Skip to main content

Full text of "DTIC AD0634951: FINISH SPECIFICATION"

See other formats








DISPOSITION INSTRUCTIONS 


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 


Para. 

1 . 

2 . 

2.1 

2.2 

2.3 

2.4 
3 . 

3.1 

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 


No. 


.1 

.2 


Page No. 


PURPOSE 1 

REFERENCE SPECIFICATIONS AND MATERIALS 1 

Processes 1 

Finishes 1 

Sealing Compounds and Rust Preventives 2 

Thi liners 2 

GENERAL REQUIREMENTS 2 


Surface Treatment 
Aluminum Alloys 

low Strength & Clad Aluminum Alloys 

All Other Aluminum Alloys 

Magnesium Alloys 

Titanium Alloys 

Carbon & Low Alloy Steels 

Sheet, Plate, Fittings & Shapes 

Tubing 


Corrosion & Heat Resisting Alloys 4 
3rass, Bronze, Copper, Lead or Tin 4 
Fiberglass Assemblies 4 
Ducts Carrying Hot Gasses 4 
Tubing (Plumbing) 4 


i i 





TABLE OF CONTENTS (Cont'd) 


Para. No, 
4 . 0.0 
4 . 1.0 
4 . 2.0 

4 . 2.1 

4 . 2.2 
5.0 

5.1 

5.2 

5.3 

5.4 

5.5 

5.6 


Page No, 

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 

Tanks 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. 

2.1 Processes. 

j QQ-P-416 Plating, Cadmium (Electro-deposited) 

(MPD #30) 

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- 

Protection of 

MIL-C-5541 Chemical Films for Aluminum Alloys 

(MPD #100) 

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- 
ficiation 

MIL-S-5002 Surface Treatments (Except Priming 

and Painting) for Metal Parts in 
Aircraft 

2.2 Finishes. 

MIL-P-8585A Primer Coating, Zinc Chromatic Low 

Moisture Sensitivity 


MIL-P-15930 


Primer, Vinyl Zinc Chromate 




2.4 


3.0 

3.1 


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 

Application 

MIL-C-16173 Compound, Rust Preventive 

3M Company .002 in. Polyester insulating tape 

#853 

Thinners. 

TT-T-266 Thinner, Dope and Lacquer (Cellulose- 

Nitrate) 

TT-T-548 Toluol 

TT-X-916 Xylene 

General Requirements. 

Surface Treatment 


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 


-2- 





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 
primer 

(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. 

3.4.1.1 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 


-3- 




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 
Protection." 

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 
none required. 

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 
lacquer. 

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. 


-4- 






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. 


4.2..1 


Magnesium Alloys. 


4.2.1.1 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. 

4.2.1.2 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. 


4.2.2 


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 
excess primer. 


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 
parts. 

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. 




«r* 


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¬ 
meter. 

5.6 Tanks. The interiors of all fluid containing tanks shall 
not be pointed or primed. 


-o- 




Shaded areas denote dissimilar materials. 


Chromium Plate