514.8Method 514.8 vibration contents

MIL-STD-810H, Environmental Engineering Considerations and Laboratory Tests

Last Updated 29 Oct 2026

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Paragraph		Page
1.	SCOPE	1
1.1	PURPOSE	1
1.2	APPLICATION	1
1.3	LIMITATIONS	4
2.	TAILORING GUIDANCE	4
2.1	SELECTING THE METHOD	4
2.1.1	EFFECTS OF ENVIRONMENT	5
2.1.2	SEQUENCE	6
2.2	SELECTING PROCEDURES	6
2.2.1	PROCEDURE SELECTION CONSIDERATIONS	6
2.2.2	DIFFERENCE AMONG PROCEDURES	7
2.3	DETERMINE TEST LEVELS AND CONDITIONS	7
2.3.1	CLIMATIC CONDITIONS	7
2.3.2	TEST ITEM CONFIGURATION	8
2.3.3	MULTI EXCITER CONSIDERATION	8
2.4	TEST ITEM OPERATION	8
3.	INFORMATION REQUIRED	8
3.1	PRETEST	9
3.2	DURING TEST	10
3.3	POST-TEST	10
4.	TEST PROCESS	10
4.1	TEST FACILITY	10
4.1.1	PROCEDURE I - GENERAL VIBRATION	10
4.1.2	PROCEDURE II - LOOSE CARGO TRANSPORTATION	11
4.1.3	PROCEDURE III - LARGE ASSEMBLY TRANSPORT	11
4.1.4	PROCEDURE IV - ASSEMBLED AIRCRAFT STORE CAPTIVE CARRIAGE AND FREE FLIGHT	11
4.2	CONTROLS, TOLERANCES, AND INSTRUMENTATION	11
4.2.1	CONTROL STRATEGY	11
4.2.1.1	ACCELERATION INPUT CONTROL STRATEGY	11
4.2.1.2	FORCE CONTROL STRATEGY	12
4.2.1.3	ACCELERATION LIMIT STRATEGY	12
4.2.1.4	ACCELERATION RESPONSE CONTROL STRATEGY	12
4.2.1.5	WAVEFORM CONTROL STRATEGY	12
4.2.2	TOLERANCES	13
4.2.2.1	ACCELERATION SPECTRAL DENSITY	13
4.2.2.2	PEAK SINUSOIDAL ACCELERATION	15
4.2.2.3	FREQUENCY MEASUREMENT	16
4.2.2.4	CROSS AXIS ACCELERATIONS	16
4.2.3	INSTRUMENTATION	17
4.3	TEST INTERRUPTION	17
4.3.1	INTERRUPTION DUE TO LABORATORY EQUIPMENT MALFUNCTION	17

MIL-STD-810H METHOD

514.8 CONTENTS - Continued

Paragraph		Page
4.3.2	INTERRUPTION DUE TO TEST ITEM OPERATION FAILURE	18
4.3.3	INTERRUPTION DUE TO SCHEDULED EVENT.	18
4.3.4	INTERRUPTION DUE TO EXCEEDING TEST TOLERANCES	18
4.4	TEST SETUP	19
4.4.1	PROCEDURE I - GENERAL VIBRATION..	19
4.4.2	PROCEDURE II - LOOSE CARGO TRANSPORTATION.	19
4.4.3	PROCEDURE III - LARGE ASSEMBLY TRANSPORT..	19
4.4.4	PROCEDURE IV - ASSEMBLED AIRCRAFT STORE CAPTIVE CARRIAGE AND FREE FLIGHT.	20
4.5	TEST EXECUTION.	21
4.5.1	PREPARATION FOR TEST..	22
4.5.1.1	PRELIMINARY STEPS	22
4.5.1.2	PRETEST STANDARD AMBIENT CHECKOUT..	22
4.5.2	PROCEDURE I - GENERAL VIBRATION..	22
4.5.3	PROCEDURE II - LOOSE CARGO TRANSPORTATION.	23
4.5.4	PROCEDURE III - LARGE ASSEMBLY TRANSPORT	23
4.5.5	PROCEDURE IV - ASSEMBLED AIRCRAFT STORE CAPTIVE CARRIAGE AND FREE FLIGHT.	24
5.	ANALYSIS OF RESULTS	26
5.1	PHYSICS OF FAILURE	26
5.2	QUALIFICATION TESTS	26
5.3	OTHER TESTS.	26
6.	REFERENCE/RELATED DOCUMENTS	26
6.1	REFERENCED DOCUMENTS	26
6.2	RELATED DOCUMENTS	29
TABLE

TABLE 514.8-I.	VIBRATION ENVIRONMENT CATEGORIES.	3
TABLE 514.8-II	RANDOM VIBRATION TEST TOLERANCES	14
TABLE 514.8-III	SINUSOIDAL VIBRATION TEST TOLERANCES	16

A ENGINEERING INFORMATION

1.	SCOPE.	A-1
1.1	PURPOSE.	A-1
1.2	APPLICATION.	A-1
1.3	LIMITATIONS	A-1
2.	ENGINEERING INFORMATION.	A-1
2.1	VIBRATION TEST TYPES.	A-1
2.1.1	DEVELOPMENT TEST.	A-1
2.1.2	QUALIFICATION TEST.	A-1
2.1.2.1	FUNCTIONAL TEST.	A-2
2.1.2.2	ENDURANCE TEST.	A-2
2.1.3	DURABILITY TEST.	A-2
2.1.4	RELIABILITY TEST.	A-2
2.1.4.1	STATISTICAL RELIABILITY TEST	A-3
2.1.4.2	RELIABILITY GROWTH TEST	A-3

MIL-STD-810H METHOD

514.8 CONTENTS - Continued

Paragraph		Page
2.1.5	WORTHINESS TEST	.A-3
2.1.6	ENVIRONMENTAL STRESS SCREENING (ESS)	.A-3
2.2	TEST TIME COMPRESSION AND THE FATIGUE RELATIONSHIP	.A-3
2.3	VIBRATION CHARACTERIZATION	.A-5
2.3.1	RANDOM VIBRATION	.A-6
2.3.2	SINUSOIDAL VIBRATION	.A-6
2.3.3	MIXED BROADBAND AND NARROWBAND VIBRATION	.A-6
2.3.4	TRANSIENT VIBRATION	.A-7
2.3.5	RANDOM VERSUS SINUSOIDAL VIBRATION EQUIVALENCE	.A-7
2.3.6	COMBINATION OF TEST SPECTRA	.A-7
2.4	PLATFORM/MATERIEL AND FIXTURE/TEST ITEM INTERACTION	.A-7
2.4.1	MECHANICAL IMPEDANCE	.A-7
2.4.2	VIBRATION ISOLATION	.A-8
2.4.3	MATERIEL RESONANT FREQUENCY VARIATION	.A-8
2.5	MODAL TEST AND ANALYSIS	.A-8
2.5.1	MODAL TEST TECHNIQUES	.A-9
2.5.2	MATERIAL NON-LINEAR BEHAVIOR	.A-9
2.6	AERODYNAMIC EFFECTS	.A-9
2.6.1	DYNAMIC PRESSURE	.A-9
2.6.2	AIRSPEED	.A-9
2.6.3	ALTITUDE	.A-10
2.7	SIMILARITY	.A-10
2.7.1	UNMODIFIED MATERIEL	.A-10
2.7.2	MODIFIED MATERIEL	.A-10
2.7.3	EQUAL VIBRATION ENVIRONMENT	.A-11
2.7.4	RELIABILITY DATA	.A-11
2.7.5	CRITICAL RESONANT RESPONSE	.A-11
2.7.6	DYNAMIC SIMILARITY	.A-11

B MANUFACTURE / MAINTENANCE TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

1.	SCOPE	B-1
1.1	PURPOSE.	B-1
1.2	APPLICATION.	B-1
1.3	LIMITATIONS.	B-1
2.	MANUFACTURE/MAINTENANCE	B-1
2.1	CATEGORY 1 - MANUFACTURING/MAINTENANCE PROCESSES	B-1
2.2	CATEGORY 2 - SHIPPING AND HANDLING	B-1
2.3	CATEGORY 3 - ENVIRONMENTAL STRESS SCREENING (ESS)	B-1

MIL-STD-810H

METHOD 514.8

CONTENTS - Continued Paragraph

Page

C TRANSPORTATION TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

1.	SCOPE	C-1
1.1	PURPOSE	C-1
1.2	APPLICATION	C-1
1.3	LIMITATIONS	C-1
2.	TRANSPORTATION	C-1
2.1	CATEGORY 4 - TRUCK/TRAILER - SECURED CARGO	C-2
2.1.1	CATEGORY 4 - TRUCK TRANSPORTATION OVER US HIGHWAYS	C-2
2.1.2	CATEGORY 4- MISSION/FIELD TRANSPORTATION	C-2
2.1.3	CATEGORY 4- EXPOSURE LEVELS	C-3
2.1.4	CATEGORY 4- EXPOSURE DURATIONS	C-16
2.2	CATEGORY 5 - TRUCK/TRAILER - LOOSE CARGO	C-16
2.3	CATEGORY 6 - TRUCK/TRAILER - LARGE ASSEMBLY TRANSPORT	C-18
2.4	CATEGORY 7 - AIRCRAFT-JET	C-19
2.5	CATEGORY 8 AIRCRAFT - PROPELLER	C-23
2.6	CATEGORY 9 - AIRCRAFT-HELICOPTER	C-27
2.7	CATEGORY 10 - WATERCRAFT - MARINE VEHICLES	C-31
2.8	CATEGORY 11 - RAILROAD - TRAIN	C-31

C TABLES

TABLE 514.8C-I.	CATEGORY 4 - COMMON CARRIER - BREAK POINTS FOR CURVES OF FIGURE 514.8C-2	C-5
TABLE 514.8C-II.	CATEGORY 4 - COMMON CARRIER - BREAK POINTS FOR CURVES OF FIGURE 514.8C-3 (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION)	C-6
TABLE 514.8C-III.	VEHICLES USED FOR TWO-WHEELED TRAILER COMPOSITE	C-7
TABLE 514.8C-IV.	CATEGORY 4 - COMPOSITE TWO-WHEELED TRAILER VIBRATION EXPOSURE - BREAK POINTS FOR CURVES OF FIGURE 514.8C-4	C-9
TABLE 514.8C-V.	CATEGORY 4 - COMPOSITE TWO-WHEELED TRAILER VIBRATION EXPOSURE - BREAK POINTS FOR CURVES OF FIGURE 514.8C-5 (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION)	C-10
TABLE 514.8C-VI.	VEHICLES USED FOR COMPOSITE WHEELED VEHICLE COMPOSITE	C-11
TABLE 514.8C-VII.	CATEGORY 4 - COMPOSITE WHEELED VEHICLE VIBRATION EXPOSURE - BREAK POINTS FOR CURVES OF FIGURE 514.8C-6	C-14
TABLE 514.8C-VIII.	CATEGORY 4 - COMPOSITE WHEELED VEHICLE VIBRATION EXPOSURE - BREAK POINTS FOR CURVES OF FIGURE 514.8C-7 (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION)	C-15
TABLE 514.8C-IX.	CATEGORY 7 - JET AIRCRAFT CARGO VIBRATION EXPOSURE - BREAK POINTS FOR FIGURE 514.8C-9	C-20
TABLE 514.8C-X.	CATEGORY 7 - JET AIRCRAFT VIBRATION EXPOSURE (SAME AS ANNEX D, TABLE 514.8D-I.)	C-22
TABLE 514.8C-XI.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE - 4-BLADED C-130	C-24
TABLE 514.8C-XII.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE - 6-BLADED C-130	C-25
TABLE 514.8C-XIII.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE - OTHER THAN C-130	C-26
TABLE 514.8C-XIVa.	CATEGORY 9 - HELICOPTER PARAMETERS (SAME AS ANNEX D, TABLE 514.8D-IIIA.)	C-30
TABLE 514.8C-XIVb.	CATEGORY 9 - HELICOPTER VIBRATION EXPOSURE (SAME AS ANNEX D, TABLE 514.8D-IIIB.)	C-31

MIL-STD-810H METHOD

514.8 CONTENTS - Continued Paragraph Page ANNEX C FIGURES

FIGURE 514.8C-1.	CATEGORY 4 - TYPICAL MISSION / FIELD TRANSPORTATION SCENARIO.	C-2
FIGURE 514.8C-2.	CATEGORY 4 - COMMON CARRIER - US HIGHWAY TRUCK VIBRATION EXPOSURE.	C-5
FIGURE 514.8C-3.	CATEGORY 4 - COMMON CARRIER - US HIGHWAY TRUCK VIBRATION EXPOSURE. (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION).	C-6
FIGURE 514.8C-4.	CATEGORY 4 - COMPOSITE TWO-WHEELED TRAILER VIBRATION EXPOSURE.	C-9
FIGURE 514.8C-5.	CATEGORY 4 - COMPOSITE TWO-WHEELED TRAILER VIBRATION EXPOSURE. (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION).	C-10
FIGURE 514.8C-6.	CATEGORY 4 - COMPOSITE WHEELED VEHICLE VIBRATION EXPOSURE.	C-14
FIGURE 514.8C-7.	CATEGORY 4 - COMPOSITE WHEELED VEHICLE VIBRATION EXPOSURE. (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION).	C-15
FIGURE 514.8C-8.	CATEGORY 5 - LOOSE CARGO TEST SETUP.	C-18
FIGURE 514.8C-9.	CATEGORY 7 - JET AIRCRAFT CARGO VIBRATION EXPOSURE	C-20
FIGURE 514.8C-10.	CATEGORY 7 - JET AIRCRAFT VIBRATION EXPOSURE (SAME AS ANNEX D, FIGURE 514.8D-1.)	C-21
FIGURE 514.8C-11.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE (4-BLADED C-130).	C-24
FIGURE 514.8C-12.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE (6-BLADED C-130).	C-25
FIGURE 514.8C-13	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE (OTHER THAN C-130).	C-26
FIGURE 514.8C-14	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION ZONES	C-27
FIGURE 514.8C-15	CATEGORY 9 - HELICOPTER VIBRATION EXPOSURE (SAME AS ANNEX D, FIGURE 514.8D-4.).	C-29
FIGURE 514.8C-16.	CATEGORY 10 - HELICOPTER VIBRATION ZONES (SAME AS ANNEX D, FIGURE 514.8D-5.).	C-29
FIGURE 514.8C-17.	CATEGORY 11 - RAIL CARGO VIBRATION EXPOSURE.	C-32

D OPERATIONAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

1.	SCOPE	D-1
1.1	PURPOSE	D-1
1.2	APPLICATION	D-1
1.3	LIMITATIONS	D-1
2.	OPERATIONAL SERVICE	D-1
2.1	CATEGORY 12 - FIXED WING AIRCRAFT - JET AIRCRAFT	D-1
2.2	CATEGORY 13 - PROPELLER AIRCRAFT	D-5
2.3	CATEGORY 14 - ROTARY WING AIRCRAFT - HELICOPTER	D-7
2.4	CATEGORY 15 - AIRCRAFT STORES - ASSEMBLED, JET AIRCRAFT	D-12
2.4.1	CATEGORY 15 - CAPTIVE FLIGHT - EXTERNAL CARRIAGE	D-12
2.4.2	CATEGORY 15 - CAPTIVE FLIGHT - INTERNAL CARRIAGE	D-14
2.4.3	CATEGORY 15 - FREE FLIGHT	D-14
2.4.4	CATEGORY 15 - EXPOSURE LEVELS	D-15
2.4.5	CATEGORY 15 - EXPOSURE DURATIONS	D-15
2.5	CATEGORY 16 - AIRCRAFT STORES - MATERIEL, JET AIRCRAFT	D-20
2.6	CATEGORY 17 - AIRCRAFT STORES - ASSEMBLED/MATERIEL, PROPELLER AIRCRAFT	D-20
2.7	CATEGORY 18 - AIRCRAFT STORES - ASSEMBLED/MATERIEL, HELICOPTER	D-21
2.8	CATEGORY 19 - MISSILES - TACTICAL MISSILES (FREE FLIGHT)	D-21
2.9	CATEGORY 20 - GROUND VEHICLES - GROUND MOBILE	D-21
2.10	CATEGORY 21 - WATERCRAFT - MARINE VEHICLES	D-23
2.11	CATEGORY 22 - ENGINES - TURBINE ENGINES	D-24

MIL-STD-810H

METHOD 514.8 CONTENTS - Continued

Paragraph	Page
ANNEX D
OPERATIONAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION
2.12 CATEGORY 23 - PERSONNEL - MATERIEL CARRIED BY/ON PERSONNEL.	.D-25

D TABLES

TABLE 514.8D-I.	CATEGORY 12 - JET AIRCRAFT VIBRATION EXPOSURE. (SAME AS ANNEX C, TABLE 514.8C-X).	D-4
TABLE 514.8D-II.	CATEGORY 13 - PROPELLER AIRCRAFT VIBRATION EXPOSURE	D-6
TABLE 514.8D-IIIa	CATEGORY 14 - HELICOPTER PARAMETERS (SAME AS ANNEX C, TABLE 514.8C-XIVa).	D-11
TABLE 514.8D-IIIb	CATEGORY 14 - HELICOPTER VIBRATION EXPOSURE (SAME AS ANNEX C, TABLE 514.8C-XIVb).	D-11
TABLE 514.8D-IV.	CATEGORY 15 - JET AIRCRAFT EXTERNAL STORE VIBRATION EXPOSURE.	D-16
TABLE 514.8D-V	DYNAMIC PRESSURE CALCULATION	D-18

D FIGURES

FIGURE 514.8D-1.	CATEGORY 12 - FIXED WING AIRCRAFT - JET AIRCRAFT (SAME AS ANNEX C, FIGURE 514.8C-9).	D-3
FIGURE 514.8D-2.	CATEGORY 13 - PROPELLER AIRCRAFT VIBRATION EXPOSURE	D-6
FIGURE 514.8D-3.	CATEGORY 13 - PROPELLER VIBRATION ZONES.	.D-7
FIGURE 514.8D-4.	CATEGORY 14 - HELICOPTER VIBRATION EXPOSURE.	.D-10
FIGURE 514.8D-5.	CATEGORY 14 - HELICOPTER VIBRATION ZONES.	.D-12
FIGURE 514.8D-6.	CATEGORY 15 - JET AIRCRAFT STORE VIBRATION RESPONSE	.D-15
FIGURE 514.8D-7.	CATEGORY 15 - JET AIRCRAFT STORE BUFFET RESPONSE	.D-17
FIGURE 514.8D-8.	DYNAMIC PRESSURE AS A FUNCTION OF MACH NUMBER AND ALTITUDE	.D-19
FIGURE 514.8D-9.	CATEGORY 16 - JET AIRCRAFT STORE EQUIPMENT VIBRATION EXPOSURE	.D-20
FIGURE 514.8D-10.	CATEGORY 20 - TRACKED VEHICLE REPRESENTATIVE SPECTRAL SHAPE.	D-22
FIGURE 514.8D-11.	CATEGORY 21 - SHIPBOARD RANDOM VIBRATION EXPOSURE	.D-24
FIGURE 514.8D-12.	CATEGORY 22 - TURBINE ENGINE VIBRATION EXPOSURE	.D-25

E SUPPLEMENTAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

1.	SCOPE	E-1
1.1	PURPOSE	E-1
1.2	APPLICATION	E-1
1.3	LIMITATIONS	E-1
2.	SUPPLEMENTAL TESTS	E-1
2.1	SUPPLEMENTAL CONSIDERATIONS	E-1
2.1.1	CATEGORY 24 - MINIMUM INTEGRITY TESTS	E-1
2.1.2	CATEGORY 25 - ALL VEHICLES - CANTILEVERED EXTERNAL MATERIEL	E-4

E FIGURES

FIGURE 514.8E-1.	CATEGORY 24 - GENERAL MINIMUM INTEGRITY EXPOSURE.	E-3
FIGURE 514.8E-2.	CATEGORY 24 - HELICOPTER MINIMUM INTEGRITY EXPOSURE.	E-4

MIL-STD-810H

METHOD 514.8

CONTENTS - Continued Paragraph

Page

F DEVELOPMENT OF LABORATORY VIBRATION TEST SCHEDULES

1.	GENERAL	F-1
2.	REQUIREMENTS	F-1
3.	DEFINITIONS	F-2
4.	NATURE OF VIBRATION	F-2
5.	PLATFORM SPECIFIC CONSIDERATIONS	F-3
5.1	ROAD TRANSPORT - WHEELED VEHICLE	F-3
5.2	ROAD TRANSPORT - TRACKED VEHICLE.	F-3
5.3	AIR TRANSPORT - ROTOR WING	F-4
5.4	AIR TRANSPORT - FIXED WING	F-4
5.5	SEA TRANSPORT	F-4
5.6	RAIL TRANSPORT	F-5
6.	DATA COLLECTION, REVIEW AND SELECTION	F-5
7.	SCENARIO DEVELOPMENT	F-5
7.1	GROUND VEHICLE	F-5
7.1.1	BETA DISTRIBUTION	F-8
7.2	AIRCRAFT	F-10
7.3	SEA VEHICLE	F-11
7.4	RAIL TRANSPORT.	F-11
8.	VSD ALTERNATIVES	F-11
9.	VSD PROCEDURES	F-11
9.1	VSD CONSIDERATIONS.	F-11
9.2	ENGINEERING DATA COMMON ACROSS VSD METHODS	F-12
9.2.1	MINER-PALMGREN HYPOTHESIS.	F-12
9.2.1.1	S/N CURVE	F-12
9.2.1.2	MINER-PALMGREN EQUATIONS.	F-13
10.	PREDICTIONS OF MAXIMUM RESPONSE	F-19
11.	SUMMARY AND CONCLUSION	F-20

F TABLES

TABLE 514.8F-I.	LIFETIME SCENARIO BREAKOUT - EXAMPLE ONLY	F-7
TABLE 514.8F-II.	SELECTION OF ALPHA FOR BETA DISTRIBUTION	F-8
TABLE 514.8F-III.	DEFAULT VALUES FOR M	F-16
TABLE 514.8F-IV.	METALS AND MATERIAL PROPERTIES	F-18

F FIGURES

FIGURE 514.8F-1.	SAMPLE BETA DISTRIBUTION (WHEELED VEHICLE)	F-9
FIGURE 514.8F-2.	S/N CURVE	F-13
FIGURE 514.8F-3.	TYPICAL STRAIN LIFE CURVE	F-14
FIGURE 514.8F-4.	RELATIVE DAMAGE AS A FUNCTION OF SURFACE FINISH - SAE-8630 STEEL	F-15
FIGURE 514.8F-5.	RELATIVE DAMAGE AS A FUNCTION OF STRAIN RANGE - SAE 8630 STEEL	F-16
FIGURE 514.8F-6.	TYPICAL S-N CURVE	F-19

MIL-STD-810H

METHOD 514.8

CONTENTS - Continued

Paragraph		Page
ANNEX F APPENDICIES
APPENDIX A. PREPARATION FOR VSD - DATA ACQUISITION		F-A1
1.	INTRODUCTION	F-A1
2.	VEHICLE PREPARATION FOR DATA ACQUISITION - CARGO	F-A1
2.1	SPECIFIED LOAD	F-A1
2.2	GENERAL CARGO SIMULATED LOAD	F-A1
2.3	TIE-DOWN	F-A1
2.4	ACCELEROMETERS	F-A1
3.	VEHICLE PREPARATION FOR DATA ACQUISITION – INSTALLED EQUIPMENT	F-A1
4.	DATA ACQUISITION PROCEDURE	F-A2
4.1	DATA ACQUISITION	F-A2
4.2	CARGO SCHEDULES	F-A2
4.3	INSTALLED EQUIPMENT SCHEDULES	F-A2
5.	DATA REQUIRED	F-A2
APPENDIX B. COMBINATION OF SPECTRA (STATISTICAL)		F-B1
1.	COMBINING SPECTRA	F-B1
1.1	AUTO AND CROSS SPECTRAL DENSITIES	F-B1
1.2	CONFIDENCE INTERVAL OF ASD ESTIMATES	F-B2
2.	STATISTICAL CONSIDERATIONS FOR DEVELOPING LIMITS ON AN ENSEMBLE OF DATA	F-B3
2.1	BASIC ESTIMATE ASSUMPTIONS	F-B3
2.2	BASIC ESTIMATE SUMMARY PREPROCESSING	F-B4
2.3	PARAMETRIC UPPER LIMIT STATISTICAL ESTIMATE ASSUMPTIONS	F-B4
2.3.1	NTL - UPPER NORMAL ONE-SIDED TOLERANCE LIMIT	F-B5
2.3.2	NPL - UPPER NORMAL PREDICTION LIMIT	F-B6
2.4	NONPARAMETRIC UPPER LIMIT STATISTICAL ESTIMATE ASSUMPTIONS	F-B6
2.4.1	ENV - UPPER LIMIT	F-B6
2.5	DFL-UPPER DISTRIBUTION-FREE TOLERANCE LIMIT	F-B7
2.6	ETL - UPPER EMPIRICAL TOLERANCE LIMIT	F-B7
2.7	EXAMPLE FROM MEASURED DATA	F-B8
3.	COMMON ANALYSIS FUNCTIONS AND STATISTICAL DEFINITIONS OF VSD DATA ENSEMBLES	F-B9

ANNEX F, APPENDIX B TABLES
TABLE 514.8F-B.I. NORMAL TOLERANCE FACTORS FOR UPPER TOLERANCE LIMIT	F-B6

F , APPENDIX B FIGURES

FIGURE 514.8F-B.1. 90-PERCENT CONFIDENCE LIMITS FOR n_d = 31 LINEAR SPECTRAL AVERAGES	F-B3
FIGURE 514.8F-B.2. EXAMPLE NORMAL TOLERANCE LIMIT APPLIED TO TYPICAL WHEELED VEHICLE DATA	F-B8
FIGURE 514.8F-B.3. AVERAGE, AVERAGE PLUS STANDARD DEVIATION, AND PEAK SPECTRA	F-B10
FIGURE 514.8F-B.4. COMBINATION OF 24 INDIVIDUAL SPECTRA	F-B11

MIL-STD-810H METHOD

514.8 CONTENTS - Continued Paragraph Page ANNEX F, APPENDIX B FIGURES

ANNEX F, APPENDIX C TABLES
FIGURE	514.8F-B.5. COMPARISON OF RESULTANT TEST SPECTRUM TO ENVELOPE OF INDIVIDUAL SPECTRA	F-B12
APPENDIX C.	COMBINATION OF SPECTRA (FATIGUE DAMAGE SPECTRA)	F-C1
1.	FATIGUE DAMAGE SPECTRUM METHOD OF COMBINING SPECTRA	F-C1
2.	EXAMPLE APPLICATION OF FATIGUE DAMAGE SPECTRUM	F-C2
3.	FDS APPROACH TO DEVELOPMENT OF A LVTS ..	F-C9
TABLE	514.8F-C.I. TEST COURSE LENGTHS, SPEEDS AND EXPOSURE TIMES	.F-C2
ANNEX F, APPENDIX C FIGURES
FIGURE	514.8F-C.1. FATIGUE DAMAGE SPECTRA FOR SPECIFIC TEST COURSES	.F-C3
FIGURE	514.8F-C.2. CUMULATIVE FATIGUE DAMAGE SPECTRUM	.F-C4
FIGURE	514.8F-C.3. CUMULATIVE FATIGUE SPECTRA FROM LOCATIONS 1 AND 2	.F-C5
FIGURE	514.8F-C.4. COMBINED VIBRATION POWER SPECTRA DEVELOPED FROM AVERAGE AND MAXIMUM FATIGUE DAMAGE SPECTRA	.F-C6
FIGURE	514.8F-C.5. COMPARISON OF COMBINED VIBRATION POWER SPECTRUM DEVELOPED FROM THE FATIGUE DAMAGE SPECTRUM, FROM THE STATISTICAL PROCESS AND FROM AN ENVELOPE PROCESS	.F-C7
FIGURE	514.8F-C.6. FATIGUE DAMAGE SPECTRA FOR TWO EXPONENTS	.F-C8
FIGURE	514.8F-C.7. COMPARISON OF COMBINED VIBRATION POWER SPECTRA DEVELOPED FROM TWO EXPONENTS	.F-C9
FIGURE	514.8F-C.8. TIME COMPRESSION OF ASD'S COMPUTED FROM THE INVERSE CUMULATIVE FATIGUE DAMAGE SPECTRUM.	.F-C10
APPENDIX D.	VIBRATION SPECIFICATION DEVELOPMENT PROCEDURE	F-D1
1.	INTRODUCTION	F-D1
2.	BROADBAND PROFILE DEVELOPMENT	F-D2
2.1	FILE SETUP (STEP 1)..	F-D2
2.2	SELECT EVENT START AND END TIME (STEP 2)	F-D3
2.3	TIME BLOCK DROP (STEP 3)	F-D3
2.4	CALCULATE ASD AVERAGE (STEP 4).	F-D3
2.5	SPECTRAL SPIKE REMOVAL (STEP 5)	F-D4
2.6	SCENARIO TABLE (STEP 6).	F-D6
2.7	CALCULATE WEIGHTED ASD (STEP 7)	F-D9
2.8	CALCULATE WEIGHTED INTERMEDIATE LVTS (STEP 8).	F-D10
3.	NARROWBAND RANDOM SPECIFICATION DEVELOPMENT PROCEDURE	F-D11
4.	SINE TONE SPECIFICATION DEVELOPMENT PROCEDURE	F-D13
5.	ALTERNATE BROADBAND DEVELOPMENT BASED ON FATIGUE DAMAGE SPECTRUM	F-D15
6.	FINAL DEVELOPMENT PROCEDURES	F-D16
7.	COMBINING LVTS	F-D16

MIL-STD-810H METHOD

514.8 CONTENTS - Continued

Paragraph	Page
ANNEX F, APPENDIX D TABLES
TABLE 514.8F-D.I. REQUIRED PARAMETERS	F-D2
TABLE 514.8F-D.II. SINGLE-EVENT ASD SUM-SET..	F-D4
TABLE 514.8F-D.III. SPECTRAL SPIKE REMOVED TABLE, AVERAGE	F-D6
TABLE 514.8F-D.IV. SCENARIO TABLE INPUT.	F-D7
TABLE 514.8F-D.V. RUNTIME CALCULATION..	F-D8
TABLE 514.8F-D.VI. GROUP SUM-SET DEFINITION	F-D9
TABLE 514.8F-D.VII. NARROWBAND RANDOM CALCULATIONS	F-D12
TABLE 514.8F-D.VIII. SINE TONE CALCULATIONS	F-D14
TABLE 514.8F-D.IX. LVTS COMBINATION EXAMPLE	F-D17
ANNEX F, APPENDIX D FIGURES
FIGURE 514.8F-D.1. VSD FLOWCHART.	F-D1
FIGURE 514.8F-D.2. SPECTRAL SPIKE REMOVAL WINDOW	F-D5
APPENDIX E. THEORETICAL ASPECTS OF MAXIMUM RESPONSE	F-E1
1. INTRODUCTION.	F-E1
2. SINUSOIDAL EXCITATION	F-E1
3. SWEPT SINE EXCITATION..	F-E2
4. RANDOM VIBRATION EXCITATION.	F-E2
ANNEX F, APPENDIX E FIGURES
FIGURE 514.8F-E.1. MRS FOR A FIXED SINE EXCITATION AT 500 HZ WITH Q=5.	F-E2
FIGURE 514.8F-E.2. MRS FOR A SWEPT SINE FROM 300 HZ TO 1200 Hz.	F-E2
FIGURE 514.8F-E.3. MRS FOR A RANDOM VIBRATION	F-E3
APPENDIX F. ANNEX F REFERENCES	F-F1

MIL-STD-810H METHOD

514.8 METHOD

514.8 VIBRATION

NOTE: Tailoring is essential. Select methods, procedures, and parameter levels based on the tailoring process described in Part One, paragraph 4, and Part One, Annex C. Apply the general guidelines for laboratory test methods described in Part One, paragraph 5 of this standard. For vibration schedule development, see Annex F.

The vibration profiles provided in Annexes B through E of this Method are default curves that are generally developed as a composite of multiple locations acquired from multiple vehicles of a similar construct. For technical guidance / contact information regarding the existence and availability of either item-specific or location-specific vibration profiles that may reside in various archives, see Part One, page iii, for Service points-of-contact. In addition, Test Operations Procedure (TOP) 01-2-601 (paragraph 6.1, reference d), includes an assortment of specific ground vehicle vibration data and TOP 01-2-603 (paragraph 6.1 reference xx) includes several specific helicopter vibration data.

Organization. The main body of this Method is arranged similarly to the other methods of MIL-STD-810H. A considerable body of supplementary information is included in the Annexes. With the exception of Table 514.8-I, all tables and figures for the entire method are in Annexes B through F. Annex A provides definitions and engineering guidance useful in interpreting and applying this Method. Annexes B through F provide guidance for estimating vibration levels and durations and for selection of test procedures. Reference citations to external documents are at the end of the main body (paragraph 6). It is highly recommended that users read Annex A before applying the vibration schedules in Annexes B through E or the vibration schedule development process in Annex F. The Annexes are as follows:

ANNEX A – ENGINEERING INFORMATION

ANNEX B – MANUFACTURE / MAINTENANCE TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

ANNEX C – TRANSPORTATION TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

ANNEX D – OPERATIONAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

ANNEX E – SUPPLEMENTAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

ANNEX F – DEVELOPMENT OF LABORATORY VIBRATION TEST SCHEDULES

514.8 ANNEX A METHOD 514.8, ANNEX A

Engineering Information

NOTE: Unless specifically noted, all document references refer to paragraph 6.1 in the front part of this Method.

514.8 ANNEX A

fully verify materiel function. This arrangement has proven to be a good way of adequately verifying that materiel survives endurance testing in all respects.

514.8 ANNEX A

to failure). Fatigue damage outside this region can be described by a power law model in the form of Equation (1) with an exponent “m” that is not equal to “b.” The value of “m” is strongly influenced by the material S-N curve, but fatigue life is also influenced by the surface finish, the treatment, the effect of mean stress correction, the contributions of elastic and plastic strain, the waveshape of the strain time history, etc. Therefore, the value of “m” is generally some proportion of the negative reciprocal of the slope of the S-N curve, known as the fatigue strength exponent and designated as “-1/b.” Typical values of “m” are 80 percent of “-1/b” for random waveshapes, and 60 percent of “-1/b” for sinusoidal waveshapes. Historically, a value of m = 7.5 has been used for random environments, but values between 5 and 8 are commonly used. A value of 6 is commonly used for sinusoidal environments. This cumulative damage assumption is based on the fatigue properties of metals. Paragraph 6.1, reference aa (chapter 35) recommends that Miner’s cumulative damage theory not be used for composite materials. However, a “wearout model,” defined as “the deterioration of a composite structure to the point where it can no longer fulfill its intended purpose,” is shown as a power law model in the form of Equation (1) with variable exponents dependent upon the type of composite system. It is recommended that test time compression for composite structures be treated on a case-by-case basis.

Since most vibration environments are expressed in terms of the auto spectral density function, Equation (1) can also be formulated as:

$\frac{t_{2}}{t_{1}}=\left[\frac{W(f)_{1}}{W(f)_{2}}\right]^{m/2}$ Equation (4)

where:

t1 = equivalent test time

t2 = in-service time for specified condition

W(f)1 ASD at test condition, g²/Hz

W(ƒ)2 = ASD at in-service condition, g2/Hz

[The ratio W(ƒ)1 /W(ƒ)2 is commonly known as the exaggeration factor]

mas stated in Equation (1)

In many instances these equations appear to offer a satisfactory solution. However, caution should always be exercised in the application of the equations. Some methods of characterizing vibration severities, notably ASDs, do not necessarily reproduce under laboratory testing the same strain responses as those experienced under in-service conditions. Exaggeration factors for materials whose fatigue characteristics are unknown or for failure mechanisms other than fatigue (such as loosening of threaded connections) cannot be calculated. Real time test levels and durations should be used in these instances unless there is sufficient information about the particular application to allow for the use of a reasonable exaggeration factor. It is recommended that the exaggeration factor be kept to a minimum value consistent with the constraints of in-service time and desired test time, and should generally not exceed values of 2 (S1/S2) or 4 (W(f)1/W(f)2).

Note: Using material S-N curves results in different equivalencies for different parts in a given test item. A decision will be required as to which equivalency to use to establish test criteria.

514.8 ANNEX A

the sinusoid(s) frequency(s) through bands representative of frequency variations in the environment and resonant frequency variations in materiel (see paragraph 2.4.3 below).

514.8 ANNEX A

b. Items acting as structural members. When materiel is installed such that it acts as a structural member of the platform, it will affect vibrations and it will be structurally loaded. This is particularly important for relatively large materiel items, but it applies to materiel of any size. In these cases, the materiel structure adds to the stiffness of the platform and may significantly affect vibration modes and frequencies. Further, the materiel will be subjected to structural loads for which it may not have been designed. An example is a beam tied down to the cargo deck of a truck, aircraft, or ship. If the tie-downs are not designed to slip at appropriate points, the beam becomes a structural part of the deck. When the deck bends or twists, the beam is loaded and it changes the load paths of the platform structure. This may be catastrophic for the beam, the platform, or both. Be careful in the design of structural attachments to assure that the materiel does not act as a structural member.
c. Large item mass relative to supporting structures. When materiel items are small relative to the overall platform, but large relative to supporting structures, account for the change in local vibration levels, if practical. This effect is discussed in Annex D, paragraph 2.1 for materiel mounted in jet aircraft. Due to differences in environments, relative sizes, and structural methods, the factor defined in Annex C, Table 514.8C-X is not applicable to materiel mounted in small, unmanned aircraft.
d. Large item size/mass relative to platform. When materiel is large in size or mass relative to the platform, always consider the potential of damage to the platform as a result of materiel vibration. It is imperative to consider these effects in the design of vibration test fixtures. Otherwise, the vibration transmitted to the test item may be greatly different than intended.

514.8 ANNEX A

shapes, modal damping, etc.). Modal parameters are used to confirm or generate analytical models, investigate problems, determine appropriate instrumentation locations, evaluate measured vibration data, design test fixtures, etc. Modal analysis methods range from frequency domain, single degree of freedom methods, to time domain, multi-degree of freedom methods (paragraph 6.1, references dd and ee).

514.8 ANNEX A

b. Indicated airspeed. Another form of airspeed measurement is indicated airspeed. Calibrated airspeed is indicated airspeed when empirical corrections are added to account for factors in the specific aircraft installation. Indicated airspeed is expressed in various units (kilometers per hour, miles per hour, and knots), but in military aircraft it is normally in knots indicated airspeed (Kias).
c. Equivalent airspeed. Equivalent airspeed is a form directly related to dynamic pressure. It is sometimes used in engineering calculations since other forces (lift, drag, and structural air-loads) acting on an airframe are also proportional to dynamic pressure. However, it is not used in airspeed measurement systems or flight handbooks. Equivalent airspeed may be expressed in various units, but it is usually seen as knots equivalent airspeed (Keas).
d. True airspeed. This is the actual airspeed. To calculate true airspeed with an aircraft air data system, local atmospheric properties must be accurately known. This was not practical until recent years and aircraft generally do not use true airspeed in handbooks or to navigate. True airspeed may be expressed in various units but it is usually seen as knots true airspeed (Ktas).
e. Mach number. Mach number is the ratio of true airspeed to the speed of sound. When Mach number is measured by an aircraft air data system, it is true Mach number.

514.8 ANNEX A

a. The total change in mass of the unit and of each subassembly is within ±10 percent.
b. The unit center of gravity is within ±10 percent of the original location in any direction.
c. The mounting configuration is unchanged.
d. The mounting configuration of circuit cards is unchanged.
e. The first three natural frequencies of the chassis and the first natural frequency of each subassembly are within ±5 percent of the original frequencies.
f. The first natural frequency of each circuit board is within ±10 percent of the original frequency.
g. Each modified circuit card is vibrated for one hour in the axis perpendicular to the plane of the board. Use a test exposure that is 0.04 g²/Hz from 15 to 1000 Hz rolled off at 6 dB per octave to 2000 Hz. Maintain electrical continuity throughout the card during and after the test. (Where vibration levels and durations at board level are known, these may be substituted for the stated exposure.)
h. Changes to mounts, chassis, internal support structures, and circuit card materials are to materials with equal or greater high cycle fatigue strength.

MIL-STD-810H METHOD 514.8, ANNEX B

METHOD 514.8, ANNEX B Manufacture / Maintenance Tailoring Guidance for Vibration Exposure Definition

514.8Method 514.8 vibration contents

MIL-STD-810H, Environmental Engineering Considerations and Laboratory Tests

Last Updated 29 Oct 2026

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Paragraph		Page
1.	SCOPE	1
1.1	PURPOSE	1
1.2	APPLICATION	1
1.3	LIMITATIONS	4
2.	TAILORING GUIDANCE	4
2.1	SELECTING THE METHOD	4
2.1.1	EFFECTS OF ENVIRONMENT	5
2.1.2	SEQUENCE	6
2.2	SELECTING PROCEDURES	6
2.2.1	PROCEDURE SELECTION CONSIDERATIONS	6
2.2.2	DIFFERENCE AMONG PROCEDURES	7
2.3	DETERMINE TEST LEVELS AND CONDITIONS	7
2.3.1	CLIMATIC CONDITIONS	7
2.3.2	TEST ITEM CONFIGURATION	8
2.3.3	MULTI EXCITER CONSIDERATION	8
2.4	TEST ITEM OPERATION	8
3.	INFORMATION REQUIRED	8
3.1	PRETEST	9
3.2	DURING TEST	10
3.3	POST-TEST	10
4.	TEST PROCESS	10
4.1	TEST FACILITY	10
4.1.1	PROCEDURE I - GENERAL VIBRATION	10
4.1.2	PROCEDURE II - LOOSE CARGO TRANSPORTATION	11
4.1.3	PROCEDURE III - LARGE ASSEMBLY TRANSPORT	11
4.1.4	PROCEDURE IV - ASSEMBLED AIRCRAFT STORE CAPTIVE CARRIAGE AND FREE FLIGHT	11
4.2	CONTROLS, TOLERANCES, AND INSTRUMENTATION	11
4.2.1	CONTROL STRATEGY	11
4.2.1.1	ACCELERATION INPUT CONTROL STRATEGY	11
4.2.1.2	FORCE CONTROL STRATEGY	12
4.2.1.3	ACCELERATION LIMIT STRATEGY	12
4.2.1.4	ACCELERATION RESPONSE CONTROL STRATEGY	12
4.2.1.5	WAVEFORM CONTROL STRATEGY	12
4.2.2	TOLERANCES	13
4.2.2.1	ACCELERATION SPECTRAL DENSITY	13
4.2.2.2	PEAK SINUSOIDAL ACCELERATION	15
4.2.2.3	FREQUENCY MEASUREMENT	16
4.2.2.4	CROSS AXIS ACCELERATIONS	16
4.2.3	INSTRUMENTATION	17
4.3	TEST INTERRUPTION	17
4.3.1	INTERRUPTION DUE TO LABORATORY EQUIPMENT MALFUNCTION	17

MIL-STD-810H METHOD

514.8 CONTENTS - Continued

Paragraph		Page
4.3.2	INTERRUPTION DUE TO TEST ITEM OPERATION FAILURE	18
4.3.3	INTERRUPTION DUE TO SCHEDULED EVENT.	18
4.3.4	INTERRUPTION DUE TO EXCEEDING TEST TOLERANCES	18
4.4	TEST SETUP	19
4.4.1	PROCEDURE I - GENERAL VIBRATION..	19
4.4.2	PROCEDURE II - LOOSE CARGO TRANSPORTATION.	19
4.4.3	PROCEDURE III - LARGE ASSEMBLY TRANSPORT..	19
4.4.4	PROCEDURE IV - ASSEMBLED AIRCRAFT STORE CAPTIVE CARRIAGE AND FREE FLIGHT.	20
4.5	TEST EXECUTION.	21
4.5.1	PREPARATION FOR TEST..	22
4.5.1.1	PRELIMINARY STEPS	22
4.5.1.2	PRETEST STANDARD AMBIENT CHECKOUT..	22
4.5.2	PROCEDURE I - GENERAL VIBRATION..	22
4.5.3	PROCEDURE II - LOOSE CARGO TRANSPORTATION.	23
4.5.4	PROCEDURE III - LARGE ASSEMBLY TRANSPORT	23
4.5.5	PROCEDURE IV - ASSEMBLED AIRCRAFT STORE CAPTIVE CARRIAGE AND FREE FLIGHT.	24
5.	ANALYSIS OF RESULTS	26
5.1	PHYSICS OF FAILURE	26
5.2	QUALIFICATION TESTS	26
5.3	OTHER TESTS.	26
6.	REFERENCE/RELATED DOCUMENTS	26
6.1	REFERENCED DOCUMENTS	26
6.2	RELATED DOCUMENTS	29
TABLE

TABLE 514.8-I.	VIBRATION ENVIRONMENT CATEGORIES.	3
TABLE 514.8-II	RANDOM VIBRATION TEST TOLERANCES	14
TABLE 514.8-III	SINUSOIDAL VIBRATION TEST TOLERANCES	16

A ENGINEERING INFORMATION

1.	SCOPE.	A-1
1.1	PURPOSE.	A-1
1.2	APPLICATION.	A-1
1.3	LIMITATIONS	A-1
2.	ENGINEERING INFORMATION.	A-1
2.1	VIBRATION TEST TYPES.	A-1
2.1.1	DEVELOPMENT TEST.	A-1
2.1.2	QUALIFICATION TEST.	A-1
2.1.2.1	FUNCTIONAL TEST.	A-2
2.1.2.2	ENDURANCE TEST.	A-2
2.1.3	DURABILITY TEST.	A-2
2.1.4	RELIABILITY TEST.	A-2
2.1.4.1	STATISTICAL RELIABILITY TEST	A-3
2.1.4.2	RELIABILITY GROWTH TEST	A-3

MIL-STD-810H METHOD

514.8 CONTENTS - Continued

Paragraph		Page
2.1.5	WORTHINESS TEST	.A-3
2.1.6	ENVIRONMENTAL STRESS SCREENING (ESS)	.A-3
2.2	TEST TIME COMPRESSION AND THE FATIGUE RELATIONSHIP	.A-3
2.3	VIBRATION CHARACTERIZATION	.A-5
2.3.1	RANDOM VIBRATION	.A-6
2.3.2	SINUSOIDAL VIBRATION	.A-6
2.3.3	MIXED BROADBAND AND NARROWBAND VIBRATION	.A-6
2.3.4	TRANSIENT VIBRATION	.A-7
2.3.5	RANDOM VERSUS SINUSOIDAL VIBRATION EQUIVALENCE	.A-7
2.3.6	COMBINATION OF TEST SPECTRA	.A-7
2.4	PLATFORM/MATERIEL AND FIXTURE/TEST ITEM INTERACTION	.A-7
2.4.1	MECHANICAL IMPEDANCE	.A-7
2.4.2	VIBRATION ISOLATION	.A-8
2.4.3	MATERIEL RESONANT FREQUENCY VARIATION	.A-8
2.5	MODAL TEST AND ANALYSIS	.A-8
2.5.1	MODAL TEST TECHNIQUES	.A-9
2.5.2	MATERIAL NON-LINEAR BEHAVIOR	.A-9
2.6	AERODYNAMIC EFFECTS	.A-9
2.6.1	DYNAMIC PRESSURE	.A-9
2.6.2	AIRSPEED	.A-9
2.6.3	ALTITUDE	.A-10
2.7	SIMILARITY	.A-10
2.7.1	UNMODIFIED MATERIEL	.A-10
2.7.2	MODIFIED MATERIEL	.A-10
2.7.3	EQUAL VIBRATION ENVIRONMENT	.A-11
2.7.4	RELIABILITY DATA	.A-11
2.7.5	CRITICAL RESONANT RESPONSE	.A-11
2.7.6	DYNAMIC SIMILARITY	.A-11

B MANUFACTURE / MAINTENANCE TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

1.	SCOPE	B-1
1.1	PURPOSE.	B-1
1.2	APPLICATION.	B-1
1.3	LIMITATIONS.	B-1
2.	MANUFACTURE/MAINTENANCE	B-1
2.1	CATEGORY 1 - MANUFACTURING/MAINTENANCE PROCESSES	B-1
2.2	CATEGORY 2 - SHIPPING AND HANDLING	B-1
2.3	CATEGORY 3 - ENVIRONMENTAL STRESS SCREENING (ESS)	B-1

MIL-STD-810H

METHOD 514.8

CONTENTS - Continued Paragraph

Page

C TRANSPORTATION TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

1.	SCOPE	C-1
1.1	PURPOSE	C-1
1.2	APPLICATION	C-1
1.3	LIMITATIONS	C-1
2.	TRANSPORTATION	C-1
2.1	CATEGORY 4 - TRUCK/TRAILER - SECURED CARGO	C-2
2.1.1	CATEGORY 4 - TRUCK TRANSPORTATION OVER US HIGHWAYS	C-2
2.1.2	CATEGORY 4- MISSION/FIELD TRANSPORTATION	C-2
2.1.3	CATEGORY 4- EXPOSURE LEVELS	C-3
2.1.4	CATEGORY 4- EXPOSURE DURATIONS	C-16
2.2	CATEGORY 5 - TRUCK/TRAILER - LOOSE CARGO	C-16
2.3	CATEGORY 6 - TRUCK/TRAILER - LARGE ASSEMBLY TRANSPORT	C-18
2.4	CATEGORY 7 - AIRCRAFT-JET	C-19
2.5	CATEGORY 8 AIRCRAFT - PROPELLER	C-23
2.6	CATEGORY 9 - AIRCRAFT-HELICOPTER	C-27
2.7	CATEGORY 10 - WATERCRAFT - MARINE VEHICLES	C-31
2.8	CATEGORY 11 - RAILROAD - TRAIN	C-31

C TABLES

TABLE 514.8C-I.	CATEGORY 4 - COMMON CARRIER - BREAK POINTS FOR CURVES OF FIGURE 514.8C-2	C-5
TABLE 514.8C-II.	CATEGORY 4 - COMMON CARRIER - BREAK POINTS FOR CURVES OF FIGURE 514.8C-3 (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION)	C-6
TABLE 514.8C-III.	VEHICLES USED FOR TWO-WHEELED TRAILER COMPOSITE	C-7
TABLE 514.8C-IV.	CATEGORY 4 - COMPOSITE TWO-WHEELED TRAILER VIBRATION EXPOSURE - BREAK POINTS FOR CURVES OF FIGURE 514.8C-4	C-9
TABLE 514.8C-V.	CATEGORY 4 - COMPOSITE TWO-WHEELED TRAILER VIBRATION EXPOSURE - BREAK POINTS FOR CURVES OF FIGURE 514.8C-5 (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION)	C-10
TABLE 514.8C-VI.	VEHICLES USED FOR COMPOSITE WHEELED VEHICLE COMPOSITE	C-11
TABLE 514.8C-VII.	CATEGORY 4 - COMPOSITE WHEELED VEHICLE VIBRATION EXPOSURE - BREAK POINTS FOR CURVES OF FIGURE 514.8C-6	C-14
TABLE 514.8C-VIII.	CATEGORY 4 - COMPOSITE WHEELED VEHICLE VIBRATION EXPOSURE - BREAK POINTS FOR CURVES OF FIGURE 514.8C-7 (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION)	C-15
TABLE 514.8C-IX.	CATEGORY 7 - JET AIRCRAFT CARGO VIBRATION EXPOSURE - BREAK POINTS FOR FIGURE 514.8C-9	C-20
TABLE 514.8C-X.	CATEGORY 7 - JET AIRCRAFT VIBRATION EXPOSURE (SAME AS ANNEX D, TABLE 514.8D-I.)	C-22
TABLE 514.8C-XI.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE - 4-BLADED C-130	C-24
TABLE 514.8C-XII.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE - 6-BLADED C-130	C-25
TABLE 514.8C-XIII.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE - OTHER THAN C-130	C-26
TABLE 514.8C-XIVa.	CATEGORY 9 - HELICOPTER PARAMETERS (SAME AS ANNEX D, TABLE 514.8D-IIIA.)	C-30
TABLE 514.8C-XIVb.	CATEGORY 9 - HELICOPTER VIBRATION EXPOSURE (SAME AS ANNEX D, TABLE 514.8D-IIIB.)	C-31

MIL-STD-810H METHOD

514.8 CONTENTS - Continued Paragraph Page ANNEX C FIGURES

FIGURE 514.8C-1.	CATEGORY 4 - TYPICAL MISSION / FIELD TRANSPORTATION SCENARIO.	C-2
FIGURE 514.8C-2.	CATEGORY 4 - COMMON CARRIER - US HIGHWAY TRUCK VIBRATION EXPOSURE.	C-5
FIGURE 514.8C-3.	CATEGORY 4 - COMMON CARRIER - US HIGHWAY TRUCK VIBRATION EXPOSURE. (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION).	C-6
FIGURE 514.8C-4.	CATEGORY 4 - COMPOSITE TWO-WHEELED TRAILER VIBRATION EXPOSURE.	C-9
FIGURE 514.8C-5.	CATEGORY 4 - COMPOSITE TWO-WHEELED TRAILER VIBRATION EXPOSURE. (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION).	C-10
FIGURE 514.8C-6.	CATEGORY 4 - COMPOSITE WHEELED VEHICLE VIBRATION EXPOSURE.	C-14
FIGURE 514.8C-7.	CATEGORY 4 - COMPOSITE WHEELED VEHICLE VIBRATION EXPOSURE. (UNKNOWN OR VARIABLE TEST ITEM ORIENTATION).	C-15
FIGURE 514.8C-8.	CATEGORY 5 - LOOSE CARGO TEST SETUP.	C-18
FIGURE 514.8C-9.	CATEGORY 7 - JET AIRCRAFT CARGO VIBRATION EXPOSURE	C-20
FIGURE 514.8C-10.	CATEGORY 7 - JET AIRCRAFT VIBRATION EXPOSURE (SAME AS ANNEX D, FIGURE 514.8D-1.)	C-21
FIGURE 514.8C-11.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE (4-BLADED C-130).	C-24
FIGURE 514.8C-12.	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE (6-BLADED C-130).	C-25
FIGURE 514.8C-13	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION EXPOSURE (OTHER THAN C-130).	C-26
FIGURE 514.8C-14	CATEGORY 8 - PROPELLER AIRCRAFT VIBRATION ZONES	C-27
FIGURE 514.8C-15	CATEGORY 9 - HELICOPTER VIBRATION EXPOSURE (SAME AS ANNEX D, FIGURE 514.8D-4.).	C-29
FIGURE 514.8C-16.	CATEGORY 10 - HELICOPTER VIBRATION ZONES (SAME AS ANNEX D, FIGURE 514.8D-5.).	C-29
FIGURE 514.8C-17.	CATEGORY 11 - RAIL CARGO VIBRATION EXPOSURE.	C-32

D OPERATIONAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

1.	SCOPE	D-1
1.1	PURPOSE	D-1
1.2	APPLICATION	D-1
1.3	LIMITATIONS	D-1
2.	OPERATIONAL SERVICE	D-1
2.1	CATEGORY 12 - FIXED WING AIRCRAFT - JET AIRCRAFT	D-1
2.2	CATEGORY 13 - PROPELLER AIRCRAFT	D-5
2.3	CATEGORY 14 - ROTARY WING AIRCRAFT - HELICOPTER	D-7
2.4	CATEGORY 15 - AIRCRAFT STORES - ASSEMBLED, JET AIRCRAFT	D-12
2.4.1	CATEGORY 15 - CAPTIVE FLIGHT - EXTERNAL CARRIAGE	D-12
2.4.2	CATEGORY 15 - CAPTIVE FLIGHT - INTERNAL CARRIAGE	D-14
2.4.3	CATEGORY 15 - FREE FLIGHT	D-14
2.4.4	CATEGORY 15 - EXPOSURE LEVELS	D-15
2.4.5	CATEGORY 15 - EXPOSURE DURATIONS	D-15
2.5	CATEGORY 16 - AIRCRAFT STORES - MATERIEL, JET AIRCRAFT	D-20
2.6	CATEGORY 17 - AIRCRAFT STORES - ASSEMBLED/MATERIEL, PROPELLER AIRCRAFT	D-20
2.7	CATEGORY 18 - AIRCRAFT STORES - ASSEMBLED/MATERIEL, HELICOPTER	D-21
2.8	CATEGORY 19 - MISSILES - TACTICAL MISSILES (FREE FLIGHT)	D-21
2.9	CATEGORY 20 - GROUND VEHICLES - GROUND MOBILE	D-21
2.10	CATEGORY 21 - WATERCRAFT - MARINE VEHICLES	D-23
2.11	CATEGORY 22 - ENGINES - TURBINE ENGINES	D-24

MIL-STD-810H

METHOD 514.8 CONTENTS - Continued

Paragraph	Page
ANNEX D
OPERATIONAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION
2.12 CATEGORY 23 - PERSONNEL - MATERIEL CARRIED BY/ON PERSONNEL.	.D-25

D TABLES

TABLE 514.8D-I.	CATEGORY 12 - JET AIRCRAFT VIBRATION EXPOSURE. (SAME AS ANNEX C, TABLE 514.8C-X).	D-4
TABLE 514.8D-II.	CATEGORY 13 - PROPELLER AIRCRAFT VIBRATION EXPOSURE	D-6
TABLE 514.8D-IIIa	CATEGORY 14 - HELICOPTER PARAMETERS (SAME AS ANNEX C, TABLE 514.8C-XIVa).	D-11
TABLE 514.8D-IIIb	CATEGORY 14 - HELICOPTER VIBRATION EXPOSURE (SAME AS ANNEX C, TABLE 514.8C-XIVb).	D-11
TABLE 514.8D-IV.	CATEGORY 15 - JET AIRCRAFT EXTERNAL STORE VIBRATION EXPOSURE.	D-16
TABLE 514.8D-V	DYNAMIC PRESSURE CALCULATION	D-18

D FIGURES

FIGURE 514.8D-1.	CATEGORY 12 - FIXED WING AIRCRAFT - JET AIRCRAFT (SAME AS ANNEX C, FIGURE 514.8C-9).	D-3
FIGURE 514.8D-2.	CATEGORY 13 - PROPELLER AIRCRAFT VIBRATION EXPOSURE	D-6
FIGURE 514.8D-3.	CATEGORY 13 - PROPELLER VIBRATION ZONES.	.D-7
FIGURE 514.8D-4.	CATEGORY 14 - HELICOPTER VIBRATION EXPOSURE.	.D-10
FIGURE 514.8D-5.	CATEGORY 14 - HELICOPTER VIBRATION ZONES.	.D-12
FIGURE 514.8D-6.	CATEGORY 15 - JET AIRCRAFT STORE VIBRATION RESPONSE	.D-15
FIGURE 514.8D-7.	CATEGORY 15 - JET AIRCRAFT STORE BUFFET RESPONSE	.D-17
FIGURE 514.8D-8.	DYNAMIC PRESSURE AS A FUNCTION OF MACH NUMBER AND ALTITUDE	.D-19
FIGURE 514.8D-9.	CATEGORY 16 - JET AIRCRAFT STORE EQUIPMENT VIBRATION EXPOSURE	.D-20
FIGURE 514.8D-10.	CATEGORY 20 - TRACKED VEHICLE REPRESENTATIVE SPECTRAL SHAPE.	D-22
FIGURE 514.8D-11.	CATEGORY 21 - SHIPBOARD RANDOM VIBRATION EXPOSURE	.D-24
FIGURE 514.8D-12.	CATEGORY 22 - TURBINE ENGINE VIBRATION EXPOSURE	.D-25

E SUPPLEMENTAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

1.	SCOPE	E-1
1.1	PURPOSE	E-1
1.2	APPLICATION	E-1
1.3	LIMITATIONS	E-1
2.	SUPPLEMENTAL TESTS	E-1
2.1	SUPPLEMENTAL CONSIDERATIONS	E-1
2.1.1	CATEGORY 24 - MINIMUM INTEGRITY TESTS	E-1
2.1.2	CATEGORY 25 - ALL VEHICLES - CANTILEVERED EXTERNAL MATERIEL	E-4

E FIGURES

FIGURE 514.8E-1.	CATEGORY 24 - GENERAL MINIMUM INTEGRITY EXPOSURE.	E-3
FIGURE 514.8E-2.	CATEGORY 24 - HELICOPTER MINIMUM INTEGRITY EXPOSURE.	E-4

MIL-STD-810H

METHOD 514.8

CONTENTS - Continued Paragraph

Page

F DEVELOPMENT OF LABORATORY VIBRATION TEST SCHEDULES

1.	GENERAL	F-1
2.	REQUIREMENTS	F-1
3.	DEFINITIONS	F-2
4.	NATURE OF VIBRATION	F-2
5.	PLATFORM SPECIFIC CONSIDERATIONS	F-3
5.1	ROAD TRANSPORT - WHEELED VEHICLE	F-3
5.2	ROAD TRANSPORT - TRACKED VEHICLE.	F-3
5.3	AIR TRANSPORT - ROTOR WING	F-4
5.4	AIR TRANSPORT - FIXED WING	F-4
5.5	SEA TRANSPORT	F-4
5.6	RAIL TRANSPORT	F-5
6.	DATA COLLECTION, REVIEW AND SELECTION	F-5
7.	SCENARIO DEVELOPMENT	F-5
7.1	GROUND VEHICLE	F-5
7.1.1	BETA DISTRIBUTION	F-8
7.2	AIRCRAFT	F-10
7.3	SEA VEHICLE	F-11
7.4	RAIL TRANSPORT.	F-11
8.	VSD ALTERNATIVES	F-11
9.	VSD PROCEDURES	F-11
9.1	VSD CONSIDERATIONS.	F-11
9.2	ENGINEERING DATA COMMON ACROSS VSD METHODS	F-12
9.2.1	MINER-PALMGREN HYPOTHESIS.	F-12
9.2.1.1	S/N CURVE	F-12
9.2.1.2	MINER-PALMGREN EQUATIONS.	F-13
10.	PREDICTIONS OF MAXIMUM RESPONSE	F-19
11.	SUMMARY AND CONCLUSION	F-20

F TABLES

TABLE 514.8F-I.	LIFETIME SCENARIO BREAKOUT - EXAMPLE ONLY	F-7
TABLE 514.8F-II.	SELECTION OF ALPHA FOR BETA DISTRIBUTION	F-8
TABLE 514.8F-III.	DEFAULT VALUES FOR M	F-16
TABLE 514.8F-IV.	METALS AND MATERIAL PROPERTIES	F-18

F FIGURES

FIGURE 514.8F-1.	SAMPLE BETA DISTRIBUTION (WHEELED VEHICLE)	F-9
FIGURE 514.8F-2.	S/N CURVE	F-13
FIGURE 514.8F-3.	TYPICAL STRAIN LIFE CURVE	F-14
FIGURE 514.8F-4.	RELATIVE DAMAGE AS A FUNCTION OF SURFACE FINISH - SAE-8630 STEEL	F-15
FIGURE 514.8F-5.	RELATIVE DAMAGE AS A FUNCTION OF STRAIN RANGE - SAE 8630 STEEL	F-16
FIGURE 514.8F-6.	TYPICAL S-N CURVE	F-19

MIL-STD-810H

METHOD 514.8

CONTENTS - Continued

Paragraph		Page
ANNEX F APPENDICIES
APPENDIX A. PREPARATION FOR VSD - DATA ACQUISITION		F-A1
1.	INTRODUCTION	F-A1
2.	VEHICLE PREPARATION FOR DATA ACQUISITION - CARGO	F-A1
2.1	SPECIFIED LOAD	F-A1
2.2	GENERAL CARGO SIMULATED LOAD	F-A1
2.3	TIE-DOWN	F-A1
2.4	ACCELEROMETERS	F-A1
3.	VEHICLE PREPARATION FOR DATA ACQUISITION – INSTALLED EQUIPMENT	F-A1
4.	DATA ACQUISITION PROCEDURE	F-A2
4.1	DATA ACQUISITION	F-A2
4.2	CARGO SCHEDULES	F-A2
4.3	INSTALLED EQUIPMENT SCHEDULES	F-A2
5.	DATA REQUIRED	F-A2
APPENDIX B. COMBINATION OF SPECTRA (STATISTICAL)		F-B1
1.	COMBINING SPECTRA	F-B1
1.1	AUTO AND CROSS SPECTRAL DENSITIES	F-B1
1.2	CONFIDENCE INTERVAL OF ASD ESTIMATES	F-B2
2.	STATISTICAL CONSIDERATIONS FOR DEVELOPING LIMITS ON AN ENSEMBLE OF DATA	F-B3
2.1	BASIC ESTIMATE ASSUMPTIONS	F-B3
2.2	BASIC ESTIMATE SUMMARY PREPROCESSING	F-B4
2.3	PARAMETRIC UPPER LIMIT STATISTICAL ESTIMATE ASSUMPTIONS	F-B4
2.3.1	NTL - UPPER NORMAL ONE-SIDED TOLERANCE LIMIT	F-B5
2.3.2	NPL - UPPER NORMAL PREDICTION LIMIT	F-B6
2.4	NONPARAMETRIC UPPER LIMIT STATISTICAL ESTIMATE ASSUMPTIONS	F-B6
2.4.1	ENV - UPPER LIMIT	F-B6
2.5	DFL-UPPER DISTRIBUTION-FREE TOLERANCE LIMIT	F-B7
2.6	ETL - UPPER EMPIRICAL TOLERANCE LIMIT	F-B7
2.7	EXAMPLE FROM MEASURED DATA	F-B8
3.	COMMON ANALYSIS FUNCTIONS AND STATISTICAL DEFINITIONS OF VSD DATA ENSEMBLES	F-B9

ANNEX F, APPENDIX B TABLES
TABLE 514.8F-B.I. NORMAL TOLERANCE FACTORS FOR UPPER TOLERANCE LIMIT	F-B6

F , APPENDIX B FIGURES

FIGURE 514.8F-B.1. 90-PERCENT CONFIDENCE LIMITS FOR n_d = 31 LINEAR SPECTRAL AVERAGES	F-B3
FIGURE 514.8F-B.2. EXAMPLE NORMAL TOLERANCE LIMIT APPLIED TO TYPICAL WHEELED VEHICLE DATA	F-B8
FIGURE 514.8F-B.3. AVERAGE, AVERAGE PLUS STANDARD DEVIATION, AND PEAK SPECTRA	F-B10
FIGURE 514.8F-B.4. COMBINATION OF 24 INDIVIDUAL SPECTRA	F-B11

MIL-STD-810H METHOD

514.8 CONTENTS - Continued Paragraph Page ANNEX F, APPENDIX B FIGURES

ANNEX F, APPENDIX C TABLES
FIGURE	514.8F-B.5. COMPARISON OF RESULTANT TEST SPECTRUM TO ENVELOPE OF INDIVIDUAL SPECTRA	F-B12
APPENDIX C.	COMBINATION OF SPECTRA (FATIGUE DAMAGE SPECTRA)	F-C1
1.	FATIGUE DAMAGE SPECTRUM METHOD OF COMBINING SPECTRA	F-C1
2.	EXAMPLE APPLICATION OF FATIGUE DAMAGE SPECTRUM	F-C2
3.	FDS APPROACH TO DEVELOPMENT OF A LVTS ..	F-C9
TABLE	514.8F-C.I. TEST COURSE LENGTHS, SPEEDS AND EXPOSURE TIMES	.F-C2
ANNEX F, APPENDIX C FIGURES
FIGURE	514.8F-C.1. FATIGUE DAMAGE SPECTRA FOR SPECIFIC TEST COURSES	.F-C3
FIGURE	514.8F-C.2. CUMULATIVE FATIGUE DAMAGE SPECTRUM	.F-C4
FIGURE	514.8F-C.3. CUMULATIVE FATIGUE SPECTRA FROM LOCATIONS 1 AND 2	.F-C5
FIGURE	514.8F-C.4. COMBINED VIBRATION POWER SPECTRA DEVELOPED FROM AVERAGE AND MAXIMUM FATIGUE DAMAGE SPECTRA	.F-C6
FIGURE	514.8F-C.5. COMPARISON OF COMBINED VIBRATION POWER SPECTRUM DEVELOPED FROM THE FATIGUE DAMAGE SPECTRUM, FROM THE STATISTICAL PROCESS AND FROM AN ENVELOPE PROCESS	.F-C7
FIGURE	514.8F-C.6. FATIGUE DAMAGE SPECTRA FOR TWO EXPONENTS	.F-C8
FIGURE	514.8F-C.7. COMPARISON OF COMBINED VIBRATION POWER SPECTRA DEVELOPED FROM TWO EXPONENTS	.F-C9
FIGURE	514.8F-C.8. TIME COMPRESSION OF ASD'S COMPUTED FROM THE INVERSE CUMULATIVE FATIGUE DAMAGE SPECTRUM.	.F-C10
APPENDIX D.	VIBRATION SPECIFICATION DEVELOPMENT PROCEDURE	F-D1
1.	INTRODUCTION	F-D1
2.	BROADBAND PROFILE DEVELOPMENT	F-D2
2.1	FILE SETUP (STEP 1)..	F-D2
2.2	SELECT EVENT START AND END TIME (STEP 2)	F-D3
2.3	TIME BLOCK DROP (STEP 3)	F-D3
2.4	CALCULATE ASD AVERAGE (STEP 4).	F-D3
2.5	SPECTRAL SPIKE REMOVAL (STEP 5)	F-D4
2.6	SCENARIO TABLE (STEP 6).	F-D6
2.7	CALCULATE WEIGHTED ASD (STEP 7)	F-D9
2.8	CALCULATE WEIGHTED INTERMEDIATE LVTS (STEP 8).	F-D10
3.	NARROWBAND RANDOM SPECIFICATION DEVELOPMENT PROCEDURE	F-D11
4.	SINE TONE SPECIFICATION DEVELOPMENT PROCEDURE	F-D13
5.	ALTERNATE BROADBAND DEVELOPMENT BASED ON FATIGUE DAMAGE SPECTRUM	F-D15
6.	FINAL DEVELOPMENT PROCEDURES	F-D16
7.	COMBINING LVTS	F-D16

MIL-STD-810H METHOD

514.8 CONTENTS - Continued

Paragraph	Page
ANNEX F, APPENDIX D TABLES
TABLE 514.8F-D.I. REQUIRED PARAMETERS	F-D2
TABLE 514.8F-D.II. SINGLE-EVENT ASD SUM-SET..	F-D4
TABLE 514.8F-D.III. SPECTRAL SPIKE REMOVED TABLE, AVERAGE	F-D6
TABLE 514.8F-D.IV. SCENARIO TABLE INPUT.	F-D7
TABLE 514.8F-D.V. RUNTIME CALCULATION..	F-D8
TABLE 514.8F-D.VI. GROUP SUM-SET DEFINITION	F-D9
TABLE 514.8F-D.VII. NARROWBAND RANDOM CALCULATIONS	F-D12
TABLE 514.8F-D.VIII. SINE TONE CALCULATIONS	F-D14
TABLE 514.8F-D.IX. LVTS COMBINATION EXAMPLE	F-D17
ANNEX F, APPENDIX D FIGURES
FIGURE 514.8F-D.1. VSD FLOWCHART.	F-D1
FIGURE 514.8F-D.2. SPECTRAL SPIKE REMOVAL WINDOW	F-D5
APPENDIX E. THEORETICAL ASPECTS OF MAXIMUM RESPONSE	F-E1
1. INTRODUCTION.	F-E1
2. SINUSOIDAL EXCITATION	F-E1
3. SWEPT SINE EXCITATION..	F-E2
4. RANDOM VIBRATION EXCITATION.	F-E2
ANNEX F, APPENDIX E FIGURES
FIGURE 514.8F-E.1. MRS FOR A FIXED SINE EXCITATION AT 500 HZ WITH Q=5.	F-E2
FIGURE 514.8F-E.2. MRS FOR A SWEPT SINE FROM 300 HZ TO 1200 Hz.	F-E2
FIGURE 514.8F-E.3. MRS FOR A RANDOM VIBRATION	F-E3
APPENDIX F. ANNEX F REFERENCES	F-F1

MIL-STD-810H METHOD

514.8 METHOD

514.8 VIBRATION

ANNEX A – ENGINEERING INFORMATION

ANNEX B – MANUFACTURE / MAINTENANCE TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

ANNEX C – TRANSPORTATION TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

ANNEX D – OPERATIONAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

ANNEX E – SUPPLEMENTAL TAILORING GUIDANCE FOR VIBRATION EXPOSURE DEFINITION

ANNEX F – DEVELOPMENT OF LABORATORY VIBRATION TEST SCHEDULES

514.8 ANNEX A METHOD 514.8, ANNEX A

Engineering Information

NOTE: Unless specifically noted, all document references refer to paragraph 6.1 in the front part of this Method.

514.8 ANNEX A

fully verify materiel function. This arrangement has proven to be a good way of adequately verifying that materiel survives endurance testing in all respects.

514.8 ANNEX A

Since most vibration environments are expressed in terms of the auto spectral density function, Equation (1) can also be formulated as:

$\frac{t_{2}}{t_{1}}=\left[\frac{W(f)_{1}}{W(f)_{2}}\right]^{m/2}$ Equation (4)

where:

t1 = equivalent test time

t2 = in-service time for specified condition

W(f)1 ASD at test condition, g²/Hz

W(ƒ)2 = ASD at in-service condition, g2/Hz

[The ratio W(ƒ)1 /W(ƒ)2 is commonly known as the exaggeration factor]

mas stated in Equation (1)

Note: Using material S-N curves results in different equivalencies for different parts in a given test item. A decision will be required as to which equivalency to use to establish test criteria.

514.8 ANNEX A

the sinusoid(s) frequency(s) through bands representative of frequency variations in the environment and resonant frequency variations in materiel (see paragraph 2.4.3 below).

514.8 ANNEX A

b. Items acting as structural members. When materiel is installed such that it acts as a structural member of the platform, it will affect vibrations and it will be structurally loaded. This is particularly important for relatively large materiel items, but it applies to materiel of any size. In these cases, the materiel structure adds to the stiffness of the platform and may significantly affect vibration modes and frequencies. Further, the materiel will be subjected to structural loads for which it may not have been designed. An example is a beam tied down to the cargo deck of a truck, aircraft, or ship. If the tie-downs are not designed to slip at appropriate points, the beam becomes a structural part of the deck. When the deck bends or twists, the beam is loaded and it changes the load paths of the platform structure. This may be catastrophic for the beam, the platform, or both. Be careful in the design of structural attachments to assure that the materiel does not act as a structural member.
c. Large item mass relative to supporting structures. When materiel items are small relative to the overall platform, but large relative to supporting structures, account for the change in local vibration levels, if practical. This effect is discussed in Annex D, paragraph 2.1 for materiel mounted in jet aircraft. Due to differences in environments, relative sizes, and structural methods, the factor defined in Annex C, Table 514.8C-X is not applicable to materiel mounted in small, unmanned aircraft.
d. Large item size/mass relative to platform. When materiel is large in size or mass relative to the platform, always consider the potential of damage to the platform as a result of materiel vibration. It is imperative to consider these effects in the design of vibration test fixtures. Otherwise, the vibration transmitted to the test item may be greatly different than intended.

514.8 ANNEX A

b. Indicated airspeed. Another form of airspeed measurement is indicated airspeed. Calibrated airspeed is indicated airspeed when empirical corrections are added to account for factors in the specific aircraft installation. Indicated airspeed is expressed in various units (kilometers per hour, miles per hour, and knots), but in military aircraft it is normally in knots indicated airspeed (Kias).
c. Equivalent airspeed. Equivalent airspeed is a form directly related to dynamic pressure. It is sometimes used in engineering calculations since other forces (lift, drag, and structural air-loads) acting on an airframe are also proportional to dynamic pressure. However, it is not used in airspeed measurement systems or flight handbooks. Equivalent airspeed may be expressed in various units, but it is usually seen as knots equivalent airspeed (Keas).
d. True airspeed. This is the actual airspeed. To calculate true airspeed with an aircraft air data system, local atmospheric properties must be accurately known. This was not practical until recent years and aircraft generally do not use true airspeed in handbooks or to navigate. True airspeed may be expressed in various units but it is usually seen as knots true airspeed (Ktas).
e. Mach number. Mach number is the ratio of true airspeed to the speed of sound. When Mach number is measured by an aircraft air data system, it is true Mach number.

514.8 ANNEX A

a. The total change in mass of the unit and of each subassembly is within ±10 percent.
b. The unit center of gravity is within ±10 percent of the original location in any direction.
c. The mounting configuration is unchanged.
d. The mounting configuration of circuit cards is unchanged.
e. The first three natural frequencies of the chassis and the first natural frequency of each subassembly are within ±5 percent of the original frequencies.
f. The first natural frequency of each circuit board is within ±10 percent of the original frequency.
g. Each modified circuit card is vibrated for one hour in the axis perpendicular to the plane of the board. Use a test exposure that is 0.04 g²/Hz from 15 to 1000 Hz rolled off at 6 dB per octave to 2000 Hz. Maintain electrical continuity throughout the card during and after the test. (Where vibration levels and durations at board level are known, these may be substituted for the stated exposure.)
h. Changes to mounts, chassis, internal support structures, and circuit card materials are to materials with equal or greater high cycle fatigue strength.

MIL-STD-810H METHOD 514.8, ANNEX B