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98-04-39
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CCOC Rear Flange Category
- Engine Applicability: Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines, with combustion chamber outer case (CCOC) part numbers (P/Ns) 490547, 542155, 616315, 728829, 728829-001, 730413, 730413-001, 730414, 730414-001, 767197, 767279, 767279-001 installed. These engines are installed on but not limited to Boeing 737 and 727 series, and McDonnell Douglas DC-9 series aircraft. 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 (c) of this AD. The request should include an assessment of the effect 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. Compliance: Required as indicated, unless accomplished previously. To prevent uncontained engine failure, inflight engine shutdown, engine cowl release, and airframe damage, accomplish the following: (a) For engines identified by serial number (S/N) in Table 1 of this AD, perform a one-time borescope inspection of the CCOC rear flange in accordance with paragraph 2.A.(5) of PW Alert Service Bulletin (ASB) No. A6202, Revision 1, dated January 4, 1996, as follows: Table 1 648796.........653799 655969 665370 674333 695297 702602 648859.........653876 655987 665372 674370 696555 702648 649077.........653904 656036 665382 674513 696573 702699 649135.........654043 656084 665393 674564 696645 702712 649157.........654115 656121 665520 674580 696668 702772 649212.........654428 656948 665529 674611 696757 707158 649262.........654557 656964 665744 687407 700037 707200 649331.........654804 657064 665992 687457 700053 707405 649354.........654860 657119 666004 687634 700103 707922 649406.........654877 657386 666019 687851 700140 708332 649451.........654915 657418 666076 687891 700145 708921 649675.........654949 657584 666331 687893 700156 709002 653316.........654986 657613 666682 688029 700223 709168 653329.........655108 657677 666715 688051 700243 709209 653363.........655310 657739 666948 688054 700248 653495.........655437 665410 667042 688103 700261 653514.........655821 665412 667045 688161 700334 653545.........655842 665461 667059 688470 700383 653574.........655857 665468 667068 688491 700398 653609.........655870 665489 667110 688499 700404 653622.........655898 665497 674193 689934 700665 653789.........655900 665364 674251 695290 700133 (1) For engines installed on McDonnell Douglas DC-9 series aircraft, inspect within 1,000 cycles in service (CIS) since the last ultrasonic inspection of the CCOC rear flange performed in accordance with AD 96-23-14, or within 100 CIS after the effective date of this AD, whichever occurs later. (2) For engines installed on Boeing 737 series aircraft, inspect within 1,500 CIS since the last ultrasonic inspection of the CCOC rear flange performed in accordance with AD 96-23-14, or within 100 CIS after the effective date of this AD, whichever occurs later. (3) For engines installed on Boeing 727 series aircraft, inspect within 2,500 CIS since the last ultrasonic inspection of the CCOC rear flange performed in accordance with AD 96-23-14, or within 100 CIS after the effective date of this AD, whichever occurs later. (b) If the ultrasonic probe assembly, PWA 47942, used to inspect the CCOC rear flange in accordance with AD 96-23-14 was overhauled, repaired, or otherwise altered since original manufacture and not subsequently functionally checked at PW, within 30 days after the effective date of this AD return ultrasonic probes to PW to perform a functional check of the ultrasonic probe assembly. Note 2: Operators should note that future inspections performed using the probe must be performed with a probe that has passed a functional check at PW since overhaul, repair, or alteration. (1) If the ultrasonic probe assembly does not pass the functional check, PW must inform the operator, within 24 hours after the probe fails the functional check. (2) If the ultrasonic probe assembly does not pass the functional check at PW, all engines that were ultrasonically inspected with that probe in accordance with AD 96-23-14 must be borescope inspected in accordance with paragraph 2.A.(5) of PW ASB No. A6202, Revision 1, dated January 4, 1996. Perform the inspections as follows: (i) For engines installed on McDonnell Douglas DC-9 series aircraft, inspect within 1,000 cycles in service (CIS) since the last ultrasonic inspection of the CCOC rear flange performed in accordance with AD 96-23-14, or within 100 CIS after determining the probe is defective, whichever occurs later. (ii) For engines installed on Boeing 737 series aircraft, inspect within 1,500 CIS since the last ultrasonic inspection of the CCOC rear flange performed in accordance with AD 96-23-14, or within 100 CIS after determining the probe is defective, whichever occurs later. (iii) For engines installed on Boeing 727 series aircraft, inspect within 2,500 CIS since the last ultrasonic inspection of the CCOC rear flange performed in accordance with AD 96-23-14, or within 100 CIS after determining the probe is defective, whichever occurs later. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 3: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The actions required by this AD shall be done in accordance with the following PW ASB: Document
No. Pages Revision
Date This incorporation by reference of Pratt & Whitney Alert Service Bulletin No. A6202, Revision 1, dated January 4, 1996, was approved previously by the Director of the Federal Register as of January 2, 1997 (61 FR 63707, December 2, 1996). Copies may be obtained from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-6600, fax (860) 565-4503. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on February 25, 1998. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7175, fax (781) 238-7199.
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