Document ID: chunk:federal_register_of_legislation:F2007L04270:body:0:p2
Version: federal_register_of_legislation:F2007L04270
Segment Type: other
Provision Reference: 
Character Range: 3193–5992

72-00-34, COMPRESSOR REAR FRAME ASSEMBLY - INSPECTION 001, Subtask 72-00-34-250-001.

        d. For CRF P/Ns 1520M26G03/G06/G08, clean and fluorescent penetrant inspect (FPI) the locations numbered 1 and 2.

        e. Information on these locations can be found in figure 801, sheet 1, of
        CF6-80E1 Engine Manual, Section 05-21-01.

        f. Information on cleaning and FPI can be found in CF6-80E1 Engine Manual, Section 72-00-34, COMPRESSOR REAR FRAME ASSEMBLY - INSPECTION 001, Subtask 72-00-34-230-051.

      Piece - Part Level Inspection of CRFs

      1. For CRF P/Ns 1520M26G03/G06/G08/G11/G12, at piece-part level:

        a. Clean and FPI the locations numbered 3 through 8.

        b. Information on these locations can be found in figure 801, sheets 2, 3, and 4, of CF6-80E1 Engine Manual, Section 05-21-01.

        c. Information on cleaning and FPI can be found in CF6-80E1 Engine Manual, Section 72-34-01, COMPRESSOR REAR FRAME - INSPECTION 001, Subtask 72-34-01-200-003.

        d. For CRF P/Ns 1520M26G03/G06/G08, clean and FPI the locations numbered 1 and 2.

        e. Information on these locations can be found in figure 801, sheet 1, of
        CF6-0E1 Engine Manual, Section 05-21-01.

        f. Information on cleaning and FPI can be found in CF6-80E1 Engine Manual, Section 72-34-01, COMPRESSOR REAR FRAME - INSPECTION 001, Subtask 72-34-01-200-003.

                Determining CSN of the Compressor Rear Frame

                  a. Air carriers and operators must use engine operating records to determine the CSN of the compressor rear frame.  If the number of cycles accumulated since new cannot be established, inspect the CRF within 300 cycles-in-service after the effective date of this AD.

                  b. For compressor rear frames that have operated in multiple engine models or thrust ratings, information on correct cycle counting can be found in Method 1 or Method 2 of CF6-80E1 Engine Manual No. GEK 99376, Section
                  05-11-00, LIFE LIMITS OF ENGINE ROTATING PARTS.

                 Definition

             For the purposes of this AD, piece-part level means that the CRF is removed and disassembled using the disassembly instructions in GE's engine manual.

             Note 2:  FAA AD 2007-18-10 Amdt 39- 15190 dated 29 August 2007 refers.
Compliance:  Within the next 30 days after the effective date of this AD, unless previously accomplished.
             This Airworthiness Directive becomes effective on 22 November 2007.
Background:  This AD requires enhanced inspections of the CF6-80E1 series turbofan engine CRFs, for cracks to prevent rupture of the CRF, which could result in an under-cowl engine fire.

Charles Lenarcic
Delegate of the Civil Aviation Safety Authority

24 September 2007