AC 29-2C, Chg 7 2/4/2016 Note: Not all ATA chapters or subchapters have been included. Also, the italicized entries are not usually included in the failure condition description but in the systems description or assumptions section.
ATA 23-00-00 - COMMUNICATIONS ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method Loss of A slight reduction in Analysis and primary ALL safety margins would / or test radio occur with a loss of communi redundancy of a required cation with system.
ATC and other Crew would switch to aircraft in secondary Comm. to IFR. coordinate with ATC and other aircraft.
Loss of A slight reduction in Analysis and primary ALL safety margins would / or test radio occur with a loss of communi redundancy.
cation with ATC and Crew would switch to other secondary Comm. to aircraft in coordinate with ATC and VFR (with other aircraft.
multiple comm.
Radios installed).
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 16
ATA 24-00-00 – ELECTRICAL POWER ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method 2400 Electrical Power Total loss of ALL electrical power and the aircraft is equipped with electrical / electronic flight controls (fly by wire).
ALL Aircraft would lose all ability to control flight within the flight envelope; non-survivable impact with ground.
Analysis and test Total loss of ALL Aircrew workload would Analysis and ALL increase to a level higher test electrical than that required for power to continued safe flight and systems landing.
essential to safe continued IFR flight
(e.g., comm., NAV, attitude, altitude, airspeed, etc.).
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 17
AC 29-2C, Chg 7 2/4/2016 Note: Not all ATA chapters or subchapters have been included. Also, the italicized entries are not usually included in the failure condition description but in the systems description or assumptions section.
ATA 24-00-00 – ELECTRICAL POWER ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method Total loss of ALL Aircrew workload would Analysis and ALL significantly increase due / or test electrical to increased difficulty power in discerning the aircraft VFR (night) attitude via outside approved references.
rotorcraft
(e.g., comm., NAV, attitude, altitude, airspeed, etc.).
Loss of ALL A significant reduction in Analysis and primary safety margins due to test electrical loss of redundant power power and of a critical flight system.
the aircraft is equipped Aircrew workload would with slightly increase to electrical / compensate for any electronic power-shed equipment.
flight controls (fly by wire).
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 18
ATA 24-00-00 – ELECTRICAL POWER ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method Loss of ALL A significant reduction in Analysis and primary safety margins due to test electrical loss of redundant power power to of a required flight systems system.
essential to safe Aircrew workload would continued slightly increase to IFR flight compensate for any
(e.g., power-shed equipment.
comm., NAV, attitude, altitude, airspeed, etc.).
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 19
AC 29-2C, Chg 7 2/4/2016 Note: Not all ATA chapters or subchapters have been included. Also, the italicized entries are not usually included in the failure condition description but in the systems description or assumptions section.
ATA 26-00-00 - FIRE PROTECTION ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method 26-11 Smoke Detection Provide smoke detection in cabin Inability to detect smoke in the cabin compart ment.
ALL A substantial reduction in safety margins would exist due to the delay in the pilot’s reaction to take immediate action.
The aircrew workload would increase substantially due to handling emergency procedures.
Occupants could succumb to smoke inhalation.
Analysis, Gnd Test Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 20
ATA 26-00-00 - FIRE PROTECTION ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method Provide Inability to A substantial reduction in Analysis, smoke detect ALL safety margins would Gnd Test detection in smoke in the exist due to the delay in baggage baggage the pilot’s reaction to compartment compart ment.
take immediate action.
The aircrew workload would increase significantly due to handling emergency procedures.
Occupants could succumb to smoke inhalation.
26-12 Fire Detection Provide fire Unannunci- A substantial reduction in Analysis detection of ated loss of ALL safety margins would and/or Flt engine fire fire exist due to the latency of Test zone. detection in the failure increasing the the engine risk of an actual fire compart going undetected.
ment (single and dual Aircrew workload would engine). not be affected.
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 21
AC 2/4/2016 Note: Not all ATA chapters or subchapters have been included. Also, the italicized entries are not usually included in the failure condition description but in the systems description or assumptions section.
29-2C, Chg 7 ATA 26-00-00 - FIRE PROTECTION ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method Unannunciat ALL A substantial reduction in ed loss of safety margins would fire exist due to the latency of detection in the failure increasing the the cargo or risk of an actual fire baggage going undetected.
compart ment. Aircrew workload would not be affected.
26-20 Fire Extinguish ing Provide fire Loss of fire ALL A slight reduction of suppression of suppression safety margin due to engine fire in engine indication to the cockpit zone. compart ment on (single and dual engine).
and the limited exposure of the failure condition.
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 22
ATA 28-00-00 – FUEL ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method 2841 Fuel Quantity Loss of fuel quantity indication (single and dual engine).
ALL Slight increase in pilot workload as the pilot must estimate remaining fuel from the last fuel quantity reading.
Loss of low fuel level warning (single and dual engine).
ALL Aircraft safety margins will decrease slightly.
Combination loss of qty indication and low fuel level warning (single and dual engine).
ALL Substantial reduction in safety margins with the loss of all fuel quantity indications.
Significant aircrew workload due to the need to change the planned flight and find a suitable landing site before approximated fuel starvation.
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 23
AC 29-2C, Chg 7 2/4/2016 Note: Not all ATA chapters or subchapters have been included. Also, the italicized entries are not usually included in the failure condition description but in the systems description or assumptions section.
ATA 28-00-00 – FUEL ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method Misleading ALL Fuel quantity fuel qty indicating more fuel indication than actual quantity.
(single and Large reduction in dual engine). aircraft safety margins due to low fuel warning indicator as the only means of fuel starvation prevention.
Aircrew workload increases substantially due to unexpected low fuel annunciation.
Misleading ALL Fuel quantity fuel quantity indicating more fuel indication and than actual quantity.
loss of low fuel warning A substantial reduction (single and in safety margins due dual engine). to sudden and unexpected loss of engine power.
Aircrew may not being able to continue safe flight and landing.
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 24
ATA 28-00-00 – FUEL ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method 2822 Fuel Boost Pump Loss of pump (single engine).
ALL Aircraft safety margins reduced to a level at which continued safe fight and landing is not guaranteed due to loss of required fuel pressure to maintain engine operation (engine stoppage).
Aircrew workload reaches a level of not being able to continue safe flight and landing due fuel starvation and resulting engine stoppage; must conduct autorotation.
Loss of pump ALL Loss of fuel flow to (dual engine one engine results in a [CAT A]). significant reduction in safety margins.
Aircrew workload significantly increases due to transition to Category A OEI flight procedures.
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 25
AC 29-2C, Chg 7 2/4/2016 Note: Not all ATA chapters or subchapters have been included. Also, the italicized entries are not usually included in the failure condition description but in the systems description or assumptions section.
ATA 28-00-00 – FUEL ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method 2843 Fuel Temperature Indicator Loss of fuel temp indication.
ALL A slight reduction of safety margin due to indication to the cockpit and the limited exposure of the failure condition.
Analysis and Test Misleading fuel temp.
ALL A large reduction in safety margins or functional capabilities.
Analysis and Test ATA 29-00-00 – HYDRAULIC POWER ATA Function Description Failure Condition (FC) Phase of Operation Effect of the Failure on the Aircraft, Crew and Occupants Classification of the FC Notes (assumptions) Supporting Material Verification Method 29-10 Hydraulic System, Main Loss of hydraulic pressure.
ALL A slight reduction of safety margin due to indication to the cockpit and the limited exposure of the failure condition.
A significant increase in pilot workload that tasks, such as precision flight, cannot be accurately conducted.
Analysis and Text Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 26
2/4/2016 A C 29-2C, Chg 7
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 27