ASTM D4054-23

This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
Designation: D4054 − 23
Standard Practice for
Evaluation of New Aviation Turbine Fuels and Fuel
Additives
This standard is issued under the fixed designation D4054; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
This standard has been approved for use by agencies of the U.S. Department of Defense.
1. Scope* 1.6 This international standard was developed in accor-
dance with internationally recognized principles on standard-
1.1 This standard practice provides procedures to develop
ization established in the Decision on Principles for the
data for use in research reports for new aviation turbine fuels,
Development of International Standards, Guides and Recom-
changes to existing aviation turbine fuels, or new aviation
mendations issued by the World Trade Organization Technical
turbine fuel additives. These research reports are intended to
Barriers to Trade (TBT) Committee.
support the development and issuance of new specifications or
specification revisions for these products. This standard prac-
2. Referenced Documents
tice has also been used to evaluate the effect of incidental
2.1 ASTM Standards:
materials on jet fuel properties and performance.
A240/A240M Specification for Chromium and Chromium-
1.2 The procedures, tests, and selection of materials detailed
Nickel Stainless Steel Plate, Sheet, and Strip for Pressure
in this practice are based on industry expertise to provide the
Vessels and for General Applications
necessary data to determine if the new or changed fuel or
B36/B36M Specification for Brass Plate, Sheet, Strip, And
additive is suitable for use on existing aircraft and engines and
Rolled Bar
for use in the current aviation operational and supply infra-
B93/B93M Specification for Magnesium Alloys in Ingot
structure. As such, it is primarily intended for the evaluation of
Form for Sand Castings, Permanent Mold Castings, and
drop-in fuels, but it can also be used for the evaluation of other
Die Castings
fuels.
D56 Test Method for Flash Point by Tag Closed Cup Tester
1.3 Because of the diversity of aviation hardware and D86 Test Method for Distillation of Petroleum Products and
potential variation in fuel/additive formulations, not every Liquid Fuels at Atmospheric Pressure
aspect may be fully covered and further work may be required. D93 Test Methods for Flash Point by Pensky-Martens
Therefore, additional data beyond that described in this prac- Closed Cup Tester
tice may be requested by the ASTM task force, Subcommittee D257 Test Methods for DC Resistance or Conductance of
J, or Committee D02 upon review of the specific composition, Insulating Materials
D395 Test Methods for Rubber Property—Compression Set
performance, or other characteristics of the candidate fuel or
additive. D412 Test Methods for Vulcanized Rubber and Thermoplas-
tic Elastomers—Tension
1.4 Units of measure throughout this practice are stated in
D445 Test Method for Kinematic Viscosity of Transparent
International System of Units (SI) unless the test method
and Opaque Liquids (and Calculation of Dynamic Viscos-
specifies non-SI units.
ity)
1.5 This standard does not purport to address all of the
D471 Test Method for Rubber Property—Effect of Liquids
safety concerns, if any, associated with its use. It is the
D790 Test Methods for Flexural Properties of Unreinforced
responsibility of the user of this standard to establish appro-
and Reinforced Plastics and Electrical Insulating Materi-
priate safety, health, and environmental practices and deter-
als
mine the applicability of regulatory limitations prior to use.
D924 Test Method for Dissipation Factor (or Power Factor)
and Relative Permittivity (Dielectric Constant) of Electri-
cal Insulating Liquids
This practice is under the jurisdiction of ASTM Committee D02 on Petroleum
Products, Liquid Fuels, and Lubricants and is the direct responsibility of Subcom-
mittee D02.J0.04 on Additives and Electrical Properties. For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Current edition approved May 1, 2023. Published May 2023. Originally contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
approved in 1981. Last previous edition approved in 2022 as D4054 – 22. Standards volume information, refer to the standard’s Document Summary page on
DOI:10.1520/D4054-23. the ASTM website.
*A Summary of Changes section appears at the end of this standard
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
D4054 − 23
D1002 Test Method for Apparent Shear Strength of Single- D4629 Test Method for Trace Nitrogen in Liquid Hydrocar-
Lap-Joint Adhesively Bonded Metal Specimens by Ten- bons by Syringe/Inlet Oxidative Combustion and Chemi-
sion Loading (Metal-to-Metal)
luminescence Detection
D1298 Test Method for Density, Relative Density, or API D4809 Test Method for Heat of Combustion of Liquid
Gravity of Crude Petroleum and Liquid Petroleum Prod-
Hydrocarbon Fuels by Bomb Calorimeter (Precision
ucts by Hydrometer Method
Method)
D1319 Test Method for Hydrocarbon Types in Liquid Petro-
D5001 Test Method for Measurement of Lubricity of Avia-
leum Products by Fluorescent Indicator Adsorption
tion Turbine Fuels by the Ball-on-Cylinder Lubricity
D1331 Test Methods for Surface and Interfacial Tension of
Evaluator (BOCLE)
Solutions of Paints, Solvents, Solutions of Surface-Active
D5291 Test Methods for Instrumental Determination of
Agents, and Related Materials
Carbon, Hydrogen, and Nitrogen in Petroleum Products
D1405 Test Method for Estimation of Net Heat of Combus-
and Lubricants
tion of Aviation Fuels
D5304 Test Method for Assessing Middle Distillate Fuel
D1414 Test Methods for Rubber O-Rings
Storage Stability by Oxygen Overpressure
D1655 Specification for Aviation Turbine Fuels
D5363 Specification for Anaerobic Single-Component Ad-
D2240 Test Method for Rubber Property—Durometer Hard-
hesives (AN)
ness
D5453 Test Method for Determination of Total Sulfur in
D2386 Test Method for Freezing Point of Aviation Fuels
Light Hydrocarbons, Spark Ignition Engine Fuel, Diesel
D2425 Test Method for Hydrocarbon Types in Middle Dis-
Engine Fuel, and Engine Oil by Ultraviolet Fluorescence
tillates by Mass Spectrometry
D5972 Test Method for Freezing Point of Aviation Fuels
D2622 Test Method for Sulfur in Petroleum Products by
(Automatic Phase Transition Method)
Wavelength Dispersive X-ray Fluorescence Spectrometry
D6304 Test Method for Determination of Water in Petro-
D2624 Test Methods for Electrical Conductivity of Aviation
leum Products, Lubricating Oils, and Additives by Cou-
and Distillate Fuels
lometric Karl Fischer Titration
D2717 Test Method for Thermal Conductivity of Liquids
D6378 Test Method for Determination of Vapor Pressure
(Withdrawn 2018)
(VP ) of Petroleum Products, Hydrocarbons, and
X
D2887 Test Method for Boiling Range Distribution of Pe-
Hydrocarbon-Oxygenate Mixtures (Triple Expansion
troleum Fractions by Gas Chromatography
Method)
D3114 Method of Test for D-C Electrical Conductivity of
D6379 Test Method for Determination of Aromatic Hydro-
Hydrocarbon Fuels (Withdrawn 1985)
carbon Types in Aviation Fuels and Petroleum
D3241 Test Method for Thermal Oxidation Stability of
Distillates—High Performance Liquid Chromatography
Aviation Turbine Fuels
Method with Refractive Index Detection
D3242 Test Method for Acidity in Aviation Turbine Fuel
D6732 Test Method for Determination of Copper in Jet
D3338 Test Method for Estimation of Net Heat of Combus-
Fuels by Graphite Furnace Atomic Absorption Spectrom-
tion of Aviation Fuels
etry
D3359 Test Methods for Rating Adhesion by Tape Test
D6793 Test Method for Determination of Isothermal Secant
D3363 Test Method for Film Hardness by Pencil Test
and Tangent Bulk Modulus (Withdrawn 2021)
D3701 Test Method for Hydrogen Content of Aviation
D6890 Test Method for Determination of Ignition Delay and
Turbine Fuels by Low Resolution Nuclear Magnetic
Derived Cetane Number (DCN) of Diesel Fuel Oils by
Resonance Spectrometry
Combustion in a Constant Volume Chamber
D3703 Test Method for Hydroperoxide Number of Aviation
D7042 Test Method for Dynamic Viscosity and Density of
Turbine Fuels, Gasoline and Diesel Fuels
Liquids by Stabinger Viscometer (and the Calculation of
D3828 Test Methods for Flash Point by Small Scale Closed
Kinematic Viscosity)
Cup Tester
D7111 Test Method for Determination of Trace Elements in
D3948 Test Method for Determining Water Separation Char-
Middle Distillate Fuels by Inductively Coupled Plasma
acteristics of Aviation Turbine Fuels by Portable Separom-
Atomic Emission Spectrometry (ICP-AES)
eter
D7153 Test Method for Freezing Point of Aviation Fuels
D4052 Test Method for Density, Relative Density, and API
(Automatic Laser Method)
Gravity of Liquids by Digital Density Meter
D7154 Test Method for Freezing Point of Aviation Fuels
D4066 Classification System for Nylon Injection and Extru-
(Automatic Fiber Optical Method)
sion Materials (PA)
D7171 Test Method for Hydrogen Content of Middle Dis-
D4175 Terminology Relating to Petroleum Products, Liquid
tillate Petroleum Products by Low-Resolution Pulsed
Fuels, and Lubricants
Nuclear Magnetic Resonance Spectroscopy
D4529 Test Method for Estimation of Net Heat of Combus-
D7359 Test Method for Total Fluorine, Chlorine and Sulfur
tion of Aviation Fuels
in Aromatic Hydrocarbons and Their Mixtures by Oxida-
tive Pyrohydrolytic Combustion followed by Ion Chroma-
tography Detection (Combustion Ion Chromatography-
The last approved version of this historical standard is referenced on
www.astm.org. CIC)
D4054 − 23
D7566 Specification for Aviation Turbine Fuel Containing MIL-PRF-81298 Dye, Liquid for the Detection of Leaks in
Synthesized Hydrocarbons Aircraft Fuel Systems
D7945 Test Method for Determination of Dynamic Viscosity MIL-PRF-81733 Sealing and Coating Compound, Corrosion
and Derived Kinematic Viscosity of Liquids by Constant Inhibitive
Pressure Viscometer MIL-PRF-87260 Foam Material, Explosion Suppression,
E411 Test Method for Trace Quantities of Carbonyl Com- Inherently Electrostatically Conductive, for Aircraft Fuel
pounds with 2,4-Dinitrophenylhydrazine Tanks
E659 Test Method for Autoignition Temperature of Chemi- MIL-S-85334 Sealing Compound, Noncuring, Low
cals Consistency, Silicone, Groove Injection, for Integral Fuel
E681 Test Method for Concentration Limits of Flammability Tanks
of Chemicals (Vapors and Gases) MIL-DTL-5578 Tanks, Fuel, Aircraft, Self-Sealing
E1269 Test Method for Determining Specific Heat Capacity MMM-A-132 Adhesives, Heat Resistant, Airframe
by Differential Scanning Calorimetry Structural, Metal to Metal
QPL-25017 Qualified Products List for MIL-PRF-25017
2.2 Federal Specifications:
(Inhibitor, Corrosion/Lubricity Improver, Fuel Soluble)
FED-STD-791 Testing Method of Lubricants, Liquid Fuels,
(NATO S-1747)
and Related Products
2.4 SAE International:
2.3 Department of Defense Specifications:
SAE-AMS-2410 Plating, Silver Nickel Strike, High Bake
DOD-L-85645 Lubricant, Dry Film, Molecular Bonded
SAE-AMS-2427 Aluminum Coating, Ion Vapor Deposition
MIL-A-8625 Anodic Coatings for Aluminum and Aluminum
SAE-AMS-3215 Acrylonitrile Butadiene (NBR) Rubber
Alloys
Aromatic Fuel Resistant 65–75
MIL-C-83019 Coating, Polyurethane, for Protection of Inte-
SAE-AMS-3265 Sealing Compound, Polysulfide (T)
gral Fuel Tank Sealing Compound
Rubber, Fuel Resistant, Non-Chromated Corrosion Inhib-
MIL-DTL-5541 Chemical Conversion Coatings on Alumi-
iting for Intermittent Use to 360 °F (182 °C)
num and Aluminum Alloys
SAE-AMS-3276 Sealing Compound, Integral Fuel Tanks
MIL-DTL-5624 Turbine Fuel, Aviation, Grades JP-4 and
and General Purpose, Intermittent Use to 360 °F (182 °C)
JP-5
SAE-AMS-3277 Sealing Compound, Polythioether Rubber
MIL-DTL-24441 Paint, Epoxy-Polyamide, General Specifi-
Fast Curing Integral Fuel Tanks and General Purpose,
cation for
Intermittent Use to 360 °F (182 °C)
MIL-PRF-25017 Inhibitor, Corrosion/Lubricity Improver,
SAE-AMS-3278 Sealing and Coating Compound: Polyure-
Fuel Soluble (NATO S-1747)
thane (PUR) Fuel Resistant High Tensile Strength/
MIL-DTL-25988 Rubber, Fluorosilicone Elastomer, Oil-
Elongation for Integral Fuel Tanks/Fuel Cavities/General
and Fuel-Resistant, Sheets, Strips, Molded Parts, and
Purpose
Extruded Shapes
SAE-AMS-3279 Sealing Compound, Sprayable, for Integral
MIL-DTL-26521 Hose Assembly, Nonmetallic, Fuel,
Fuel Tanks and Fuel Cell Cavities, for Intermittent Use to
Collapsible, Low Temperature with Non-Reusable Cou-
350 °F (177 °C)
plings
SAE-AMS-3281 Sealing Compound, Polysulfide (T) Syn-
MIL-DTL-83054 Baffle and Inerting Material, Aircraft Fuel
thetic Rubber for Integral Fuel Tank and Fuel Cell
Tank
Cavities Low Density for Intermittent Use to 360 °F
MIL-DTL-83133 Turbine Fuel, Aviation, Kerosene Type,
(182 °C)
JP-8 (NATO F-34), NATO F-35, and JP-8+100 (NATO
SAE-AMS-3283 Sealing Compound, Polysulfide Non-
F-37)
Curing, Groove Injection Temperature and Fuel Resistant
MIL-H-4495 Hose Assembly, Rubber, Aerial Refueling
SAE-AMS-3361 Silicone Potting Compound, Elastomeric,
MIL-DTL-17902 Hose, End Fittings and Hose Assemblies,
Two-Part, General Purpose, 150 to 400 Poise (15 to 40
Synthetic Rubber, Aircraft Fuels
Pa·s) Viscosity
MIL-HDBK-510 Aerospace Fuels Certification
SAE-AMS-3375 Adhesive/Sealant, Fluorosilicone, Aro-
MIL-P-25732 Packing, Preformed, Petroleum Hydraulic
matic Fuel Resistant, One-Part Room Temperature Vulca-
Fluid Resistant, Limited Service at 275 °F (135 °C)
nizing
MIL-PRF-370 Hose and Hose Assemblies, Nonmetallic:
SAE-AMS-3376 Sealing Compound, Non-Curing, Groove
Elastomeric, Liquid Fuel
Injection Temperature and Fuel Resistant
MIL-PRF-6855 Rubber, Synthetic, Sheets, Strips, Molded or
SAE-AMS-4017 Aluminum Alloy Sheet and Plate, 2.5Mg –
Extruded Shapes, General Specification for
0.25Cr (5052–H34) Strain-Hardened, Half-Hard, and Sta-
MIL-PRF-8516 Sealing Compound, Synthetic Rubber, Elec-
bilized
tric Connectors and Electric Systems, Chemically Cured
SAE-AMS-4027 Aluminum Alloy, Sheet and Plate 1.0Mg –
MIL-PRF-46010 Lubricant, Solid Film, Heat Cured, Corro-
0.60Si – 0.28Cu – 0.20Cr (6061; –T6 Sheet, –T651 Plate)
sion Inhibiting, NATO Code S-1738
4 5
Copies of these documents are available online at http://quicksearch.dla.mil/ or Available from SAE International, 400 Commonwealth Dr., Warrendale,
http://assist.dla.mil. Pennsylvania 15096, http://www.sae.org/servlets/index
D4054 − 23
Solution and Precipitation Heat Treated SAE AMS 6472 Steel, Bars and Forgings, Nitriding 1.6Cr –
SAE-AMS-4029 Aluminum Alloy Sheet and Plate 4.5Cu – 0.35Mo – 1.1Al (0.38-0.43C) Hardened and Tempered,
112 ksi (772 MPa) Tensile Strength
0.85SI – 0.80Mn – 0.50Mg (2014; –T6 Sheet, –T651
SAE-AMS-7257 Rings, Sealing, Perfluorocarbon (FFKM)
Plate) Solution and Precipitation Heat Treated
Rubber High Temperature Fluid Resistant 70 – 80
SAE-AMS-4037 Aluminum Alloy, Sheet and Plate 4.4Cu –
SAE-AMS-7271 Rings, Sealing, Butadiene-Acrylonitrile
1.5Mg – 0.60 Mn (2024; –T3 Flat Sheet, –T351 Plate)
(NBR) Rubber Fuel and Low Temperature Resistant 60 –
Solution Heat Treated
SAE-AMS-4107 Aluminum Alloy, Die Forgings
SAE-AMS-7276 Rings, Sealing, Fluorocarbon (FKM) Rub-
(7050–T74) Solution Heat Treated and Overaged
ber High-Temperature-Fluid Resistant Low Compression
SAE-AMS-4260 Aluminum Alloy, Investment Castings
Set 70–80
7.0Si – 0.32Mg (356.0–T6) Solution and Precipitation
SAE-AMS-7902 Beryllium, Sheet and Plate, 98Be
Heat Treated
SAE-AMS-C-27725 Coating, Corrosion Preventative, Poly-
SAE-AMS-4750 Solder, Tin–Lead 45Sn – 55Pb
urethane for Aircraft Integral Fuel Tanks for Use to 250 °F
SAE-AMS-4751 Tin–Lead Eutectic 63Sn – 37Pb
(121 °C)
SAE-AMS-4901 Titanium Sheet, Strip, and Plate Commer-
SAE AMS-I-7444 Insulation Sleeving, Electrical, Flexible
cially Pure Annealed, 70.0 ksi (485 MPa)
SAE-AMS-DTL-23053/5 Insulation Sleeving, Electrical,
SAE-AMS-4915 Titanium Alloy Sheet, Strip, and Plate 8Al
Heat Shrinkable, Polyolefin, Flexible, Crosslinked
–1V – IMo Single Annealed
SAE-AMS-P-5315 Butadiene–Acrylonitrile (NBR) Rubber
SAE-AMS-5330 Steel Castings, Investment, 0.80Cr – 1.8Ni for Fuel- Resistant Seals 60 to 70
– 0.35Mo (0.38–0.46C) (SAE 4340 Modified) Annealed SAE-AMS-P-83461 Packing, Preformed, Petroleum Hy-
draulic Fluid Resistant, Improved Performance at 275 °F
SAE-AMS-5338 Steel, Investment Castings 0.95Cr –
(135 °C)
0.20Mo (0.35–0.45C) (SAE 4140 Mod) Normalized or
SAE-AMS-QQ-A-250/12 Aluminum Alloy 7075, Plate and
Normalized and Tempered
Sheet
SAE-AMS-5504 Steel, Corrosion and Heat–Resistant,
SAE-AMS-QQ-P-416 Plating, Cadmium (Electrodeposited)
Sheet, Strip, and Plate 12.5Cr (SAE 51410) Annealed
SAE-AMS-R-25988 Rubber, Fluorosilicone Elastomer, Oil-
SAE-AMS-5525 Steel, Corrosion and Heat Resistant, Sheet,
and-Fuel-Resistant, Sheets, Strips, Molded Parts, and
Strip, and Plate 15Cr – 25.5Ni – 1.2Mo – 2.1Ti – 0.006B
Extruded Shapes
–0.30V 1800 °F (982 °C) Solution Heat Treated
SAE-AMS-R-83485 Rubber, Fluorocarbon Elastomer, Im-
SAE-AMS-5604 Steel, Corrosion Resistant, Sheet, Strip,
proved Performance at Low Temperatures
and Plate 16.5Cr – 4.0Ni – 4.0Cu – 0.30 Solution Heat
SAE-AMS-S-4383 Sealing Compound, Topcoat, Fuel Tank,
Treated, Precipitation Hardenable
Buna-N Type
SAE-AMS-5613 Steel, Corrosion and Heat Resistant, Bars,
SAE-AMS-S-8802 Sealing Compound, Temperature
Wire, Forgings, Tubing, and Rings 12.5Cr (SAE 51410)
Resistant, Integral Fuel Tanks and Fuel Cell Cavities,
Annealed
High Adhesion
SAE-AMS-5643 Steel, Corrosion Resistant, Bars, Wire,
SAE AS5127/1 Aerospace Standard Test Methods for Aero-
Forgings, Tubing, and Rings 16Cr – 4.0Ni – 0.30Cb –
space Sealants Two-Component Synthetic Rubber Com-
4.0Cu Solution Heat Treated, Precipitation Hardenable
pounds
SAE-AMS-5688 Steel, Corrosion–Resistant, Wire
2.5 American Welding Society (AWS):
18Cr–9.0Ni (SAE 30302) Spring Temper
AWS C3.4 Specification for Torch Brazing
SAE-AMS-5737 Steel, Corrosion and Heat–Resistant, Bars,
AWS C3.5 Specification for Induction Brazing
Wire, Forgings, and Tubing 15Cr – 25.5Ni – 1.2Mo –
AWS C3.6 Specification for Furnace Brazing
2.1Ti – 0.006B – 0.30V Consumable Electrode Melted,
AWS C3.7 Specification for Aluminum Brazing
1650 °F (899 °C) Solution and Precipitation Heat Treated
2.6 IPC:
SAE-AMS-6277 Steel Bars, Forgings, and Tubing 0.50Cr –
J-STD-004 Requirements for Soldering Fluxes
0.55Ni – 0.20Mo (0.18–0.23C) (SAE 8620) Vacuum Arc
J-STD-005 Requirements for Soldering Pastes
or Electroslag Remelted
J-STD-006 Requirements for Electronic Grade Solder Al-
SAE-AMS-6345 Steel, Sheet, Strip and Plate 0.95Cr – loys and Fluxed and Non-Fluxed Solid Solders for Elec-
0.20Mo (0.28–0.33C) (SAE 4130) Normalized or Other- tronic Soldering Applications
wise Heat Treated
2.7 Boeing Material Specifications (BMS):
SAE-AMS-6415 Steel, Bars, Forgings, and Tubing, 0.80Cr –
BMS 5-267 Fuel Tank Coating
1.8Ni –0.25Mo (0.38–0.43C) (SAE 4340)
SAE-AMS-6444 Steel, Bars, Forgings, and Tubing 1.45Cr
(0.93–1.05C) (SAE 52100) Premium Aircraft-Quality, Available from American Welding Society, 550 N.W. LeJeune Road, Miami,
Florida 33126; http://www.aws.org/
Consumable Electrode Vacuum Remelted
Available from IPC, 3000 Lakeside Drive, Suite 309S, Bannockburn, Illinois
SAE-AMS-6470 Steel, Nitriding, Bars, Forgings, and Tub-
60015; http://www.ipc.org
ing 1.6Cr – 0.35Mo – 1.13Al (0.38–0.43C) Available from Boeing.
D4054 − 23
BMS 10-20 Corrosion Resistant Finish for Integral Fuel IP 435 Determination of the freezing point of aviation
Tanks turbine fuels by the automatic phase transition method
BMS 10-39 Fuel and Moisture Resistant Finish for Fuel IP 438 Petroleum products—Determination of water—
Tanks Coulometric Karl Fischer titration method
IP 523 Determination of flash point—Rapid equilibrium
2.8 International Organization for Standardization (ISO):
closed cup method (ISO 3679:2004)
ISO 20823 Petroleum and related products determination of
IP 528 Determination of the freezing point of aviation
the flammability characteristics of fluids in contact with
turbine fuels—Automated fibre optic method
hot surfaces manifold ignition test
IP 529 Determination of the freezing point of aviation
2.9 United Kingdom Ministry of Defence (UK MOD):
fuels—Automatic laser method
DEF STAN 91–091 Turbine Fuel, Kerosine Type, Jet A-1,
IP 585 Determination of fatty acid methyl esters (FAME),
NATO Code: F-35 Joint Service Designation: AVTUR
11 derived from bio-diesel fuel, in aviation turbine fuel—
2.10 Environmental Protection Agency (EPA):
GC-MS with selective ion monitoring/scan detection
Method 8015 Nonhalogenated Organics by Gas Chromatog-
method
raphy
2.13 University of Dayton Research Institute (UDRI):
Method 8260 Volatile Organic Compounds by Gas
UDRI Method FC-M-101 Flow Modulation GCXGC for
Chromatography/Mass Spectrometry (GC/MS)
Hydrocarbon Type Analysis of Conventional and Alterna-
Method 8270 Semivolatile Organic Compounds by Gas
tive Aviation Fuels
Chromatography/Mass Spectrometry (GC/MS)
UDRI Method FC-M-102 Identification and Quantitation of
2.11 American Petroleum Institute (API)
Polar Species in Conventional and Alternative Aviation
API/EI 1581 Specifications and qualification procedures for
Fuels Using SPE-GCXGC
aviation jet fuel filter/separators, Fifth Edition
2.14 UOP Test Methods:
2.12 Energy Institute Standards:
UOP 389 Trace Metals in Oils by Wet Ash/ICP-AES
EI 1581 Specifications and qualification procedures for avia-
tion jet fuel filter/separators
3. Terminology
IP 16 Determination of the freezing point of aviation fuels—
Manual method
3.1 Definitions:
IP 71 Section 1 Petroleum Products—Transparent and
3.1.1 For definitions of terms used in this standard practice,
opaque liquids—Determination of kinematic viscosity and
refer to Terminology D4175.
calculation of dynamic viscosity
3.1.2 additive, n—in aviation turbine fuel, a substance
IP 123 Petroleum products—Determination of distillation
added to a base aviation turbine fuel in relatively small
characteristics at atmospheric pressure
amounts that either enables that base aviation turbine fuel to
IP 160 Crude petroleum and liquid petroleum products—
meet the applicable specification properties or does not alter
Laboratory determination of density—Hydrometer
the applicable specification properties of that base aviation
method
turbine fuel beyond allowable limits.
IP 170 Determination of flash point—Abel closed-cup
3.1.3 task group, n—an ad-hoc group operating in an
method
unofficial capacity for the subcommittee for a specific activity.
IP 323 Jet fuel thermal oxidation tube rating training guide-
3.1.3.1 Discussion—If appropriate, a timetable for comple-
lines
tion may be established. Society or Committee membership is
IP 354 Determination of the acid number of aviation turbine
not required, but the task group is encouraged to represent a
fuels—Colour-indicator titration method
balance of interests wherever possible and appropriate. Formal
IP 365 Crude petroleum and petroleum products—
balloting is not required at the task group level. Discharge may
Determination of density—Oscillating U-tube method
occur with completion or cause to abandon the activity.
IP 379 Determination of organically bound trace nitrogen—
3.2 Definitions of Terms Specific to This Standard:
Oxidative combustion and chemiluminescence method
3.2.1 aviation regulatory authorities, n—governmental or-
IP 406 Petroleum products—Determination of boiling range
ganizations such as agencies or departments that are empow-
distribution by gas chromatography
ered by statute to oversee and enforce compliance to a nation’s
airworthiness regulations.
Available from ISO, 1, ch. de la Voie-Creuse, CP 56, CH-1211 Geneva 20, 3.2.1.1 Discussion—Aviation regulatory authorities such as
Switzerland; http://www.iso.org/
the U.S. Federal Aviation Administration (FAA) and the
Available from Defence Equipment and Support, UK Defence
European Union Aviation Safety Agency (EASA) typically
Standardization, Kentigern House, 65 Brown Street, Glasgow, G2 8EX; http://
participate in the task force activities and review the submitted
www.dstan.mod.uk
Available from US EPA, Office of Resource Conservation and Recovery
data. These authorities work very closely with the OEMs to
(5305P), 1200 Pennsylvania Avenue, NW, Washington, DC 20460; http://
www.epa.gov/
Available from American Petroleum Institute (API), 1220 L. St., NW,
Washington, DC 20005-4070, http://www.api.org or Energy Institute (EI), 61 New Available from University of Dayton Research Institute (UDRI), 300 College
Cavendish St., London, W1G 7AR, U.K., http://www.energyinst.org. Park, Dayton, OH 45469-0043, https://udayton.edu/udri.
13 15
Available from Energy Institute, 61 New Cavendish St., London, W1G 7AR, Available from ASTM International, www.astm.org, or contact ASTM Cus-
U.K., http://www.energyinst.org. tomer Service at service@astm.org.
D4054 − 23
support certification activities that may be necessary to accom- 4.3.1 Tier 1 consists of testing a small sample of the new
modate the new aviation turbine fuel, the change to an existing fuel (approximately 10 U.S. gallons (37.8 L), or of existing jet
aviation turbine fuel, or the new aviation turbine fuel additive.
fuel with the new additive, to the existing properties specified
in the most referenced global aviation turbine fuel specifica-
3.2.2 drop-in, adj—as applied to a substance, possessing
tions.
essentially identical physical and performance properties and
chemical composition as an existing substance and intended for 4.3.2 Tier 2 consists of testing a larger volume of fuel
use as an alternative to that existing substance. (approximately 80 U.S. gallons (302.8 L) to an expanded set of
3.2.2.1 Discussion—Drop-in alternative fuels exhibit essen- properties that have been defined by the aviation fuel subcom-
tially identical composition, performance, and physical prop-
mittee. These properties are called Fit-for-purpose (FFP)
erties as existing petroleum-derived fuels and require no properties, and they address properties that are not listed in the
special handling or unique operating procedures.
specification criteria but are inherent in petroleum-derived jet
fuel.
3.2.3 fit-for-purpose, adj—describes a condition of accep-
tance of an aviation fuel or aviation fuel additive that signifies 4.3.3 Upon completion of Tier 1 and 2, the data are reported
acceptable performance in aircraft and aircraft engines.
to the subcommittee task group for Phase 1 review. The
3.2.3.1 Discussion—Fit-for-purpose properties are charac-
subcommittee task group relies on the recommendations of the
teristics of an aviation fuel or aviation fuel additive in the fuel
engine and aircraft manufacturers (OEMs) and the Federal
that are not listed in the specification criteria but are inherent in
Aviation Administration (FAA) to determine if the initial
petroleum-derived jet fuel. These properties are specified for
property data indicates that the fuel or additive is acceptable for
evaluation in addition to the specification properties to provide
further evaluation. A Phase 1 data report is provided to the FAA
a comprehensive assessment of the suitability of an aviation
and OEMs for this purpose. If the data is found to be
fuel for use in aircraft and aircraft engines.
acceptable, then the fuel or additive is ready for Tier 3 and 4
testing. Because these final two tiers involve testing of the fuel
3.2.4 identified incidental materials, n—chemicals and com-
or additive with unique aerospace materials, and on specialized
positions that have defined upper content limits in an aviation
fuel specification but are not approved additives. aircraft or engine component rigs, complete engines, or aircraft
flight testing, the subcommittee task group solicits recommen-
3.2.5 original equipment manufacturers (OEMs),
dations for Tier 3 and 4 testing from the FAA and the OEMs.
n—manufacturers of aircraft and aircraft engines.
The FAA and each of the OEMs will conduct their own internal
3.2.5.1 Discussion—Engine OEMs include but are not lim-
review of the data to determine the acceptability of the fuel or
ited to Pratt & Whitney (P&W), GE Aviation (GE), Rolls
additive for use on their aircraft and engines and to identify the
Royce (RR), SAFRAN, and Honeywell. Airframe OEMs
Tier 3 and 4 testing recommendations (see Appendix X2).
include but are not limited to Boeing, Airbus, Embraer,
These determinations and recommendations will be based on a
Bombardier, Dassault, and Lockheed. OEM review and evalu-
comparison of the data with the fuel properties scope of
ation of new fuels and new additives is required to ensure that
experience described in Annex A1.
safety of flight, engine operability, performance, and durability
requirements are not impacted by the new fuel or additive.
4.3.4 Tier 3 consists of testing the fuel or additive on
specialized engine or aircraft rigs or test benches, and of testing
4. Summary of Practice
the compatibility of the fuel or additive with fuel system
4.1 This practice provides a procedure and associated labo-
materials. This testing can require up to 10 000 U.S. gallons
ratory and aircraft equipment test methods to evaluate a new
(37 854 L) of test fuel to complete.
aviation turbine fuel, a change to an aviation turbine fuel, or a
4.3.5 Tier 4 consists of testing the fuel or additive on aircraft
new or changed aviation turbine fuel additive.
engines in ground test cells, or on aircraft in flight. This testing
4.2 The practice is an iterative process that relies on the can require up to 225 000 U.S. gallons (851 718 L) of test fuel
generation of data and periodic review by the OEMs, task
depending on the equipment recommended for testing.
group, and subcommittee members to determine subsequent
4.3.6 Upon completion of Tier 3 and 4 testing, which will
testing recommendations. As such, the practice should not be
vary from candidate to candidate, the data for all four tiers is
considered prescriptive, and it should be recognized that test
reported to the subcommittee task group. A final ASTM
requirements may be added or removed based upon the specific
Research Report is submitted to the OEMs and FAA for Phase
characteristics of the new fuel, changed fuel, or new additive,
2 review. The subcommittee relies on the recommendations of
and upon the review of the test data generated at each phase in
the OEMs and the FAA to determine if data contained in the
the process.
research report validates that the fuel or additive is acceptable
4.3 An overview of the practice is shown in Fig. 1. The for use on aircraft and engines. As with the Phase 1 review
practice consists of four tiers of testing, with a review after the described in 4.3.3 above, the OEMs conduct their own internal
second tier to determine the recommended scope of testing for review to make this final recommendation (see Appendix X2).
the final two tiers. If acceptable, then a motion is made to ballot the research
D4054 − 23
FIG. 1 Overview Fuel and Additive Approval Process
report, and the associated new specification, or specification 5.2 Its purpose is to guide the sponsor of a new fuel or new
revision to the subcommittee.
fuel additive through a defined evaluation process that includes
the prerequisite testing and required periodic reviews with the
4.4 Fast Track Annex A4—The process described in 4.3.1
subcommittee members. This practice provides a basis for
through 4.3.6 is a rigorous and comprehensive evaluation of
calculating the volume of additive or fuel required for
alternative jet fuels that requires a significant level of resources
assessment, insight into the cost associated with taking a new
to accomplish. This was intentional because of the critical role
fuel or new fuel additive through the evaluation process, and a
that aviation fuel plays in the safe conduct of air transportation.
However, extensive testing and evaluation of alternative jet defined path forward for introducing a new technology for the
fuels has provided a sufficient experience base to allow the benefit of the aviation community.
establishment of a fast track process with reduced testing
5.3 The allocation of resources necessary to support the full
requirements. This fast track process may only be used for new
scope of the evaluation process is the responsibility of the
alternative jet fuel blending components that fall within com-
sponsor of the new fuel or fuel additive. This will include
positional and performance criteria that reflect the typical range
laboratory, rig, or engine tests, if required, as well as support of
of current OEM-approved blendstocks and kerosine jet fuels.
OEM activities such as the Phase 1 and 2 reviews.
Target values are provided as a guideline and starting point for
the evaluation of candidate alternative jet fuels for acceptabil-
5.4 This process may also be used to assess the impact of
ity for the fast track process. The fast track process is described
changes to fuels due to changes in production methods and/or
in Annex A4 of this practice and is available for consideration
changes during transportation. An example is the assessment of
by sponsors of new alternative jet fuel blending components. It
the impact of incidental materials on fuel properties. In the
is not applicable to the OEM qualification and approval of
context of Practice D4054, incidental materials shall be con-
aviation turbine fuel additives.
sidered as an additive.
5. Significance and Use
5.5 This guide is not an approval process. It is intended to
describe test and analysis requirements necessary to generate
5.1 This practice is intended to describe the data require-
data to support specification revision or development. This
ments necessary to support the review of new aviation turbine
guide does not address the approval process for ASTM
fuels or additives by ASTM members for the developers or
sponsors of these new products. International standards.
D4054 − 23
5.6 This guide does not purport to specify an all-inclusive (NDA). The chemical nature of the fuel or additive plays a
listing of test and analysis requirements to achieve ASTM critical role in the following elements of the evaluation.
International issuance of a specification or specification revi- (1) Compatibility with fuel system seals and metallics.
sion. The final requirements will be dependent upon the (2) Hot section compatibility.
specific formulation and performance of the candidate fuel or (3) Cold flow properties.
additive and be determined by the ASTM International task (4) Thermal stability.
groups and committees charged with overseeing the specifica- (5) Rig tests for performance and operability.
tion development. (6) Emissions.
(7) Fuel handling.
5.7 Neither the generation of data and issuance of a research
6.1.3 It is important to note that during the evaluation
report described in this practice, nor the ultimate issuance of a
process, any change in the formulation of the fuel or additive,
new or revised ASTM fuel specification based on that data,
method of manufacture, or the way it is to be used, must be
constitutes approval to use the new or changed fuel or new
brought to the attention of the recipients of the compositional
additive on civil aircraft. As described in Appendix X2, the
data (i.e., OEMs) and the ASTM task group. It is possible that
OEMs will conduct an internal review process in coordination
such changes will render invalid any data collected previously
with their aviation regulatory authorities to determine if the
and require the qualification process be started anew.
new fuel or additive is acceptable for use on each of their
6.1.4 Conduct of the D4054 evaluation of a new fuel may
respective products. Only upon successful completion of this
involve several separate and distinct batches of test fuel. It is
OEM internal review will the new fuel or additive be permitted
important that each batch of test fuel is clearly identified and
for use on civil aircraft.
that the presented test data is clearly associated with the batch
5.8 This guide does not describe data requirements of other
of fuel used for that particular test.
approving authorities, such as national aviation regulatory
6.1.5 Much experience has been garnered from past indus-
authorities, or of other organizations or industry associations.
try and military efforts directed at investigating fuels and fuel
However, it is expected that the data generated in the conduct
additives. Additive investigations have been conducted on
of the procedure will be used by the OEMs and national
biocides, leak-detectors, thermal oxidative stability improvers,
aviation regulatory authorities to support their internal ap-
pipeline drag reducers, anti-static additives, and a water
proval processes (see Appendix X2) and may be useful for
solubilizer for use in jet fuel. Fuel evaluations have included
other purposes or other organizations.
oil sands, shale oil, Fischer-Tropsch synthetic kerosines and
biofuels. Lessons learned include the importance of prioritizing
6. Procedure
testing and performing first those tests that have the greatest
potential to be cause for rejection.
6.1 General:
6.1.1 The scope of properties that could be tested are shown 6.1.6 A test program directed at evaluating a fuel or additive
in Fig. 2. The purpose of the testing is to investigate the impact for use in a gas turbine engine shall contain the elements shown
of the candidate fuel or additive on fuel specification in the paragraphs that follow. The order of testing, as well as
properties, fit-for-purpose properties, fuel system materials, the tests that must be performed, may be redefined based on the
turbine materials, fuel system components, other approved specific nature and composition of the fuel or additive. Simi-
additives, and engine operability, durability, and emissions. larity to currently qualified fuels or additives is a chief
“Fit-for-Purpose properties” refers to properties inherent in a consideration. In most cases, testing of a candidate fuel
petroleum-derived fuel and assumed to be within a given range additive shall be performed at four times (4×) the concentration
of experience. Fit-for-Purpose Properties are not controlled being requested for qualification. If solubility of the additive
explicitly by specification but are considered critical to engine prevents blending at 4×, then the maximum level that is soluble
and airframe fuel system design. Examples include fuel surface should be used. The requirement to test at 4× is a means for
tension, seal swell, and dielectric constant. During the testing, assessing the impact of accidental additive overdose. It also
lends itself to early detection of possible negative impacts.
special considerations may be identified and investigated to
resolve anomalies. Examples include minimum aromatic level, Additionally, testing at 4× permits more flexibility in selecting
the baseline fuel to be used in the qualification process. Fuels
maximum flash point, and minimum lubricity.
can vary in their sensitivity to a particular additive. Testing at
6.1.2 A complete chemical description of the candidate fuel
4× negates the need to spend resources searching for a sensitive
or additive is required at the start of the testing. Additionally,
fuel for use as the baseline test fuel.
a description of the manufacturing process is required for a
new fuel. If the new material is an additive, its carrier solvent 6.1.7 If a problem is identified with an additive at 4×,
and recommended concentration must also be provided. This consideration will be given to assessing the impact of the
information is important for determining test requirements and additive at a lower concentration. Tests shall be performed with
the order in which the tests should be performed. Because the and without the candidate additive in the baseline test fuel. The
OEMs require this information to support their internal ap- baseline test fuel shall be Jet A or Jet A-1 conforming to the
proval process with the aviation regulatory authorities (see most recent revision of Specification D1655 or DEF STAN
Appendix X2), they have been designated by the subcommittee 91–091; JP-8 conforming to the most recent revision of
for receipt of any proprietary compositional information. This MIL-DTL-83133 (NATO F-34); or JP-5 conforming to the
information can be provided under a non-disclosure agreement most recent version of MIL-DTL-5624 (NATO F-44). The
D4054 − 23
* Testing must be performed at P&W, GE, Rolls Royce, Snecma, Honeywell, or in other locations per OEM agreement due to proprietary concerns and test methods.
NOTE 1—Additive testing to be performed at 4× the concentration being requested for approval except for filtration.
FIG. 2 Test Program
D4054 − 23
same batch of test fuel should be used in performing tests material as well as the final blend. The OEM team will provide
directed at impact on fuel specification properties. The same guidance on which tests are appropriate for the synthetic blend
batch of test fuel should be used for as many of the Fit-for- material.
Purpose Property tests as possible. The material compatibility 6.3.1 A special consideration under Tier 1 testing for a new
tests should be performed using the same batch of test fuel.
fuel is that heat of combustion be measured using Test Method
Some notable exceptions to using the same batch of test fuel D4809. Alternative methods for determining heat of combus-
might be component and engine tests.
tion such as Test Methods D1405, D3338, and D4529 are
6.1.8 A passing or failing test result is based on the type of estimation methods. Test Method D3338 states in subsection
test performed. In the case of specification testing, minimum or
1.2: This test method is purely empirical and is applicable to
maximum specification requirements must be met. Some areas liquid hydrocarbon fuels that conform to the specifications for
of investigation called out in this practice may not be amenable
aviation gasolines or aircraft turbine and jet engine fuels of
to a “pass” or “fail” result. For example, significant deviation grades Jet A, Jet A-1, Jet B, JP-4, JP-5, JP-7 and JP-8. Test
from the baseline fuel or from what is judged to be the norm
Method D4529 has a similar statement. The estimation meth-
during the Fit-for-Purpose Tests could result in a failure. ods are not appropriate for a new fuel not yet demonstrated to
During aircraft, engine, rig, or component testing, results may
be equivalent to the above conventional fuels. Subsequent to
be considered as failing when equipment performance or
measuring heat of combustion using Test Method D4809, the
function is impacted. Further, test results that extend beyond
fuel should be tested to D1405, D3338, and D4529 to demon-
the current range experience, such that a degree of risk is
strate that estimation methods hold true for the proposed fuel.
introduced to users of the fuel or additive, could result in a
6.4 Tier 2—Fit-for-Purpose Properties—When evaluating a
failure or a need for further testing.
new fuel, some of the Fit-for-Purpose Properties may be
6.2 The Evaluation Process:
required to be performed on both the synthetic blend material
6.2.1 The test program is comprised of four tiers. Each tier
as well as the final blend. The OEM team will provide guidance
consists of a distinct set of tests focused on a critical consid-
as to which tests will need to be performed.
eration that impacts engine and airplane design, safety,
6.4.1 Accepted Test Methods and Limits—Fit-for-Purpose
durability, performance, and reliability. The four tiers of testing
Properties and associated test methods are shown in Table 2.
are comprised of (1) Fuel Specification Properties; (2) Fit-for-
Some Fit-for-Purpose Properties do not have well-defined
Purpose Properties; (3) Component, Rig, and Materials Tests;
limits. In these cases, the effect of the new fuel or new additive
and (4) Engine and Aircr
...