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 Cruise rapid attitude change, Flt Test (hardover) in a single resulting in a possible axis. flight. departure from stable Substantial increase in aircrew workload to recover from the resulting unusual attitude prior to departure from stable flight.
Unrestrained occupant injuries resulting from the abrupt attitude changes of the aircraft.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 6
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 Description Function Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method (FC) Occupants Malfunction Aircraft responds with a Analysis and (slowover) Hover, TO slow attitude change, Flt Test in a single App/Lnd attitude situation. This resulting in an unusual axis. could result in an airspeed, attitude or yaw outside the approved limits (depart stabilized flight) or result in a ground impact.
Substantial increase in aircrew workload to recognize and recover from the resulting unusual attitude prior to departure from stable flight and without impacting the ground.
2212 Pitch Attitude loss of pitch Annunciated ALL unaugmented pitch Aircraft reverts to Flt Test Analysis and Control stabilization. control.
Slight increase in aircrew workload to maintain pitch attitude.
Occupants may encounter some slight discomfort.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 7
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 Function ATA Description Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method (FC) Occupants ated loss of Unannunci- ALL Significant reduction in safety margins due to the Flt Test Analysis and pitch delay in pilot reaction to stabilization. take control.
Significant increase in aircrew workload due to the delayed recognition and recovery of pitch attitude.
Occupants may encounter some slight discomfort.
2216 Trim Autopilot Loss of autopilot ALL Slight reduction in safety margins due to loss of Gnd and Flt Test trim (IFR). finite control.
Aircrew workload may increase significantly due to loss of automatic control.
Occupants may encounter some slight discomfort.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 8
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 Description Function Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method (FC) Occupants Unannuncia Aircraft responds with a Analysis and -ted Hover, TO rapid attitude change, Flt Test malfunction App/Lnd resulting in a possible departure from stable (runaway). flight, or impact with terrain or ground-based obstacles.
Substantial increase in aircrew workload to recover from the resulting unusual attitude.
Occupant injuries and possible death resulting from the abrupt attitude changes of the aircraft and possible ground impact.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 9
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 Function ATA Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method Description (FC) Occupants Gnd and Flt 2250 Aerody- Loss of A significant reduction in namic Load stability Hover system margins is Test Alleviating augmenta- expected because of the (Stability tion (VFR). inherent instability of Augmenta- most rotorcraft in hover.
tion) 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.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 10
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 Function ATA Description Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method (FC) Occupants Unannunci- The information to the Analysis and ated loss of Hover flight crew could be 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 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 11
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 (hardover) Hover, TO rapid attitude change, Flt Test in a single App/Lnd resulting in departure axis. from stable flight and possible ground impact.
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 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 12
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 Description Function Condition Operation the Aircraft, Crew and of the FC (assumptions) Material Method (FC) Occupants Malfunction Aircraft responds with a Analysis and Cruise rapid attitude change, Flt Test (hardover) resulting in an unusual in a single axis. stable flight. attitude or departure from The aircrew workload would significantly increase in order to recognize and recover from an unusual attitude and regain stable flight.
Figure AC 27 MG 21-1. Generic Examples by ATA.
Page MG 21 - 13
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