Airworthiness Directive · Amendment 39-11830 · CFM International CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5A, -5B, -5C Series Turbofan Engines
CFM International CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5A, -5B, -5C Series Turbofan Engines
CFM International CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5A, -5B, -5C series engines installed on but not limited to McDonnell Douglas DC-8 series, Boeing 737 series, Airbus Industrie A319, A320, A321 and A340 series, as well as Boeing E-3, E-6, and KC-135 (military) series airplanes.
Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5A, -5B, -5C series turbofan engines, that requires initial and repetitive visual inspections of the fuel pump filter cover helicoil inserts and bolts for damage, and, if necessary, repair or replacement with serviceable parts. This amendment also requires the installation of new or reworked fuel pumps that incorporate an improved filter cover retention design (D-bolts), or an on-wing repair of existing fuel pumps, as terminating action to the inspections. This amendment is prompted by reports that fuel pump filter cover helicoil inserts have loosened or pulled out. The actions specified by this AD are intended to prevent fuel leakage from between the fuel pump filter cover and gear housing, which could result in an engine fire and damage to the airplane.
Required as indicated, unless accomplished previously.
To prevent fuel leakage from between the fuel pump filter cover and gear housing which could result in an engine fire and damage to the airplane, accomplish the following:
Perform initial and repetitive visual inspections of the fuel pump filter cover helicoil inserts and bolts for damage in accordance with Section 2, Accomplishment Instructions, of the applicable Service Bulletins (SBs) listed in paragraph (a)(5) of this AD, as follows:
(1) If the fuel pump has not been previously inspected prior to the effective date of this AD, inspect at the next fuel filter replacement, but not to exceed 200 cycles-in-service (CIS) after the effective date of this AD.
(2) If the fuel pump has been previously inspected prior to the effective date of this AD, inspect at the next fuel filter replacement.
(3) Thereafter, inspect at each fuel filter replacement.
(4) If damage equals or exceeds the reject criteria stated in Section 2, Accomplishment Instructions, of the SBs listed in paragraph (a)(5) of this AD, prior to further flight remove the fuel pump from service and replace or repair the helicoil in accordance with Section 2, Accomplishment Instructions, of the SBs listed in paragraph (a)(5), (b) or (c) as applicable, of this AD.
(5) Inspect and replace, if necessary, in accordance with the CFMI SB that applies to your engine from the following list:
CFM56-2 SB 73-110, Revision 2, dated April 29, 1999.
CFM56-2A SB 73-055, Revision 1, dated April 29, 1999.
CFM56-2B SB 73-076, Revision 1, dated April 29, 1999.
CFM56-3/3B/3C SB 73-126, Revision 1, dated April 29, 1999.
CFM56-5 SB 73-136, Revision 2, dated April 29, 1999.
CFM56-5B SB 73-056, Revision 2, dated April 29, 1999.
CFM56-5C SB 73-073, Revision 2, dated April 29, 1999.
Remove and replace the fuel pump with a newly manufactured or reworked fuel pump that incorporates a D-bolt filter cover attachment. This action must be done at the next engine or fuel pump shop visit, which ever occurs first, but no later than 5 years from the effective date of this AD in accordance with the CFMI SB that applies to your engine from the following list:
CFM56-2 SB 73-A113, dated August 17, 1999.
CFM56-2A SB 73-A058, dated August 17, 1999.
CFM56-2B SB 73-A079, Revision 1, dated October 22, 1999.
CFM56-3/3B/3C SB 73-A129, dated August 17, 1999.
CFM56-5 SB 73-A143, dated June 18, 1999.
CFM56-5B SB 73-A062, dated June 18, 1999.
CFM56-5C SB 73-A078, dated June 21, 1999.
Installation of a new or reworked fuel pump that incorporates a D-bolt filter cover attachment in accordance with this paragraph constitutes terminating action to the inspections required by paragraph (a) of this AD.
(c) An alternative terminating action is an on-wing repair that may be performed. Terminating action must be accomplished no later than 5 years from the effective date of this AD, in accordance with one of the following CFMI SB's that applies to your engine:
CFM56-2 SB 73-109, Revision 1, dated January 7, 1998.
CFM56-2A SB 73-054, Revision 1, dated January 7, 1998.
CFM56-2B SB 73-074, Revision 1, dated January 12, 1998.
CFM56-3/3B/3C SB 73-125, Revision 1, dated January 7, 1998.
CFM56-5 SB 73-135, Revision 1, dated January 7, 1998.
CFM56-5B SB 73-055, Revision 1, dated January 7, 1998.
CFM56-5C SB 73-070, Revision 1, dated January 7, 1998.
Inspection, replacement or repair of fuel pumps, in accordance with paragraph (a), (b) or (c) of this AD, on all engines installed on the same airplane by the same individual prior to the same flight is prohibited.
For the purpose of this AD:
(1) A serviceable part is defined as a part with gear housing helicoil inserts that meet the inspection requirements of the applicable CFMI SBs listed in paragraph (a)(5) of this AD. A serviceable part is also defined as a fuel pump that has been newly manufactured, reworked or repaired in accordance with the applicable CFMI SBs listed in paragraphs (a)(5), (b) or (c) of this AD.
(2) A fuel pump shop visit is defined as introduction of an engine into a shop for the purpose of removal of the fuel pump from the gearbox.
(3) An engine shop visit is defined as introduction of an engine into a shop for the purpose of maintenance or inspection.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
