Scope
1.1 This specification covers the manufacture of aviation turbine fuel that consists of conventional and synthetic blending components.
1.2 This specification applies only at the point of batch origination, as follows:
1.2.1 Aviation turbine fuel manufactured, certified, and released to all the requirements of Table 1 of this specification (D7566), meets the requirements of Specification D1655 and shall be regarded as Specification D1655 turbine fuel. Duplicate testing is not necessary; the same data may be used for both D7566 and D1655 compliance. Once the fuel is released to this specification (D7566) the unique requirements of this specification are no longer applicable: any recertification shall be done in accordance with Table 1 of Specification D1655.
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| Part 1—Basic Requirements | |||
| Property |
| Jet A or Jet A-1 | Test MethodB |
| COMPOSITION |
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| Acidity, total mg KOH/g | Max | 0.10 | D3242 / IP 354 |
| Aromatics: One of the following requirements shall be met: |
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| 1. Aromatics, vol % | Max | 25 | D1319 or IP 156 |
| 2. Aromatics, vol % | Max | 26.5 | D6379 / IP 436 |
| Sulfur, mercaptan,C mass % | Max | 0.003 | D3227 / IP 342 |
| Sulfur, total mass % | Max | 0.30 | |
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| VOLATILITY |
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| Distillation |
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| Distillation temperature, °C: |
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| 10 % recovered, temperature (T10) | Max | 205 |
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| 50 % recovered, temperature (T50) |
| report |
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| 90 % recovered, temperature (T90) |
| report |
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| Final boiling point, temperature | Max | 300 |
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| Distillation residue, % | Max | 1.5 |
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| Distillation loss, % | Max | 1.5 |
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| Flash point, °C | Min | 38F | |
| Density at 15°C, kg/m3 |
| 775 to 840 | |
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| FLUIDITY |
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| Freezing point, °C | Max | –40 Jet AH | D5972 / IP 435, D7153 / IP 529, D7154 / IP 528, or D2386 / IP 16 |
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| –47 Jet A-1H |
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| Viscosity –20°C, mm2/sI | Max | 8.0 | D445 / IP 71, Section 1 |
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| COMBUSTION |
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| Net heat of combustion, MJ/kg | Min | 42.8J | |
| One of the following requirements shall be met: |
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| (1) Smoke point, mm, or | Min | 25 | D1322 / IP 57 |
| (2) Smoke point, mm, and | Min | 18 | D1322 / IP 57 |
| Naphthalenes, vol, % | Max | 3.0 | |
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| CORROSION |
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| Copper strip, 2 h at 100°C | Max | No. 1 | D130 / IP 154 |
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| THERMAL STABILITY |
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| 2.5 h at control temperature of 260°C, min |
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| D3241 / IP 323 |
| Filter pressure drop, mm Hg | Max | 25 |
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| Tube deposits less than |
| 3K |
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| No peacock or |
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| CONTAMINANTS |
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| Existent gum, mg/100 mL | Max | 7 | D381, IP 540 |
| Microseparometer,L Rating |
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| Without electrical conductivity additive | Min | 85 |
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| With electrical conductivity additive | Min | 70 |
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| ADDITIVES |
| See 6.3 |
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| Electrical conductivity, pS/m |
| D2624 / IP 274 | |
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| Part 2—Extended Requirements | |||
| Property |
| Jet A or Jet A-1 | Test MethodB |
| COMPOSITION |
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| Aromatics: One of the following requirements shall be met: |
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| 1. Aromatics, vol % | 8 | D1319 or IP 156 | |
| 2. Aromatics, vol % | 8.4 | D6379 / IP 436 | |
| Distillation |
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| T50-T10, °C | 15 |
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| T90-T10, °C | 40 |
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| Lubricity,M mm | Max | 0.85 | |
1.2.2 Field blending of synthesized paraffinic kerosine (SPK) blendstocks, as described in Annex A1 (FT SPK) or Annex A2 (HEFA SPK) with D1655 fuel (which may on the whole or in part have originated as D7566 fuel) shall be considered batch origination in which case all of the requirements of Table 1 of this specification (D7566) apply and shall be evaluated. Short form conformance test programs commonly used to ensure transportation quality are not sufficient. The fuel shall be regarded as D1655 turbine fuel after certification and release as described in 1.2.1.
1.3 This specification defines specific types of aviation turbine fuel that contain synthesized hydrocarbons for civil use in the operation and certification of aircraft and describes fuels found satisfactory for the operation of aircraft and engines. The specification is intended to be used as a standard in describing the quality of aviation turbine fuels and synthetic blending components at the place of manufacture but can be used to describe the quality of aviation turbine fuels for contractual transfer at all points in the distribution system.
1.4 This specification does not include all fuels satisfactory for aviation turbine engines. Certain equipment or conditions of use may permit a wider, or require a narrower, range of characteristics than is shown by this specification.
1.5 While aviation turbine fuels defined by Table 1 of this specification can be used in applications other than aviation turbine engines, requirements for such other applications have not been considered in the development of this specification.
