- All tubing cleaned, inspected, oiled, primed with epoxy primer and painted.
- Wood given 2 coats of epoxy varnish before installation.
- All wiring replaced with new in accordance with 43-13-1A /2A section 2 and removed
12 volt system and rewired for 24 volt system (see field approval 337 dated 4-20-01).
- Fabricate new battery boxes to hold 2 24 volt #G-24 batteries and vented both boxes.
- Gear and flap motors rewound to 24 volts.
- Converted original flap and gear electrical systems to use limit switches, solenoid
and micro switch.
- Replaced generator with Skytronic STC'd alternator under STC-SA-2015-WE and field
approval (see 337 dated 01/05/99.
- Continual use electrical load calculated to be 15 AMPS with alternator output capacity
rated at 50 AMPS. This puts electrical system capacity within limits specified by
AC 41.13-1A/2A, sec.2.
- Remove bungee cord and replace with spring for tail wheel retract under 337
field approval dated 04/20/01
- Remove red rotating beacon and replace with Whelen PMA strobe system under 337
field approval and STC-615-EA and 337 dated 04/20/01.
- Remove wobble pump and manual primer and replace with electric boost pump and
electric primer. Original 2 fuel selector valves were replaced with a single selector
valve. Original fuel gages replaced with Rochester aircraft fuel gages. Fuel gages
were calibrated for accuracy. Fuel system was flow tested to ensure sufficient fuel
supply in all positions. See 337 dated 04/20/01. Installed decal per AD 99-05-13.
- Install cabin blower system. See field approval and 337 dated 04/20/01.
- Fabricate replacement tail wheel fork per factory drawings. Tail wheel fork heat treated
before installation.
- Landing gear assembly and hinge brackets for rudder and elevator chromed and heat
treated by Homan Plating in accordance with ANSI/NCSL Z540-1-1994/ISO-10012-1.
- Landing gear cross shaft repaired to better than original strength by addition of 3/4"
diameter, .095" wall, 4130 steel tube welded inside original shaft.
- Installed 2 new landing gear slide tubes.
- Original brakes replaced with Cessna 310 brakes (Cylinders, wheels, rotors, discs,
hoses and lines). Replaced mechanical parking brake with new hydraulic parking
brake valve. Brake mods performed under STC-2378SW and parking brake mod
under field approval 337 dated 04/20/01.
- Install all three new tires and tubes (Mains and tailwheel).
- Landing gear retract system cycled through numerous cycles to ensure fault free
operation of assembly.
- Assembly of all components with new AN hardware as shown in BEECH P&M 
manuals.
- All control cables replaced with new cables.
- All instruments overhauled or repaired as necessary. Reinstall in panel and check
for proper operation.
- Install new windshield and 4 side windows.
- Appropriate placards and labels installed as necessary to instrument panel
and fuel selector.
- Radio and avionics installation done by Avionics Inc. (See 337 and operating
handbook for revisions)
- Installed rocker box sump drain valve under field approval 337 dated 04/20/01
- Install Beryl D'Shannon air / oil separator under STC-SA2653WE and field
approval dated 04/20/01.
WINGS AND EMPENAGE
- Wings were returned to original configuration to accommodate original retractable
landing and taxi lights.
- Wirng installed for landing lights, nav lights, flap motor, pitot heat and RMI
per 43.13-1A/2A
- Install new leading edges on all 4 wings using wood screws instead of nails.
- Rib stitched using original BEECH hidden rib stitch knot.
- All 4 wing fuel tank bays were given 2 coats of aluminum powdered epoxy varnish
to fuel proof.
- All 4 wings were given 2 coats of epoxy varnish.
- Ailerons, flaps, rudder, elevator and stabilizers were given 2 coats of epoxy varnish.
These items were also rib stitched with the BEECH hidden knot.
- All controls were checked for balance per BEECH assembly and repair manuals.
All found to be within limits except for left elevator counterweight. The counterweight
and support tube were replaced and adjusted for proper elevator balance.
COVERING SYSTEM
- All required components were covered using the Stits Process in accordance with
STC-SA-1000-WE and Stits Poly-Fibre Covering and Painting Manual #1,
revision 15, 6th edition dated june 1992. Used Stits HD 2X2 fabric and Stits finishing
tapes, rib lacing cord and rib reinforcing tape. Final finish consisted of 3 coats of
Poly-Brush, 6 coats of Poly-Spray and 4 coats of Aero-Thane #161 Pontiac Red.
The stripes are Boston Maroon and Gold Aero-Thane.
FINAL ASSEMBLY & TESTING
- Aircraft assembled in accordance with BEECH Maintenance Manual. Engine and
prop installed. All rigging, cable tensions, and control surface travels checked and
and found to be within limits.
- Aircraft weighed and new weight and balance computed and determined to be within
CG envelope as per BEECH Manual.
- Aircraft empty weight 2840 LBS. Useful load 1410 LBS.
- The following AD's complied with prior to aircraft runup and taxi: 48-51-01, 75-05-02,
and 99-05-13.
- Aircraft ground run and taxi test performed.
- Electrical system tested and load limits found to be within part 43-13-1 requirements.
- Aircraft determined to be OK for test flight.
I certify that this aircraft has been inspected in accordance with an annual inspection
and was determined to be in airworthy condition.
DATE: JULY 01, 2001 SIGNED:_________________________________________
Michael H. Wells AP 2099762 IA
