PPC

Question 1

PA

Answer 1

Forecast maximum pressure altitude (PA) for the mission and current PA for time and location of departure.

Question 2

FAT

Answer 2

Forecast maximum free air temperature (FAT) for the mission and FAT for time and location of departure.

Question 3

Note. Maximum PA and FAT will be used when computing all items in the departure section except for _______________, and ___________ which will be computed using PA and temperature for time and location of departure.

Answer 3

GO/NO GO TORQUE OGE/IGE

PREDICTED HOVER TORQUE

Question 4

AIRCRAFT GWT.

Answer 4

Total planned aircraft gross weight (GWT) at takeoff. This
includes the aircraft basic weight, crew, internal load, internal fuel, and when applicable, external

Question 5

STORES WEIGHT.

Answer 5

Planned weight of any jettisonable items such as external
loads, ESSS wing stores and volcano.

Question 6

FUEL WEIGHT.

Answer 6

Total planned fuel weight (internal and external) at takeoff.

Question 7

ATF/ETF.

Answer 7

Aircraft torque factor (ATF) is the ratio of individual aircraft’s power available to a specification power at 35 degrees Celsius. The ATF is an average of both engines and allowed to range from .90 to 1.0.

Engine torque factor (ETF) is the ratio of individual engine torque available to specification torque at a reference temperature of 35 degrees Celsius. The ETF is allowed to range from .85 to 1.0. The ATF and ETF values are found on the engine health
indicator test (HIT) log.

Question 8

TORQUE RATIO.

Answer 8

Torque ratio (TR) is the ratio of torque available to
specification torque at the desired ambient temperature and incorporates ambient temperature effects on engine performance. The tr equals the ATF/ETF for temperatures of 35 degrees
Celsius and above.

Question 9

MAX TORQUE AVAILABLE

Answer 9

MAX TORQUE AVAILABLE is based on TGT, NG or fuel flow limiting. 30, 10, or 2.5 min limit depending on how the PPC was configured

Question 10

Note. Adjust the maximum torque available as required for planned use of ______________________ IAW the current operator’s manual.

Answer 10

engine bleed air accessories (anti-ice, cockpit/cabin heaters)

Question 11

MAX ALLOWABLE GWT OGE/IGE.

Answer 11

This is the maximum weight the aircraft is capable of at a 10-foot hover height for IGE operations, or to a 100-foot hover for OGE operations. This weight will be limited by engine capabilities or aircraft structural design.

Question 12

Note. If OGE capability does not exist, the _____________ must be computed.

Answer 12

MAX HOVER HEIGHT IGE

Question 13

Note. For sling load operations, select an altitude that will place the load at an altitude of _____

Answer 13

10 feet.

Question 14

GO/NO GO TORQUE OGE/IGE.

Answer 14

This value provides a method to verify the
aircraft weight is at or below maximum weight and is capable of lifting to an IGE or OGE altitude.

The hover altitude is normally 10 feet but may be adjusted based on conditions. GO/NO GO is computed using the departure PA, item 1, and temperature, item 2.

Question 15

MAX HOVER HEIGHT IGE.

Answer 15

Maximum hover height when aircraft gross weight exceeds max allowable gross weight OGE and power is not available for an OGE hover.

Question 16

PREDICTED HOVER TORQUE.

Answer 16

Estimated torque required for a stationary hover, using takeoff gross weight, and current PA and FAT.

Question 17

MIN SE AIRSPEED – IAS – WO/W STORES.

Answer 17

Minimum (MIN) airspeed to sustain level flight single engine (SE) without or with stores. Value derived from cruise charts using departure conditions. Consideration should be given to an IGE takeoff if conditions merit.

Question 18

14-ZERO FUEL WEIGHT:

Answer 18

The zero fuel weight on the DD Form 365-4 (Weight
and Balance Clearance Form F-Tactical/Transport) is computed using standard, average, orestimated weight for personnel, equipment, and fuel.

Question 19

21-CRUISE TORQUE/CONT TORQUE AVAILABLE

Answer 19

Cont torque available is also called Max continuous power

Question 20

23-MAX RANGE-IAS/TORQUE (DUAL ENGINE).

Answer 20

Airspeed which yields the maximum distance per pound of fuel for a specific configuration, weight, and altitude. The airspeed is derived from the cruise chart for a no-wind condition.

A method of adjusting the maximum range airspeed to reduce flight time and minimize loss in range is to increase IAS by 2.5 knots for every 10 knots of effective headwind and decrease IAS by 2.5 knots for every 10 knots of effective tailwind.

Question 21

24-MAX ENDURANCE-IAS/TORQUE (DUAL ENGINE).

Answer 21

This IAS and torque yields the minimum fuel flow for a specific weight and altitude. In addition, total drag is at its lowest, and at this airspeed the aircraft will remain aloft for the longest period of time.

Question 22

25-CRITICAL TORQUE (DUAL ENGINE).

Answer 22

Critical torque (CT) is the dual engine torque value, which when exceeded, may not allow the aircraft to maintain % RPM R within normal limits under single-engine operations in the same flight conditions.

Question 23

26-MAX ALLOWABLE GWT and OPTIMUM IAS AT MAX ALLOWABLE
GWT (DUAL ENGINE).

Answer 23

The maximum allowable gross weight the aircraft is capable of flying at cruise conditions and the associated maximum endurance airspeed.

Question 24

27-MAX R/C-IAS/TORQUE (DUAL ENGINE).

Answer 24

IAS that allows the aircraft to climb from one altitude to a higher altitude in the least amount of time when using maximum torque available.

Question 25

28-MAX ALTITUDE-MSL/MAX ENDURANCE-IAS

Answer 25

The maximum altitude the aircraft is capable of flying at maximum endurance airspeed.

Question 26

29-MIN/MAX-IAS (SINGLE ENGINE).

Answer 26

Minimum and maximum airspeeds based on gross weight, power available and conditions.

Question 27

36-MAX ANGLE.

Answer 27

Value derived from the AIRSPEED FOR ONSET OF BLADE STALL chart in the aircraft operator’s manual, chapter 5. While not a limitation, the value provides the level flight angle of bank at which blade stall will begin to occur as a function of
airspeed, gross weight, PA, and temperature.

Question 28

What AC performance items are we required to obtain for dynamic in flight update?

Answer 28

a. Maximum torque available.
b. Maximum allowable gross weight OGE.
c. Torque required to hover at maximum gross weight OGE and IGE.
d. Aircraft gross weight.

Question 29

When must we compute dynamic in flight update?

Answer 29

W/N 3000LB of Max gross weight
1000 increase in PA (from our PPC)
5 increase in temp (from our PPC)