Piper PA-28-181 Archer II_III — peter_pa28-simulator-flight-planner
NOT FOR FLIGHT — source fidelity: unreviewed | operational review: none | completeness: full
Source: Piper/PA-28-181 Archer II_III/peter_pa28-simulator-flight-planner.txt
Rights: licensed
Checklist hash: 36421b6802f26c5f9b3b57ee27f1fce8afb597b655638c5fb4061c2627fae245
Verify against the aircraft's own approved documentation before use.
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GENERAL SPECIFICATIONS
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1. WEIGHT
SYMBOL | DESCRIPTION | VALUE [LBS]
[ ] MTOW maximum takeoff .................. 2550 (normal); 2130 (utility)
[ ] MLW maximum landing ................... 2550 (normal); 2130 (utility)
[ ] Mbc maximum baggage compartment ........... 200 (normal); 0 (utility)
[ ] Wb (unusable fuel + fluids) basic empty ........................ 1604
[ ] MUW (MTOW - Ws) maximum useful .......... 946 (normal); 526 (utility)
** NOTE: utility = no rear passengers; no (baggage + cargo)
** NOTE: useful load normal = usable fuel + front passengers + rear passengers + (baggage + cargo)
** NOTE: useful load utility = usable fuel + front passengers
2. SPEED
SYMBOL | DESCRIPTION | SPEED VALUES [KIAS]
[ ] Va maneuvering .......................... 113 (2550 GW); 89 (1634 GW)
[ ] Vfe max flap extended ........................................... 102
[ ] Vne never exceed ................................................ 154
[ ] Vno structural cruising (> in smooth air) ....................... 125
[ ] Vs stalling speed .......................................... fig. 5-3
[ ] Vso Vs/Vs in landing config. .................................... n/a
[ ] Vx best angle of climb ........................................... 64
[ ] Vy best rate of climb ............................................ 76
[ ] Vapp (full flaps) final approach speed ........................... 66
[ ] Vcrosswind max crosswind ......................................... 17
[ ] Green arc operational range .................................. 55-125
[ ] White arc flaps range ........................................ 49-102
3. CENTER OF GRAVITY
** NOTE: datum @ WLE + 78.4"
[ ] NORMAL 2550 lbs ................................. 88.6" aft / 82" aft
[ ] NORMAL < 2050 lbs ................................. 93" aft / 93" aft
[ ] UTILITY 2130 lbs .................................. 82" aft / 83" aft
[ ] UTILITY < 2050 lbs ................................ 93" aft / 93" aft
4. FUEL
CONDITION | VALUE [US GAL]
[ ] max .............................................................. 50
[ ] unusable .......................................................... 2
[ ] usable ........................................................... 48

FLIGHT PLANNING SHEET
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STEP | VALUES
0. LOAD CONFIGURATION
1. CONFIG-O-MATIC
ITEM | WEIGHT [LBS]
[ ] standard empty .................................................... —
[ ] operational equipment ............................................. —
[ ] basic empty ....................................................... —
[ ] pilot ............................................................. —
[ ] passenger 1 (co-pilot) ............................................ —
[ ] passenger 2 (rear) ................................................ —
[ ] passenger 3 (rear) ................................................ —
[ ] baggage + cargo ................................................... —
[ ] MAXIMUM USABLE FUEL ............................................... —
[ ] MAXIMUM GROSS ..................................................... —
[ ] DRY ............................................................... —
2. CLIMB
A. CLIMB PERFORMANCE
STATE | ITEM | VALUE
[ ] INPUT OAT [°C] .................................................... —
[ ] Hp [ft] ........................................................... —
[ ] OUTPUT V/S [ft/min] ............................................... —
B. CLIMB TIME, DISTANCE, FUEL
STATE | ITEM | VALUE
[ ] INPUT OAT [°C] departure .......................................... —
[ ] Hp [ft] departure ................................................. —
[ ] OAT [°C] cruise ................................................... —
[ ] Hp [ft] cruise .................................................... —
[ ] OUTPUT CORRECTIONS climb time departure [min] ..................... —
[ ] climb distance departure [mi] ..................................... —
[ ] climb fuel departure [gal] ........................................ —
[ ] climb time cruise [min] ........................................... —
[ ] climb distance cruise [mi] ........................................ —
[ ] climb fuel cruise [gal] ........................................... —
[ ] OUTPUT climb time [min] ........................................... 0
[ ] climb distance [mi] ............................................... 0
[ ] climb fuel [gal] .................................................. 0
3. DESCENT
STATE | ITEM | VALUE
[ ] INPUT OAT [°C] arrival ............................................ —
[ ] Hp [ft] arrival ................................................... —
[ ] OAT [°C] cruise ................................................... 0
[ ] Hp [ft] cruise .................................................... 0
[ ] OUTPUT CORRECTIONS descent time arrival [min] ..................... —
[ ] descent distance arrival [mi] ..................................... —
[ ] descent fuel arrival [gal] ........................................ —
[ ] descent time cruise [min] ......................................... —
[ ] descent distance cruise [mi] ...................................... —
[ ] descent fuel cruise [gal] ......................................... —
[ ] OUTPUT descent time [min] ......................................... 0
[ ] descent distance [mi] ............................................. 0
[ ] descent fuel [gal] ................................................ 0
4. CRUISE
A. DISTANCE [MI]
TRIP DISTANCE [MI] | CLIMB DISTANCE [MI] | DESCENT DISTANCE [MI] | CRUISE DISTANCE [MI]
[ ] TRIP DISTANCE [mi] ................................................ 0
[ ] CLIMB DISTANCE [mi] ............................................... 0
[ ] DESCENT DISTANCE [mi] ............................................. 0
[ ] CRUISE DISTANCE [mi] .............................................. 0
B. TAS [KTS]
STATE | ITEM | VALUE | CRUISE TYPE [P/E]
[ ] INPUT OAT [°C] cruise ............................................. 0
[ ] Hp [ft] cruise .................................................... 0
[ ] Cruise Power [65 %, 70 %, 75 %] ................................... —
[ ] OUTPUT TAS [kts] .................................................. —
C. TIME [HR]
CRUISE DISTANCE [MI] | TAS [KTS] | TAS [MI/HR] | CRUISE TIME [HR]
[ ] CRUISE DISTANCE [mi] .............................................. 0
[ ] TAS [kts] ......................................................... 0
[ ] TAS [mi/hr] ....................................................... 0
[ ] CRUISE TIME [hr] .................................................. 7
D. FUEL [GAL]
CRUISE POWER [%] | CRUISE TYPE [P/E] | FUEL FLOW [GPH] | CRUISE FUEL [GAL]
[ ] CRUISE POWER [%] .................................................. 0
[ ] CRUISE TYPE [P/E] ................................................. 0
[ ] FUEL FLOW [gph] ................................................... —
[ ] CRUISE FUEL [gal] ................................................. 7
E. MIXTURE RANGE [NM]
CRUISE OAT [°C] | CRUISE HP [FT] | CRUISE POWER [%] | CRUISE P/E RANGE [NM]
[ ] CRUISE OAT [°C] ................................................... 0
[ ] CRUISE Hp [ft] .................................................... 0
[ ] CRUISE POWER [%] .................................................. 0
[ ] CRUISE P/E RANGE [nm] ............................................. —
5. TOTAL FLIGHT TIME
[ ] TOTAL FLIGHT TIME [hr] ............................................ 7
6. TOTAL FLIGHT FUEL
[ ] TOTAL FLIGHT FUEL [gal] ........................................... 7
7. FLIGHT SIM FUEL
CAPACITY [LBS] | LEFT WING FUEL [LBS] | RIGHT WING FUEL [LBS]
[ ] CAPACITY [lbs] .................................................. 288
[ ] LEFT WING FUEL [lbs] .............................................. 7
[ ] RIGHT WING FUEL [lbs] ............................................. 7
8. LOADING CONSTRAINTS
ITEM | WEIGHT [LBS] | ARM AFT DATUM [IN] | MOMENT [LB*IN]
[ ] basic empty ............................................ 0 / 87.6 / —
[ ] pilot + passenger 1 (front) ............................ 0 / 80.5 / —
[ ] passenger 2 + passenger 3 (rear) ...................... 0 / 118.1 / —
[ ] baggage + cargo ....................................... 0 / 142.8 / —
[ ] total flight fuel ........................................ 7 / 95 / —
[ ] ACTUAL GROSS .............................................. 7 / — / 0
A. WEIGHT CONSTRAINT
** NOTE: The actual gross weight must be < 2550 lbs (normal) and < 2130 lbs (utility).
A. CG CONSTRAINT
[ ] CG POSITION THEO. [in] ............................................ —
[ ] CG POSITION GRAPH [in] ............................................ 7
** NOTE: The CG position must adhere to the value range from the "General Specifications" data sheet with operational maxima and minima shown on the graph.
9. TAKEOFF
STATE | ITEM | VALUE
[ ] INPUT OAT [°C] departure .......................................... 0
[ ] Hp [ft] departure ................................................. 0
[ ] Headwind (H) / Tailwind (T) [kts] ................................. —
[ ] Actual Gross Weight [lbs] ......................................... 7
[ ] Flaps 0/25 [°] .................................................... —
[ ] Performance (P) / Ground Roll (G) ................................. —
[ ] OUTPUT minimum takeoff distance [ft] .............................. —
10. LANDING
STATE | ITEM | VALUE
[ ] INPUT OAT [°C] arrival ............................................ 0
[ ] Hp [ft] arrival ................................................... 0
[ ] Headwind (H) / Tailwind (T) [kts] ................................. —
[ ] Landing Gross Weight [lbs] ........................................ 7
[ ] Performance (P) / Ground Roll (G) ................................. —
[ ] OUTPUT minimum landing distance [ft] .............................. —
11. EXTRA

CREDITS AND VERSION NUMBER
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** NOTE: All information in this worbook was based on the Piper Archer II manuals by Dreamfleet.
** WARNING: All information contained herein is only to be used for flight simulation entertainment purposes and NOT real world flying!
** NOTE: The coding and layout of the document was made by me, Peter.
** NOTE: I am in no way responsible for the manner in which you use this document and am not responsible for any damages it may incurr with your software or hardware.
** NOTE: You are free to modify certain things (but wouldn't recomment it due to the programming and cell detail) but cannot distribute this document for financial gain.
** NOTE: If you choose to upload the document with your modifications to a flight simulator enthusiasts website, I require credit for my work cause this took some time.
** NOTE: Enjoy! Peter
** NOTE: VERSION : 1.0
** NOTE: 37377