76_S-F502_77751_SP_L_0001_L_NULL_0001_753_U_N_Y_N_N_Y_D.PDF

CAGE 77751 S-F502

Revision L

13 August 2019

Data contained on this sheet is subject to the restrictions on the title page of this document.

ii

TABLE OF REVISIONS

Revision Changes Reason for Change Approved Original issue 06/24/1971

New document. H. Kleindienst

Revision A 01/02/1974

Incorporated Amendment 1. H. Kleindienst

Revision B 09/01/1978

Incorporated Amendments A1 through A4. H. Kleindienst

Revision C 09/06/1979

Incorporated Amendments B1 through B5. H. Kleindienst

Revision D 07/16/1981

Incorporated Amendments C1 through C5. H. Kleindienst

Revision E 08/12/1981

General update. R. Bruning

Revision F 04/14/1988

Incorporated Amendments E1 through E5. G. Leavy

Revised Section 2.0 and removed exact issue callouts.

Relocated wet layup and repair procedures in separate appendix.

Replaced obsolete repair materials.

Reformatted per MIL-STD-490.

Revision G 04/10/1997

Revised or redrew most figures. K. Grube

Added Foreword describing review of this specification for toxins, pollutants and other hazardous materials, and establishing user responsibility for following all laws and regulations involving their use.

Deleted TT-M-261, Methyl Ethyl Ketone, to reduce use of hazardous air pollutants (HAPs).

General update of document titles and corporate designations/contact info.

Deleted release agent Frekote 33, which contained Freon and hence is no longer manufactured.

Replaced release agent Frekote 44 with Frekote 48-NC, which does not contain ozone depleting substances (ODSs) and is lower in HAPs.

iii

Revision Changes Reason for Change Approved Added release agents Frekote C-200/C-210 and 710-NC, which are all lower in HAPs.

Redesignated release agent Ram 225 as Lilly Mold Release 225.

Deleted peel ply materials (Burlington no longer manufactures peel ply materials).

Section 3.2.2.6(c): deleted Flowmaster Marking Pens, which are no longer made by present owner of former Esterbrook Pen Co.

Deleted TT-M-261, Methyl Ethyl Ketone, to reduce the use of HAPs.

Restricted TT-N-95 to Type II, which is lower in HAPs.

Added Section 3.2.2.7(c), Methyl Propyl Ketone (MPK), since it is lower in HAPs.

Added Section 3.2.2.7(d), MPK/Naphtha 50/50 by weight blend, since it is lower in HAPs.

Updated application instructions to reflect use of Frekote 48-NC, 710-NC, and C-200/C210.

Deleted application instructions for Frekote 33; replaced with application instructions for Lilly Mold Release 225.

Deleted use of MEK; restricted to cleaning core with TT-N- 95 Type II aliphatic naphtha, since new solvent is lower in HAPs.

Revision H 03/03/2013

Added Air Force T.O. 1-1-690 to Section 2.1. K. Grube

Incorporated Air Force Engineering Orders 12A2975-H, 09A1418, 08A0634, and 06A1012 with the exception to allow for the original sandwich part acceptance criteria as an option because many composite parts manufacturers do not have differential scanning calorimetry (DSC) equipment nor are skilled in its use.

Updated Section 2.2 to include BMS 8-79 as an alternative for C-M605 in accordance with Air Force EO and added ASTM E2160 for DSC test protocol.

Section 3.1.2.1.1: added cleanroom requirements per T.O.

1-1-690 and ISO.

iv

Revision Changes Reason for Change Approved Section 3.2, Materials: general updating of materials/vendor information.

Section 3.2.1.3: added adhesives: FM 300-2 as a preferred low temperature version of FM 300M, plus EA9628NW and EA9696 to be compatible with S-F501.

Clarified adhesive procurement test requirements.

Updated Section 3.2.1.5, Syntactic Adhesives.

Updated Section 3.2.2.8, Repair Materials.

Added EA9628NW to Sections 3.3.4(g), 3.3.5(f), 3.3.7.7(a) and 4.3.4.1 per Air Force EO 04C0164.

Clarified criteria and temperature in Table II cure schedule.

Section 4.5.3: added 162S900718, Inspection of Composite Structures: S-F502 Supplement for A-10 Wing Replacement Program.

Amend. J1 10/19/2015

Cancelled unreleased Rev. J;

released EO to add G-S901 to Sections 2.2 and 4.1(a).

To add NDI requirements.

S. Miro

Revision K 01/17/2018

Incorporated Amendment J1;

redrew figures; corrected typos and made minor grammatical changes.

Specification update;

improve clarity.

M. Kassinger

Rewrote 1.0 (was: “This specification establishes the requirements for the processing and inspection of laminate and sandwich construction 250°F curing epoxy resin composite parts suited for use in an environment of –65 to 180°F.”).

More accurate description of document’s scope.

Updated applicable documents and all references and callouts throughout.

Specification requirement.

In 2.2 and 3.2.1.1(b), deleted references to EO06A1617.

No longer applicable.

Added 3.1.1.4. To provide oven parameters.

v

Revision Changes Reason for Change Approved Revision K (continued)

Reworded 3.1.2 introductory paragraph.

Clarity; per Air Force direction.

Replaced 3.1.2.2 and 3.1.2.3 with greatly expanded 3.1.2.1 and new Table I; renumbered subsequent tables.

To more fully define cleaning/housekeeping requirements.

Added 3.1.3.2 through 3.1.3.5. To more fully define tooling requirements.

In 3.2.1.1, added BMS 8-79. Per Air Force direction.

In 3.2.1.3, deleted (b), FM 300;

re-lettered remaining items; in 1/ and 2/, changed “S-F501 Table VII” to “S-F501 Table VIII”; added nominal thicknesses.

FM 300 is not applicable to this specification;

revision of S-F501 changed some table numbers; clarity.

Added 3.2.1.5; renumbered subsequent sections.

To provide identification and storage

Added new Table II;

renumbered subsequent tables.

To provide more complete storage conditions and material life information.

In 3.2.1.6 [formerly 3.2.1.5], updated supplier name and address.

To reflect current supplier information.

In 3.2.1.7(a) [formerly 3.2.1.6(a)], added American Durafilm.

To provide an alternate supplier to DuPont.

In 3.2.1.8 [formerly 3.2.1.7], updated product designation and supplier name and address.

To reflect current material and supplier name.

In 3.2.2 introductory paragraph, added the following clause: “when substantiated by test data and approved by the

A-10 SPO.”

To ensure that only tested and approved materials are used.

vi

Revision Changes Reason for Change Approved Revision K (continued)

In 3.2.2.1(a) and (b), added American Durafilm.

To provide an alternate supplier to DuPont.

In 3.2.2.1(c), updated Airtech International’s address.

To reflect supplier’s current location.

In 3.2.2.2, updated suppliers’ names and addresses.

To reflect suppliers’ current identities and locations.

In 3.2.2.3(a), deleted 1B301- F58 peel ply and replaced with “Peel ply shall be qualified only with the written approval of A- 10 SPO Engineering.”

Material is no longer available; A-10 SPO Engineering will approve qualification of peel ply materials.

Deleted 3.2.2.3(b) and related asterisked note below.

Material is no longer available; supplier is no longer in business.

In 3.2.2.4, updated Airtech International’s address; deleted item (c) and relettered subsequent items; deleted Bleeder Lease F.

To reflect supplier’s current location; material is no longer available (supplier is no longer in business); material is no longer available.

In 3.2.2.5(a), changed supplier to Airtech International.

Material is available through Airtech.

In 3.2.2.5(b) and (c), Schnee- Morehead changed to ITW Polymers Sealants; 3.2.2.5(c) product part number changed to 5126 (was 5126-2).

To reflect current supplier identity; to reflect current product identification.

In 3.2.2.6(c), updated product designation and supplier name and address.

To reflect current product identification, and supplier’s name and location.

In 3.2.2.6(d)(3), deleted reference to Hill AFB document QSM-0043; 3.2.2.6(d)(4), added part numbers for individual sizes.

Per Air Force direction;

to provide more-complete information.

vii

Revision Changes Reason for Change Approved Revision K (continued)

In 3.2.2.6(f), changed to Type J, deleted wire gauge (was 24 AWG or finer)

To provide updated designation and permit supplier to choose appropriate wire gauge.

In 3.2.2.6(g), added cloths per AMS 3819, and incorporated Rymplecloth as example of AMS 3819 cloth.

AMS 3819 cloths are the approved wipers;

Rymplecloth meets AMS 3819 requirements.

In 3.2.2.6, added (h), squeegees.

Required but were omitted previously.

In 3.2.2.7(b), added MACH- DYNAMICS as supplier.

To provide alternate source for aliphatic naphtha.

In 3.2.2.7, replaced MPK/naphtha blend with ultra-high purity MPK; added MEK, MIBK and isopropyl alcohol.

No longer available;

alternate to technical grade MPK; solvent alternatives.

Deleted 3.2.2.8(e); relettered subsequent item.

Material is no longer available; supplier is no longer in business.

In 3.2.2.8(e) [formerly 3.2.2.8(f)], updated material callouts; changed supplier name and address.

To reflect current product identification, and supplier’s name and location.

In 3.3.1.1(d), added the following clause to bullet:

“including key inspection points throughout the process.”

To ensure that inspection points are defined in suppliers’ work orders.

Rewrote 3.3.1.5 to permit gloves other than those made of cotton.

Per Air Force direction, to provide alternative gloves.

In 3.3.1.7, added new first sentence.

To more fully define the proper squeegees.

In 3.3.3.1(a) and elsewhere, replaced “refrigeration” with “cold storage.”

Consistency; to cover unrefrigerated storage such as dry ice.

viii

Revision Changes Reason for Change Approved Revision K (continued)

In 3.3.3.1(a), third sentence, replaced “for a minimum of two hours prior to opening the bags” with “above the dew point (free of surface condensation) prior to opening for use.”

To clarify proper procedure for opening bags prior to use.

In 3.3.3.1(a), rewrote fourth sentence.

Clarity.

In 3.3.3.1(e), changed “prepreg working life” to “material out time.”

Consistency of terminology.

In 3.3.3.1(f), changed “5 more days” to “120 unit hours.”

Clarity.

In 3.3.3.2(b), replaced “for two hours minimum prior to opening” with “above the dew point (free of surface condensation) prior to opening for use.”

To clarify proper procedure for opening bags prior to use.

In Table III [formerly Table I], in Note 6, appended to the end “when available from the supplier.”

Clarity.

Added 3.3.3.3, including a new Table IV; renumbered subsequent tables.

To define film adhesive

Added new 3.3.4; renumbered subsequent sections.

To define foam adhesive

Added new 3.3.5(a). To define single-stage sandwich fabrication.

Added CAUTION below 3.3.5(b) [formerly 3.3.4(a)] and 3.3.5(h) [formerly 3.3.4(g)].

To warn against overheating of prepreg during warming.

In 3.3.5(d) [formerly 3.3.4(c)], added third and fourth sentences.

Clarity.

ix

Revision Changes Reason for Change Approved Revision K (continued)

In 3.3.6(a) [formerly 3.3.5(a)], added “using separate cure cycle.”

Clarity.

In 3.3.6(c), (e) and (f) [formerly 3.3.5(c), (e) and (f)], made several minor changes.

Clarity.

In 3.3.6(e) [formerly 3.3.5(e)], changed “When multi-staging honeycomb sandwich structure...” to “When fabricating a multi-stage honeycomb sandwich structure...”

Clarity.

In 3.3.7(d) [formerly 3.3.6(a)(4)], changed “Teflon” to “parting.”

To permit non-Teflon parting films.

In 3.3.8.1 [formerly 3.3.7.1], replaced “TT-N-95 Ty. II, aliphatic naphtha” with “solvents per Section 3.2.2.7.”

To permit use of solvents other than aliphatic naphtha where appropriate.

In 3.3.8.2 [formerly 3.3.7.2], in first sentence, after “correct type,” added “including cell size, density, ribbon direction and thickness”; added third sentence in its entirety; added Note beneath section.

To ensure that all core parameters are verified prior to use; to permit use of solvent to aid in release of core from doubleback tape; to ensure removal of adhesive residue, if any.

In 3.3.8.6 [formerly 3.3.7.6], reworded end of second sentence (was “it is acceptably cured”).

Clarity.

In 3.3.8.7 [formerly 3.3.7.7], Method 1 (a), reworded sentence in entirety.

x

Revision Changes Reason for Change Approved Revision K (continued)

In 3.3.8.7 [formerly 3.3.7.7], Method 1 (b), first sentence, added “(if 0.03-lb./sq.-ft. weight is not available, consult with A- 10 SPO for alternative).”

To provide guidance of user to A-10 SPO if material is unavailable.

In 3.3.8.7 [formerly 3.3.7.7], Method 1, relettered item (d) as item (b) and relocated;

relettered subsequent items.

Clarity.

In Figure 6, changed designation of adhesive to “Film Adhesive (0.06 lb./sq. ft.)

per 3.2.1.3” (was “FM 123-2 Film Adhesive.”

To recognize the use of more than one adhesive type.

In 3.3.8.8 [formerly 3.3.7.8], in introductory paragraph, changed “used” to “required to prevent core movement or core crushing.”

Clarity.

In 3.3.8.8 [formerly 3.3.7.8], Method 1 (a), deleted first sentence in its entirety.

Clarity.

In Figure 7, added and identified the oversize trim line.

Clarity

Added new 3.3.9; renumbered subsequent sections.

To define thermocouple

In 3.3.10 [formerly 3.3.8], made several minor verbiage changes; in (c), added the second sentence.

Clarity; to ensure that the breather is smooth and not in contact with the bleeder system.

In 3.3.11(d) [formerly 3.3.9(d)], changed vacuum level to 22 inches of mercury minimum;

was 20.

Consistency with vacuum during cure.

In 3.3.11(e) [formerly 3.3.9(e)], changed “fabric” to “woven prepreg.”

xi

Revision Changes Reason for Change Approved Revision K (continued)

In 3.3.12 [formerly 3.3.10], in the introductory paragraph, changed second sentence (was “Cure time is the period after the part has reached that temperature.”).

Clarity.

In 3.3.12(a) [formerly 3.3.10(a)], changed vacuum level to 22 inches of mercury minimum; was 20.

Consistency with vacuum during cure.

In 3.3.12(c), (d) and (e) [formerly 3.3.10(c), (d) and (e)], specified leading and/or lagging thermocouples as applicable.

Clarity.

In Table V [formerly Table II], changed leading thermocouple value for 100°–190°F temperature range to 190°F (was 100°F).

To correct typo.

In 3.3.12(e) [formerly 3.3.10(e)], replaced third and fourth sentences in their entirety.

Clarity.

In 3.4.5(c), deleted Fiber-Resin 5318S and 5318C.

No longer available;

manufacturer no longer in business.

In 3.4.5(a) and (d), changed mixing instructions from specific proportions to “Mix per manufacturer’s directions.”

Consistency with other multi-part materials’ mixing instructions.

Retitled 4.2 as “Process Control Requirements” (was “Process Control”).

Clarity.

Retitled 4.2.1 as “Process Documentation” (was “Process Control Record”).

xii

Revision Changes Reason for Change Approved Revision K (continued)

In 4.2.1, replaced introductory paragraph [formerly 4.2.1(a)] in its entirety.

To ensure that process documentation is retained permanently within the work order.

Rewrote and reorganized 4.2.2 in its entirety.

To more fully define process control test panel requirements.

Deleted 4.2.2.4 in its entirety. No longer required.

In 4.3.3, changed “operation sheets” to “work orders.”

Consistency.

Retitled 4.3.4 as “Laminate and Sandwich Production Part Acceptability” (was “Sandwich Production Part Acceptability”).

Clarity.

In 4.3.4, deleted first introductory paragraph in its entirety; in the second paragraph, in two instances, replaced “sandwich” with “laminate or sandwich.”

To reflect the post-production environment;

clarity.

Retitled 4.3.4.1 as “Film Adhesive T-Peel Test Panels” (was “Film Adhesive Peel Test Panel”).

Clarity.

In 4.3.4.1, made minor verbiage changes to introductory paragraph.

Clarity.

In 4.3.4.1(a) through (d), updated certification requirements; changed table reference in S-F501 to Table VIII (was Table VII).

To ensure that only properly certified materials are used; table designation within S- F501 was changed.

In 4.4.3.2(b), changed figure reference to Figure 3; was Figure 6.

To correct typo.

Added new 4.5.1; renumbered

4.5.1 as 4.5.2; deleted original

4.5.2 in its entirety.

To coordinate test methods with C-M605.

xiii

Revision Changes Reason for Change Approved Revision K (continued)

Deleted 4.5.3 in its entirety. Per Air Force direction.

Added 6.3.2, 6.3.3, 6.3.4, 6.3.5 and 6.3.6.

To provide more definitions.

In Appendix A, Section A- 1.0(e), replaced solvent callouts with “solvent per Section 3.2.2.7” in two places.

To permit flexibility in use of appropriate solvents.

In Appendix A, rewrote Section A-3.3 in its entirety.

To require repair of punctures to be per MRB action only.

In Appendix A, added Sections A-3.8 and A-3.9.

To provide repair procedures for other forms of damage.

08/13/2019

In 1.0, added “or aramid” after “fiberglass” and before “woven fabric.”

Due to the use of a small amount of aramid fabric on the A-10.

M. Kassinger

In 2.1, added MIL-STD-130. MIL-STD-130 has been added to 3.3.1.8(d).

In 2.2, added S-F501. To correct an omission.

In 3.1.2, changed the beginning of the first sentence [was “Facilities...”].

Clarity, per Air Force

In 3.1.2, first sentence, after “contamination areas” added “(clean rooms).”

In 3.1.2, first sentence, after “ISO 14644-1” changed “and” to “or.”

In 3.1.2.1(h), added “vaping, e-cigarettes” to prohibitions in the layup area.

Per Air Force direction.

In 3.1.3.5, made minor verbiage changes.

Clarity and succinctness, per Air Force direction.

Added 3.1.3.6. Per Air Force direction.

xiv

Revision Changes Reason for Change Approved Revision L (continued)

In 3.2.1.1(a), changed beginning to “Aramid/epoxy”;

was “Kevlar/epoxy.”

To conform to the title and scope of C-M602.

In 3.2.1.1(c), added “Class III” after BMS 8-79 specification.

Proper designation, per Air Force direction.

In 3.2.1.3, rewrote 2/. Clarity, per Air Force

Added 3.2.1.9, Surfacing Film. Per Air Force direction.

In 3.2.2, deleted “substantiated by test data and....”

Per Air Force direction.

In 3.2.2.1(c), added heading “Perforated FEP film” with the existing two materials beneath.

Clarity, consistency.

In 3.2.2.3, added peel ply and manufacturer name and address.

Per Air Force direction.

In 3.2.2.4(a), deleted Airweave SS, replaced with Airweave N7 and N10.

SS is obsolete, N7 and N10 were recommended by the Air Force.

In 3.2.2.4(b), revised to read “Style 181, 1581, or 7781 glass fabric”; was “Type 181 glass fabric”; added Note.

To permit substitution of style 1581 or style 7781 for style 181, per Air Force direction.

In 3.2.2.5, added (d) RS 200 sealant tape.

Per Air Force direction.

In 3.2.2.6(d)(3), changed “mill” to “mil”; updated product numbers; added Touch N Tuff Blue 92-625; replaced supplier with manufacturer and provide address.

To correct a typo; to conform to latest manufacturer information; to provide an alternative glove; to provide manufacturer’s name and location.

Added 3.2.2.6(i), Grit Strip. To provide alternative tie-down method; per Air xv

Revision Changes Reason for Change Approved Revision L (continued)

In 3.3.1.7, first sentence, deleted “UHMW polyethylene or nylon 6-6”; deleted second and third sentences in their entirety.

Redundant, since squeegees of only those materials are listed in 3.2.2.6(h); not required since Teflon squeegees are not permitted.

In 3.3.1.8(d), added Note beneath.

To permit marking per MIL-STD-130, if applicable.

In 3.3.3.1(f), rewrote in entirety;

added Note beneath.

Per Air Force direction;

to direct user to 6.3.9 for definition of unit hour.

Reworded beginning of 3.3.3.2(d); was “General layup “splice” requirements of prepreg materials....”

Per Air Force direction.

In Table III, added NOTE 7. Per Air Force direction.

In Table IV, added second application for 0.060-lb./sq.-ft.

film adhesive.

Per Air Force direction.

Rewrote 3.3.3.3.7 in its entirety.

Per Air Force direction.

Added 3.3.3.3.7.1. To provide shelf life and temperature exposure information, per Air

Redesignated 3.3.4 as 3.3.3.4 and renumbered subsequent paragraphs accordingly.

Per Air Force direction.

Rewrote 3.3.3.4.4 [was 3.3.4.4] in its entirety.

Per Air Force direction.

Added new 3.3.4, new 3.3.4.1 and new Table V; reidentified previous Table V as Table VI.

All per Air Force xvi

Revision Changes Reason for Change Approved Revision L (continued)

In 3.3.4.3, second sentence, changed temperature and range to “250°F ± 10°F” [was “255°F ± 15°F”].

To agree with temperature and range in 3.3.9.6(e) [was 3.3.8.6(e)].

Rewrote 3.3.5(d) in its entirety;

modified Fig.1 dimension accordingly: to “0.75 inch” and moved right-hand dimension line to end of longest filler ply [was “1/2 to 1 inch,” to shorter filler ply].

Per Air Force direction.

In 3.3.5(f)(1), deleted “or equivalent.”

Per Air Force direction.

In 3.3.5(h), last sentence, deleted “and certified to the mechanical properties in accordance with MMM-A-132 and MIL-A 25463.”

Per Air Force direction.

In 3.3.5(h), added Note beneath limiting vacuum after core placement to 10 inches of mercury.

Per Air Force direction.

Rewrote 3.3.5(l) in its entirety. Clarity, per Air Force

Redesignated 3.3.5(m) as new 3.3.6, Single-Stage Solid Laminate Layup; renumbered subsequent sections.

Added new 3.3.5(m) and 3.3.7 [was 3.3.6] (g), to add optional use of SURFACE MASTER® 905.

Per Air Force direction.

In 3.3.6 [was 3.3.5(m)], first sentence, added Items c, f and m; in third sentence, changed “should” to “shall.”

To ensure proper fabrication; to mandate the use of peel ply per 3.2.2.3.

xvii

Revision Changes Reason for Change Approved Revision L (continued)

In 3.3.7(c) [was 3.3.6(c)], made third sentence, with slight modification, into a separate Caution statement.

Rewrote 3.3.7(e) [was 3.3.6(e)] in entirety.

Per Air Force direction.

In 3.3.7(e) [was 3.3.6(e)], added Note beneath limiting vacuum after core placement to 10 inches of mercury.

Per Air Force direction.

In 3.3.7(f) [was 3.3.6(f)], first sentence, deleted “and certified to the mechanical properties in accordance with MMM-A-132 and MIL-A 25463.”

Per Air Force direction.

In 3.3.7(f) [was 3.3.6(f)], replaced last sentence in its entirety with “See Table IV.”

Per Air Force direction.

In 3.3.8(a) [was 3.3.7(a)], changed “Kevlar” to “aramid”;

made the change to all instances of “Kevlar” in this document.

Consistency, per Air

In 3.3.8(c) [was 3.3.7(c)], added “partial” before “shop vacuum.”

In 3.3.8(g) [was 3.3.7(g)], added Note beneath limiting vacuum after core placement to 10 inches of mercury.

Per Air Force direction.

In 3.3.9.3(b) [was 3.3.8.3(b)], at end of second sentence, changed abrasive paper to “150-grit or finer” [was “280- or 320-grit”].

xviii

Revision Changes Reason for Change Approved Revision L (continued)

In 3.3.9.7 Method 1(a) [was

3.3.8.7 Method 1(a)], added

Note.

To require SPO approval to use adhesives other than FM 123-2 or EA9696, per Air Force

In 3.3.9.7 Method 1(b) [was

3.3.8.7 Method 1(b)], first

sentence, added “B-staged” after “pre-cured”.

In Figures 5, 6, 7, and 8, deleted method designations from their titles.

Per Air Force direction.

In 3.3.9.7 Method 1(b) [was

3.3.8.7 Method 1(b)], in first

sentence, changed parenthetical phrase to “(if 0.03-lb./sq.-ft. weight is not available, use 0.06-lb./sq.-ft.

weight film adhesive)” [was “(if 0.03-lb./sq.-ft. weight is not available, consult with A-10 SPO for alternative)”].

Per Air Force direction.

In 3.3.9.7 Method 1(c) [was

3.3.8.7 Method 1(c)], changed

temperature to “250°F” [was “240°F”].

Per Air Force direction.

Rewrote introductory paragraph of 3.3.9.8 [was 3.3.8.8] in its entirety.

Per Air Force direction.

Added fourth sentnce to

3.3.9.8 Method 1(a) [was

3.3.8.8 Method 1(a)].

To permit the use of Grit Strip to aid in core stabilization, per Air

In Figure 7, changed solid line to right of “Filler Plies” to an arrow and leader.

To correct error made during redrawing of figure.

Created new Figure 7A. To define the use of Grit Strip; per Air Force xix

Revision Changes Reason for Change Approved Revision L (continued)

In 3.3.11(c) [was 3.3.10(c)], first sentence, changed “Airweave SS” to “Airweave N7 or N10.”

Airweave SS is obsolete and has been replaced by Airweave N7 and N10.

In 3.3.12(a) [was 3.3.11(a)], at end of last sentence, changed to “1 inch Hg. in 1 minute” [was “5 inches Hg. in 1 minute”].

Per Air Force direction.

In 3.3.12(b) [was 3.3.11(b)], changed end of sentence to read “Tedlar film per Paragraph 3.2.2.1” [was “Tedlar moisture barrier film per Paragraph 3.2.2”].

Clarity and to correct typo.

In 3.3.12(d) [was 3.3.11(d)], changed vacuum requirement to 20 inches of mercury minimum [was 22 inches].

In 3.3.12(d) [was 3.3.11(d)], added Note beneath limiting vacuum after core placement to 10 inches of mercury.

Per Air Force direction.

In 3.3.12(h) [was 3.3.11(h)], beginning of second sentence, deleted “Teflon” from before “squeegee.”

Teflon squeegees are not permitted.

In Figure 9, deleted heatup ramp rate; deleted note 1/ in its entirety from beneath graph.

Both per Air Force

In 3.3.12(a) [was 3.3.11(a)], changed vacuum requirement to 20 inches of mercury minimum [was 22 inches];

changed all occurrences of vacuum to 20 inches of mercury minimum.

xx

Revision Changes Reason for Change Approved Revision L (continued)

In Table VI [was Table V], changed all values in right-hand “Leading Thermocouple” column to 100°F; deleted “(20-min. interval)” from the third “Leading Thermocouple” cell;

rewrote Notes 1/ and 3/ to reflect changes in table itself.

Per Air Force direction.

Relocated repair resins from

3.4.5 to 3.4.4.

Appropriate location for this information.

In 3.4.4(b) [was 3.4.5(b)], added Epocast 1619 A/B.

Omitted in error.

In 4.2.1(a), at end of sentence, changed “units” to “unit hours.”

Consistency.

In 4.2.1(f), at beginning of sentence, changed “Verification” to “Documentation.”

Per Air Force direction.

In 4.2.2, fourth sentence, deleted “concurrently (under the bag).”

Per Air Force direction.

In 4.2.2, fifth sentence, rewrote to require that process control panels contain the majority style, as well as the majority batch, of the material in a given autoclave load.

In 4.2.2, rewrote sixth sentence in its entirety.

In 4.2.2.2, at the beginning of the first sentence, deleted “type 1581 or type 7781.”

No longer required due to changes to 4.2.2.

In 4.2.2.2, first sentence, deleted “woven fabric laminate-faced.”

Per Air Force direction.

In 4.3.4.1, introductory statement, changed class of material to Cl. 2 [was Cl. 1].

To correct error.

xxi

Revision Changes Reason for Change Approved Revision L (continued)

In 4.3.4.1, deleted (a) through

(d) in entirety.

Redundant to 3.2.1.3.

In 4.4.6(b), added Note beneath.

Per Air Force direction.

Added 4.4.13, Core Cell Mark- Off.

Per Air Force direction.

In 6.3, added 6.3.7, 6.3.8 and 6.3.9.

To define the terms “prepreg,” “laminate” and “unit hour,” per Air Force

In Appendix A, A-1.0(b) Note, changed “type 181” to “style 1581 or style 7781.”

Type 181 is obsolete;

styles 1581 and 7781 are suitable replacements.

In Appendix A, A-1.0(c), at end of first sentence, added “and other NDI methods.”

Per Air Force direction.

In Appendix A, A-3.5(a), changed “0.10” to 0.010.”

Per Air Force direction.

In Appendix A, deleted A-3.7 in its entirety; reidentified subsequent sections.

Per Air Force direction.

In Appendix A, A-3.7 [was A- 3.8], title and text, changed “0.100 inch deep by 3 square inches” to “0.500 inch in diameter x 0.020 inch deep.”

To correct typos.

xxii

TABLE OF CONTENTS

TABLE OF REVISIONS ...................................................................................................... ii LIST OF TABLES ........................................................................................................... xxv

LIST OF FIGURES ......................................................................................................... xxvi FOREWORD ................................................................................................................. xxvii

1.0 SCOPE

2.0 APPLICABLE DOCUMENTS

2.1 Government Documents

2.2 Non-Government Documents

3.0 REQUIREMENTS

3.1 Equipment, Facilities and Tooling

3.1.1 Equipment

3.1.2 Facilities

3.1.3 Tooling

3.2 Materials

3.2.1 Primary Materials

3.2.2 Secondary Materials

3.3 Required Procedures and Operations

3.3.1 General Requirements

3.3.2 Preparation of Molds

3.3.3 Prepreg Material

3.3.4 Material Handling Life

3.3.5 Single-Stage Sandwich Fabrication

3.3.6 Single-Stage Solid Laminate Layup

3.3.7 Multiple-Stage Layup

3.3.8 Debulking

3.3.9 Core Preparation

3.3.10 Thermocouple Requirements

3.3.11 Application of Edge Bleeders and Breathers

3.3.12 Application of Pressure (Bagging)

3.3.13 Cure

3.4 Recommended Procedures

xxiii

3.4.1 In-Process Correction

3.4.2 In-Process Correction of Core

3.4.3 Repair Resin Systems

3.4.4 Material and Methods

3.4.5 Repaired Parts

3.5 Certification

4.0 QUALITY ASSURANCE

4.1 Responsibility for Inspection

4.2 Process Control

4.2.1 Process Control Record

4.2.2 Process Control Test Panels

4.3 Monitoring Procedures for Materials

4.4 Certification

4.4.1 Personnel

4.4.2 Monitoring Equipment

4.4.3 Production Assembly Evaluation

4.4.4 Fraying and Burrs

4.4.5 Voids

4.4.6 Wrinkling or Reinforcement Distortion

4.4.7 Surface Condition

4.4.8 Adhesive Patches

4.4.9 Skin Marking

4.4.10 Skin-to-Core Bond

4.4.11 Drilling and Trimming

4.4.12 Delamination

4.4.13 Core Cell Mark-Off

4.5 Test Methods

5.0 PREPARATION FOR DELIVERY

6.0 NOTES

6.1 Intended Use

6.2 General Information

6.3 Definitions

xxiv

APPENDIX A: REPAIR AND WET LAYUP PROCEDURES – FIBERGLASS, EPOXY

RESIN

A-1.0 Replacement of Damaged Plies – Wet Layup A-2.0 Repair of Damaged Core A-3.0 Minor Repairs

A-3.1 Repair of Surface Scratches – Not Extending Through First Ply of the Reinforcement

A-3.2 Repair of Gouges Less Than 1/8 Inch in Width and 3 Inches in Length Extending Through One or More Plies but Not Exposing the Core

A-3.3 Repair of Punctures

A-3.4 Repair of Delaminations

A-3.5 Removal of Surface Resin Over Core

A-3.6 Removal of Surface Resin Ridges Over Solid Laminate

A-3.7 Core Depressions Less Than 0.500 Inch in Diameter x 0.020 Inch Deep

A-3.8 Repair of Honeycomb Core Separations of Seven or Less Contiguous Cells xxv

LIST OF TABLES

Table I. Cleaning Time Intervals

Table II. Storage Conditions and Life

Table III: Splice Requirements

Table IV. Applicable Weight of Film Adhesive

Table V: Material Handling Life

Table VI: Cure Schedule xxvi

LIST OF FIGURES

Figure 1: Staggered Filler Plies

Figure 2: Solid Buildup Edge Band Configuration (Ply by Ply)

Figure 3: Honeycomb Core Edge Waviness

Figure 4: Typical Core Bevel

Figure 5: Subassembly Bond Configuration, Scarf Joint, Septum Bond

Figure 6: Septum Bonding of Core

Figure 7: Honeycomb Core Stabilization

Figure 7A: Use of Grit Strip to Aid in Honeycomb Core Stabilization

Figure 8: Honeycomb Core Stabilization

Figure 9: Cure Cycle – Laminate and Sandwich

Figure 10: Example of Cure Cycle Showing Rate of Temperature Rise

Figure 11: Core Nodes xxvii

FOREWORD

This specification has been reviewed for EPA 17 toxic chemicals, SARA 313-listed pollutants, as well as ozone depleting substances. All ozone depleting substances have been eliminated.

Hazardous air pollutants and toxic materials have been eliminated or minimized to comply with the Air Force Pollution Prevention Program, AFI 32-7080. A reasonable effort has been made to eliminate rather than minimize pollutants and to use environmentally acceptable substitutes.

Certain substitutions, however, have not been made due to their potential unknown deleterious effects on the A-10 weapon system.

Government and other industry specifications called out in this specification have been reviewed. (See Applicable Documents section of this specification for documents reviewed.)

Ozone depleting substances and hazardous materials have been identified and reported on in accordance with Contract F04606-96-D-0021 CET SM-ALC/LAF 96-A10-Al-9 D.O. 0016.

It must be understood that the materials, methods, applications and processes can contain toxic and hazardous materials. It is the responsibility of the user to ensure safe and proper use in accordance with all applicable OSHA, EPA, Federal, state and local regulations.

1.0 SCOPE

This specification establishes the requirements for the fabrication of laminate and honeycomb sandwich structural parts with a 250°F curing epoxy resin preimpregnated fiberglass or aramid woven fabric capable of withstanding a –65 to 180°F service temperature range.

2.0 APPLICABLE DOCUMENTS

The following documents of the issue in effect on the effective date of contract shall form part of this specification. In the event of conflict between the contractual documents referenced herein and the requirements of this specification, the contractual documents referenced herein shall govern.

2.1 Government Documents

Federal

MMM-A-132 Adhesives, Heat Resistant, Airframe Structural, Metal-to-Metal

TT-N-95 Naphtha; Aliphatic

Military

MIL-STD-130 Identification Marking of U.S. Military Property

T.O. 1-1-690 Technical Manual, General Advanced Composite Repair Processes

2.2 Non-Government Documents

A-10 Program

162S900718 Inspection of Composite Structure; S-F502 Supplement A-10 (WRP)

B-M101 Adhesive, Expandable, Honeycomb Core Splice

C-M602 Aramid Fabrics Preimpregnated with Epoxy Resin, 250°F (121°C) Curing

C-M605 Glass Fabrics Preimpregnated with Epoxy Resin, 250°F (121°C) Curing

G-S901 Non-Destructive Inspection of Composite Laminates and Bonded Parts

P-M601 Core, Fibrous Nylon Base, Phenolic Coated

S-F501 Fabrication of 250°F Curing Epoxy Resin Composite Laminate and Honeycomb Sandwich Parts

Z-P801 Storage, Handling, Shipping

Industry

AMS 3819 Cloths, Cleaning, for Aircraft Primary and Secondary Structural Surfaces

AMS-A-25463 Adhesive, Film Form, Metallic Structural Sandwich Construction

AMS-C-8073 Core Material, Plastic Honeycomb, Laminated Glass Fabric Base, for Aircraft Structural and Electronic Applications

AMS-C-9084 Cloth, Glass, Finished, For Resin Laminates

ASTM D329 Standard Specification for Acetone

ASTM D740 Standard Specification for Methyl Ethyl Ketone

BMS 8-79 Glass Fabric Preimpregnated Epoxy Resin, Low Temperature Curing

3.0 REQUIREMENTS

3.1 Equipment, Facilities and Tooling

3.1.1 Equipment

3.1.1.1 An autoclave capable of maintaining temperatures and pressures within the requirements of this specification.

3.1.1.2 A refrigerator-freezer capable of maintaining temperatures of 0°F (–17.8°C) or less.

3.1.1.3 A vacuum system capable of utilization within the requirements of this specification.

3.1.1.4 Air circulating ovens capable of maintaining a temperature range of 100°F to 260°F and holding a given temperature to ±10°F.

3.1.2 Facilities

Manufacturing controlled contamination areas (clean rooms) shall be in accordance with Class 9 of ISO 14644-1 or, when required for Air Force field or depot repair activities, facilities shall be in conformance with T.O. 1-1-690. Subparagraphs and/or statements subordinate to this section delineate specific facilities requirements that shall apply when deemed over and above the ISO and/or T.O. requirements.

3.1.2.1 The application of epoxy-prepreg, honeycomb core, adhesives, etc. shall be conducted in an environmentally controlled area where visible dust or dirt shall be removed in accordance with a clean room housekeeping schedule.

Operations performed per this specification, from prepreg layup through assembly for final bonding, shall be conducted in a controlled contamination area as follows:

(a) Filter all incoming air. Periodically check, clean or replace filters to ensure proper operation.

(b) Maintain a positive air pressure differential, such that unfiltered air does not enter the area.

Air pressure monitoring equipment capable of verifying the pressure differential shall be installed and accessible for inspection within the controlled area.

(c) Enclosed areas are required. Keep doors and other openings closed when not in use.

(d) Seal and/or cover floors with non-flaking, easily cleaned material, such as plastic, paint, vinyl tile, etc.

(e) Only the following methods may be used for cleaning within the controlled contamination areas:

(1) Water mopping – Use mops wet or dampened with water.

(2) Vacuuming – The exhaust air must either be vented outside the limited contamination area or filtered to at least the same degree as the incoming air for the area.

(3) Chemical mopping – Use mops commercially treated with either propylene glycol or slightly tacky epoxy resin.

(f) Cleaning is required when visual inspection shows any accumulated dust, dirt, or other contamination, according to the following inspection schedule, except that the maximum time interval between cleaning operations shall not exceed the limits specified in Table I.

Table I. Cleaning Time Intervals

Items Inspection Schedule

Maximum Cleaning Time Interval

Equipment, tables, floors, etc. No Inspection Required 24 hours

Walls from floor to 7-ft. height No Inspection Required 30 days

All walls above 7 ft., ceiling, beams, overhead fixtures, lights, etc. 30 days 6 months

(g) Do not allow internal combustion engines within the areas.

(h) Do not permit smoking, vaping, e-cigarettes, or eating in the areas.

(i) All materials, tools, parts, or equipment taken into the areas shall be free of dirt, grease, oil or other contaminants detrimental to adhesion.

(j) Do not permit processes or operations that produce uncontrolled spray, dust, fumes, or particulate matter in the area.

(k) The temperature shall be 65°F to 85°F and the maximum relative humidity shall not exceed 65% in the controlled contamination area.

(I) Keep the controlled contamination area used for prepreg layup and structural bonding segregated from other fabrication areas.

(m) Do not use waxes, compounds containing uncured silicone, or any material detrimental to adhesion in the controlled contamination area.

3.1.3 Tooling

3.1.3.1 Tools may be fabricated of any suitable material that will withstand the pressures and temperatures of the cure cycle and not exhibit leaking or outgassing or become dimensionally unstable.

3.1.3.2 The basic tooling requirements for prepreg and adhesive curing are to have tools that control the location of the details while allowing uniform pressure to be applied to the assembly during the bonding operation.

3.1.3.3 When a flexible diaphragm is used to apply pressure, care must be taken to prevent bridging. Bridging will not allow the proper transmission of pressure. Free floating pressure bars or rings may be used where bridging may occur. They may also be used where a local increase in pressure is required because of a specific part design or where the tolerances and bond line of the part are critical.

3.1.3.4 Tools and fixtures used to locate details to be bonded shall hold details in proper alignment during the bonding operation. These tools and fixtures shall permit the transfer of pressure to all surfaces being bonded and shall produce a bond line thickness within the required limits where specified on Engineering drawings.

3.1.3.5 Tools should be designed to avoid the problem of thermal expansion between the tool and the part being fabricated.

3.1.3.6 Tools should allow the proper transfer of heat to the part to support the cure requirements of this specification.

3.2 Materials

3.2.1 Primary Materials

Primary materials make up the basic structure of the fabricated part.

3.2.1.1 Prepreg Materials

(a) Aramid/epoxy prepreg in accordance with C-M602.

(b) Fiberglass/epoxy prepreg in accordance with C-M605.

(c) Fiberglass/epoxy prepreg in accordance with BMS 8-79, Class III.

3.2.1.2 Non-Metallic Core

(a) Nylon fiber (Nomex), phenolic coated core in accordance with P-M601.

(b) Fiberglass, phenolic core in accordance with AMS-C-8073.

3.2.1.3 Film Adhesives

(a) FM® 123-2 1/

0.06 psf, purple, 0.011 nom. thk.

Cytec Industries, Inc.

Engineered Materials 1300 Revolution Street Havre de Grace, MD 21078-3800

(b) FM® 300-2K 2/

0.08 psf, red, 0.013 nom. thk.

Cytec Industries, Inc.

Engineered Materials 1300 Revolution Street Havre de Grace, MD 21078-3800

(c) EA9628NW 2/

0.045 psf, tan, 0.007 nom. thk.

0.060 psf, yellow, 0.010 nom. thk.

0.080 psf, red, 0.012 nom. thk.

0.085 psf, cream, 0.014 nom. thk.

Henkel Aerospace 2850 Willow Pass Road PO Box 312 Bay Point, CA 94565-3237

(d) EA9696NW 2/

0.060 psf, purple/violet, 0.010 nom. thk.

0.085 psf, white, 0.014 nom. thk.

Henkel Aerospace 2850 Willow Pass Road PO Box 312 Bay Point, CA 94565-3237

1/ Certified to MMM-A-132 Type I, Class 2; AMS-A-25463 Type 1, Class 2; and S-F501 Table VIII mechanical properties.

2/ Certified only to the mechanical properties that apply to Type 1, Class 2 materials per MMM-A-132 and AMS-A-25463, and S-F501 Table VIII mechanical properties.

NOTES: FM 123-2, EA9628NW and EA9696NW certified to the requirements of S-F501 also meet the procurement requirements of S-F502.

Psf = pounds per square foot of adhesive.

Nom. thk. = nominal thickness of uncured adhesive, in inches.

3.2.1.4 Core Splice Adhesive Foam. Structural adhesive foams in accordance with B-M101.

3.2.1.5 Identification and Storage of Adhesive System

3.2.1.5.1 Each roll of adhesive shall be identified with items of information listed below. Rolls of film adhesive and foam adhesive sheets shall contain the following information both inside and outside the package:

(a) Specification number (S-F502).

(b) Supplier’s product designation.

(c) Supplier’s name and address.

(d) Supplier’s batch and roll number.

(e) Date of manufacture.

(f) Purchase order number.

(g) Quantity.

(h) Distributor’s name and address, if applicable.

(i) Each individual package or roll must be labeled with storage life expiration tags.

3.2.1.5.2 Each adhesive shall be shipped in such a manner that the adhesive temperature is below 0°F.

3.2.1.5.3 After identification of packages by the manufacturer, materials shall be immediately placed in cold storage. The storage conditions and maximum storage life are given in Table II.

Material Temperature Storage Life Film Adhesive Below 0°F 1/ 2/ 3/

Foam Adhesive Below 0°F 6 months

1/ Henkel (Hysol) EA9628NW and EA9696NW film adhesive shall be stored at or below 0°F for twelve (12) months maximum. The material may be re-evaluated for up to two additional 3-month storage lives, per lap shear requirements of Table VIII of S-F501.

2/ Cytec Solvay FM 300-2K film adhesive shall be stored at or below 0°F for twelve (12) months maximum. The material may be re-evaluated for up to two additional 3-month storage lives per the lap shear requirements of Table VIII of S-F501.

3/ Cytec Solvay FM 123-2 film adhesive shall be stored at or below 0°F for six (6) months maximum. The material may be re-evaluated for up to two additional 3-month storage lives per the lap shear requirements of Table VIII of S-F501.

Table II. Storage Conditions and Life

3.2.1.6 Syntactic Adhesives

(a) Epocast 1619 A/B Huntsman Corporation 10003 Woodloch Forest Drive The Woodlands, TX 77380

(b) Epocast 167 A/B (pourable) Huntsman Corporation 10003 Woodloch Forest Drive The Woodlands, TX 77380

(c) Corfil 615 (paste); curing agent ‘z’ Cytec Industries, Inc.

Engineered Materials 1300 Revolution Street Havre de Grace, MD 21078-3800

3.2.1.7 Sealing Film

(a) Tedlar Film (Bondable)

(1) Transparent TTR10 BG3 E.I. DuPont de Nemours Fluoroproducts 1007 Market Street Wilmington, DE 19898-1100 American Durafilm 55 Boynton Road PO Box 6770 Holliston, MA 01746-1460

(2) Gray TGY20 BE3 E.I. DuPont de Nemours Fluoroproducts 1007 Market Street Wilmington, DE 19898-1100 American Durafilm 55 Boynton Road PO Box 6770 Holliston, MA 01746-1460

(3) White TWH20 BE3 E.I. DuPont de Nemours Fluoroproducts 1007 Market Street Wilmington, DE 19898-1100 American Durafilm 55 Boynton Road PO Box 6770 Holliston, MA 01746-1460

3.2.1.8 Core Stabilization Material

(a) DURITE™ Resin SC-1008 Hexion, Inc.

180 East Broad Street Columbus, OH 43215-3707

3.2.1.9 Surfacing Film

(a) SURFACE MASTER® 905 Solvay Composite Materials Headquarters 4500 McGinnis Ferry Road Alpharetta, GA 30005-3914

3.2.2 Secondary Materials

Secondary materials are used only to assist in the fabrication process and do not make up any part of the fabricated structure and may be substituted for, when approved by the A-10 SPO, providing the final structure meets the requirements of this specification and the Engineering drawing.

3.2.2.1 Parting Film Materials

(a) Non-bondable Tedlar (PVF) E.I. DuPont de Nemours Fluoroproducts 1007 Market Street Wilmington, DE 19898-1100 American Durafilm 55 Boynton Road PO Box 6770 Holliston, MA 01746-1460

(b) FEP film, 1 mil E.I. DuPont de Nemours Fluoroproducts 1007 Market Street Wilmington, DE 19898-1100 American Durafilm 55 Boynton Road PO Box 6770 Holliston, MA 01746-1460

(c) Perforated FEP film A4000P3 A4000P5

Airtech International, Inc.

5700 Skylab Road Huntington Beach, CA 92647-2055

3.2.2.2 Mold Releases or Parting Agents

(a) Frekote® 48-NC Henkel Loctite Corporation One Henkel Way Rocky Hill, CT 06067-3581

(b) Frekote® C-200/C-210 Henkel Loctite Corporation One Henkel Way Rocky Hill, CT 06067-3581

(c) Frekote® 710-NC Henkel Loctite Corporation One Henkel Way Rocky Hill, CT 06067-3581

(d) Mold Release 225 Lilly-RAM Chemical Co., LLC PO Box 3337 Ontario, CA 91761-9998

3.2.2.3 Peel Ply Materials

Code 60001/Style 56009 with Finish 060 (natural scoured and heat-set)

Precision Fabrics Group 301 North Elm Street, Suite 600 Greensboro, NC 27401-2185

3.2.2.4 Bleeder/Breather Materials

(a) Breather Airweave N7 Airweave N10

Airtech International, Inc.

5700 Skylab Road Huntington Beach, CA 92647-2055

(b) Style 181, 1581, or 7781 glass fabric NOTE: Where style 181 cloth is called out on a drawing, style 1581 or style 7781, which have similar properties to style 181, may be substituted, depending upon availability from prepreg suppliers.

AMS-C-9084

(c) Fiberglass tape AMS-C-9084

(d) Bleeder Lease® A nylon coated with nontransferring release agent

Airtech International, Inc.

5700 Skylab Road Huntington Beach, CA 92647-2055

(e) Bleeder Lease® B Airtech International, Inc.

5700 Skylab Road Huntington Beach, CA 92647-2055

(f) Bleeder Lease® E Airtech International, Inc.

5700 Skylab Road Huntington Beach, CA 92647-2055

3.2.2.5 Vacuum Bag Sealing Compounds

(a) GS-43MR Airtech International, Inc.

5700 Skylab Road Huntington Beach, CA 92647-2055

(b) Schnee-Morehead 5144 extruded sealing compound

ITW Polymers Sealants 111 S. Nursery Road Irving, TX 75060-3153

(c) Schnee-Morehead 5126 ITW Polymers Sealants 111 S. Nursery Road Irving, TX 75060-3153

(d) RS 200 sealant tape Solvay Composite Materials Headquarters 4500 McGinnis Ferry Road Alpharetta, GA 30005-3914

3.2.2.6 Miscellaneous Materials

(a) Double-backed pressure-sensitive tape, non-silicone type

Any source

(b) Flash-breaker tape, thickness optional Airtech International, Inc.

5700 Skylab Road Huntington Beach, CA 92647-2055

(c) Sharpie no. 30000 (Fine Point Markers) Newell Rubbermaid Office Products 2707 Butterfield Road Oak Brook, IL 60523-1278

(d) Gloves

(1) Clean, white cotton gloves NOTE: Materials shall contain less than

0.75% oil by acetone extraction and less than 1.2% oil by water extraction. Laundered materials shall not be used.

Any source

(2) White cotton glove, style L31M-105 American Glove Company 98 Alpine Street Lyerly, GA 30730-3087

(3) Thin-mil gloves (nitrile), Ansell Touch N Tuff 92-600, S, M, L, XL Touch N Tuff Blue 92-625, S, M, L, XL

Ansell Limited Corporate Headquarters 200 Schulz Drive Red Bank, NJ 07701-6776

(4) Nitrile exam glove, 55082-55084, powder free, textured, purple

55082, Small 55083, Large 55084, Extra Large

Kimberly-Clark Professional 1400 Holcomb Bridge Road Roswell, GA 30076-2190

(e) Pressure-sensitive tape, non-silicone adhesive type

Any source

(f) Thermocouple wire, iron-constantan, Type J Any source

(g) Cloths, AMS 3819 Cl. 1, Gr. A, Form 1 e.g., Rymplecloth #301, 100% purified cotton

Any source suggested sources:

1) American Fiber and Finishing, Inc.

225 North Depot Street Albemarle, NC 28001-3914

2) John R. Lyman Company 60 Depot Street Chicopee, MA 01013-1251

(h) Squeegees, UHMW polyethylene or nylon 6-6

Any source

(i) Aluminum Grit Strip De-Comp Composites, Inc.

1519 Eastgate Drive Cleveland, OK 74020-6789

3.2.2.7 Solvents

(a) Acetone ASTM D329 Any source

(b) Aliphatic Naphtha, TT-N-95 Ty. II NOTE: Each batch of aliphatic naphtha shall successfully pass the acrylic crazing test outlined in TT-N-95, Section 4.3.7.

Shell Chemical Company PO Box 2463 Houston, TX 77252-2463 Part No. ShellSol W HT

MACH-DYNAMICS

494 Main Street Susquehanna, PA 18847-7979

(c) Methyl Propyl Ketone (MPK), Technical Grade [90.0% by wt. min. MPK/10.0% by wt.

max. MIBK]

Eastman Chemical Company PO Box 431 Kingsport, TN 37662-5280

(d) Methyl Propyl Ketone (MPK), Ultra High Purity [99.5% by wt. min. MPK/0.5% by wt.

max. MIBK]

Eastman Chemical Company PO Box 431 Kingsport, TN 37662-5280

(e) Methyl Ethyl Ketone (MEK) ASTM D740 Any source

(f) Methyl Isobutyl Ketone (MIBK) ASTM D1153 Any source

(g) Isopropyl Alcohol TT-I-735 Gr. A Any source

3.2.2.8 Repair Materials

(a) Epocast 50-A1 resin Hardener 9816 Hardener 946

Huntsman Corporation 10003 Woodloch Forest Drive The Woodlands, TX 77380

(b) Epocast 167 A/B epoxy syntactic Huntsman Corporation 10003 Woodloch Forest Drive The Woodlands, TX 77380

(c) Epibond 156-1 A/B epoxy paste adhesive (replaces Epibond 156 A/B)

Huntsman Corporation 10003 Woodloch Forest Drive The Woodlands, TX 77380

(d) Epocast 1619 A/B epoxy syntactic, pourable (replaces Epocast 168 A/B)

Huntsman Corporation 10003 Woodloch Forest Drive The Woodlands, TX 77380

(e) EPONTM 815C *, EPONTM 828 Curing agent EPIKURE™ 3282 (was curing agent “T”) or Curing agent EPIKURE™ 3234 (similar to curing agent “U”)

* EPONTM 815C, replaces EPONTM 815

Hexion, Inc.

180 East Broad Street Columbus, OH 43215-3707

3.3 Required Procedures and Operations

3.3.1 General Requirements

3.3.1.1 Operation sheets shall be prepared for each part or assembly and shall control, in accordance with this specification, the following operations:

(a) Tool and mold preparation.

(b) Material out-time recording.

(c) Material handling and cutting.

(d) Individual steps and sequence of the fabrication process, including key inspection points throughout the process.

(e) Last date permissible for cure of adhesives, potting compounds, and prepreg materials.

(f) A quality control record of all anomalies in the fabrication process.

(g) Part and/or assembly identification.

(h) Final inspection record.

3.3.1.1.1 The requirements of the applicable Engineering drawings as implemented by this specification shall apply.

3.3.1.2 All Quality Assurance provisions of this specification as they relate to specific constructions shall be met.

3.3.1.3 Primary materials other than those specified herein shall not be used in the fabrication of parts in accordance with this specification.

3.3.1.4 In-process correction or repair is permitted within the limits specified for each specific repair or correction. Repairs or corrections beyond the specified limitations are not permitted.

Discrepancies exceeding the specified limits for…