, P/N 6018T30P14 or P/N 4923T56G08; and
(2) Installed fan blade S/Ns listed in Appendix A of GEAE SB No. 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 listed fan blades, P/N 6018T30P14, from service within 2,400 CSN.
(2) Remove listed 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 No. 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 No. 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 No. 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 any fan blade S/Ns listed in Appendix A of GEAE SB No. 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 No. 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 No. 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 No. 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 No. 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 No. 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 No. CF34-BJ S/B 73-0062, Revision 02, dated August 27, 2008, to perform the inspection.
