T-6 T.O. for fixed center flap

[Stoney]

Anybody know where I can get a copy?

[A2C]

I'll check.

[51fixer]

Anybody know where I can get a copy?

I have the T-6G prints.
If I have some time soon I can check.
If you happen to have a G model book you can look it up and let me know P/Ns.
Mine is at the printers having a copy made.
Rich

[skymstr02]

If the airplane is a T-6G and in standard category, a center flap is required to be operable IAW Aircraft Specification A-2-575 (TCDS) Note 2 (o). You would have to have an STC or field approval to restrict the center flap operation.

If the airplane is experimental, nevermind.

[A2C]

If the airplane is a T-6G and in standard category, a center flap is required to be operable IAW Aircraft Specification A-2-575 (TCDS) Note 2 (o). You would have to have an STC or field approval to restrict the center flap operation.

If the airplane is experimental, nevermind.

What if you bought a registered T-6G with the flap change done while in military service? The Type Certificate does not specify this as being necessary or unnecessary. By ambiguity no field approval would be required. The conclusion in my opinion is no field approval is required by ambiguity. Due to the fact that the type certificate for the G model could've meant an aircraft with the inoperative center flap.

[stumac]

I will send it up to you Stoney. I'll get it out Monday.

[skymstr02]

What if you bought a registered T-6G with the flap change done while in military service? The Type Certificate does not specify this as being necessary or unnecessary. By ambiguity no field approval would be required. The conclusion in my opinion is no field approval is required by ambiguity. Due to the fact that the type certificate for the G model could've meant an aircraft with the inoperative center flap.

Yes, please read the type certificate, on a T-6G, the center flap must be operational. This is spelled out in Note 2, para (o). Its in black and white. If you bought a military surplus T-6G with the flap change, you must return it to its original unmodified condition prior to civil certification. When the mechanic performs the conformity inspection, and when the IA performs the annual inspections, it is in reference to the TCDS.
For a civil registered aircraft, the type certificate trumps any military modification.
For instance, some AT-6's/SNJ's had wooden outer wing panels. These are prohibited on civil registered aircraft per the TCDS.

[RMAllnutt]

some AT-6's/SNJ's had wooden outer wing panels.

Wow! I never knew that! Do any still survive?

Cheers,
Richard

[Matt Gunsch]

some AT-6's/SNJ's had wooden outer wing panels.

Wow! I never knew that! Do any still survive?

Cheers,
Richard

and a wooden tail cone.
For those that don't know what a Type Certificate is, it is what a 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 a 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 ... enFrameSet

Every plane except experimentals has a TCDS, so you could look at one for a T-craft to a 747, it is on there.

Here is the TCDS for the T-6.

AIRCRAFT SPECIFICATION NO. A-2-575
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 climb 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 center section with dividing partition)
Oil capacity 15.5 gals. ( - 8 )
Control surface movements Wing flaps Down 41°
Elevators Up 30° Down 20°
Elevator trim tabs Up 6° Down 17°
Ailerons Up 30° Down 16°
Aileron balance tabs Up 13° Down 27°
Rudder Right 35° Left 35°
Rudder trim tab Right 4° Left 10°
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 14° Down 16°
Rudder Left 30° Right 30°
Serial Nos. eligible All manufacturer's serial Nos. 55-1548 through 55-1630, 59-1631 through 59-1639, and
59-1906 through 59-1990. Manufacturer's serial number will be found stamped on
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).
A-2-575 2
I - Model BC-1A, AT-6 (cont’d)
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. Aluminum 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 centersection)
(20 gal. reserve included in 55.5 gal. capacity of 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 45°
Elevators Up 30° Down 20°
Elevator trim tabs Up 8° Down 16°
Ailerons Up 29° Down 16°
Aileron balance tabs Up 15° Down 30°
Rudder Right 35° Left 35°
Rudder trim tab Right 4° Left 10°
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 14° Down 16°
Rudder Right 30° Left 30°
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. Aluminum alloy outer wing panels
and aft fuselage section are required.
3 A-2-575
SPECIFICATIONS PERTINENT TO ALL MODELS
Datum Leading edge of wing centersection
Leveling 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.: 11.5° low, 27° 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. Tail wheel, 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. Tail wheel gear (less wheel, tire and tube)
(a) Steerable 26 lbs. (+230)
(b) Free swivel with lock 26 lbs. (+230)
A-2-575 4
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 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 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 instrument panel and
baggage compartment: "When flown solo lbs. of baggage or equivalent must be carried in baggage
compartment."
NOTE 2. The following must be accomplished prior to original certification of the aircraft:
(a) Aircraft must have aluminum 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 center of gravity.
(e) Mark fuel tank filler caps, "Fuel capacity gal., 87 min. oct."
(f) Mark oil tank filler cap, "Oil capacity gal."
5 A-2-575
(g) Mark instruments for approved operating limits.
(h) Provide oil measuring stick for 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 airplane 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 aluminum alloy
plates. Install Grimes Model E wing-tip position lights and connect them into the present position light
junction boxes located near the wing tips. 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 airplanes. 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 be marked to indicate a limiting temperature of 500°F.
(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 center
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 center 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:
AT-6 AT-6A, 6B, 6C
(a) Maximum takeoff weight 5870 lbs. 5830 lbs.
Maximum landing weight 5340 lbs. 5300 lbs.
Maneuvering speed at maximum weight 151 mph 151 mph
(b) The following placard must be in full view of the pilot:
"Maneuvering speed at 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 standard American system, that is "lean-aft, Rich-forward".
A conversion to 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.
Utilization of winterized 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 back pressure.
(3) Determination that system was 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 utilized as a guide.
(e) The use of a 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.
......END......

[snj-5]

I wasn't aware that the T-6 was ever built with wood wings....(???).
Wood tailcones, wood horizontal stabs, wood seats yes, but were
there any ever really built with wood wings?

Bela P. Havasreti

[bdk]

I wasn't aware that the T-6 was ever built with wood wings....(???).
Wood tailcones, wood horizontal stabs, wood seats yes, but were
there any ever really built with wood wings?

I'd sure like to see how they worked out the attach angles!

[Jack Cook]

and how many are flying with the center flap locked up???
I can name 10 off the top of my head

[A2C]

I'd sure like to see how they worked out the attach angles!

Wood Screws.. and nails

[Obergrafeter]

And glue and duct tape!

[skymstr02]

and how many are flying with the center flap locked up???
I can name 10 off the top of my head

T-6G's, or other variants?