Api mpms 6 4 2007 (2012) (american petroleum institute)

Manual of Petroleum
Measurement Standards
Chapter 6—Metering Assemblies
Section 4—Metering Systems for Aviation Fueling
Facilities
SECOND EDITION, JANUARY 2007
REAFFIRMED, JANUARY 2012



Manual of Petroleum
Measurement Standards
Chapter 6—Metering Assemblies
Section 4—Metering Systems for Aviation Fueling
Facilities
Measurement Coordination
SECOND EDITION, JANUARY 2007
REAFFIRMED, JANUARY 2012


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iii



CONTENTS
Page

6.4.1 INTRODUCTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1
6.4.2 SCOPE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1
6.4.3 REFERENCES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1
6.4.4 DISPENSING EQUIPMENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2
6.4.4.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2
6.4.4.2 Design Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2
6.4.4.3 Design Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2
6.4.5 OPERATING GUIDELINES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3
6.4.6 PROVING EQUIPMENT FOR AVIATION FUELING METERS. . . . . . . . . . . . . . .4
Figures
1a
1b
2a
2b

Typical Flow Diagram for a Refueler with Mechanical-type Meter . . . . . . . . . . . .

Typical Flow Diagram for a Refueler with Electronic-type Meter . . . . . . . . . . . . .
Typical Flow Diagram for a Hydrant Cart with Mechanical-type Meter . . . . . . . .
Typical Flow Diagram for a Hydrant Cart with Electronic-type Meter. . . . . . . . . .

v

6
7
8
9



Chapter 6—Metering Assemblies
Section 4—Metering Systems for Aviation Fueling Facilities
6.4.1 Introduction
There are two basic methods of fueling large aircrafts. Fuel can be delivered to the aircraft by a refueler, or by a hydrant cart.
Refuelers are fuel tank trucks equipped with flow metering, control and filtration equipment to deliver fuel to an aircraft. A refueler may also be used to de-fuel an aircraft. In comparison, a hydrant cart, which is also equipped with flow metering and control
equipment, is connected to a hydrant system rather than having an onboard aviation fuel storage tank. Hydrant cart is also known
as “dispenser.”
A hydrant system delivers aviation fuel from storage tanks of the airport fueling system to aircraft through a pressurized airport
pipeline network. The airport fueling system typically consists of the following components:
1.
2.
3.
4.
5.

Fuel storage tanks.
Facilities to receive fuel and to fill storage tanks (receiving station).

Facilities for withdrawing fuel from the tanks and distributing it to fueling equipment.
Hydrant pumps, control valves, and filters (hydrant system).
Refeuler fueling equipment:
a.
b.
c.
d.
e.
f.

Refueler loading equipment.
Refuelers.
Hydrant carts.
Hydrant pits.
Refueling cabinets.
De-fueling equipment.

Small aircrafts are often fueled using a metering and control system in an aviation refueler cabinet.

6.4.2 Scope
This section of MPMS Chapter 6 is limited to the general requirements of flow metering of aviation fuel as it is either dispensed to
aircraft or used to defuel aircraft.

6.4.3 References
API Manual of Petroleum Measurement Standards
Chapter 1
Chapter 4
Chapter 5
Chapter 7
Chapter 8.1

Chapter 9
Chapter 11
Chapter 12
Chapter 21.2

“Vocabulary”
“Proving Systems”
“Metering”
“Temperature Determination”
“Manual Sampling of Petroleum and Petroleum Products”
“Density Determination”
“Physical Properties Data”
“Calculation of Petroleum Quantities”
“Flow Measurement—Electronic Liquid Measurement”

Other useful API/IP standards on aircraft fueling equipment may be obtained from the following API or joint API/IP publications:
API/IP Std 1529
API/IP Std 1542
API/IP Spec 1581
API/IP Draft Std 1583
API/IP Spec 1584
API/IP 1585
API/IP Spec 1590

Aviation Fueling Hose
Identification Markings for Dedicated Aviation Fuel Manufacturing and Distribution Facilities, Airport Storage and Mobile Fuelling Equipment
Specifications and Qualification Procedures for Aviation Jet Fuel Filter/Separators
Laboratory Tests and Minimum Performance Levels for Aviation Fuel Filter Monitors
Four-inch Hydrant System Components and Arrangements
Guidance in the Cleaning of Airport Hydrant Systems

Specifications and Qualification Procedures for Aviation Fuel Microfilters
1


2

CHAPTER 6—METERING ASSEMBLIES

6.4.4 Dispensing Equipment
6.4.4.1 GENERAL
A refueler is a vehicle equipped with tank, pumps, hoses, hose rail, filters, separators (or filter monitors), flow meter and other
accessories required to deliver fuel to an aircraft (see Figures 1a and 1b). The refueler, after being loaded with fuel at a loading
rack, transports the fuel to the aircraft and loads it. A refueler is also typically designed to allow de-fueling of aircraft. It then
either stores the fuel in its tank or off-loads the fuel to another storage tank.
A hydrant cart is used to dispense fuel from the hydrant system to the aircraft through aviation fueling hoses that connect to the
aircraft and an inlet hose coupler that connects to a hydrant valve located in a pit near the aircraft fueling position (see Figures 2a
and 2b). A hydrant cart is equipped with hoses, filters, meters, valves and other accessories.
On a refueler or a hydrant cart, it is essential that all equipment be marked for product identification in accordance with API/IP
Std 1542.
6.4.4.2 DESIGN CONSIDERATIONS
Accurate measurement of jet fuel delivered to an aircraft is necessary for both billing and determination of fuel quantity on board
the aircraft. The following should be considered for application design of aviation fuel metering equipment:
1. The meter should have a maximum error of ±0.15% over its operating flow range, which is typically between 20% and
85% of its maximum design flow rate.
2. Meters used on all fueling units should have relatively low pressure drops and should provide the required level of accuracy
with minimum maintenance.
3. Some fueling units (i.e., hydrant cart or refueler) have multiple meters to allow each meter to operate within its rated capacity, as well as to permit a single dispensing unit to provide fuel to different groups of fuel tanks within a single aircraft. In these
cases, the fueling unit is frequently equipped with a meter rated at the maximum design flow of the servicer, with an additional
meter installed to a branch fueling circuit to handle fueling at a reduced rate of flow.
The larger meter designed to handle the full rated capacity of the fueling unit is installed in a supply line to relatively short

delivery hoses installed on a fuel servicing platform for servicing under-wing connections of large commercial aircraft. The
second meter, and possibly a third, rated at approximately one-half the design flow of the servicer, is installed in a delivery line
supplying product to a hose reel or reels used to furnish product to a fueling point remote from the servicer location, such as to
the wing fueling points on the opposite side of the aircraft.
4. At present, the volume delivered in the majority of fuel sales contracts are at ambient temperature, i.e., they are based on
gross observed volume (GOV). However, determination of the gross standard volume (GSV) of the fuel may be used for the
purposes of:
a. stock reconciliation, and
b. calculating the weight of the fuel in some cases.
Refer to API MPMS Chapter 12.2 for calculation procedures.
5. Since refuelers operate at relatively low pressure, a pressure sensor onboard a refueler can be ignored with little effect on
accuracy. However, hydrant carts are operated at the elevated line pressure of the hydrant system. The effect of pressure on
determining the compressibility factor, which is used to calculate gross standard volume and/or meter factor, may be required.
6. For product quality check, a means for taking a manual line sample at the fueling unit should be provided in accordance
with API MPMS Chapter 8.1 (ASTM D 4057).
6.4.4.3 DESIGN REQUIREMENTS
The following design requirements are normally specified for meters used on aviation fuel dispensers/refuelers:
1. Meters shall be constructed of aluminum, stainless steel, or epoxy-coated steel. The use of uncoated ferrous materials
should be avoided.
2. The number and size of meters to be used depends on the design loading rate.
3. Meter performance shall conform to the requirements of Section 6.4.4. Facilities shall be provided in some part of the airport fueling system for meters to be volumetrically proved.


SECTION 4—METERING SYSTEMS FOR AVIATION FUELING FACILITIES

3

4. The meter and totalizer used may be either of the mechanical or electronic type. Normally, mechanical totalizers are only
used with displacement meters.
5. Mechanical type meters will usually be non-temperature compensated and equipped with rate-of-flow indicators and registers reading in gallons (liters). Adequate lighting shall be provided so that counters can be read at night.

6. The meter onboard a refueler should be capable of measuring defueled quantities from an aircraft.
7. Large-numeral counters or digital displays indicating the quantity delivered, should be provided and should be visible to
the operator from the normal fueling stations.
8. Aviation fuel meters in both refueling and defeuling services shall have thermowell(s) on the refueling line and defueling line. The thermowell should preferably be located within a distance of 30 cm (12 in.) – 50 cm (20 in.) in accordance to API MPMS Chapter 7. Where existing equipment design limits, the thermowell may be located further away but
should not exceed 100 cm (40 in.), from the flow meter. The thermowell may be used with a portable thermometer to
determine the fuel temperature. For electronic flow meters, the temperature should be measured by a resistance temperature detector (RTD). If the system is used for fueling and for de-fueling in separate lines, and if the RTD is not located in
the common line, then an RTD shall be provided in each line (i.e., one on the fueling line and one on the de-fueling line).
9. An electronic type meter is typically equipped with a flow computer having a digital counter for displaying measured volume and product temperature.
10. The electronic flow computer connected to the meter may be able to perform the following functions:
a. Calculate and display measured fuel quantities.
b. Generate fuel quantity delivery transaction record, also known as a meter ticket using a local printer.
c. Communicate and transfer data remotely to a remote, host computer system. Communication may be by hand-held units
used for controlling aircraft fueling operations, and transferring data.
d. Display instantaneous and average temperature of product loaded during aircraft fueling operations.
e. Store product standard density.
f. Control product flow using flow control valve.
g. Store the last meter factor or K factor resulting from meter proving.
h. Allow for multi-point meter factors or K factors.
i. Provide security and audit trail.
j. Record aircraft type, flight number, tail number, destination/origin, time of day, and amount of fuel delivered.
11. The pressure sensor is typically installed near the meter. Local display by a pressure gauge, or by a pressure indicating
transmitter, or by the electronic flow computer is considered sufficient.
12. If the metering system operates at extreme cold climate, insulation should be applied at least 5 nominal pipe diameters on
either side of the temperature monitoring location if practical.

6.4.5 Operating Guidelines
6.4.5.1 Aviation fuel meters should preferably be proved with either a master meter, a pipe prover (including piston type), or a
tank prover, primarily.
6.4.5.2 Aviation fuel meters should be proved as often as necessary to insure accuracy. For example, many aviation fuel meters
are proved every six (6) months. Meters with high throughout may be proved more often.

6.4.5.3 Newly installed meters and meters after repair or overhaul should be proved at least every quarter for two consecutive
quarters. If the meter demonstrates satisfactory performance (refer to Section 6.4.5.15 on the requirements), the frequency can be
relaxed to a normal schedule, for example, once every six (6) months.
6.4.5.4 Meters that have been inoperative for a considerable period should be proved prior to use.
6.4.5.5 If there is more than one meter on a refueler or a hydrant cart, each meter shall be proved individually. The other meters
on the refueler or hydrant cart should be completely isolated during proving.
6.4.5.6 Meters shall be proved under normal operating conditions of temperature, pressure and flow rate.
6.4.5.7 Meters should be proved at normal operating flow rate. If the operating condition during proving does not allow this
flow rate to be reached, prove the meter at its maximum achievable flow and the condition noted in the proving report.
6.4.5.8 The flow rate during meter proving shall be kept constant, i.e., within ± 10% of its normal operating flow rate.


4

CHAPTER 6—METERING ASSEMBLIES

6.4.5.9 A meter shall be re-proved if a substantial change occurs in system pressure, e.g., 20% or 175 kPa (25 psi,) whichever
is greater, or the meter has been opened for maintenance.
6.4.5.10 If meter accessories are changed, replaced or the meter has been opened for maintenance, or repair, the meter shall be
re-proved prior to being used.
6.4.5.11 When using a tank prover, meter proving should be avoided during bad weather (heavy rain or strong winds).
6.4.5.12 Meter proving should be considered invalid if the ambient temperature variation exceeds 5°C (or 9°F) during the
proving.
6.4.5.13 The time intervals between proving runs shall be kept to a minimum in order to avoid changes in temperature and
pressure.
6.4.5.14 Dynamic Slip Test—This test is used to establish whether a meter experiences an excessive change in meter factor or
K factor at low flow rates relative to those in the normal operating range of the meter. After completing the normal meter proving
and all calibrator adjustments, perform two (2) consecutive Dynamic Slip Test runs at a flow rate between 15% and 20% of the
manufacturer’s maximum continuous flow rate (capacity). The repeatability of the two runs shall not exceed 0.05%.
6.4.5.15 Compute the average meter factor for the Dynamic Slip Test runs. Compute the Dynamic Slip “Test Difference” by

subtracting the average meter factor during the Dynamic Slip Test from the average meter factor during normal operation. If the
Dynamic Slip Test difference is greater than 0.2% (0.002), the meter shall be removed from service and designated for maintenance.
6.4.5.16 The meter may be returned to service with no further action if:
a. The meter proving shows acceptable repeatability (0.05% or better).
b. The new meter factor, or pre-run error found (on mechanical meter) does not exceed 0.25% (0.0025) from the previous meter
factor.
c. The Test Difference in the Dynamic Slip Test does not exceed 0.2% (0.002).
6.4.5.17 De-fueling operation should not be attempted until the fuel has warmed up to a temperature that will not cause harm to
the metering equipment or cause an out of range problem for temperature sensing devices.
6.4.5.18 If a meter is to be stored for long periods of time, it should be filled with lubricating oil to prevent corrosion in accordance with manufacturer’s instructions.

6.4.6 Proving Equipment for Aviation Fueling Meters
API MPMS Chapter 4 specifies the general design requirements and operations for provers. The following requirements, of which
some are also discussed in API MPMS Chapter 4, apply to proving equipment for aviation fuel dispenser and refueler meters.
6.4.6.1 Master meters equipped with mechanical registers should be proved (e.g., using a tank prover) for all products and flow
rates at which they will be operated. Master meters equipped with pulse generators may be proved using a dynamic prover (e.g.,
small pipe prover).
6.4.6.2 A master meter shall not be temperature compensated. Its reading shall indicate units of volume without corrections.
6.4.6.3 A master meter shall have a minimum readout resolution of 0.1 liter (or 0.1 gallon).
6.4.6.4 Master meters shall meet the repeatability and linearity requirements per API MPMS Chapter 4.5.
6.4.6.5 Master meters should be protected against damage during transportation, installation and handling.
6.4.6.6 Master meters should not have mechanical adjustment devices. If one is fitted, it should be sealed or disengaged.
6.4.6.7 A typical master meter proving system consists of:
a.
b.
c.
d.
e.

Meter with a volume display and an accurate flow rate indicator.

Upstream and downstream isolation valves.
Strainer located before the meter.
Thermometer or RTD.
Pressure gauge or transmitter.


SECTION 4—METERING SYSTEMS FOR AVIATION FUELING FACILITIES

5

f. Suitable hoses and fittings to connect the master meter to the meter being tested.
6.4.6.8 All master meters used for proving aviation fuel meters shall be proved at least once a year, or every 1.5 million liters
(or 400,000 gallons) throughput, whichever comes first.
6.4.6.9 Trailer tires, brakes, jacks, jockey wheel and towing wheel shall all be in an acceptable condition.
6.4.6.10 Pipe provers used for proving aviation fuel meters shall be calibrated according to guidelines established by API
MPMS Chapter 4.9.4.
6.4.6.11 The performance of the rate-of-flow indicators should be checked.
6.4.6.12 Meter sumps should be drained frequently to prevent accumulation of water.
6.4.6.13 Tank provers used to calibrate aviation fuel meters onboard a refueler or a hydrant cart should have been cleaned to
ensure the quality of the fuel will not be affected. Proving data shall be recorded and a proving report generated in accordance
with API MPMS Chapter 12.2.3.


6

CHAPTER 6—METERING ASSEMBLIES

Figure 1a—Typical Flow Diagram for a Refueler with Mechanical-type Meter

Basic Components
1. Bottom loading vent.
2. Float control.
3. Valve emergency dump.
4. Fuel/defuel valve.
5. Product pump and power takeoff unit.
6. Bypass pressure relief valve (secondary pressure control).
7. Filter/separator with air eliminator, drain.
8. Control valve (primary control valve) and deadman control.
9. Check valve.
10. Meter with electronic flow computer.
11. Venturi set for long hoses.
12. Reel, hose.
13. Reel, grounding.
14. Deadman.

25

15. Emergency valve operator (mechanical).
16. Bottom loading adapter.
17. Bottom loading control valve.
18. Butterfly valve.
19. Gage (mounted on panel).
20. Discharge hose.
21. Hose end pressure control valve (primary pressure control for long hoses).
22. Under-wing nozzel with strainer.
23. Nozzle holder/drive away interlock.
24. Deck hose swivel joint.
25. Resistance temperature detector.
Note: Line distinctions indicate flow scheme and do not represent separate piping configurations.

25

SECTION 4—METERING SYSTEMS FOR AVIATION FUELING FACILITIES
7

Figure 1b—Typical Flow Diagram for a Refueler with Electronic-type Meter


8

CHAPTER 6—METERING ASSEMBLIES

Figure 2a—Typical Flow Diagram for a Hydrant Cart with Mechanical-type Meter


Basic Components
1. Hydrant coupler.
2. Inlet hose.
3. Inlet hose swivel joint.
4. Butterfly valve.
5. Product pump and power takeoff unit.
6. Bypass pressure-relief valve (secondary pressure control).
7. Filter/separator with air eliminator drain.
8. Control valve (primary control valve) and deadman control.
9. Thermal relief valve.
10. Meter with electronic flow computer.
11. Venturi set for long hoses.
12. Reel, hose.

22

13. Reel, grounding.
14. Deadman.
15. Hose exacuation hand pump (optional).
16. Gage (mounted in panel).
17. Discharge hose.
18. Hose end pressure control valve (secondary pressure control).
19. Under-wing nozzle, with strainer.
20. Nozzle holder/drive away interlock.
21. Surge suppressors.
22. Resistance temperature detector.
Note: Line distinctions indicate flow scheme and do not represent separate piping
configurations.

22

SECTION 4—METERING SYSTEMS FOR AVIATION FUELING FACILITIES

Figure 2b—Typical Flow Diagram for a Hydrant Cart with Electronic-type Meter

9



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The Job Done Right.®


01/07


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Product No. H60402