Airworthiness Directive · Amendment 39-11868 · General Electric Company CF6-45, -50, -80A, -80C2, and -80E1 Turbofan Engines
General Electric Company CF6-45, -50, -80A, -80C2, and -80E1 Turbofan Engines
Superseded. A later AD replaced this one: AD 2002-25-08. Comply with the one in force.
This airworthiness directive is applicable to General Electric Company (GE) CF6-45, -50, -80A, -80C2, and -80E1 turbofan engines with high pressure compressor rotor stage 3-9 spools with the following part numbers (P/N's). These engines are installed on, but not limited to, Airbus A300, A310, and A330 series, Boeing 747 and 767 series, and McDonnell Douglas DC-10 and MD-11 series airplanes.
| Engine model | HPCR 3-9 spool P/N |
|---|---|
| CF6-45/50 Series Engines | 9136M89G02, 9136M89G03, 9136M89G06, 9136M89G07, 9136M89G08, 9136M89G09, 9136M89G17, 9136M89G18, 9136M89G19, 9136M89G21, 9136M89G22, 9136M89G27, 9273M14G01, 9331M29G01, 9253M85G01, 9253M85G02 |
| CF6-80A Series Engines | 99136M89G10, 9136M89G11, 9136M89G20, 9136M89G21, 9136M89G22, 9136M89G27 |
| CF6-80C2 Series Engines | 1333M66G01, 1333M66G03, 1333M66G07, 1333M66G09, 1781M52P01, 1781M53G01, 1854M95P01, 1854M95P02, 1854M95P03, 1854M95P04, 1854M95P05, 1854M95P06, 1854M95P07, 9380M28P05 |
| CF6-80E1 Series Engines | 1669M22G01, 1669M22G03, 1782M22G01, 1782M22G02 |
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 (j) 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) that is applicable to General Electric Company (GE) CF6-45, -50, -80A, - 80C2, and -80E1 turbofan engines with certain high pressure compressor rotor (HPCR) stage 3-9 spools installed. This action requires initial ultrasonic and eddy current inspections of certain HPCR stage 3-9 spools for cracks. This amendment is prompted by an uncontained failure of an HPCR 3-9 spool. The actions specified in this AD are intended to detect cracks which can cause separation of the HPCR stage 3-9 spool and result in an uncontained engine failure.
Compliance with this AD is required as indicated below, unless already done.
To detect cracks which can cause separation of the HPCR stage 3-9 spool and result in an uncontained engine failure, perform the following inspections:
For HPCR stages 3-9 spools installed in CF6-45/50 series engines that have not been inspected in accordance with AD 99-24-15, do the following:
| Number of Cycles-Since-New (CSN) | Action | By the earliest of |
|---|---|---|
| (1) More than 7,000 CSN but fewer than 10,500 CSN after the effective date of this AD | Eddy current and ultrasonic inspect bores for cracks in accordance with ASB 72-A1108, Revision 3, dated November 12, 1999 | (i) Within the next 1,000 cycles-in-service (CIS) after the effective date of this AD, OR (ii) At the next engine shop visit (ESV) after the effective date of the AD, OR (iii) Before July 29, 2001. |
| (2) 10,500 or more CSN, after the effective date of this AD, on HPCR 3-9 spools P/N 9136M89G02, 9136M89G03, 9136M89G06, 9136M89G07, 9136M89G08, 9136M89G09, 9136M89G17, 9136M89G18, 9273M14G01, 9331M29G01, 9253M85G01, 9253M85G02 | Eddy current and ultrasonic inspect bores for cracks in accordance with ASB 72-A1108, Revision 3, dated November 12, 1999 | (i) Within the next 500 CIS after the effective date of this AD, OR (ii) At the next ESV after the effective date of the AD, OR (iii) Before May 31, 2001. |
| (3) 10,500 or more CSN, after the effective date of this AD, on HPCR 3-9 spools P/N 9136M89G19, 9136M89G21, 9136M89G22, 9136M89G27 | Replace with a serviceable HPCR 3-9 spool | (i) Within the next 500 CIS after the effective date of this AD, OR (ii) At the next ESV after the effective date of the AD, OR (iii) Before May 31, 2001. |
(b) Remove any HPCR 3-9 spool from service that equals or exceeds the reject criteria established by ASB 72-A1108, Revision 3, dated November 12, 1999; and replace it with a serviceable spool before further flight.
For HPCR stages 3-9 spools installed in CF6-80A series engines that have not been inspected in accordance with AD 99-24-15, do the following:
| Number of cycles-since-new (CSN) | Action | By the earliest of |
|---|---|---|
| (1) More than 7,000 CSN but fewer than 10,500 CSN, after the effective date of this AD | Eddy current and ultrasonic inspect bores for cracks in accordance with ASB 72-A0678, Revision 3, dated November 12, 1999 | (i) Within the next 1,000 CIS after the effective date of this AD, OR. (ii) At the next ESV after the effective date of the AD, OR. (iii) Before July 29, 2001. |
| (2) 10,500 or more CSN, after the effective date of this AD, on HPCR 3-9 spools P/N 9136M89G10, 9136M89G11 | Eddy current and ultrasonic inspect bores for cracks in accordance with ASB 72-A0678, Revision 3, dated November 12, 1999 | (i) Within the next 500 CIS after the effective date of this AD, OR. (ii) At the next ESV after the effective date of the AD, OR. (iii) Before May 31, 2001. |
| (3) 10,500 or more CSN, after the effective date of this AD, on HPCR 3-9 spools P/N 9136M89G20, 9136M89G21, 9136M89G22, 913M89G27 | Replace with a serviceable HPCR 3-9 spool | (i) Within the next 500 CIS after the effective date of this AD, OR. (ii) At the next ESV after the effective date of the AD, OR. (iii) Before May 31, 2001. |
(d) Remove any HPCR 3-9 spool from service that equals or exceeds the reject criteria established by ASB 72-A0678, Revision 3, dated November 12, 1999, and replace it with a serviceable spool before further flight.
For HPCR stages 3-9 spools installed in CF6-80C2 series engines that have not been inspected in accordance with both ASB 72-A0812, Revision 2, dated October 28, 1999; and ASB 72-A0848, Revision 5, dated August 3, 2000; or AD 99-24-15, do the following:
| Number of cycles-since-new (CSN) | Action | By the earliest of |
|---|---|---|
| (1) More than 7,000 CSN but fewer than 10,500 CSN, after the effective date of this AD | Eddy current and ultrasonic inspect the bores and webs for cracks in accordance with ASB 72-A0812, Revision 2, dated October 28, 1999; and ASB 72-A0848, Revision 5, dated August 3, 2000 | (i) Within the next 1,000 CIS after the effective date of this AD, OR (ii) At the next ESV after the effective date of the AD, OR (iii) Before July 29, 2001. |
| (2) 10,500 or more CSN, after the effective date of this AD | Replace with a serviceable HPCR 3-9 spool | (i) Within the next 500 CIS after the effective date of this AD, OR (ii) At the next ESV after the effective date of the AD, OR (iii) Before May 31, 2001. |
(f) Remove any HPCR 3-9 spool from service that equals or exceeds the reject criteria established by ASB 72-A0812, Revision 2, dated October 28, 1999; and ASB 72-A0848, Revision 5, dated August 3, 2000, and replace it with a serviceable spool before further flight.
For HPCR stages 3-9 spools installed in CF6-80E1 series engines that have not been inspected in accordance with both ASB 72-A0135, Revision 1, dated October 28, 1999; and ASB 72-A0126, Revision 3, dated August 3, 2000; or AD 99-24-15, do the following:
| Number of cycles-since-new (CSN) | Action | By the earliest of |
|---|---|---|
| (1) More than 7,000 CSN but fewer than 10,500 CSN, after the effective date of this AD | Eddy current and ultrasonic inspect the bores and webs for cracks in accordance with ASB 72-A0126, Revision 3, dated August 3, 2000, and ASB 72-A0135, Revision 1, dated October 28, 1999. | (i) Within the next 1,000 CIS after the effective date of this AD, OR (ii) At the next ESV after the effective date of the AD, OR (iii) Before July 29, 2001. |
| (2) 10,500 or more CSN after the effective date of this AD | Replace with a serviceable HPCR 3-9 spool | (i) Within the next 500 CIS after the effective date of this AD, OR (ii) At the next ESV after the effective date of the AD, OR (iii) Before May 31, 2001. |
(h) Remove any HPCR 3-9 spool from service before further flight that equals or exceeds the reject criteria established by ASB 72-A0135, revision 1, dated October 28, 1999; or ASB 72-A0126, revision 3, dated August 3, 2000, and replace it with a serviceable spool.
(i) For the purpose of this AD, an ESV is defined as any time an engine is introduced into a shop for the separation of a major engine flange.
