93-20-02 MCDONNELL DOUGLAS: Amendment 39-8709. Docket 92-NM-220-AD. Supersedes AD 92-02-05, Amendment 39-8141. \n\n\tApplicability: Model DC-8-61, -62, -63, and -73 series airplanes equipped with a cargo conversion modification installed in accordance with Supplemental Type Certificate (STC) SA1802SO; and Model DC-8-21, -32, -33, and -51 series airplanes equipped with a cargo conversion modification installed in accordance with STC SA421NW; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent loss of the cargo door, damage to flight control surfaces, and reduced controllability of the airplane, accomplish the following: \n\n\t(a)\tWithin 7 days after the effective date of this AD, revise the Limitations Section of the appropriate FAA-approved Airplane Flight Manual Supplement (AFMS) by replacing item 5 in the AFMS for SA1802SO, and item 6 in the AFMS for SA421NW, with the following. (This may be accomplished by inserting a copy of this AD into the AFMS.) \n\n\t"Prior to initiating the cargo door closing sequence, a flight crew member must verify that the cargo door warning light is illuminated. After the door closing sequence is complete, and visual verification has been made that the latches are closed and the lockpins are properly engaged, a flight crew member must verify that the cargo door warning light is extinguished, and then conduct a PRESS-TO-TEST of the warning light to ensure that the light is operational. Pull the cargo door circuit breakers labeled "pump" and "valve" prior to takeoff. Methods for documentation of compliance with the preceding procedures must be approved by the FAA Principal Maintenance Inspector (PMI)." \n\n\t(b)\tWithin 7 days after January 21, 1992 (the effective date of AD 92-02-05, Amendment 39-8141), and thereafter at intervals not to exceed 100 hours time-in-service, perform the following inspections: \n\n\t\t(1)\tInspect the cargo door wire bundle between the exitpoint of the cargo liner and the attachment point on the cargo door to detect crimped, frayed, or chafed wires; and inspect for damaged, loose, or missing hardware mounting components. Prior to further flight, repair any damaged wiring or hardware mounting components in accordance with FAA-approved maintenance procedures. \n\n\t\t(2)\tInspect the cargo door latch rollers in the lower sill of the cargo door opening of the airplane to ensure that all twelve rollers can be freely rotated by hand. Prior to further flight, replace any discrepant roller components found, and repair any rollers that cannot be rotated freely by hand, in accordance with FAA-approved maintenance procedures. \n\n\t(c)\tAn 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, Atlanta Aircraft Certification Office (ACO), ACE-115A, FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(e)\tThis amendment becomes effective on November 17, 1993.