General Electric Turbine Engines - CF34 Series
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/CF34/4 and issues the following AD under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
AD/CF34/4
Amdt 1
Main Fuel Control 7/2000
Applicability: General Electric CF34-1A, -3A, -3A1, -3A2, -3B and -3B1 series engines installed on but not limited to Bombardier, Inc. Canadair model CL-600-2A12, -2B16 and - 2B19 aircraft.
Requirement: 1. If a Main Fuel Control (MFC) part numbers (P/N’s) 6078T55P02 thru P10 inclusive is installed, and the MFC has Buna-N preformed packings (O-rings), P/N’s R1307P020 and R1307P141 incorporated, do one of the following:
(a) Replace Buna-N O-rings with Viton O-rings, P/N’s M83485-1-020 (M83485/1-020) and 37B201714P130, in accordance with the Accomplishment Instructions, paragraph 3.A., of alert service bulletin (ASB) CF34AL 73-A0025, dated July 7, 1999 or ASB CF34BJ 73-A0040, dated July 7, 1999, OR
(b) For all CF34-3A1 engines with serial numbers (SN’s) 807001 and up, CF34- 3B engines with SN’s 872001 and up, and CF34-3B1 engines with SN’s 872001 and up, with MFC P/Ns 6078T55P02 thru P10 inclusive installed, install a MFC with a flange vent groove that conforms to the requirements of CF34 ASB CF34AL S/B 73-0026 dated August 12, 1999, or CF34BJ S/B 73- 0041, dated August 12, 1999 or Revision 1, dated November 1, 1999.
2. For all CF34-1A, -3A, and -3A2 series engines with SN’s 350003 thru 350525, install an MFC with a flange groove that conforms to the requirements of CF34 ASB CF34BJ S/B 73-0041 dated August 12, 1999 or Revision 1 dated November 1, 1999.
3. Install a serviceable MFC with improved overspeed protection as follows:
(a) For all CF34-1A, -3A, and -3A2 series engines, install a serviceable MFC in accordance with step 2A thru step 2G of the Accomplishment Instructions of CF34 ASB No. A73-33, dated November 21, 1997, or Revision 1, dated May 29, 1998 or Revision 2, dated March 9, 1999, or in accordance with step 3A(1) thru step 3A(7) of the Accomplishment Instructions of CF34 ASB No. CF34BJ 73-A0033, Revision 3, dated September 9, 1999, or Revision 4, dated November 1, 1999.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
(b) For CF34-3A1, and -3B series engines installed on Canadair aircraft models CL 601 or CL 604 (Challenger aircraft), install a serviceable MFC in accordance with step 2A thru step 2G of the Accomplishment Instructions of CF34 ASB No. A73-33, dated November 21, 1997, or Revision 1, dated May 29, 1998, or Revision 2, dated March 9, 1999 or in accordance with step 3A(1) thru step 3A(7) of the Accomplishment Instructions of CF34 ASB No. CF34BJ 73-A0033, Revision 3, dated September 9, 1999, or Revision 4, dated November 1, 1999.
(c) For CF34-3A1 and -3B1 series engines installed on Canadair aircraft model CL 601RJ (Regional Jet aircraft), install a serviceable MFC in accordance with step 2A thru step 2G of the Accomplishment Instructions of CF34 ASB No. A73-19, Revision 1, dated February 20, 1998, or Revision 2, dated March 9, 1999 or in accordance with step 3A(1) thru step 3A(7) of the Accomplishment Instructions of CF34 ASB CF34AL 73-A0019, Revision 3, dated September 9,1999.
Replacing an MFC with a serviceable MFC, constitutes terminating action for the requirements of this AD. For the purposes of this AD, a serviceable MFC is defined as any MFC that incorporates the improved overspeed protection modifications, or an MFC that has been reworked to provide the improved overspeed protection as provided by the applicable GE ASB and is not one of the following P/Ns; 6078T55P02 thru P10 inclusive, or 6047T74P07, 6047T74P09, or 6091T07P01,
Note: FAA AD 99-23-26R1 refers.
Compliance: 1. Unless accomplished previously, before 6 January 2000.
2. Unless accomplished previously, at the next time the engine is removed or the next time the MFC is removed.
3. Unless accomplished previously;
(a) at the next hot section inspection, or within 53 months after the effective date of this AD, whichever occurs first;
(b) at the next hot section inspection, or within 53 months after the effective date of this AD, whichever occurs first;
(c) within 4000 hours time in service (TIS) after the effective date of this AD, or within 17 months after the effective date of this AD, whichever occurs first.
This Amendment becomes effective on 13 July 2000.
Background: This AD is issued to prevent uncommanded engine accelerations, which could result in an engine overspeed, uncontained engine failure, and damage to the aircraft. The requirements of this AD supersede the requirements of AD/CF34/3 which has been cancelled. Engines in compliance with AD/CF34/3 may be affected by the requirements of this AD.
This Amendment reflects corrections to the FAA AD as detailed in FAA AD 99-23- 26R1.
The original issue of this Airworthiness Directive became effective on 22 December 1999.
Eugene Paul Holzapfel
Delegate of the Civil Aviation Safety Authority 31 May 2000
The above AD is notified in the Commonwealth of Australia Gazette on 14 June 2000.