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 22-00-00 – AUTO FLIGHT SYSTEM 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 2250 Aerody namic Load Alleviating (Stability Augmenta tion) Loss of stability augmenta tion (VFR).
Hover A significant reduction in system margins is expected because of the inherent instability of most rotorcraft in hover.
The aircraft will lose short-term stability requiring a significant increase in workload is expected to maintain control.
Occupant injuries resulting from the abrupt attitude changes of the aircraft and possible ground impact.
Gnd and Flt Test Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 10
ATA 22-00-00 – AUTO FLIGHT SYSTEM 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 Unannunci ated loss of Hover The information to the flight crew could be Analysis and Flt Test stability delayed long enough for augmenta the aircraft to attain an tion (IFR). unusual attitude, which significantly reduces the safety margins or functional capabilities.
The aircrew workload would significantly increase in order to recognize and recover from an unusual attitude and regain stable flight.
Occupant injuries resulting from the abrupt attitude changes of the aircraft and possible ground impact.
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 11
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 22-00-00 – AUTO FLIGHT SYSTEM 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 Malfunction (hardover) in a single axis.
Hover, TO App/Lnd Aircraft responds with a rapid attitude change, resulting in departure from stable flight and possible ground impact.
Analysis and Flt Test Substantial increase in aircrew workload to recover from the resulting unusual attitude prior to departure from stable flight and possible ground impact.
Occupant injuries and possible death resulting from the abrupt attitude changes of the aircraft and possible ground impact.
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 12
ATA 22-00-00 – AUTO FLIGHT SYSTEM 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 Malfunction (hardover) in a single axis.
Cruise Aircraft responds with a rapid attitude change, resulting in an unusual attitude or departure from stable flight.
The aircrew workload would significantly increase in order to recognize and recover from an unusual attitude and regain stable flight.
Analysis and Flt Test Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 13
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 22-00-00 – AUTO FLIGHT SYSTEM 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 Malfunction (slowover) in a single axis.
Hover, TO App/Lnd Aircraft responds with a slow attitude change, resulting in an unusual attitude situation. This could result in an Analysis and Flt Test airspeed, attitude or yaw outside the approved limits (depart stabilized flight) or result in CFIT.
Substantial increase in aircrew workload to recognize and recover from the resulting unusual attitude prior to departure from stable flight.
Occupant injuries and possible death resulting from the abrupt attitude changes by the pilot and possible CFIT.
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 14
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 2300 Communica tion System Total loss of ALL radio communi cation with ATC and other aircraft (IFR).
ALL Aircrew workload would increase significantly for the requirement of the crew to increase awareness for other aircraft.
Significant reduction in safety margins as one level of protection against a collision is lost.
Analysis and / or test No effect on occupants.
Total loss of Aircrew workload would Analysis and ALL radio ALL slightly increase by / or test communicat setting 7600 on the ion with Transponder and ATC and changing the planned other flight by landing at an aircraft uncontrolled airfield or (VFR). receiving light signals from a controlled airfield.
Figure AC 29 MG 21-1. Generic Examples by ATA.
Page MG 21 - 15
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