AD 2001-11-05 Airworthiness Directives; CFM International (CFMI) CFM56-2, -2B, -3, -5B, -5C and -7B Series Turbofan Engines

This airworthiness directive (AD) is applicable to CFM International CFM56-2, -2B, -3, -5B, -5C and -7B series turbofan engines with a No. 4 bearing, part number (P/N) 305-355-717-0, that has a serial number (SN) listed in Table 1 of this AD installed. These engines are installed on, but not limited to Airbus Industrie A319, A320, A321 and A340 series airplanes, Boeing 737 and KC135 series airplanes, and McDonnell Douglas DC8 series airplanes. Note 1: This 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 (h) 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 with this AD is required as indicated, unless already done. To prevent bearing failures, which could cause an engine failure, do the following: Number of Hours Until Number of Engines Must Be Limited (a) Limit the number of engines with a suspect No. 4 bearing that has a SN listed in the following Table 1 of this AD to one on each airplane within 300 hours time-in-service (TIS) after the effective date of this AD, but no later than July 1, 2001, whichever occurs earlier: Table 1.—CFM56 Engines With Suspect No. 4 Bearings Part No. Part serial No. Engine model Engine serial No. 305-355-717-0 DB387598-C 2B 714172 305-355-717-0 DB387670-5 2 692251 305-355-717-0 DB387608-F 3 725109 305-355-717-0 DB387612-8 3 720493 305-355-717-0 DB387614-4 3 721253 305-355-717-0 DB387625-H 3 720383 305-355-717-0 DB387647-Y 3 857594 305-355-717-0 DB387650-6 3 721237 305-355-717-0 DB387651-5 3 726245 305-355-717-0 DB387661-K 3 856671 305-355-717-0 DB387604-K 5B 779783 305-355-717-0 DB387605-J 5B 779784 305-355-717-0 DB387603-L 5B 779785 305-355-717-0 DB387590-5 5B 779786 305-355-717-0 DB387591-4 5B 779787 305-355-717-0 DB387634-3 5B 779796 305-355-717-0 DB387658-D 5B 779798 305-355-717-0 DB387654-2 5B 779799 305-355-717-0 DB387683-G 5B 779802 305-355-717-0 DB387648-W 5B 779803 305-355-717-0 DB387660-L 5B 779804 305-355-717-0 DB387606-H 5B 779960 305-355-717-0 DB387618-O 5B 779961 305-355-717-0 DB387599-B 5C 741948 305-355-717-0 DB387609-Y 7B 876395 305-355-717-0 DB387611-7 7B 876399 305-355-717-0 DB387615-3 7B 876400 305-355-717-0 DB387601-N 7B 876401 305-355-717-0 DB387594-1 7B 876403 305-355-717-0 DB387592-3 7B 876405 305-355-717-0 DB387610-8 7B 876406 305-355-717-0 DB387600-P 7B 876410 305-355-717-0 DB387649-V 7B 876421 305-355-717-0 DB387678-C 7B 876423 305-355-717-0 DB387652-4 7B 876424 305-355-717-0 DB387659-C 7B 876429 305-355-717-0 DB387693-1 7B 876431 305-355-717-0 DB387655-1 7B 876432 305-355-717-0 DB387684-F 7B 876434 305-355-717-0 DB387588-V 7B 876727 305-355-717-0 DB387657-E 7B 876729 305-355-717-0 DB387653-3 7B 876730 305-355-717-0 DB387597-D 7B 877404 305-355-717-0 DB387602-M 7B 877408 305-355-717-0 DB387589-U 7B 877427 305-355-717-0 DB387656-O 7B 875232 305-355-717-0 DB387671-4 7B 874219 Replacement of Suspect No. 4 Bearings (b) For engines that have a suspect No. 4 bearing that has a SN listed in Table 1 of this AD, replace the No. 4 bearing with a serviceable part within 2,000 hours TIS, after the effective date of this AD, but no later than December 31, 2001, whichever occurs earlier. Installation of Suspect No. 4 Bearings (c) After the effective date of this AD, do not install any No. 4 bearing that has a SN listed in Table 1 of this AD. (d) After the effective date of this AD, do not install any engine that has a No. 4 bearing with a serial number listed in Table 1 of this AD. Initial Inspections for Chip Detector Indications (e) For engines that have a suspect No. 4 bearing that has a SN listed in Table 1 of this AD, inspect for magnetic chip indications within in the specified times, and if necessary, disposition as follows: (1) For CFM56-5B engines, check electronic magnetic chip detector (EMCD) visual indicator within 50 to 75 hours TIS after the effective date of this AD. (2) For CFM56-5C engine (741948), check for class 2 Electronic Centralized Aircraft Monitor (ECAM) message “MAGNETIC CHIP DETECTED” before further flight. (3) For CFM56-7B engines equipped with Debris Monitoring System (DMS) option, check Flight Management Computer—Master Control Display Unit (FMC-MCDU) for message 79-2114 before further flight. (4) For CFM56-7B engines equipped with classic magnetic chip detectors (MCD), inspect aft sump MCD within 50 to 75 hours TIS after the effective date of this AD. (5) For CFM56-2, -2B, and -3 engines, inspect aft sump MCD within 50 to 75 hours TIS after the effective date of this AD. (6) If bearing particles are found, remove engine from service before further flight. Repetitive Inspections for Chip Detector Indications (f) Thereafter, inspect for chip indications in accordance with the specified time-since-last-inspection (TSLI), and if necessary, disposition as follows: (1) For CFM56-5B engines, check EMCD visual indicator every 50-75 hours TSLI. (2) For CFM56-5C engine (741948), check for class 2 ECAM message “MAGNETIC CHIP DETECTED” after every flight. (3) For CFM56-7B engines equipped with DMS option, check FMC-MCDU for message 79-2114 once per day. (4) For CFM56-7B engines equipped with classic MCD, inspect aft sump MCD every 50-75 hours TSLI. (5) For CFM56-2, -2B, and -3 engines, inspect aft sump MCD every 50-75 hours TSLI. (6) If bearing particles are found, remove engine from service before further flight. Terminating Action (g) Replacement of a No. 4 bearing that has a SN listed in Table 1 of this AD with a No. 4 bearing that does not have a SN listed in Table 1 of this AD is terminating action for the repetitive inspection requirements specified in paragraph (f) of this AD. Alternative Methods of Compliance (h) 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 request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. Special Flight Permits (i) Special flight permits may be issued in accordance §§ 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. Effective Date of This AD (j) This amendment becomes effective on June 11, 2001. Issued in Burlington, Massachusetts, on May 24, 2001. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 01-13720 Filed 5-31-01; 8:45 am] BILLING CODE 4910-13-U