AC 27-1B, 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 substantially 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 loss test electrical of redundant power of a power and 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 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 18
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 Loss of ALL A significant reduction in Analysis and primary safety margins due to loss test electrical of redundant power of a power to required flight system.
systems essential to Aircrew workload would safe slightly increase to continued compensate for any IFR flight power-shed equipment.
(e.g., comm., NAV, attitude, altitude, airspeed, etc.).
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 19
AC 27-1B, 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 compartment.
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 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 20
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 Provide Inability to A substantial reduction in Analysis, smoke detect smoke ALL safety margins would Gnd Test detection in in the exist due to the delay in baggage baggage the pilot’s reaction to take compart compart immediate action.
ment ment.
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 detection exist due to the latency of Test zone. in the engine compartment (single and dual engine).
the failure increasing the risk of an actual fire going undetected.
Aircrew workload would not be affected.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 21
AC 27-1B, 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 Unannunci ated loss of fire detection in the cargo or baggage compartment.
ALL A substantial reduction in safety margins would exist due to the latency of the failure increasing the risk of an actual fire going undetected.
Aircrew workload would not be affected.
26-20 Fire Extinguish ing Provide fire suppression of engine fire zone.
Loss of fire suppression in engine compartment on (single and dual engine).
ALL A slight reduction of safety margin due to indication to the cockpit and the limited exposure of the failure condition.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 22
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 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 ALL Aircraft safety margins fuel level will decrease slightly.
warning (single and dual engine).
Combination ALL Substantial reduction in loss of qty safety margins with the indication loss of all fuel quantity and low fuel indications.
level warning Significant aircrew (single and workload due to the need dual to change the planned engine). flight and find a suitable landing site before approximated fuel starvation.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 23
AC 27-1B, 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 indicating fuel qty more fuel than actual indication quantity.
(single and Large reduction in aircraft dual safety margins due to low engine). fuel warning indicator as the only means of fuel starvation prevention.
Aircrew workload increases substantially due to unexpected low fuel annunciation.
Misleading fuel quantity indication and loss of low fuel warning (single and dual engine).
ALL Fuel quantity indicating more fuel than actual quantity.
A substantial reduction in safety margins due to sudden and unexpected loss of engine power.
Aircrew may not being able to continue safe flight and landing.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 24
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 2822 Airframe Fuel Pump Provide fuel to the engine 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 ALL Loss of fuel flow to one pump (dual engine results in a engine significant reduction in [CAT A]). safety margins.
Aircrew workload significantly increases due to transition to Category A OEI flight procedures.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 25
AC 27-1B, 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 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 26
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 34-00-00 - NAVIGATION 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) Supportin g Material Verification Method 3416 Altimeter Total loss of ALL altitude indication in IFR.
ALL Aircrew workload increases to a level at which continued safe flight and landing is not guaranteed due to unknown height above the ground; no external cues.
Analysis and Test Total loss of ALL altitude indication in night VFR.
ALL Aircrew workload substantially increases due to unknown height above the ground; low external cues.
Misleading indication and/or malfunction of the altitude in IFR.
ALL Aircrew workload increases to a level at which continued safe flight and landing is not guaranteed due to unknown height above the ground; no external cues.
Analysis and Test Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 27
AC 27-1B, 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 34-00-00 - NAVIGATION 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) Supportin g Material Verification Method Misleading indication and/or malfunction of the altitude indication in night VFR.
ALL Aircrew workload increases to a level at which continued safe flight and landing is not guaranteed due to unknown height above the ground; no indication to use external cues.
Analysis and Test 3414 Airspeed Indicator Total loss of ALL airspeed indication in IFR.
ALL The reduction in safety margins and functional capability in the system may prohibit continued safe flight and landing.
Analysis Total loss of ALL airspeed indication in VFR – night.
ALL The loss of critical information will result in a large reduction in safety margins and functional capability.
Aircrew workload may increase to a level such that they could not be relied upon to perform tasks accurately or completely.
Analysis and Test Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 28
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 34-00-00 - NAVIGATION 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) Supportin g Material Verification Method Misleading indication and/or malfunction of the airspeed in IFR.
ALL Aircrew workload may increase to a level such that they could not be relied upon to perform tasks accurately or completely.
Analysis and Test Misleading indication and/or malfunction of the airspeed in VFR – night.
ALL Aircrew workload may increase to a level such that they could not be relied upon to perform tasks accurately or completely.
Analysis and Test 3421 Attitude Total loss of ALL attitude indication in IFR.
ALL The reduction in safety margins and functional capability in the system may prohibit continued safe flight and landing.
Analysis Total loss of ALL attitude indication in VFR – night.
ALL Aircrew workload may increase to a level such that they could not be relied upon to perform tasks accurately or completely.
Analysis and Test Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 29