REPUBLIC RC-3 SEABEE # 813

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AIRCRAFT DATA

Bill of Sale (Form ACA-500 Pt C).  Seller: Republic Aviation Corp. / Purchaser: Anderson Air Activities; General Mitchell Field, Milwaukee 7, Wisconsin, USA.

Signed by Assistant Treasurer; M. G. Veckman (Republic) on 1952-02-14 (Duplicate Bill of Sale).

C of A issued by CAA Inspector Harry M. Jones.

Annual Inspection (C of A Form ACA-1362 issued to expire 1953-01-08).

The original throttle and propeller pitch controls were removed and new controls installed as shown in Pan Air Corporation drawing #80001.  A standard aircraft throttle and mixture control quadrant was used.  This modification is similar to that approved by R. E. McKissick, 9-30-55, on RC-3 #N-6537K, owned by Mechanical Equipment Company, Inc., New Orleans, Louisiana.

The rivets attaching the aft spar of the center section were replaced with AN24 bolts.  The holes were reamed.  The left u-right channel was reinforced on each side, at top, with an .064 angle riveted to the channel.  The lower end of the same channel was reinforced with a plate on the outside of skin.

Removed oil cooler Heat Exchanger Mod. 100, and installed APU3170-W-D5 Item 102.  Installed identical as approved on RC3, N6705K dated 4/22/54 and on file at FAA regional office, Fort Worth, Tex.

Installed rotating beacon on vertical fin with machine screws and anchor nuts Re. CAR 3.386.  The #16 gage wire meets specification MIL-W-5086.  The beacon is protected by a 10 ampere circuit breaker switch.

Installed Narco VHT3 superhomer in radio cutout on instrument panel with machine screws and stop nuts, Re. CAR 3.286(d).  The wires used were supplied by the manufacturer of the radio or meet specifications of MIL-W-5086A.  All wires and bundles are tied and clamped in accordance with standard aircraft practice, Ref. CAR 3.721.  This radio given a functional test, CAR 3.652.  This radio is protected by a 10 ampere automatic circuit breaker mounted under the radio.  Magnetic compass has been checked with radio on, Ref. CAR 3.758.

The total electrical running load is 11.8 amperes.  This is less than 80% of the 35 ampere generator, Ref. CAM 18.30-12(i).

Installed Delco DC-12 battery in original battery box with a 1/2" felt pad saturated with bicarbonate soda to absorb and neutralize spillage.

Empty weight: 2262.5 lbs.

Removed Autolite voltage regulator and installed and Allstate P/N 1457 regulator,  This regulator is a replacement part for Autolite.  No weight change.

Franklin 6A8-215-B9F s/n 24010.

Removed Narco VHF-3 Superhomer and antenna,  Installed Genavo A200A Nav. Comm and ARC A-15 antenna.  Work accomplished in accordance with AC 43.13-2 chap. 2 and 3.  Weight and balance computed.

Fabricated spark plug bushings to replace pulled out heli-coil and threads from Franklin 6A8-215-B9F s/24010 engine.  Bushings fabricated from aluminum bronze conforming to ASTM spec. B-148(9c).  Center spark plug hole is standard 14 mm tapped hole.  Outside diameter machined .003 larger than 3/4"-16 NF hole which is tapped into cylinder head.  A 1/8" hole was drilled into bushing and cylinder head and a 1/8" brass shear rod was installed.  On installation the bushings were chilled and screwed into the cyl. head dry.

Replaced damaged skin on underneath of Hull as illustrated (27" from step and forward).

1. Patch (1) piece same as original material full width.
2. Splice pattern as shown in 43:13-1A Page 50-Par 97 and 100-b.
3. Rivet count taken from 43:13-A figure 2.18.

1. Installed STS Loran-C110 in instrument panel radio rack (Station 40.5).  Installation is in accordance with STS instructions and AC 43.13-2A, Chapter 2, Para. 23e and Fig. 2-2.
   
2. Installed antenna on top of cabin at Station 69.5 in accordance with AC 43.13-2A Chapter 3, Para. 38b, Fig. 3.5.
   
3. Electrical power was supplied from a 3A circuit breaker.
   
4. The Loran-C was installed as supplemental equipment in a "stand alone" configuration, to be used for VFR flight only.
   
5. The instrument panel was placarded "Loran-C not certified for IFR".
   
6. Performed electrical load analysis and maximum continuous electrical load was 17.6 amperes, which does not exceed 80% of the generator capacity (35A).
   
7. All work was performed using instructions furnished with the Loran-C, AC20-121A guidelines, and the applicable provisions of AC 43.13-1A, Chapters 11 and 15, and AC 43.13-2A, Chapters 2 and 3.
   
8. Compass checked for deviation, equipment list revised, and new weight and balance data entered in the aircraft records.

03 June 1995; A test flight was performed to insure that the Loran-C equipment is not a source of objectional electromagnetic interference (EMI), does not interfere with the normal operation of other equipment installed in the aircraft, is functioning properly and safely, and operates in accordance with the manufacturers specifications.

Repair was made on the aft cabin skin reinforcement gussets (SB#48) that support the lower hat channels and skin.  On the right side, the bottom rivets were replaced with cherry max rivets, CR3243-5-6 & CR3243-5-5 according to the thickness of skins, using existing holes.  Extra rivets were also used to strengthen upper skin to hat channels.  Cherry max rivets CR3243-4-3, CR3243-4-5.  On the left side cherry max rivets CR3243-4-3 & CR3243-5-4 were installed where some were missing using the same holes and adding extra rivets for reinforcing.

All work accomplished as per AC 43-12-1B pg 4-39 - table 4-9, rivet spacing, pg 4-20 - fig 4-5 rivet spacing & edge distance, pg 4-24 - fig 4-9 cherry max rivets.  And FAR 43:13, paragraph 9 (a), (b) & (c).  Log book entry made.

Price: $35,000 Call Les Christianson at 561) 866 6083 or (561) 241-7324

Per Otto Leth-Olsen
Fagerneset 57
NO-7057 Jonsvatnet
Norway 

Tel: 73 83 98 34 / 951 54 396
e-mail: perottle@online.no