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 22-00-00 - AUTO FLIGHT SYSTEM Failure Phase of Effect of the Failure on Classification Notes Supporting Verification ATA Function Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method Description (FC) Occupants Malfunction Aircraft responds with a Analysis and (slowover) Hover, TO slow attitude change, Flt Test App/Lnd resulting in an unusual in a single axis. attitude situation. This could result in an 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 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 14
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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification Function ATA Description (FC) Condition Operation Occupants the Aircraft, Crew and of the FC (assumptions) Material Method 2300 Communica Total loss of Aircrew workload would Analysis and tion System ALL radio ALL increase significantly for / or test communica- the requirement of the tion with crew to increase ATC and awareness for other other aircraft.
aircraft (IFR). Significant reduction in safety margins as one level of protection against a collision is lost.
No effect on occupants.
Total loss of Aircrew workload would Analysis and ALL radio ALL slightly increase by / or test communica- setting 7600 on the tion with Transponder and changing ATC and the planned flight by other landing at an uncontrolled aircraft airfield or receiving light (VER). signals from a controlled airfield.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 15
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 23-00-00 - COMMUNICATIONS Failure Phase of Effect of the Failure on Classification Notes Supporting Verification ATA Function Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method Description (FC) Occupants Loss of A slight reduction in Analysis and primary ALL safety margins would / or test radio occur with a loss of communica- redundancy of a required tion 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 communica- redundancy.
tion with ATC and Crew would switch to other secondary Comm. to aircraft in coordinate with ATC and VER (with other aircraft.
multiple comm.
Radios installed).
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 16
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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification Function ATA Description (FC) Condition Operation the Aircraft, Crew and Occupants of the FC (assumptions) Material Method 2400 Electrical Total loss of ALL Aircraft would lose all Analysis and Power ALL ability to control flight test electrical within the flight envelope;
power and non-survivable impact the aircraft is with ground.
equipped with electrical / electronic flight controls (fly by wire).
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 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 17
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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification ATA Function Description (FC) Condition Operation the Aircraft, Crew and Occupants of the FC (assumptions) Material 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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification Function ATA Description (FC) Condition Operation the Aircraft, Crew and Occupants of the FC (assumptions) Material 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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification ATA Function Description (FC) Condition Operation the Aircraft, Crew and Occupants of the FC (assumptions) Material Method 26-11 Smoke Detection Provide Inability to A substantial reduction in Analysis, smoke detect smoke ALL safety margins would Gnd Test detection in in the cabin exist due to the delay in cabin compartment. 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.
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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification ATA Function Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method Description (FC) Occupants 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 the failure increasing the compartment risk of an actual fire going (single and undetected.
dual engine).
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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification ATA Description Function (FC) Condition Operation the Aircraft, Crew and Occupants of the FC (assumptions) Material Method Unannunci- ALL A substantial reduction in ated loss of safety margins would fire detection exist due to the latency of in the cargo the failure increasing the or baggage risk of an actual fire going compartment. undetected.
Aircrew workload would not be affected.
26-20 Fire Extinguishing Provide fire Loss of fire ALL A slight reduction of suppression suppression safety margin due to of engine in engine indication to the cockpit fire zone. compartment and the limited exposure on (single of the failure condition.
and dual engine).
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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification ATA Function Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method Description (FC) Occupants 2841 Fuel Loss of fuel ALL Slight increase in pilot Quantity quantity workload as the pilot must indication estimate remaining fuel (single and from the last fuel quantity dual reading.
engine).
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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification ATA Function Description Condition (FC) Operation Occupants the Aircraft, Crew and of the FC (assumptions) Material 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 ALL Fuel quantity indicating fuel quantity more fuel than actual indication quantity.
and loss of low fuel A substantial reduction in warning safety margins due to (single and sudden and unexpected dual loss of engine power.
engine).
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 Failure Phase of Effect of the Failure on Classification Notes Supporting Verification ATA Function Description Condition (FC) Operation Occupants the Aircraft, Crew and of the FC (assumptions) Material Method 2822 Airframe Loss of ALL Aircraft safety margins Fuel Pump pump reduced to a level at Provide fuel (single which continued safe fight to the engine engine). 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 AI). 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