Attachment_3_-_APN-209_Pulse_Repition_Frequency_Specification_-_17R0017.pdf

MIL-A-49079A(CR)

9 JUNE 1986

SUPERSEDING

MIL-A-49079(CR)

5 DECEMBER 1979

MILITARY SPECIFICATION

ALTIMETER SET, ELECTRONIC AN/APN-209(V)

(UNITS O F )

This specification is approved for use within Comniunications- Electronics Command, Department of the Army, and is available for use by all Departments and agencies of the Department of Defense.

1. SCOPE

"1.1 SCOPE. This specification covers the following units of Radar Altimeters which provide an accurate indication of altitude of. an air-craft over an altitude range of O to 1,500 feet and are designated Altimeter Set, Electronic AN/APN-209A(V), and AN/APN-209B(V) (See 6.1 and 6.4):

Antenna, AS-2595/APN-l94(V) Antenna, AS-3586/APN-209A(V) Receiver-Transmitter, Height Indicator; RT-1115A/APN-209(V) Receiver-Transmitter, Height Indicator; RT-1115B/APN-209(V) Receiver-Transmitter, RT-1411/APN-209A(V) Indicator, Height, ID-1917/APN-209(V) Indicator, Height, ID-1917A/APN-209(V)

2. APPLICABLE DOCUMENTS

2.1 Government documents.

2.1.1 Specifications, standards and handbooks. The following

specifications, standards and handbooks form a part of this specifica-tion to the extent specified herein. Unless otherwise specified, the issues of these documents shall be those listed in the Department of Defense Index of Specifications and Standards (DODISS) and supplement thereto, cited in the solicitation.

Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to Commander, U.S. Army Communications-Electronics Command, ATTN: AMSEL-ED-TO, Fort Monmouth, New Jersey 07703 by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter.

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SPECIFICATIONS

Federal

L-P-378

NN-P-71

QQ-S-Y~~

PPP-T-97

PPP-B-585

PPP-B-601

PPP-B-621

PPP-B-636

PPP-B-6 4 O

PPP-B-1672

PPP-S-760

Military

MIL-P-116

MIL-C-5541

MIL-P-11268

MIL-"13231

MIL-F-14072

MIL-P-15024/6

MIL-L-25467

MIL-M-38510/104

MIL-1-49077

Plastic Sheet Strip, Thin Gauge Polyolefin

Pallet, Material Handling, Wood, Stringer Construction, 2 Way and 4 Way (Partial )

Strapping, Steel and Seals

Tape, Packaging/Industrial, Filament Reinforced

Box, Wood, Wirebound

Box, Wood, Cleated Plywood

Box, Wood, Nailed and Lock Corner

Box, Shipping, Fiberboard

Box, Fiberboard, Corrugated, Triplewall

Box, Shipping, Reusable with Cushioning

Strapping, Nonmetallic (and Connectors)

Preservation-Packing, Methods of

Chemical Conversion Coatings and Aluminum and Aluminum Alloys

Parts, Materials and Processes Used in Electronic Communication Equipment

Marking of Electronic Items

Finishes for Ground Signal Equipment

Plate, Identification

Lighting, Integral, Instrument, General Specification for

Microcircuits, Linear, Line Drivers and Receivers, Monolithic Silicon

Installation and Acceptance Testing of Altimeter Set, Electronic AN/APN-209 in Army Aircraft

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STANDARDS

0 Federal

PED-STD-595

Military

MIL-STD-105 Sampling Procedures and Table for . Inspection by Attributes

Color

MIL-STD-129 Marking for Shipment and Storage

L MIL-STD-252

MIL-STD-454

MIL-STD-461

MIL-STD-462

MIL-STD-704

Wired Equipment, Classification of Visual and Mechanical Equipment

Standard General Requirements for Elec-tronic Equipment

Electromagnetic Interference Characteristics, Requirements for Equipment

Electromagnetic Interference Characteristics, Measurement of

Electric Power, Aircraft, Characteristics and Utilization of

O MIL-STD-781B Reliability Tests, Exponential Distribution

MIL-STD-810 Environmental Test Methods

MIL-STD-1188 Commercial Packaging of Supplies and Equipment

2.1.2 Other Government documents, drawings, and publications. The fol-lowing other Government documents, drawings and publications form a part of this specification to the extent specified herein. Unless otherwise specified, the issues shall be those in effect on the date of the solici-tation.

F.

*DRAWINGS

1- USAECOM (80063)

DL-SM-B-707893 Indicator, Height ID-1917/APN-209(V)

DL-SM-B-967122 Receiver-Transmitter, Height Indicator

RT-1115A/APN-209(V)

DL-SM-B-967240 Indicator, Height, ID-1917A/APN-209(V)

DL-SM-B-967283 Receiver-Transmitter, Height Indicator

RT-1115B/APN-209(V)

DL-SM-B-967310 Receiver-Transmitter RT-1411/APN-209A(V)

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MIL-A-47079A 5 8 W 3977706 0358637 L W

DL-SM-B-967316 Antenna AS-2595/APN-194 (V) DL-SM-B-967321 Antenna AS-3586/APN-209A(V)

(Copies of specifications, standards, drawings and publications required by suppliers in connection with specific procurement functions should be obtained from the procuring activity or as directed by the Contracting Officer.)

2.2 Order of precedence. In the event of a conflict between the text of this specification and the references cited herein (except for.

associated detail specification, specification sheets of MS standards), the test of this specification shall take precedence.

Nothing in this specification, however, shall supersede applicable laws and regualations unless a specific exemption has been obtained.

3 . REQUIREMENTS

"3.1 Description (See 4.18) - The Altimeter Set provides a con-tinuous indication of absolute altitude of an aircraft above the sur-face of the earth and the features upon it by transmitting a radio frequency signal in the range of 4200 to 4400 MHz to the ground, re-ceiving the reflected signal and indicates the altitude of the aircraft on the IRT unit and a remote indicator. The Altimeter set operates from an aircraft supply having a nominal voltage of 27.5 volts DC. Absolute altitude indications are accomplished by the use of the units listed in 1.1. The Receiver-Transmitter, Height Indicator (IRT) or Receiver-Transmitter (RT) transmits a radio frequency signal, receives the reflected signal, and derives the proper signals for O to 1500 feet radar altitude in accordance with the requirements of this specification. In addition, the Receiver- Transmitter, Height Indicator displays analog altitude, digital altitude and high and low altitude warnings. It provides these signals along with an auxiliary analog altitude signal, a reliability signal and a self test confidence signal. The Receiver-Transmitter also provides the auxiliary analog altitude, reliability and self test confidence signals. The Receiver-Transmitter, Height Indicator or Receiver-Transmitter shall be capable of driving a remote Height Indicator (RI).

3.2 First Article - The contractor shall furnish the specified number of First Article units on order, as required by the contract (see 4.3).

*3.3 Construction (see 4.11) - The unit(s) on order shall be con-structed in accordance with the following:

DL-SM-B-707893 Indicator, Height ID-1917/APN-209(V) DL-SM-B-967122 Receiver-Transmitter, Height Indicator

RT-1115A/APN-209 (V)

DL-SM-B-967240 Indicator, Height ID-1917A/APN-209 (V)

DL-SM-B-967283 Receiver-Transmitter, Height Indicator

RT-1115B/APN-209 (V)

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DL-SM-B-967310 Receiver-Transmitter RT-1411/APN-209A(V)

DL-SM-B-967316 Antenna AS-2595/APN-l94(V)

DL-SM-B-967321 Antenna AS-3586/APN-209A(V)

3.3.1 Parts, Materials and Processes (See 4.4) - In addition to the requirements of this specification, the requirements of MIL-P- 11268 including the selection requirement therein, shall apply.

*3.3.2 Weiqht (See 4.14) - The weight of each completely assembled il unit shall not exceed 4.2 pounds for the RT-1115( )/APN-209(V), 2.5 pounds for the ID-1917( )/APN-209(V), 0.65 pounds for AS-2595/APN- 194(V), 3.4 pounds for the RT-1411( )/APN-209A(V), and 0.15 pounds for the AS-3586/APN-209A(V).

3.3.3 Controls (See 4.11) - All movable controls shall operate properly without binding or other undue restriction. Controls shall not be assembled in a misaligned condition.

*3.3.4 Finish, Protective (See 4.4) - The units shall be given protective finish in accordance with MIL-F-14072. This includes finish -of hardware, such as screws, etc., and necessary touch-up after mount-ing. The final paint film on Type 1 surfaces shall be Film B in accord-ance with MIL-F-14072, except that the face of the AS-2595/APN-l94(V) shall be in accordance with 3.10.1.9 and that of the 0 AS-3586/APN-209A(V) shall be in accordance with 3.10.2.8.

3.4 Service Conditions (See 4.8) - The unit(s) on order shall meet the following service conditions:

3.4.1 Temperature-Altitude (See 4.8.1) - The unit(s) on order shall be subjected to and mget the temperature-altitude requirements when non-operating from -62 C through +85 C at sea level to 40,000 feet. The unit(s),shall be operable and conforming to limits specified from -54 C through +71 C at sea level to 30,000 feet with the exception that the accuracy may degrads to + ( 6 . 2 feet + 38 of alt&tude)- in the temperature ranges of -54 C to”40 C and +55 C to

+55 C to +71 C. Noodamage s8all result from exposure to temperatures in the range of -62 C to +85 C and pressures from sea level to 40,000

W +7lOC. Opergtion shall be intermittent over the temperature range of z m feet.

3.4.2 Humidity (See 4.8.2) - The unit(s) shall withstand up to 100 percent relative humidity including conditions wherein conden-sation takes place in the f0r.m of water. When exposed to the above conditions the unit shall suffer no damage in the non-operating condi-tion and shall meet specified performance when operated.

3.4.3 Dust (See 4.8.3) - The unit(s) shall withstand exposure to dust particles as encountered in desert areas with winds up to 17

O knots.

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MIL-A-49079A(CR)

3.4.4 Vibration (See 4.8.4) - The unit(s) normally mounted shall not suffer damage or fail to meet specified performance when subjected to vibration normally encountered in both airplanes and helicopters up to 500 Hz.

3.4.5 Shock (See 4.8.5)

3.4.5.1 Bench Handlinq (See 4.8.5.1) - The non-operating unit(s) shall be capable of withstanding the normal bench handling required during servicing.

3.4.5.2 Basic (See 4.8.5.2) - The unit(s) shall withstand the normal shocks encountered in airplanes and helicopters.

3.4.5.3 Crash Safety (See 4.8.5.3) - The normally mounted units shall show no failures of the attaching points when the unit(s) are subjected to the level of shock encountered in a crash situation.

Bending-and distortion is permitted.

3.4.6 Funqus (See 4.8.6) - The unit(s) shall show no evidence of viable fungus after being subjected to 28 days of fungus exposure.

3.4.7 Salt Fog (See 4.8.7) - The unit (S) shall be capable of withstanding exposure, in normal operating configuration, to salt fog for 48 hours and shall show no evidence of corrosion as evidenced by any visible degradation that can be attributed to flaky, pitted, blistered, or otherwise loosened finish or clogging or binding of moving parts.

3.4.8 Explosive Atmosphere (See 4.8.8) - When operated in an

ambient explosive mixture of gas and air the units shall cause no ignition.

3.4.9 Acceleration (See 4.8.9) - The unit(s) shall be operable without desradation in specified performance, and shall sustain no physical damage, when exposed to steady-state acceleration levels up to 6 g for one (1) minute.

*3.4.10 Rain (See 4.8.10) -

(1) The antenna shall be operable without degradation in speci-fied performance, and shall sustain no physical damage during periods of heavy precipitation with intermittent wind.

(2) The Receiver-Transmitter, Height Indicator RT-1115( )/APN- 209 (V) unit (S) , Receiver-Transmitter RT-1411( )/APN-209A(V) and Indi-cator, Height ID-1917( )/APN-209(V) unit(s) shall withstand a "steady-state" rainfall on all surfaces, meet specified performance, and sus-tain no physical damage.

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*3.4.11 Leakaqe (Immersion) (see 4.8.11) - The Antennas AS-2595/APN-l94(V) and AS-3586/APN-209A(V) shall be capable of immersibn in water without leakage of water into the enclosure. (This re uirement is only for the Antennas and does not apply to any other AN7APN- 209 ( ) (V) equipment).

*3.4.12 Differential Pressure (See 4.8.12) - The Antennas AS-2595/APN-l94(V) and AS-3586/APN-209A(V) shall be capable of with-standing a differential pressure across the radome of at least one atmosphere.

3.5 Numerical Reliability Requirement (See 4.6.2)

3.5.1 AN/APN-209( )(V)l Altimeter Set - The equipment shall have a specified (0,) Mean-Time-Between-Failure (MTBF) of 1000 hours when operating in aggregate under the conditions of 4.6.2.2. This MTBF is allocated to system components as follows:

Receiver-Transmitter, Height Indicator 1,020 hours Antenna 100,000 hours Altimeter Set (0,) 1,000 hours

3.5.2 AN/APN-209 ( ) (V) 2 Altimeter Set - The equipment shall have a specified (0,) Mean-Time-Between-Failure (MTBF) of 800 hours when operating in aggregate under the con'ditions of 4.6.2.2. This MTBF is allocated to system components as follows:

Receiver-Transmitter, Height Indicator Height Indicator

1,020 hours 4,000 hours

Antenna 100,000 hours Altimeter Set (eo) 800 hours

"3.5.3 AN/APN-209( )(V)3 Altimeter Set - The equipment shall have a specified (0 ) Mean-Time-Between-Failure (MTBF) of 2800 hours when operating in aggregate under the conditions of 4.6.2.2. This MTBF is allocated to system components as follows:

Receiver-Transmitter, 2,970 hours Antenna 100,000 hours Altimeter Set (0,) 2,800 hours

3.6 Electromaqnetic Interference (See 4.10) - The emission of electromagnetic interference by the Altimeter Set and the suscep-tibility of the Altimeter Set to electromagnetic interference shall comply with the following requirements of MIL-STD-461 as specified herein.

3.6.1 Power Lead Conducted Emission (30 Hz to 50 KHz) Method

CEO1 - The narrowband conducted interference shall not exceed the limits shown in Figure 4 of MIL-STD-461, Notice 4.

*3.6.2 Siqnal Lead Conducted Emission ( 3 0 Hz to 50 KHz) Method CE03 - The narrowband conducted interference shall not exceed the limits shown on Figure 4 of MIL-STD-461, Notice 4. The test shall be conducted on the signal cable and shall include the following leads separated from their returns:

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(a) Self test confidence signal

(b) Self test input signal

(c) Auxiliary analog range signal

(d) 5 VAC light control

(e) Blanking pulse

3.6.3 Conducted Emission, Power and Signal Leads (50 KHz to 50 MHz) Methods CE04 and CE05 - The broadband conducted interference shall not exceed the limits shown on Figure 5 of MIL-STD-461, Notice 4 except as shown below and the narrowband conducted interference shall not exceed the limits shown on Figure 6 of MIL-STD-461, Notice 4.

MODIFIED CONDUCTED LIMITS - Test CE04 & CE05

Test CE04 Fr eq Max Limit

Test CE05 Fr eq Max Limit

2-3 MHz 59 dB ua 1.5-6 MHz 56 dB ua 3-4 MHz 57 dB ua 6-10 MHz 59 dB ua 4-10 MHz 53 dB ua

*3.6.4 Power Lead Conducted Susceptibility (30 Hz to 50 KHz) Method CSOi - The Altimeter and Indicator shall show no change in indication or performance greater than the specified tolerance when the 28 VDC power lines are subjected to audio signals at a level shown on Figure 8 of MIL-STD-461, Notice 4.

3.6.5 Power Lead Conducted RF Susceptibility (50 KHz to 400 MHz) Method CS02 - The Altimeter and Indicator shall show no change in indication or performance greater than the specified tolerance when the +28 V power line is subjected to RF signals at the level shown in Figure 19 of MIL-STD-461, Notice 4.

3.6.6 Conducted Susceptibility Intermodulation (430 MHz to 10 GHz) Method CS03 - The Altimeter analog range voltage shall not change by more than + ( (3 feet +.O3 X altitude) X (7)) mV when performing the two signal inFermodulation test.

3.6.7 Conducted Susceptibility, Rejection of Undesired Siqnals (3 KHz to 10 GHz) Method CS04 - The Altimeter analog range voltage shall not change by more than + ( ( 3 feet +.O3 X altitude) X (7)) mV when performing the rejection Öf undesired signals test.

3.6.8 Conducted Susceptibility, Power Lead Spike Method CS06 - The Altimeter and Indicator shall show no change in indication or per-formance greater than the specified tolerance when the 28 V power lines are subjected to transients of 56 volts peak magnitude and 10 microseconds duration.

*3.6.9 Radiated mission, Electric Field (14 KHz to 10 GHz)

- Method RE02 and RE02.1 - The broadband and narrowband radiated inter-ference shall not exceed the limits shown in Figures 13 and 14 of MIL- STD-461, Notice 4, except as shown below. Emissions from the Receiver-Transmitter, Height Indicator or the Receiver-Transmitter at the operating frequency are excluded from the requirements of RE02.

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MODIFIED RADIATION EMISSION LIMITS - Test RE02 Broadband - - Narrowband

Fr eq Max Limit Fr eq Max Limit i

100-250 MHz 6&dB uV/M/MHZ 22-28 MHz 31 dB uV/M/MHZ

"3.6.10 Transmitter Spurious and Harmonic Emission Method RE03 - The spurious and harmonic radiated emission from the altimeter trans-mitting antenna shall be 70 dB beiow the level of the transmitter fun-damental radiated emission (dBm/m ) except as listed below:

4.085 - 4.515 GHz No Limit

3.900 - 4.084 GHz -20 dB

4.516 - 4.700 GHz -20 dB

3.300 - 3.899 GHz -40 dB

4.701 - 5.300 GHz -40 dB

1.75 - 2.40 GHz -55 dB

The spurious and harmonic radiated emission from the receiving antenna shall be less than -60 dBm except in the 4.29 GHz to 4.31 GHz frequency range. Emission in the 4.29 GHz to 4.31 GHz frequency range shall be no greater than -17 dBm.

3.6.11 Radiated Susceptibility, Maqnetic Induction Field Spike Method RS02 - The Altimeter and Indicator shall show no change in indi-cation or Derformance qreater than the specified tolerance when 100 volts peak; 10 microsecond, spikes are applied to the radiating wire.

3.6.12 Electric Field Radiated Susceptibility (10 KHz to 12.4 GHz) Method RS03.2 - The Altimeter and Indicator shall show no change in indication or performance greater than the specified tolerance when the test setup is subjected to the electric fields listed below.

Frequency Field Level

10 KHz - 2 MHz 1 V/M 2 MHz - 30 MHz 5 V/M 30 MHz - 200 MHz 10 V/M 200 MHz - 2 GHz 10 V/M 2 GHz - 12.4 GHz 5 V/M

3.7 Electrical Requirements (See 4.9) - Unless otherwise Speci-fied, the equipment shall be capable of meeting the following require-ments.

3.7.1 Altitude Ranqe (See 4.9.2) - The set shall accurately indi-cate absolute altitude from O to maximum range over all types of terrain surfaces, such as trees, foliage, deep snow, ice, land and water. The altimeter shall provide a digital output from O to 1500 feet, and an analog output from O to 1500 feet.

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3.7.2 Ranqe Accuracy

3.7.2.1 Altitude Accuracy-(See 4.9.3.1 and 4.18) - For altitudes up to 1500 feet, the output altitude-sicnal levels, as measured on the digital portion of the indicators and the analog output signals, shall be within +(3 feet t 3% of actual altitude) from the correct terrain clearance altitude.

3.7.2.2 Pointer Accuracy (See 4.9.3.1, 4.9.3.2 and 4.18) - The pointer of the indicators shall be within 5 2 feet or 52% of the ânalog altitude voltage whichever is greater for altitude of 200 feet or less. Above 200 feet the pointer accuracy shall be L 1 0 feet or 2% of the analog altitude voltage whichever is greater.

3.7.2.3 Remote Digital Altitude Display (See 4.9.3.2 and 4.18) - The remote indicator digital display shall be within 4-1 foot of the digital output signal of the IRT or RT for altitudes Eelow 255 feet, above 255 feet the remote digital altitude display shall be within 10 feet of the digital output signal of the IRT or RT.

3.7.2.4 Short Term Drift (See 4.9.21) - The short term drift at any constant temperature within the stated environmental requirements shall not exceed +2 feet within 15 minutes as displayed on the digital portion of the inaicators for altitude range between O and 200 feet.

3.7.3 Frequency (See 4.9.20) - The set shall operate within the allocated frequency range of 4200 to 4400 MHz with a center frequency of 4300 MHz.

3.7.4 Electrical Trackinq Rate (See 4.9.16) - The altitude

signal (Set less Indicator) shall follow changes in height at the rate of at least 1000 feet/second. .

*3.7.5 System Sensitivity (see 4.9.4) - Minimum loop gain (trans-mi& port tooreceive port) shall be 119 dB under standard conditions (O C to +40 C). At temperatures other than standard conditions the minimum loop gain shall be 117 dB. The transmitter peak power shall not exceed t38.5 dBm when measured at the transmitter port.

"3.7.6 Search Rate (See 4.9.17) - While in the search mode the system shall search from zero altitude to maximum at a rate of 4 t 0.5 times per second.

3.7.7 Output Protection (See 4.9.14) - Protection circuitry

shall be included in the system, both receivers and transmitters, to prevent damage due to accidental shott-circuits or open-circuits of the electrical signal outputs (remote' indicator outputs, auxiliary outputs, relay closures, etc.), and the RF signal outputs.

3.7.8 Multiple Indicator Protection (See 4.9.10) - When more

than one indicator is used, isolation shall be provided between indi-cators to prevent a short-circuit to ground or incorrect voltage on one indicator from affecting other indicators.

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3.7.9 Installation Delay Adjustment (See 4.9.19) - The system shall be adjustable externally to allow for an aircraft installation delay from 1 to 70~feet. (Antenna"h-eight above ground and for RF coaxial cable lengths.)

3.7.10 Self,.Test Provisions (See 4.9.5) - A self test shall be incorDorated. This shall be used for inflight and preflight testing o f - th; set and shall designate failure at least down to the Line Replaceable Unit (LRU) level. Self test shall be.activated by depress-ing the control knob on the Indicator and shall be capable of being energized continually with no degradation of performance effects to the set. Whenever self test is activated, the indicator display and electrical signal output shall indicate 1000 5 100 feet. The self test function shall also be capable of being activated remotely by grounding pin 8 of J2 (auxiliary connector). A self test confidence logic output shall be provided by the altimeter at pin 13 of J2 (auxil-iary connector) if the self test acceptance criteria have been met during the self test operation.

3.7.11 Input Electrical Power

*3.7.11.1 Operatinq Power (See 4.19) - Operating power shall be

27.5 VDC at 1.1 amperes maximum for the Receiver-Transmitter, Height Indicator, 27.5 VD? at 0.8 amperes maximum for the Receiver-Transmitter and 27.5 VDC at 0.6 amps maximum for, the Indicator, Height. The equip-ment shall meet the performance as specified herein when energized from a power source having characteristics as defined in MIL-STD-704, Notice 2, for Category B utilization equipment. Steady-state DC vol-tage limits of operation shall be as specified in MIL-STD-704, Notice 2, Table II for normal, abnormal and landing modes of electric system operation. Reduced system performance is acceptable for emergency electrical system operation. If conflicts arise between the require-ments of MIL-STD-704 and MIL-STD-461, Notice 4, the requirements of MIL-STD-461, Notice 4 shall apply.

3.7.11.2 Inteqral Liqhting Power (See 4.9.15) - Input power for integral lighting shall require not more than 0.5 ampere at 5 VAC or VDC per indicator.

3.7.11.3 Dimfling Control Power (See 4.9.15) - Input power for controllins the dimninq of the digital display and warning lamps shall not exceed-6 mA at 27.5 VDC per indicator.

"3.7.11.4 Power On Control (See 4.20) - Each unit shall be turned on when the LO set knob on the indicator is rotated to position the LO warning index at or above zero feet. Additionally, each unit shall switch input power to a separate connector pin for use as a system power on control. The-unit shall be turned on whenever the signal is +25 + 5 VDC even though the power control knob on the indicator is off. The Receiver-Transmitter shall be turned on when 27.5 VDC power is applied to the power input at J1 pin 9 and the signal on the power on control line J2 pin 5 is +25 2 5 VDC.

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3.7.11.5 Transient Spike Voltages (see 4.19.1) - The altimeter shall show no degradation in performance after being subjected to a transient spike voltage of 60OLV¿5¡3s.~n magnitude and 10 microseconds duration; decreasing linear&--f-rczm t 600V to t200V and -6OOV to -170V, in 40 microseconds; decreasing"lfnear1y from t200V to t70 and -170V to t7V in 400 microseconds; and remaini-ng at these levels for 9.5 milliseconds. This spike shall be cycled at least 60 times within one hour.

*3.7.12 Altitude Memory (See 4.9.18) - All "in track" outputs of the Altimeter shall be maintained for 1.8 + 0.5 seconds after loss of return signal before reverting to the seargh (out of track) state.

"3.7.13 Data Laq (See 4.9.22) - Electrical analog data from the Receiver-Transmitter, Height Indicator or the Receiver-Transmitter shall not lag any simulated or actual altitude by more than 0.1 second when tracking at a rate up to 1000 feet per second. This requirement does not pertain to the digital altitude signal inasnuch as the digital data is averaged over a period of 0.44 second.

"3.7.14 Dimminq (See 4.9.8.3) - Dimming of the digital display and warning lamps shall be controlled separately from the dial lighting. The dimming voltage shall be O to 27.5 VDC. The digital display shall be dimmable from full brightness with 27.5 VDC input to full off with 5 VDC or less input. The warning lamps shall be dimmable from full brightness with 27.5 VDC input to a level visible only with night vision devices such as AN/PVS-5. Maximum current required by the dimming circuits shall not exceed 6 milliamperes at

27.5 VDC. An AN/PVS-5 will be furnished as government loaned

property.

3.7.15 Inteqral Liqhtinq (See 4.9.23) -- The indicators shall be red internal lighted in accordance with MIL-L-25467.

*3.7.16 Zero Altitude Power (see 4.9.27) - The IRT or RT shall have a peak output power level of +27 dBm at an altitude of zero feet.

3.8 Electrical Siqnal Output Characteristics

3.8.1 Altitude Outputs (See 4.9.12) - The system shall provide sufficient isolated analoq DC voltaqes proportional to altitude to drive its internal indicator and remote-indicator. This signal shall be O to -10.5 VDC representing O to 1500 feet respectively. During no-track or unreliable operation, this signal shall be -13 - + 2 VDC.

3.8.2 Auxiliary Altitude Outputs (See 4.9.6) - In addition to the outputs specified in 3.8.1, the system shall provide a separate isolated linear DC voltage proportional to altitude,. having a fixed scale factor of -7 millivolts per foot. During search or unreliable conditions this signal shall be +0.75 + 0.5 VDC and shall be capable of driving a 2000 ohms or greater resistive load.

3.8.3 Reliability Siqnal (See 4.9.7) - The system shall provide a 4.5 1.0 VDC reliability signal voltage during track or reliable operation and 0.5 + 0.5 VDC during search or unreliable system opera-tion. This signal-shall be TTL compatible.

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3.8.4 High Altitude and Low Altitude Trip Tests (See 4.9.9) - The LO warning lamp shall be on when the indicated digital altitude is below the LO set index and off when the indicated digital altitude is above the LO set index. When descending between 1500 feet and 200 feet, activation of the LO warning shall occur when the indicated altitude is within +SO, -20 feet, or +5, -2 percent (whichever is greater) of the selected warning altitude. When descending below 200 feet, actuation of the warning shall occur when the indicated altitude is within +5,.-2 feet or +5, -2 percent (whichever is greater) of the selected warning altitude.

D Below 200 feet when ascending, deactivation of the warning shall occur when the indicated digital altitude is within 7 feet or 5 percent, whichever is greater, above the point of activation of the warning.

when the indicated digital altitude is within 70 feet or 5 percent, whichever is greater, above the point of activation of the warning.

- > Above 200 feet when ascending, deactivation of the warning shall occur

The HI warning lamp shall be on when the indicated digital altitude is above the HI set index and off when the indicated digital altitude is below the HI set index. When ascending between O and 200 feet, activation of the warning shall occur when the indicated digital altitude is within +2, -5 feet or +2, -5 percent (whichever is greater) of the selected warning altitude. When ascending above 200 feet, actuation of the warning shall occur when the indicated digital altitude is within +20, -50 feet or +2, -5 percent (whichever is

@ greater) of the selected warning altitude. Below 200 feet, when descending, deactivation of the warning shall occur when the indicated digital altitude is within 7 feet or 5 percent, whichever is greater, below the point of activation of the warning. Above 200 feet when descending, deactivation of the warning shall occur when the indicated digital altitude is within 70 feet or 5 percent, whichever is greater, below the point of activation of the warning.

3.8.4.1 Low Altitude Warninq Siqnal (See 4.9.9) - The low alti-tude warnincr function shall be activated when the actual altitude dis-played is a< or below the pilot adjustable low altitude limit setting.

The output shall be controlled by a transistor switch. The transistor warning. When on the output voltage shall be 1.2 V maximum, when sinking 80 milliamperes. When off, the output shall be an open collector and capable of withstanding 50 VDC.

" shall be on when the warning is activated and off when there is no

3.8.4.2 High Altitude Warninq Siqnal (See 4.9.9) - The high

altitude warninq function shall be activated when the actual altitude displayed is at-or above the pilot adjustable high altitude limit setting. The output shall be controlled by a transistor switch. The transistor shall be on when the warning is activated and off when there is no warning. When on the output voltage shall be 1.2 V maximum, when sinking 80 milliamperes. When off, the output shall be an open collector and capable of withstanding 50 VDC.

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3.8.5 Push-To-Test (PTT) Control (See 4.9.13) - The Height Indi-cator shall provide a ground to initiate system self test. This signal shall be open circuit at all other times.

*3.8.6 Remote Diqital Altitude Siqnal (See 4.9.24) - The Receiver- Transmitter, Height Indicator and Receiver-Transmitter shall provide a digital altitude signal for use in a remote indicator. This signal shall be a series of pulses with each pulse equal to 1 foot of altitude.

Pulses shall be transmitted from a differential line driver in accord-ance with MIL-M-38510/104. The signal shall have the following charac- 'teristics:

(a) Pulse Width: 100 nanoseconds minimum

(b) Rise Time: 50 nanoseconds maximum

(c) Frequency: 150 KHz maximum

(d) Amplitude: 4.5 - + 1.0 volts peak

*3.8.7 Remote Enable Pulse (See 4.9.25) - The Receiver-Transmitter, Heiqht Indicator and Receiver-Transmitter shall Provide an enable pulse during the time that the digital altitude pulses-are being transmitted.

The pulse shall be transmitted from a differential line driver in accordance with MIL-M-38510/104 and shall have the following.character-istics (See 6.7):

(a) Lead Time: 15 microseconds minimum

(b) Lag Time: 75 microseconds maximum

(c) Rise Time: 50 nanoseconds maximum

(d) Width: 0.20 2 0.06 seconds

(e) Frequency : 2.7 + 0.8 Hz

(f) Amplitude: 4.5 - T 1.0 volts

*3.8.8 Blankinq Pulse (See 4.9.26) - The Receiver-Transmitter, Heiqht Indicator and Receiver-Transmitter shall provide a blankinq pulse during the time that the transmitted RF puise from J4 is being transmitted. The blanking pulse shall have the following character-istics:

(a) Width: 2.6 + 0.3 microseconds

(b) Amplitude: 6.0 T 0.75 volts

(c) PRF: 18 +-4, -6 KHz

(d) Source Impedance 15 ohms maximum to +BV

(e) Source Impedance 1050 ohms to ground maximum

(f) Lead Time: 2 . O - + . O . 2 microseconds

On (+6V) :

Off (OV) :

*3.9 Display Functions (See 4.9.8) - The difference between the AN/APN-209A(V) and AN/APN-209B(V) involves the indicator display fea-tures. The AN/APN-209A(V) has red digital displays and amber warning lights. The AN/APN-209B(V) has green digital displays and green infrared filtered warning lamps.. See paragraph 6.1 for specific system configurations. The RT-1411/APN-209A(V) Receiver-Transmitter does not contain display functions.

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*3.9.1 RT-1115( )/APN-209(V) (See 4.9.8.1) - Digital altitude shall be indicated on a four digit lighted readout. Above 255 feet, the digital altitude shall be rounded to the nearest 10 feet. Analog altitude shall be indicated from O to 1500 feet by means of a single pointer against a fixed dial. Movable markers positioned against the same dial shall indicate the pre-selected height above or below which the high and low altitude warnings operate. Unreliable operation shall be indicated by an "OFF" flag coming into view, the pointer shall go behind the masked portion of the Indicator dial and the digital readout and the high and low warning lamps blanked when:

(a) The signal strength to the Receiver-Transmitter, Height Indicator becomes inadequate to provide reliable altitude information (See 3.7.5) or

(b) Aircraft altitude is between 1500 and 2000 feet.

(Unreliable indications shall remain in view at altitudes above 2000 feet.)

3.9.1.1 Power Failure and Power Off Display Functions (See

4.9.11) - The unreliable operation indications of 3.9.1 shall occur when 28 VDC power to the system is lost, except that the pointer need not go behind the masked portion of the indicator dial.

3.9.2 ID-1917( )/APN-209(V) (See 4.9.8.2) - The Height Indicator shall provide remote display of the analog and digital altitude signals generated by the Receiver-Transmitter, Height Indicator or Receiver-Transmitter. The display features shall be identical to those provided by the Receiver-Transmitter, Height Indicator.

3.10 Antennas AS-2595/APN-194 (V) and AS-3586/APN-209A(V)

3.10.1 Antennas AS-2595/APN-l94(V) - The antenna shall be NSN 5841-100-181-0330 and shall be in accordance with SM-D-967316.

*3.10.1.1 Impedance - (For reference only) The nominal antenna impedance shall be 50 ohms.

*3.10.1.2 Beam Width (See 4.17.1.1) - The antenna shall provide a 3 dB, one-way beam width of 45 + 5 degrees in the H plane by 45 + 5 degrees in the E plane.

"3.10.1.3 Antenna Gain (See 4.17.1.2) - The antenna one-way gain shall be not less than 10.5 dB.

*3.10.1.4 V.S.W.R (See 4.17.1.3) - The free space VSWR of the antenna and connector shall be not greater than 1.3 at 4.30 GHz and

1.4 at 4.25 and 4.35 GHz. .

*3.10.1.5 Antenna Isolation (See 4.17.1.4) - The antenna electrical isolation shall be not less than 85 d B at a spacing of two feet, center to center when flush mounted on a ground plane. The isolation test shall be made at 4.30 GHz.

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"3.10.1.6 Antenna Pattern (See 4.17.1.5) - The main lobe shall be in accordance with 3.10.1.2. Pattern shape tests shall be made at

4.30 5 .O05 GHz. The one-way gain 22.5 +-2.5 degrees either side of boresight shall be not less than 7.5 dB.

*3.10.1.7 Time Delay of RF Signal - (For reference only) The variation in delay over all environments shall not exceed 0.1 nanoseconds. The total delay from 4.25 to 4.35 GHz shall not exceed one nanosecond.

3.10.1.8 Siqnal Rejection (See 4.17.1.6) - The signal rejection from the input to antenna output shall be not less than the following:

(a) 25 dB at 8.35 and 8.85 GHz.

(b) 50 dB from 8.50 to 8.70 GHz.

*3.10.1.9 Antenna Finish (See 4.4) - The surface treatment of exposed-aluminum shall be chemical film per MIL-C-5541 or cadmium plate followed by clear irridite or dichiornate and finished with one coat epoxy paint primer and one coat gray epoxy paint, color 36440 per FED-STD-595. Both sides of the mounting flange shall be free of paint, except if radome material encompasses the entire flange area only the opposite side of the flange need be clear of paint. The radome shall be free of paint except for marking in accordance with 3.10.1.10.

*3.10.1.10 Radome Markinq (See 4.17.1.7) - The radome shall be marked "DO NOT PAINT" in 0.5 + 0.1 inch characters, " H PLANE" in 0.25

- t .O5 inch characters and double arrow using gray epoxy paint, color 36440 per FED-STD-595.

*3.10.2 Antenna AS-3586/APN-209A(V) - The antenna shall be in accordance with SM-D-967321.

*3.10.2.1 Impedance - (For reference only) The nominal antenna impedance shall be 50 ohms.

*3.10.2.2 Beamwidth (See 4.17.2.1) - The antenna shall provide a 3 dB, one-way beamwidth of 30 degrees full angle minimum in the H-plane and 30 degrees full angle minimum in the E plane.

"3.10.2.3 Gain (See 4.17.2.2) - The antenna one-way gain shall be 9 dB minimum.

*3.10.2.4 V.S.W.R. (See 4.17.2.3) - The free space VSWR of the antenna shall be 1.8 maximum at 4300 MHz, 2.2 maximum from 4275 to 4325 MHz and 3.0 maximum from 4250 to 4275 MHz and from 4325 to 4350 MHz.

*3.10.2.5 Isolation (See 4.17.2.4) - The antenna electrical isolation shall be 85 dB minimum at a spacing of 2 feet, center to center spacing when flush mounted on a ground plane. The isolation test shall be made at 4.30 GHz.

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*3.10.2.6 Antenna Pattern (See 4.17.2.5) - The main lobe shall be shaped to provide the beamwidth described in 3.10.2.2. The one way gain 15.0 - + 2.5 degrees either side of boresight shall be 6.0 dB minimum. Pattern shape tests shall be conducted at 4.30 2 0.005 GHz.

"3.10.2.7 Time Delay of RF Siqnal - (For reference only) The variation in delay over all environments shall not exceed 0.1 nanoseconds. The total delay from 4.25 to 4.35 GHz shall not exceed five nanoseconds.

*3.10.2.8 &ntenna Finish - The back surface shall be tin plated.

The radome surface shall be unpainted.

3.11 Burn-In/Debuqginq and Preconditioning (See 4.6.1)

3.11.1 Burn-In/Debuqqing (See 4.6.1.1) - Each unit on order

shall meet the requirements herein after subjection to the Burn-in/Debugging as specified in 4.6.1.1. Antennas are excluded from the burn-in requirement.

*3.11.2 Pre-Conditioning (See 4.6.1.2) - Prior to Burn-In/Debug-ging, the Receiver-Transmitter, Height Indicator and Receiver-Transmitter shall be subjected to the preconditioning specified in 4.6.1.2.

3.12 Interchanqeability (See 4.12) - Like units, assemblies, subassemblies and replaceable parts shall conform to requirement 7 of military standard MIL-STD-454 and shall be physically and functionally interchangeable. Items which are covered by specified electrical per-formance requirements shall meet such specified performance requirements prior to installation into the unit(s) . After installation of these items and prior to submission of unit(s) for the quality performance specifications, adjustments shall be made, if required, to permit the unit(s) to meet full equipment specification requirements. Alterations of any items, or the unit(s) shall not be permitted.

3.13 Operational Inspection (See 4.13) - Immediately prior to packaging and after applicable processes, inspections and tests are completed, each unit(s) shall be subjected to the operational inspec-tion as specified.

3.14 Markinq (See 4.4) _ - Markings shall be in accordance with MIL-Y-13231 except that the nameplates shall be in accordance with Figure 1 of MIL-k"15024/6.

3.15 Workmanship (See 4.11) - The equipment shall be

manufactured and assembled in accordance with the equipment drawings (see 3.3) and the following requirements:

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MIL-STD-454

Soldering Requirement 5 Workmanship Requirement 9

4. QUALITY ASSURANCE PROVISIONS

4.1 Responsibility For Inspection - Unless otherwise specified in the contract, the contractor is responsible for the performance of all1 inspection requirements as specified herein. Except as otherwise specified in the contract, the contractor may use his own or any other facilities suitable for the performance of the inspection requirements specified herein, unless disapproved by the Government, The Government reserves the right to perform any of the inspections set forth in the specification where such inspections are deemed necessary to assure that supplies and services conform to prescribed requirements.

4.2 Classification of Inspection - Inspection shall be

classified as follows:

(a) First article inspection (does not include packaging,). (see 4.3.)

(b) Inspection covered by subsidiary documents. (See 4.4.)

(c) Quality conformance inspection of equipment before packaging. (See 4.5. )

(a) Quality conformance inspection of packaging. (See 4.15.)

4.3 First Article - Unless otherwise specified in the contract, the first article inspection shall be performed by the contractor.

(See 3.2)

4.3.2 First Article Inspection - The first article inspection shall consist of the inspections specified in subsidtary documents covering the items listed in 4.4, Burn-In, and the inspections speci-fied for Group A , Group B, Group C and Group D (See Table I, II, III and IV respectively). The inspection shall be performed in the following order: 4.4, Burn-In, Gr0up.A and Group B for all units, Group D, and designated units for specific subgroups within Group C in accordance with 4.5.3.1. After completion of Group C and Group D inspection, conforming units shall be re-inspected and shall pass all Group A inspection. The Group D inspection may be conducted concurrently with Group C inspections.

4.3.3 First Article Data - First article test plan and test

report(s) shall be as required in the contract.

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4.4 Inspection Covered By Subsi'diary Documents - The following shall be inspected under the applicable subsidiary documents, as part of the inspection before preparation for delivery:

Inspections Reqt Para

Parts, Materials and Processes 3.3.1 Protective Finish 3.3.4 Antenna 3.10.1.9, 3.10.2.8 Marking 3.14

4.5 Quality Conformance Inspection of Equipment Before

Packaging - Following the reliability screening each unit shall be subjected to Burn-In/Debugging (see 3.11.1) prior to conformance inspection. The contractor shall perform the inspection specified in

4.4 and 4.5.1 through 4.5.4. This does not relieve the contractor of his responsibility for performing any additional inspection which is necessary to control the quality of the product and to assure compliance with all specification requirements. Failure to meet any requirement after Burn-In/Debugging shall be classified as a defect and recorded as such. The Government will review and evaluate the contractor's inspection procedures and examine the contractor's inspection records. In addition, the Government at its discretion, may perform all or any part of the specified inspection, to verify the contractor's compliance with specified requirements. Test equipment for Government verification inspection shall be made available by the contractor at the contractor's facility.

4.5.1 Group A Inspection - Each unit on contract shall be

inspected for conformance to the inspections specified in Table I.

Discrete lots shall be formed on all-units that pass this inspection.

Factors of lot composition not defined herein, or in the contract, shall be in accordance with MIL-STD-105. Each lot shall be subject to sampling inspection, utilizing the procedures of MIL-STD-105; using the general inspection levels and AQL's indicated in Table I.

4.5.1.1 Order of Inspection Within Group A - Group A inspection shall be performed in an order satisfactory to the Government except that Operational shall be last and performed immediately prior to packaging.

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MIL-A-47077A 5 8 m 7777906 0 3 5 8 6 5 5 T W

*TABLE I - Group A Inspection

INSPECTION

Visual and Mechanical

Modules :

Assemblies:

RT-1115 ( ) /APN-209 (V)

and RT-1411/APN-209A(V less case .

and RT-1411/APN-209A(V assembled less case assembled and AS-3586/APN-209A(V assembled

RT-1115 ( ) /APN-209 (V)

ID-1917 ( ) /APN-209 (V)

ID-1917 ( ) /APN-209 (V)

AS-2595/APN-194 (V)

Electrical

RT-1115 ( ) /APN-209 (V)

and RT-1411/APN-209A(V):

Altitude range*** Altitude accuracy System sensitivity Self test

Auxiliary alt output Reliability signal Display, function*** Operational inspection

ID-1917 ( ) /APN-209 (V) :

Display, function Self test Altitude range Altitude accuracy Operational inspection

REQT.

PARA.

3.15,3.3 3.3.3 3.10.1.10

3.7.1 3.7.2.1 3.7.5 3.7.10

3.8.2 3.8.3 3.9.1 3.13

3.9.2 3.7.10 3.7.1 3.7.2 3.13

INSP.

PARA.

4.11, 4.17.1.7

4.9.2.1 4.9.3.1 4.9.4 4.9.5.1, 4.9.5.3 4.9.6 4.9.7 4.9.8.1 4.13

4.9.8.2 4.9.5.2 4.9.2.2 4.9.3.2 4.13

O. 65%

0.65%

O. 65%

1.0%

O. 65%

1.0%

1.0%

1.0%

Combined

1.0% Combined

AQL

MAJOR MINO1

2.5%

2.5%

2.5%

4.0%

2.5%

4.0%

4.0%

O

O

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MIL-A-47079A 5 8 m 7777906 0 3 5 8 6 5 6 L

*TABLE I - Group A Inspection (Continued)

REQT. AQL INSP.

INSPECTION MINO? MAJOR , PARA. PARA.

AS-2595/APN-194 (V) and

AS-3586/APN-209A(V):

VSWR Test (AS-2595)

4.13 3.13 Operational inspection

1.0% 4.17.1.3 3.10.1.4

(AS-3586) 4.17.2.3 3.10.2.4

**All electrical defects are considered major.

***Not applicable to the RT-1411/APN-209A(V).

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4.5.2 Group B Inspection - Group B inspection shall normally be performed on inspection lots that have passed Group A inspection and O on samples selected from units that have been subjected to and met the Group A inspection. This inspection shall conform to Table II and to the special inspection levels of Table I of MIL-STD-105.

4.5.2.1 Group B Samplinq Plans - The Group B AQL shall be 6.5% and the inspection level shall be S 4 .

4.5.2.2 OKder of Inspection Within Group B - Group B inspection sial1 be performed in any order which is satisfactory to the Govern-ment.

4.5.3 Group C Inspection - This inspection shall be as listed in Table III…