Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 Turbofan Engines, 61395-61399 [E6-17327]

Download as PDF Federal Register / Vol. 71, No. 201 / Wednesday, October 18, 2006 / Rules and Regulations 61395 TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Service Bulletin Revision level Boeing Service Bulletin 747–21A2414 ................................................................................................. Boeing Service Bulletin 747–21–2405 ................................................................................................. Boeing Service Bulletin 777–21A0048 ................................................................................................. Boeing Service Bulletin 777–21–0035 ................................................................................................. Boeing Service Bulletin 777–21–0087 ................................................................................................. Hamilton Sundstrand Service Bulletin 816086–21–01 ........................................................................ Hamilton Sundstrand Service Bulletin 821486–21–01 ........................................................................ 3 ....................... 4 ....................... 3 ....................... 1 ....................... Original ............. Original ............. Original ............. Effective Date (m) This amendment becomes effective on November 22, 2006. Issued in Renton, Washington, on October 6, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–17187 Filed 10–17–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25809; Directorate Identifier 2001–NE–30–AD; Amendment 39– 14791; AD 2006–17–07R1] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, –17AR, –209, –217, –217A, –217C, and –219 Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; correction. hsrobinson on PROD1PC76 with RULES AGENCY: SUMMARY: The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, –17AR, –209, –217, –217A, –217C, and –219 turbofan engines. That AD currently requires either replacing high pressure compressor (HPC) front hubs and HPC disks that have operated at any time with PWA 110–21 coating and that operated in certain engine models, or, visually inspecting and fluorescent penetrant inspecting (FMPI) for cracking of those parts and re-plating them if they pass inspection. This AD requires the same actions, but makes necessary corrections to inadvertent reference errors and omissions found in AD 2006– VerDate Aug<31>2005 15:59 Oct 17, 2006 Jkt 211001 17–07, and relaxes some of the compliance times in Table 5. This AD results from our finding reference errors and omissions in AD 2006–17–07, from determining that the AD as drafted imposed an unnecessary burden on operators if they have to immediately remove engines, and from requests to clarify compliance paragraphs. We are issuing this AD to prevent a rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and damage to the airplane. DATES: This AD becomes effective November 2, 2006. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of October 4, 2006 (71 FR 51459, August 30, 2006). ADDRESSES: You can get the service information identified in this AD from Pratt & Whitney, 400 Main St., East Hartford, CT 06108, telephone (860) 565–7700; fax (860) 565–1605. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7189; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: On August 21, 2006, the FAA issued AD 2006–17– 07, Amendment 39–14728 (71 FR 51459, August 30, 2006). That AD requires either replacing HPC front hubs and HPC disks that have operated at any time with PWA 110–21 coating and that operated in certain engine models, or, visually inspecting and FMPI for cracking of those parts and re-plating them if they pass inspection. That AD was the result of an investigation by PW, which concluded that any HPC front hub or HPC disk coated with PWA PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 Date May 12, 2006. July 29, 1999. May 12, 2006. October 19, 2000. June 17, 2004. March 15, 2000. March 15, 2000. 110–21 that ever operated on JT8D–15, –15A, –17, –17A, –17R, –17AR, –209, –217, –217A, –217C, and –219 turbofan engines, could crack before reaching their published life limit. That condition, if not corrected, could result in an uncontained engine failure and damage to the airplane. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Actions Since AD 2006–17–07 Was Issued After we issued AD 2006–17–07, we found reference errors and omissions. These errors and omissions could affect your ability to comply with the AD. The following errors and omissions were discovered. We made the associated corrections: • In the third column of Table 1 of this AD, we omitted ‘‘–17A’’ in two places. We added the missing ‘‘–17A’’ from AD 2006–17–07 in both places. • The third column of Table 4 and Table 5 reads ‘‘Paragraph (h)(3) of this AD’’. Paragraph (h)(3) does not exist. We corrected it to read ‘‘Paragraph (j) of this AD.’’ We also determined that based on the compliance times in Table 5 of AD 2006–17–07, some operators might have to immediately remove their engines from service. If so, we concluded that those immediate removals might impose an unanticipated undue burden. Table 5 of AD 2006–17–07, appears below. E:\FR\FM\18OCR1.SGM 18OCR1 61396 Federal Register / Vol. 71, No. 201 / Wednesday, October 18, 2006 / Rules and Regulations TABLE 5 OF AD 2006–17–07—HPC FRONT HUB INSPECTION SCHEDULE—HUBS COATED WITH NICKEL-CADMIUM HPC front hub CSN on the effective date of this AD Inspect before additional CIS or CSN, whichever occurs first Also inspect 7th stage HPC disks and 9th stage-through-12th stage HPC disks using: (i) 19,000 or more .............................................. (ii) 17,000 or more, but fewer than 19,000 ....... (iii) 9,000 or more, but fewer than 17,000, that have not been inspected. (iv) 9,000 or more, but fewer than 17,000, that were inspected before accumulating 9,000 CSN. 500 CIS or 20,000 CSN ................................... 1,000 CIS or 19,500 CSN ................................ 18,000 CSN ...................................................... Paragraph (h)(3) of this AD. Paragraph (h)(3) of this AD. Paragraph (h)(3) of this AD. 15,500 CSN ...................................................... Paragraph (h)(3) of this AD. Therefore, we changed Table 5 to reflect relaxed compliance requirements in item (iii), and we changed the compliance requirements in item (iv). With the addition of the ‘‘–17A’’ noted previously, and the changed compliance requirements that relax compliance time, Table 5 now reads as follows: (CHANGED) TABLE 5.—HPC FRONT HUB INSPECTION SCHEDULE—HUBS COATED WITH NICKEL-CADMIUM HPC front hub CSN on the effective date of this AD Inspect before additional CIS or CSN, whichever occurs first (i) 19,000 or more .............................................. (ii) 17,000 or more, but fewer than 19,000 ....... (iii) 9,000 or more, but fewer than 17,000 ......... (iv) Fewer than 9,000 that are accessible ......... 500 CIS or 20,000 CSN ................................... 1,000 CIS or 19,500 CSN ................................ 18,000 CSN ...................................................... If the parts have been inspected and are acceptable, parts may be reinstalled. Inspect again using the criteria in (iii) of this table. Paragraph Paragraph Paragraph Paragraph As part of relaxing the requirements, we also clarified that paragraphs (f)(3) and (j) pertain to 7th stage HPC disks and 9th stage-through-12th stage HPC disks coated with PWA 110–21. Finally, since AD 2006–17–07 was issued, we received multiple instances of operators requesting clarification of compliance paragraph (e) in AD 2006– 17–07. Based on the frequency of requests, we decided to clarify the paragraph. AD 2006–17–07 paragraph (e) originally read as follows: –217, –217A, –217C, and –219 turbofan engines of the same type design. We are issuing this AD to prevent a rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and damage to the airplane. This AD requires either replacing HPC front hubs and HPC disks that have operated at any time with PWA 110–21 coating and that operated in certain engine models, or, visually inspecting and FMPI for cracking of those parts and replating them if they pass inspection. ‘‘(e) You must accomplish the actions required by this AD within the compliance times specified, unless the actions have already been done. Any engine with an HPC front hub that has been inspected using AD 2002–23–14, AD 2003–12–07, or AD 2003– 16–05, is considered in compliance with this AD.’’ FAA’s Determination of the Effective Date Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. We rewrote paragraph (e) to now read as follows: hsrobinson on PROD1PC76 with RULES ‘‘(e) You must accomplish the actions required by this AD within the compliance times specified, unless the actions have already been done. Any engine with an HPC front hub that has been inspected for fretting wear using AD 2002–23–14, AD 2003–12–07, or AD 2003–16–05, counts as an inspection toward compliance with this AD.’’ FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other Pratt & Whitney JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, –17AR, –209, VerDate Aug<31>2005 15:59 Oct 17, 2006 Jkt 211001 Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are unnecessary, and that good cause exists for making this amendment effective in less than 30 days. Docket Number Change We are transferring the docket for this AD to the Docket Management System as part of our on-going docket management consolidation efforts. The new Docket No. is FAA–2006–25809. The old Docket No. became the Directorate Identifier, which is 2001– NE–30–AD. This AD might get logged into the DMS docket, ahead of the previously collected documents from the old docket file, as we are in the process of sending those items to the DMS. PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 Also inspect 7th stage HPC disks and 9th stage-through-12th stage HPC disks using: (j) (j) (j) (j) of of of of this this this this AD. AD. AD. AD. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; E:\FR\FM\18OCR1.SGM 18OCR1 Federal Register / Vol. 71, No. 201 / Wednesday, October 18, 2006 / Rules and Regulations (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. Adoption of the Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: Amendment 39–14791, to read as follows: 2006–17–07R1 Pratt & Whitney: Amendment 39–14791. Docket No. FAA–2006–25809; Directorate Identifier 2001–NE–30–AD. PART 39—AIRWORTHINESS DIRECTIVES Effective Date (a) This airworthiness directive (AD) becomes effective November 2, 2006. 1. The authority citation for part 39 continues to read as follows: Affected ADs (b) This AD revises AD 2006–17–07. I I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 List of Subjects in 14 CFR Part 39 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–14728 (71 FR 51459, August 30, 2006), and by adding a new airworthiness directive, I Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 61397 Applicability (c) This AD applies to the following Pratt & Whitney (PW) JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, –17AR, –209, –217, –217A, –217C, and –219 turbofan engines, with 8th stage high pressure compressor (HPC) front hubs: TABLE 1.—AD APPLICABILITY If the HPC front hub is coated with: And if the stage 8–9 spacer is coated with: And the HPC front hub: (1) PWA 110–21 at any time Any .................................... Operated in a JT8D–15, –15A, –17, –17A, –17R, or –17AR engine. (2) PWA 110–21 at any time Any .................................... Operated in a JT8D–209, –217, –217A, –217C, or –219 engine. (3) Nickel-Cadmium ............. PWA 110–21 at any time .. Operated in a JT8D–209, –217, –217A, –217C, or –219 engine. (4) Nickel-Cadmium ............. PWA 110–21 at any time .. (5) PWA 110–21 at any time Any .................................... (6) Nickel-Cadmium ............. Any type but PWA 110–21 Operated in a JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, or –17AR engine. Operated in a JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, or –11, but never operated in a JT8D–15, –15A, –17, –17A, –17R, –17AR, –209, –217, –217A, –217C, or –219 engine. Any ................................................................................ These engines are installed on, but not limited to, Boeing DC–9, MD–80 series, 727 series, and 737 series airplanes. Unsafe Condition (d) This AD results from inadvertent reference errors and omissions found in AD 2006–17–07, which could affect ability to comply with that AD. We are issuing this AD to prevent a rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and damage to the airplane. Compliance (e) You must accomplish the actions required by this AD within the compliance times specified, unless the actions have already been done. Any engine with an HPC front hub that has been inspected for fretting wear using AD 2002–23–14, AD 2003–12–07, or AD 2003–16–05, counts as an inspection toward compliance with this AD. JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, and –17AR Turbofan Engines—Inspect or Replace HPC Front Hubs, HPC Disks, and Stage 8–9 Spacers (f) For applicable JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, and –17AR turbofan engines Then this AD is: Applicable. See paragraph (f) and Table 2 of this AD. Applicable. See paragraph (h) and Table 4 of this AD. Applicable. See paragraph (i) and Table 5 of this AD. Not applicable. Not applicable. Not applicable. specified in Table 1 of this AD, do the following: (1) Using the inspection schedule in Table 2 of this AD, strip the protective coating, visually inspect for fretting wear, fluorescent magnetic particle inspect (FMPI) for cracks, reidentify, replate HPC front hubs and stage 8–9 spacers, and replace if necessary. (2) Use paragraphs 1. through 3.B.(7)(b) under ‘‘For Rear Compressor Front Hubs that Have Operated With PWA 110–21 coating AT ANY TIME During Their Service Life in JT8D–15, –15A, –17, –17A, –17R, –17AR Engine Models.’’ of PW Alert Service Bulletin (ASB) JT8D A6468, dated December 23, 2004. TABLE 2.—HPC FRONT HUB INSPECTION SCHEDULE hsrobinson on PROD1PC76 with RULES HPC front hub cycles-since-new (CSN) on the effective date of this AD Inspect before additional cycles-in-service (CIS) or CSN, whichever occurs first (i) 19,000 or more .............................................. (ii) 15,500 or more, but fewer than 19,000 ....... (iii) 5,000 or more, but fewer than 15,500 ......... 500 CIS or 20,000 CSN ................................... 1,000 CIS or 19,500 CSN ................................ 16,500 CSN ...................................................... VerDate Aug<31>2005 15:59 Oct 17, 2006 Jkt 211001 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 Also inspect 7th stage HPC disks and 9th stage-through-12th stage HPC disks using: Paragraph (f)(3) of this AD. Paragraph (f)(3) of this AD. Paragraph (f)(3) of this AD. E:\FR\FM\18OCR1.SGM 18OCR1 61398 Federal Register / Vol. 71, No. 201 / Wednesday, October 18, 2006 / Rules and Regulations TABLE 2.—HPC FRONT HUB INSPECTION SCHEDULE—Continued HPC front hub cycles-since-new (CSN) on the effective date of this AD Inspect before additional cycles-in-service (CIS) or CSN, whichever occurs first Also inspect 7th stage HPC disks and 9th stage-through-12th stage HPC disks using: (iv) Fewer than 5,000 that are accessible ......... If the parts have been inspected and are acceptable, parts may be reinstalled. Inspect again using the criteria in (iii) of this Table. Paragraph (f)(3) of this AD. (3) When the HPC front hub is inspected, visually inspect for fretting wear and FMPI for cracks on 7th stage HPC disks and 9th stage-through-12th stage HPC disks coated with PWA 110–21. Inspection information can be found in the applicable sections of JT8D Engine Manual Part Number (P/N) 481672, listed in the following Table 3: TABLE 3.—SEVENTH STAGE HPC DISKS AND 9TH STAGE-THROUGH-12TH STAGE HPC DISKS INSPECTION INFORMATION Chapter/ section Stage 7 .................................................... 9 .................................................... 10 .................................................. 11 .................................................. 12 .................................................. Visual inspection 72–36–41 72–36–43 72–36–44 72–36–45 72–36–46 JT8D–15, –15A, –17, –17A, –17R, and –17AR Turbofan Engines—Cycle Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium Plating and PWA 110–21 Coating (g) For JT8D–15, –15A, –17, –17A, –17R, and –17AR turbofan engines with front hubs that entered service with Nickel-Cadmium plating, but have also operated during the life of the hub with PWA 110–21 coating: Inspection–01 Inspection–01 Inspection–01 Inspection–01 Inspection–01 Fretting inspection .............................. .............................. .............................. .............................. .............................. Inspection–04 Inspection–04 Inspection–04 Inspection–04 Inspection–04 (1) You are allowed to make a cycle adjustment if the hub was never operated with a PWA 110–21-coated stage 8–9 spacer. (2) Use the information under ‘‘Compliance’’ of PW ASB JT8D A6468, dated December 23, 2004, to determine the adjustment. JT8D–209, –217, –217A, –217C, and –219 Turbofan Engines—Inspect or Replace HPC Front Hubs and Stage 8–9 Spacers (h) For applicable JT8D–209, –217, –217A, –217C, and –219 turbofan engines specified FMPI .............................. .............................. .............................. .............................. .............................. Inspection–03. Inspection–03. Inspection–03. Inspection–03. Inspection–03. in Table 1, Row (2) of this AD, do the following: (1) Using the inspection schedule in Table 4 of this AD, strip the protective coating, visually inspect for fretting wear, FMPI for cracking, reidentify, replate HPC front hubs and the stage 8–9 spacers, and replace if necessary. (2) Use paragraphs 1. through 1.A. and paragraphs 2. through 2.C.(2)(g)2 of Accomplishment Instructions of PW ASB JT8D A6430, Revision 2, dated December 23, 2004. TABLE 4.—HPC FRONT HUB INSPECTION SCHEDULE—HUBS COATED WITH PWA 110–21 HPC front hub CSN on the effective date of this AD Inspect before additional CIS or CSN, whichever occurs first Also inspect 7th stage HPC disks and 9th stage-through-12th stage HPC disks using: (i) 19,000 or more .............................................. (ii) 15,500 or more, but fewer than 19,000 ....... (iii) 5,000 or more, but fewer than 15,500 ......... (iv) Fewer than 5,000 that are accessible. ........ 500 CIS or 20,000 CSN ................................... 1,000 CIS or 19,500 CSN ................................ 16,500 CSN ...................................................... If the parts have been inspected and are acceptable, parts may be reinstalled. Inspect again using the criteria in (iii) of this Table. Paragraph Paragraph Paragraph Paragraph (i) For applicable JT8D–209, –217, –217A, –217C, and –219 turbofan engines specified in Table 1, Row (3) of this AD, do the following: (1) Using the inspection schedule in Table 5 of this AD, strip the protective coating, visually inspect for fretting wear, FMPI for cracking, reidentify, replate HPC front hubs and the stage 8–9 spacers, and replace if necessary. (2) Use paragraphs 1., 1.C, and 4. through 4.B.(2)(g)2 of Accomplishment Instructions of PW ASB JT8D A6430, Revision 2, dated December 23, 2004, for all applicable hubs with any type of coating. (j) (j) (j) (j) of of of of this this this this AD. AD. AD. AD. TABLE 5.—HPC FRONT HUB INSPECTION SCHEDULE—HUBS COATED WITH NICKEL-CADMIUM hsrobinson on PROD1PC76 with RULES HPC front hub CSN on the effective date of this AD Inspect before additional CIS or CSN, whichever occurs first (i) 19,000 or more .............................................. (ii) 17,000 or more, but fewer than 19,000 ....... (iii) 9,000 or more, but fewer than 17,000 ......... (iv) Fewer than 9,000 that are accessible ......... 500 CIS or 20,000 CSN ................................... 1,000 CIS or 19,500 CSN ................................ 18,000 CSN ...................................................... If the parts have been inspected and are acceptable, parts may be reinstalled. Inspect again using the criteria in (iii) of this Table. VerDate Aug<31>2005 15:59 Oct 17, 2006 Jkt 211001 PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 Also inspect 7th stage HPC disks and 9th stage-through-12th stage HPC disks using: Paragraph Paragraph Paragraph Paragraph E:\FR\FM\18OCR1.SGM (j) (j) (j) (j) of of of of 18OCR1 this this this this AD. AD. AD. AD. 61399 Federal Register / Vol. 71, No. 201 / Wednesday, October 18, 2006 / Rules and Regulations (j) When the HPC front hub is inspected, visually inspect for fretting wear and FMPI for cracks on 7th stage HPC disks and 9th stage-through-12th stage HPC disks coated with PWA 110–21. Inspection information can be found in the applicable sections of JT8D–200 Engine Manual P/N 773128, listed in Table 3 of this AD. (1) Install a Nickel-Cadmium plated HPC front hub that has never operated with PWA 110–21 coating in the interface between the HPC front hub and the stage 8–9 spacer. (2) Install a Nickel-Cadmium plated or Electroless Nickel-plated stage 8–9 spacer. (3) Install HPC disks that have never operated with PWA 110–21 coating. JT8D–209, –217, –217A, –217C, and –219 Turbofan Engines—Cycle Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium Plating and PWA 110–21 Coating (k) For JT8D–209, –217, –217A, –217C, and –219 turbofan engines with HPC front hubs that entered service with Nickel-Cadmium plating, but have also operated during the life of the hub with PWA 110–21 coating: (1) You are allowed to make a cycle adjustment. (2) Use the information under ‘‘CONDITION A’’ of PW ASB JT8D A6430, Revision 2, dated December 23, 2004, to determine the adjustment. Prohibition Against Recoating the HPC Front Hub, Stage 7 HPC Disk, and Stage 8–9 Spacer With PWA 110–21—All Engines (m) Do not recoat the HPC front hub with PWA 110–21 (Repair-23 of Chapter/Section 72–36–42 of JT8D–200 Engine Manual, P/N 773128, and Repair-27 and Repair-28 of Chapter/Section 72–36–42 of JT8D Engine Manual, P/N 481672). (n) Do not recoat the 7th stage disk with PWA 110–21 (Repair-15 of Chapter/Section 72–36–41 of JT8D–200 Engine Manual, P/N 773128, and Repair-15 of Chapter/Section 72–36–41 of JT8D Engine Manual, P/N 481672). (o) Do not recoat the stage 8–9 spacer with PWA 110–21 (Repair-03, Task 72–36–12–30– 003–002, of Chapter/Section 72–36–12 of JT8D–200 Engine Manual, P/N 773128, and Repair-01, Task 72–36–12–30–001–002, of Chapter/Section 72–36–12 of JT8D Engine Manual, P/N 481672). Replacement of HPC Front Hubs and Stage 8–9 Spacers That Have Operated With PWA 110–21 Coating, As Optional Action—All Engines (l) For all applicable engines, as an optional action for the visual inspections in this AD, replace HPC front hubs and stage 8– 9 spacers that have operated with PWA 110– 21 coating in the interface between the hub and the stage 8–9 spacer and HPC disks currently coated with PWA 110–21, as follows: Prohibition Against Reinstalling HPC Front Hubs and Stage 8–9 Spacers Coated With PWA 110–21 (p) After the effective date of this AD, do not reinstall HPC front hubs and stage 8–9 spacers coated with PWA 110–21. Definition (q) For the purpose of this AD, ‘‘accessible’’ is defined as when the HPC front hub is removed from the engine and the hub is debladed. Alternative Methods of Compliance (r) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (s) None. Material Incorporated by Reference (t) You must use the service information specified in Table 6 of this AD to perform the actions required by this AD. The Director of the Federal Register previously approved the incorporation by reference of these alert service bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of October 4, 2006 (71 FR 51459, August 30, 2006). Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108, telephone (860) 565–7700; fax (860) 565–1605 for a copy of this service information. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html. TABLE 6.—INCORPORATION BY REFERENCE Pratt & Whitney Alert Service Bulletin No. Page Revision JT8D A6430, Total Pages: 35 ................................................................................... JT8D A6468, Total Pages: 20 ................................................................................... ALL ................... ALL ................... 2 ....................... Original ............. Issued in Burlington, Massachusetts, on October 11, 2006. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–17327 Filed 10–17–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Bureau of Customs and Border Protection DEPARTMENT OF THE TREASURY 19 CFR Parts 12 and 163 [USCBP–2006–0108; CBP Dec. 06–25] RIN 1505–AB73 Entry of Softwood Lumber Products From Canada hsrobinson on PROD1PC76 with RULES AGENCIES: Customs and Border Protection, Department of Homeland Security; Department of the Treasury. ACTION: Interim rule. SUMMARY: This document sets forth interim amendments to title 19 of the Code of Federal Regulations (CFR) establishing special entry requirements applicable to shipments of softwood lumber products from Canada. The VerDate Aug<31>2005 15:59 Oct 17, 2006 Jkt 211001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 Date December 23, 2004. December 23, 2004. interim amendments involve the collection of additional entry summary information for purposes of monitoring and enforcing the Softwood Lumber Agreement between the Governments of Canada and the United States, entered into on September 12, 2006. DATES: Interim rule effective October 16, 2006. Comments must be received on or before December 18, 2006. ADDRESSES: You may submit comments, identified by docket number, by one of the following methods: • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments via docket number USCBP–2006–0108. • Mail: Trade and Commercial Regulations Branch, Office of Regulations and Rulings, Bureau of Customs and Border Protection, 1300 Pennsylvania Avenue, NW. (Mint Annex), Washington, DC 20229. Instructions: All submissions received must include the agency name and E:\FR\FM\18OCR1.SGM 18OCR1

Agencies

[Federal Register Volume 71, Number 201 (Wednesday, October 18, 2006)]
[Rules and Regulations]
[Pages 61395-61399]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-17327]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25809; Directorate Identifier 2001-NE-30-AD;
Amendment 39-14791; AD 2006-17-07R1]
RIN 2120-AA64

Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, -
7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -
217A, -217C, and -219 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule; correction.

-----------------------------------------------------------------------

SUMMARY: The FAA is revising an existing airworthiness directive (AD)
for Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11,
-15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219
turbofan engines. That AD currently requires either replacing high
pressure compressor (HPC) front hubs and HPC disks that have operated
at any time with PWA 110-21 coating and that operated in certain engine
models, or, visually inspecting and fluorescent penetrant inspecting
(FMPI) for cracking of those parts and re-plating them if they pass
inspection. This AD requires the same actions, but makes necessary
corrections to inadvertent reference errors and omissions found in AD
2006-17-07, and relaxes some of the compliance times in Table 5. This
AD results from our finding reference errors and omissions in AD 2006-
17-07, from determining that the AD as drafted imposed an unnecessary
burden on operators if they have to immediately remove engines, and
from requests to clarify compliance paragraphs. We are issuing this AD
to prevent a rupture of an HPC front hub or an HPC disk that could
result in an uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective November 2, 2006. The Director of the
Federal Register previously approved the incorporation by reference of
certain publications listed in the regulations as of October 4, 2006
(71 FR 51459, August 30, 2006).

ADDRESSES: You can get the service information identified in this AD
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108, telephone
(860) 565-7700; fax (860) 565-1605.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7189; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On August 21, 2006, the FAA issued AD 2006-
17-07, Amendment 39-14728 (71 FR 51459, August 30, 2006). That AD
requires either replacing HPC front hubs and HPC disks that have
operated at any time with PWA 110-21 coating and that operated in
certain engine models, or, visually inspecting and FMPI for cracking of
those parts and re-plating them if they pass inspection. That AD was
the result of an investigation by PW, which concluded that any HPC
front hub or HPC disk coated with PWA 110-21 that ever operated on
JT8D-15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -
219 turbofan engines, could crack before reaching their published life
limit. That condition, if not corrected, could result in an uncontained
engine failure and damage to the airplane.

Examining the AD Docket

You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.

Actions Since AD 2006-17-07 Was Issued

After we issued AD 2006-17-07, we found reference errors and
omissions. These errors and omissions could affect your ability to
comply with the AD. The following errors and omissions were discovered.
We made the associated corrections:
In the third column of Table 1 of this AD, we omitted ``-
17A'' in two places. We added the missing ``-17A'' from AD 2006-17-07
in both places.
The third column of Table 4 and Table 5 reads ``Paragraph
(h)(3) of this AD''. Paragraph (h)(3) does not exist. We corrected it
to read ``Paragraph (j) of this AD.''
We also determined that based on the compliance times in Table 5 of
AD 2006-17-07, some operators might have to immediately remove their
engines from service. If so, we concluded that those immediate removals
might impose an unanticipated undue burden. Table 5 of AD 2006-17-07,
appears below.

[[Page 61396]]

Table 5 of AD 2006-17-07--HPC Front Hub Inspection Schedule--Hubs
Coated With Nickel-Cadmium
------------------------------------------------------------------------
Also inspect 7th
Inspect before stage HPC disks
HPC front hub CSN on the additional CIS or and 9th stage-
effective date of this AD CSN, whichever through-12th stage
occurs first HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (h)(3)
CSN. of this AD.
(ii) 17,000 or more, but fewer 1,000 CIS or Paragraph (h)(3)
than 19,000. 19,500 CSN. of this AD.
(iii) 9,000 or more, but fewer 18,000 CSN........ Paragraph (h)(3)
than 17,000, that have not been of this AD.
inspected.
(iv) 9,000 or more, but fewer 15,500 CSN........ Paragraph (h)(3)
than 17,000, that were of this AD.
inspected before accumulating
9,000 CSN.
------------------------------------------------------------------------

Therefore, we changed Table 5 to reflect relaxed compliance
requirements in item (iii), and we changed the compliance requirements
in item (iv). With the addition of the ``-17A'' noted previously, and
the changed compliance requirements that relax compliance time, Table 5
now reads as follows:

(Changed) Table 5.--HPC Front Hub Inspection Schedule--Hubs Coated With
Nickel-Cadmium
------------------------------------------------------------------------
Also inspect 7th
Inspect before stage HPC disks
HPC front hub CSN on the additional CIS or and 9th stage-
effective date of this AD CSN, whichever through-12th stage
occurs first HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (j) of
CSN. this AD.
(ii) 17,000 or more, but fewer 1,000 CIS or Paragraph (j) of
than 19,000. 19,500 CSN. this AD.
(iii) 9,000 or more, but fewer 18,000 CSN........ Paragraph (j) of
than 17,000. this AD.
(iv) Fewer than 9,000 that are If the parts have Paragraph (j) of
accessible. been inspected this AD.
and are
acceptable, parts
may be
reinstalled.
Inspect again
using the
criteria in (iii)
of this table.
------------------------------------------------------------------------

As part of relaxing the requirements, we also clarified that
paragraphs (f)(3) and (j) pertain to 7th stage HPC disks and 9th stage-
through-12th stage HPC disks coated with PWA 110-21.
Finally, since AD 2006-17-07 was issued, we received multiple
instances of operators requesting clarification of compliance paragraph
(e) in AD 2006-17-07. Based on the frequency of requests, we decided to
clarify the paragraph. AD 2006-17-07 paragraph (e) originally read as
follows:

``(e) You must accomplish the actions required by this AD within
the compliance times specified, unless the actions have already been
done. Any engine with an HPC front hub that has been inspected using
AD 2002-23-14, AD 2003-12-07, or AD 2003-16-05, is considered in
compliance with this AD.''

We rewrote paragraph (e) to now read as follows:

``(e) You must accomplish the actions required by this AD within
the compliance times specified, unless the actions have already been
done. Any engine with an HPC front hub that has been inspected for
fretting wear using AD 2002-23-14, AD 2003-12-07, or AD 2003-16-05,
counts as an inspection toward compliance with this AD.''

FAA's Determination and Requirements of This AD

The unsafe condition described previously is likely to exist or
develop on other Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -
9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C,
and -219 turbofan engines of the same type design. We are issuing this
AD to prevent a rupture of an HPC front hub or an HPC disk that could
result in an uncontained engine failure and damage to the airplane.
This AD requires either replacing HPC front hubs and HPC disks that
have operated at any time with PWA 110-21 coating and that operated in
certain engine models, or, visually inspecting and FMPI for cracking of
those parts and re-plating them if they pass inspection.

FAA's Determination of the Effective Date

Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are unnecessary, and that good
cause exists for making this amendment effective in less than 30 days.

Docket Number Change

We are transferring the docket for this AD to the Docket Management
System as part of our on-going docket management consolidation efforts.
The new Docket No. is FAA-2006-25809. The old Docket No. became the
Directorate Identifier, which is 2001-NE-30-AD. This AD might get
logged into the DMS docket, ahead of the previously collected documents
from the old docket file, as we are in the process of sending those
items to the DMS.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;

[[Page 61397]]

(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the Federal
Aviation Administration amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by removing Amendment 39-14728 (71 FR
51459, August 30, 2006), and by adding a new airworthiness directive,
Amendment 39-14791, to read as follows:

2006-17-07R1 Pratt & Whitney: Amendment 39-14791. Docket No. FAA-
2006-25809; Directorate Identifier 2001-NE-30-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective November
2, 2006.

Affected ADs

(b) This AD revises AD 2006-17-07.

Applicability

(c) This AD applies to the following Pratt & Whitney (PW) JT8D-
1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R,
-17AR, -209, -217, -217A, -217C, and -219 turbofan engines, with 8th
stage high pressure compressor (HPC) front hubs:

Table 1.--AD Applicability
----------------------------------------------------------------------------------------------------------------
If the HPC front hub is coated And if the stage 8-9
with: spacer is coated with: And the HPC front hub: Then this AD is:
----------------------------------------------------------------------------------------------------------------
(1) PWA 110-21 at any time......... Any................... Operated in a JT8D-15, - Applicable. See
15A, -17, -17A, -17R, or - paragraph (f) and
17AR engine. Table 2 of this AD.
(2) PWA 110-21 at any time......... Any................... Operated in a JT8D-209, - Applicable. See
217, -217A, -217C, or -219 paragraph (h) and
engine. Table 4 of this AD.
(3) Nickel-Cadmium................. PWA 110-21 at any time Operated in a JT8D-209, - Applicable. See
217, -217A, -217C, or -219 paragraph (i) and
engine. Table 5 of this AD.
(4) Nickel-Cadmium................. PWA 110-21 at any time Operated in a JT8D-1, -1A, - Not applicable.
1B, -7, -7A, -7B, -9, -9A,
-11, -15, -15A, -17, -17A,
-17R, or -17AR engine.
(5) PWA 110-21 at any time......... Any................... Operated in a JT8D-1, -1A, - Not applicable.
1B, -7, -7A, -7B, -9, -9A,
or -11, but never operated
in a JT8D-15, -15A, -17, -
17A, -17R, -17AR, -209, -
217, -217A, -217C, or -219
engine.
(6) Nickel-Cadmium................. Any type but PWA 110- Any........................ Not applicable.
21.
----------------------------------------------------------------------------------------------------------------

These engines are installed on, but not limited to, Boeing DC-9,
MD-80 series, 727 series, and 737 series airplanes.

Unsafe Condition

(d) This AD results from inadvertent reference errors and
omissions found in AD 2006-17-07, which could affect ability to
comply with that AD. We are issuing this AD to prevent a rupture of
an HPC front hub or an HPC disk that could result in an uncontained
engine failure and damage to the airplane.

Compliance

(e) You must accomplish the actions required by this AD within
the compliance times specified, unless the actions have already been
done. Any engine with an HPC front hub that has been inspected for
fretting wear using AD 2002-23-14, AD 2003-12-07, or AD 2003-16-05,
counts as an inspection toward compliance with this AD.

JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -
17R, and -17AR Turbofan Engines--Inspect or Replace HPC Front Hubs, HPC
Disks, and Stage 8-9 Spacers

(f) For applicable JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11,
-15, -15A, -17, -17A, -17R, and -17AR turbofan engines specified in
Table 1 of this AD, do the following:
(1) Using the inspection schedule in Table 2 of this AD, strip
the protective coating, visually inspect for fretting wear,
fluorescent magnetic particle inspect (FMPI) for cracks, reidentify,
replate HPC front hubs and stage 8-9 spacers, and replace if
necessary.
(2) Use paragraphs 1. through 3.B.(7)(b) under ``For Rear
Compressor Front Hubs that Have Operated With PWA 110-21 coating AT
ANY TIME During Their Service Life in JT8D-15, -15A, -17, -17A, -
17R, -17AR Engine Models.'' of PW Alert Service Bulletin (ASB) JT8D
A6468, dated December 23, 2004.

Table 2.--HPC Front Hub Inspection Schedule
------------------------------------------------------------------------
Inspect before Also inspect 7th
HPC front hub cycles-since-new additional cycles- stage HPC disks
(CSN) on the effective date of in-service (CIS) and 9th stage-
this AD or CSN, whichever through-12th stage
occurs first HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (f)(3)
CSN. of this AD.
(ii) 15,500 or more, but fewer 1,000 CIS or Paragraph (f)(3)
than 19,000. 19,500 CSN. of this AD.
(iii) 5,000 or more, but fewer 16,500 CSN........ Paragraph (f)(3)
than 15,500. of this AD.

[[Page 61398]]

(iv) Fewer than 5,000 that are If the parts have Paragraph (f)(3)
accessible. been inspected of this AD.
and are
acceptable, parts
may be
reinstalled.
Inspect again
using the
criteria in (iii)
of this Table.
------------------------------------------------------------------------

(3) When the HPC front hub is inspected, visually inspect for
fretting wear and FMPI for cracks on 7th stage HPC disks and 9th
stage-through-12th stage HPC disks coated with PWA 110-21.
Inspection information can be found in the applicable sections of
JT8D Engine Manual Part Number (P/N) 481672, listed in the following
Table 3:

Table 3.--Seventh Stage HPC Disks and 9th Stage-Through-12th Stage HPC Disks Inspection Information
----------------------------------------------------------------------------------------------------------------
Chapter/ Fretting
Stage section Visual inspection inspection FMPI
----------------------------------------------------------------------------------------------------------------
7.............................. 72-36-41 Inspection-01.... Inspection-04.... Inspection-03.
9.............................. 72-36-43 Inspection-01.... Inspection-04.... Inspection-03.
10............................. 72-36-44 Inspection-01.... Inspection-04.... Inspection-03.
11............................. 72-36-45 Inspection-01.... Inspection-04.... Inspection-03.
12............................. 72-36-46 Inspection-01.... Inspection-04.... Inspection-03.
----------------------------------------------------------------------------------------------------------------

JT8D-15, -15A, -17, -17A, -17R, and -17AR Turbofan Engines--Cycle
Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium
Plating and PWA 110-21 Coating

(g) For JT8D-15, -15A, -17, -17A, -17R, and -17AR turbofan
engines with front hubs that entered service with Nickel-Cadmium
plating, but have also operated during the life of the hub with PWA
110-21 coating:
(1) You are allowed to make a cycle adjustment if the hub was
never operated with a PWA 110-21-coated stage 8-9 spacer.
(2) Use the information under ``Compliance'' of PW ASB JT8D
A6468, dated December 23, 2004, to determine the adjustment.

JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines--Inspect or
Replace HPC Front Hubs and Stage 8-9 Spacers

(h) For applicable JT8D-209, -217, -217A, -217C, and -219
turbofan engines specified in Table 1, Row (2) of this AD, do the
following:
(1) Using the inspection schedule in Table 4 of this AD, strip
the protective coating, visually inspect for fretting wear, FMPI for
cracking, reidentify, replate HPC front hubs and the stage 8-9
spacers, and replace if necessary.
(2) Use paragraphs 1. through 1.A. and paragraphs 2. through
2.C.(2)(g)2 of Accomplishment Instructions of PW ASB JT8D A6430,
Revision 2, dated December 23, 2004.

Table 4.--HPC Front Hub Inspection Schedule--Hubs Coated With PWA 110-21
------------------------------------------------------------------------
Also inspect 7th
Inspect before stage HPC disks
HPC front hub CSN on the additional CIS or and 9th stage-
effective date of this AD CSN, whichever through-12th stage
occurs first HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (j) of
CSN. this AD.
(ii) 15,500 or more, but fewer 1,000 CIS or Paragraph (j) of
than 19,000. 19,500 CSN. this AD.
(iii) 5,000 or more, but fewer 16,500 CSN........ Paragraph (j) of
than 15,500. this AD.
(iv) Fewer than 5,000 that are If the parts have Paragraph (j) of
accessible.. been inspected this AD.
and are
acceptable, parts
may be
reinstalled.
Inspect again
using the
criteria in (iii)
of this Table.
------------------------------------------------------------------------

(i) For applicable JT8D-209, -217, -217A, -217C, and -219
turbofan engines specified in Table 1, Row (3) of this AD, do the
following:
(1) Using the inspection schedule in Table 5 of this AD, strip
the protective coating, visually inspect for fretting wear, FMPI for
cracking, reidentify, replate HPC front hubs and the stage 8-9
spacers, and replace if necessary.
(2) Use paragraphs 1., 1.C, and 4. through 4.B.(2)(g)2 of
Accomplishment Instructions of PW ASB JT8D A6430, Revision 2, dated
December 23, 2004, for all applicable hubs with any type of coating.

Table 5.--HPC Front Hub Inspection Schedule--Hubs Coated With Nickel-
Cadmium
------------------------------------------------------------------------
Also inspect 7th
Inspect before stage HPC disks
HPC front hub CSN on the additional CIS or and 9th stage-
effective date of this AD CSN, whichever through-12th stage
occurs first HPC disks using:
------------------------------------------------------------------------
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (j) of
CSN. this AD.
(ii) 17,000 or more, but fewer 1,000 CIS or Paragraph (j) of
than 19,000. 19,500 CSN. this AD.
(iii) 9,000 or more, but fewer 18,000 CSN........ Paragraph (j) of
than 17,000. this AD.
(iv) Fewer than 9,000 that are If the parts have Paragraph (j) of
accessible. been inspected this AD.
and are
acceptable, parts
may be
reinstalled.
Inspect again
using the
criteria in (iii)
of this Table.
------------------------------------------------------------------------

[[Page 61399]]

(j) When the HPC front hub is inspected, visually inspect for
fretting wear and FMPI for cracks on 7th stage HPC disks and 9th
stage-through-12th stage HPC disks coated with PWA 110-21.
Inspection information can be found in the applicable sections of
JT8D-200 Engine Manual P/N 773128, listed in Table 3 of this AD.

JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines--Cycle
Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium
Plating and PWA 110-21 Coating

(k) For JT8D-209, -217, -217A, -217C, and -219 turbofan engines
with HPC front hubs that entered service with Nickel-Cadmium
plating, but have also operated during the life of the hub with PWA
110-21 coating:
(1) You are allowed to make a cycle adjustment.
(2) Use the information under ``CONDITION A'' of PW ASB JT8D
A6430, Revision 2, dated December 23, 2004, to determine the
adjustment.

Replacement of HPC Front Hubs and Stage 8-9 Spacers That Have Operated
With PWA 110-21 Coating, As Optional Action--All Engines

(l) For all applicable engines, as an optional action for the
visual inspections in this AD, replace HPC front hubs and stage 8-9
spacers that have operated with PWA 110-21 coating in the interface
between the hub and the stage 8-9 spacer and HPC disks currently
coated with PWA 110-21, as follows:
(1) Install a Nickel-Cadmium plated HPC front hub that has never
operated with PWA 110-21 coating in the interface between the HPC
front hub and the stage 8-9 spacer.
(2) Install a Nickel-Cadmium plated or Electroless Nickel-plated
stage 8-9 spacer.
(3) Install HPC disks that have never operated with PWA 110-21
coating.

Prohibition Against Recoating the HPC Front Hub, Stage 7 HPC Disk, and
Stage 8-9 Spacer With PWA 110-21--All Engines

(m) Do not recoat the HPC front hub with PWA 110-21 (Repair-23
of Chapter/Section 72-36-42 of JT8D-200 Engine Manual, P/N 773128,
and Repair-27 and Repair-28 of Chapter/Section 72-36-42 of JT8D
Engine Manual, P/N 481672).
(n) Do not recoat the 7th stage disk with PWA 110-21 (Repair-15
of Chapter/Section 72-36-41 of JT8D-200 Engine Manual, P/N 773128,
and Repair-15 of Chapter/Section 72-36-41 of JT8D Engine Manual, P/N
481672).
(o) Do not recoat the stage 8-9 spacer with PWA 110-21 (Repair-
03, Task 72-36-12-30-003-002, of Chapter/Section 72-36-12 of JT8D-
200 Engine Manual, P/N 773128, and Repair-01, Task 72-36-12-30-001-
002, of Chapter/Section 72-36-12 of JT8D Engine Manual, P/N 481672).

Prohibition Against Reinstalling HPC Front Hubs and Stage 8-9 Spacers
Coated With PWA 110-21

(p) After the effective date of this AD, do not reinstall HPC
front hubs and stage 8-9 spacers coated with PWA 110-21.

Definition

(q) For the purpose of this AD, ``accessible'' is defined as
when the HPC front hub is removed from the engine and the hub is
debladed.

Alternative Methods of Compliance

(r) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.

Related Information

(s) None.

Material Incorporated by Reference

(t) You must use the service information specified in Table 6 of
this AD to perform the actions required by this AD. The Director of
the Federal Register previously approved the incorporation by
reference of these alert service bulletins in accordance with 5
U.S.C. 552(a) and 1 CFR part 51, as of October 4, 2006 (71 FR 51459,
August 30, 2006). Contact Pratt & Whitney, 400 Main St., East
Hartford, CT 06108, telephone (860) 565-7700; fax (860) 565-1605 for
a copy of this service information. You may review copies at the
FAA, New England Region, Office of the Regional Counsel, 12 New
England Executive Park, Burlington, MA; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Table 6.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Pratt & Whitney Alert Service
Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
JT8D A6430, Total Pages: 35.... ALL.................... 2...................... December 23, 2004.
JT8D A6468, Total Pages: 20.... ALL.................... Original............... December 23, 2004.
----------------------------------------------------------------------------------------------------------------

Issued in Burlington, Massachusetts, on October 11, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-17327 Filed 10-17-06; 8:45 am]
BILLING CODE 4910-13-P

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