<table cellspacing="0" cellpadding="0" style="width:510.3pt; margin-top:0pt; margin-bottom:0pt; border-collapse:collapse"><tbody><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Applicability:</span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-bottom:12pt"><span>Pratt and Whitney (PW) models PW4164, PW4168, and PW4168A turbofan engines, serial numbers P733301 through P733500, that have HPC inner case assembly part nu</span><span>mber (P/N) 53H272-01 installed.</span></p><p class="Note" style="margin-top:12pt"><span>Note 1: </span><span></span><span>These engines are installed on, but not limited to Airbus Industrie A330 aeroplanes.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Requirement:</span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-bottom:12pt"><span>Unless previously accomplished, to prevent engine power loss during takeoff due to high pressure compressor (HPC</span><span>) surge, perform the following:</span></p><p style="margin-top:12pt; margin-left:21.3pt; margin-bottom:12pt; text-indent:-21.3pt"><span>1.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Borescope-inspect in accordance with paragraphs 1.A. through 1.I of the Accomplishment Instructions, Borescope Inspection of Pratt & Whitney (PW) Alert Service Bulletin (ASB) PW4G-100-A72-170, Revision 3, dated</span><br><span>31 </span><span>January 2003, using s</span><span>chedules in Table 1 of this AD:</span></p><p style="margin-top:12pt; text-align:center"><span style="font-weight:bold">Table 1.</span><span style="font-weight:bold"> </span><span style="font-weight:bold">-</span><span style="font-weight:bold"> </span><span style="font-weight:bold">Installed-Engine Initial Borescope Inspection Schedule</span></p><table cellspacing="0" cellpadding="0" style="width:100%; margin-top:0pt; margin-bottom:0pt; border:0.75pt solid #000000; border-collapse:collapse"><tbody><tr><td style="width:50%; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="text-align:center"><span>Accumulated engine cycles on</span><br><span>the effective date of this AD:</span></p></td><td style="width:50%; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="text-align:center"><span>Initial borescope-inspect 14</span><span style="font-size:8pt; vertical-align:super">th</span><br><span>and 15th stage rubstrips:</span></p></td></tr><tr><td style="width:50%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(1) </span><span></span><span>Fewer than 900 cycles-since-new (CSN) or cycles-since-refurbishment (CSR) of the HPC inner rear case assembly.</span></p></td><td style="width:50%; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:4.65pt"><span>Before accumulating 1,500 CSN or CSR, whichever occurs later.</span></p></td></tr><tr><td style="width:50%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(2) </span><span></span><span>900 or more CSN or CSR</span></p></td><td style="width:50%; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:4.65pt"><span>Within 600 cycles-in-service (CIS) after the effective date of this AD.</span></p></td></tr></tbody></table><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>2.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Perform the applicable action as spec</span><span>ified in the following Table 2:</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="text-align:center"><span style="font-weight:bold">Table 2. - Borescope Inspection Results and Required Action</span></p><table cellspacing="0" cellpadding="0" style="width:100%; margin-top:0pt; margin-bottom:0pt; border:0.75pt solid #000000; border-collapse:collapse"><tbody><tr><td style="width:62%; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="text-align:center"><span>Results observed at last borescope inspection:</span></p></td><td style="width:38%; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="text-align:center"><span>Action:</span></p></td></tr><tr><td style="width:62%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(1)</span><span> </span><span>14th stage rubstrip shows wear through to the parent material of the stator, with the circumferential length of the wear being 1.0" or more.</span></p></td><td style="width:38%; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:4.6pt"><span>Remove engine from service within 250 CIS.</span></p></td></tr></tbody></table><p></p></td></tr></tbody></table>
Division Pratt and Whitney Turbine Engines - PW40 - AD/PW4000/15 - 14th and 15th Stage Rubstrips - Pratt and Whitney Turbine Engines - PW4000 Series | Zoe
<table cellspacing="0" cellpadding="0" style="width:510.3pt; margin-top:0pt; margin-bottom:0pt; border-collapse:collapse"><tbody><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><table cellspacing="0" cellpadding="0" style="width:100%; margin-top:0pt; margin-bottom:0pt; border:0.75pt solid #000000; border-collapse:collapse"><tbody><tr><td style="width:62%; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(2)</span><span> </span><span>15th stage rubstrip shows wear through to the parent material of the stator, with the circumferential length of the wear being 2.0" or more.</span></p></td><td style="width:38%; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:4.6pt"><span>Remove engine from service within 250 CIS.</span></p></td></tr><tr><td style="width:62%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(3)</span><span> </span><span>14th stage rubstrip shows wear through to the parent material of the stator, with the circumferential length of the wear being less than 1.0".</span></p></td><td style="width:38%; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:4.6pt"><span>Reinspect every 300 CIS.</span></p></td></tr><tr><td style="width:62%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(4)</span><span> </span><span>15th stage rubstrip shows wear through to the parent material of the stator, with the circumferential length of the wear being less than 2.0".</span></p></td><td style="width:38%; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:4.6pt"><span>Reinspect every 300 CIS.</span></p></td></tr><tr><td style="width:62%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(5)</span><span> </span><span>Both 14th and 15th stage rubstrips show no wear through to the parent material of the stator.</span></p></td><td style="width:38%; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:4.6pt"><span>Reinspect every 600 CIS.</span></p></td></tr></tbody></table><p style="margin-left:21.3pt; margin-bottom:12pt; text-indent:-21.3pt"><span>3.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>For aeroplanes with two affected engines installed, perform the actions as </span><span>specified in following Table 3:</span></p><p style="margin-top:12pt; text-align:center"><span style="font-weight:bold">Table 3. - Borescope Inspection Results and</span><br><span style="font-weight:bold">Required Actions for Two Affected Engines</span></p><table cellspacing="0" cellpadding="0" style="width:100%; margin-top:0pt; margin-bottom:0pt; border:0.75pt solid #000000; border-collapse:collapse"><tbody><tr><td style="width:23.9%; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="text-align:center"><span>First engine borescope results:</span></p></td><td style="width:23.98%; border-right:0.75pt solid #000000; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="text-align:center"><span>Second engine borescope schedule:</span></p></td><td style="width:25.7%; border-right:0.75pt solid #000000; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="text-align:center"><span>Second engine borescope results:</span></p></td><td style="width:26.42%; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="text-align:center"><span>Action:</span></p></td></tr><tr><td style="width:23.9%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(1) </span><span></span><span>Wear as specified in Table 2, Steps (1) through (4).</span></p></td><td style="width:23.98%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; border-left:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:8.85pt"><span>Within 10 CIS since borescope inspection of first engine.</span></p></td><td style="width:25.7%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; border-left:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:4.65pt"><span>Wear as specified in Table 2, Steps (1) through (4).</span></p></td><td style="width:26.42%; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:7.5pt"><span>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.</span></p></td></tr></tbody></table><p style="text-align:center"></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><table cellspacing="0" cellpadding="0" style="width:100%; margin-top:0pt; margin-bottom:0pt; border:0.75pt solid #000000; border-collapse:collapse"><tbody><tr><td style="width:23.9%; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(2)</span><span> </span><span>Wear as specified in Table 2, Steps (1) through (4).</span></p></td><td style="width:23.98%; border-right:0.75pt solid #000000; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:6.3pt"><span>Within 10 CIS since borescope inspection of first engine.</span></p></td><td style="width:25.7%; border-right:0.75pt solid #000000; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:6.3pt"><span>Wear as specified in Table 2, Step (5).</span></p></td><td style="width:26.42%; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:6.25pt"><span>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.</span></p></td></tr><tr><td style="width:23.9%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:5.95pt"><span>(3)</span><span> </span><span>Wear as specified in Table 2, Step (5).</span></p></td><td style="width:23.98%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; border-left:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:6.3pt"><span>Inspect as specified in Table 1.</span></p></td><td style="width:25.7%; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; border-left:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:6.3pt"><span>Wear as specified in Table 2.</span></p></td><td style="width:26.42%; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; padding:0.38pt; vertical-align:top"><p style="margin-left:6.25pt"><span>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.</span></p></td></tr></tbody></table><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">Definition of Serviceable Engine.</span></p><p style="margin-top:12pt; margin-bottom:12pt"><span>For the purposes of this AD, a serviceable engine is:</span></p><p style="margin-top:12pt; margin-left:42.55pt; margin-bottom:12pt; text-indent:-21.25pt"><span>a.</span><span style="width:12.92pt; text-indent:0pt; display:inline-block"> </span><span>An engine that incorporates an HPC with zero CSN; or</span></p><p style="margin-top:12pt; margin-left:42.55pt; margin-bottom:12pt; text-indent:-21.25pt"><span>b.</span><span style="width:12.25pt; text-indent:0pt; display:inline-block"> </span><span>An engine covered by the Terminating Action detailed in this AD; or</span></p><p style="margin-top:12pt; margin-left:42.55pt; margin-bottom:12pt; text-indent:-21.25pt"><span>c.</span><span style="width:12.92pt; text-indent:0pt; display:inline-block"> </span><span>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.</span></p><p style="margin-top:12pt; margin-bottom:12pt"><span>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.</span></p><p style="margin-top:12pt; margin-bottom:12pt"><span>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.</span></p><p style="margin-top:12pt; margin-bottom:12pt"><span>Terminating Action.</span></p><p style="margin-top:12pt"><span>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 Chromalloy Repair Procedure 00-CFL-039-0, constitutes terminating action for the repetitive engine borescope inspections of this AD.</span></p></td></tr></tbody></table>
Note 2: FAA AD 2003-09-02 Amdt 39-13131 date 21 April 2003 refers.
Compliance:
For Requirement 1 - As detailed in Table 1 of this AD.For Requirement 2 - As detailed in Table 2 of this AD.For Requirement 3 - As detailed in Table 3 of this AD.
This Airworthiness Directive becomes effective on 14 August 2010.
Background:
This AD requires operators to initially and repetitively borescope-inspect 14th and 15th stage rubstrips located on the 13th and 14th stage stator set for wear. This AD is prompted by reports of high pressure compressor (HPC) surges during the takeoff phase of flight that have been attributed to increased stage 14 and stage 15 HPC blade tip clearances caused by excessive wear on the HPC inner rear case rear hook. The actions specified by this AD are intended to prevent engine power loss during takeoff due to HPC surge.From a review of State of Design ADs, CASA has determined that this AD may be applicable to Australian aircraft.
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David Punshon
Delegate of the Civil Aviation Safety Authority