Document ID: chunk:federal_register_of_legislation:F2010L02202:body:0:p2
Version: federal_register_of_legislation:F2010L02202
Segment Type: other
Provision Reference: 
Character Range: 3319–6326

stage rubstrip shows wear through to the parent material of the stator, with the circumferential length of the wear being less than 2.0".   Reinspect every 300 CIS.
    (5)  Both 14th and 15th stage rubstrips show no wear through to the parent material of the stator.                                                    Reinspect every 600 CIS.

      3. For aeroplanes with two affected engines installed, perform the actions as specified in following Table 3:

   Table 3. - Borescope Inspection Results and
   Required Actions for Two Affected Engines
   First engine borescope results:                             Second engine borescope schedule:                           Second engine borescope results:                       Action:
    (1)  Wear as specified in Table 2, Steps (1) through (4).   Within 10 CIS since borescope inspection of first engine.   Wear as specified in Table 2, Steps (1) through (4).   Remove either the first or second engine from service within 25 CIS since borescope inspection of the second engine and replace with a serviceable engine. Remove or re-inspect in accordance with Table 2 for remaining engine and if still applicable perform actions as specified in Requirement 3 of this AD.

    (2)  Wear as specified in Table 2, Steps (1) through (4).   Within 10 CIS since borescope inspection of first engine.   Wear as specified in Table 2, Step (5).   For both engines, remove or re-inspect in accordance with Table 2 and, if still applicable, perform actions as specified in Requirement 3 of this AD.
    (3)  Wear as specified in Table 2, Step (5).                Inspect as specified in Table 1.                            Wear as specified in Table 2.             For both engines, remove or inspect in accordance with Table 2 and, if still applicable, perform actions as specified in Requirement 3 of this AD.

   Definition of Serviceable Engine.

   For the purposes of this AD, a serviceable engine is:

        a. An engine that incorporates an HPC with zero CSN; or

        b. An engine covered by the Terminating Action detailed in this AD; or

        c. An engine inspected as specified in Requirements 1 through 3 of this AD, and is following the 600 CIS re-inspection interval as specified in Table 2 of this AD.

   Engines borescope-inspected before the effective date of this AD in accordance with PW ASB PW4G-100-A72-170, Revision 1, or Revision 2, must follow Requirements 1 through 3 of this AD, after the effective date of this AD.

   Later revisions of the above ASB, approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 2003-09-02, are considered acceptable for compliance with the equivalent Requirements of this AD.

   Terminating Action.

   Replacement of HPC inner rear case assembly with an HPC inner rear case assembly containing a Haynes 242 rear hook, including assemblies modified or replaced by PW SB No. PW4G-100-72-159, PW SB No. PW4G-100-72-187, or