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IEC TR 62131-7
Edition 1.0 2020-04
TECHNICAL
REPORT
colour
inside
Environmental conditions – Vibration and shock of electrotechnical equipment –
Part 7: Transportation by rotary wing aircraft:
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IEC TR 62131-7
Edition 1.0 2020-04
TECHNICAL
REPORT
colour
inside
Environmental conditions – Vibration and shock of electrotechnical equipment –
Part 7: Transportation by rotary wing aircraft:
INTERNATIONAL
ELECTROTECHNICAL
COMMISSION
ICS 19.040 ISBN 978-2-8322-8237-3
– 2 – IEC 62131-7:2020 © IEC 2020
CONTENTS
FOREWORD . 5
1 Scope . 7
2 Normative references . 7
3 Terms and definitions . 7
4 Data source and quality . 8
4.1 Vibration of Boeing CH-47 rotorcraft . 8
4.2 Set down of underslung cargo from a Boeing CH-47 rotorcraft . 9
4.3 Supplementary data . 10
5 Intra data source comparison . 13
5.1 General . 13
5.2 Vibration of Boeing CH-47 rotorcraft . 13
5.3 Set down of underslung cargo from a Boeing CH-47 rotorcraft . 13
5.4 Supplementary data . 14
6 Inter data source comparison . 14
7 Environmental description . 14
7.1 Physical sources producing mechanical vibrations . 14
7.2 Environmental characteristics and severities . 16
7.3 Derived test severities . 17
8 Comparison with IEC 60721 (all parts) [16] . 18
9 Recommendations . 21
Bibliography . 50
Figure 1 – Typical vibration spectra for CH-47 rotorcraft during straight and level flight at
160 kn [1] . 22
Figure 2 – Typical vibration spectra for CH-47 rotorcraft during hover [1] . 22
Figure 3 – Typical vibration spectra for CH-47 rotorcraft during transition to hover [1] . 23
Figure 4 – Typical vibration spectra for CH-47 rotorcraft during autorotation [1] . 23
Figure 5 – Comparison of CH-47 vibration overall RMS for different flight conditions [1] . 24
Figure 6 – Comparison of CH-47 vibration RMS severities at rotor shaft frequency (r) for
different flight conditions [1] . 25
Figure 7 – Comparison of CH‑47 vibration RMS severities at rotor blade passing
frequency (nr) for different flight conditions [1] . 26
Figure 8 – Comparison of CH‑47 vibration RMS severities at second rotor blade passing
frequency (2nr) for different flight conditions [1] . 27
Figure 9 – Comparison of CH‑47 vibration RMS severities at third rotor blade passing
frequency (3nr) for different flight conditions [1] . 28
Figure 10 – Comparison of CH‑47 vibration RMS severities at fourth rotor blade passing
frequency (4nr) for different flight conditions [1] . 29
Figure 11 – Comparison of CH‑47 vibration RMS severities across cargo bay floor during
hover [1] . 30
Figure 12 – Comparison of CH‑47 vibration RMS severities across cargo bay floor during
transition to hover manoeuvre [1] . 30
Figure 13 – Comparison of CH‑47 vibration RMS severities across cargo bay floor during
a transition to autorotation manoeuvre [1] . 31
Figure 14 – Comparison of CH‑47 vibration RMS severities across cargo bay floor during
straight and level flight [1] . 31
IEC 62131-7:2020 © IEC 2020 – 3 –
Figure 15 – CH‑47 rotorcraft ISO container set down shock severities [2] . 32
Figure 16 – Relative amplitude variations with airspeed for the Lynx rotorcraft [3]. 32
Figure 17 – Relative amplitude variations with airspeed for the Seaking rotorcraft [3] . 33
Figure 18 – Relative amplitude variations with airspeed for the Chinook rotorcraft [3] . 33
Figure 19 – Airframe to airframe relative amplitude variations for the Lynx rotorcraft [3] . 34
Figure 20 – Comparison of fleet vibration statistics [5] . 35
Figure 21 – Super Frelon rotorcraft measurements for X axis [6] . 36
Figure 22 – Super Frelon rotorcraft measurements for Y axis [6] . 36
Figure 23 – Super Frelon rotorcraft measurements for Z axis [6] . 37
Figure 24 – Vibration test severity derived for the CH‑47 rotorcraft using the approach of
Mil Std 810 [9] . 37
Figure 25 – Vibration test severity derived for the transportation of equipment in CH‑47
rotorcraft using the approach of STANAG 4370 AECTP 400 Method 401 Annex D [10] . 38
Figure 26 – Vibration test severity for equipment carried as underslung loads STANAG
4370 AECTP 400 Method 401 Annex D [10] . 38
Figure 27 – Rotorcraft specific vibration test severities for Chinook (CH‑47) from
Def Stan 00‑35 [5]. 39
Figure 28 – Rotorcraft specific vibration test severities for Merlin from Def Stan 00‑35 [5] . 39
Figure 29 – Rotorcraft specific vibration test severities for Lynx/Wildcat from
Def Stan 00‑35 [5]. 40
Figure 30 – Vibration test severities for underslung loads from Def Stan 00‑35 [5] . 40
Figure 31 – Rotorcraft specific vibration test severities for CH‑47 from RTCA/DO‑160 [11]
and EUROCAE/ED‑14 [12] . 41
Figure 32 – IEC 60721‑3‑2:1997 [17] – Stationary vibration random severities . 41
Figure 33 – IEC TR 60721‑4‑2:2001 [18]– Stationary vibration random severities . 42
Figure 34 – IEC 60721‑3‑2:1997 [17] – Stationary vibration sinusoidal severities . 42
Figure 35 – IEC TR 60721‑4‑2:2001 [18] – Stationary vibration sinusoidal severities . 43
Figure 36 – IEC 60721‑3‑2:1997 [17] – Shock severities . 43
Figure 37 – IEC TR 60721‑4‑2:2001 [18] – Shock severities for IEC 60068‑2‑29:1987 [20]
test procedure . 44
Figure 38 – IEC TR 60721‑4‑2:2001 [18] – Shock severities for IEC 60068‑2‑27 [19] test
procedure . 44
Figure 39 – Comparison of CH‑47 rotorcraft vibrations [1] with IEC 60721‑3‑2:1997 [17] . 45
Figure 40 – Comparison of Super Frelon rotorcraft X axis vibrations [6] with
IEC 60721‑3‑2:1997 [17] . 45
Figure 41 – Comparison of Super Frelon rotorcraft Y axis vibrations [6] with
IEC 60721‑3‑2:1997 [17] . 46
Figure 42 – Comparison of Super Frelon rotorcraft Z axis vibrations [6] with
IEC 60721‑3‑2:1997 [17] . 46
Figure 43 – Comparison of Mil Std 810 vibration test severity [9] with
IEC 60721‑3‑2:1997 [17] . 47
Figure 44 – Comparison of AECTP 400 vibration test severity [10] with
IEC 60721‑3‑2:1997 [17] . 47
Figure 45 – Comparison of Def Stan 00‑35 vibration test severity [5] with
IEC 60721‑3‑2:1997 [17] . 48
Figure 46 – Comparison of DO160 vibration test severity [11] with
IEC 60721‑3‑2:1997 [17] . 48
– 4 – IEC 62131-7:2020 © IEC 2020
Figure 47 – Comparison of underslung load vibration test severities [5] and [10] with
IEC 60721‑3‑2:1997 [17] . 49
Figure 48 – Comparison of CH‑47 rotorcraft set down shock severities [2] with
IEC 60721-3-2:1997 [17] . 49
Table 1 – Typical structural dynamic excitation frequencies and their source . 15
IEC 62131-7:2020 © IEC 2020 – 5 –
INTERNATIONAL ELECTROTECHNICAL COMMISSION
____________
ENVIRONMENTAL CONDITIONS – VIBRATION AND
SHOCK OF ELECTROTECHNICAL EQUIPMENT –
Part 7: Transportation by rotary wing aircraft
FOREWORD
1) The International Electrotechnical Commission (IEC) is a worldwide organization for standardization comprising all
national electrotechnical committees (IEC National Committees). The object of IEC is to promote international co-
operation on all questions concerning standardization in the electrical and electron
...