Airworthiness Directive · Amendment 39-15196 · General Electric Company Aircraft Engine Group (GEAE) CF6-45A Series, CF6-50A, CF6-50C Series and CF6-50E Series Turbofan Engines
General Electric Company Aircraft Engine Group (GEAE) CF6-45A Series, CF6-50A, CF6-50C Series and CF6-50E Series Turbofan Engines
This AD applies to General Electric Company Aircraft Engine Group (GEAE) CF6-45A, 45A2, -50A, -50C, -50CA, -50C1, -50C2, -50C2B, -50C2D, -50C2F, -50C2R, -50E, -50E1, -50E2, and -50E2B turbofan engines that have a main engine control (MEC) with a part number (P/N) specified in Table 1 of this AD installed. These engines are installed on, but not limited to, Airbus A300 series airplanes, McDonnell Douglas DC-10, KC-10, and MD-10 series airplanes, and Boeing 747 series airplanes.
| Engine model series | Woodward P/N | GEAE P/N |
|---|---|---|
| CF6-50A, -50C, -50CA, -50C1, -50C2, -50C2B, -50C2D, -50C2F, -50C2R. | 8062-275 8062-279 | 9070M55P42 9070M55P44 |
| 8062-287 | 9070M55P49 | |
| 8062-289 | 9070M55P51 | |
| 8062-819 | 9070M55P101 | |
| 8062-822 | 9070M55P102 | |
| 8062-824 | 9070M55P103 | |
| 8062-823 | 9070M55P104 | |
| 8062-826 | 9070M55P105 | |
| 8062-827 | 9070M55P106 | |
| 8062-828 | 9070M55P107 | |
| 8062-829 | 9070M55P108 | |
| CF6-45A, -45A2, -50E, -50E1, -50E2, -50E2B | 8062-276 8062-280 | 9187M29P10 9187M29P11 |
| 8062-290 | 9187M29P14 | |
| 8062-291 | 9187M29P15 | |
| 8062-817 | 9187M29P100 | |
| 8062-820 | 9187M29P101 | |
| 8062-896 | 9187M29P22 | |
| 8062-897 | 9187M29P23 | |
| 8062-898 | 9187M29P20 | |
| 8062-899 | 9187M29P21 |
(d) This AD results from reports of five events involving fractured compressor discharge pressure (CDP) restoring spring assembly. We are issuing this AD to prevent loss of engine thrust control that could lead to loss of control of the airplane.
The FAA is adopting a new airworthiness directive (AD) for GEAE CF6-45A, -45A2, -50A, -50C, -50CA, -50C1, -50C2, -50C2B, -50C2D, - 50C2F, -50C2R, -50E, -50E1, - 50E2, and -50E2B turbofan engines. This AD requires replacing the compressor discharge pressure (CDP) restoring spring assembly on certain main engine controls (MECs) or re-marking MECs that already incorporate GEAE Service Bulletin (SB) No. CF6-50 S/B 73-0119, dated March 21, 2005. This AD results from reports of five events involving fractured CDP restoring spring assemblies. We are issuing this AD to prevent loss of engine thrust control that could lead to loss of control of 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 CF6-50A model engines and -50C series engines that have an MEC that has a P/N listed in Table 1 of this AD, replace the CDP restoring spring assembly as follows in Table 2 of this AD:
| If the CDP restoring spring assembly in your MEC | Then | By | Use |
|---|---|---|---|
| (1) Was already replaced using GEAE CF6-50 S/B 73-0119, dated March 21, 2005 | Re-mark the MEC | The next time the MEC is routed for repair such as the next MEC shop visit | Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6-50 S/B 73-0119, Revision 02, dated March 9, 2007. |
| (2) Was already replaced within 10,000 or fewer hours time-in-service (TIS) before the effective date of this AD, and the replacement spring assembly (P/N 3018-248) had zero hours TIS | Replace the spring assembly and remark the MEC | The first MEC shop visit or engine shop visit after the MEC exceeds 10,000 hours TIS, but do not exceed 20,000 hours TIS | Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6-50 S/B 73-0119, Revision 02, dated March 9, 2007. |
| (3) Has more then 10,000 hours TIS | Replace the spring assembly and remark the MEC | The next MEC shop visit or engine shop visit whichever occurs first | Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6-50 S/B 73-0119, Revision 02, dated March 9, 2007. |
For CF6-45A series and -50E series engines that have an MEC that has a P/N listed in Table 1 of this AD, replace the CDP restoring spring assembly as follows in Table 3 of this AD:
| If the CDP restoring spring assembly in your MEC | Then | By | Use |
|---|---|---|---|
| (1) Was already replaced within 10,000 or fewer hours time-in-service (TIS) before the effective date of this AD, and the replacement spring assembly (P/N 3018-248) had zero hours TIS | Replace the spring assembly and remark the MEC | The first MEC shop visit or engine shop visit after the MEC exceeds 10,000 hours TIS, but do not exceed 20,000 hours TIS | Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6-50 S/B 73-0120, dated March 21, 2007. |
| (2) Has more then 10,000 hours TIS | Replace the spring assembly and remark the MEC | The next MEC shop visit or engine shop visit whichever occurs first | Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6-50 S/B 73-0120, dated March 21, 2007. |
For the purpose of this AD, a shop visit is induction of the engine or MEC into the shop for any cause.
(i) After the effective date of the AD, do not install an MEC that:
(1) Has not complied with SB No. CF6-50 S/B 73-0119, Revision 02, dated March 9, 2007 or earlier revision, or SB No. CF6-50 S/B 73-0120, dated March 21, 2007, or
(2) Has not had the CDP restoring spring replaced with a spring assembly, P/N 3018-248, or FAA-approved equivalent spring assembly, within the previous 10,000 hours of MEC operation.
