78-22-05 BEECH: Amendment 39-3329. Applies to the following models and serial number airplanes, certificated in all categories: \n\n\nMODEL\nSERIAL NUMBERS\n50\nH-1 through H-11\nB50, C50\nCH-12 through CH-360\nD50, D50A, D50B, D50C and D50E\nDH-1 through DH-347 \nE50\nEH-1 through EH-70\nF50\nFH-71 through FH-93, FH-95, FH-96\nG50\nGH-94, GH-97 through GH-119\nH50\nHH-120 through HH-149\nJ50\nJH-150 through JH-176\n65, A65, A65-8200\nL-1, L-2, L-6, LF-7, LF-8, LC-1 through LC-335\n70\nLB-1 through LB-35\n65-80, 65-A80, 65-A80-8800, 65-B80\nLD-1 through LD-511 \n65-88\nLP-1 through LP-28, LP-30 through LP-47\n65-90, 65-A90, B90, C90\nLJ-1 through LJ-797 \nE90\nLW-1 through LW-297\n99, 99A, A99A, B99\nU-1 through U-164\n100, A100\nB-1 through B-247 \nB100\nBE-1 through BE-55\n\n\tCOMPLIANCE: Required as indicated unless already accomplished. \n\n\tTo prevent partial loss of elevator control due to possible failure of elevator control push rods, in accordance with instructions set forth herein and in Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions, accomplish the following: \n\n\tA)\tOn the following airplanes: \n\n\nMODEL\nSERIAL NUMBERS\n50\nH-1 through H-11\nB50, C50\nCH-12 through CH-360 \nD50, D50A, D50B, D50C and D50E\nDH-1 through DH-347 \nE50\nEH-1 through EH-70\nF50\nFH-71 through FH-93, FH-95, FH-96\nG50\nGH-94, GH-97 through GH-119\nH50\nHH-120 through HH-149\nJ50\nJH-150 through JH-176\n65, A65, A65-8200\nL-1, L-2, L-6, LF-7, LF-8, LC-1 through LC-335\n70\nLB-1 through LB-35\n65-80, 65-A80, 65-A80-8800 and 65-B80\nLD-1 through LD-511 \n65-88\nLP-1 through LP-28 and LP-30 through LP-47\n65-90, 65-A90, B90 and C90\nLJ-1 through LJ-716 \nE90\nLW-1 through LW-222\n99, 99A, A99A and B99\nU-1 through U-164\n100, A100\nB-1 through B-233\nB100\nBE-1 through BE-23\n\n\tUpon the accumulation of 1,050 hours total time-in-service for airplanes with less than 1,000 hours total time-in-service on the effective date of this AD,or \n\n\tWithin 50 hours time-in-service after the effective date of this AD, for airplanes with more than 1,000 hours total time-in-service on the effective date of this AD, that have not complied with AD 70-18-02, or \n\n\tWithin 500 hours time-in-service after the last inspection in accordance with AD 70-18- 02, for airplanes with more than 1,000 hours total time-in-service that have complied with AD 70-18-02: \n\n\t\t1.\tReview the airplane maintenance records for entries showing that Beechcraft Service Instructions No. 0334-152, Revision II, has been complied with. If Revision II of the Service Instructions has not been complied with, accomplish Paragraph A)2 of this AD. If Revision II of the Service Instructions has been complied with, accomplish Paragraph A)3 of this AD within an additional 100 hours time-in-service after this finding. \n\n\t\t2.\tGain access to the elevator control push rods (reference Figures I and II of this AD) and visually inspect for the words "CORROSION PROOFED"ink stamped near the center of the rods. If the words "CORROSION PROOFED" are ink stamped on a rod, no further action on that rod is required by this AD. If the words "CORROSION PROOFED" are not ink stamped on the rods, remove the elevator control push rods, clean, dye penetrant and visually inspect, check for bows, apply corrosion preventative treatment, identify and reinstall, all in accordance with Part I of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. \n\n\t\t3.\tGain access to the elevator control push rods (reference Figures I and II of this AD) and visually inspect for the words "CORROSION PROOFED" ink stamped near the center of each rod. If the words "CORROSION PROOFED" are ink stamped on a rod, then no further action on that rod is required by this AD. If the words "CORROSION PROOFED" are not ink stamped on any rod and new rods were not installed during compliance with Revision II of the Service Instructions, paint a black stripe around the center of each rod in accordance with Part II of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. If any new rods were installed during compliance with Revision II of the Service Instructions and the new rods are not ink stamped "CORROSION PROOFED", on each new rod so installed, remove the elevator control push rod, disassemble, inspect for corrosion preventative treatment and alignment, and if not found accomplished, apply the corrosion preventative treatment, identify, reassemble and reinstall, all in accordance with Part III of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. \n\n\tB)\tOn the following airplanes: \n\n\nMODEL\nSERIAL NUMBERS\nC90\nLJ-717 through LJ-797\nE90\nLW-223 through LW-297\nA100\nB-234 through B-247 \nB100\nBE-24 through BE-55\n\n\tWithin 100 hours time-in-service after the effective date of this AD: \n\n\t\t1.\tGain access to the elevator control push rods (reference Figures Iand II of this AD) and visually inspect for the words "CORROSION PROOFED" ink stamped near the center of the rods. If the words "CORROSION PROOFED" are ink stamped on a rod, no further action on that rod is required by this AD. If the words "CORROSION PROOFED" are not ink stamped on the rods, remove the elevator control push rod tubes, disassemble, inspect for corrosion preventative treatment and alignment, and if not found accomplished, apply the corrosion preventative treatment, identify, reassemble and reinstall, all in accordance with Part III of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. \n\n\tC)\tOn all airplanes affected by this AD, replace any elevator control push rods found cracked or otherwise unserviceable during any inspection required by this AD with serviceable rods that comply with the requirements of this AD prior to returning the airplane to service. \n\n\tD)\tAny equivalent means of compliance with this AD must be approvedby the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tThis AD supersedes AD 70-18-02, Amendment 39-907 (35 FR 305) as amended by Amendments 39-1074 (35 FR 13722 and 13723) and 39-1879 (39 FR 21120). \n\n\tThis amendment becomes effective November 6, 1978.