Normal Procedures for the Beechcraft T-34 Mentor

Full document text

T-34 Spar Corporation T-34 AIRFRAME LIFE EXTENSION CABLE SYSTEM Continued Airworthiness Manual This report applies to T-34 Spar Corp. Airframe Life Extension Cable systems per STC SA 10362SC. 45-1760002 Continued Airworthiness Rev. E Page 1 10 August 2010 T-34 Spar Corporation LOG OF REVISIONS Pages Revision Date Remarks 1-10 NC 06 Apr 10 Initial Release 4,6 A 14 May 10 Cable tension nut now turn 4½ to 434 turns was 44 to 4½. Revised inspection intervals. Add bolt and nut replacement every 10,000 hours. 4,6,7 B 01 July 10 1,6 C 20 Jul 10 6 D 05 Aug 10 6 E 10 Aug 10 Clarify inspection/replacement interval timing Add STC number and clarify logbook entry Clarify cable retension interval Revise cable retension interval Revisions Lettered revisions of this document may be issued periodically. Each revision will cover the entire document. Changes to data in the previous revisions will be identified by revision bars in the outer margins of the pages. Change bars will be shown only against the immediate prior revisions. Extensive changes will not be accompanied by change bars but will be identified on Log of Revisions page under the Remarks section. Revision Distribution The latest revision of this document in its entirety will be posted at www.taturbo.com/drawings/ 45-1760002 Continued Airworthiness Rev. E Page 12 10 August 2010 T-34 Spar Corporation TABLE OF CONTENTS Subject Log of Revisions Referenced Instructions for Continued Airworthiness and other Publications AIRWORTHINESS LIMITATIONS ALEC SYSTEM DESCRIPTION MAINTENANCE PRACTICES Time Limits and Maintenance Checks ALEC REMOVAL AND REINSTALLATION A. Wing Removal B. Wing Installation C. Adjustments - Post Wing Installation Page 2 3 4 5 6 6 7 7 7 7 Referenced Instructions for Continued Airworthiness and other Publications The latest revision to the following publications should be used in conjunction with this manual: Vendor T-34 Spar Corporation T-34 Spar Corporation T-34 Spar Corporation Manual Title Installation Instructions For T-34, T-34A, And T-34B Main Wing Spar Lower Wing Bolt Replacement And Tension Cable Per T-34 Spar Corp. AMOC To AD 2004-25-51 T-34A/B Main Spar Carry-through Rotating Probe, Bolt-hole Eddy Current Inspection Procedure and Cold Work T-34A/B Main Spar Carry-through Surface Eddy Current Inspection Procedure Part Number 45-6460002 TSC 3507 TSC 3505 45-1760002 Continued Airworthiness Rev. E Page 3 10 August 2010 T-34 Spar Corporation AIRWORTHINESS LIMITATIONS The Airworthiness Limitations Section is FAA approved and specifies inspection and maintenance required under paragraphs 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. Every 2900 hours of accumulated flight time: Perform "Surface" eddy current inspection in accordance with T-34 Spar Corp. TSC-3505. Every 2900 hours of accumulated flight time: Perform "Bolt Hole" eddy current inspection in accordance with T-34 Spar Corp. TSC-3507. The lower front spar wing attach bolts and nuts, T-34 Spar Corporation Part Numbers 45-133A and 45- 132, are life limited and must be replaced on or before accumulating 10,000 hours of flight time. This a repetitive requirement. All inspection interval and replacement times are referenced from initial installation of ALEC system. Each subsequent inspection or replacement interval time is referenced from time of last inspection or replacement time. A. There are no other limiting inspections and/or maintenance items. FAA Approved SSSE Date 8.27.10 45-1760002 Continued Airworthiness Rev. E Page 14 10 August 2010 T-34 Spar Corporation ALEC SYSTEM DESCRIPTION T-34 Spar Corp has developed a tension cable system to be installed in the lower front spar carry through structures of the Hawker Beechcraft T-34 aircraft, Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T- 34B). The tension cable system is intended to reduce tension loading and to also produce beneficial compression stresses at identified critical fastener holes in the center fuselage carry through structure. The results of the cable installation is to extend the life of the spar carry through structure in order to eliminate the restrictions placed upon the structure by AD 2004-25-51. Specific modifications to the fuselage wing carry through structure include the replacement of OEM 160- 180 ksi carbon steel bolt system (bolt nut combination) with a modified 220 ksi Inconel 718 bolt system (new bolt nut combination). These are tension bolts used to attach the lower wing main spars to the fuselage center section carry through structure. These tension bolts have holes through the length of the bolts for the ALEC cable to pass through. The pre-tensioned ALEC cable is designed to apply approximately 7,500 pounds of compressive pre-loading to the center spar carry through structure. The intent of the modification is to lower the peak cyclic maximum tension stress through the front center spar carry through structure. The pre-loading is further supplemented during aircraft maneuver loading so that when the airframe experiences a six (6) g "event" the lower spar carry through structure will have approximately 10,000 to 12,000 lbs of load carried by the tension cable that would otherwise pass through the front center spar carry through structure. 45-1760002 Continued Airworthiness Rev. E Page 5 10 August 2010 1. 2. 3. T-34 Spar Corporation MAINTENANCE PRACTICES TIME LIMITS AND MAINTENANCE CHECKS Airframe Group Visually inspect the carry through structure Visually inspect the forward and aft webs and high shear fasteners of the forward spar carry through structure Visually inspect the lower belly skins for any signs of loose or missing rivets, deformed or buckling skins or any other signs of failure. Interval Initials 100 hrs Special X X X 4. Visually inspect all wing bolt bath tub fittings for corrosion, cracks or any other sign of failure and to make sure that the drain holes of the upper bathtub fittings are unobstructed. X 5.