Method of and system for one-engine-inoperative training in aircraft with dissimilar engines
A method of simulating an aircraft one-engine inoperative (“OEI”) event includes operating a supplemental power unit (“SPU”) at a first SPU power level less than an SPU contingency power rating, operating a primary engine at a first primary-engine power level, reducing the primary-engine power level to less than the first primary-engine power level, and maintaining a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.
1 . A method of simulating a one-engine inoperative (“OEI”) event in a multi-engine aircraft that does not employ identical engines, the method comprising:
operating a supplemental power unit (“SPU”) at a first SPU power level less than an SPU contingency power rating, wherein the SPU contingency power rating is a power level after which the SPU must be inspected to assess a need for an overhaul of the SPU;
operating a primary engine at a first primary-engine power level;
simulating the OEI inoperative event by reducing the primary-engine power level to less than the first primary-engine power level; and
maintaining a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.
2 . The method of claim 1 , wherein the first SPU power level is a power level at which the SPU can be operated continuously without damage.
3 . The method of claim 1 , wherein the first SPU power level is a non-zero power level.
4 . The method of claim 1 , wherein the first SPU power level is zero.
5 . The method of claim 1 , comprising operating the SPU at a second SPU power level greater than the first SPU power level and less than the SPU contingency power rating.
6 . The method of claim 1 , comprising operating the SPU at a second SPU power level less than the first SPU power level.
7 . A system for simulating an aircraft one-engine inoperative (“OEI”) event in a multi-engine aircraft that does not employ identical engines, the system comprising:
a supplemental power unit (“SPU”) operable at a first SPU power level less than an SPU contingency power rating, wherein the SPU contingency power rating is a power level after which the SPU must be inspected to assess a need for an overhaul of the SPU;
a primary engine operable at a first primary-engine power level;
a flight control system (“FCS”) that controls the SPU and the primary engine, wherein the FCS is operable to:
simulate the OEI inoperative event by reducing the primary-engine power level to less than the first primary-engine power level; and
maintain a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.
8 . The system of claim 7 , wherein the first SPU power level is a power level at which the SPU can be operated continuously without damage.
9 . The system of claim 7 , wherein the first SPU power level is a non-zero power level.
10 . The system of claim 7 , wherein the first SPU power level is zero.
11 . The system of claim 7 , wherein the SPU is operable at a second SPU power level greater than the first SPU power level and less than the SPU contingency power rating.
12 . The system of claim 7 , wherein the SPU is operable at a second SPU power level less than the first SPU power level.
13 . A computer-program product comprising a non-transitory computer-usable medium having computer-readable program code embodied therein, the computer-readable program code adapted to be executed to implement a method comprising:
operating a supplemental power unit (“SPU”) of a multi-engine aircraft that does not employ identical engines at a first SPU power level less than an SPU contingency power rating, wherein the SPU contingency power rating is a power level after which the SPU must be inspected to assess a need for an overhaul of the SPU;
operating a primary engine of the multi-engine aircraft at a first primary-engine power level;
simulating the OEI inoperative event by reducing the primary-engine power level to less than the first primary-engine power level; and
maintaining a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.
14 . The computer-program product of claim 13 , wherein the first SPU power level is a power level at which the SPU can be operated continuously without damage.
15 . The computer-program product of claim 13 , wherein the first SPU power level is a non-zero power level.
16 . The computer-program product of claim 13 , wherein the first SPU power level is zero.
17 . The computer-program product of claim 13 , the method comprising operating the SPU at a second SPU power level greater than the first SPU power level and less than the SPU contingency power rating.