Norm

ASTM D7566 - 12a en

Standard Specification for Aviation Turbine Fuel Containing Synthesized Hydrocarbons

  • Deze norm is ingetrokken sinds 01-05-2013

73,70 89,18 Incl BTW

Over deze norm

Status Ingetrokken
Aantal pagina's 24
Gepubliceerd op 01-11-2012
Taal Engels

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 Once the fuel is released to this specification (D7566) the unique requirements of this specification are no longer applicable: any recertification shall be done in accordance with Table 1 of Specification D1655.

TABLE 1 Detailed Requirements of Aviation Turbine Fuels Containing Synthesized HydrocarbonsA

 

Part 1—Basic Requirements

Property

 

Jet A or Jet A-1

Test MethodB

COMPOSITION

 

 

 

Acidity, total mg KOH/g

Max

0.10

D3242 / IP 354

Aromatics: One of the following requirements shall be met:

 

 

 

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

D1266, D2622, D4294, D5453, or IP 336

 

 

 

 

VOLATILITY

 

 

 

Distillation

 

 

D2887 / IP 406D or D86E or IP 123E

Distillation temperature, °C:

 

 

 

 10 % recovered, temperature (T10)

Max

205

 

 50 % recovered, temperature (T50)

 

report

 

 90 % recovered, temperature (T90)

 

report

 

 Final boiling point, temperature

Max

300

 

Distillation residue, %

Max

1.5

 

Distillation loss, %

Max

1.5

 

Flash point, °C

Min

38F

D56 or D3828G, IP 170G or IP 523G

Density at 15°C, kg/m3

 

775 to 840

D1298 / IP 160 or D4052 or IP 365

 

 

 

 

FLUIDITY

 

 

 

Freezing point, °C

Max

–40 Jet AH

D5972 / IP 435, D7153 / IP 529, D7154 / IP 528, or D2386 / IP 16

 

 

–47 Jet A-1H

 

Viscosity –20°C, mm2/sI

Max

8.0

D445 / IP 71, Section 1

 

 

 

 

COMBUSTION

 

 

 

Net heat of combustion, MJ/kg

Min

42.8J

D4529, D3338, D4809 or IP 12

One of the following requirements shall be met:

 

 

 

 (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

D1840

 

 

 

 

CORROSION

 

 

 

Copper strip, 2 h at 100°C

Max

No. 1

D130 / IP 154

 

 

 

 

THERMAL STABILITY

 

 

 

2.5 h at control temperature of 260°C, min

 

 

D3241 / IP 323

 Filter pressure drop, mm Hg

Max

25

 

 Tube deposits less than

 

3K

 

 

 

No peacock or
abnormal color deposits

 

 

 

 

 

CONTAMINANTS

 

 

 

Existent gum, mg/100 mL

Max

7

D381, IP 540

Microseparometer,L Rating

 

 

D3948

 Without electrical conductivity additive

Min

85

 

 With electrical conductivity additive

Min

70

 

 

 

 

 

ADDITIVES

 

See 6.3

 

Electrical conductivity, pS/m

 

M

D2624 / IP 274


 

 

 

 

Part 2—Extended Requirements

Property

 

Jet A or Jet A-1

Test MethodB

COMPOSITION

 

 

 

Aromatics: One of the following requirements shall be met:

 

 

 

1. Aromatics, vol %

MinN,O

8

D1319 or IP 156

2. Aromatics, vol %

MinN,O

8.4

D6379 / IP 436

Distillation

 

 

D2887 / IP 406D, D86E or IP 123E

T50-T10, °C

MinO,P

15

 

T90-T10, °C

MinO,P

40

 

Lubricity,M mm

Max

0.85

D5001

A For compliance of test results against the requirements of Table 1, see 7.3.
B The test methods indicated in this table are referred to in Section 11.
C The mercaptan sulfur determination may be waived if the fuel is considered sweet by the doctor test described in Test Method D4952 or IP 30.
D Distillation property criteria are specified in D86 or IP 123 scale units. D2887 / IP 406 results shall be converted to estimated D86 or IP 123 results by application of the correlation in Appendix X5 of D2887 or Annex G of IP 406 for comparison with the specified property criteria. Distillation residue and loss limits provide control of the distillation process during the D86 and IP 123 test methods and do not apply to D2887 / IP 406. Distillation residue and loss shall be reported as “not applicable” (N/A) when reporting D2887 / IP 406 results.
ED86 or IP 123 distillation of jet fuel is run at Group 4 conditions, except Group 3 condenser temperature is used.
F A higher minimum flash point specification may be agreed upon between purchaser and supplier.
G Results obtained by other test methods can be up to 2°C lower than those obtained by Test Method D56, which is the preferred method. In case of dispute, Test Method D56 will apply.
H Other freezing points may be agreed upon between supplier and purchaser.
I 1 mm2/s = 1 cSt.
J For all grades use either Eq 1 or Table 1 in Test Method D4529 or Eq 2 in Test Method D3338 or IP 12. Test Method D4809 may be used as an alternative. In case of dispute, Test Method D4809 shall be used.
K Tube deposit ratings shall always be reported by the Visual Method.
L At point of manufacture.
M If electrical conductivity additive is used, the conductivity shall not exceed 600 pS/m at the point of use of the fuel. When electrical conductivity additive is specified by the purchaser, the conductivity shall be 50 to 600 pS/m under the conditions at point of delivery. (1 pS/m = 1 × 10-12  Ω-1m-1)
N Minimum aromatics contents are based on current experience with the approved synthetic fuels and those levels were established from what is typical for refined jet fuel. Research is ongoing on the actual need for aromatics.
O The minimum aromatics and distillation slope criteria only apply to aviation turbine fuels containing synthesized hydrocarbons produced to this specification and are not applicable to conventional aviation turbine fuels produced to Specification D1655. Some batches of aviation turbine fuels produced to Specification D1655 may not meet the minimum aromatics and distillation slope criteria specified in Table 1 of this specification.
P These distillation slope limits are based on current experience with the approved synthetic fuels and these values were established from what is typical for refined jet fuel. Research is ongoing on the actual requirements for distillation slope.

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.

1.2.3 Once a fuel is redesignated as D1655 aviation turbine fuel, it can be handled in the same fashion as the equivalent refined D1655 aviation turbine fuel.

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.

1.6 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.

1.7 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Details

ICS-code 75.160.20
Engelse titel Standard Specification for Aviation Turbine Fuel Containing Synthesized Hydrocarbons
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