NATIONAL AEROSPACE STANDARD

© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

FED. SUPPLY CLASS

5310
1. SCOPE

1.1 Scope. This specification covers self-locking nuts for use in temperatures of 250 °F, 450 °F, and 800 °F (see
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

6.1).

2. APPLICABLE DOCUMENTS

2.1 General. The documents listed in this section are specified in sections 3 and 4 of this specification. This section
does not include documents cited in other sections of this specification or recommended for additional information or as
examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they
must meet all specified requirements and documents cited in sections 3 and 4 of this specification, whether or not they are
listed.
ARLINGTON, VA 22209
1000 WILSON BLVD.

2.1.1 Specifications, standards, and handbooks. The following specifications, standards, and handbooks form a part
of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those listed in
the issue of the Department of Defense Index of Specifications and Standards (DODISS) and supplement thereto, cited in the
solicitation (see 6.2).

SPECIFICATIONS

FEDERAL

AMS-QQ-A-250/12 Aluminum Alloy 7075, Plate and Sheet

GGG-W-636 Wrench (Box, Open End, and Combination)
GGG-W-641 Wrench, Socket (and Sockets, Handles, and Attachments for Socket Wrenches, Hand)
TT-E-751 Ethyl Acetate, Technical
TT-I-735 Isopropyl Alcohol
TT-N-97 Naphtha, Aromatic

REVISION DATE: DECEMBER 21, 2012

Copies can be obtained from the Department of Defense Single Stock Point (DODSSP). http://dodssp.daps.dla.mil
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

MILITARY
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

MIL-DTL-5541 Chemical Conversion Coatings on Aluminum and Aluminum Alloys

MIL-S-7742 Screw Threads, Standard, Optimum Selected Series: General Specification for
MIL-A-8625 Anodic Coatings, for Aluminum and Aluminum Alloys
AMS-S-8802 Sealing Compound, Temperature-Resistant Integral Fuel Tanks and Fuel Cavities, High-Adhesion
AS8879 Screw Threads, Controlled Radius Root with Increased Minor Diameter, General Specification for
MIL-PRF-23377 Primer Coating, Epoxy Polyamide, Chemical and Solvent Resistant
MIL-PRF-81733 Sealing and Coating Compound, Corrosion Inhibitive

Copies can be obtained from the Department of Defense Single Stock Point (DODSSP). http://dodssp.daps.dla.mil

ISSUE DATE: SEPTEMBER 1999

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REVISION DATE.

THE INITIAL RELEASE OF THIS DOCUMENT SUPERSEDES MLL-DTL-25027 REVISION H, AMENDMENT 1.

THIRD CUSTODIAN REVISION

ANGLE
PROJECTION NATIONAL AEROSPACE STANDARDS COMMITTEE 1
PROCUREMENT TITLE CLASSIFICATION
FORM 09-01

SPECIFICATION PART STANDARD

NUT, SELF-LOCKING, 250 °F, 450 °F, AND 800 °F
NONE NASM25027
SHEET 1 OF 26
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANYlicense from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY
PARTICULAR THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

STANDARDS/HANDBOOKS

MILITARY
MIL-STD-129 Marking for Shipment and Storage
AN503 Screw and Machine, Drilled Fillister Head, Coarse Thread
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

MIL-HDBK-57 Fastener Manufacturers’ Identification Symbols, Listing of

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Copies can be obtained from the Department of Defense Single Stock Point (DODSSP). http://dodssp.daps.dla.mil

2.2 Non-Government publications. The following document(s) form a part of this document to the extent
specified herein. Unless otherwise specified, the issues of the documents which the DoD adopted are those listed in the issue of
the DoDISS cited in the solicitation (see 6.2).

Aerospace Industries Association

ARLINGTON, VA 22209

NAS9703 THRU NAS9724 Bolt, Hex Head, Alloy Steel, Close Tolerance, Minimum Major, Long Threads.
1000 WILSON BLVD.

NAS9603 THRU NAS9624 Bolt, Hex Head, A286 Cres, Close Tolerance, Minimum Major, Long Threads.
NAS1589 Fasteners, Threaded, Corrosion and Heat Resistant, 1200° F
NASM6812 Bolt, Aircraft
NAS410 Qualification of Inspection, Personnel (Magnetic Particle and Penetrant)
NASM1312-1 Salt Spray
NASM1312-7 Vibration
NASM1312-8 Tensile Strength
NASM1312-9 Stress Corrosion
NASM1312-14 Stress Durability (Internally Threaded Fasteners)
NASM1312-31 Fastener Test Methods, Method 31, Torque

Copies can be obtained from the Aerospace Industries Association, 1000 Wilson Blvd., Suite 1700, Arlington, VA
22209. www.aia-aerospace.org

ASME
ASME B46.1 Surface Texture (Surface Roughness, Waviness and Lay)

Copies can be obtained from ASME, Three Park Ave., New York, NY 10016-5990. www.asme.org
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

American Society for Quality

ASQ Z1.4 Sampling Procedures and Tables for Inspection by Attributes

Copies can be obtained from the American Society for Quality, 600 North Plankinton Ave., Milwaukee, WI 53203.
www.asq.org

SAE INTERNATIONAL
AMS-QQ-P-416 Plating, Cadmium (Electrodeposited)
AMS2410 Silver Plating, Nickel Strike - High Bake
AMS2411 Plating, Silver, for High Temperature Applications
AMS2750 Pyrometry
AS1310 Fastener Torque for Threaded Applications, Definitions of
AS5272 Lubricant, Solid Film, Heat Cured, Corrosion Inhibiting

Copies can be obtained from SAE International, 400 Commonwealth Dr., Warrendale, PA 15096-0001. www.sae.org
REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 2
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

ASTM International
ASTM A 342/A 342M Permeability of Feebly Magnetic Materials, Test Methods For
ASTM A967 Chemical Passivation Treatments for Stainless Steel Parts
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

ASTM D740 Methyl Ethyl Ketone

ASTM D3951 Packaging, Commercial
ASTM E1417 Liquid Penetrant Examination, Standard Practice For
ASTM E1444 Magnetic Particle Examination, Standard Practice For

Copies can be obtained from ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA
19428-2959. www.astm.org

2.3 Order of precedence. In the event of a conflict between the text of this document and the references cited
ARLINGTON, VA 22209

herein (except for related associated detail specifications, specification sheet, or MS sheets), the text of this document takes
1000 WILSON BLVD.

precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has
been obtained.

3. REQUIREMENTS

3.1 Part Standards. The individual item requirements shall be as specified herein and in accordance with the
applicable Part Standards. In the event of any conflict between requirements of this specification and the standard, the latter
shall govern.

3.2 Qualification. The nut manufacturer shall be responsible for conducting qualification tests and furnishing part
drawings, certified qualification test reports (if required by the purchaser) and test samples. The nuts furnished under this
specification shall be produced using the same manufacturing methods as used to produce nuts that have passed qualification
tests. The purchaser may apply any or all tests specified herein to any product represented as meeting this specification, at any
time, to verify conformance.

3.2.1 Retention of qualification. To maintain product qualification status, manufacturers shall maintain on file, a
certified qualification test report (See 4.3.2) available for inspection by the procuring activity. The retention of a certified
qualification test report by the manufacturer signifies that the manufacturer has demonstrated compliance to the qualification
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

requirements of this specification. Products previously qualified through government-certified qualification tests and reports
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

shall be considered qualified to this specification.

3.3 Materials.

3.3.1 250 °F nuts. The threaded and load-carrying elements of the 250 °F nuts shall be fabricated from noncorrosion
resistant steel, corrosion-resistant steel, aluminum alloy, nickel-copper alloy or copper-base alloy in accordance with the
applicable standard. The sulfur or phosphorus content of noncorrosion-resistant steel shall not be greater than .050 percent by
weight for thread sizes. 164-32 inch and above when the nut is heat treated to 36 HRc or greater.

3.3.2 450 °F nuts. The threaded and load-carrying elements of the 450 °F nuts shall be fabricated from
noncorrosion-resistant steel or corrosion-resistant steel. The sulfur content or the phosphorus content of noncorrosion-resistant
steel shall not be greater than. 050 percent by weight for thread sizes .164-32 and above when the nut is heat treated to 36
HRc or greater.

3.3.3 800 °F nuts. The 800 ºF nuts shall be fabricated from corrosion-resistant steel.

3.4 Design. Nut design shall conform to the applicable standard.

REVISION DATE.

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REVISION

1
FORM 09-01

NASM25027
SHEET 3
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

3.5 Construction. The self-locking nut or nut element shall be a self-contained unit, including the self-locking
device. The locking device shall not operate by separate movement from the installation and shall not depend on pressure on
the bearing surface for locking action. Tool marks resulting from producing the self-locking feature shall blend smoothly without
abrupt change. For wrenchable nuts, dimensions across flats and corners shall be applicable prior to incorporation of the
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

locking feature.

3.5.1 Bearing surface. The bearing surface shall be normal to the axis of the pitch diameter of the threads within the
values shown in Figure 1. The bearing surface roughness average shall not be greater than 125 microinches in accordance with
ASME B46. 1 (see 4.5.1.1).

3.5.2 Threads. Unless otherwise specified, the threads shall be Class 3B in accordance with AS8879 MIL-S-8879 prior
to the incorporation of the locking feature. Threads used for the locking feature may be displaced or deformed in any manner
which produces self-locking nuts conforming to this specification. The nut, after incorporation of the locking feature and prior to
ARLINGTON, VA 22209

lubrication, shall allow the “go” gage to enter not less than a half turn. When the application of a lubricant prevents the use of
1000 WILSON BLVD.

standard gages, the nuts shall permit a minimum free rotation of three quarters of a turn (270 degrees) on the test bolt,
having Class 3A threads.

3.5.3 Plate nut rivet-bolt hole spacing. Plate nut attaching rivet-bolt hole spacing shall be in accordance with the
applicable standard (see 4.5.1.2).
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3.6 Plating or surface treatment.

3.6.1 Noncorrosion-resistant steel nuts. Unless otherwise specified, nuts fabricated from noncorrosion-resistant steel
shall be cadmium plated in accordance with AMS-QQ-P-416 QQ-P-416, Type II, Class 2 except nuts that are heat treated to 39
HRc or higher and cadmium plated shall be baked for not less than 23 hours at 375° +/- 25° F starting within 2 hours after
plating to provide hydrogen embrittlement relief. The baking process shall be controlled in accordance with AMS 2750.

3.6.1.1 Zinc plated nuts. Nuts that are heat treated to 39 HRc or higher and zinc plated shall be baked for not less than
3.5 hours at 375 °F +/- 25° starting within 4 hours after plating to provide hydrogen embrittlement relief.

3.6.2 Corrosion-resistant steel nuts. Unplated nuts, parts or components fabricated from corrosion-resistant steel
shall be passivated in accordance with ASTM A967. Staining requirements of ASTM A967 do not apply to parts that receive a
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

supplementary coating or lubricant after passivation.

THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

3.6.2.1 800° F corrosion-resistant steel nuts. Unless otherwise specified, the threads of 800° F corrosion-resistant steel
nuts shall be silver plated in accordance with AMS 2410 or AMS 2411. Application of such finish to the exterior surface of the
nut or nut retaining cage may be omitted.

3.6.3 Plate nuts. No plating finish shall be applied in the area of the projection weld nibs of projection weld plate
nuts.

3.6.4 Aluminum alloy nuts. Unless otherwise specified, nuts fabricated from aluminum alloy shall be anodized in
accordance with MIL-A-8625 or chemically surface treated in accordance with MIL-DTL-5541 MIL-C-5541. No protective finish
need be applied to clad aluminum-plate nut retainers or gang channels. For identification, the threaded element of the high-
strength aluminum alloy nuts, from .112-40 through .250-28 size of the regular type and from .112-40 through .190-32 size of
the shear type, shall be dyed blue. When the threaded element of the nut assembly is not exposed, the exposed portion of the
nut shall be dyed blue.

3.6.5 Copper-base alloy nuts. Unless otherwise specified, nuts fabricated from copper-base alloy shall be cadmium
plated in accordance with AMS-QQ-P-416, Type II, Class 2.
REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 4
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

3.7 Lubrication. Nuts may be lubricated to prevent nut-bolt seizure, provided the lubricant has passed the
applicable tests (see 4.5.2). The qualification test report shall identify the lubricant and shall classify it as either solid (dry) film
or soluble film. The lubricant shall not be changed without requalification of the nut, except as noted in 3.7.1.
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

3.7.1 Solid (dry) film lubricant. When specified, the 250 °F and 450 °F nuts shall be coated with graphite-free solid
(dry) film lubricant. If lubricant is in accordance with AS5272, Type I, no testing of lubricant is required; if lubricant does not
meet the requirements of AS5272, Type I, then lubricant shall be subjected to and pass the applicable tests (see 4.5.2 through
4.5.2.5). Nickel and/or copper plate as a pretreatment for the application of solid (dry) film is optional.

3.7.2 Soluble lubricant. Soluble lubricant coated panels shall be composed of the same material and contain the same
finish as the nut (see 4.5.2.1, 4.5.2.2, 4.5.2.5 and 4.5.2.6).

3.8 Mechanical properties.

ARLINGTON, VA 22209
1000 WILSON BLVD.

3.8.1 Axial tensile strength. The nuts shall have a minimum axial tensile strength as specified in Table I (see 4.5.3.1).

3.8.2 Torque.

3.8.2.1 Wrench torque. Wrenchable nuts when tested in accordance with 4.5.3.2 shall withstand the wrench torque
values specified in Table II. There shall be no permanent deformation that may interfere with the use of a box or open end
wrench conforming to GGG-W-636.

3.8.2.2 Locking torque.

3.8.2.2.1 Maximum locking torque. The torque required for installation and/or removal shall not be greater than the
values specified in Tables III and IV as applicable (see 4.5.3.3.2 and 6.1.2).

3.8.2.2.2 Minimum breakaway torque. The torque required to start the unseated nut in the removal direction shall be
measured and shall not be less than the values specified in Table III for the minimum breakaway (see 4.5.3.3.3).

3.8.2.2.3 Permanent set. The nuts shall meet the minimum breakaway torque requirements on minimum material
condition bolts or studs, subsequent to installation on maximum material condition bolts or studs, when tested in accordance
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

with 4.5.3.3.4. The nuts shall not exceed the maximum locking torque nor be below the minimum breakaway torque values
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

specified in Table III when subjected to this test.

3.8.2.3 Torque out. Torque out values for floating and retained nonfloating plate nuts, gang channel nuts, and
Attached Retention Element (A.R.E.) nuts with no axial load on the bearing surface of the nut, shall not be less than the values
listed in Table V (see 4.5.3.4). This test is not applicable to wrenchable nuts.

3.9 Push out. Push out values for the floating and nonfloating plate nuts, gang channel nuts, and (A.R.E.) nuts shall
be not less than the values listed in Table VI when tested in accordance with 4.5.3.5.

3.10 Vibration. Self-locking nuts shall show no evidence of failure when tested in accordance with 4.5.3.6. Failure to
meet this requirement will be cause for rejection of the lot represented by the test sample.

3.11 Discontinuities. Discontinuities shall not be greater than depths specified in Table VII (see 4.5.4 and Figures 2
and 2a). Care must be taken not to confuse cracks with discontinuities. Cracks as defined in 6.1.2 are not permitted in any
location.

3.12 Stress embrittlement (durability). Noncorrosion-resistant steel cadmium or zinc plated nuts that are heat
treated to 39 HRC or higher shall show no evidence of cracking or fracture when subjected to the applicable stress
REVISION DATE.

embrittlement tests (see 4.5.5.1 and 4.5.5.2). Stress embrittlement testing is not required for .138-inch and smaller size nuts.
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3.13 Stress corrosion. Aluminum alloy nuts shall show no evidence of cracking when subjected to the stress corrosion
tests (see 4.5.6 and 4.5.6.1).

REVISION

1
FORM 09-01

NASM25027
SHEET 5
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

3.14 Magnetic permeability. The magnetic permeability of the corrosion-resistant steel nuts shall be less than 2.0
(air= 1.0) for a field strength of H = 200 oersteds (see 4.5.7).

3.15 Manufacturer’s identification. Nut thread sizes .190-inch diameter and larger manufactured after 30 June 1985
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

shall be permanently marked with the trademark or symbol of the manufacturer. The symbol or trademark must be listed in

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MIL-HDBK-57. On solid (dry) film lubricated parts, the marking shall be legible after solid (dry) film lubricant removal. However,
the color of the nonmetallic locking element may be used if the color has been established as the manufacturer’s trademark or
symbol.

3.15.1 Copper-base alloy nuts. Unless otherwise specified, copper-base alloy nuts shall be identified as specified on
the applicable standard.

3.16 Workmanship. Workmanship shall be consistent with the type of product, finish, and the class of thread fit specified.
ARLINGTON, VA 22209

Sharp edges shall be broken; loose or hanging burrs and slivers which might become dislodged under usage shall be removed.
1000 WILSON BLVD.

4. VERIFICATION

4.1 Inspection conditions. Unless otherwise specified, all inspections shall be performed in accordance with the test
conditions specified in the applicable test method documents or paragraphs in this specification.

4.2 Classification of inspection. The inspections specified herein are classified as follows:

a. Qualification inspection (4.3)

b. Quality conformance inspection (4.4)

4.3 Qualification inspection. Qualification inspection shall consist of the inspections listed in table XIII (see 6.4).

4.3.1 Sample. Test samples shall be of the same material and manufactured by the same method as production parts. The
number of nuts to be subjected to qualification tests shall be as specified in table XIII. Complete identification (e.g. trade
name) of the lubricant used on the nuts shall be included in the qualification test report.
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

4.3.2 Certified test report. The manufacturer shall maintain on file a certified test report showing that the
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

manufacturer’s product satisfactorily conforms to this specification. The test report shall include actual results of the tests
specified herein. The manufacturer shall also maintain a dated drawing that completely describes the manufacturer’s product.
The drawing shall specify all dimensions. The test report shall include composition of material selected, coating or plating
applied, forming process (machined, stamped, forged or drawn), and the Rockwell hardness and heat treatment. The drawing
shall also specify the manufacturer’s part number for each size.

4.3.3 Retention of qualification. Requalification will be required in the event any change is made in the product
design, construction, materials, method of manufacture, heat treatment, finish, lubricant or manufacturer’s part-number or
designation.

4.4 Quality conformance inspection. Quality conformance inspections shall consist of the tests specified in table
XIV. The purchaser may apply any or all tests specified herein to any product represented as meeting this specification, at any
time, to verify conformance.

4.4.1 Selection of samples. Sample nuts shall be selected at random from each lot as specified herein.

4.4.1.1 Inspection lot. An inspection lot shall consist of finished nuts which are of the same type and diameter
manufactured from one material heat using the same process, heat treated in the same manner and produced as one
REVISION DATE.

continuous run or part thereof.

REVISION

1
FORM 09-01

NASM25027
SHEET 6
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

4.4.1.2 Sampling plan A. Sample sizes for inspection of product characteristics delineated in paragraph 4.4.1.2.1 shall
be in accordance with ASQ Z1.4 as follows:

Major A - Inspection Level S-4

Major B - Inspection Level S-3
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

Minor - Inspection Level S-2

Acceptance = 0 Rejection = 1

4.4.1.2.1 Product Characteristics. The following characteristics shall be inspected.

Major A:
Self-locking feature missing

Major B:
ARLINGTON, VA 22209

101 Thread fit

1000 WILSON BLVD.

102 Bearing surface squareness

103 Surface finish, plating or surface treatment
104 Rivet hole location and alignment (plate nuts only)
105 Height of nut

Minor:
201 Dimensions of wrenching element (wrenchable nuts only; see 3.5)
202 Loose or hanging burrs
203 All other dimensional characteristics not covered above

4.4.1.3 Sampling plan B. For the axial strength test (4.5.3.1), the sample shall be selected in accordance with Table
VIII or IX, as specified herein. Samples for magnetic permeability will be selected in accordance with Table IX.

4.4.1.4 Sampling plan C. For the locking torque, the torque out, and push out tests (4.5.3.3, 4.5.3.4 and 4.5.3.5,
respectively), sampling shall be in accordance with the attribute plan shown in Table IX. The acceptance or rejection numbers
shall apply to all of the individual inspections for the locking torque, torque out, and push out tests taken separately; i.e., a nut
shall be classified defective if it fails any of these inspections.
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

4.4.1.5 Sampling plan D. For the discontinuities test (4.5.4), sampling shall beat random in accordance with ASQ Z1.4,
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

Level S-3. Failure of any nut sample to meet the requirements of Figure 2a and Table VII after micro-examination in
accordance with 4.5.4 shall be cause for rejection of the lot.

4.5 Inspection methods.

4.5.1 Examination of product. The nuts shall be examined for conformance to this specification and applicable
standards with respect to material, workmanship, dimensions, design and construction, and finish.

4.5.1.1 Bearing surface. Prior to incorporation of the locking feature the nut shall be assembled on a Class 3A threaded
member having a minimum thread length equal to the nut height. The bearing surface values shall be measured with a feeler
gage after contact when the nut is turned finger tight on a table squareness gage having a seating surface diameter equal to
“W” (see Figure 1).

4.5.1.2 Plate nut rivet-bolt hole spacing. Plate nut rivet-bolt hole spacing may be determined by suitable variable
gages or by means of a functional alignment gage specified in Figure 3.
REVISION DATE.

REVISION
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`-

1
FORM 09-01

NASM25027
SHEET 7
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

4.5.2 Lubricant coatings.

4.5.2.1 Effect of the coating on the ability of cadmium plating to prevent galvanic corrosion Four panels made of the
same material as the finished fastener shall be cadmium plated in accordance with AMS-QQ-P-416, Type II, Class 2. Two of the
panels shall be coated with the candidate lubricant and two with any product in accordance with AS5272, Type I. The panels
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

shall then be scribed with an “X” extending to .250-inch from each corner, and subjected to a 96-hour salt spray test in
accordance with NASM1312-1. After exposure, there shall be no significant difference in corrosion when a comparison is made
between the panels with the candidate lubricant and those panels coated with a lubricant in accordance with AS5272, Type I.

4.5.2.2 Effect of the coating on structural materials in contact with the fastener. Corrosion test specimens shall be
panels with four test fasteners per panel. The four fasteners shall be cadmium plated in accordance with AMS-QQ-P-416, Type
II, Class 2. Two fasteners shall be overcoated with the candidate lubricant and two with any product in accordance with
AS5272, Type I. Duplicate specimen sets of the following alloys and finishes shall be subjected to a 96-hour salt spray test in
accordance with NASM1312-1.
ARLINGTON, VA 22209
1000 WILSON BLVD.

a. Bare 7075-T6 aluminum alloy and bare 2024-T6 aluminum alloy treated in accordance with MIL-DTL-5541,
Class IA.

b. Bare 7075-T6 aluminum alloy and bare 2024-T6 aluminum alloy anodized in accordance with MIL-A-8625,
Type II, Class 1.

c. Clad 7075-T6 aluminum alloy and clad 2024-T6 aluminum alloy treated in accordance with MIL-DTL-5541.

d. Untreated titanium alloy.

e. Untreated 300 series corrosion resistant steel.

After exposure, the specimens shall be disassembled and there shall be no significant difference in corrosion on either the
fasteners or panel faying surface when a comparison is made between the fasteners coated with the candidate lubricant and
fasteners coated with a lubricant in accordance with AS5272, Type I.

4.5.2.3 Behavior of coating with paint. Corrosion test specimens shall be of the same aluminum alloys and treatments
as specified in 4.5.2.2b and c, and painted with two coats of primer in accordance with MIL-PRF-23377, Class 2. The specimens
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

shall be subjected to a 96-hour salt spray test in accordance with NASM1312-1. After exposure, there shall be no significant
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

difference in corrosion, blistering, or loss of adhesion of the paint when a comparison is made between the fasteners coated
with the candidate lubricant and fasteners coated with a lubricant in accordance with AS5272, Type I.

4.5.2.4 Effect of coating on sealing materials. Corrosion test specimens shall be of the same aluminum alloys and
treatments as specified in 4.5.2.2b and c, except that sealant materials in accordance with AMS-S-8802 and MIL-PRF-81733
shall be applied to the fasteners. A specimen panel shall be prepared for each sealant material. Before the application of the
sealant material, the fasteners and panels shall be cleaned by scrubbing and rinsing with solvent formulated in accordance with
Table XII. After rinsing, and while still wet, the specimens shall be wiped dry with a clean, non-oily wiping cloth. The specimen
shall be subjected to a 96-hour salt spray test in accordance with NASM1312-1. After exposure, there shall be no significant
difference in loss of adhesion or degradation of sealant material when a comparison is made between the fasteners coated with
the candidate lubricant and fasteners coated with lubricant in accordance with AS5272, Type I.

4.5.2.5 Effect of lubricant on stress corrosion resistance of aluminum fasteners. The lubricated threaded fastener
shall be scratched through to the basis metal. Torque shall be applied against the aluminum alloy panels to induce 90,000 psi
in mating bolt. The assembly shall be salt-spray tested for 96 hours in accordance with NASM1312-1. After exposure, the
lubricated fastener shall not have any cracks which can be determined under 10X magnification.

4.5.2.6 Soluble lubricant removability. Soluble lubricant coated panels, made of the same material and containing the
REVISION DATE.

same finish as the fastener, shall be submerged for 10 minutes +/-1 minute in the cleaner specified in Table XII. The panel
shall then be wiped dry with a clean cloth. Failure of all lubricants to be removed from the panel by the above process shall be
cause for rejection.

4.5.3 Mechanical properties.

REVISION

1
FORM 09-01

NASM25027
SHEET 8
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

Copyright Aerospace Industries Association of America Inc.

CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS FOR ANY PARTICULAR
No reproduction or networking permitted without license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

4.5.3.1 Axial strength. The axial strength test shall be conducted in accordance with NASM1312-8. Steel bolts or
studs heat treated to 160-180 KSI with threads per AS8879 modified per Table XV shall be used for this test. For nuts with
tensile requirements other than those specified in this document, bolts or mandrels with AS8879 threads and sufficient strength
to meet or exceed the tensile value requirements shall be used.
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

4.5.3.1.1 Qualification Testing. Prior to testing, three nuts of the 450 °F shall be baked on a bolt for 6 hours at 450 °F.
Three of the 800 °F (corrosion-resistant steel) nuts shall be baked on the bolt for 6 hours at 800 °F. The 250 °F nuts need not
be baked prior to the test. The nuts shall be tested to destruction at room temperature.

4.5.3.1.2 Quality Conformance Testing. The nuts shall be assembled on the bolts or studs and subjected to axial
strength test at room temperature. Nuts will not be tested to destruction if attribute plans are used.

4.5.3.2 Wrench torque (wrenchable nuts only). Steel bolts, with Class 3A threads in accordance with MIL-S-7742 or
AS8879, shall be used for this test. The nut submitted shall be finger tightened on the bolt up to the self-locking element. The
ARLINGTON, VA 22209

regular nut shall be tightened against a steel bushing with a socket wrench per GGG-W-641 to the torque value specified in
1000 WILSON BLVD.

Table II. The regular nuts shall also be tightened against a steel bushing with an open end wrench to the torque values
specified in Table II for shear nuts up to .625-inch. Shear nuts shall be tightened with a socket or box wrench to the values
specified in Table II. The open end wrench and box wrench shall be in accordance with GGG-W-636, Type I, Class 1, and Type
IV. Deformation that interferes with the proper installation and removal of the nut with the wrench is sufficient cause for
rejection.

4.5.3.3 Locking torque. The locking torque tests shall be conducted with no axial load on the nut at a rate such that
the temperature rise of the nut under test shall not be greater than 75 °F above room ambient temperature. Throughout the
test the same nut and bolt combination shall be used unless the bolt or mandrel threads do not remain in serviceable condition
during testing, then, a new bolt or mandrel shall be used and so noted in the test report. No more than one additional bolt or
mandrel shall be used per test sample.

4.5.3.3.1 Bolts, screws or studs for maximum locking torque, minimum breakaway torque, and permanent set tests.
For the maximum locking torque, minimum breakaway torque, and permanent set tests, screws, bolts or studs with Class 3A fit
threads conforming to MIL-S-7742 or AS8879, with the major thread diameters per NAS9600 and NAS9700 series, as defined in
Table XV, shall be used on nuts with mating threads conforming to MIL-S-7742 or AS8879, as applicable. The pitch diameter
after plating shall be class 3A. The nut shall be capable of being assembled with the fingers on the screws, bolts or studs up to
the locking element. Cadmium-plated, noncorrosion-resistant steel screws, bolts or studs shall be used for testing noncorrosion-
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

resistant steel nuts, copper-based alloy nuts, and aluminum alloy nuts. Corrosion resistant steel screws, bolts or studs shall be
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

used for testing corrosion resistant steel and nickel-copper alloy nuts. (See Table XV for test bolts).

4.5.3.3.2 Maximum locking torque. - Room Temperature. (For these tests, installation shall be considered completed
when one (1) to two (2) bolt threads, excluding the bolt end chamfer, protrude through the top of the nut.). For configurations
where the end of the nut is not visible, such as closed end blind or domed fasteners, and where the locking mechanism is not
at the end of the nut, the bolt threads shall extend a minimum of one and a maximum of two pitches beyond the locking
device.

4.5.3.3.2.1 Tests for 250 ºF 450 ºF and 800 ºF nuts. Install and remove nut for 15 cycles. Measure and record the
maximum installation and removal torque values for the first, seventh and fifteenth cycles, to determine compliance with
3.8.2.2.1. For all metal aluminum nuts 250° application install and remove nut for one cycle only. Record the maximum
installation and removal torque values.

4.5.3.3.3 Minimum breakaway torque - Room Temperature. Minimum breakaway torque for the tests specified in
4.5.3.3.3.1 shall be measured between the limits of one and maximum of two (2) threads of the bolt or screw, as applicable,
extending beyond the nut. For configurations where the end of the nut is not visible, such as closed end blind or domed
fasteners, and where the locking mechanism is not at the end of the nut, the bolt threads shall extend a minimum of one and a
maximum of two pitches beyond the locking device.
REVISION DATE.

4.5.3.3.3.1 Tests for 250 °F 450 ºF and 800 °F nuts. While performing the maximum locking torque test measure and
record the minimum breakaway torque during the first, seventh and fifteenth removal cycles to determine compliance with
3.8.2.2.2. For all metal aluminum nuts 250 °F application record the minimum breakaway torque during the single cycle test.

REVISION

1
FORM 09-01

NASM25027
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---
SHEET 9
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

4.5.3.3.4 Permanent set. Permanent set shall be evaluated by subjecting three of the nuts, at room ambient
temperature, to installation on a maximum material condition bolt or stud, followed by removal from a minimum material
condition bolt or stud as described herein and in 4.5.3.3.4.1 and 4.5.3.3.4.2. For all-metal aluminum nuts that specify one-cycle
use, three nuts shall be tested on the maximum material condition bolt or stud, and three other nuts, representative of the
same production lot, shall be tested on the minimum material condition bolt or stud.
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

4.5.3.3.4.1 Maximum material condition bolts and studs. Three nuts from the same lot shall be assembled on maximum
material condition bolts or studs (as defined below) so that at least three threads protrude through the top of the nut. The
maximum prevailing locking torque shall be measured and recorded during the third complete turn of the nut and after the top
of the nut is flush with the end of the bolt or stud. The nut shall then be removed completely from the bolt or stud. The locking
torque shall not exceed the maximum values specified in Table III. Thread pitch diameter size for the maximum material
condition test bolts or studs shall be as specified in Table X, and shall be inspected with a single element pitch diameter gage.
Test bolt or stud threads shall also meet functional ring gage requirements of AS8879.
ARLINGTON, VA 22209

4.5.3.3.4.2 Minimum material condition bolts and studs. The same three nuts shall then be assembled on minimum
1000 WILSON BLVD.

material condition bolts or studs (as defined below) so that at least three threads protrude through the top of the nut.
Breakaway torque required to start the nut in the removal direction shall be measured and recorded. The breakaway torque
shall not be less than the minimum values specified in Table III. Thread pitch diameter size for the minimum material condition
test bolts or studs shall be as specified in Table X, and shall be inspected with a single element pitch diameter gage. Test bolt
or stud threads shall also meet functional ring gage requirements of AS8879.

4.5.3.3.5 Conditioning tests - (At temperature).

4.5.3.3.5.1 Locking Torque.

4.5.3.3.5.1.1 Tests for 450 °F and 800 °F nuts. Install nut on bolt, record the maximum locking torque, bake at test
temperature for 6 hours, cool to room ambient temperature. Record the maximum removal torque. Install and remove nut an
additional 14 cycles recording the maximum installation and removal torques at the seventh cycle and fifteenth cycles. Take the
test nuts and install on a brand new bolt or screw, bake at test temperature for one hour and remove nut at this temperature.
Record the maximum installation and removal torques.

4.5.3.3.5.1.2 Tests for 250 °F nuts. Install nut on bolt or screw and record maximum installation torque, bake at test
temperature for 3 hours, cool to room ambient temperature. Record the maximum removal torque. Take test nuts and install
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

on a brand new bolt or screw, record the maximum installation torque, bake at test temperature for one hour and remove nut
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

at this temperature. Record the maximum removal torque.

4.5.3.3.5.2 Minimum breakaway torque - Conditioning tests (At temperature).

4.5.3.3.5.2.1 Tests for 450 °F and 800 °F nuts. Minimum breakaway shall be measured and recorded at the first,
seventh, fifteenth and last removal cycles.

4.5.3.3.5.2.2 Tests for 250 °F nuts. Minimum breakaway shall be measured and recorded for the first and the last
removal cycle.

4.5.3.4 Torque out. Nuts when tested in accordance with NASM1312-31 shall meet the torque out values specified in
Table V with no axial load on the bearing surface of the nut. Torque applied by wrenching an ease-out tool inserted from the --``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

top or bottom of the nut is optional.

Gang channel and plate nuts shall be attached to a .250-inch thick steel plate. Gang channel shall be attached to the test plate
at locations equal to the rivet hole locations of standard two lug plate nuts or half the distance between 2 consecutive nuts
whichever is smaller. A hole in the plate shall be located concentric with the nominal position of the threads in the nut and shall
have a diameter equal to the nominal thread size plus twice the minimum radial float specified on the applicable specification
REVISION DATE.

sheet or standard. A.R.E. nuts shall be installed into 2024-T3 aluminum alloy panels having a thickness as specified on the
applicable specification sheet or standard. The nuts shall not crack the retainer. The nuts shall not become malformed enough
to preclude the application of the same torque in the opposite direction.

REVISION

1
FORM 09-01

NASM25027
SHEET 10
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

4.5.3.5 Push out. The minimum load required to push out the nut from the retainer of any plate nut and gang channel
nut, or from the installation material of A.R.E. nuts shall not be less than the values specified in Table VI. For the plate nut and
gang channel nuts, the minimum load required to affect a permanent deformation axial with a threaded element of .030-inch,
measured at the thread centerline between the test plate and the base of the nut, shall not be less than the values specified in
Table VI. The nuts shall be prepared for this test in the manner specified in 4.5.3.4, except that the push-out stud or device
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

shall be provided with a hemispherical end of a diameter equal to the thread diameter plus .030-inch minimum.

4.5.3.6 Vibration. Sample nuts with bolts of the size and quantities specified in Table XI shall be vibrated in accordance
with NASM1312-7. There shall be no failures at less than 30,000 cycles. Vibration tests on nuts larger than. 500-inch are
waived, provided that. 500-inch nuts and smaller, of the same type and design of locking device, have passed the vibration
test.

4.5.3.6.1 Preparation for vibration test.

ARLINGTON, VA 22209

4.5.3.6.2 Nut assembly. Five (5) nuts shall be assembled at room temperature in accordance with Figure 1 of
1000 WILSON BLVD.

NASM1312-7, with bolts and torque values as specified in Table XI. The nuts shall then be removed and reinstalled to the
torque values four additional times before being vibrated.

4.5.3.6.2.1 Baking of test specimens. Five (5) additional pieces of the 450 ºF and 800 ºF nuts shall be assembled on
the appropriate bolts and baked for six hours at 450 ºF and 800 °F, respectively. The baked specimens shall be allowed to cool
in air to room temperature. The nuts shall then be removed and reinstalled to torque values specified in Table XI for four
additional times before being vibrated. It is not necessary to bake the 250 °F nuts for this test. Different spacers may be used
for baking and vibration.

4.5.3.6.2.2 Anchor nuts and A.R.E. nuts. One piece anchor nuts may have their lugs trimmed equal to the width of the
nut base to provide symmetry about the thread axis. Only the trimmed portion of one piece anchor nuts and the nut element
from A.RE. nuts and multi-piece anchor nuts shall be tested.

4.5.3.6.3 Vibration test method. The assembly shall traverse the entire length of the slots in the test fixture
throughout the test. The test shall be run for 30,000 cycles. The test shall be stopped if a nut becomes disassembled from the
bolt. The nut samples shall be examined under 10X magnification for cracks. The nuts shall be considered to have failed the
vibration test under the following conditions:
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

a. When any structural failure (such as broken segments, locking inserts falling out) or cracks occur in the nuts during
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

the test (not including failure of the bolt).

b. When any nut comes completely off the bolt or can be turned completely on or off the bolt with the fingers during
or after completion of 30,000 cycles.

--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---
c. When relative rotation between any nut and bolt is greater than 360 °F.

4.5.4 Discontinuities. Discontinuities in nuts, such as laps, seams, and inclusions shall be determined by one of the
following methods of inspection, unless visual inspection discloses discontinuities which would preclude the necessity for these
inspections. The presence of cracks in nuts shall be cause for rejection (see Figures 2 and 2A). If, in the opinion of the
inspector, the discontinuities are cause for rejection, representative samples shall be taken from those nuts showing
discontinuities. The nuts shall be further examined by micro-examination to determine if the discontinuities are in accordance
with the limits specified herein. Discontinuities within the acceptable limits of Table VII shall not be cause for rejection. Multi-
piece nuts such as gang channel and floating anchor nuts shall be inspected prior to assembly. If the multi-piece nut is heat
treated after assembly, the unit may, at manufacturers discretion be inspected as an assembly. The presence of cracks in nuts,
channel and/or retainers shall be cause for rejection.

4.5.4.1 Inspection method for noncorrosion-resistant steel nuts. Magnetic particle inspection shall be performed in
REVISION DATE.

accordance with ASTM E1444. Such inspection shall be performed on finished nuts of thread sizes .190-inch and larger
subsequent to any processing operations which would adversely affect the ability of the part to be inspected. The nuts shall be
magnetically inspected in a circular manner. The magnetized field shall be normal to the longitudinal axis of the nut. Nuts shall
not be dyed as an indication of magnetic particle inspection specified by the sampling requirements of this specification.
Personnel conducting magnetic particle inspection shall be qualified in accordance with NAS410.
REVISION

1
FORM 09-01

NASM25027
SHEET 11
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

4.5.4.2 Inspection method for corrosion-resistant steel nickel-copper alloy and aluminum nuts. Fluorescent penetrant
inspection shall be performed in accordance with ASTM E1417. This inspection shall be performed on finished nuts of thread
sizes .190 and larger and prior to coating and subsequent to any processing operations which would adversely affect the ability
of the part to be inspected. Nuts shall not be dyed as an indication of fluorescent penetrant inspection specified by the
sampling requirement of this specification. Personnel conducting fluorescent penetrant inspection shall be qualified in
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

accordance with NAS410.

4.5.5 Stress embrittlement.

4.5.5.1 23-hour stress embrittlement test. Ten nuts or 10 percent, whichever is less, shall be selected from each lot
and tested in accordance with NASM1312-14. The test load shall be 75-80 percent of the axial strength specified on the
applicable standard. The duration of the test shall be 23 hours.

4.5.5.2 168-hour stress embrittlement test. Five nuts shall be tested in accordance with NASM1312-14. The test load
ARLINGTON, VA 22209

shall be 75-80 percent of the axial strength specified on the applicable standard. The duration of the test shall be 168 hours.
1000 WILSON BLVD.

4.5.6 Stress corrosion. Samples of the sizes .086-56 through and including .2500-28 aluminum alloy nuts shall be
subjected to the following test. Five of the nuts of the size being qualified shall be assembled on cadmium plated steel bolts or
screws, as applicable, against cadmium plated steel bushings. The torque used in assembly shall be:

a. 4 inch-pounds for the .086-56 size.

b. 8 inch-pounds for the .112-40 size.

c. 15 inch-pounds for the .138-32 size.

d. 20 inch-pounds for the .164-32 size.

e. 40 inch-pounds for the .190-32 size.

f. 100 inch-pounds for the .250-28 size.

The assembly shall then be submerged in a solution consisting of 53 grams of sodium chloride and 50 grams of sodium
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

chromate per liter of solution for 2 weeks at room temperature (75 °F). After 2 weeks, the nut shall be examined and any
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

cracks visible to the unaided eye shall be cause for rejection. If no cracks are visible, one sample of each size shall be
sectioned, polished, and subjected to metallurgical examination. Any cracks shown by this examination shall cause rejection of
the lot.

4.5.6.1 Stress corrosion test for aluminum plate nuts. Stress corrosion testing shall conform to NASM1312-9. Nuts shall
be installed into test panels conforming to Figure 1. Aluminum alloy 7075-T6 nuts shall be installed into test panels conforming
to QQA-250/12. The test bolt shall be in accordance with NAS1589. The test duration shall be 96 hours. Following exposure,
torque out resistance shall be evaluated in accordance with 4.5.3.4 herein. No failures are permitted.

4.5.7 Magnetic permeability. The magnetic permeability shall be determined by the use of an indicator in accordance
with ASTM A 342/A 342M Method 6.

4.6 Inspection of packaging. The sampling and inspection of preservation, packing and container marking shall be in
accordance with ASTM D3951.

5. PACKAGING

5.1 Packaging. For acquisition purposes, the packaging requirements shall be as specified in the contractor order
REVISION DATE.

(see 6.2). When actual packaging of material is to be performed by DoD personnel, these personnel need to contact the
responsible packaging activity to ascertain requisite packaging requirements. Packaging requirements are maintained by the
Inventory Control Point’s packaging activity within the Military Department or Defense Agency, or within the Military
Department’s System Command. Packaging data retrieval is available from the managing Military Department’s or Defense
Agency’s automated packaging files, CD-ROM products, or by contacting the responsible packaging activity.
REVISION

1
FORM 09-01

NASM25027
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---
SHEET 12
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

6. NOTES

6.1 Intended use. The nuts conforming to this specification are intended for use in applications where the
temperature is not greater than the following values:
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

Copper-base alloy nuts – 250 °F

Aluminum-alloy nuts – 250 °F
Corrosion-resistant steel – 250 °F, 450 °F, or 800 °F
Noncorrosion-resistant steel – 250 °F or 450 °F
Nickel-copper alloy nuts – 250 °F

NOTE: Temperature limits below those listed may occur due to coatings, lubricants and/or non-metallic locking
elements. Certain limitations in reusability (less than 15 cycles) occur for certain material and lubricant combinations.
ARLINGTON, VA 22209

6.1.1 Cadmium Plating interchangeability. For all applications, nuts plated in accordance with AMS-QQ-P-416, Class
1000 WILSON BLVD.

2, Type II can be used to replace nuts plated with AMS-QQ-P-416, Class 2, Type I. Nuts with Type I plating cannot be used in
place of nuts with Type II plating. In applications for solid (dry) film lubricated nuts, the type and class are optional providing
the nuts meet the salt spray requirements of AMS-QQ-P-416, Class 2, Type II.

6.1.2 Definitions. For the purpose of clarification and interpretation, the following definitions are applicable to this
specification.

Maximum Locking Torque. The maximum torque encountered during the installation or removal with no load on the base
of the nut. On the first installation cycle, maximum locking torque is defined as the highest reading measured during the third
complete turn of the nut after the top of the nut is flush with the end of the bolt.

Maximum Installation Torque. (See “Maximum Locking Torque”.)

Maximum Removal Torque. This is the highest torque value obtained when the nut (or bolt) is rotated from its installed
position in the removal direction. This torque is measured when the nut (or bolt) is in motion and until the bolt disengages the
nut locking device. There should be no axial load on the base of the nut when the torque is measured.

Minimum Breakaway Torque. The torque required to start nut (or bolt) rotation from its installed position during the
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

removal cycle with no load on the base of the nut. Also: “Breakaway torque.”
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

Installed. A nut is considered installed when one (1) or two (2) bolt threads, excluding the bolt end chamfer, protrude
through the top of the nut.

Removal Cycle. The removal cycle should be considered complete when the locking device is disengaged.

Regular (reg) nuts. Nuts identified as “Regular Height”, “Low Height”, or “125 KSI Ftu” in the title block of the part
standard.

Shear Nuts. Nuts identified as “Thin”, or “Shear Type” in the title block.

Crack. A clean crystalline break passing through the grain or grain boundary without the inclusion of foreign elements.

6.2 Ordering data.

6.2.1 Acquisition requirements. Acquisition documents should specify the following:

a. Title, number and date of this specification.

REVISION DATE.

b. MS or NAS part numbers.

c. Applicable levels of packaging and packing (see 5.1).

REVISION

1
FORM 09-01

NASM25027
SHEET 13
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

Copyright Aerospace Industries Association of America Inc.

CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

6.2.2 Acquisition of Nuts Not Previously Qualified. Nuts which have not been previously qualified via Government-
certified qualification tests and reports may be acquired, provided that certified qualification test reports for these nuts are
retained on file by the manufacturer along with the quality conformance inspection data and they are made available to the
buyer upon request.
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

6.2.3 Acquisition of nuts manufactured prior to issuance of Revision H. Unless otherwise specified, Revision H is
applicable to nuts manufactured after 15 August 1997.

6.2.4 Certification. When requested each shipment of parts will include a Certification Report. That contains the
following:

a. Customer’s name (and Division, if applicable)

b. Purchase Order number and date
c. Part number
ARLINGTON, VA 22209

d. Part name
1000 WILSON BLVD.

e. Procurement specification number

f. Thread specification and gaging system used (if applicable)
g. Inspection lot size
h. Production lot number
i. Quantity shipped
j. Shipper number
k. Material producer
l. Material type and heat number
m. Material composition (Mill heat test report, independent laboratory report)
n. Mechanical property test reports, include, hardness, tensile strength, stress embrittlement, locking torque
tests, push-out, torque-out, etc., as applicable
o. Magnetic particle inspection results
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

p. Fluorescent penetrant inspection results

q. Magnetic permeability test results
r. Other data as specified in the part standard

1 6.3 References to this Specification. This paragraph intentionally blank.

PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

6.4 Qualification. This paragraph intentionally blank.

THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

6.5 Subject term (key word) listing.

a. Nut self-locking hexagon

b. Nut, self-locking heavy hex
REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 14
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

TABLE I – Axial tensile load (pounds).

FINE THD SERIES COARSE THD SERIES
THD SIZE REG NUTS 1/ SHEAR NUTS 2/ REG NUTS 1/ SHEAR NUTS 2/
STEEL AL ALLOY STEEL AL ALLOY THD SIZE STEEL AL ALLOY STEEL AL ALLOY
.086-56 440 440 3/ 230 230 3/
.112-40 750 750 3/ 370 370 3/
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

.138-32 1,130 1,130 3/ 560 560 3/

.164-32 1,720 1,720 3/ 860 860 3/
.190-32 2,460 2,460 3/ 1,230 1,230 3/ .190-24 4/ 2,010 1,000
.250-28 4,580 4,580 3/ 2,290 1,140 .250-20 4/ 3,760 1,860
.312-24 7,390 3,670 3,700 1,830 .312-18 4/ 6,360 3,150
.375-24 11,450 5,680 5,720 2,840 .375-16 4/ 9,540 4,730
.437-20 15,450 7,660 7,720 3,830 .437-14 4/ 13,140 6,520
.500-20 21,110 10,470 10,550 5,240 .500-13 4/ 17,730 8,800
.562-18 26,810 13,300 13,400 6,650 .562-12 4/ 22,890 11,360
.625-18 34,130 16,930 17,060 8,460 .625-11 4/ 28,530 14,150
.750-16 50,020 24,810 25,010 12,400 .750-10 4/ 42,770 21,200
ARLINGTON, VA 22209
1000 WILSON BLVD.

.875-14 68,440 33,950 34,220 16,970 .875-9 4/ 60,330 29,920

1.000-12 90,000 44,640 45,000 22,320 1.000-8 4/ 79,280 39,330
1.125-12 116,700 57,880 58,350 28,940 1.125-7 4/ 99,500 49,350
1.250-12 147,940 73,380 73,970 36,690 1.250-7 4/ 125,000 62,000
1.375-12 171,000 84,800 85,500 42,400 1.375-64/ 150,000 74,400
1.500-12 205,000 101,700 102,500 50,800 1.500-6 4/ 181,000 89,800
1.750-5 4/ 245,000 121,500
2.000-4.5 4/ 322,000 160,000
2.250-4.5 4/ 414,000 205,000
2.500-4 4/ 510,000 253,000

NOTES:
1/ There are no axial tensile strength requirements on copper-base alloy nuts.
2/ The regular nut values shall be used unless the standard specifies that the values for shear nuts are applicable.
3/ These are the axial tensile strength values for the aluminum alloy nuts identified by a blue dye.
4/ Inactive for design for military aircraft. For applicability other than military aircraft, see 6.1.

TABLE II – WRENCH TORQUE (INCH-POUND)

FINE THD SERIES COARSE THD SERIES
THREAD REG NUTS SHEAR NUTS THREAD REGNUTS SHEAR NUTS
SIZE SIZE
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

STEEL AL COPPER STEEL AL COPPER- STEEL AL COPPER STEEL AL COPPER

THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

ALLOY -BASE ALLOY BASE ALLOY -BASE ALLOY -BASE

ALLOY ALLOY ALLOY ALLOY
.086-56 4 4 2
.112-40 8 8 4
.138-32 15 15 8
.164-32 23 23 12 14 14 7
.190-32 46 46 23 29 29 15 .190-24 1/ 40 20 20 22 22 11
.250-28 115 115 58 69 35 35 .250-20 1/ 86 43 43

--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---
.312-24 260 130 130 160 80 80 .312-18 1/ 185 93 93
.375-24 450 225 225 270 138 138 .375-16 1/ 315 158 158
.437-20 965 483 483 575 288 288 .437-14 1/ 550 225 225
.500-20 1,265 633 633 760 380 380 .500-13 1/ 1,000 500 500
.562-18 1,840 920 920 1,110 550 550 .562-12 1/ 1,265 633 633
625-18 2 760 1,380 1,380 1,600 800 800 .625-11 1/ 1,725 863 863
.750-16 5,750 2,875 2,875 3,450 1,725 1,725 .750-10 1/ 2,875 1,438 1,438
.875-14 8,050 4,025 4,025 4,830 2,415 2,415 .875-9 1/ 5,300 2,650 2,650
1.000-12 10,990 5,495 5,495 6,822 3,441 3,441 1.000-8 1/ 8,750 4,375 4,375
1.125-12 14,850 7,425 7,425 10,350 5,175 5,175 1.125-7 1/ 13,100 6,550 6,550
1.250-12 22,500 11,250 11,250 17 250 8,625 8,625 1.250-7 1/ 17,600 8,800 8,800
1.375-12 22,500 11,250 11,250 17,250 8,625 8,625 1.375-6 1/ 20,000 10 000 10,000
1.500-12 22,500 11,250 11,250 17,250 8,625 8,625 1.500-6 1/ 20,000 10,000 10,000
1.750-5 1/ 20,000 10 000 10,000
REVISION DATE.

2.000-4.5 1/ 20,000 10 000 10,000

2.250-4.5 1/ 20,000 10,000 10,000
2.500-4 1/ 20,000 10,000 10,000

NOTES:
1/ Inactive for design for military aircraft.
REVISION

1
FORM 09-01

NASM25027
SHEET 15
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

TABLE III – Maximum Locking and Minimum Breakaway Torque Values (inch-pounds)
FINE THD SERIES COARSE THD SERIES
THD SIZE MAX MIN THD SIZE MAX MIN
LKG TRQ BREAKAWAY LKG TRQ BREAKAWAY
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

INSTL OR TORQUE INSTL OR TORQUE

REMOVAL REMOVAL

.086-56 2.5 .2
.112-40 5 .5
.138-32 10 1.0
.164-32 15 1.5
.190-32 18 2.0 .190-24 1/ 18 2.0
.250-28 30 3.5 .250-20 1/ 30 4.5
ARLINGTON, VA 22209
1000 WILSON BLVD.

.312-24 60 6.5 .312-18 1/ 60 7.5

.375-24 80 9.5 .375-16 1/ 80 12.0
.437-20 100 14.0 .437-14 1/ 100 16.5
.500-20 150 18.0 .500-13 1/ 150 24.0
.562-18 200 24.0 .562-12 1/ 200 30.0
.625-18 300 32.0 .625-11 1/ 300 40.0
.750-16 400 50.0 .750-10 1/ 400 60.0
.875-14 600 70.0 .875-9 1/ 600 82.0
1.000-12 800 90.0 1.000-8 1/ 800 110.0
1.125-12 900 117.0 1.125-7 1/ 900 137.0
1.250-12 1,000 143.0 1.250-7 1/ 1,000 165.0
1.375-12 1,200 180.0 1.375-6 1/ 1,200 200.0
1.500-12 1,400 210.0 1.500-6 1/ 1,400 230.0
1.750-5 1/ 1,800 300.0
2.000-4.5 1/ 2,200 360.0
2.250-4.5 1/ 2,600 430.0
2.500-4 1/ 3,000 500.0
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

1/ Inactive for design of military aircraft.

THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

TABLE IV – Locking torque tests

Nut types 1/ Test Temperature Test Paragraph Percent allowable maximum

2/ of Table III
250 °F Room ambient 4.5.3.3.2 100
4.5.3.3.3.1
250 °F 250 °F 4.5.3.3.5.1.2 150
4.5.3.3.5.2.2
450 °F Room ambient 4.5.3.3.2.1 100
4.5.3.3.3.1
450 °F 450 °F 4.5.3.3.5.1.1 200 3/
4.5.3.3.5.2.1 150 4/
800 °F Room ambient 4.5.3.3.2.1 100
4.5.3.3.3.1
800 °F 800 °F 4.5.3.3.5.1.1 200 3/
4.5.3.3.5.2.1 150 4/
REVISION DATE.

--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

1/ Maximum usage temperature

2/ Installation and/or removal torque
3/ First, seventh and fifteenth cycles
4/ Last cycle only

REVISION

1
FORM 09-01

NASM25027
SHEET 16
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

TABLE V – Torque out

Thread Size Torque
(minimum inch-pounds)
.086 10
.112 20
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

.138 30
.164 45
.190 60
.250 100
.312 160
.375 240
.437 350
.500 400
ARLINGTON, VA 22209

.562 450
1000 WILSON BLVD.

.625 500

TABLE VI – Push out

Thread Size Pounds
.086 20
.112 40
.138 60
.164 80
.190 100
.250 and over 125

TABLE VII – Limits of Depths (inches) on Laps, Seams and Inclusion

Thread .312 and .375 .437 .500 .562 .625 .750 .875
size of nut under
Nuts .005 .006 .007 .009 .011 .012 .014 .017
made
from
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

sheet
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

metal
Nuts .010 .011 .012 .014 .016 .017 .019 .022
made
from bar
or wire

TABLE VII – Limits of Depths (inches) on Laps, Seams and Inclusion (CONTINUED)

Thread size 1.000 1.125 1.250 1.375 1.500 1.750 2.000 2.250 2.500
of nut
Nuts made --- --- --- --- --- --- --- --- ---
from sheet
metal

Nuts made .025 .028 .031 .048 .052 .066 .075 .084 .096
from bar or
wire
REVISION DATE.

REVISION
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`--

1
FORM 09-01

NASM25027
SHEET 17
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

TABLE VIII – Variables plan

Lot size Sample size
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

Under 10,000 5
10,000 to 50,000 7
50,001 to 100,000 10
Over 100,00 15

TABLE IX – Attribute plan

ARLINGTON, VA 22209
1000 WILSON BLVD.

Lot size Sample Size Acceptance Number

Under 10,000 5 0
10,000 to 50,000 10 0
50,001 to 100,000 15 0
Over 100,000 27 0
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 18
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

Copyright Aerospace Industries Association of America Inc.

CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

TABLE X – Pitch Diameter dimensions for permanent set test

Thread Pitch Dia Min Material Condition Max Material Condition
Size Total Tol. MIN PD MAX PD MIN PD MAX PD
1 2 3 4 5 6
.086-56 0.0016 0.0728 0.0732 0.0736 0.0744
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

.112-40 0.0019 0.0939 0.0943 0.0949 0.0958

.138-32 0.0021 0.1156 0.1161 0.1167 0.1177
.164-32 0.0022 0.1415 0.1421 0.1427 0.1437
.190-24 * 0.0025 0.1604 0.1610 0.1619 0.1629
.190-32 0.0023 0.1674 0.1680 0.1687 0.1697
.250-20 * 0.0028 0.2147 0.2154 0.2164 0.2175
.250-28 0.0025 0.2243 0.2249 0.2257 0.2268
.312-18 * 0.0030 0.2734 0.2742 0.2752 0.2764
ARLINGTON, VA 22209

.312-24 0.0027 0.2827 0.2834 0.2843 0.2854

1000 WILSON BLVD.

.375-16 * 0.0033 0.3311 0.3319 0.3331 0.3344

.375-24 0.0029 0.3450 0.3457 0.3467 0.3479
.437-14 * 0.0035 0.3876 0.3885 0.3897 0.3911
.437-20 0.0031 0.4019 0.4027 0.4038 0.4050
.500-13 * 0.0037 0.4463 0.4472 0.4485 0.4500
.500-20 0.0032 0.4643 0.4651 0.4662 0.4675
.562-12 * 0.0039 0.5045 0.5055 0.5068 0.5084
.562-18 0.0034 0.5230 0.5238 0.5250 0.5264
.625-11 * 0.0041 0.5619 0.5629 0.5644 0.5660
.625-18 0.0035 0.5854 0.5863 0.5875 0.5889
.750-10 * 0.0044 0.6806 0.6817 0.6832 0.6850
.750-16 0.0038 0.7056 0.7065 0.7079 0.7094
.875-9 * 0.0047 0.7981 0.7993 0.8009 0.8028
.875-14 0.0041 0.8245 0.8255 0.8270 0.8286
1.000-8 * 0.0051 0.9137 0.9150 0.9168 0.9188
1.000-12 0.0044 0.9415 0.9426 0.9441 0.9459
1.125-7 * 0.0054 1.0268 1.0282 1.0300 1.0322
1.125-12 0.0045 1.0664 1.0675 1.0691 1.0709
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

1.250-7 * 0.0055 1.1517 1.1531 1.1550 1.1572

THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

1.250-12 0.0046 1.1913 1.1925 1.1940 1.1959

1.375-6 * 0.0060 1.2607 1.2622 1.2643 1.2667
1.375-12 0.0047 1.3162 1.3174 1.3190 1.3209
1.500-6 * 0.0061 1.3856 1.3871 1.3893 1.3917
1.500-12 0.0048 1.4411 1.4423 1.4440 1.4459
1.750-5 * 0.0067 1.6134 1.6151 1.6174 1.6201
2.000-4.5 * 0.0071 1.8486 1.8504 1.8529 1.8557
2.250-4.5 * 0.0073 2.0984 2.1002 2.1028 2.1057
2.500-4 * 0.0078 2.3298 2.3318 2.3345 2.3376

--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---
NOTES: Asterisk (*) indicates coarse threads, Inactive for design for military aircraft.
Column 3 is the minimum pitch diameter per AS8879.
Column 4 is the minimum PD plus one-quarter (0.25) of the total PD tolerance.
Column 5 is the maximum pitch diameter (Col 6) minus 0.4 of the total PD tolerance.
Column 6 is the maximum pitch diameter per AS8879.
REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 19
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

TABLE XI – Vibration requirements

NASM1312-7

Nut size Bolt 1/ size 250 ºF 450 ºF and 800 ºF Assembly torque
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

Number of Number of Samples (inch-pound)

Samples Required +5%-0
Required
.190-32 NAS9603/9703-20 5 10 36
.250-28 NAS9604/9704-21 5 10 60
.312-24 NAS9605/9705-21 5 10 120
.375-24 NAS9606/9706-21 5 10 160
.437-20 NAS9607/9707-22 5 10 200
.500-20 NAS9608/9708-22 5 10 300
ARLINGTON, VA 22209
1000 WILSON BLVD.

1/ For CRES nuts use NAS 96XX series of bolts. Equivalent bolts of different configurations may be substituted.

TABLE XII – Formulation of cleaner

Ingredient Specification Percent
by volume
Aromatic petroleum TT-N-97 type I 50
naphtha grade B
Ethyl acetate TT-E-751 20
Methyl-ethyl-ketone ASTM D740 20
Isopropyl alcohol TT-I-735 10

TABLE XIII – Qualification inspections

Test Requirement paragraph Test method paragraph Sample Size
Examination of product 3.3 - 3.5 4.5.1 - 4.5.1.2 All
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---
Suitability of lubricant coating 3.7 - 3.7.2 4.5.2 - 4.5.2.6 3
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

Axial tensile strength 3.8.1 4.5.3.1 10

Wrench torque 3.8.2.1 4.5.3.2 3
Locking torque 3.8.2.2 - 3.8.2.2.2 4.5.3.3 - 4.5.3.3.5 20 1/
Permanent set 3.8.2.2.3 4.5.3.3.4 3
Torque out 3.8.2.3 4.5.3.4 5
Push out 3.9 4.5.3.5 5
Vibration 3.10 4.5.3.6 - 4.5.3.6.3 10
Discontinuities 3.11 4.5.4 – 4.5.4.2 All
168-hour stress embrittlement 3.12 4.5.5.2 10
Stress corrosion 3.13 4.5.6 5
Magnetic permeability 3.14 4.5.7 All

1/ For locking torque (10) of the (20) samples shall be used for tests at room temperature and (10) for conditioning
tests.
2/ Torque out and push out are not applicable to right angle plate nut and wrenchable nuts.
REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 20
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

TABLE XIV – Quality conformance inspections

Test Requirement Test method
paragraph Paragraph
Examination of product 3.4 – 3.5.2 4.5.1 - 4.5.1.2
Axial tensile strength 3.8.1 4.5.3.1
Locking torque 1/ 3.8.2.2 - 3.8.2.2.3 4.5.3.3 thru
4.5.3.3.4.1
Torque out (not applicable to right angle plate and 3.8.2.3 4.5.3.4
ARLINGTON, VA 22209
1000 WILSON BLVD.

wrenchable nuts)
Push out (not applicable to right-angle plate wrenchable nuts) 3.9 4.5.3.5
Discontinuities 3.11 4.5.4
23-hour stress embrittlement 3.12 4.5.5.1
Magnetic Permeability 3.14 4.5.7
1/ Except paragraphs 3.8.2.2.3 and 4.5.3.3.4.
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---
REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 21
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

TABLE XV – TEST BOLTS 3/ 4/

FINE THREAD SERIES COARSE THREAD SERIES EXTERNAL THREAD MAJOR
DIAMETER 1/
NUT SIZE NUT MATERIAL NUT SIZE NUT MATERIAL
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

NONCRES STEEL CRES NONCRES STEEL CRES

ALUMINUM ALUMINUM
Ni-Cu ALLOY Ni-Cu ALLOY
Cu BASE ALLOY Cu BASE ALLOY

.086-56 MS16997 MS16995 -

.112-40 MS16997 MS16995 -
.138-32 MS16997 MS16995 -
ARLINGTON, VA 22209

.164-32 M816997 MS16995 -

1000 WILSON BLVD.

.190-32 NAS9703 NAS9603 .190-24 2/ 2/ -

.250-28 NAS9704 NAS9604 .250-20 2/ 2/ -
.312-24 NAS9705 NAS9605 .312-18 2/ 2/ -
.375-24 NAS9706 NAS9606 .375-16 2/ 2/ -
.437-20 NAS9707 NAS9607 .437-14 2/ 2/ -
.500-20 NAS9708 NAS9608 .500-13 2/ 2/ -
.562-18 NAS9709 NAS9609 .562-12 1/ 1/ -
.625-18 NAS9710 NAS9610 .625-11 2/ 2/ -
.750-16 NAS9712 NAS9612 .750-10 2/ 2/ -
.875-14 NAS9714 NAS9614 .875-9 2/ 2/ -
1.000-12 NAS9716 NAS9616 1.000-8 2/ 2/ -
1.125-12 NAS9718 NAS9618 1.125-7 2/ 2/ -
1.250-12 NAS9720 NAS9620 1.250-7 2/ 2/ -
1.375-12 NAS9722 NAS9622 1.375-6 2/ 2/
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

1.500-12 NAS9724 NAS9624 1.500-6 2/ 2/

1.750-5 1/ 1/ 1.723/1.750
2.000-4.5 1/ 1/ 1.978/2.000
2.250-4.5 1/ 1/ 2.228/2.250
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

2.500-4 1/ 1/ 2.476/2.500
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

Threads per MIL-S-7742 or AS8879 except as follows:

1/ External thread major diameter modified as tabulated.
2/ External thread major diameter per NAS9600 or NAS9700 series
3/ Screws, bolts, studs or threaded mandrels having like characteristics such as, material, dimensions, heat treat,
finish and lubricant may be used.
4/ Cadmium plated, non-corrosion resistant steel screws, bolts or studs. Unplated, corrosion resistant steel screws,
bolts or studs.
REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 22
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

À OF TAPPED HOLE

W W
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

ARLINGTON, VA 22209
1000 WILSON BLVD.

90° A 90°

W A W A
Width or Base Ring Bearing (to Maximum (Inch) Width or Base Ring Bearing (to Maximum (Inch)
Nearest .0625-inch) Nearest .0625-inch)

Less Than. 188 .004 2.063, 2.125 0.020

PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST

.188, .250 .005 2.188, 2.250 .021

THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

.313, .375 .006 2.313, 2.375 .022

.438, .500 .007 2.438, 2.500 .023
.563, .625 .008 2.563, 2.625 .024
.688, .750 .009 2.688, 2.750 .025
.813, .875 .010 2.813, 2.875 .026
.938, 1.000 .011 2.938, 3.000 .027
1.063, 1.125 .012 3.063, 3.125 .028
1.188, 1.250 .013 3.188, 3.250 .029
1.313, 1.375 .014 3.313, 3.375 .030
1.438, 1.500 .015 3.438, 3.500 .031

--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---
1.563, 1.625 .016 3.563, 3.625 .032
1.688, 1.750 .017 3.688, 3.750 .033
1.813, 1.875 .018 3.813, 3.875 .034
1.938, 2.000 .019 3.938, 4.000 .035

FIGURE 1 – Dimensions for measuring relationship of bearing surface with respect to the axis of the pitch diameter of the
REVISION DATE.

threads.

REVISION

1
FORM 09-01

NASM25027
SHEET 23
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

ACCEPTABLE
ARLINGTON, VA 22209
1000 WILSON BLVD.
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

Tool marks and draw marks on self-locking nuts as a result of normal machining or heading operations shall not be cause for
rejection, provided discontinuities are within the limits of Table VII.

FIGURE 2 – Acceptable indications of self-locking nuts as revealed by

magnetic particle or fluorescent penetrant inspection.
REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 24
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

REJECTABLE
AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

Nut having seams, laps, or inclusions which intersect an Nut fabricated from bar stock which has seams, laps, or -
ARLINGTON, VA 22209
1000 WILSON BLVD.

edge in line with beam slots passing through the center inclusions which intersect an edge.
of the hex flats.
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

Nuts having laps or seams due to the forming of the metal in excess of the limits specified in Table VII.

FIGURE 2a – Rejectable indications of self-locking nuts as revealed

by magnetic particle or fluorescent penetrant inspection.
REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 25
USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

Copyright Aerospace Industries Association of America Inc.

CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT
 NATIONAL AEROSPACE STANDARD
© COPYRIGHT 2012 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED

LAP FIT 4 HOLES "K" -.002 MIN

AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC

C ± .0002
.750 MIN
NOM
J ± .0002
NOM

.004 CLEARANCE
PER SIDE
J ± .0002
C ± .0002
ARLINGTON, VA 22209

NOM
1000 WILSON BLVD.

NOM
J ± .0002
NOM

.008 CLEARANCE
ON DIAMETER

BASIC "GO"
THREAD GAGE

NOTES:
1. Dimensions in inches.
2. MS or AN tolerance on dimension “J” between rivet holes = +0.002, gage pins being 0.002 below min “K” dia check
parts to 0.002 functionally.
3. MS tolerance on dimension “C” between rivet and tapped hole equal the center of tapped hole shall not deviate in any
direction from the center of plate nut as determined by the rivet holes by more than 0.005.
4. The center hole in the gage having 0.004 clearance per side and the rivet hole pins having 0.001 clearance per side
checks the relationship to a total of 0.005 per side functionally.
PRODUCT AND SHALL BECOME EFFECTIVE NO LATER THAN SIX MONTHS FROM THE LAST
THIS DRAWING SUPERSEDES ALL ANTECEDENT STANDARD DRAWINGS FOR THE SAME

FIGURE 3 – Plate nut functional alignment gage

REVISION DATE.

REVISION

1
FORM 09-01

NASM25027
SHEET 26
--``,,`,,,``,```,``,```,,,,,,,`-`-`,,`,,`,`,,`---

USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY
Copyright Aerospace Industries Association of America Inc.
CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF
Provided by Accuris under license with AIA/NAS Licensee=Safran Seats LLC Engineering/5935306001, User=Realyvazquez, Paula
ITEMS without
No reproduction or networking permitted FOR ANY PARTICULAR
license from Accuris APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO
Not for Resale, OF PATENT
05/22/2024 OR TRADEMARKS RIGHTS.
15:06:59 MDT