Task Card En Blanco.docx

Date: Rev: STABILATOR - REMOVAL / INSTALLATION / RIGGING Task Number: TASK CARD OT Number: Service Frequency: Page: Make: Model: Type of Manual: Service Manual S/N:____________________ P/N: ______________________ GAMA: Last Revision: Nationality: Registration: Year: Station: Manual Efectivity/Code: Owner: Manpower:

Name, Signature, Date of Work License Number

PROCEDURES

STANDARD

REMOVAL OF STABILATOR CONTROL CABLES. (Refer to Figure 5-6.)

To remove either the forward or aft stabilator cables, first remove the access panel to the aft section of the fuselage located in the baggage compartment, the two front seats, and the baggage area floor panel on the PA-28-140 airplanes or the bottom of the rear seat on the PA-28-150, 160, -180; PA28-235 and PA-28R airplanes. Disconnect the desired control cable at the turnbuckle in the aft section of the fuselage.

Technician

Encountered Condition

Inspector Name, Signature, License Number

Either forward stabilator cable (2 or 3) may be removed by the following procedure: PA-28-235: Remove the fuel selector and rudder trim covers by removing the knobs and the attaching screws. Disconnect the fuel indicator control lever from the fuel selector torque tube by removing the attaching pin located at the bottom of the lever. Remove the tunnel plate located just aft of the tee bar by laying back enough tunnel carpet to remove the plate attaching screws.

If the right (upper) stabilator control cable (2) is to be removed, remove the cotter pin guards at the pulley(2) located in the forward area of the tunnel. Disconnect the cables (2 and 3) from the lower end of the tee bar on PA-28-140; PA28-150, 160, -180 and PA-28-235 or from the idler arm on the PA-28R by removing cotter pin, nut, washer and bolt (15). Within the access opening aft of the main spar, remove the cable rub blocks that are attached to the spar housing by removing the block attaching screws. Remove the cotter pin cable guard at the pulley cluster located in the aft area the access opening aft of the main spar. NOTE: To facilitate in the installation of control cables, a line may be attached to the cable end prior to removal. Draw the cable aft through the floor tunnel.

Either aft stabilator control cable (4 or 5) may be removed by the following procedure: 1. Disconnect the cable end at the balance arm (18) of the stabilator by removing the cotter pin, nut, washer and bolt (8). 2. Remove the cotter pin cable guard at the pulley (7) located either above or below the balance arm. 3. Remove the cable from the airplane. The forward stabilator cables (2 and 3) may be installed by the following procedure:

Draw the control cable through the floor tunnel. Ascertain that the right (upper) cable (2) is routed around the pulley(s) (14) in the forward area of the floor tunnel.

Connect the cables (2 and 3) to the lower end of the control column tee bar (1) or the idler arm with bolt, washer, nut and cotter pin (15). Allow the cable ends freedom to rotate.

If the aft control cable (4 or 5) is not installed, install per step b.

Connect the control cable to the aft cable at the turnbuckle (16) in the aft section of the fuselage. For the right control cable (2), install the cotter pin cable guards at the pulley(s) (14) in the forward area of the tunnel.

Within the access opening aft of the main spar, install the cable rub blocks (10) to the spar housing and secure with screws. In the access opening, install the cotter pin cable guard at the pulley cluster (6).

Set cable tension and check rigging and adjustment per paragraph 5-17.

Install the floor tunnel plate and trim covers by the following procedure: PA-28-235: Install the floor tunnel plate and secure with the attachment screws. Fasten the tunnel carpet into place and install the fuel selector lever on the selector torque tube and secure with a clevis pin and cotter pin. Replace the fuel selector and rudder trim covers and the rudder trim knob.

Install the front seats and rear seat bottom on floor panel.

Either aft stabilator control cable (4 or 5) may be installed by the following procedure:

Route the cable (4 or 5) around its pulley (7) located either over or under the balance arm (18) of the stabilator. Connect the cable to the stabilator balance arm and secure with bolt, washer, nut and cotter pin (8). (Ensure bushing is installed with bolt.)

Connect the cable to the forward cable at the turnbuckle (16) in the aft section of the fuselage. The upper aft cable (5) connects to the right forward cable (2) and the lower cable (4) to the left cable (3). Install the cotter pin cable guard at the pulley (7), where required.

Set cable tension and check rigging and adjustment per paragraph 5-17.

Install the seats and access panels. 5-17. RIGGING AND ADJUSTMENT OF STABILATOR CONTROLS. CAUTION: VERIFY FREE AND CORRECT MOVEMENT OF STABILATOR. WHILE IT WOULD SEEM SELF-EVIDENT, FIELD EXPERIENCE HAS SHOWN THAT THIS CHECK IS FREQUENTLY MISINTERPRETED OR NOT PERFORMED AT ALL. ACCORDINGLY, UPON COMPLETION OF STABILATOR RIGGING AND ADJUSTMENT, VERIFY THAT THE REAR EDGE OF THE STABILATOR MOVES UP WHEN THE WHEEL IS PULLED BACK; AND, THAT THE REAR EDGE OF THE STABILATOR MOVES DOWN WHEN THE WHEEL IS PUSHED FORWARD.

a. Level the airplane. (Refer to Leveling, Section II.) b. To check and set the correct degree of stabilator travel, the following procedure may be used: 1. Check the stabilator travel by placing a rigging tool on the upper surface of the stabilator as shown in Figure 5-7. (This tool may be fabricated from dimensions given in Figure 5-7.)

2. Set on a bubble protractor the number of degree up travel as given in Table V-II and place it on the rigging tool. Raise the trailing edge of the stabilator and determine that when the stabilator contacts its stops, the bubble of the protractor is centered. NOTE: The stabilator should contact both of its stops before the control wheel contacts its stops. The neutral position of the stabilator is with the stabilator chord line parallel with the top of the front seat tracks. 3. Set on the protractor the number of degrees down travel as given in Table VII and again place it on the rigging tool. Lower the trailing edge of the stabilator and determine that when it contacts its stops, the bubble of the pro-tractor is centered. 4. Should the stabilator travel be incorrect in either the up or down position, remove the tail cone fairing by removing the attaching screws and with the use of the rigging tool and bubble protractor turn the stops located at each stabilator hinge in or out (Refer to Figure 5-14) to obtain the correct degree of travel 5. Ascertain that the lock nuts of the stop screws are secure and reinstall the tail cone fairing. c. To check and set stabilator control cable tension, the following procedure may be used: 1. Ascertain that the stabilator travel is correct. 2. Remove the access panel to the aft section of the 3. Secure the control column in the near forward position. Allow one-quarter inch between the column and the stop bumper

4. Check each control cable for the correct tension as given in Table V-II. 5. Should tension be incorrect, loosen the turnbuckle of the lower cable in the aft section of the fuselage and adjust the turnbuckle of the upper cable to obtain correct tension. Cable tension should be obtained with the control wheel at the one-quarter inch dimension from the stop and the stabilator contacting its stop. 6. Check safety of all turnbuckles and bolts. 7. With the tension of the upper, cable correct and the control wheel still forward, adjust the turnbuckle of the lower cable to obtain correct tension. 8. Check the full travel of the control wheel with relation to the full travel of the stabilator to determine that the stabilator contacts its stops before the control wheel contacts its stops. With the control wheel in the fore and aft positions, the travel distance from the point where the stabilator contacts its stops and the control wheel contacts its stops should be approximately equal. Readjust turnbuckles if incorrect. 9. Reinstall access panels.