| First Flight (NA-49): | Sept. 28, 1938 |
|---|---|
| Span: | 42 feet 1/4 inch |
| Length: | 28 feet 11-7/8 inches |
| Seating: | Tandem |
| Power plant: | Pratt & Whitney Wasp R-1340-AN-1 550 horsepower (later uprated), air-cooled |
| Speed: | 205 mph at 5,000 feet |
| Crew: | Pilot, co-pilot |
| Landing gear: | Retractable |
| Propeller: | Controllable pitch |
For those that don’t know what a Type Certificate is, it is what an IA has to refer to at every annual to make sure the plane is as it is supposed to be. There are type certificates data sheet ( TCDS) for the Airframe, Engine and Propeller, and all have to be consulted. I have found incorrect Mags, Carbs, and even an incorrect engine because of reading the TCDS for the plane I was inspecting at the time, if you want to look them up on your own, try here http://www.airweb.faa.gov/Regulatory_an … frameset Every plane except experimental has a TCDS, so you could look at one for a T6-Harvard to a 747, it is on there. Here are the TCDS for the T-6.
Manufacturer Rockwell International Corporation, 2201 Seal Beach Boulevard, Seal Beach, CA 90740-8250
I – Model BC-1A, AT-6 (Navy SNJ-2), 2 PCLM, Approved November 6, 1946
Engine Pratt & Whitney Military model R-1340-47, R-1340-49, R-1340-AN-1 or R-1340-36
Fuel 87 min. grade aviation gasoline
Engine limits Maximum continuous, (Sea level) 34.0 in.Hg., 2200 rpm (550 hp) (5000 ft.) 32.5 in.Hg., 2200 rpm (550 hp)
Takeoff (one minute), 36.0 in.Hg., 2250 rpm (600 hp)
Airspeed limits Level flight or climbs 189 mph (164 knots) True Ind.
Glide or dive 226 mph (197 knots) True Ind.
Flaps extended 111 mph ( 97 knots) True Ind.
C.G. range (+27.3) to (+31.2) with landing gear extended.
Empty weight C.G. range None
Maximum weight 5340 lbs. (See NOTE 3 for crop dusters) No. seats 2 (+45 and +97) (See Items 408 and 409 for 3 or 4-place)
Maximum baggage 100 lbs. (+126)
Fuel capacity 170 gals. (+37) (One integral tank in wing centre section with dividing partition)
Oil capacity 15.5 gals. ( – 8 )
Control surface movements Wing flaps Down 41ยฐ
Elevators Up 30ยฐ Down 20ยฐ
Elevator trim tabs Up 6ยฐ Down 17ยฐ
Ailerons Up 30ยฐ Down 16ยฐ
Aileron balance tabs Up 13ยฐ Down 27ยฐ
Rudder Right 35ยฐ Left 35ยฐ
Rudder trim tab Right 4ยฐ Left 10ยฐ
Note: Aileron balance tabs may be used in fixed positions as trim tabs. When rudder and aileron control systems are modified pr North American Dwg. 88-05016, pertinent control surface movements are as follows:
Ailerons Up 14ยฐ Down 16ยฐ
Rudder Left 30ยฐ Right 30ยฐ
Serial Nos. eligible All manufacturer’s serial Nos. 55-1548 through 55-1630, 59-1631 through 59-1639, and 59-1906 through 59-1990. The manufacturer’s serial number will be found stamped on the same identification plate with Army or Navy serial number.) Harvard I aircraft manufactured in the United States: Manufacturer’s serial Nos. 49-748 through 49-947, 49-1053 through 49-1252 (See NOTE 4).
I – Model BC-1A, AT-6 (contโd) Required equipment In addition to the pertinent required basic equipment specified in CAR 4a, the following
items of equipment must be installed:
Items 1, 2, 101, 103, 104, 105, 109, 111, 201(a) or (b), 202(a) or (b), 203(a) or (b), 301(a), 405(a), (b) or (c), 406(a) or (b), 407, 602. Aluminium alloy outer wing panels and aft fuselage section are required.
II – Model AT-6A (Navy SNJ-3), AT-6B, AT-6C (Navy SNJ-4), AT-6D (Navy SNJ-5), AT-6F (Navy SNJ-6), Navy SNJ-7, T-6G; 2 PCLM, Approved February 1, 1946
Engine Pratt & Whitney Military model R-1340-47, R-1340-49, R-1340-AN-1 or R-1340-36
Fuel 87 min. grade aviation gasoline
Engine limits Maximum continuous,
(Sea level) 34.0 in.Hg., 2200 rpm (550 hp)
(5000 ft.) 32.5 in.Hg., 2200 rpm (550 hp)
Takeoff (one minute),
36.0 in.Hg., 2250 rpm (600 hp)
Airspeed limits Level flight or climb 189 mph (164 knots) True Ind.
Glide or dive 226 mph (197 knots) True Ind.
Flaps extended 115 mph ( 97 knots) True Ind.
C.G. range (+27.5) to (+32.5) with landing gear extended.
Empty weight C.G. range None
Maximum weight 5300 lbs.
No. seats 2 (+45 and +97) (See Items 408 and 409 for 3 or 4-place)
Maximum baggage 100 lbs. (+126)
Fuel capacity 111 gals. (+36) (Two 55.5 gal. tanks in wing centre section)
(20 gals. reserve included in 55.5 gals. the capacity of the left tank)
Note: In addition to the above, Models T-6G incorporate an additional 29 gals. (+50).
(Two internal bladder cells in outer wing panel, 14.5 gals. each side).
Oil capacity 10 gals. ( -9 )
Control surface movements Wing flaps Down 45ยฐ
Elevators Up 30ยฐ Down 20ยฐ
Elevator trim tabs Up 8ยฐ Down 16ยฐ
Ailerons Up 29ยฐ Down 16ยฐ
Aileron balance tabs Up 15ยฐ Down 30ยฐ
Rudder Right 35ยฐ Left 35ยฐ
Rudder trim tab Right 4ยฐ Left 10ยฐ
Note: Aileron balance tabs may be used in fixed positions as trim tabs. On some of the
models AT-6C and on all of the models AT-6D, AT-6F and T-6G the rudder and
aileron control systems have been modified per North American Dwg. 88-05016. The
pertinent control surface movements for these aircraft are as follows:
Ailerons Up 14ยฐ Down 16ยฐ
Rudder Right 30ยฐ Left 30ยฐ
Serial Nos. eligible All serial numbers of aircraft models covered by this section. (Manufacturer’s serial
number will be found stamped on same identification plate with the military serial number.) Harvard II aircraft manufactured in the United States:
Manufacturer’s serial Nos. 66-2234 through 66-2833, 75-3048 through 75-3057, 75-3418 through 75-3507, 76-3508 through 76-3957, 81-4008 through 81-4132. (See NOTE 4).
Required equipment In addition to the pertinent required basic equipment specified in CAR 4a, the following
items of equipment must be installed: Items 1, 2, 101, 103, 104, 105, 109, 111, 201(a) or (b), 202(a) or (b), 203(a) or (b),
301(a), 405(a), (b) or (c), 406(a) or (b), 407, 602. Aluminium alloy outer wing panels and aft fuselage section are required.
Datum Leading edge of wing centre section
Levelling means Lugs left side rear cockpit
Certification basis Airworthiness Certificate only (CAR 4a)
Export eligibility Eligible for export to all countries subject to the provisions of MOP 2-4 except as
follows:
(Note: Export license from State Department may be required) Canada – Landplane, eligible Skiplane, not eligible
Equipment: A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed.
Propeller and Propeller Accessories
1. Propeller – Hamilton Standard, constant speed hub 12D40, 175 lbs. (-57) blades 6101-12 to -14, incl. Dia.: Max. 9’1″, Min. allowable for repairs 8’10-5/8″. No further reduction permitted. Pitch settings at 42 in. sta.: 11.5ยฐ low, 27ยฐ high Following placard required: (With blade models 6101-12 and -13),
“Avoid ground operation between 1280 and 1800 RPM unless the aircraft is headed into the wind.” (With blade model 6101-14),
“Avoid ground operation between 1450 and 1800 RPM unless the aircraft is headed into the wind.”
2. Constant speed governor, Ham. Std. 1M12-A, -G, or 1P12-A 5 lbs. (-50)
3. Propeller spinner (Montgomery) Part No. 42J15621 for 12 lbs. (-57) Hamilton Standard propeller
Engine and Engine Accessories – Fuel and Oil System
101. Carburetor air heater
102. Air filter, Air Maze 3 lbs. (-23)
103. Engine-driven fuel pump (Army Type B-21 or F-10) 1 lb. (-30)
104. Wobble pump and strainer (Army Type D-3) 12 lbs. (+16)
105. Oil temperature regulator (8″ dia. radiator) 21 lbs. ( -9)
106. Oil diluation system 3 lbs. ( +2)
107. Exhaust gas analyzer 5 lbs. (+20)
108. Engine-driven vacuum pump (Pesco Type B-12) 6 lbs. (-26)
109. Engine-driven hydraulic pump (Pesco 1P-263-E)
110. Starter
(a) 12 volt (Eclipse type C-20 or H-2) 33 lbs. (-19)
111. Cylinder head temperature gages (See NOTE 2(k) for markings)
Landing Gear and Floats
201. Main wheels, tires and tubes
(a) 27″ smooth contour wheels and brakes (AC-25258 or Hayes 131 lbs. (+10)
Model 2750A) with 6-ply tires
(b) 27″ smooth contour wheels and brakes (AN-W-6 or Hayes 136 lbs. (+10)
Model 2750A) with 8-ply tires
202. Tailwheel, tire and tube
(a) 10″ smooth contour wheel with 6-ply tire 6 lbs. (+234)
(b) 12.5″ smooth contour wheel with 6-ply tire 10 lbs. (+234)
203. Tailwheel gear (less wheel, tire and tube)
(a) Steerable 26 lbs. (+230)
(b) Free swivel with lock 26 lbs. (+230)
Electrical Equipment (24-volt electrical system may be substituted for 12-volt system per North American Dwg. 121-954004)
301. Battery and case
(a) 12 volt – 68 amp. hr. (5 hr. rate) (Exide 6-TAS-17) 71 lbs. ( -1)
302. Generator
(a) 12 volt – 50 amp. (Leece-Neville E-5A) 32 lbs. (-26)
303. Landing lights 3 lbs. (+21)
304. Radio installations
(a) Antenna and mast 7 lbs. (+29)
(b) Marker beacon receiver and antenna 5 lbs. (+63)
(c) Radio compass and loop 42 lbs. (+14)
305. Interphone 10 lbs. (+62)
306. Electric heated pitot 1 lb. ( +7)
Interior Equipment
401. Fire extinguisher and bracket 7 lbs. (+101)
402. Cabin heater and ventilator 17 lbs. ( -1 8 )
403. Oxygen system
(a) High pressure 30 lbs. (+136)
(b) Low pressure 29 lbs. (+116)
404. Provisions for 90 lbs. of photographic equipment at (+113)
405. Front seat
(a) Dural 8 lbs. (+52)
(b) Wood 12 lbs. (+52)
(c) Magnesium (Warren McArthur or Shick-Johnson) 8 lbs. (+52)
406. Rear seat
(a) Swivel type 28 lbs. (+101)
(b) Dural 8 lbs. (+101)
407. Safety belts, A-3,B-11, B-12, or B14
408. Two-place rear seat installation (Vent Aircraft & Finance Co., 4600 Dehlia St., Hayden Field,
Denver, Colo.) Seat kits to be installed in accordance with the manufacturer’s installation instructions dated October 9, 1946.
409. “Air Tandem” Three passenger seat kit (Ralph R. Richardson, Route 1, Box 303, Port Orchard, Washington). Installation must be made per the manufacturer’s dwgs. and instructions as listed in Detail Folder No. RC-2 consisting of Pages 1, 1a, 1b, 2 thru 9
and three pages of Installation Instructions. Miscellaneous (Not listed above)
601. Blind flying hood 4 lbs. (+105)
602. Control surface tabs, dural or wood
603. Mooring kit 11 lbs. (+140)
604. Engine cover 15 lbs. (+140)
605 Wood horizontal stabilizer -3 lbs. (+222)
NOTE 1. Current weight and balance report including a list of equipment included in certificated empty weight must be in each aircraft at the time of original certification and at all times thereafter. If removable ballast is used to stay within the specified forward limit, the following placard must be installed on the instrument panel and baggage compartment: “When flown solo lbs. of baggage or equivalent must be carried in the baggage compartment.”
NOTE 2. The following must be accomplished prior to the original certification of the aircraft:
(a) Aircraft must have aluminium alloy wing outer panels and fuselage aft sections.
(b) Placard rear cockpit, “Solo Flying From Front Seat Only.”
(c) Placard both cockpits, “Intentional Spinning Prohibited” and “Caution: Unless Left Tank is Full, use
reserve or Right Tank for Take-off and Landing.”
(d) Placard baggage compartment: “Maximum Capacity 100 lbs. With Both Seats Occupied lbs. Maximum” The latter weight to be determined per NOTE 1, the limiting factor being the rearward centre of gravity.
(e) Mark fuel tank filler caps, “Fuel capacity gal., 87 min. oct.”
(f) Mark oil tank filler cap, “Oil capacity gal.”
(g) Mark instruments for approved operating limits.
(h) Provide an oil measuring stick for the oil tank.
(i) For day operation, electrical protective devices in circuits to all equipment used in such operation should be
accessible to the pilot in flight. The aeroplane should then be restricted to day operation.
(j) In order for these aircraft to be eligible for night operation, it will be necessary that the following changes
be made:
1. Remove the present red and green wing position lights and cover the mounting holes with aluminium alloy
plates. Install Grimes Model E wing-tip position lights and connect them into the present position light junction boxes located near the wingtips. Also, remove the present two rear position lights from the fin and replace them with either Grimes lights No. A-4060 or Grimes lights A-2063 modified specifically by Grimes for use on these aeroplanes. Either type of lights should have 15 candlepower lamps installed.
2. Remove position light resistors and eliminate the work “Dim” at the position light switch.
3. Relocate all electrical circuit protectors so that they are accessible to the pilot in flight.
(k) The cylinder head temperature gauge is marked to indicate a limiting temperature of 500ยฐF.
(l) On models BC-1A, AT-6 and SNJ-2 only, inspect fuel tank to determine whether gasoline can flow from
one compartment into the other. If so, the following placard should be placed adjacent to the fuel selector
valve: “Refer to both fuel gauges to determine remaining fuel.”
(m) Add the following information to the engine nameplate: “C.A.A. Spec. No.5E-2.”
(n) Fixed ballast not to exceed 33 lbs. may be installed at Station 240 to prevent exceeding the forward centre
of gravity limit. Ballast weight installation must be approved and is to be placarded, “Removal requires
weight and balance check.”
(o) On Model T-6G determine that the centre wing flap is in the operative configuration. NOTE 3. Model AT-6 series aircraft certificated in the restricted category prior to October 11, 1950, for crop dusting may continue to be operated with the following limitations:
(a) Maximum takeoff weight 5870 lbs. 5830 lbs. Maximum landing weight 5340 lbs. 5300 lbs. Manoeuvring speed at maximum weight 151 mph 151 mph
(b) The following placard must be in full view of the pilot: “Manoeuvring speed at a maximum weight not to exceed 151 mph.”
Each aircraft certificated on the above basis must be subjected to a flight test to determine that the installed duster apparatus has no adverse effect on the flight characteristics of the aircraft. In the case of identical duster installations in aircraft of the same model, the flight test need only be made to the prototype. All original certification in the restricted category after October 11, 1950, must be in accordance with CAR and CAM 8.
NOTE 4. Prior to civil certification, it must be ascertained that Harvard aircraft manufactured in the United States
conform to the type design. Some of the known deviations from the original configuration are discussed as
follows:
(a) The mixture control must be reworked to the standard American system, that is “lean-aft, Rich-forward”.
A conversion to the exact AT-6 system would be acceptable. Any other system would have to be evaluated.
(b) The long exhaust stack configuration should be modified to the AT-6 system.
The utilisation of winterised stack would require evaluation with respect to:
(1) Carbon monoxide content in the cockpit from both the fresh air system, heat exchanger within the stack and the stack proper.
(2) Detrimental temperature effects on the fuselage skin due to the proximity of the stack to the fuselage as well as possible adverse exhaust backpressure.
(3) Determination that the system was the United States manufactured inasmuch as a foreign-built unit would not
be eligible for approval.
A-2-575 6
(c) The use of Pratt & Whitney S3H1 engine is acceptable with Item 1 propeller.
(d) The acceptability of engine accessories must be determined. In this regard, Technical Order 00-25-29 “Maintenance Interchangeability Cross Reference Charts” may be utilised as a guide.
(e) The use of foreign manufactured landing gear is not considered acceptable, and therefore must be
replaced by an acceptable gear manufactured in the United States.
(f) The landing gear fairing and associated attachment hardware must be installed.
(g) The forward control stick has a four inch hand grip which differs from the standard straight stick
installation. If clearance from the structure appears adequate this may be considered acceptable.
(h) Electrical system deviations from the approved type design data must be appropriately changed and adjusted satisfactorily.
(i) Airspeed flap speed and cylinder head gage limits must be incorporated as in the AT-6 aircraft. Other existing difference must be satisfactorily resolved with the local FAA Engineering Office prior to certification.