QS) Destroy this report when no longer needed. Do not return it to originator.
14. When this report is no longer needed, Department of the Army organizations
will destroy it in accordance with the procedures given in A& 380-5. Navy and Air
Force elements will destroy it in accordance wish applicable directions. Depart¬
ment o£ Defense contractors will destroy the report according to the requirement
of Section 54 of the Industrial Security Manual for Safeguarding Classified Infor¬
mation. All others will return the report to US Army Aviation Materiel Labora¬
tories, Fort Euotis, Virginia 23604.
August 16, 1962
Flight Propulsion Laboratory Department
General Electric Company
Cincinnati 15, Ohio
TABLE OF CONTENTS
3 . 1.1
3 . 1.2
3 . 1.3
3 . 2.1
3 . 3.1
3 . 4.1
3 . 4.1
3 . 4.1
3 . 5.1
3 . kj . i
3 . 7.1
3 . 8.1
3 . 9.1
REFERENCE SPECIFICATIONS AND MATERIALS 1
Sealing Compounds and Rust Preventives 2
Thi liners 2
GENERAL REQUIREMENTS 2
low Strength & Clad Aluminum Alloys
All Other Aluminum Alloys
Carbon & Low Alloy Steels
Sheet, Plate, Fittings & Shapes
Corrosion & Heat Resisting Alloys 4
3rass, Bronze, Copper, Lead or Tin 4
Fiberglass Assemblies 4
Ducts Carrying Hot Gasses 4
Tubing (Plumbing) 4
TABLE OF CONTENTS (Cont'd)
4 . 0.0
4 . 1.0
4 . 2.0
4 . 2.1
4 . 2.2
DISSIMILAR METAL PROTECTION 5
Definition of Dissimilar Materials 5
Faying Surface Protection 3
Magnesium Alloys 0
Dissimilar Materials Other Than Magnesium 5
SPECIAL EXEMPTIONS AND NOTES 5
Lubricated or Functional Surfaces 3
Attaching Parts ®
Surface Treatment ®
Bonded Parts °
Drainage Provisions 6
FINISH SPECIFICATION FOR MODEL 143 (VZ-11)
1, Purpose. The purpose of this specification is to define
the finishes necessary to assure adequate surface protection for the
materials used in the Army VZ-11 airplanes (Model 143).
In the event of discrepancies relative to finish information
shown on the drawing and the requirements of this specification, the
drawing will govern.
2. Reference Specifications.
j QQ-P-416 Plating, Cadmium (Electro-deposited)
MIJLr-C-490 Cleaning and Preparation of Ferrous
and Zinc Coated Surfaces for Or¬
ganic Protective Coatings
MIL-M-3171A-1 Magnesium Alloy; Process for Corrosion-
MIL-C-5541 Chemical Films for Aluminum Alloys
MII/-A-8625A Anodic Films; Corrosion Protection
(for) Aluminum Alloys (MPD #32)
MPD-102 Dow 17 x*.~>od'. ° for Magnesium Alloy,
Ryan Aeromutical Company Speci-
MIL-S-5002 Surface Treatments (Except Priming
and Painting) for Metal Parts in
MIL-P-8585A Primer Coating, Zinc Chromatic Low
Primer, Vinyl Zinc Chromate
MIL-V-6894 Varnish. Oil Type, Gloss Finish, Gly¬
ceryl Phthalate Base
MIL-C-15328 Pre-Treatment, Wash Primers
MIL-P-15930 Primer, Vinyl Zinc Chromate
MIL-L-7178 Lacquer, Aluminized
W. P* Fuller Co. #163-W-52 Lacquer Primer Surfacer
Sealing Compounds and Rust Preventives.
MIL-P-8116 Putty, Zinc-Chromate, General Purpose
MIL-C-11796 Corrosion Preventive, Petrolatum, Hot
MIL-C-16173 Compound, Rust Preventive
3M Company .002 in. Polyester insulating tape
TT-T-266 Thinner, Dope and Lacquer (Cellulose-
3.1.1 Aluminum Alloys. - The following surface treatments shall
be applied to all aluminum alloys as applicable:
3.1.2 Low Strength and clad aluminum alloys 3003, 5052, 5356, 6061,
clad 2024 and clad 7075:
(a) No chemical treatment required
(b) No organic protective treatment
3.1.3 All other aluminum alloys not listed in item 3.1.2 shall le-
ceive the following:
(a) Alodine in accordance with Spec. MIL-C-5541
(MPD #100). Anodize per MIL-A-8625A (MPD #32)
is an acceptable alternate treatment.
(b) One coat zinc-chromate primer per MIL-C-5541
(MPD #3 00).
(c) See section 5.0 for exceptions to the above.
3.2.1 Magnesium Alloys. The following surface treatments shall be
applied to all nugnesium alloys:
(a) Dow 17 anodize per Ryan MPD-102
(b) One box coat of MIL-C-15328 wash primer
(c) One box coat of MIL-P-15930 vinyl zinc-chromate
(d) For external applications coat outside surface with
two coats aluminized lacquer per MIL-L-7178
Cut edges and abraded spots on magnesium alloys shall be
touched up with a chrome pickle solution meeting Type I, Specification
MIL-M-3171. Areas treated must be thoroughly rinsed and wiped dry prior
to primer application.
3.3.1 Titanium Alloys. The following surface treatments shall be
applied to all titanium alloys:
(a) No chemical treatment
(b) No organic protective treatment except as specified
under item 4,0 - "Dissimilar Materials Protection".
3.4.1 Carbon and Low Alloy Steels.
188.8.131.52 Sheet, Plate, Fittings and Shapes: All carbon steels and
low alloy 3teels shall receive Type II cadmium plate per Spec. QQ-P-416
(MPD #30). Bolts, studs, washers and articles with portions externally
threaded shall receive a minimum of Class 3 thickness plate.
Classes of cadmium plating are:
Class 1 - .0005" thick
Class 2 - .0003" thick
Class 3 - .0002' thick
3.4.1-2 Tubing. All carbon and low alloy steel tubing; shall be
cadmium plated per QQ-P-146 (MPD #30) on the exterior. Interior treat¬
ment shall be as follows:
Closed tubing : Coat inside with MIL-C-11796 Class
I rust preventive compound per MPD #39.
Open ended tubing : Phosphate treat interior per
MPD #15 plus one coat of zinc chromate primer.
3.5.1 Corrosion and Heat Resisting Alloys.
(a) No chemical treatment
(b) No organic protective treatment except as
specified under item 4.0 "Dissimilar Materials
3.6.1 Rrass, Bronze, Copper, Lead or Tin Alloys, Cadmium plate
per QQ-P-416 (MPD #30) if a dissimilar metal contact exists; otherwise
3.7.1 Fiberglass Assemblies, All fiberglass sui *. shall be
washed with a solution consisting of equal parts of Shell > u^olv W.
Spec. TT-T-548 or equivalent, and lacquer thinner Spec. TT-T-?66 or
equivalent prior to finishing.
(a) After cleaning as noted above, apply 2 box
coats of W. P. Fuller 163-W-52 or equivalent
lacquer surface primer. Air dry.
(b) Apply aluminum airfoil putty, Sherwin-Williams
No. PX-4045 as necessary. Sand smooth.
(c) Finish with 2 coats MIL-L-7178 aluminized
3.8.1 Ducts Carrying Hot Gases. The finish on all of the hot
ducts shall be as specified on individual detail and assembly drawings,
3.9.1 Tubing (Plumbing lines). Tube fittings and tubing shall net
be painted. The exterior surfaces of aluminum tubing shall be anodized in
accordance with MIL-A-8625A (MPD #32) or alodine per MIL-C-5541.
a a a - j —. j ■» -n _ _ 4. » -i. j .
*i,u«u uiaaiuujiar miuciittis nvic^uyu,
4.1.0 Definition of Similar and Dissimilar Materials. For the
purposes of the finish requirements for this airplane, the following
table defines the dissimilar metal contacts which require the faying
surface protection outlined in Section 4_.2. (See page 7).
4.2.0 Faying Surface Protection. ~ Dissimilar Metal Contacts.
The following protection is required in addition to the
surface protection specified in Section 3.0 of this specification.
184.108.40.206 Faying surfaces shall be protected from contacting materials
by (1) layer of .002 in, polyester tape (3M Company #853 or equivalent).
Ihe tape shall overlap the joint by 1/4" on either side wherever possible.
220.127.116.11 Fasteners in Magnesium.
Aluminum fasteners shall be of 5056 material or equivalent.
All other fasteners through magnesium shall be installed with
wet prime. In addition, insulating washers (.010 min. thickness) shall be
used under the fastener heads in contact with the magnesium.
Dissimilar metals other than magnesium.
All faying surfaces shall receive one coat of zinc-chromate
primer with a tolerance of 1/2 ' on interior surfaces coated beyond the
edge of the mating part. Exterior surfaces are to be wiped clean of all
Slip fits shall be assembled using wet zinc-chromate primer.
Press fits f?hal 1 be accomplished with a lightly oiled surfaces on the mating
5.0 Special Exceptions and Notes.
5.1 Lubricated or Functional Surfaces. Paint coatings shall not
be appliea to those pares which are permanently coated with or housed in
lubricating oil, hydraulic oil oi* grease. Paint coatings shall not be
applied to working surfaces, adjustable screw threads, sliding mechanisms
or to fittings in such a manrer as to cause malfunctioning.
5.2 Attaching Parts.- Attaching parts such as nuts, '"ashsrs,
rivets, high shear rivets, screws, bushings, spacers etc., need not be
painted in detail except when used in contact with wood or magnesium.
(See Section 4.0).
5.3 Surface Treatment. All metal surfaces shall receive accept¬
able surface treatment prio" to painting. This treatment shall be in
accordance with the requirements of Specification MIL-S-5002.
5.4 Bonded Parts. Aluminum alloy parts which are to be subse¬
quently bonded shall not be painted or primed in the detail. Bonded
assemblies shall receive the organic finish specified m Section 3.0
of this specification.
5.5 Drainage Provisions. Where practicable, drainage provisions
shall be incorporated in the design o' the structure except where such
drainage provisions would interfere with the utility or function of the
part. Drain holes, 1/4' diameter, shall be so located to drain the struc¬
ture when the airplane is in a thiee-point position. When necessary
for structural considerations, drain holes may be reduced to 3/16’’ dia¬
5.6 Tanks. The interiors of all fluid containing tanks shall
not be pointed or primed.
Shaded areas denote dissimilar materials.