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[Cozy MKIV Information]
COZY MKIV FIRST EDITION PLANS
Plans S/N through 500
(Newsletters 34 - 84)
Table Of Contents
CHAPTER 2: Bill of Materials
- Remove 2" x 4" x .063 aluminum shown on Wicks material list.
- Page 1, Foam: Suppliers advises 4 sheets of 1/4" PVC foam
needed in Chapters 4, 13, and 14 is no longer available in the
sheet size shown. Replace foam with sheet sizes (29-1/2" x
43-1/4"), which can be shipped via UPS and FEDEX. The smaller
size provides enough material for the necessary parts and will
result in less waste.
- Page 1, Prefab Parts: The elevator torque tube offsets we
list as CZNC-12A may be listed by Brock as MKNC-12A.
- Page 1, Prefab Parts: The rudder pedals we list as CZRPLR
etc. may be listed by Brock as MKRPLR etc.
- Page 1, Prefab Parts: The elevator torque tubes (2 rights
req'd) are listed by Brock as NCTT-R.
- Page 1, Equipment, Tools & Supplies: Add (1) 3/4"
counter bore (needed in Chap. 8)
- Page 1: Change (1) Sheet 3/4" x 32" x 48' H45 PVC to (1.5)
Sheets 3/4" x 24" x 48" H45 PVC and make the same change Chap.
2, p. 3, foam needed in Chap. 4.
- Page 1, Wood: Change 1"x1"x1" to 1"x1"x12" Spruce. Also, you
may accept .75" instead of .7" for all of the Spruce
- Page 1, Prefab Parts: The torque tube sleeve NGT-63 is shown
in Chap. 13, p. 3 and in Brock catalog as NG-63.
- Page 2, and Page 4, (Chap. 13, hardware): Add (2) AN5268R14
screws for the nose gear crank bearing on the instrument
- Page 2, and Page 4, (Chap. 13, hardware): Add (2) AN5268R14
screws for the nose gear crank bearing on the instrument
- Page 2, Misc:
- Change FC100-2 to FC100 002.
- Change l"x6"xl0" 100 PVC to 6 Lb. Clark
- Change 3/4"x4"x48" 6 Lb. Clark to 4.5 Lb. Clark
- Change .7"x2"x18" spruce to .7"x2"x24"
- Change l"x l"x l" spruce to l"xl"x12" spruce
- Change 1/4" birch plywood to 6mm through out plans Chap.
2, page 2.
- Screws - add (2) AN526-832R14
- Washers - change (8) AN960-10 to (10)
- Washers - change (32) AN960-l0L to (62)
- Nuts - change (2) AN364-832 to (2) MS20364-832
- Nuts - change (1) AN365-524 to (1) MS20365-524
- Nuts - delete (2) AN526-832-14 _
- Nut plates - change (28) MS21047-3 to (31) MS21047-3
- Rivets - change BSP-43 to BSPQ-43
- Bar Stock - delete (1) 1/8"xl.5"x6" 2024T3
- Bar Stock - change (4) 7/16"x36" CRS to (2) 7/16"x72"
- Sheet Stock - change 1/4"x4"x9" 2024T3 to 1/4"x6"x8"
- Tubing - change 1/4"OD x .035W to 1/4"OD x .032W
- Tubing - add (1) pc. 5/8"0D x .058"x24" 4130 stl.
- Tubing - add (2) pcs. 3/4"OD x.058"x48" 6061T6 Alum.
- Misc. - change (2) CWB199-152 to (1) set CWB199-152
- Misc. - change (2) sq. ft. 1/8" to (4) sq. ft. 1/16"
- Misc. - change (2) lengths 303-6 to (2) pcs. (specify
- Misc. - change (2) FC100-02 to (2) FC100-002
- Page 2 & 3. Change (16) MS24694 S58 screws to (16)
MS24694 S60 screws.
- Page 2 & 3. Add (2) AN525-416RI8 and (2) AN525416R14
screws (needed in Chap. 8).
- Page 2 & 4. Add (2) AN960-516 washers (needed in Chap.
- Page 2, Misc.: add 1 pc.2 x 4 x 1/4 phenolic
- Page 2 and Page 4: Add (2) AN4-16A bolts and (2) MS210424
nuts needed in Chap. 19.
- Page 3, (Chap. 9, Metal): Change 4 pieces of .063 x 1.25 x
1.25 aluminum angle, to 1 piece of .063 x 1.25 x 1.25 x 4". It
is needed to make the LB-18 brackets.
- Page 2: Change (2) CWB199-152 wheels & brakes to (1)
CWB199-152 wheels & brakes. kit.
- Page 3, Fuselage: Change 2" x 12" x 12" to 2" x 24" x 24"
- Page 3, Elevators: Change (2) pcs 1" OD x .035w x 57" to (1)
pc 1" OD x .035" w x 36" 2024T3 Al. Tube
- Page 4, Chap.19, Misc.: add 1 pc. 2" x 4" phenolic
- Page 4: Add (2) AN5268R14 screws for the nose gear crank
bearing on the instrument panel.
- Page 5: Change (5) 7" x 14" x 41" pieces Styrofoam to (4) 7"
x 14" x 41" pieces Styrofoam.
- Preference Page 2 (MISC): Change (10) MM-3 rodends to (10)
- Preference Page 3, (Chap. 16, Hardware): Change (10) MM-3
rodends to (10) HM-4 rodends
- Page 1 - change 18" bandsaw to 14" bandsaw
- Page 1, para. 2: Change reference Chap. 5 to Chap. 6.
- Page 1, Fig. 2. Change .65" to .75" to get a 45 degree
- Page 2, para. 1: After (Fig. 7) add: See also Chap. 2, p. 5
- Page 3, Step 5 - add "Install alum. hard points per drwg.
M-7 before glassing.
- Page 3, Step 5 - Upper longeron doubler is shown incorrectly
on M-7. Doubler is 3/4" wide, not 1" wide. Reduce width of
hole through firewall to 1-5/8"
- Page 3, Step 5, 1st para: Add, "cut out and install the two
1 x 1 x 1/4" in. alum. inserts for the engine mount shown on
M-7and the two shown on M-8 before glassing the firewall
- Page 3, Step 5, 2nd para: Add, "Locate the two groups of
three MS24694-S54 blind screws 2.0 in. higher than shown on
M-7 and M-8 and detail D-D to provide more clearance between
the rudder cable and the aileron push rods.
- Foam - change 6 Lb. Clark to 4.5 Lb. Clark
- Foam - change lx24x24 urethane to lx24x48.
- Wood - change .7x2x18 to .7x2x24
- Page 3, Step 3: Change 2-1/2" tape to 2" tape.
- Page 3, Sec. A-A: Change ??? (typ.) to 3/8 (typ).
- Page 3, Step 3: 2-1/2" wide tape not necessary. Use 2" wide.
- Page 3, Step 3: 21/2" wide tape not necessary. OK to use 2"
- Page 6, Some of you noticed the pictures do not agree with
the drawings on the previous page. Follow the drawings. The
layup was changed after the pictures were taken to provide
more shoulder room in the back seat.
- Foam - change 6 Lb. Clark to 4.5 Lb. Clark
- Page 4, Fig. 18: Change 24-5/8" to 24-7/8" to agree with
- Page 8, 2nd line: Change "medium" to "low" density
Page 2, Step 2, 4th sentence, add after: back to the
firewall, “except remove all the foam on the outside of the
upper longeron and LWY starting at a point 5.5 inches
forward of the firewall, and taper the foam down to where it
is removed along the longeron and LWY so the glass will
conform (refer to M-7 and M-8)”.
Page 4, Step 4, para. 2, change last sentence to read:
“From this point the curvature gradually transitions to DD
just ahead of the center section spar cut-out”.
- Page 4, Fig. 21: Change 20-1/2" to 19", & 22 to 20-1/2
- Page 5 Step 5: Delete para. 4 starting with "Now...".
- Metal - change l/8" x l" xl/8" to l/8" x 1" x 12" Al angle
- Misc. - change MS200001-P6 to MS20001-P6
- Page 1, Fig. 1: For the head rest bottom piece, change 3" to
3-3/8" and change 7" to 7-3/4" and show the ends beveled to
match the sides.
- Page 1, Step 1, last paragraph. You may wait until you have
Chap. 18 to install the hinges.
- Page 1, in Fig. 1, change 14 to 13 and change 15 to 14.
- Add 3 additional layers of UND 4" wide x 13" long over each
attach point, starting 2" forward of the shoulder support on
the seat back, extending over the shoulder support, and then
around the back of the seat back. Please make this notation in
- Discrepancies in the material list for Chapter 9, change 4
pieces of .063 x 1.25 x 1.25 aluminum angle should have been 1
piece of .063 x 1.25 x 1.25 x 4". It is needed to make the
- The 8" x 12" x .063 aluminum was intended to make heat
shields, placed between the axle and strut to shield the strut
from red hot brake discs.
- Hardware - change MK-100 to MK100
- Misc. - change (2) CWB199-152 to (1) set
- Page 2, Step 2: Add note to trim 2-1/2" from each leg of the
main gear strut and then trim the end at 13 deg. (leading edge
longest) to avoid fuselage sitting high in the rear.
- Page 2, Step 2, and Fig. 7: Keith Spreuer suggests that that
13 strips of UND should be sufficient.
- Page 2, Step 2, para. 2: Change 13 deg. to 8 deg. (3 places)
- Page 2, Step 2: The landing gear strut is now being supplied
about 95-1/2" long by Featherlite. Check inside length and
trim to 95".
- Page 6, Fig. 30. Change .049 wall to .063 wall.
- Page 6. Para.2 & Fig. 31: Change #30 holes to #30
dimples (not through).
- Page 6, Fig. 45: Change 22.25" to 24.25".
- Page 9, 3rd paragraph: Change ½" square to 5/8"
square, to agree with Fig. 50
- Page 1, Step 2, Para. 2: Add this note, "Change top of
template F on Drwg. M-17 to agree with top of template G on
- Page 2, Step 3, Para. 2: Change "open up the 1/4" holes into
the doublers" to "open up the 3/16" holes...".
- Hardware - change AN526-832-14 nuts to AN526-832R14 screws
- Metal - change 1/4 0D x.035W to .032W
- Page 4. Step 3, Para. 2: Add: Open the pivot hole for MKNG-6
to 5/16" I.D.
- Page 7 call for riveting K-1000-4 nut plates to a 3/4" x
1-1/4" piece of 0.063" aluminum, while drawing M-11 calls for
the nut plate to be riveted to an AN 970-4 wide area washer.
Both are equally satisfactory.
- Page 9, Fig. 41: Change the thread size on Rosenhan Cylinder
from 1/4" x 20 to 1/4" x 28.
Page 10, Fig. 43: In the early 90’s, the clamp plate MKNG-2
was changed from a flat aluminum plate to a hat-shaped .090
steel plate, so the nose wheel would be able to swivel 360
degrees, but Fig. 43 was never updated to show this change.
At a somewhat later date, the MKNG-15A casting was changed
to make the ears longer and stronger, but again Fig. 43 was
NOTE: It is recommended that builders drill a 3/16”
hole through the side of MKNG-15 and strut and install an
AN-3 bolt of the proper length and nut to prevent the
MKNG-15A assembly from coming loose from the strut and
departing the aircraft in the event of nose wheel.
NOTE: It will help make the MKNG-15A assembly
attachment more secure to dimple the strut and fitting
before floxing the fitting in place.
- Page 10, Step 8: After reference to Fig. 43, add the
WARNING: Over-tightening the four bolts
clamping MKNG-15A to the strut will stress the ears of the
casting and reduce the safety factor on load carrying
ability. Snug the bolts only as much as necessary to hold
the assembly together while the flox cures. A limit of 10
in. lbs. is suggested. Fill in the space between the
casting and the clamp plate with flox to provide
additional bonding to the strut.
- Page 12: Change referenced Dwg. M-17 to M-l9.
- Page 12, View AA: Add note "After assembly with wheel and
bearings, check to see whether there is enough pressure on the
bearings so they rotate inside raceway. If they rotate around
the MKNG-1 bushings instead, shorten the length of the
bushings with a file until the bearings rotate on the
- Page 12: Change reference drwg from M17 to M19.
- Page 2, Step 3, end of 2nd par. - change LWA2 to LWAl
- Page 3, Fig. 14. Chang 3.5 to 5.25 (both sides).
- Page 3: Both steps 7 & 8 instruct you to install LWA2
and LWA3. You need only install them once.
- Page 4, Step 10, 4th para., change 2nd sentence to read:
“When everything is perfect, lay up a 5 ply BID tape spar to
LWY, inside and out, both sides, as shown on M-8, and a 5 ply
BID tape spar to longeron, inside and out, both sides as shown
- Page 5, shows a bulkhead installed at the centerline of the
center section spar, but this bulkhead is not shown on p. 7.
Make and install this bulkhead similar to bulkheads 6 & 7.
One inch diameter holes may be cut in the bulkheads for
routing electrical wires and co-ax cables through center
- Page 7, lower left hand corner. Change 33.21 to 33.58
- Page 8. Change 8.41 to 8.51, and 8.50 to 8.60
- Page 1, SCHEDULE A - PREFAB PARTS: Change CS-50 from AN-3
rodend insert to AN-4 rodend insert.
- Page 2, COZY STICK ASSEMBLY - CZSA (2 REQ'D): Change CS-50
from drill and tap 10-32 to drill and tap ¼-28 AN-3 rodend
insert to AN-4 rodend insert.
- Page 2, The plans show the bearings for the aileron torque
tubes inside the fuselage, CS 108 and CS 115, to be made from
¼” thick phenolic. These are quite acceptable; however,
inexpensive bearings FMN10 may be substituted, in which case
the holes in bearing blocks CS-109 and CS-118 must be
relocated and enlarged to accept AN-4 bolts.
- Page 1, Schedule B: Change 11" for CS126L to 12.25".
- Page 1, Step 1, para. 2: Change l" to 7/8" diam. holes
- Page 1: You will need 7 ft of 1/2" O.D. x .035" w 4130 STL
tubing. Make this change in the Sec. II bill of materials
Preface p. 3, and add to bill of materials p. 2
- Page 1, Prefab parts: Change CS-1 to CS-50. These inserts
were originally made to fit inside .028" w. tubing, but have
been changed to fit inside .035" w tubing. If you have the
earlier ones, the .035" w tubing can be reamed so they will
- (Sec. H, Preface p. 2 and p. 3), Add 4" of 3/8" OD x .065" W
4130 steel (for CS112 and CS131 in Chap. 16).
- Page 4: Change view G-G from MM-3 to HM-4, and all related
AN-3 hardware to AN-4 hardware.
- Change any reference to MM-3 rodends in text or drawings to
- Page 6, Step 4, para4: Change 19-5 & 19-6 to 19-15 &
- Page 6, Step 5: Change 82" long to 86" long.
- Page 7, Step 6: Change Fig. 2 to Fig. 3.
- Page 7, Fig. 8: Delete 4" rudder deflection. Maximum
deflection is 26 deg which is only 1-3/4" at the top.
- Page 7, Step 6, 3rd line: Change to read "no more than 4.5"
- Page 8, Step 5: K-mart #82-20-57 may not be available. Use
any similar after-market lamp and modify linkage to suit.
- Page 9: The LL-2 should not be purchased from Brock because
length varies depending upon lamp used.
- Page 1, Step 2: Change two sheets to three sheets.
- Page 5, para. 3: Delete relocating screws per design change
in NL #39.
- Page 8, Fig. 45, Change 5.5" to 4.5" aft of the instrument
panel to keep from having interference with the canopy latch.
- Page 9, top of Fig. 51) Connect the two 2-1/2" pads (for the
latch and safety catch, together, and widen the pads (Section
A-A from 1.6" to 2.0") to make the location of the screws less
- Metal - change (4) 7/16" OD x36" to (2) 72"
- Page 1, Step 10, para. 3: Keith Spreuer advises to change 23
to 24 pop rivets to agree with rivet layout Chap. 19, p. 17,
and to add 48 BSPQ-43
- Page 5, para. 1: Change 3 plies (typo) thick to 2 plies
thick from B.L. 132 to B. L. 169.
- Page 7, Fig 40: Change B.L. 55.5 to B.L. 67.5, and change
B.L. 106.25 to B.L. 118.25
- Page 8, Step 10 - change 3/8" rod to 7/16" rod
- Page 9, Step 11, Para. 2. Change layup #11 to layup #12
- Page 9, Step 11, para.3: ChangeAN3-4A to AN3-5A
- Page l4: Sections I-I, H-H, J-J - change A11 to A13
- Page14: Change A11 to A13 in sections I-I, H-H, and J-J
- Page14: The plans show the bearings in the wing rib for the
aileron torque tubes to be made from 1/4" thick phenolic.
These are quite acceptable, however, inexpensive bearings
FMN10 may be substituted, in which case they must be floxed
and glassed in place.
- Page 16: Change nut AN4-16A bolt from MS21042-3 to
- Page 16: Change nut for AN4-16A to MS21042-4.
- Page 17: Change A13 from 3/8" to 7/16" steel rod.
- Page 17: For A13, change 3/8" to 7/16"
- Page 17: For A13, change 3/8" to 7/16".
- Page 17: A13 - change 3/8" rod to 7/16" rod
- Page 17: CS151 - change approx. 30" to 34"
- Page 18: Para. 1. Change p. 19-8 to p. 19-7.
- Cherry pop rivets to the material list for Ailerons, Chap.
2, p.4, and the summary list Chap. 2, p. 2.
- Change any reference to MM-3 rod-ends in text or drawings to
- Page 1, Step 1, 2nd line. Change Chap. 23 to Chap. 3
- Page 1, Fig. 1: Change 48" to 47" & 39" to 40".
- Page 6, View B-B, upper right: Change BL 157 to BL 169.
- Misc. - after B2Dx62 add x 12V
- Misc. - change (2) 303-6 to (2) pcs. 303-6
- Page 2: Fuel tank capacity is 26-30 gal. per side, depending
upon how built.
- Page 2: Correct calculated fuel volume to 26 gal. each side
at FS 102.5.
- Page 3: Some of these sections might he reversed.
- Page 5, para. 2: Assemble with flox as shown on Chap. 21, p.
3, and radius corners with micro before taping.
- Strakes Chap. 21, p.5, 2nd para. 4th
line. Where it says to assemble the parts with micro, use
- Page 6, Fig. I 1. Change 1.8 to 3.5. 1.4 to 3.1 . and 1.35
to 2.5. Also 6.0 to 4.0, 7.0 to 5.0, and 7.2 to 6.2.
- Page 8, Sec. A-A Spacers for gascolator: Change 3/8"OD x
3/l6"ID to 5/16"OD x .065W 2024-T3 as shown in material list
or substitute 5/l6"OD x 3/16"ID 1015 steel bushing stock.
- Page 1: Top of page change Chap. 25 to Chap. 23.
- Page 2, para. 1 and Fig. 1: Change (4) AN6-40A to (4)
AN6-34A. Make the same change in the Bill of Materials Sec.
II, Preface p. 2 and p. 4. (The engine mount is now being
supplied by Brock with 2" rather than 2-1/2" stand-offs as
shown on Drwg. M-29).
- Page 2, Fig. 3 and Step 7 text: Change MS21042-7 to
NAS1291-7 (new designation for small profile nut).
- Page 2, Fig. 3, Reduced dimension engine mount nuts. Change
MS21042-7 to NAS1291-7. Make same change Preface p.2 and
Preface p.4, Chap. 23.
- Page 4, 3rd para. and Fig. 18: Change 1 ply BID to 4 plies
BID to agree with drwg. M-7, Section BB.
- Page 6, Step 4, after the 1st para. add this: “If the pipes
are not tightly supported going through the rear baffle (zero
clearance), they can shake, fatigue, break, and go through the
prop. For insurance against this, bind together both pipes on
each side with a stainless worm hose clamp on the engine side
of the baffle”.
- Page 9, Change AN3-10A to AN3-4 or 5A.
- Page10, Fig. 40: Add a note that the baffle shown for
cylinder #4 is upside down.
- Page 13, Step 9: Ellison throttle body installation, Fig. 54
shows the throttle in the correct position but it should be
labeled B rather than A, to agree with Ellison's schematic.
Also, we have been advised by Cablecraft that for aircraft
applications, the cable designation should be #580-700-109.
Please make these changes.
- Page 15, the mounting hole should be 11/32" rather than
9/32", and the 1.06" radius should be increased to approx.
- Drwg. M-4: The hole for the nose gear torque tube should be
off-center to the right and need only be 3/4" I.D.
- Drwg. M-4: Change the 3.3" dimension on F-28 to 4.0", and
curve the top edge of F-28 gently from the center to each
side. This will make the top of the nose more rounded (less
flat) and enhance its appearance. If F-28 is already
installed, epoxy a strip of 1/4" foam on the top and glass
each side with 1 layer of BID.
- Drwg. M-5, Change 4.l" to 4.3".
- Drwg. M-6, Change 3.65' to 3.85" and adjust other dimensions
- Drwg. M-6, Change 7.4" to 7.2".
- Drwg. M-6, Change 3.6 to 3.3.
- Drwg. M-7: Where upper longeron and doubler penetrate
firewall, doubler is shown as 1" wide, when it should have
been shown as .75" wide.
- Drwg. M-7: Change washer call out under engine mount bolt
head from AN960-616 to AN970-6.
- Drwg. M-7: Delete bushing in engine mount detail so it looks
like Chap. 23, p. 2, Fig. 1.
- Drwg. M-7, Upper longeron doubler is shown incorrectly.
Doubler is 3/4" wide, not 1"
- Drwg. M-8 calls for 5 plies BID reinforcement over the lower
engine mount hard point. Change this to 2 plies BID and 3
plies UND to agree with Chap. 7, p.5, Fig. 24.
- Drwg. M-8: Change 5 plies BID reinforcement over lower
engine mount hardpoint to 2 plies BID and 3 plies UND to agree
with Chap. 7, p.5, Fig. 24.
- Drwg. M-8, sec. E-E: Change to "select height so cable
misses pushrods and leads in to CS 72. This height should be
- Drwg. M-9 Belcrank assembly MKCS 122/124 is shown
incorrectly as 2.5" long. It should be 13-1/8" long per Chap.
- Drwg. M-10. Change join to M-17 to join to M-19.
- Add a note on M-11 to use a washer (416L preferred) under
lift tab bolts.
- Drwg. M-11: Elevator hinge NC-3 is shown installed too deep
in canard. Install hinge so bottom surface is approx. 1/8"
below bottom of canard. 17) Drwg. M-11: Trailing edge of
canard extends slightly farther aft than shown.
- Drwg. M-13: This drawing incorrectly shows the landing brake
attached to LB-23 with AN3 bolts rather than the AN525 screws
and aluminum slugs specified in Chap. 9.
- Drwg. M-15, Change join to page M-16 to M-9
- Drwg. M-15: Change "join to M-16" to "join to M-9".
- Drwg. M-17, Template F: Top of template F is not shown at
the correct angle. Change it to agree with top of template G
on Drwg. M-18.
- Drwg. M-25: Delete jig board sketch lower left, and write:
See Fig. 5, Chap. 21, p. 4.
- Drwg. M-25: Re-dimension the isometric drawing lower left
corner to agree with Chap. 21, p4, Fig. 5.
- M-35, Sec. A-A: Change 2" to 2-1/2".
- move the shoulder attach points closer together so that they
are no farther apart than 8.5". This will require installing new
hard points, same procedure as shown in the plans. The bolts may
just clear the head rest, but the triangular harness brackets
will not, so it will be necessary to notch the forward corners
at the base of the headrest to provide the necessary clearance
for the brackets.
- As explained in our aft c.g. flight test report, the canard
span shown in the plans is too long and will allow the main wing
to be stalled at a c.g. of 101.6 and beyond. This is
unacceptable! The span must be shortened by 6" (3" at each tip).
In Chap. 11, p.2, shorten the 11" outboard section of the canard
to 8". This will put the counterweight recess adjacent to the
tip. Also, remove 3" from the outboard end of the elevator. It
will then be at B.L. 70.4 and the counterweight will be flush
with the end of the elevator. After making this change on our
plans model, we were no longer able to stall the main wing with
the c.g. as far aft as 103.2. After this change is made, the
approved c.g. operating range will be 97.5" to 102. 1", which
provides a safety factor at both ends of the range. This design
change is mandatory!
- If you have an exhaust system with a heat muff welded on to #4
pipe, ground your airplane until you replace it with a new #4
pipe with a heat muff that is clamped on.
- On drawings M-32 and M-33 indicate that the aft baffles should
be reinforced locally with 1/8" aluminum (instead of .032) where
they are cut out for the exhaust pipes, and the cut-outs for the
pipes should be a .875" radius for a tight fit around 1.75"
pipes, and the two exhaust pipe baffles shown on M-33 should be
similarly dimensioned and made from 1/8" aluminum. Add a note
that each pair of pipes should be clamped together or wired
together with safety wire ahead of the aft baffle to prevent any
relative movement. Your airplane should be grounded until these
changes are made.
- The 2" x 4" x .063 aluminum shown on Wicks material list
appears to be a mistake, because I couldn't see a use for it.
- Discrepancies in Section II, Preface Page 1 (Table of
- Change Chap. 4 from 9 to 4 pages
- Chap. 16 from 7 to 8 pages
- Chap. 18 from 17 to 18 pages
- Chap. 23 from 21 to 22 pages
- On the back covers of both Section I and Section II, both
editions, change the canard tip leading edge B.L 75.5 to B.L.
72.5, and the canard tip trailing edge B.L. 78.5 to B.L.75.5.
In the Owners Manual, the dimensions are correct.
- The recommended nicopress sleeve to use on SS (stainless
steel) cable is zinc plated, 28-1-C, NOT copper, 18-1-C.
Change the bill of materials for Chapter 16, where they are
used on the rudder cables, and Chapter 17, where used on the
roll trim. Beware, hardware stores carry aluminum sleeves.
They are a no, no!
- The control system rodend insert, have undergone an
evolution since they were first designed by Burt in 1976 for
the Varieze. The CS-1 insert was originally aluminum with a
.427 OD to fit inside .035 wall tubing and drilled and tapped
for AN3 rod ends. When Varieze and Long EZ builders were
accidentally bending the AN3 rod ends while removing and
installing their canards, a change was made to the AN4 rod
ends, for the elevator push rods, requiring the CS-1A insert,
which was drilled and taped for ¼x28. Then, after a Long EZ
experienced compartment were change to .5 OD x.028 wall steel
and the CS-1 insert was changed to a .441 OD for .028 wall
tubing with a new designation, CS-50. But the wall steel
tubing is almost impossible to obtain, so the OD will probably
be changed back to .427. We are dealing with two different
wall thickness', each with a tolerance of +/- 10%, so some fit
problems may occur.
The optimum angle of incidence for the Roncz canard is the
angle that puts the elevators in trail (0 degrees) or slightly
reflexed in cruise at a mid c.g. But a number of builders
have reported that they have carefully set their canard
incidence-using template F on M-17, and yet their elevators are
3 or more degrees trailing edge down at cruises with a mid
c.g. Apparently the template F on drawing M-17 does not
produce the recommended result, so it has been modified as shown
to the right. Please copy this new template and paste it over
the old template F on drawing M-17. If you are satisfied with
the way your airplane performs, it is not necessary for you to
change. But new builders should use this new template.
The elevator travel-checking template G on drawing M-18 has
been modified to agree with the new template F described above
and is shown on the next page of this newsletter, 80-3. Please
copy this new template and paste it over the old template G on
The nose gear LST shock strut assembly shown on Chap 13, p.3,
is exactly as designed by RAF for the Long EZ and as supplied by
Brock Mfg. The LST strut shown on drawing M-10 is not correct,
because it is 1/2" shorter. We don’t know how this happened.
There is enough adjustment, however, so 1/2" longer should not
cause a problem.
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[Cozy MKIV Information]
Last Updated Online: January 09,
(Thanks to Larry
Capps for this compilation)