Emergency Airworthiness Directives
|EASA AD 2016-0180 (388 KB)||
ATA 25 - Equipment and Furnishings - Emergency
Floatation Gear Lighting and Ancillary Control Unit
(LACU) Pushbutton - In-Flight Check/Replacement
This AD is applicable to EC120 B helicopters fitted with LACU P/N 040101AB or 040101BA and that are not marked with 'ASB31A008'.
|27 Sep 2016|
|FAA AD 2016-17-04 (83 KB)||
Applicable to FAA Type Certificated
hot air balloons fitted with Kubicek fuel hoses made of
The FAA AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country (EASA) to identify and correct an unsafe condition on an aviation product.
The AD is prompted by three reports received by EASA of leaks found on burners manufactured by Balóny Kubíček spol. s.r.o. with fuel hoses made of “EGEFLEX” hose material.
The AD requires identification and replacement of affected fuel hoses.
|29 Aug 2016|
|EASA AD 2016-0173 (361 KB)||
ATA 64 - Tail Rotor Drive - Blade
Retention Bolts - Inspection/Replacement (Retirement
This AD with effective date 26 August 2016 is applicable to A109E, A109K2, A109LUH, A109S, A119, AW109SP and AW119MKII helicopters, all S/N.
The AD is prompted by a crack found in a TRB retention bolt P/N 709-0160-57-101 durring a pre-flight inspection on an A109E helicopter.
The investigation did not identify the cause of the crack. However, it was determined that bolts with P/N 709-0160-47-101 are not affected.
To address this potential unsafe condition, Leonardo issued Bollettino Tecnico (BT) 109SP-105, BT 109K-72, BT 109EP-149, BT 109L-087, BT 109S-072 and BT 119-080 to provide inspection instructions and introduce a reduced life limit for bolts P/N 709-0160-57-101.
This AD is considered an interim measure and further AD action may follow.
|26 Aug 2016|
|EASA AD 2016-0151 (493 KB)||
ATA 28 - Fuel - Burner and Fuel Hoses
This AD with effective date 9 August 2016 is applicable to hot air balloons fitted with Kubicek fuel hoses made of “EGEFLEX” material. The AD is prompted by three reports received by EASA of leaks found on burners manufactured by Balóny Kubíček spol. s.r.o. with fuel hoses made of “EGEFLEX” hose material. The AD requires identification and replacement of affected fuel hoses.
|09 Aug 2016|
|EASA AD 2016-0144 (411 KB)||
Rotax 912 A1/A2/A3/A4, 912
F2/F3/F4, 912 S2/S3/S4, and 914 F2/F3/F4 engines, all
This AD is prompted by a quality escape in the manufacturing process of certain floats, P/N 861185, which may cause a partial separation of the float outer skin during engine operation. Separated particles could lead to a restriction of the jets in the carburetor, possibly reducing or blocking the fuel supply to the affected cylinder.
This condition, if not detected and corrected, could lead to in-flight engine shutdown and forced landing, possibly resulting in damage to the aeroplane and injury to occupants.
To address this potential unsafe condition, BRP-Powertrain published Alert Service Bulletin (ASB) ASB-912-069/ASB-914-051 (single document) providing instructions for identification and replacement of the affected parts.
For the reasons stated above, this AD mandates the identification and replacement of the affected floats with serviceable parts, in accordance with the instructions of the ASB.
|26 Jul 2016|
Pacific Aerospace Cresco 08-600
Aircraft and FU24 and FU24A Series Aircraft
Elevator Torque Tube - Inspection
These ADs are prompted by two reports received by the CAA of finding a crack in the elevator torque tube on two Cresco 08-600 aircraft.
The same P/N elevator torque tube is fitted to FU24 and FU24A series aircraft.
These ADs are issued to prevent failure of the elevator torque tube due to possible fatigue, which could result in cracks, and loss of elevator and aileron control.
|07 Jul 2016|
EASA AD 2016-0118-E
AIRBUS HELICOPTERS DEUTSCHLAND GmbH - BO105
This AD with effective date 21 June 2016 is applicable to BO105 C, BO105 D, BO105 LS A-3 and BO105 S helicopters (all variants, except CB-5, D, DS, DBS-5 and CBS-5), all S/N.
This AD is prompted by a report of finding a debonded leading edge erosion cap on a main rotor blade (MRB) of a BO105 helicopter during an inspection. The investigation determined that incorrect preparation of the protective cap resulted in the debonding.
To address this unsafe condition, Eurocopter Deutschland GmbH (ECD) issued Emergency Alert Service Bulletins (EASBs) BO105-10A-128 and BO105 LS-10A-016, which introduces repetitive inspections to determine the correct installation of MRB leading edge erosion caps.
|21 Jun 2016|
This AD with effective date 17 June 2016 introduces
Kawasaki SB No. KSB-117-361F and is applicable to
Kawasaki BK117 series helicopters fitted with Goodrich
hoists P/N 42325-14-1, 44301-10-4 or 44301-10-7.
The AD supersedes the requirements in JCAB AD TCD-8201B-2015 dated 9 January 2015.
|17 Jun 2016|
|CF-2016-09 (140 KB)||
Transport Canada CF-2016-09-E - Main
Rotor - Corrosion of Tension - Torsion Straps
This AD with effective date 4 April 2016 is applicable to Bell Helicopter Textron Canada (BHTC) model 206 series helicopters fitted with tension torsion straps P/N 206-011-147-005, S/N BTFS-23868 through to BTFS-24277, and P/N 206-011-147-007, S/N BT-22719 through to BT-23437.
It has been determined that tension-torsion straps with P/N listed in the AD applicability may develop cracks in the urethane protective coating. This condition may result in internal corrosion of the straps. Corroded straps may fail earlier than their approved airworthiness life resulting in loss of aircraft control For that reason it is necessary to reduce the airworthiness life of affected parts. The new life limits are specified in the Corrective Actions section of the AD.
|04 Apr 2016|
|CF-2016-01R1 (145 KB)||
Transport Canada AD CF-2016-01R1 - Tail
Rotor - Pitch Link Corrosion
This AD with effective date 24 February 2016 is applicable to Bell Helicopter Textron Canada (BHTC) model 429 helicopters, S/N 57001 onwards.
AD CF-2016-01R1 provides clarification of affected part numbers and the action required for the installation of spare parts.
An additional corrective action has been added to verify that pitch links that were installed to replace corroded pitch links have been inspected and modified.
|24 Feb 2016|
EASA AD 2016-0025-E-Correction
EASA AD 2016-0025-E - GE AVIATION CZECH - M601
EASA AD 2016-0025-E (Correction dated 27 Jan 2016) with effective date 28 Jan 2016 has been re-issued to correct typographical errors in the AD applicability and Table 1.
The AD is applicable to GE Aviation Czech S.R.O. (formerly Walter Engines a.s.) M601D, M601D-1, M601D-2, M601E, M601E-11, M601E-21, and M601Z engines with S/N listed in Table 1 of EASA AD 2016-0025-E (Correction dated 27 Jan 2016).
During engine shop visits or overhauls certain power turbine (PT) discs may have been damaged in the area of the balance weights.
Additional PT discs with non-conforming geometry of the slot radius may have also been released to service as a result of incorrect machining of the PT disc slot.
This condition, if not corrected could result in PT disc failure, possible release of high-energy debris, damage and/or loss of aircraft control.
To address this unsafe condition, GE Aviation Czech issued ASB No. SB-2016-72-50-00-1 to provide inspection instructions for the affected engines.
This AD requires inspection of the PT disc and, depending on findings, replacement with a serviceable part.
|28 Jan 2016|
Transport Canada AD CF-2016-01 - Tail
Rotor - Pitch Link Corrosion
This AD with effective date 19 January 2016 is applicable to Bell Helicopter Textron Canada (BHTC) model 429 helicopters.
A model 429 helicopter experienced an in-flight failure of a tail rotor pitch link, resulting in noticeable vibration and difficulty controlling the helicopter. A safe landing was completed with no injuries; however there was collateral damage to the tail rotor system in addition to the failed pitch link.
Investigation revealed that the pitch link had fractured. A crack had initiated at a corrosion pit located between the roll staked lip of the part number (P/N) 429-312-107-103 bearing and the beveled edge of the P/N 429-012-112-103 tail rotor pitch link. Further investigation revealed deficiencies in the application of corrosion resistant finishes to the pitch link during the manufacturing process.
This condition, if not detected and corrected, could lead to pitch link failure, resulting in loss of controllability of the helicopter.
This AD requires inspection of the tail rotor pitch link within 10 flight hours from the effective date of the AD, in accordance with BHTC Alert Service Bulletin (ASB) 429-15-26 dated 07 December 2015.
|19 Jan 2016|
Transport Canada AD CF-2015-29 with effective date 21 December 2015 is
applicable to certain Bell 427 and Bell 429 helicopters.
The AD is prompted by several reports of finding cracked and leaking check valves with P/N 209-062-520-001. The check valve is used in the lubrication system of the main rotor transmission and engine of Bell 429 helicopters. The valve was supplied as a replacement part for use in the engine lubrication system of Bell 427 helicopters.
|21 Dec 2015|
DCA/350/128A (38 KB)
DCA/355/97A (38 KB)
These ADs with effective date 14 Dec 2015 is applicable to all AS350 and AS355
series helicopters fitted with any forward two-place
The ADs have been revised to clarify the AD requirements and introduce an AFM limitation.
|14 Dec 2015|