87-17-10 GENERAL DYNAMICS (Convair): Amendment 39-5715. Applies to Models 340, 440, and C-131 (Military) series airplanes, including all such model airplanes converted to turbo- propeller power, equipped with main landing gear drag strut pivot bolt assembly Part Numbers (P/N) 340-5110105, or 340-5110105-1, or 340-5110105-3, certificated in any category. Compliance required as indicated, unless previously accomplished.
To prevent failure of the main landing gear drag strut pivot bolt and possible subsequent main landing gear collapse, accomplish the following:
A. Within 500 hours time-in-service after the effective date of this AD, inspect the main landing gear drag strut pivot bolt assembly P/N 340-5110105 or 340-5110105-1 or 340- 5110105-3, using magnetic particle inspection procedures, in accordance with Paragraph 2., "Accomplishment Instructions" of General Dynamics, Convair Division, Service Bulletin 640(340D)32-14, dated October 10, 1986, or later revisions approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region.
1. If no cracks are found, reinstall the bolt and repeat the bolt inspection in accordance with paragraph A., above, at intervals not to exceed 500 hours time-in-service since last bolt inspection.
2. If any crack is found, prior to further flight replace main landing gear drag strut pivot bolt assembly with P/N 340-5110105, 340-5110105-1, 340-5110105-3, 340- 5110105-5, or equivalent approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region.
a. If a new P/N 340-5110105 or 340-5110105-1 main landing gear drag strut pivot bolt assembly is used as a replacement, repeat the bolt inspection in accordance with paragraph A., above, within 3,000 hours time-in-service after bolt installation and thereafter at intervals not to exceed 500 hours time-in-service since last bolt inspection.
b. If a new main landing gear drag strut pivot bolt assembly P/N 340-5110105-3 is used as a replacement part, repeat bolt inspection in accordance with paragraph A., above, within 8,000 hours time-in-service after bolt installation and thereafter at intervals not to exceed 500 hours time-in-service since last bolt inspection.
c. Installation of main landing gear drag strut pivot bolt assembly P/N 340-5110105-5 constitutes terminating action for the repetitive inspections required by this AD.
B. Upon the request of an operator, an FAA Maintenance Inspector, subject to prior approval by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of that operator if the request contains substantiating data to justify the change for that operator.
C. Alternate means of compliance which provide an acceptable level of safety, may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region.
D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to a base to comply with the requirements of this AD.
All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the General Dynamics, Convair Division, P.O. Box 85377, San Diego, California 92138, Attn: Chief, Aircraft Logistical Support, Mail Zone 92-2920. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at FAA, Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California.
This amendment becomes effective September 24, 1987.