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AD 62-02-02 ACTIVE

Engine Compressor Rotor Disc
Key Information
AD Number 62-02-02 Status Active
Effective Date Not specified Issue Date Not specified
Docket Number Unknown Amendment N/A
Product Type ["Aircraft"] Product Subtype ["Large Airplane"]
CFR Part --- - Part 39 CFR Section N/A
Citation (Federal Register: January 16, 1962)
Applicability
Manufacturer(s) The Boeing Company
Model(s) 707-100 Long Body 707-100B Long Body 707-100B Short Body 707-200 707-300 Series 707-300B Series 707-300C Series 707-400 Series 720 Series 720B Series DC-8-11 DC-8-12 DC-8-21 DC-8-31 DC-8-32 DC-8-33 DC-8-41 DC-8-42 DC-8-43 DC-8-51 DC-8-52 DC-8-53 DC-8-55 DC-8-61 DC-8-61F DC-8-62 DC-8-62F DC-8-63 DC-8-63F DC-8-71 DC-8-71F DC-8-72 DC-8-72F DC-8-73 DC-8-73F DC-8F-54 DC-8F-55
Regulatory Text

62-02-02 BOEING AND DOUGLAS: Amdt. 385 Part 507 Federal Register January 16, 1962. Applies to All 707/720 Series and DC-8 Series Aircraft Equipped With Pratt and Whitney JT3D-3 Turbofan Engines. \n\n\tCompliance required as indicated. \n\n\t(a) For engines previously inspected by the procedure described in paragraph (c), reinspect in accordance with paragraph (c) every 225 hours' time in service thereafter. \n\n\t(b) For engines not previously inspected by the procedure described in paragraph (c) inspect in accordance with paragraph (c) as follows: \n\n\t\t(1) Inspect engines with 200 or more hours' time in service within the next 25 hours' time in service and every 225 hours time in service thereafter. \n\n\t\t(2) Inspect engines with less than 200 hours' time in service by the time 225 hours' time in service have been accumulated and every 225 hours' time in service thereafter. \n\n\t(c) Due to recent failures of P/N 393504 fourth stage compressor rotor disc, inspect the disc for cracks adjacent to the inside edge of the tie bolt circular rib in the disc web. Such cracks may progress along the inside of the rib and then toward the disc bore through the bore stiffening section. \n\n\tTo accomplish the inspection, remove the front accessory drive support assembly (N1 gearcase) and the front accessory drive main spur gear (N1 gearcase coupling). Using a strong light and borescope or similar optical device, visually inspect the fourth stage compressor rotor disc in the area noted above. If any cracking is found, the engine must be removed for disc replacement prior to further flight. \n\n\t(d) The requirement for main oil screen inspection per AD 61-24-01 does not apply when the No. 1 bearing compartment is exposed for this disc inspection. \n\n\t(Pratt and Whitney Aircraft telegraphic message of December 19, 1961, covers the same subject.) \n\n\tThis directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated December 22, 1961. \n\n\tRevised October 12, 1962.