EASA AD - Helicopter
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EASA AD - Helicopter
Rather than start a new thread each time an AD is issued by EASA I thought it might be useful to have one thread with posts for new ADs.
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AD 2014-0040 AB412 and AB412 EP
AB412 and AB412 EP helicopters : Tail rotor Drive - Flanged Adapter - Inspection / Replacement.
A crack has been found during a scheduled inspection of a flanged adapter, Part Number (P/N) 412-040-622-101, installed on the tail rotor drive shaft P/N 412-040-621-107 of an AB412EP helicopter.
This condition, if not detected and corrected, could lead to tail rotor drive shaft failure, possibly resulting in reduced control of the helicopter.
To address this potential unsafe condition, AgustaWestland issued the Bollettino Tecnico (BT) 412-139, providing instructions to inspect the affected parts. However, the investigation to determine the root cause of the crack on the flanged adapter is in progress and the instructions of BT 412-139 will be updated according to the investigations results.
For the reasons described above, this AD requires repetitive inspections of the flanged adapters, P/N 412-040-622-101 and P/N 412-040-623-101, installed on the tail rotor drive shaft and, in case cracks are found, replacement of the cracked part with a serviceable one.
A crack has been found during a scheduled inspection of a flanged adapter, Part Number (P/N) 412-040-622-101, installed on the tail rotor drive shaft P/N 412-040-621-107 of an AB412EP helicopter.
This condition, if not detected and corrected, could lead to tail rotor drive shaft failure, possibly resulting in reduced control of the helicopter.
To address this potential unsafe condition, AgustaWestland issued the Bollettino Tecnico (BT) 412-139, providing instructions to inspect the affected parts. However, the investigation to determine the root cause of the crack on the flanged adapter is in progress and the instructions of BT 412-139 will be updated according to the investigations results.
For the reasons described above, this AD requires repetitive inspections of the flanged adapters, P/N 412-040-622-101 and P/N 412-040-623-101, installed on the tail rotor drive shaft and, in case cracks are found, replacement of the cracked part with a serviceable one.
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EASA EAD 2014-0046-E: MBB-BK 117 C-2 helicopters
EASA EAD 2014-0046-E: MBB-BK 117 C-2 helicopters: Optional Equipment - External Rescue Hoist System - Deactivation
In a recent incident involving an MBB-BK 117 C-2 helicopter, the rescue hoist
damper unit detached from the cable when the hoist damper was lifted by hand
(no load attached).
Subsequent investigation revealed that the detachment occurred because a
retaining ring inside the damper unit was not located at its correct installation
position. It was determined that the displacement of the retaining ring may
occur as a maintenance induced error, or as a result of retaining ring interaction
with the bonding strap unit during operation.
This condition, if not detected and corrected, could lead to the detachment of
an external load or person from the helicopter hoist, possibly resulting in
personal injury, or injury to persons on the ground.
For the reason described above, this AD requires replacement of the affected
rescue hoist damper units, or deactivation of the rescue hoist.
This AD is considered a temporary measure and further AD action may follow.
http://www.caa.co.uk/docs/33/2014022...D20140046E.pdf
In a recent incident involving an MBB-BK 117 C-2 helicopter, the rescue hoist
damper unit detached from the cable when the hoist damper was lifted by hand
(no load attached).
Subsequent investigation revealed that the detachment occurred because a
retaining ring inside the damper unit was not located at its correct installation
position. It was determined that the displacement of the retaining ring may
occur as a maintenance induced error, or as a result of retaining ring interaction
with the bonding strap unit during operation.
This condition, if not detected and corrected, could lead to the detachment of
an external load or person from the helicopter hoist, possibly resulting in
personal injury, or injury to persons on the ground.
For the reason described above, this AD requires replacement of the affected
rescue hoist damper units, or deactivation of the rescue hoist.
This AD is considered a temporary measure and further AD action may follow.
http://www.caa.co.uk/docs/33/2014022...D20140046E.pdf
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AB 412 helicopters equipped with hydraulic external hoist part number (P/N) BL10300-6
EASA EAD 2014-0063-E: AgustaWestland AB 412 helicopters: Equipment / Furnishings - Utility Hydraulic System / Pressure Line Pump and Filter - Inspection / Replacement
During hoist operation of an AB 412 helicopter equipped with hydraulic external hoist P/N BL10300-60, failure of pressure line pump P/N 1-8072 Rev. A was reported.
Preliminary investigations revealed that unusual wear of an internal subcomponent generated metal particles which caused the pump to fail. The root cause of this wear is under investigation, but has not yet been determined.
This condition, if not detected and corrected, could lead to further occurrences of pump failure, possibly resulting in personal injury or hoisting accidents.
To address this unsafe condition, AgustaWestland issued Bollettino Tecnico (BT) 412-140 providing instructions for inspection of filter P/N 1-12028 installed on the pressure line of the utility hydraulic system.
For the reason described above, this AD requires repetitive inspections of the filter for presence of metal particles and, in case of findings, replacement of the pressure line pump.
Pending final investigation results, this AD is considered an interim action and further AD action may follow.
During hoist operation of an AB 412 helicopter equipped with hydraulic external hoist P/N BL10300-60, failure of pressure line pump P/N 1-8072 Rev. A was reported.
Preliminary investigations revealed that unusual wear of an internal subcomponent generated metal particles which caused the pump to fail. The root cause of this wear is under investigation, but has not yet been determined.
This condition, if not detected and corrected, could lead to further occurrences of pump failure, possibly resulting in personal injury or hoisting accidents.
To address this unsafe condition, AgustaWestland issued Bollettino Tecnico (BT) 412-140 providing instructions for inspection of filter P/N 1-12028 installed on the pressure line of the utility hydraulic system.
For the reason described above, this AD requires repetitive inspections of the filter for presence of metal particles and, in case of findings, replacement of the pressure line pump.
Pending final investigation results, this AD is considered an interim action and further AD action may follow.
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Eu/ad 2014-0073 Aw 139 lower scissor
Some cases of dislodging of lower half scissor spherical bearings Part Number (P/N) 3G6230V00654 have been reported on in-service helicopters. These bearings are installed on main rotor (M/R) Rotating Scissors P/N 3G6230A00733.
As a result of the investigations accomplished by the supplier of the spherical bearings, it was determined that a quality issue might have affected the production of these bearings.
This condition, if not detected and corrected, could lead to loss of control of the helicopter.
To address this potential unsafe condition, AgustaWestland published Alert Bollettino Tecnico (BT) 139-368, providing inspection and replacement instructions.
For the reasons described above, this AD requires repetitive inspections of the M/R Rotating Scissors P/N 3G6230A00733 that have been manufactured or repaired by installing a potentially defective lower half scissor spherical bearing.
This AD also requires replacement of the affected spherical bearings or, as an alternative, replacement of the M/R Rotating Scissors with an affected bearing, which constitutes terminating action for the repetitive inspections required by this AD.
EASA Airworthiness Directives Publishing Tool
As a result of the investigations accomplished by the supplier of the spherical bearings, it was determined that a quality issue might have affected the production of these bearings.
This condition, if not detected and corrected, could lead to loss of control of the helicopter.
To address this potential unsafe condition, AgustaWestland published Alert Bollettino Tecnico (BT) 139-368, providing inspection and replacement instructions.
For the reasons described above, this AD requires repetitive inspections of the M/R Rotating Scissors P/N 3G6230A00733 that have been manufactured or repaired by installing a potentially defective lower half scissor spherical bearing.
This AD also requires replacement of the affected spherical bearings or, as an alternative, replacement of the M/R Rotating Scissors with an affected bearing, which constitutes terminating action for the repetitive inspections required by this AD.
EASA Airworthiness Directives Publishing Tool
Last edited by John R81; 20th Mar 2014 at 19:19.
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EASA EAD 2014-0076-E AS350 AS355
EASA EAD 2014-0076-E AS350 AS355
Fuselage – Rear Structure Junction Frame Reinforcement Angles – Inspection
Applies to AS 350 B, BA, BB, B1, B2, B3 and D helicopters, and AS 355 E, F, F1, F2, N and NP helicopters, all serial numbers,
- if incorporating modification (MOD) 07 3215, or
- if equipped with at least one reinforcement angle, Part Number (P/N)
350A08.2493.21 or P/N 350A08.2493.23, following the repair carried out in accordance with MRM Work Card 53.10.22.772 or AMM Task 53-31-00, 8-5.
Reason: During the inspection of several AS 355 helicopters, cracks were found in the reinforcement angles of the rear structure / tail boom junction frame. Subsequent investigation revealed that cracks were initiated on the non-visible surface of the angle (surface in contact with the frame).
This condition, if not detected and corrected, could lead to further crack propagation and subsequent loss of the tail boom, resulting in loss of the helicopter.
For the reason described above, this AD requires repetitive inspections of the affected area and, depending on findings, replacement of affected parts.
Terminating corrective action is currently under investigation by Airbus Helicopters. This AD is considered as a temporary measure and further AD action may follow.
Fuselage – Rear Structure Junction Frame Reinforcement Angles – Inspection
Applies to AS 350 B, BA, BB, B1, B2, B3 and D helicopters, and AS 355 E, F, F1, F2, N and NP helicopters, all serial numbers,
- if incorporating modification (MOD) 07 3215, or
- if equipped with at least one reinforcement angle, Part Number (P/N)
350A08.2493.21 or P/N 350A08.2493.23, following the repair carried out in accordance with MRM Work Card 53.10.22.772 or AMM Task 53-31-00, 8-5.
Reason: During the inspection of several AS 355 helicopters, cracks were found in the reinforcement angles of the rear structure / tail boom junction frame. Subsequent investigation revealed that cracks were initiated on the non-visible surface of the angle (surface in contact with the frame).
This condition, if not detected and corrected, could lead to further crack propagation and subsequent loss of the tail boom, resulting in loss of the helicopter.
For the reason described above, this AD requires repetitive inspections of the affected area and, depending on findings, replacement of affected parts.
Terminating corrective action is currently under investigation by Airbus Helicopters. This AD is considered as a temporary measure and further AD action may follow.
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US-2014-06-51 BK117
US-2014-06-51 BK117
Air conditioning drive pulley - inspection
This AD supersedes FAA AD 2013-12-06, dated July 9, 2013.
It affects Airbus Helicopters Deutschland GmbH (previously Eurocopter Deutschland GmbH) Model MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, and MBB-BK 117 C-2 helicopters with a Metro Aviation, Inc. (Metro) vapor-cycle air conditioning kit pulley (pulley), part number (P/N) 30001, installed in accordance with Supplemental Type Certificate (STC) No. SH3880SW.
Air conditioning drive pulley - inspection
This AD supersedes FAA AD 2013-12-06, dated July 9, 2013.
It affects Airbus Helicopters Deutschland GmbH (previously Eurocopter Deutschland GmbH) Model MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, and MBB-BK 117 C-2 helicopters with a Metro Aviation, Inc. (Metro) vapor-cycle air conditioning kit pulley (pulley), part number (P/N) 30001, installed in accordance with Supplemental Type Certificate (STC) No. SH3880SW.
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EAD 2014-0085 PZL SW4 Tail Rotor – Push-Pull Rod Spherical Bearings – Inspection / Replacement
[Trouble adding link today, see EASA Airworthiness Directives Publishing Tool ]
During post flight check of an SW-4 helicopter (military version of PZL SW-4 helicopter), a failure of one spherical bearing of the TR push-pull rod was detected. The affected bearing was found with its outer ring slipped out of the inner spherical race. There were no failure symptoms observed during flight.
Further investigation of the affected TR push-pull rod bearing showed wiping and peeling of the Teflon-steel liner of the inner spherical race which resulted in extensive wear of the bearing. That wear of the affected bearing had not been discovered previously during scheduled DAILY INSPECTIONS and POST-FLIGHT CHECKS, as these only consisted of general visual inspections of the TR for overall condition.
Failure of a spherical bearing causes changes in loading conditions in the TR push-pull rod and can lead to fatigue cracking.
This condition, if not detected and corrected, could lead to structural failure of a TR push-pull rod and consequent loss of the TR anti-torque function, possibly resulting in loss of control of the helicopter.
For the reasons described above, this AD requires repetitive inspections of the TR push-pull rod bearings for condition and no play and, depending on findings, accomplishment of corrective action.
[Trouble adding link today, see EASA Airworthiness Directives Publishing Tool ]
During post flight check of an SW-4 helicopter (military version of PZL SW-4 helicopter), a failure of one spherical bearing of the TR push-pull rod was detected. The affected bearing was found with its outer ring slipped out of the inner spherical race. There were no failure symptoms observed during flight.
Further investigation of the affected TR push-pull rod bearing showed wiping and peeling of the Teflon-steel liner of the inner spherical race which resulted in extensive wear of the bearing. That wear of the affected bearing had not been discovered previously during scheduled DAILY INSPECTIONS and POST-FLIGHT CHECKS, as these only consisted of general visual inspections of the TR for overall condition.
Failure of a spherical bearing causes changes in loading conditions in the TR push-pull rod and can lead to fatigue cracking.
This condition, if not detected and corrected, could lead to structural failure of a TR push-pull rod and consequent loss of the TR anti-torque function, possibly resulting in loss of control of the helicopter.
For the reasons described above, this AD requires repetitive inspections of the TR push-pull rod bearings for condition and no play and, depending on findings, accomplishment of corrective action.
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EASA EAD 2014-0098-E: Airbus AS 332 and EC 225 helicopters: Fuselage – Splice of Frame X5295 – Modification / Inspection / Repair
https://www.caa.co.uk/docs/33/201404...D20140098E.pdf
AS 332 L2 helicopters, all serial numbers, if equipped with extended aluminium splices on frame X5295 installed in accordance with Airbus Helicopters modification (MOD) 0726517, or Service Bulletin (SB) 53.01.52 or repair FR 332 53 507 06, and EC 225 LP helicopters, all serial numbers, if equipped with extended aluminium splices on frame X5295 installed in accordance with Airbus Helicopters MOD 0726517 or SB 53-003.
Cracks in helicopter frame
https://www.caa.co.uk/docs/33/201404...D20140098E.pdf
AS 332 L2 helicopters, all serial numbers, if equipped with extended aluminium splices on frame X5295 installed in accordance with Airbus Helicopters modification (MOD) 0726517, or Service Bulletin (SB) 53.01.52 or repair FR 332 53 507 06, and EC 225 LP helicopters, all serial numbers, if equipped with extended aluminium splices on frame X5295 installed in accordance with Airbus Helicopters MOD 0726517 or SB 53-003.
Cracks in helicopter frame
