AC 91-16 Attachment 1 8/7/67 Page 35 (and 36) Section VI
TECHNICIAN-CONDUCTED INSPECTIONS
AC 91-16 Attachment 1 8/7/67 Page 37
GLIDE SLOPE RECEIVER SYSTEM INSPECTION AJAX MODEL 22-G The following inspection will be conducted on both glide slope receiving systems at the intervals specified in the "Schedule of Inspection and Bench Checks" contained in this manual. The inspection will be accomplished by a qualified certificated mechanic or a repair station, using ramp test equipment which will perform the tests listed in Paragraphs 1, 2 and 3. The flight director system must be turned on and set to GS MAN while performing these tests, because glide slope information is displayed on the flight director course indicator.
Following the test equipment manufacturer's instructions, perform the following sequence of tests:
1. Position the ramp test equipment at the proper distance from the airplane and radiate a standard glide slope test signal on the desired frequency of a sufficient strength to move the glide slope indicator flag alarm to the "out of sight" position.
2. Test for correct glide slope indicator deflection, full scale up and down and centering.
3. Test for correct flag alarm sensing and deflection and confirm that the alarm indicator is displayed during loss of either the 90 or 150 cps modulation, or reduction of both signals to one-half the normal 40 percent.
If possible, determine if any noise or interference is present which would cause erratic indications by running the engine(s) to check for ignition, electrical motor, or generator noise, and channel other receivers and transmitters to determinethat interaction is not taking place.
5. Make a thorough visual inspection of both receiving installations for physical security, electrical cable connections, condition of antenna,
6. Enter the date, name of the agency or person conducting the inspection, indicate satisfactory or unsatisfactory performance in the maintenance record of the glide slope receivers.
The above inspection will also be made after the repair or replacement of any component of the glide slope receiving systems.
Attachment 1 AC 91-16 Page 38 8/7/67
LOCALIZER RECEIVER SYSTEM INSPECTION AJAX MODEL 16L The following inspection will be conducted on both localizer receiving systems at the intervals specified in the Schedule of Inspection and Bench Checks contained in this manual. The inspection will be accomplished by a qualified certificated mechanic or a repair station, using ramp test equipment which will perform the tests listed in paragraphs 1, 2 and 3. The flight director system must be turned on and set to GS MAN while performing these tests, because localizer deflection is displayed on the flight director course indicator.
Following the test equipment manufacturer's instructions, perform the following sequence of tests:
l. Position the ramp test equipment in the proper location from the airplane and radiate a standard localizer test signal on the desired frequency of a sufficient strength to move the localizer flag alarm to the "out of sight" position.
2. Test for correct localizer indicator deflection, full scale to left and right and centering.
3. Test for correct flag alarm sensing and deflection and confirm that the alarm indicator is displayed during loss of either the 90 or 150 cps modulation, or reduction of both signals to one-half the normal 20 percent.
4. Channel the receiver to all navigational facilities which may be received at the test location, and confirm that the selector dial indicates the correct frequency.
5. Test the receiver audio outputs for satisfactory level, proper rotation and absence of noise in level control and selector switches when operated.
6. If possible, determine if any noise or interference is present by running the engine(s) to check for ignition, electrical motors, or generator noise, and channel other receivers and transmitters to determine that interaction is not taking place.
7. Make a thorough visual inspection of both receiving installations for physical security, electrical cable connections, condition of antenna, etc.
Enter the date, name of the agency or person conducting the inspection, indicate satisfactory or unsatisfactory performance in the maintenance record of the localizer receivers.
The above inspection will also be made after the repair or replacement of any component of the localizer receiving systems.
AC 91-16 Attachment 1 8/7/67 Page 39
MARKER BEACON RECEIVER SYSTEM INSPECTION VOLE MODEL AV-21 The following inspection will be conducted on the marker beacon receiving system at the intervals specified in the Schedule or Inspection and Bench Checks" contained in this manual. The inspection will be performed by a qualified certificated mechanic or a repair station, using ramp test equipment which will perform the tests listed in paragraphs 1, 2 and 3.
Following the test equipment manufacturer's instructions:
1. Position the ramp test equipment directly beneath the marker beacon antenna and set the test generator for 20,000 microvolts output with 90 percent modulation at 3000 cps.
2. Turn on the airplane marker receiver and set the 'High-Low" switch for "High" (maximum) sensitivity and determine that a 3000 cps tone is clearly audible in the airplane speaker and headset. The inner marker (white) incicator light should be brightly lighted at this time.
3. Repeat the above procedure using the 1300 and 400 cps tones, and make the same determinations. The amber indicator light (middle marker) should be brightly lighted when 1300 cps is applied, and the blue indicator light (outer marker) should be lighted when 400 cps is applied.
4. Repeat steps 2 and 3 with the "High-Low" switch in the "Low" position and determine at least that each audio tone is audible.
5. Make a thorough visual inspection of the receiving installations for physical security, electrical cable connections, condition of antenna,
6. Enter the date, name of the agency or person conducting the inspection, indicate satisfactory or unsatisfactory performance, in the maintenance record of the marker receiver.
The above inspection will also be made after the repair or replacement of any component of the marker receiving systems.
Attachment 1* AC 91-16 Page 40 8/7/67
FLIGHT DIRECTOR INSPECTION GAINS MODEL 263-B The following inspection will be performed on the flight director system at the intervals specified in the "Schedule of Inspection and Bench Checks" contained in this manual. The inspection will be performed by a qualified certificated mechanic or a repair station, using ramp test equipment to radiate the necessary test signals. Although not required in the Category 1l maintenance program, the VOR functions of the flight director system will also be tested, following the sequence of tests below.
Ramp test equipment capable of radiating standard VOR/ILS test signals, and marker beacon test signals will be used to perform the tests.
1. Preparation
a. Determine that all power to the flight director system is OFF.
b. Determine that the flight director control MODE SELECTOR switch is in the OFF position.
c. Connect external power supply to aircraft and apply power.
2. Functional Test
a. Turn on power to all units of the flight director system.
b. Allow five minutes for equipment warmup, and then check erection of the vertical gyro. When the gyro is erected, the horizon bar will be centered, provided the airplane is level, and the GYRO flag will be retracted.
Determine that the gyro-stabilized magnetic compass is slaved by observing the azimuth card on the Course Indicator for correct airplane magnetic heading. Determine that the COMPASS, COMPUTER and GIRO flag alarms, and V-bar command indicator are in the "out of sight" position.
d. Turn on VOR/LOC and glide slope receivers and tune the VOR receiver to the VOR test signal frequency.
e. Turn the flight director control MODE SELECTOR to SC (speed control) position and determine that the V-bar command indicator comes into view and that SC appears in the right annunciator window of the flight director indicator.
Turn the MODE SELECTOR control to HDG position. The GYRO COMPUTER and COMPASS warning flags should remain "out of sight." The course indicator azimuth card should indicate the airplane magnetic head- The annunciator windows should be blank.
AC 91-16 Attachment 1 8/7/67 Page 41
g. If the heading marker has been left set in another position, turn the HDG knob on the course indicator until the heading marker is under the lubber line. The V-bar should center (wings level).
h. Rotate the PITCH COMMAND (on control unit) control knob clockwise, and determine that the V-bar command indicator in the flight indicator moves upward. The V-bar should move downward for a counterclockwise rotation. Return PITCH COMMAND control knob to zero (V-bar aligned with airplane symbol).
i. Vary the heading marker 10 degrees both sides of the lubber line.
The V-bar should call for a bank toward the new headings. Return the heading marker to the lubber line. The V-bar should center (wings level).
j. Turn the ALTITUDE HOLD toggle switch (on control unit) ON. Rotate the PITCH COMMAND control throughout its range and determine that the V-bar does not move, and that ALI appears in the left annunciator window of the director indicator. Turn ALTITUDE HOLD to OFF.
k. Rotate the COURSE knob on the course indicator until the course arrow is 15 degrees to either side of the course to the test signal, and set the MODE SELECTOR to VOR/LOC. Determine that HDG/VL appears in the right annunciator window of the director indicator, and the V-bar follows the heading marker for bank commands. The VOR/LOC flag alarm should be "out of sight."
1. Rotate the COURSE knob until the course arrow is on the inbound course to the test signal. The lateral deviation bar should center and the TO-FROM arrow should point to the head of the course arrow. When the system has captured the course, the right annunciator window should be blank.
m. Move the course arrow ten degrees both sides of the inbound course to the test signal. The V-bar should call for banks toward the new courses, and center (wings level) when the new courses are reached.
n. Tune the pilot's navigation receivers (one at a time) to the test set localizer signal frequency and set the MODE SELECTOR to GS MAN. GS should appear in the left annunciator window. Set course arrow to the inbound localizer course. The lateral deviation bar should show the localizer path in relation to the miniature airplane symbol.
The ALTITUDE HOLD switch should return to OFF. The glide slope scale and pointer should become visible, and the localizer deviation display should become visible and operate.
o. Press the SC switch on the pilot's wheel. Determine that the MODE SELECTOR returns to SC mode and that SC appears in the right annunciator window. Detcrmine that the V-bar calls for sufficient pitchup indication to effect a safe go-around.
Attachment 1' AC 91-16 Page 42 8/7/67 P. After approximately three seconds, set the MODE SELECIOR to GS MAN.
The V-bar should be centered until the system again captures the localizer and glide slope course.
q. Turn the MODE SELECTOR to GS AUTO and determine that GS remains displayed in the left annunciator but that the right annunciator remains blank. Turn the marker test set on and set it to radiate a standard marker test signal with 1300 cps modulation. When the amber (middle) marker lamp (in the cockpit) is lighted, EXI should appear in the right annunciator window.
Press the SC switch on the pilot's control wheel. The MODE SELECTOR should revert to SC mode and SC should appear in the right annunciator window. The V-bar should call for fly-up.
During the above tests determine that the second in command's course indicator and flight director indicator display the same annunciator signals, alarm action, position and command signals as the pilot's display.
Upon completion of the tests, turn MODE SELECTOR to OFF, radio and power switches OFF, and disconnect external power supply to the airplane.
Make a thorough visual inspection of the flight director system for physical security of mounting in racks and instrument panel, electrical cable connection security, condition of dust covers and cases, inoperative instrument lights, etc.
Enter the date, name of the agency or person conducting the check, indicate satisfactory or unsatisfactory performance in the maintenance record of the flight director system.
The above check will also be made after the repair or replacement of any component of the flight director system.
AC 91-16 Attachment l 8/7/67 Page 43 (and 44) Section VII
PILOT-CONDUCTED FUNCTIONAL FLIGHT CHECKS
AC 91-16 Attachment 1 8/7/67 Page 45 Section VII PILOT-CONDUCTED FLIGHT CHECK FOR LOCALIZER, GLIDE SLOPE, AND MARKER RECEIVERS:
AND, BAROMETRIC AND RADIO ALTIMETER PERFORMANCE TESTS This functional flight check will be made to check the operation of the localizer, glide slope, and marker receiving systems; and, the barometric and radio altimeter systems. It must be performed by a pilot holding Category II pilot authorization for the type airplane in which the instruments and equipment are installed. To minimize potential traffic conflict, pilots should contact the controlling air traffic control (ATC) facility, describe the planned maneuver, and obtain clearance to conduct the flight check. To eliminate radio frequency congestion, whenever possible such coordination should be effected in person or by telephone prior to the flight.
1. The flight check will be conducted in two stages designated as Stage 1 and Stage 2. Stage 1 will consist of a check of the proper sensing and indication of the radio and electronic instrumentation systems. Stage 2 will consist of a check during a simulated Category II ILS approach and landing (or go-around).
Either Category I or Category Il ground facilities may be used, providing that there are no outstanding NOTAMs restricting the use of the facility.
The sequence of checks is optional. However, the sequence outlined below is intended to accomplish all required tests with minimum flight time.
For convenience, see plan view, sketch attached.
2. Stage l - Flag alarm and deviation sensitivity check; first, of the localizer receiving systems on all headings; and, then of the glide slope receiving systems by intercepting the localizer inbound heading at an angle.
a. With the airplane at least 15 miles from the ground facility, and at an altitude of 2000 feet above the terrain and positioned so that the localizer deviation indicator reads full scale deflection from the front course line of the localizer ground station, fly the airplane in the appropriate right-hand or left-hand 360 degree circle to cross the localizer center line, holding a ten degree bank in the turn. Under all of these conditions, the flag alarm indicator should be out of sight at all times. The localizer deviation indicator should move from full scale deflection to on-course to full scale opposite deflection. Be sure to observe that the indicator moves in the proper direction.
Determine the altitude at which the glide slope intercepts the outer marker. While flying at that altitude, establish an inbound course to pass through the localizer course in the vicinity of the outer marker at approximately a 45 degree angle to the localizer centerline.
The fly-through of the localizer course should begin at a point far enough beyond the outer marker to give full scale fly-up deflection of the glide slope indicator. Determine that:
Attachment 1 AC 91-16 Page 46 8/7/67
(1) Normal glide slope indicator action is from full fly-up to full fly-down while passing through the glide slope path.
(2) The glide slope alarm indicator is out of sight at all times.
Stage 2 - Use a current ILS approach chart for the facility on which the check is to be conducted. Set the airplane altimeter barometric scale to the current altimeter setting for that facility.
Conduct a simulated Category ll 1LS approach and observe the following:
a. All warning systems indicate normal operating conditions.
b. Upon intercepting the glide slope at the outer marker, note that the barometric altimeters indicate proper altitude.
Test the radio altimeter for proper operation and required indications using the self-test feature of the equipment. The self-test feature of this equipment is shop adjusted to indicate a simulated 100 foot altitude when the self-test function is activated.
d. Observe proper altitude indication at the middle marker.
e. Observe proper altitude indication at the decision altitude.
f. No unusual roughness or excessive attitude changes occur after leaving the outer marker.
g. Observe that the correct marker receiver indications are received while passing over the outer marker, middle marker, and inner marker (if installed at the facility). Observe that the marker indicator light colors are received in the following sequence:
Marker Beacon Light Color Outer Blue Middle Amber Inner White Upon completion of the flight check, make an entry in the inspection record for the localizer receivers, glide slope receivers, marker receiver, radio altimeter, and barometric altimeters showing the date, name of pilot, whether periormance was satistactory or unsatistactory, and indicate that it was a pilot-conducted flight check.
PLAN VIEW OF LOCALIZER AND GLIDE 8/7/67 AC 91-16 SLOPE PERFORMANCE TESTS;
STAGES la and 1b.
LOCALIZER DECREES PLUS 45 OM
LEFT OR RIGHT - TOCALIZER BRONT COURSE CA--- 360 deg.
LOCALIZER COURSE MINUS 45 DEGREES.
15 MILE AREA FOR LOCALIZER Page 47 (and 48) Attachment 1
CIRCLING CHECK,
AC 91-16 Attachment 1 8/7/67 Page 49 (and 50) Section VIII