Various
337s for Globe/Temco GC Series produced under Type Certificate
A-766
This listing is not complete and may contain out-of-date information,
particularly in regards to the name/address of the 337 holder.
Additional information may be obtained by
contacting the 337 holder. This listing is for information
only.
The Swift Museum Foundation, Inc. and it's webmaster are not
responsible for the content or accuracy of the following information.
AVIONICS,
INSTRUMENTS and SYSTEMS
WINDSHEILDS
ENGINES,
PROPS, COWLINGS, & SPINNERS, ETC.
LANDING
GEAR
AIRFRAME
FUEL
SYSTEM
MISCELLANEOUS
Turn Coordinator:
Installed Electric Gyro Coorporation turn coordinator model
No. 1384T100 7S, s/n 6309327 per AC 43.13-2A, Chapter 11 and
Cessna Aircraft drawing No. 057010, for C-172. 20 January
1997. Contact: Gerald P.
Mahoney
GPS Antenna: Installed
Comant Industries GPS antenna, Model No. 405-30C, TSO C 129
per Comant drawing A010038. Antenna installed on upper surface
of boot cowl, 14" aft of firewall. 10 January 1997. Contact:
Gerald P. Mahoney
Encoder: Install
encoder model # ACK A30, s/n39741, wire to transponder as
necessary. check correspondence to verify accuracy. Weight
and Balance negligible. 22 July, 1992. Contact: Gerald
P. Mahoney
CHT/EGT Scanner:
Remove old CHT gage. Install J.P. Instruments CHT/EGT scanner
per STC SA2586NM, Revision number 2, dated 7-22-86. Inst p/n
100-4, s/n 3368 mfg. 1-1-92. 17 October 1992. Contact: Gerald
P. Mahoney
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"Bubble" Windshield: Installed GC-1-3 heavy
duty "Bubble" windshield per STC SA$-403WE. No change
to C.G. 26 September 1991. Contact: Gerald
P. Mahoney
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Bracket Airfilter: Bracket airfilter installed per
STC SA71GL. Field approval for BA731D filter required as Globe
Swift is not on STC. 24 September 1991. Contact: Gerald
P. Mahoney
Cont O-300-C: Installed Continental O-300-C in accordance
with STC SA1-326 with the following changes: (1) Installed
Sensenich Propellor Model M74DC-0-59. The Sensenich 74DC series
propellor (TC No. P-886) is equivalent to the McCauley 1A170DM
series (TC No. P-857)except for the propellor flange. The
same power and RPM limits apply per STC. No RPM limits to
the propellor/engine combination other than thoselisted in
the STC. (2) Compute new C.G. and enter on weight and balance
form and in log book. (3) Installed O-300-C in lieu of O-300-A.
Minor engine differences noted in type certificate data sheet
no. E-253. 13 May 1986. contact: Gerald
P. Mahoney
Lycoming O-360: Installed Lycoming O-360 A1D engine,
accessories, and Hartzell HC-C2YK-1BF/F7666 A2 propeller per
STC SA 275 NW. STC SA 275 NW approval installation of the
Lycoming IO-360, 200hpengine on this airframe. Oil cooler
located on right side of firewall per STC SA1680WE on Globe
Swift N80772. Additional placard required: "Aviod continuous
operation between 2000-2250 RPM." Aircraft weighed and
equipment list revised. Instrument markings: (A) Tachometer
- 2700 rpm radial red line. (B) cylinder head temp - 260 degrees
C radial red line (C) Oil tem gauge - 118 degrees C radial
red line (D) Fuel press gauge - Normal range 3 - 6 psi green
arc. Minimum range .5 psi radial red line. Maximum range 8
psi radial red line. (E) Oil press gauge - Normal range 60-90
psi green arc. Minimum range 25 psi radial red line. Maximum
range 100 psi radial red line. 26 September 1991. Contact:
Gerald P. Mahoney
Engine Mount for O-360 Lyc: Installed Serv-Aero engineering
engine mount, serial No. 133, for Lycoming O-360/IO-360 engines.
Mount manufactured per Serv-Aero dwg. no. 1073 (rev. B) -
load limit factor 4.8. Load limit ultimate = 7.2 (4.8 x 1.5)
Mount static test report no. 23, 24 January 1985 applies.
26 September 1991 Contact: Gerald
P. Mahoney
Alternator: Installed Inter-AV Alternator model no.
1255A in accordance with STC SA334SW. Equipment list revised,
and weight and balance recomputed. 18 September 1991 Contact:
Gerald P. Mahoney
High Torque Starter: Installed B&C Specialty Products
Starter. P/N BC315-100-1 in accordance with STC SE2390CE,
and AC43.13-1A-3, chap. 11. Weight - 10.2 lbs. Revised equipment
list and weight and balance re-computed. 18 September 1991
Contact: Gerald P. Mahoney
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Vertical Stabilizer Beef-up: Installed doubler on
lower 13 inches of trailing edge spar of vertical stabilizer.
Work accomplished per AC43.13-1A-3, chapt.2, sec.3, para.
96D, 97a, and 99 B 7 c, 100 bc&g, 101 a&b, fig 2.19
and fig. 2.32, per Swift museum foundation dwg. no. 11-120-3376A.
Contact: Gerald P. Mahoney
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Wingtip Strobe Lights: Installed aeroflash wingtip
strobes p/n 156-0003. The power supplies and lamps are located
in the wingtips. This strobe light system approved at anti-collision
lights as required by FAA 23.1401, and 91.33 (c) as ammended
by Federal docket 10129, dated 10 July 1971. FAA PMA in compliance
with standards of FAR part 21, sec. 21.303 has been granted.
These units installed per AC43.13-1A-3 chapt. 2, AC43.13-2A,
chpat. 2 & 4, and AC20-30A. Ammended equipment list and
re-computed weight and balance. 26 September 1991 Contact:
Gerald P. Mahoney
Cessna 150 Seats: Cessna 150 seats installed. Cessna
seat rails and hardware were used. The seat belt attach points
were unchanged and the load supporting seat rails were attached
to the same floor area that the original seats were. Ref.
AC43.13-1A-3, chapt. 8, sec.3, para 361, chapt. 5, sec. 1,
para 227, chapt. 13, para. 656 & 662 and AC43.13-2A chapt.
1, para. 1 & 2. Ammended equipment list and re-computed
weight and balance. 26 September 1991 Contact: Gerald
P. Mahoney
Left Cockpit Sidewall Throttle Tuadrant: Relocated
throttle and propeller RPM control to left side of cockit
using mil-spec Corry-Penna throttle quadrant. Quadrant installed
via AN3-5A bolts and 2024 T3x.040 plateinstalled with MS20470
AS 3-4 rivets between FS27 and FS36. Installation complies
with AC43.13-1A-3 ch.1, sec.3, and AC43.13-2A ch.1. 18 September
1991 Contact: Gerald P.
Mahoney
Battery Relocation:
Relocated battery to aft fuselage between FS105 and FS125.
Original battery mount brackets and box used in instalation
STC SA1680WE, drawing no. 11 applies. All structural fabrication
is in accordance with AC 43.13-2A ch. 3 chapt. 10, sec.1 para.177
sec.2, para. 186, 187, 188, 189, and STC SA1680WE for Globe
Swift N80772. Battery installed forward of location listed
in STC due to difference in aircraft weight. Battery relay
located on battery box with ground to airframe. Number 2 wire
selected to starter relay and starter in accordance with ch.11
sec.2. Loads computed in accordance with ch.1, para. 2, and
static tested in accordance with para. 3, FAR 23, (CAR-3)
limits apply. Computed new C.G. and entered in aircraft records.
18 September 1991 Contact: Gerald
P. Mahoney
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