U.S. Department 

of Transportation 

Federal Aviation 

Administration

Subject: Date: SPECIFICATION FOR L-884, 8/7/00 AC No.: 150/5345-54A 

POWER AND CONTROL UNIT 

FOR LAND AND HOLD SHORT 

LIGHTING SYSTEMS 

Initiated by: AAS-200 Change: Including Change 1 

1. PURPOSE. This advisory circular (AC) contains the Federal Aviation Administration (FAA) standards for power and 

control units for Land and Hold Short Lighting Systems. 

2. CANCELLATION. AC 150/5345-54, Specification for L-884 Power and Control Unit for Land and Hold Short 

Lighting Systems, dated 4/29/99, is cancelled. 

3. PRINCIPAL CHANGES. The following principal changes have been incorporated into this AC. 

a. The final version of AC 150/5340-29 describes a LAHSO lighting system consisting of only one bar of pulsing 

white lights. Accordingly, all references to the L-884H and L-884A have been dropped from this specification. 

b. In response to pilot comments to provide a more continuous indication of the location of the hold short point 

while maintaining an acceptable pulse rate, the “on” time of the pulsing lights has been lengthened and the “off” time has 

been shortened. 

c. Addition of basic impulse insulation level (BIL) tests. 

d. Provided more specific label for PCU control switch settings. Also provided for a “field control” and “tower 

control” indication on the PCU. 

4. BACKGROUND. FAA Order 7110.118, Land and Hold Short Operations (LAHSO), provides operational 

requirements for lighting systems and other visual navigation aids required to conduct LAHSO. The order is available on 

the Internet at: www.faa.gov/ats/ato/12014.htm. 

5. APPLICATION. The standards contained herein are recommended by the FAA in all applications involving airport 

development of this nature. The use of these standards is mandatory for airport projects receiving Federal funds under the 

airport grant assistance program or the passenger facility charge (PFC) program. 

6. METRIC UNITS. To promote an orderly transition to metric units, this AC includes both English and metric 

dimensions. The metric conversions may not be exact equivalents and, until there is an official changeover to the metric 

system, the English dimensions will govern. 

David L. Bennett 

Director, Office of Airport Safety 

 and Standards 

8/7/00 AC 150/5345-54A 

1

FAA SPECIFICATION FOR L-884 POWER AND CONTROL UNIT 

FOR LAND AND HOLD SHORT LIGHTING SYSTEMS 

1. SCOPE AND CLASSIFICATION. 

1.1 Scope. This specification contains the requirements for a power and control unit (PCU) used to control and pulse land 

and hold short lighting systems. 

1.2 Equipment Classification. 

1.2.1 Style. Two styles of systems are covered by this specification. 

 

Style Description 

I Indoor Unit 

II Outdoor Unit 

1.2.2 Ratings. Standard ratings are as follows; however, other voltages, frequencies, or sizes may be used to suit local site 

conditions. 

Standard Voltages (Volts in) Standard Frequency (Hz) 

120, 208, 240 60 

2. REFERENCED DOCUMENTS. The following is a list of documents referenced in this AC. 

2.1 FAA Advisory Circulars. 

 AC 150/5300-13 Airport Design Standards 

 AC 150/5340-29 Installation Details for Land and Hold Short Lighting Systems 

AC 150/5345-3 Specification for L-821, Panels for Control of Airport Lighting

 AC 150/5345-46 Specification for Runway and Taxiway Light Fixtures

 AC 150/5345-47 Isolation Transformers for Airport Lighting Systems 

 AC 150/5345-53 Airport Lighting Equipment Certification Program 

2.2 FAA Drawings. 

 FAA Drawing C-6046 Frangible Coupling Type I and Type IA, Details

2.3 FAA Standards.

 FAA-STD-020 Transient Protection, Grounding, Bonding and Shielding Requirements for Electronic 

Equipment 

2.4 FAA Orders. 

 Order 7110.118 Land and Hold Short Operations (LAHSO) 
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2.5 American National Standards Institute (ANSI) publications. 

 ANSI C57.12.00 General Requirements for Distribution, Power, and 

 Regulating Transformers 

 ANSI C57.12.91 Standard for Dry-Type Transformers 

2.6 Military Standards. 

 MIL-STD-810E Environmental Test Methods

 MIL-STD-461D Requirement for the control of Electromagnetic Interference Emissions of Susceptibility 

 MIL-STD-462D Electromagnetic Interference Characteristics, Measurement of 

2.7 National Electrical Manufacturers Association (NEMA) Standards 

 

 NEMA 250-1985 Enclosures for Electrical Equipment (1000 volts maximum)

Notes: Copies of FAA ACs may be obtained from the Department of Transportation, General Services Division, 

M-45, 400 7th Street SW., Washington, DC 20590. Telephone: (202) 267-3161/3115/8329. Some ACs are available on 

the Internet at: www.faa.gov/arp/150acs.htm. 

 Copies of FAA Order 7110.118 may be obtained from the Internet at: www.faa.gov/ats/ato/12014.htm. 

 Copies of ANSI publications may be obtained from the ANSI, 11 W. 42 Street, New York, NY 10036. 

Telephone: (212) 642-4900 and 764-3274. 

 Copies of Military Standards may be obtained from the Defense Printing Service, 700 Robins Avenue (Bldg. 4d), 

Philadelphia, PA 19111-5094, Attn: Customer Service. Telephone: (215) 697-2179 Fax: (215) 697-1460. 

 Copies of National Electrical Manufacturers Association (NEMA) Standards may be obtained from Global 

Engineering Documents (Global) and Information Handling at (800) 854-7179 (within the U.S.) (303) 397-7956 

(international) (303) 397-2740 (fax) or at 15 Inverness Way East, Englewood, Colorado 80112-5776. 

3. EQUIPMENT REQUIREMENTS. 

3.1 General Requirements. Each L-884 power and control unit (PCU) shall be a power supply designed to power and 

simultaneously pulse all lights in a LAHSO light bar. A LAHSO light bar is a row of six or seven in-pavement 

unidirectional pulsing white lights installed in a runway to visually indicate the location of a LAHSO hold short point. 

Detailed installation criteria for LAHSO lighting systems are contained in AC 150/5340-29, Installation Details for Land 

and Hold Short Lighting Systems. 

3.2 Environmental Requirements. 

3.2.1 Style I, Indoor PCU. Equipment intended for indoor installation shall be designed to operate properly under the 

following conditions: 

a. Temperature. Any ambient temperature from -40F (-40C) to 131F (55C). 

b. Humidity. Any relative humidity from 10% to 95%. 
6/29/01 AC 150/5345-54A CHG 1 

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 c. Altitude. Any altitude from zero to 6,600 feet (2000 m). 

3.2.2 Style II, Outdoor PCU. Equipment intended for outdoor installation shall be designed to operate properly under the 

following conditions: 

a. Temperature. Any ambient temperature from -67F (-55C) to 158F (70C). 

 b. Humidity. Any relative humidity from 0% to 100% at an ambient temperature of 158F (70C). 

c. Altitude. Any altitude from zero to 6,600 feet (2000 m). 

d. Sand and Dust. Exposure to wind borne sand and dust particles. 

e. Windblown Rain. Exposure to windblown rain from any direction. 

 

f. Wind. Exposure to wind speeds up to 100 mph (161 km/hr) from any direction. 

 

g. Salt-Spray. Exposure to salt-laden atmosphere. 

h. Sunshine. Exposure to solar radiation. 

3.3 Design Requirements. 

3.3.1 Enclosures. All PCUs shall be housed in the appropriate NEMA style housing and shall provide suitable space for 

the installation of the communication interface(s) to provide the control requirement specified in paragraph 3.5 of this 

document. Each unit shall have a hinged access door with provisions for padlocking. 

3.3.1.1 Style I, Indoor PCU. Style I, PCUs shall be housed in a stainless steel or aluminum NEMA Style 1 enclosure. 

3.3.1.2 Style II, Outdoor PCU. Style II, PCUs shall be housed in a stainless steel or aluminum NEMA Style 4 or 4X 

enclosure. The total weight of each style II, PCU shall not exceed 100 lbs (46 kg). When style II, PCUs are installed in 

accordance with the manufacturer’s instructions, the top of the unit shall not be higher than 42 inches (1070 mm) above the 

ground. PCU’s designed for installation inside the runway and taxiway safety areas shall: not be higher than 30 inches 

above the ground, not exceed 75 lbs, and be installed with frangible couplings which conform to FAA drawing C-6046. 

(Runway Safety Areas (RSA) and Taxiway Safety Areas (TSA) are defined in AC 150/5300-13, Airport Design Standards.) 

The frangible coupling and mounting flanges shall be designed for use with 2-inch (51 mm) electrical metallic tubing 

(EMT) and shall be suitable for mounting on a concrete pad. The point of frangibility shall be located no higher than 

3 inches above grade when installed. 

3.3.1.3 Size. Each unit with enclosure shall comply with the following maximum dimensions: width 24 inches (610 mm), 

height 36 inches (915 mm), and depth 9 inches (228 mm). 

3.3.1.4 Painting and Finishing. The inside and outside of the PCU enclosure shall be protected by at least one prime coat 

(or other suitable preparatory painting process) and one finish coat. Paint for the finish coat shall be high-quality paint 

suitable for the drying process used. Paint for the prime coat shall be suitable for the metal treatment involved. The color 

of the outside finish coat for all PCUs shall be color No. 12197, Federal Standard 595. The outside painted surface of the 

enclosure shall be free of scratches, blemishes, and chipping.

3.3.2 Control Cabinet. The control circuits, relays, sensing devices, control terminal block, remote/local control switch or 

keypad, and other low voltage control components shall be protected from the elements of the specified environment. This 

protection may be provided by the main enclosure or an additional cabinet/compartment installed inside the PCU. All low 

voltage control components shall be accessible by opening the housing (main enclosure, cabinet/compartment) in which 

they are installed. 
8/7/00 AC 150/5345-54A 

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3.3.3 Switches. Each PCU shall have a local control switch and an input power switch, both located inside the enclosure. 

The switches shall have a contact rating of 125% of the load current and shall be rated to meet the circuit voltage 

requirements. All switches installed with style II PCUs shall be designated for outdoor applications. 

3.3.3.1 PCU Local Control Switch (Output Power). The local control switch shall energize and de-energize the PCU 

output power. The switch shall be clearly and permanently marked to indicate the local control settings. The positions shall 

include “REMOTE,” “OFF,” “B3 (4.1A),” “B4 (5.2A),” and “B5 (6.6A).” When the switch is in the “off” position or set 

to any of the brightness steps, the local setting shall override the “on/off” switch on the L-821 remote control panel and the 

PCU’s automatic intensity control system described in 3.5.2. The PCU shall have a provision (terminal strip, etc.) that 

would be used to send the status of the PCU local control switch to the airport traffic control tower. When connected, a 

“tower control” light will illuminate on the L-821 LAHSO panel in the tower when the local control switch on the PCU is 

set to “remote.” A “field control” light will illuminate on the L-821 panel whenever the local control switch is on a setting 

other than “remote.” If a relay is used for this function, the “field control” light shall be illuminated with the relay deenergized. 

3.3.3.2 PCU Input Power Switch. The input power switch shall be provided inside the PCU to de-energize input power to 

the unit for maintenance. When this switch is locked in the “off” position the input power to the unit shall be disabled and 

the unit shall be completely de-energized. The input power switch shall be clearly marked with a permanent marking to 

indicate when the PCU is “on”(energized) or “off”(de-energized). 

3.3.4 Components. All PCU components shall be suitable for their function and shall not be operated in excess of the 

component manufacturer’s recommended rating. 

3.4 Electrical Requirements. 

3.4.1 Input Voltage. The PCU should be designed to operate from any standard utility single-phase alternating current 

service voltage less than 600 volts, and frequencies of 50 or 60 Hz. The standard voltages are 120 V, 208 V, or 240 V, and 

the standard frequency is 60 Hz AC. 

3.4.2 Output Current. 

3.4.2.1 Pulse Rate. The output current of the PCU shall continuously alternate between “on” and “off” to pulse the 

LAHSO light units simultaneously. The "on" cycle duration shall be 1.72 seconds (+/- 0.1 seconds), and the "off" cycle 

duration shall be 0.46 seconds (+/- 0.1 seconds). The light units in the LAHSO light bar shall pulse simultaneously at all 

times, therefore the duration of the tolerance applies to the entire light bar inclusive of all light units. 

3.4.2.2 Peak Current. The PCU shall develop a peak output current (rms) during the “on” cycle within the limits specified 

in Table 1, while powering any load between no load (short circuit) and full (rated) load. Once the peak output current is 

reached, the current shall not fall below the allowable range until the beginning of the “off” cycle. The peak output current 

shall not exceed the maximum value of the allowable range stated in Table 1. The output current during the “off” cycle 

shall be 1 ampere, (-0.5, +0.5 amperes) for all intensity steps. 

Table 1. PCU Peak Output Current (Amperes rms).

Step Nominal Output Allowable Range 

5 6.6 6.40 - 6.70 

4 5.2 5.04 - 5.36 

3 4.1 3.98 - 4.22 

2 Not Used -- 

1 Not Used -- 

3.4.2.3 Output Current Surge Limitation. Switching the PCU “on” and “off,” changing brightness steps, or shorting the 

load shall not produce output surges that cause damage to the lamps. If a time delay is utilized, the time delay between the 

PCU being switched “on” to the delivery of current to the LAHSO light bar shall not be more than 2 seconds. 
8/7/00 AC 150/5345-54A 

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3.4.3 Loss of Power. In the event of a loss of input power, the PCU shall resume normal operation within 5 seconds after 

the restoration of input power. 

3.4.4 Transient Suppression. For solid state equipment, transient suppression shall be provided in accordance with FAASTD-020, Paragraph 3. The transient suppression devices shall be capable of withstanding lightning transients consisting of 

a 10-by-20 microsecond current surge of 15,000 amperes with the subsequent power-follow current and a voltage surge of 

10 kV/microsecond. The system shall also withstand without damage the repeated application of an over voltage transient 

on the input power lines equal to 500 volts peak for a duration of 50 milliseconds. 

3.4.5 Lightning Arresters. Lightning arresters shall be provided with each PCU. The lightning arresters shall be sized to 

protect the unit and should be connected between each output terminal and ground. The ground side of the arresters shall be 

connected to the grounding lug of the enclosure or other suitable location. The lightning arresters shall be able to withstand

without damage the repeated application of an over voltage transient on the input power lines equal to 500 volts peak for a 

duration of 50 milliseconds. 

3.4.6 Electromagnetic Interference. The PCU shall cause minimal radiated or conducted electromagnetic interference to 

other equipment such as computers, radars, instrument landing systems, radio receivers, very high frequency 

omnidirectional radio ranges, global positioning system units, etc., that may be located on or near an airport, or use the same

power supply. Any electromagnetic interference that degrades, obstructs, or repeatedly interrupts the desired performance 

of electronic equipment in the airport environment is unacceptable. Each PCU shall meet the requirements in MIL-STD461, CE101, applying the limit in Figure CE101-4 and CE102, applying the limits in Figure CE102-1. Each PCU shall also 

meet the requirements in FAA-STD-020. 

3.4.7 Terminal Block. Pressure-style terminal blocks having a suitable voltage rating shall be installed in the control 

cabinet for connection of the external wiring associated with monitoring and remote control. Terminal blocks shall 

accommodate No. 12 to No. 20 AWG wire with insulation rating up to 600 V. Two spare positions shall be provided. Each 

individual terminal shall be identified with permanent markings that match the identities in the wiring diagram furnished 

with the unit. 

3.5 Control Requirements. 

3.5.1 General Requirement. The PCU shall have provisions to control the appropriate operational functions locally 

and/or remotely. The local control shall be located on the PCU. A remote control panel shall be located in the airport 

traffic control tower (ATCT). All control panels shall comply with AC 150/5345-3, Specification for L-821, Panels for 

Control of Airport Lighting. 

3.5.2 Intensity (Brightness) Control. When the PCU local control switch is set to the “remote” position, the PCU 

automatically selects the intensity of LAHSO light bar. The PCU receives input control signals from a photocell and a 

sensor that detects the intensity/current (step) of the runway edge lights installed on the same runway as the LAHSO light 

bar. Based on the background illumination falling on the photocell, the PCU shall be automatically set in day mode or night 

mode. In day mode the system intensity shall be set to step 5 (6.6 A). In night mode the intensity selection is dependent on 

the intensity setting of the runway edge lights and shall be in accordance with Table 2. If the PCU local control switch is set 

to “off” or a brightness step, then the local control setting shall override all automatic intensity control, in accordance with 

3.3.3.1. 

3.5.3 Photoelectric Control. The photocell shall be installed facing the northerly direction. The PCU shall automatically 

set the intensity to the specified day mode setting when the illumination on the photocell rises to 55 (+/- 5) footcandles, and

to night mode settings when the illumination drops to 30 (+/-5) footcandles. An intensity setting transition time delay of 45 

to 75 seconds shall be incorporated into the unit to prevent the unit from switching due to stray light or temporary shadows. 

The photocell shall be an integral part of style II PCUs. The photocell mounting system shall allow the photocell to be 

turned around 360 in azimuth and shall have locking provisions to keep it from moving out of position under the wind 

loads stated in Paragraph 3.2.2. A photocell shall be provided with each style I PCU. The purchaser is responsible for 

installing the photocell remotely in accordance with the PCU manufacturer’s instructions. In the event of the failure of the 

photoelectric control circuit, the PCU shall revert to the highest intensity step: step 5 (6.6 A). Photoelectric circuit failure is 

defined as a non-communication or miscommunication of information, e.g. the photocell identifies daytime lighting 

conditions at night or vice versa. 
8/7/00 AC 150/5345-54A 

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Table 2. LAHSO Light Bar Intensity Steps (amperes). 

 Day Mode Night Mode 

MIRL/HIRL 

Light Intensity 

LAHSO Light Bar 

with MIRL 

LAHSO Light Bar 

with HIRL 

LAHSO Light Bar 

with MIRL 

LAHSO Light Bar 

with HIRL 

5 -- 5 (6.6 A) -- 5 (6.6 A) 

4 -- 5 (6.6 A) -- 5 (6.6 A) 

3 5 (6.6 A) 5 (6.6 A) 4 (5.2 A) 4 (5.2 A) 

2 5 (6.6 A) 5 (6.6 A) 3 (4.1 A) 3 (4.1 A) 

1 5 (6.6 A) 5 (6.6 A) 3 (4.1 A) 3 (4.1 A) 

Off 5 (6.6 A) 5 (6.6 A) 3 (4.1 A) 3 (4.1 A) 

Note: The above intensity selections are based on the intensity selections of the runway edge lighting system installed on 

the same runway as the LAHSO light bar. (Runway edge lighting systems are described in AC 150/5340-24.) High 

intensity runway lights (HIRL) circuits are installed with 5-step constant current regulators. Similarly, medium intensity 

runway lights (MIRL) circuits are installed with 3-step regulators. 

3.5.4 Monitoring. The PCU shall have monitoring capabilities internal to the unit. The monitor shall detect the status of 

the PCU (“on”, “off”, etc.), LAHSO light bar circuit (lights on, lights off, current intensity step, etc.), and each light unit (on 

or not on when required to be on or off) in the system. The monitor shall operate at all lighting intensity steps and when the

PCU is controlled remotely or locally. The monitor outputs shall be connected to a terminal block to facilitate external 

connections, and shall operate properly while connected to a circuit with a minimum round-trip length of 20,000 feet (3,000 

m) using No. 19 AWG wire. The voltage for the monitor external output shall not exceed 120 V. An RS-232 monitor 

output port may be provided at the request of the purchaser, in addition to the terminal block. A visual indication shall be 

provided on the monitor to indicate which fault has occurred (except for fault (i)). A PCU-on indicator light shall be 

provided on each unit to indicate when the unit is energized. If any of the system faults described below occur, a fault light

shall be displayed for the affected LAHSO light bars on the LAHSO control panel in the ATCT. Upon initial detection of a 

fault the monitor shall delay the specified amount of time before indicating the fault. The fault and time delay requirements 

are as follows: 

 i) Loss of input power to the PCU. (0 seconds) 

 ii) Shutdown of the PCU due to operation of any protective circuits. (0 seconds) 

 iii) A failure of the PCU to pulse the light fixtures. (5 seconds) 

 iv) A failure of two or more lamps in a LAHSO light bar. (5 seconds) 
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3.6 General Requirements. 

3.6.1 Wiring Diagram. A legible wiring diagram shall be permanently mounted in an unobstructed place in the control 

cabinet. The wiring diagram shall be protected from dirt, dust, and moisture. (i.e. place in a protective sheet cover.) 

3.6.2 Warning Label. A plate or decal shall be affixed to the front of the control cabinet door warning maintenance 

personnel to remove input and control power before opening the cabinet. 

3.6.3 Nameplate. A nameplate with the information below shall be securely attached to the front of the PCU enclosure. If 

the nameplate is attached to a readily removable surface, such as a cover, the serial number shall be duplicated in a 

permanent conspicuous place elsewhere on the PCU. 

 (1) Land and hold short light power and control unit, 

 single phase. 

 (2) Input:_______Volts _______Hertz _______Amperes. 

 (3) Control:_______Volts _______Hertz. 

 (4) Output:_______kW at _______Amperes. 

 (5) Output Current: ____/____/____Amperes. 

 (6) Identification: FAA-L-884 _______Serial No. 

3.6.4 Instruction Book. An instruction book containing at least the following information shall be furnished with each 

PCU: 

 (1) Complete schematic and wiring diagrams showing all components cross-indexed to the parts list. 

(2) Complete parts list with applicable rating and characteristics of each part and with the component 

manufacturer's name and part number. 

 (3) Installation instructions. 

 (4) Maintenance instructions. 

 (5) Troubleshooting charts. 

 (6) Theory of operation. 

 (7) Software User’s Manual. (If software is used in the system design.) 

4. EQUIPMENT QUALIFICATION PROCEDURES.

4.1 Qualification Procedures. Procedures for qualifying equipment to be furnished under the Federal grant assistance 

program for airports are contained in AC 150/5345-53, Airport Lighting Equipment Certification Program.

4.2 Qualification Tests. The following tests shall be performed on each unit submitted for qualification, to demonstrate 

compliance with the specification. 

4.2.1 Visual Examination. The equipment shall be examined for compliance with the requirements on size, weight, 

materials, finish, and quality of workmanship. 
8/7/00 AC 150/5345-54A 

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4.2.2 High Temperature Test. A high temperature test shall be conducted in accordance with MIL-STD-810E, Method 

501.3, Procedure II. The equipment shall be subjected to a stable temperature of +131 F (55 C), +/- 5F (style I), +158F 

(70 C), +/- 5 F (style II), for a period of 4 hours after temperature stabilization. The test unit shall be operated throughout 

this test and perform all specified functions. Any deterioration in materials or performance will be cause for test failure and 

cause the equipment to be rejected. 

4.2.3 Low Temperature Test. A low temperature test shall be conducted in accordance with MIL-STD-810E, Method 

502.3, Procedure II. Style I PCUs shall be subjected to a 24 hour soak at -40F (40 C), +/-5F. Style II PCUs shall be 

subjected to a 24 hour soak at -67F (-55 C), +/-5F. The test unit shall be operated on the first and last cycles of this test 

and perform all specified functions. Any deterioration in materials or performance will be cause for test failure and cause 

the equipment to be rejected. 

4.2.4 Humidity Test. Subject all PCUs to a humidity test in accordance with MIL-STD-810E, Method 507.3, Procedure I. 

The equipment shall be subjected to three cycles (72 hours) according to Table 507.3-I, except the maximum temperature at 

cycle 1 shall be +131 F (+55 C), +/-5 F+158F (70 C), +/- 5 F (style II). The test unit shall be operated throughout this 

test and perform all specified functions. Any deterioration in materials or performance will be cause for test failure and 

cause the equipment to be rejected. 

4.2.5 Low Pressure (Altitude). Each PCU shall be tested for low pressure (altitude) according to MIL-STD-810E, 

Method 500.2, Procedure II. The maximum altitude shall be 6,600 feet (2,000 m) and the ambient temperature shall be 

+131 F (+55 C), +/-5 F, +158F (70 C), +/- 5 F (style II). The PCU shall be operated at rated voltage, load, and 

maximum brightness for 4-hours. Failure of the input voltage test immediately after the 4-hour cycle shall be cause for 

rejection. 

4.2.6 Sand and Dust Test. [Applies to Style II PCUs only] A sand and dust test shall be conducted in accordance with 

MIL-STD-810E, Method 510.1, Procedure I. Rotate the equipment 120 degrees twice during the test. The air velocity shall 

be 2,500 +/- 500 feet per minute (760 +/- 150 meters per minute). 

4.2.7 Rain Test. [Applies to Style II PCUs only] A wind-blown rain test shall be conducted in accordance with 

MIL-STD-810E, Method 506.3, Procedure I, with a rain rate of 5.2 inches/hr (13 cm/hr). The test duration shall be 

30 minutes per side. Any deterioration of system performance or excessive accumulation of water in the PCU enclosure 

shall be cause for rejections. 

4.2.8 Wind Test. [Applies to Style II PCUs only] The test unit shall be mounted to one or more 2-inch (51 mm) EMT 

conduit and subjected to a 100 MPH wind which shall be applied from all directions. Any physical distress, damage, or 

deterioration to any part of the test unit’s assembly or alteration of the units performance will be cause for test failure and

cause the equipment to be rejected. 

4.2.9 Salt-Fog Test. [Applies to Style II PCUs only] A salt-fog test shall be conducted in accordance with 

MIL-STD-810E, Method 509.3, Procedure I. The test duration shall be 48 hours exposure and 48 hours drying. Any 

evidence of damage, rust, pitting, or corrosion (except for sacrificial coatings) shall be cause for rejection . 

4.2.10 Solar Radiation (sunshine) Test. [Applies to Style II PCUs with non metallic external parts only] A sunshine 

test shall be conducted in accordance with MIL-STD-810 E, Method 505.2, Procedure II. The material shall be subjected to 

a minimum of 56 cycles. The test unit shall operate and perform all specified functions after this test. Any evidence of 

deterioration or alteration of the test unit’s performance shall be cause for rejection. 

4.2.11 Frangibility Test. [Applies to Style II PCUs only] The manufacturer shall demonstrate that the frangibility of the 

mounted unit is equivalent to that of a 2-inch (51mm) frangible coupling depicted in FAA drawing C-6046. 

4.2.12 Basic Impulse Insulation Level (BIL) Tests. Subject the primary and secondary of the PCU to BIL tests in 

accordance with ANSI C57.12.91. 

4.2.13 Temperature Rise. Determine the temperature rise of the PCU transforming device in accordance with ANSI 

C57.12.91. 
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4.2.14 Dielectric Test. The test unit shall be subjected to a minimum of 2000 V (input circuit lines to ground), 1000 V 

(control circuit lines to ground), and 2,000 V (output lines to ground) at 60 Hz RMS for one minute without failure. The 

minimum insulation resistance for this test shall be 50 megohms. Components of the test unit not designed to meet the 

requirements of this test, such as lightning arresters, shall be disconnected for the dielectric test. 

4.2.15 Transient Suppression Test. For PCUs containing solid-state components, the power input lines shall be tested for 

resistance to the lightning transient in accordance with MIL-STD-462D, Method CS06, including Notices 1, 2, and 3. The 

system shall be tested for resistance to the over voltage transient given in Paragraph 3.4.4. After the transients have been 

applied to the system, it shall continue to supply specified output currents at all intensity settings. 

4.2.16 Electromagnetic Interference Test. The test unit shall be tested to verify conformance with the interference 

requirements in paragraph 3.4.6. Conducted interference levels on the power leads, control leads, and signal leads, shall not 

exceed the limits for CE101, Figure CE101-4, and CE02, Figure CE102-1. Test in accordance with the test methods 

defined in MIL-STD-462D. 

4.2.17 Operational Test. An operational test shall be performed to demonstrate compliance with all operating 

requirements specified in this AC. 

5. PRODUCTION TEST REQUIREMENTS.

5.1 Production Tests. The following tests shall be conducted on each PCU. 

5.1.1 Visual Examination. The equipment shall be examined for compliance with the requirements on materials, finish, 

and quality of workmanship. 

5.1.2 Operational Test. An operational test shall be performed to demonstrate compliance with all operating requirements 

specified in this AC. 
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Figure 1. Typical Block Diagram For Land And Hold Short Lighting System 
8/7/00 AC 150/5345-54A 

Appendix 1 

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APPENDIX 1. Terms. 

A. Land and Hold Short Operations (LAHSO) – Air Traffic Control Operations that include landing and holding short 

of an intersection runway, a taxiway, a predetermined point, or an approach/departure flight path. 

B. LAHSO Light Bar – A row of six or seven in-pavement unidirectional pulsing white lights installed in a runway to 

visually indicate to the pilot the hold short point during a LAHSO operation. 

C. Light Unit – A single light assembly including the fixture, filter, bulb, etc.