CHAPTER 2 AIRCRAFT INFORMATION SUMMARY TABLE OF CONTENTS

CHAPTER 2 AIRCRAFT INFORMATION SUMMARY TABLE OF CONTENTS General...2 Kinds of Operations...2 Structural and weight limitations...2 Maneuvering limitations...3 Flight load factor limitations...3 Power plant limitations...3 Engine starter limitations...3 Engine operating limitations...3 Oil limitations...4 Propeller limitations...4 Fuel limitations...4 Electrical System limitations...5 Airspeeds limitations...5 Airspeed indicator markings...5 Normal operations airspeeds...6 Emergency operations airspeeds...7 Training maneuvers limitations...7 Excerpts from Airworthiness directives / Service Bulletins... NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 1

General This section presents a partial summary of the operating limitations and aircraft information necessary for the safe operation of the PA28R200 Arrow. This section is provided for quick reference only, and is not intended to substitute the approved Aircraft Flight Manual and other official materials. All BSU Aircraft are operated in accordance with the FAA regulations and BSU Aviation policies and procedures. In some cases, BSU policies and procedures will be more restrictive. Pilots shall refer to the BSU AOM and be familiar with/adhere to all general BSU aircraft operating procedures. In all cases, pilots operating the BSU Piper PA28R200 Arrow shall be thoroughly familiar with the information contained in the approved Aircraft Flight Manual, FAA regulations and applicable BSU Aviation policies and procedures. Observance of these limitations is mandatory. This chapter provides only a partial summary of limitations in accordance with the Aircraft Flight Manual. Pilots must refer to the Aircraft Flight Manual and BSU Aviation Operations manual to become familiarize with all required information. NOTE For aircraft equipped with specific options, refer to the Pilot s Information Manual (PIM) and FAA Approved Airplane Flight Manual (AFM) for amended operating limitations, procedures, performance data and/or other necessary information. Kinds of Operations The airplane is approved for the following operations when equipped in accordance with 14 CFR Part 91: Day V.F.R. Night V.F.R. Day I.F.R. Night I.F.R. Non-icing The BSU PA28R200 Arrow is not equipped for flight into icing conditions. Structural and Weight Limitations Flight into known icing conditions is PROHIBITED. Maximum Ramp Weight...2,658 lbs Maximum Takeoff Weight...2,650 lbs Maximum Landing Weight)...2,650 lbs Rear Baggage Area Maximum Weight... 200 lbs NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 2

Maneuvering Limitations The PA28R200 Arrow is rated in the Normal category only. The only authorized maneuvers in the Arrow are those maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and steep turns (with not more than 60 0 of bank). W A R N I N G Avoid any situations and maneuvers that may place the aircraft outside of the approved Normal category limits. All intentional aerobatic maneuvers, including SPINS are PROHIBITED. Flight Load Factor Limitations - Normal Category Positive Load Limit Negative Load Limit +3.8 g Flaps Up No inverted maneuvers approved. Power Plant Limitations Manufacturer... Lycoming Model Numbers... IO-360-C1C Maximum Horsepower... 200 BHP Maximum Engine Rotation Speed (RPM)...2700 Minimum Fuel Flow... 0.5 psi (2.0 gal/hr) Minimum Fuel Pressure... 14 psi Maximum Fuel Flow... 12 psi (21.4 gal/hr) Maximum Fuel Pressure... 45 psi Fuel Minimum Grade.... 100 (Green) / 100 LL (Blue) Engine Starter Limitations Maximum continuous cranking time (single start attempt)... 10 seconds Minimum cool-down time between attempts... 20 seconds Maximum number of start attempts...3 Engine Operating Limitations (all operations) Maximum Continuous Power...200 hp @ 2700 RPM Maximum RPM for all operations...2700 RPM Maximum Oil Temperature...245 F Oil Temperature Range (Normal)... 75 0-245 F Maximum Oil Pressure...90 psi Oil pressure range (normal)... 60-90 psi Minimum Oil Pressure...25 psi NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 3

Power Plant Instrument Markings INSTRUMENT Tachometer (RPM) Oil Pressure (PSI) Oil Temp. ( 0 F) Fuel Flow/Press. (GPH) Vacuum Press. (Hg) Red Line (Min) Green Arc Normal Red Line (Max) ----- 500-2700 2700 25 60 60 90 90 (Range at Idle) ----- 75 245 245 2.0 gph 21.4 gph 21.4 gph 14 psi 14 45 psi 45 psi ----- 4.9 5.1 ----- NOTE Proper engine (oil) temperature management is critical to air-cooled engine reliability and maximum service life. Flight crews will monitor oil temperature and adjust airspeed, climb gradient and power/mixture settings, as appropriate, in accordance with the AFM and above limitations for all operations. Oil Limitations Maximum Oil Capacity (per engine)... 8 qts Minimum Oil Quantity (per engine) / Flight of under 2 hours (BSU Policy)... 6 qts Minimum Oil Quantity (per engine) / Flight of 2 hours or more (BSU Policy)... 7 qts Do not operate the engine with less than six (6) quarts of oil. Propeller Specifications and Limitations Manufacturer... Hartzell / Model HC-C2YK-1/7666A-2 Type... Controllable Pitch Max. Diameter... 74 Min. Diameter... 72.5 Blade Angle Low Limit... 14.0 0 +/- 0.2 0 Blade Angle High Limit... 29.0 0 +/- 2.0 0 Avoid continuous static operations (over 5 minutes) between 1500-1950 RPM below 15 of manifold pressure. NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 4

Fuel Limitations Approved Fuel... Aviation Grade 100LL (Blue) or 100 (Green) Total Capacity (all tanks)... 50 Gallons Total Usable Fuel (all tanks)... 48 Gallons Total Unusable Fuel (all tanks)... 2 Gallons Usable Fuel (each wing tank)... 24 gallons Unusable Fuel (each wing tank)... 1 Gallon W A R N I N G The fuel remaining in the tank(s) when the quantity indicator reads zero cannot be safely used in flight. Flight crews shall avoid maneuvers that could uncover or un-port the wing outlet in the fuel tanks. Un-porting can result in fuel flow interruption and power loss. Avoid extreme running takeoffs, slips/skids resulting in altitude loss in excess of 2000, or other radical or extreme maneuvers. Electrical System Limitations Electrical system voltage... 14 Volts Alternator Output... 14 Volts Amps Load... Maximum 60 Amps Battery Output / Capacity... 12 Volts / 25 Amp/hour Minimum voltage to attempt engine start... 20 Volts W A R N I N G Alternator must be functional to initiate a flight. Departing on battery power alone, without a functional alternator, is prohibited. Airspeed Limitations The Airspeed Indicator for this aircraft is marked on the OUTER RING as MPH (miles per hour) and as KIAS on the INNER RING. Flight crews must take care to adhere to published airspeed limitations regardless of the type of marking used. NOTE The primary airspeed reference for the purposes of this manual will be in MILES PER HOUR (MPH). NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 5

Instrument Marking White Arc Green Arc Yellow Arc Airspeed Indicator Markings Explanation Full Flap Operating Range: Lower limit is max. weight V SO in the landing configuration. Upper limit is maximum speed permissible with flaps fully extended. Normal Operating Range: Lower limit is max. weight V S1 with flaps retracted. The upper limit is V NO. Caution Range: Flight in this range is limited to smooth air only, and then with caution. MPH 64-125 71-170 170 214 Red Line Never Exceed Speed: Maximum speed for all operations. 214 NOTE The maximum crosswind component for this aircraft is 17 KNOTS (20 MPH) The maximum crosswind component allowed for any BSU PA28R200 operations is 17 KNOTS (20 MPH), unless specifically authorized otherwise prior to flight. NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 6

NORMAL OPERATIONS AIRSPEEDS Symbol Reference Definition MPH V FE Max Flap Extend Speed Do not deploy wing flaps above this speed, and do not exceed this speed with wing flaps extended V LO V LE Max Landing Gear Operating Speed Max. Landing Gear Extended Speed Do not cycle the landing gear above these speeds. UP DOWN Do not exceed this speed with the landing gear extended V A Maneuvering Speed Do not make full or abrupt control movements above this speed. 2600 lbs. 1800 lbs. V NO Max Structural Cruising Speed Do not exceed this speed except in smooth air, and then only with extreme caution V NE Never Exceed Speed Maximum speed for all operations. V S1 Stall Speed, Specified Stall speed in a specified Configuration configuration, flaps up V SO Stall Speed, Landing Configuration Stall speed in the landing configuration, typically flaps down Vr Rotation speed Rotate at this speed on take-off Normal Short-field V X V Y Best Angle of Climb (max climb over distance) Best Rate of Climb (max vertical speed in climb) Maintain this speed until clear of obstacles, to gain maximum altitude in minimum forward distance Gear DOWN Gear UP Maintain this speed to gain greatest altitude in minimum time Gear DOWN Gear UP V climb Enroute or cruise climb speed Maintain this speed for the best combination of visibility, engine cooling and climb performance Traffic Pattern Typical speed to be maintained Maintain this airspeed in the at TPA, if appropriate downwind leg of a traffic pattern V ref(normal) Final approach speed / NORMAL landing Maintain this airspeed on final approach (with no gusts) 125 125 150 150 131 96 170 214 71 64 65 60 85 96 95 100 110 110-120 90 V ref(short) Final approach speed / SHORT- FIELD landing Maintain this airspeed on final approach (with no gusts) 83 V ref(no flap) X/W component Final approach speed / NO FLAP landing Maximum crosswind component on takeoff and landing Maintain this airspeed on final approach (with no gusts) Do not intentionally exceed this crosswind component on takeoff and landing 95 20 mph / 17 knots NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 7

EMERGENCY OPERATIONS AIRSPEEDS Symbol Reference Definition MPH V ref(no flap) V G Final approach speed / NO FLAP landing Best Glide Speed (engine inoperative) Maintain this airspeed on final approach during no-flap landings (with no gusts) Maintain this speed with the engine inoperative 95 105 Training maneuvers limitations W A R N I N G No intentional touch-and-go operations are permitted in BSU retractable gear aircraft. Full stop / stop-and-go landings are authorized only. All intentional aerobatic maneuvers, including spins, are prohibited. Min. altitude for any portion of stalls and slow flight, including recovery, is 1500 AGL. Intentional banks in excess of 60 are prohibited. Airworthiness Directives The following section lists the current Airworthiness Directives and Service Bulletins for the Piper PA-28R-200 Arrow. Flight crews are responsible for reviewing the maintenance summary sheet to ensure that the aircraft is in compliance with the following ADs and SBs: AD 97-01-01 R1 Main Gear Side-brace Stud This amendment revises (AD) 97-01-01, which currently requires repetitively inspecting the main gear side-brace studs for cracks on (Piper) Models PA-28R series airplanes, and replacing any main gear side-brace stud found cracked. The FAA has approved certain alternative methods of compliance (AMOC) for AD 97-01-01. This AD retains all the actions of AD 97-01-01, and will incorporate certain AMOC s as a way of accomplishing the actions specified in AD 97-01- 01. The actions specified by this AD are intended to prevent a main landing gear collapse caused by main gear side-brace stud cracks, which could result in loss of control of the airplane during landing operations. Effective 12/8/98. AD 96-10-03 Flap Handle Attachment Bolt The FAA issued this AD to require inspection and modification of the flap lever assembly. Reports of worn flap handle attach bolts and elongated holes in the flap lever to cable mounting attach point prompted issuance of the AD. The AD requirements are intended to prevent failure of the flap handle attach bolt and sudden retraction of the flaps, which, if not detected and NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 8

corrected, could result in loss of control of the airplane. Compliance time was established as follows: with a 2,000 hour TIS threshold or within the next 100 hours TIS for those airplanes with greater than 2,000 hours TIS. Effective 6/14/96. AD 95-26-13 Oil Cooler Hose Inspection Numerous incidents/accidents caused by oil cooler hose rupture or failure on the affected airplanes prompted this action. This amendment superseded (AD) 76-25-06, which required replacing oil cooler hoses on Piper Model PA28-140 airplanes, and inspecting for a minimum clearance between the oil cooler hose assemblies and the front exhaust stacks and adjusting if proper clearance was not obtained. This AD maintains the clearance inspection and oil cooler hose replacements, requires this inspection and these replacements to be repetitive, and extends the applicability to include other PA28 series airplanes. It also provides the option of installing approved TSO-C53a, Type D oil cooler hose assemblies as terminating action for the repetitive inspection requirement. The actions specified by this AD are intended to prevent these oil cooler hoses from failing or rupturing, which could result in engine stoppage and subsequent loss of control of the airplane. This AD requires a repetitive 100-hour time-in-service (TIS) inspection and 8-year (or 1,000 hours TIS) repetitive oil cooler hose assembly replacement. Effective 2/05/96. AD 94-14-14 Nose Landing Gear Modification This AD requires installing a certain nose landing gear modification kit (Piper part number (P/N) 764-377). Several service difficulty reports of collapsed nose gear on the affected airplanes prompted the AD. The reports revealed failure of the bolt (AN4-20) connecting the lower nose gear drag link to the upper drag link. The actions specified by this AD are intended to prevent nose gear collapse because of AN4-20 bolt failure, which could lead to airplane damage. Effective 8/19/94. AD 86-17-01 Ammeter Replacement This AD was issued to prevent smoke in the cockpit and possibly complete electrical failure resulting from shorting of ammeter terminal posts, and required the following: Within 50 hours time-in-service (TIS) after the effective date of the AD, replacement of the ammeter(s) with Ammeter Replacement Kit(s), Piper Part No. 765-186, on the above listed airplanes in accordance with the instructions contained in Piper Service Bulletin No. 811A, dated May 12, 1986. Effective 8/21/86. AD 82-06-11 Nose Landing Gear, Inspect, Rig, Modify This AD was issued to require modification of the nose landing gear that would prevent the inadvertent retraction of the nose landing gear. Within the next 100 hours time-in-service after the effective date of the AD, owners/operators are required to inspect, rig and modify the nose landing gear in accordance with Piper Service Bulletin No. 724A, dated April 20, 1982, Parts I and II as applicable, except dye penetrant must be used for detection of cracks. A record of compliance with this AD is required via an appropriate entry in the airplane maintenance records. Effective 6/16/82. NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 9

AD 81-11-02 Oil Drain Valves This AD requires compliance within the next 50 hours time in service (TIS) or at the next oil change, whichever comes first, after the effective date of the AD (unless it has already accomplished). The AD was issued to prevent possible loss of oil due to installation of an incorrect engine oil quick drain valve. The AD requires installation of two warning placards, one on each side, on the lower engine mount beneath the intake and exhaust tubes. For those airplanes equipped with an engine oil quick drain valve, the following actions are required: Inspection of the oil quick drain valve and installation and correct safety wiring of Piper Part No. 492-172V. If an incorrect valve is installed, replace with Piper PN 492-172V, and safety wire. Effective 10/2/81. AD 80-19-01 Carbon Monoxide in Cabin This AD was issued to prevent possible leakage of carbon monoxide into the cabin. Compliance is required within the next 50 hours time in service (TIS) after the effective date of the AD unless already accomplished, and includes the following actions: Removal of upper and lower engine cowling, removal and discard of clips on muffler shroud end plates, inspection for movement between the muffler shroud end plates and the muffler pipes. Piper Service Bulletin No. 691, dated August 6, 1980, pertains to this subject. Effective 9/12/80. AD 77-23-03 Control Rod Ends This AD applied to PA-28R-200 serial numbers 28R-35001 through 28R-7635512, and was issued to prevent power loss due to thermal contraction binding on a control rod end. Inspection of the rod bearing ends for the throttle, mixture, and propeller controls was required to be performed within 25 hours after issuance of the AD. If the rod bearing ends did not pass inspection, replacement with a serviceable part was required. Effective 11/14/77. AD 77-01-01 Fuel Quantity Indicators This AD applied to PA-28R-200 serial numbers 28R-7235001 through 7635459, and was intended to prevent fuel exhaustion resulting erroneous readings on the fuel gauges. The AD required the installation of a placard reading "WARNING FUEL GAUGES MAY INDICATE AS MUCH AS 2 1/2 GALLONS WHEN TANKS ARE EMPTY" within 10 hours TIS after issuance of the AD, and an inspection of the gauges for proper operation within the next 200 hours TIS or 12 calendar months, whichever came first. Effective 1/7/77. AD 76-15-08 Nose Gear Trunnion This AD applied to PA-28R-200 serial numbers 28R-7635001 to 28R-7635432 inclusive, and all PA-28R-200 airplanes that had the Nose Gear Trunnion Assembly (Piper part number 67054-00V) replaced with one supplied by the manufacturer between 8/1/75 and 8/1/76. The AD required a visual inspection of the nose gear trunnion to detect any obvious cracks on the trunnion ear that attaches to the nose landing gear arm spring. The AD allowed the inspection to be conducted by the pilot or by other persons authorized to perform preventive maintenance under FAR 43. Effective 8/6/1976. NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 10

AD 75-25-02 Rear Seat Leg Inspection This AD was issued to prevent the seats from coming loose during an accident, and required an inspection within the next 100 hours time in service or at the next annual inspection, whichever came first. The inspection required inspection of the rear legs on the quick-disconnect seats in accordance with Piper Service Letter No. 763, and adjustment or replacement of any component that did not pass inspection. Effective November 21, 1975. AD 75-08-03 Fuel Drain Valves This AD was issued to detect and correct an unsecured fuel drain valves installed at the gascolator. Compliance was required prior to next flight (or 50 hours time in service after the effective date of the AD) unless already accomplished, and was to be accomplished by a pilot check of the fuel gascolator drain valve, (Piper Part No. 492-022) to determine if it is tight in the fitting by attempting to turn the valve counter-clockwise by hand. Effective April 4, 1975. AD 74-09-04 Rear Seatbelt Installation This AD was issued to require the installation of improved rear seat belt by relocating the rear seat safety belt outboard attachments in accordance with Piper Service Bulletin Number 393. Effective 4/24/74. Service Bulletin No. 866A Backup Landing Gear Extender Removal The Piper PA-28R Back Up Gear Extender System was designed as a safety device to help prevent both inadvertent landing with the gear retracted and premature retraction of the gear during takeoff. When correctly operated and maintained, the system automatically extends the landing gear when the airspeed falls below a certain value, and also prevents the landing gear from being retracted before a specified airspeed. Allegedly, properly functioning systems were contributing factors in certain aircraft accidents, propagated by other emergencies. Piper issued Service Bulletin No. 866A, requiring the removal of the BGE system to eliminate the possibility of accidents occurring due to the system. NF ISSUE 9/12 AIRCRAFT INFORMATION SUMMARY 11