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BOLLETTINO TECNICO N° 139-269
The technical content of this document is approved under the authority of DOA nr. EASA.21J.005 DATE September 30, 2011
REV. /
Compliance with this bulletin is:
An appropriate entry should be made in the aircraft log book upon accomplishment.
If ownership of aircraft has changed, please, forward to new owner.
Page 1 of 11
SUBJECT: OPERATIONAL CHECK OF NR.1 AND NR.2 HYDRAULIC SYSTEMS
REASON: to confirm correct functionality of both hydraulic systems and then to introduce a periodicity.
HELICOPTERS AFFECTED: all AB139/AW139 helicopters S/N 31005 and subsequent (except the S/N’s 31007, 3109 4, 31293, 31301, 31303, 31313 and 31329) that have not accomplished a Flight Control Hydraulic System ground functional test procedure or a main Hydraulic System operational check within the la st fifty (50) flight hours prior to the receipt of this Bollettino.
COMPLIANCE: within fifty (50) flight hours or two (2) months from the receipt of this Bollettino, whichever occurs first.
Note Operational Checks of the Hydraulic Systems shall be repeated periodically. Refer to the approved AMPI schedule and AMP procedures for the subsequent repetitions.
MANDATORY An appropriate entry should be made in the aircraft log book upon accomplishment.
If ownership of aircraft has changed, please, forward to new owner .
An Company Via GiovanniAgusta, 520 21017 Cascina Costa di Samarate (VA) Italy T el.: +39 0331-229111 - Fax: +39 0331-229605/222595
B.T. 139-269
Page 2 of 11
DESCRIPTION: a recent reassessment of the hy draulic systems has indentified the need for the introduction of a periodical Operational Check.
REQUIRED MANPOWER: it is estimated that in order to accomplis h this Bollettino two
(2) man-hours (MMH) are necessary.
Man-hours are based on hands-on time and may vary with personnel and facilities available.
WARRANTY: N.A.
REQUIRED MATERIALS: N.A.
SPECIAL TOOLS: Refer to ITEP for the special tool s required to comply with the AMP DM referenced in this Bollettino.
WEIGHT AND BALANCE CHANGES: N.A.
REFERENCES:
9 AW139 Aircraft Fault Isolation Publication (AFIP) 9 AW139 Aircraft Maintenance Publication (AMP) 9 AW139 Illustrated Tools and Eq uipment Publication (ITEP)
PUBLICATIONS AFFECTED:
9 AW139 Aircraft Maintenance Pl anning Information (AMPI) 9 AW139 Aircraft Maintenance Publication (AMP)
B.T. 139-269
Page 3 of 11
COMPLIANCE INSTRUCTIONS:
1. Prepare the helicopter for a safe ground maintenance. Disconnect the battery and all the electrical power sources and/or the external power supply.
NOTE Performing following steps 2 thru 4, do not decrease the pressure of the Number 1 and Number 2 mainhydraulic systems to zero at the end of the single procedures as required by the applicable DM.
Do not disconnect external hydraulic power and external electrical powe r and do not perform the related “Requirements after job completions”.
2. Do the operational check of the Number 1 power-control module. Refer to AMP, see DM no. 39-A-29-11-01-00A-321A-A.
3. Do the operational check of the Number 2 power-control module. Refer to AMP, see DM no. 39-A-29-12-01-00A-321A-A.
4. Do the operational check of the Tail shutoff valve (4). Re fer to AMP, see DM no. 39- A-29-12-04-00A-321A-A.
5. With reference to figures 2 and 3, do the operational check of the PCM2 Flight control shutoff valve as follows:
5.1 On HCP (8) select the SOV2-CLOSE pos ition to depressurize the circuit 2.
5.2 Check that F/C CIRCUIT 2 has been shut off. Make sure that:
- on the instrument panel the M ASTER CAUTION (6) illuminates;
- on the HCP (8) the light HYD2 PRESS illuminates;
- on MFD (CAS area) (7) the caution message 2 HYD PRESS and 2 SERVO are displayed;
- on MFD HYDRAULIC SYNOPTIC page the cl osure of SOV 2 is indicated.
Verify that the MAIN ROTOR / TAIL ROTOR actuators section 2 depressurization is indicated;
B.T. 139-269
Page 4 of 11
- on MFD (HYD page) the displayed CIRCUIT 2 pressure value remains stable at 207 bar (3000 psi);
If, on MFD HYDRAULIC SYNOPTIC page, no caution massages are in view, SOV 2 remains open, see AFIP DM no. 39-A-29-12-00-00A-421C-A (Number 2 main hydraulic system - Fault Code 2912-03).
5.3 Reset the MASTER CAUTION.
5.4 On the HCP (8) select the SOV2-OPEN position to pressurize the circuit.
5.5 Check that F/C circuit 2 has been pressurized. Make sure that:
- On the instrument panels the MASTER CAUTION goes OFF.
- On the HCP the light HYD2 PRESS goes OFF.
- On MFD (CAS area), the caution message 2 HYD PRESS and 2 SERVO go out of view.
- On MFD HYDRAULIC SYNOPTIC page, the SOV 2 must be indicated OPEN. Verify that the MAIN ROTOR / TAIL ROTOR actuators section 2 pressurization is indicated.
5.6 If the 2 SERVO caution message stays in view, see AFIP DM no. 39-A-29-12- 00-00A-421E-A (Number 2 main hydraulic system - Fault Code 2912-05).
5.7 If the 2 HYD PRESS caution message stays in vi ew, see AFIP DM no. 39-A- 29-32-00-00A-421A-A (Indicating - Fault Code 2932-01).
5.8 If, on MFD HYDRAULIC SYNOPTIC page, t he closure of SOV 2 is indicated, replace the Number 2 power-control m odule (3). Refer to AMP, see DM no.
39-A-29-12-01-00A-520A-A and DM no. 39-A-29-12-01-00A-520A-A.
6. With reference to figures 1 and 3, do the operational check of the PCM1 Flight control shutoff valve as follows:
6.1 On HCP (8) raise the guard and move the three-position SOV switch to SOV1-CLOSE position to depressurize the CIRCUIT 1.
6.2 Check that F/C CIRCUIT 1 has been shut off. Make sure that:
- on the instrument panel the M ASTER CAUTION (6) illuminates;
B.T. 139-269
Page 5 of 11
- on the HCP (8) the light HYD1 PRESS illuminates;
- on MFD (CAS area) (7), the caution message 1 HYD PRESS and 1 SERVO appear.
- on the MFD HYDRAULIC SYNOPTIC page, the closure of the SOV 1 valve is indicated. Verify that the MAIN ROTOR / TAIL ROTOR actuators section 1 depressurization is indicated.
- Make sure that on MFD (HYD page) the displayed CIRCUIT 1 pressure value remains stable at 207 bar (3000 psi).
If on MFD HYDRAULIC SYNOPTIC page no caution massages are in view, SOV 1 remains open, replace the Number 1 power-control module (1). Refer to AMP, see DM no. 39-A-29-11-01- 00A-520A-A and DM no. 39-A-29-11-01- 00A-520A-A.
6.3 Reset the MASTER CAUTION (6).
6.4 On the HCP (8) select the SOV1-OPEN position to pressurize the circuit.
6.5 Check that F/C circuit 1 has been pressurized. Make sure that:
- On the instrument panels the MASTER CAUTION must be OFF.
- On the HCP the light HYD1 PRESS must be OFF.
- On MFD (CAS area), the caution message 1 HYD PRESS and 1 SERVO go out of view.
- On MFD HYDRAULIC SYNOPTIC page, the SOV 1 must be indicated OPEN. Verify that the MAIN ROTOR / TAIL ROTOR actuators section 1 pressurization is indicated.
6.5 If the 1 SERVO caution message stays in view, see AFIP DM no. 39-A-29-11- 00-00A-421B-A (Number 1 main hydraulic system - Fault Code 2911-02).
6.6 If the 1 HYD PRESS caution message stays in view, see AFIP DM no. 39-A- 29-31-00-00A-421A-A (Indicating - Fault Code 2931-01).
B.T. 139-269
Page 6 of 11
6.7 If On MFD HYDRAULIC SYNOPTIC page t he closure of SOV 1 is indicated, replace the Number 1 power-control module (1). Refer to AMP, see DM no.
39-A-29-11-01-00A-520A-A and DM no. 39-A-29-11-01-00A-520A-A.
7. With reference to figures 1, 3 and 4, do the operational ch eck of the Emergency landing gear shutoff valve as follows:
7.1 On the PCM1 (1), manually turn and ma intain the TEST LEVER (2) in the UP TEST position. See Figure 4 for details.
7.2 Check for the emergency L/G shut off valves closure as follows:
7.2.1 Make sure that on the hydr aulic synoptic page the emergency L/G shutoff valves indications are in t he closed position. If they are not, replace the Number 1 power-control module (1). Refer to AMP, see DM no. 39-A-29-11-01-00A-520A-A and DM no. 39- A-29-11-01-00A-520A- A.
7.2.2 In the MFD (CAS area) (7), ma ke sure that the caution messages EMERG L/G PRESS and 1 HYD MIN illuminate.
7.2.3 Make sure that on the instru ment panel the MASTER CAUTION (6) comes on.
7.2.4 Reset the MASTER CAUTION.
7.2.5 Make sure that on the HCP no change is seen.
7.3 Release the TEST LEVER (2) and make sure that:
- The TEST LEVER (2) returns automatic ally in the DOWN NORM position.
- The emergency shut off valve automatically re-opens.
7.4 Make sure that on the MFD (CAS ar ea) (7), the caution messages EMERG L/G PRESS and 1 HYD MIN go out of view.
7.5 If the EMERG L/G PRESS stays in view, see AFIP DM no. 39-A-29-31-00- 00A-421B-A (Indicating - Fault Code 2931-02).
B.T. 139-269
Page 7 of 11
7.6 If the 1 HYD MIN caution message stays in view, see AFIP DM no. 39-A-29- 31-00-00A-421E-A (Indicating - Fault Code 2931-05).
7.7 If the caution messages stay in vi ew, replace the Number 1 power-control module (1). Refer to AMP, see DM no. 39-A-29-11-01-00A -520A-A and DM no. 39-A-29-11-01-00A-520A-A.
8. On the hydraulic test bench, decrease t he pressure of the Nu mber 1 and Number 2 main-hydraulic systems to zero.
9. Disconnect the external hydraulic power from the helicopter. Refer to AMP, see DM no. 39-A-12-42-00-00A-510A-A.
10. Disconnect the external electrical power from the helicopter. Refer to AMP, see DM no. 39-A-12-41-00-00A-510A-A.
11. Remove all the tools and t he other items from the work area. Make sure that the work area is clean.
12. Close the access door 473AL. Refer to AMP, see DM no. 39-A-06-41-00-00A-010A- A.
13. Remove the platforms from the left and right sides of the fuselage.
14. Return helicopter to flight configuration and record for compliance with this bollettino on the helicopter logbook.
B.T. 139-269 2 Figure 1 Page 8 of 11
B.T. 139-269 _ 3 5 Figure 2 Page 9 of 11
B.T. 139-269 HYD 1 HYD 2 PRESS TEMP Figure 3 Page 10 of 11
B.T. 139-269
Page 11 of 11
Figure 4
SEALING REF
TEST POSITION
NORMAL POSITION
TEST LEVER Refer to Figure 1 item (2) and to Figure 2 item (5)
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