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SERVICE BULLETIN
N° SB 398 – CS – Ed 2 Rev 1 Date: 05 08 2020 The technical content of this document is approved under the authority of DOA ref. EASA.21J.335 Approval No: DO-398-200805 Rev.1 Date, 17/08/2020 Page 1 / 6
MOD. PD-006-03 rev.2 data: 18/11/13
SERVICE BULLETIN Edition 2 Rev.1 MANDATORY by the AD No. yyyy-xxxx May become MANDATORY after EASA evaluation RECOMMENDED …………………………. INFORMATION …………………………………………
SUBJECT: P2012 Trim tab inspection.
SCOPE: This service bulletin has the purpose to provide additional criteria and details concerning the P2012 trim tab inspection applicable each “B” level inspection according to P2012 AMM. These additional criteria will be embodied as standard in the next issue of AMM.
Following the experience gained on some P2012 occurrences, Tecnam mandate s to inspect the trim tab surface and related control system according to instruction reported in the Appendix A.
APPLICABILITY: TECNAM P2 012 Traveller SNs which not embodying MOD2012/128 “AMM ed2rev2”
TIME OF COMPLIANCE: each “B” level inspection according to P2012 AMM.
MANPOWER: 1 man-hours for step 1 2 man-hour for step 2
REQUIRED MATERIAL: Nil.
TOOLING: Nil.
WEIGHT AND BALANCE: Nil.
REFERENCES: P2012 Traveller AMM - last issue;
PUB. AFFECTED: P2012 Traveller AMM
For further information, please contact TECNAM:
P2012 Traveller Technical Support:
o Email: traveller.support@tecnam.com o Tel: 0039 0823 997538
SERVICE BULLETIN
N° SB 398 – CS – Ed 2 Rev 1 Date: 05 08 2020 The technical content of this document is approved under the authority of DOA ref. EASA.21J.335 Approval No: DO-398-200805 Rev.1 Date, 17/08/2020 Page 2 / 6
MOD. PD-006-03 rev.2 data: 18/11/13
SERVICE BULLETIN Edition 2 Rev.1
APPENDIX A
Accomplishment Instructions
1. Aircraft preparation
1. Park the aircraft in a closed hangar;
2. Master Switch: OFF;
3. Starter relay breaker: OFF;
4. Parking brake: ON;
5. Lock wheels;
6. Apply following instructions;
NOTE: the following instructions aim to measure the amount of free play on the elevator trim tab control system and it is divided in two steps:
STEP 1 – this step i ndicates how to measure the trim tab surface free play, if any. The measurement performed with this step takes into account the sum of all free plays existing into the trim tab control line, starting from the tab mechanical actuator, connecting rod to the first lever, control rod to the trim surface, and trim tab surface as well.
The instructions below show a plunger dial with angular pointer as tool used to perform measurements. Different tool can be used, but it is required that the measuring tool is a pl unger dial (with axial or angular travel plunger).
STEP 2 - in case the tab surface free play measured lies within prescribed tolerances, the inspection can be concluded and the aircraft returned to service. If instead the free play measured on the tab trailing edge is outside the prescribed tolerances, it is likely that mechanical actuat or has free play on it and the STEP 2 prescribes how to perform the actuator free play inspection and measurement, without need to remove it from the aircraft. Also in this case, the instructions show a plunger dial with angular pointer as tool used to per form measurements. Different tool can be used, but it is required that the measuring tool is a plunger dial (axial or angular travel plunger).
SERVICE BULLETIN
N° SB 398 – CS – Ed 2 Rev 1 Date: 05 08 2020 The technical content of this document is approved under the authority of DOA ref. EASA.21J.335 Approval No: DO-398-200805 Rev.1 Date, 17/08/2020 Page 3 / 6
MOD. PD-006-03 rev.2 data: 18/11/13
SERVICE BULLETIN Edition 2 Rev.1
2. STEP 1 – Trim Tab surface free play measurement
1. With the entire trim tab control line connected, use the tool 212-10-30-0001-1 “trim tab neutral template” in order to verify the trim tab lies in any position between “MIN” and “MAX”. This allows to measure free plays always in similar conditions. If the tool is not available, measurement can be done as per the following picture.
2. According with the plunger dial available, locate the best position for the plunger dial base. The support must be on the elevator skin to be sure that the free play measured is just the one coming from the tab. The following picture shows a suitable position of plunger dial base.
NOTE: the plunger dial in the picture is an angular one, this is why its body is not perpendicular to the tab skin.
NOTE: the plunger dial should touch the tab skin onto the trailing edge angle flat s urface. The continuous line represents where the bend radius starts. The distance between continuous and dotted lines (where the dial plunger should fall) is 6.35mm (1/4in);
SERVICE BULLETIN
N° SB 398 – CS – Ed 2 Rev 1 Date: 05 08 2020 The technical content of this document is approved under the authority of DOA ref. EASA.21J.335 Approval No: DO-398-200805 Rev.1 Date, 17/08/2020 Page 4 / 6
MOD. PD-006-03 rev.2 data: 18/11/13
SERVICE BULLETIN Edition 2 Rev.1
3. Record both upwards and downwards values on dial, repeat the measurement three times to be sure the record is correct, and fill out the following table, to be recorded into the Aircraft Logbook:
Tail Number S/N A B Total Free play
NOTE: the tab free play, when present, is clearly felt by hands before measurement. If the free play is not present or felt, this means that the tab has no play. The force to be applied by hands while moving the tab upwards and downwards should be approximately 5lb in order to be able to feel play, if any.
NOTE
allowable edge free play is 0.039in, with 0.020in tolerance. If the free play is out of tolerance apply step 2
SERVICE BULLETIN
N° SB 398 – CS – Ed 2 Rev 1 Date: 05 08 2020 The technical content of this document is approved under the authority of DOA ref. EASA.21J.335 Approval No: DO-398-200805 Rev.1 Date, 17/08/2020 Page 5 / 6
MOD. PD-006-03 rev.2 data: 18/11/13
SERVICE BULLETIN Edition 2 Rev.1
3. STEP 2 – Trim Actuator free play measurement
1. Remove the upper tail cone fairing F7U;
2. Disconnect the bolt connecting the actuator screw to the trim control leverage;
3. Disconnect the trim indicator plunger bolt;
4. Move away the control leverage to allow free access to the actuator screw flat end (it will be the point to measure free play)
NOTE Avoid to screw or unscrew the actuator rod from actuator body in order to avoid need to perform the system rigging
5. According with the plunger dial available, locate the best position for the plunger dial base. The support must be on the stabilizer skin or on fuselage bulkhead to be sure that the free play measured is just the one coming from the actuator.
NOTE: the plunger dial in the picture is an angular one, this is why its body is not axial to the actuator screw flat surface.
6. Record both IN and OUT values of axial free play on dial (using an AN3 bolt can be helpful to move the actuator screw inside and outside without rotating it), repeat the measurement three times to be sure the record is correct, and fill out the following table, to be recorded into the Aircraft Logbook:
Tail Number S/N Total Free play
NOTE: free play on actuator screw, when present, is clearly felt by hands before measurement. If the free play is not present or felt, this means that the actuator has no play.
NOTE
allowable actuator screw free play is 0.000 to 0.020in. If the free play is out of tolerance proceed as follows:
free play within 0.000 and 0.020 no action needed free play within 0.021 and 0.036 actuator servicing per Job Card 1249 needed free play exceeding 0.037 actuator replacement needed (item 212-27-30-0410-000)
QUALITY AIRCRAFT SINCE 1948
TECNAM SERVICE BULLETIN N° SB 398 - CS - Ed 2 Rev 1 Date: 05 08 2020 The technical content of this document is approved under the authority of DOA ref. EASA.21J.335 Approval No: DO-398-200805 Rev. 1 Date, 17/08/2020 Page 6 / 6
4. Summary of actions STEP 1 Tab surface free play measurement free play exceeding 0.059in free play btw 0.000 and 0.059n STEP 2 Actuator rod END OF Return aircraft to service free play CHECKS Log values into logbook measurement actuator free play actuator free play actuator free play between 0.000 and 0.020n between 0.021 and 0.036in exceeding 0.037in Inspect the trim tab Service the Replace rods actuator per trim actuator No need to replace Job Card 1249 actuator After corrective actions have been performed, repeat STEP 1
5. Final Operations Make sure that the A/C is clear from foreign objects and tools
2. Install the removed fairings.
3. Register the works in the A/C logbook as described above;
4. Close the inspection Caps, if removed
5. Report the inspection results to Tecnam if any discrepancies has been found.
MOD. PD-006-03 rev.2 data: 18/11/13
SERVICE BULLETIN Edition 2 Rev.1