I have two MK8 MOD 1 airplane auxiliary fuel tanks. Would any of you guys know what type or model of plane they would have been use on. Tried google but can't come up with anything.

They hold it looks like several hundreds of gallons of fuel.

Are there any other numbers, such as manufacture dates?

Are you planning on building one of these?

Mark
Tell us a little more about that buggy!

Here is the link:
http://www.popularmechanics.com/home_journal/workshop/4219198.html

Here's proof that green design can be kick-butt cool. Retired mechanic Robert Lange of Kelseyville, Calif., transformed the fuel tank from an F-4 jet into this three-wheeled dragster. Four motorcycle batteries power the 225-pound vehicle that, says Lange, "handles like a go-kart and moves like a rocket ship." Lange started building electric vehicles in the late 1960s — a racing bar stool was an early effort — and began powering them using solar panels in 1983. Now, his entire shop runs on solar power. "I don't like to pollute the atmosphere with my hobby," he says.

Hey P Dog, your drop tanks go to a Grumman Albatross. PM me an email addy and I'll send you a type certificate data sheet on it.

You could do a lookup on all the Albatrosses in the FAA database, these tanks may be worth some money to the right person looking to restore a plane.

Mark thanks for the info I would like to sell them to some one who could use them well pm a email address to you

I'll send it later, I think I also just figured out how to convert a PDF and paste:


TYPE CERTIFICATE DATA SHEET NO. A2GL
This data sheet which is part of type certificate No. A2GL prescribes conditions and limitations under which the product for
which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.
Type Certificate Holder Trans American Air Transport, Inc.
P.O. Box 66155
O'Hare International Airport
Chicago, Illinois 60666
I - Grumman Model HU-16B (Restricted Category) approved June 20, 1978
Engines 2 Wright R1820-76B or R1820-76D
Fuel 100/130 minimum grade aviation gasoline
MP
Engine limits Low Impeller Ratio HP RPM in. HG ALT. FT.
Takeoff (five min.) 1425 2700 51.5 Sea Level
Takeoff (five min.) 1425 2700 50.5 2,600
Minimum Continuous 1275 2500 46.5 Sea Level
Maximum Continuous 1275 2500 45.5 3,500
High Impeller Ratio
Maximum Continuous 975 2500 42.0 18,300
Maximum Continuous 975 2500 43.5 12,000
Straight line variation between points given
Propeller and 3 blade Hamilton standard hydromatic constant speed full feathering
propeller limits and reversible with integral oil system.
Hub Model No. Blade No.
43D50-( ) 6601-( )
Pitch settings at the 42 in. station:
Low 16°
Feather 89°
Reverse -12°
Diameter
Maximum 132.00 in.
Minimum 129.36 in.


A2GL 2
Airspeed limits Vne (Never exceed) 254 KIAS
In severely turbulent air 110 - 130 KIAS
Full Aileron deflection 208 KIAS
Full Rudder deflection 150 KIAS
Landing gear extending 150 KIAS
With landing gear extended 150 KIAS
With landing lights extended 120 KIAS
Flaps 15° down 243 KIAS
Flaps 30° down 163 KIAS
Flaps full down 40° design limit 140 KIAS
De-icer boot operation 175 KIAS
C.G. range 294.4" (20.5% MAC) to 304" (28% MAC).
Datum 71.5" forward of nose jack pad.
Leveling means Leveled laterally by leveling lugs located in the nose wheel and longitudinally by a plum
bob drop from the small hole located in the shelf of either wheel well.
Maximum weight 32,000 lbs.
Minimum crew 1 (pilot) - See Note 5 Day VFR
2 (pilot & Copilot) IFR, Night VFR
2 (pilot & competent observer) All water operations
No. of seats 2 Pilot and Copilot (+154.")
1 crew (+187.")
1 crew (+238.")
1 crew (+252.")
1 crew (+279.")
1 crew (+306.")
3 crew (+378.")
4 crew (+418.")
2 crew (+453.")
Fuel capacity Right and left main tanks 340 gal. (each) 2040 lbs. (+297.3")
Right float tank 209 gal. 1254 lbs. (+307.5")
Left float tank 212 gal. 1272 lbs. (+307.5")
Right and left drop tanks
MK8 MOD 0 295 gal. (each) 1770 lbs. (+295.0")
MK8 MOD 1 304 gal. (each) 1824 lbs. (+295.0")
Oil capacity Right and left tanks 25.6 gal. (each) ( 262.0")
Control surface movements Wing flaps Down 40° + 3°
Aileron tab Up 18° + 1° Down 12° + 1°
Aileron Up 17° + 1° Down 17° + 1°
Elevator tab Up 5° + 1° Down 12° + 1°
Elevator Up 30° + 1° Down 20° + 1°
Rudder tab Right 16° + 1° Left 26° + 1°
Rudder Right 20° + 1° Left 15° + 1°
Other operating limitations U.S.A.F. Flight Manual No. T.O. IU-16(H)B-1 dated December 1, 1967
Serial Nos. eligible Serial No. 51-5292 only.
Certification Basis FAR 21.25
Application for Type Certificate dated August 9, 1976. Type Certificate No. A2GL
issued June 20, 1978 for the special purpose of water photographic and salvage work.


3 A2GL
Production basis None
Equipment Basic required equipment as prescribed in the Basic Weight Check List Chart A
pages 1-9 dated December 10, 1978 and Chart E Sheets 1 & 2 dated September 30, 1978.
NOTE 1. Current weight and balance report including list of equipment in certificated empty weight and loading
instructions when necessary, must be in the aircraft at the time of original airworthiness certification and at all
times thereafter.
NOTE 2. The following placards must be prominently displayed in full view of the pilot:
Airspeed limits Vne (Never exceed) 254 KIAS
In severely turbulent air 110 - 130 KIAS
Full Aileron deflection 208 KIAS
Full Rudder deflection 150 KIAS
Landing gear extending 150 KIAS
With landing lights extended 120 KIAS
Flaps 15° down 243 KIAS
Flaps 30° down 163 KIAS
Flaps full down 40° design limit 140 KIAS
De-icer boot operation 175 KIAS
This airplane must be operated in accordance with U.S.A.F. Flight Manual TO. IU-16(H)B-1 dated
December 1, 1967. NOTE 3. Prior to civil airworthiness certification, the following must be accomplished:
(a) The provisions of U.S.A.F. T.O.'s
IU-16(H)-502, -524, and -530.
(b) An inspection of the engine support structures to verify their structural integrity.
(c) An inspection of the engine generator cables to verify their airworthiness.
(d) An eddy current inspection of the jack pad holes in accordance with U.S.A.F. T.O. IU- 16(H)B-513.
There must be no evidence of cracks or corrosion. This inspection must be performed subsequently
every 200 flight hours.
NOTE 4. The wing lower main beam spar caps are limited to 10,000 hours total time in service.
NOTE 5. Single pilot operation must be authorized in accordance with the provisions of FAR 91.213.