88-03-08 MCDONNELL DOUGLAS: Amendment 39-5838. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent failure of a horizontal stabilizer skin panel or a spar cap bolt due to stress corrosion, accomplish the following: \n\n\tA.\tWithin the next 6 months after the effective date of this AD, unless already accomplished since May 8, 1987, and thereafter at intervals not to exceed 2 years, inspect the horizontal stabilizer constant and outer section upper and lower skin panels and apply LPS-3 (or equivalent) corrosion-inhibiting compound in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision. \n\n\tB.\tWithin the next 6 months after the effective date of this AD, unless already accomplished since May 8, 1987, and thereafter at intervals not to exceed one year, inspect the horizontal stabilizer spar cap bolts made from H-11 material in accordance with McDonnell Douglas Alert Service Bulletin A55-17, dated May 8, 1987, or later FAA-approved revision. \n\n\tC.\tIf a broken bolt is found, prior to further flight, replace the broken bolt with a new bolt in accordance with McDonnell Douglas Alert Service Bulletin A55-17, dated May 8, 1987, or later FAA-approved revision. \n\n\tD.\tIf a crack is found in a skin panel: \n\n\t\t1.\tPrior to further flight, repair or replace in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision; or \n\n\t\t2.\tIf the crack is within limits defined in McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision, accomplish the following: \n\n\t\t\ta.\tPrior to further flight, apply LPS-3 (or equivalent corrosion inhibiting compound in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision; and \n\n\t\t\tb.\tPrior to further flight, inspect the horizontal stabilizer spar cap bolts nearest to the cracked panel(s) and, if necessary, replace broken attachment bolts in accordance with McDonnell Douglas Alert Service Bulletin A55-17, dated May 8, 1987, or later FAA-approved revision; and \n\n\t\t\tc.\tAt intervals not to exceed 3 months from the last inspection, reinspect the cracked skin panel(s) and the adjacent panels (forward and aft and inboard or outboard) and horizontal stabilizer spar cap bolts nearest to the cracked panel(s) in accordance with paragraphs A. and B., above. \n\n\tE.\tIf, at any inspection, a crack is found in the skin panel which is outside acceptable limits defined in paragraph D.2., above, prior to further flight, repair or replace in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision. \n\n\tF.\tInstallation of a new inconel or multiphase bolt, as applicable, to replace an H-11material bolt constitutes terminating action for the repetitive inspections required by this AD for that bolt. \n\n\tG.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tH.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective March 11, 1988.