INVESTIGATION REPORT - avclaimsavclaims.com/N858MB Inspection Report AHI2016... · A/C: AS350B3e S/N: 7842 Hours: 331 Fab. date: 2014 Purpose: To determine the extent of damage sustained

INVESTIGATION REPORT Report #: AHI2016-IR170; Rev: IR Status: Final – December 19, 2016

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INVESTIGATION REPORT

Customer: AMRG Date: December 02, 2016 Place: Burleson, TX Reg: N858MB A/C: AS350B3e S/N: 7842 Hours: 331 Fab. date: 2014

Purpose:

To determine the extent of damage sustained when the aircraft was struck by an SUV while the aircraft was not running.

Airbus Helicopters, Inc. mission:

To determine the inspections and repairs required to return the aircraft to service.

Person(s) performing the investigation:

Name Company Function Drew Cook Airbus Helicopters, Inc. Airframe Investigation Expert

Structural Design Engineer Engineering Support and Liaison Lead

Summary:

_______________________Drew Cook Report completed by

During the investigation, damages resulting from the impact were extensive. The FWD, center, and aft fuselage sections all exhibit signs of severe structural damage and will require replacement. The tail boom shows buckling in multiple sections and will also require replacement or extensive repairs. The engine, gearboxes, and blades will all need further evaluation to determine serviceability.

Note: As of December 19, 2016, this report is considered final. This report will be updated as appropriate if a full investigation is complete and all damage is quantified. Subsequent releases of this report will be indicated by revision level.

This report and any attachments are intended for the addressee(s) only and may contain privileged, private or confidential information of AHI, AHF, AHD and/or one of their subsidiaries. Unauthorized review, disclosure, dissemination, distribution, duplication or other use of this information is strictly prohibited without the express written permission of AHI.

DISCLAIMER: This response/service is based on a Airbus Helicopters Group definition of the subject aircraft model. The response/service may be incompatible with an aircraft which has been modified according to a non Airbus Helicopters Group definition. For such an aircraft, it is your duty to check with the party responsible for the modification (and thus the change in the aircraft's definition) to ensure that this response/service is still valid for this particular aircraft. Your failure to ensure this may result in aircraft performance or flight safety being compromised. If this response/service is incompatible with the modified aircraft, Airbus Helicopters Group shall not be liable for any damages, including consequential damages, resulting from or related to the use of this response/service. By using this response/service, you agree to be bound by this disclaimer.


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Investigation:

Overview of Damages:

1. Center Fuselage – Beyond Repair

2. Aft Fuselage Cone – Beyond Repair

3. Tail Boom – Extensive Repairs

4. Canopy – Beyond Repair

5. Landing Gear – Beyond Repair

6. Dynamic Components – Additional Inspections Required

This report and any attachments are intended for the addressee(s) only and may contain privileged, private or confidential information of AHI, AHF, AHD and/or one of their subsidiaries. Unauthorized review, disclosure, dissemination, distribution, duplication or other use of this information is strictly prohibited without the express written permission of AHI.

DISCLAIMER: This response/service is based on a Airbus Helicopters Group definition of the subject aircraft model. The response/service may be incompatible with an aircraft which has been modified according to a non Airbus Helicopters Group definition. For such an aircraft, it is your duty to check with the party responsible for the modification (and thus the change in the aircraft's definition) to ensure that this response/service is still valid for this particular aircraft. Your failure to ensure this may result in aircraft performance or flight safety being compromised. If this response/service is incompatible with the modified aircraft, Airbus Helicopters Group shall not be liable for any damages, including consequential damages, resulting from or related to the use of this response/service. By using this response/service, you agree to be bound by this disclaimer.


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Damage 1: Center Fuselage / Aft Fuselage Cone

View looking at the LH side of the fuselage

This report and any attachments are intended for the addressee(s) only and may contain privileged, private or confidential information of AHI, AHF, AHD and/or one of their subsidiaries. Unauthorized review, disclosure, dissemination, distribution, duplication or other use of this information is strictly prohibited without the express written permission of AHI. DISCLAIMER: This response/service is based on a Airbus Helicopters Group definition of the subject aircraft model. The response/service may be incompatible with an aircraft which has been modified according to a non Airbus Helicopters Group definition. For such an aircraft, it is your duty to check with the party responsible for the modification (and thus the change in the aircraft's definition) to ensure that this response/service is still valid for this particular aircraft. Your failure to ensure this may result in aircraft performance or flight safety being compromised. If this response/service is incompatible with the modified aircraft, Airbus Helicopters Group shall not be liable for any damages, including consequential damages, resulting from or related to the use of this response/service. By using this response/service, you agree to be bound by this disclaimer.


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View looking at the LH X-frame and baggage floor



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View looking at the aft bulkhead where the center and aft fuselage sections join



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View looking up at the LH keel beam



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View looking OTBD at the RH keel beam



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View looking FWD at the RH side of the aft fuselage section

Damage:

The fuselage sustained extensive damages from the impact with the vehicle. The impact was on the LH side of the aircraft and buckled the LH/RH keel beams, LH/RH X-frames, and FWD/AFT bulkheads. Additionally, the LH baggage floor and entire aft fuselage cone were destroyed. The transmission deck showed signs of upward buckling at the aft end. However, a more detailed inspection of the deck with the mechanical components and fuel tank removed would likely reveal more damage. Due to the condition of the aircraft at the time of the inspection, it was not possible to remove the belly panels and thoroughly inspect the floor structure. However, the FWD bulkhead was extensively damaged in the area that attaches to the floor structure. Further damage is likely.

The center and aft fuselage sections must be replaced. Further inspection of the floor structure is required.



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Damage 2: Tail Boom (PN: 350A23-0020)

View looking FWD at the RH side of the tail boom and aft fuselage

View looking aft at the LH side of the tail boom



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View looking at the RH side of the lower vertical stabilizer

Damage: The tail boom skins have multiple areas of buckling. The horizontal stabilizer and lower vertical stabilizer were destroyed when the aircraft rolled onto its side. The upper vertical stabilizer was not present during the inspection.

The tail boom must be completely rebuilt or replaced.



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Damage 3: Canopy

View looking aft at the LH windscreen and canopy

View looking at the LH windscreen This report and any attachments are intended for the addressee(s) only and may contain privileged, private or confidential information of AHI, AHF, AHD and/or one of their subsidiaries. Unauthorized review, disclosure, dissemination, distribution, duplication or other use of this information is strictly prohibited without the express written permission of AHI. DISCLAIMER: This response/service is based on a Airbus Helicopters Group definition of the subject aircraft model. The response/service may be incompatible with an aircraft which has been modified according to a non Airbus Helicopters Group definition. For such an aircraft, it is your duty to check with the party responsible for the modification (and thus the change in the aircraft's definition) to ensure that this response/service is still valid for this particular aircraft. Your failure to ensure this may result in aircraft performance or flight safety being compromised. If this response/service is incompatible with the modified aircraft, Airbus Helicopters Group shall not be liable for any damages, including consequential damages, resulting from or related to the use of this response/service. By using this response/service, you agree to be bound by this disclaimer.


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View looking aft/INBD at the canopy roof and air intake

View looking at the cracked sealant bead along the RH windscreen and canopy



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View looking at FWD at the RH canopy support tube Damage: The canopy appears to have been twisted in the impact. The eyelet of the RH support tube has been torn out at the canopy attachment point. The canopy roof also has multiple areas where the skin is buckled downward. The sealant along both windscreens and the upper air intake is cracked and separated. The LH windscreen is also broken. The canopy and windscreen must be replaced.



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Damage 4: Doors

View looking at the RH FWD door

View looking at the lower hinge of the RH FWD door This report and any attachments are intended for the addressee(s) only and may contain privileged, private or confidential information of AHI, AHF, AHD and/or one of their subsidiaries. Unauthorized review, disclosure, dissemination, distribution, duplication or other use of this information is strictly prohibited without the express written permission of AHI. DISCLAIMER: This response/service is based on a Airbus Helicopters Group definition of the subject aircraft model. The response/service may be incompatible with an aircraft which has been modified according to a non Airbus Helicopters Group definition. For such an aircraft, it is your duty to check with the party responsible for the modification (and thus the change in the aircraft's definition) to ensure that this response/service is still valid for this particular aircraft. Your failure to ensure this may result in aircraft performance or flight safety being compromised. If this response/service is incompatible with the modified aircraft, Airbus Helicopters Group shall not be liable for any damages, including consequential damages, resulting from or related to the use of this response/service. By using this response/service, you agree to be bound by this disclaimer.


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View looking at the LH crew door



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View looking at the lower hinge of the LH crew door

Damage: The LH crew door has multiple areas of buckling and cracking around the attachment points and corners. The RH FWD door has minor cracking around the attachment points and the RH flap door was buckled near the hinge. The LH sliding door was not present during the investigation. The LH baggage door and aft cargo door were also not present but the impact occurred directly at their location and both are likely destroyed. The LH doors must be replaced. RH doors should undergo a detailed evaluation to determine reparability/serviceability.



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Additional Damages:

• Landing Gear – Destroyed

• Fuel Tank – Destroyed



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• • Transmission Cowls – Heavily Dented – To be Replaced

• Main Rotor Blades – Two Blades Contacted the Ground – Additional Evaluations



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• Anti-Vibration Assembly (AVA) – Upper Cap Deformed – Replace

• Vertical Flight Control Rods – Bent Due to Fuel Tank – Replace



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• FWD Belly Panels – Multiple Punctures / Fractures - Replace

• Aft Belly Panel – Not Present (Likely Destroyed)



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Required Inspections:

• AMM 05-50-00, 6-6 – Procedure After Impact on a Main Rotor Blade

• AMM 05-50-00, 6-7 – Procedure After Impact/Unbalance on the Tail Rotor Blade

• Contact Turbomeca for additional requirements for the engine

• Inspect all instrumentation and avionics in accordance with the respective component maintenance manuals

• Main rotor blades to evaluated for additional damages by AHI blade shop


Documents

INVESTIGATION REPORT - avclaimsavclaims.com/N858MB Inspection Report AHI2016... · A/C: AS350B3e S/N: 7842 Hours: 331 Fab. date: 2014 Purpose: To determine the extent of damage sustained