Airworthiness Directive · Amendment 39-15826 · General Electric Company CF6-80C2 and CF6-80E1 Series Turbofan Engines
General Electric Company CF6-80C2 and CF6-80E1 Series Turbofan Engines
Superseded. A later AD replaced this one: AD 2014-21-01. Comply with the one in force.
This AD applies to:
(1) General Electric (GE) CF6-80C2A1, -80C2A2, -80C2A3, -80C2A5, -80C2A8, -80C2A5F, -80C2B1, -80C2B2, -80C2B4, -80C2B6, -80C2B1F, -80C2B1F1, -80C2B1F2, -80C2B2F, -80C2B3F, -80C2B4F, -80C2B5F, -80C2B6F, -80C2B6FA, -80C2B7F, -80C2B8F, -80C2D1F, -80C2L1F, -80C2K1F turbofan engine models with fuel manifold part numbers (P/Ns) 1303M31G12 and 1303M32G12, installed in drainless fuel manifold assemblies (introduced by GE Aircraft Engines (GEAE) Service Bulletin (SB) CF6-80C2 S/B 73-0253). These engines are installed on, but not limited to, Boeing 747, 767, MD11, and Airbus A300-600 and A310 airplanes.
(2) This AD also applies to GE CF6-80E1A1, -80E1A2, -80E1A3, -80E1A4, -80E1A4/B turbofan engine models with fuel manifold P/Ns 1303M31G12 and 1303M32G12, installed in drainless fuel manifold assemblies (introduced by GEAE SB CF6-80E1 S/B 73-0026). These engines are installed on Airbus A330 airplanes.
The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80C2 and CF6-80E1 series turbofan engines with fuel manifolds part numbers (P/Ns) 1303M31G12 and 1303M32G12, installed in drainless fuel manifold assemblies (introduced by GE Aircraft Engines (GEAE) Service Bulletins (SB) CF6-80C2 S/B 73- 0253 and CF6-80E1 S/B 73-0026). This AD requires removing the loop clamps that hold the fuel manifold to the compressor rear frame (CRF) damper brackets, inspecting the fuel manifold for wear at each clamp location, and replacing the clamps with new, zero-time parts. This AD also requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) and air carrier's Continuous Airworthiness Maintenance Programs (CAMP) to require repetitive fuel manifold inspection and loop clamp replacement. This AD results from reports of fuel leaks during engine operation. We are issuing this AD to prevent fuel leaks that could result in an under- cowl fire and 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.
Using Table 1 of this AD, Schedule for Inspections and Replacements, accomplish the following actions in the intervals indicated in the table: remove and discard all loop clamps, P/N J1220G10, or part manufacturer approval (PMA) equivalent, that hold the fuel manifold to the compressor rear frame (CRF) friction damper brackets. Inspect the fuel manifold for wear at each clamp location as specified in paragraphs (g) and (h) of this AD. Replace the discarded loop clamps with new, zero-time clamps.
| If: | Then replace clamps and inspect within: |
|---|---|
| (1) The engine was previously inspected using GEAE SB CF6-80C2 S/B 73-0326, dated March 5, 2003, for CF6-80C2 engines; or GEAE SB CF6-80E1 S/B 73-0061, dated April 14, 2003, for CF6-80E1 engines | 1,750 flight hours (FH) time-since-last-inspection (TSLI) or within 4 months after the effective date of this AD. |
| (2) Used loop clamps or clamps of unknown heritage were installed at last shop visit | 1,750 FH time-since-last-shop-visit or within 4 months after the effective date of this AD. |
| (3) The engine is a first-run engine or is an engine with zero-time, new loop clamps previously installed on-wing or at shop visit | 7,500 FH time-since-new or since zero-time, new loop clamps were installed (regardless if previously inspected per GEAE SB CF6-80C2 S/B 73-0326 or GEAE SB CF6-80E1 S/B 73-0061). |
| (4) The engine has already exceeded the 1,750 FH initial inspection threshold on the effective date of this AD, but has fewer than 4,500 flight hours TSLI | 4,500 FH TSLI, or 4 months after the effective date of this AD, whichever occurs first. |
| (5) The engine has already exceeded the 4,500 FH initial inspection threshold on the effective date of this AD | 4 months after the effective date of this AD. |
Remove any tape at any clamp location. Visually inspect the full circumference of the manifold for wear at each clamp location. If any wear is found, follow paragraph (h) of this AD.
(h) When the fuel manifold shows any signs of wear, determine the depth of the wear as follows:
(1) Measure the outside diameter of the tube adjacent to the worn area.
(2) Measure the worn area at the smallest diameter.
(3) Subtract the measurement of the worn tube diameter from the unworn diameter measurement. Allowable wear is 0.0035 inch.
(4) Replace fuel manifolds with wear greater than 0.010 inch before further flight.
(5) Replace fuel manifolds with wear greater than 0.0035 inch but less than 0.010 inch, within 50 flight cycles.
(i) Within 30 days of the effective date of this AD, revise the air carrier's approved CAMP and Instructions for Continued Airworthiness (ICA) Chapter 5, Airworthiness Limitation Section for the CF6-80C2 and CF6-80E1 series engines to require:
(1) Repetitive inspections of fuel manifolds, P/Ns 1303M31G12 and 1303M32G12, installed in drainless fuel manifold assemblies introduced by CF6-80C2 S/B 73-0253 and CF6-80E1 S/B 73-0026, as detailed in paragraphs (g) and (h) of this AD, at 7,500 FH intervals.
(2) Mandatory removal of all loop clamps that hold the fuel manifold, P/Ns 1303M31G12 and 1303M32G12, to the CRF damper brackets, at each inspection.
(3) Replacement of all loop clamps with new, zero-time loop clamps, at each inspection.
