690A B Training Manual

Turbo Commander 690A/B

Reference Ref erence Manual

Turbo Commander 690A/B

Reference Manual

Introduction This manual is a stand-alone document appropriate for various levels of training. Its purpose is to serve as an informational resource and study aid. The Quick Reference chapter provides limitations and other data for quick review. The Operating Procedures section contains chapters that provide a preflight inspection of the aircraft, normal procedures, maneuvers, and other information for day-to-day operations. The Flight Planning chapter covers weight and balance and performance. Several charts are included. The Systems section is subdivided by aircraft system. At the beginning of the Systems Syst ems section, sec tion, a list of systems system s is cross-referenced to AT ATA codes to facilitate faci litate further furth er self-study, if desired, with the manufacturer’s manuals.

Using this Manual

Introduction This manual is a stand-alone document appropriate for various levels of training. Its purpose is to serve as an informational resource and study aid.

Using this Manual

The Quick Reference chapter provides limitations and other data for quick review. The Operating Procedures section contains chapters that provide a preflight inspection of the aircraft, normal procedures, maneuvers, and other information for day-to-day operations. The Flight Planning chapter covers weight and balance and performance. Several charts are included. The Systems section is subdivided by aircraft system. At the beginning of the Systems Syst ems section, sec tion, a list of systems system s is cross-referenced to AT ATA codes to facilitate faci litate further furth er self-study, if desired, with the manufacturer’s manuals.

Turbo Commander 690 A/B January 2005

Developed for Training Purposes

1-3

1-4



Quick Reference This chapter contains the aircraft operating limits and requirements as well as a system-by-system summarization of power sources, distribution, controls and monitors for both the TC 690A and 690B models. Each model’s limitations are in a separate, labeled section to avoid confusion. All limitations are printed in bold italic . Quick reference also contains supplement-directed limitations and operations. This section presents the operating limitations, the significance of such limitations instrument markings, color coding and basic placards necessary neces sary for the safe operation of the airplane, ai rplane, its powerplants, standard systems and standard equipment. The limitations included in this section have been approved by the FAA. Observance of these operating limitations is required by law. This chapter is intended to serve as a convenient reference.



Quick Reference Chapter 2

NOTE: Refer to section IX of the Manufacturer’s Pilot’s Operating Handbook for amended operating limitations, operating procedures, performance data and other necessary information for airplanes equipped with specific options.

2-1

2-2



Quick Reference General Limitations (690 A) Powerplant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5

Table of Contents

Engine Operation Limitations . . . . . . . . . . . . . . . . . . . . 2-5 Reverse Power Limitations . . . . . . . . . . . . . . . . . . . . . 2-5 Ignition Override Time Limits . . . . . . . . . . . . . . . . . . . . 2-5 Flight in Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . 2-6 Operating Temperature Temperature Limits . . . . . . . . . . . . . . . . . . . . 2-8 2 -8 Operating Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9 Propellers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10 Operational Limitations (690 A) . . . . . . . . . . . . . . . . 2-13 Instrument Markings. . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 Flight Load Factors . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 Weight and Center of Gravity. Gravity . . . . . . . . . . . . . . . . . . . 2-15 2 -15 Maneuvers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17 Airstart Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17 2 -17 Altitude Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 Cabin Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 Battery Temperature Temperature Monitor . . . . . . . . . . . . . . . . . . . 2-18 Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 Elevator Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 Placards Schematics . . . . . . . . . . . . . . . . . . . . . . . . 2-19 General Limitations (690 B) . . . . . . . . . . . . . . . . . . . . 2-21 Powerplant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 Engine Operation Limitations . . . . . . . . . . . . . . . . . . . 2-21 Engine RPM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 Reverse Power Limitations . . . . . . . . . . . . . . . . . . . . 2-21 Ignition Override Time Limits . . . . . . . . . . . . . . . . . . . 2-22 Flight in Icing Conditions . . . . . . . . . . . . . . . . . . . . . . 2-23 Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23 Operating Temperature Temperature Limits . . . . . . . . . . . . . . . . . . . 2-24 2 -24 Operating Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . 2-25 Turbo Commander 690 A/B January 2005


2-3

Propellers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-10 Restrictions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-26 Diameter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-26 Blade Angles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-26 . 2-26 Propeller SPeed Restrictions . . . . . . . . . . . . . . . . . . .2-26 Operational Limitations (690 B) . . . . . . . . . . . . . . . . .2-27 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-27 Types of Operation . . . . . . . . . . . . . . . . . . . . . . . . . . .2-27 Altitude Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . .2-27 Cabin Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . .2-27 Maximum Seating Limits . . . . . . . . . . . . . . . . . . . . . . .2-27 Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . .2-29 Powerplant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-29 .2 -29 Airspeed Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-30 Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . .2-31 Maneuver Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-34 Weight and Center of Gravity Limits . . . . . . . . . . . . . .2-34 C.G. C.G. Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-34 Placards Schematics. Schematics . . . . . . . . . . . . . . . . . . . . . . . . . .2-35

2-4



Quick Reference

General Limitations

Powerplant Engine - Two AiR AiRes esear earch ch TPE3 TPE33131-55-25 251K 1K

Model 690 A

Engine Operation Limitations: Condition

SHP

Propeller RPM

I TT ° C

Time Limit

Oil Temp °C

All

–

1679 (105.5% - 1686 (106%)

–

5 sec.

+40 to +110

All

–

1607 (101%) - 1679 (105.5%)

–

30 sec.

–

All

–

1599 (100.5%) - 1607 (101%)

–

5 min.

–

Starting

–

–

1149

1 sec.

-40 (min.)

717.5

1591 (100%)

923

None

Takeoff and Max. Continuous

+55 to +110

Reverse Power Limitations: Condition levers must be set at HIGH RPM when using reverse thrust during landing. Do not raise flight idle latches latches until nose gear has been lowered to to the runway. Do not enter reverse power range until both BETA lights are illuminated. Full Reverse is limited to speed less than 90 KIAS, at or above 95% RPM. Position power lever at GND GND IDLE until speed is reduced to 90 KIAS. Do not allow RPM to decrease below 95% while in reverse. Return power levers to GND IDLE if engine speed drops below 95% RPM.

Ignition Override Time Limits: L imits: 1. Engines Engines equipped with with ignition ignition units P/N 868962-2, 868962-2, manufactured manufactured by Simmonds, or P/N 868962-2, manufactured by Bendix, without Garrett Turbine Engine Co. SB75-0004 incorporated: a. 1 Minute Minute On followe followed d by 1 Minute Minute Off Off —or— b. 2 Minutes Minutes On followed followed by 2 Minute Minutess Off, Off, Followed by 2 more Minutes On Followed by 23 Minutes Off —or— c. 5 Minutes Minutes On followed followed by 55 Minutes Minutes Off.



2-5

2. Engines equipped equipped with with ignition ignition units P/N P/N 868962-2, manufactu manufactured red by Bendix, Bendix, with with Garre Garrett tt Turbi Turbine ne Engi Engine ne Co. Co. SB75SB75-0004 0004 incorpo incorporat rated: ed: Duty cycle of up to two hours hours continuous duty. The The total time “on” cannot exceed two hours without two hours “off.” The two hours “on” can be either continuous or intermitt ent. ent. NOTE: If ambient OAT is above 50°F (+10°C), observe duty cycle per step 1 above.

3. Engines Engines equipped with with ignition ignition units P/N 868962-3, 868962-3, manufactured manufactured by Bendix, without Garrett Turbine Engine Co. SB75-0004 incorporated: Duty cycle of up to one hour continuous co ntinuous duty. The total time “on” cannot exceed one hour without one hour “off”. The one hour “on” can be either continuous or intermittent. 4. Engines equipped with with ignition ignition units units P/N 868962-3 868962-3 manufactured manufactured by Bendix, with Garrett Turbine Engine Co. SB7 5-0004 incorporated: Duty cycle is unlimited when ambient OAT is less than + 50°F (+ 10°C). NOTE: If ambient OAT is above +50°F (+10°C), observe duty cycle of one hour continuous duty as noted in step 3.

Flight in Icing Conditions

NOTE: If icing conditions are entered in flight without the engine anti-icing system having been selected, switch one ENGINE system to ENG INLET position. If the engine runs satisfactorily, switch the second ENGINE system to ENG INLET position and check that the second engine continues to run satisfactorily.

2-6

Compliance with the following Limitations meets the requirements of Paragraph (a) of Airworthiness Directive No. 86-24-12, dated 28 November 1986. The requirements of Paragraph (a) of AD. of AD. 86-24-12 are superseded by Paragraph (b) and no longer apply when Custom Kit No. 139 (Auto-Ignition System) is installed. The IGN OVRD switch shall be selected to IGN OVRD position during all operations in actual or potential icing conditions described as follows: 1. During During takeoff takeoff and climb out in actual or potential potential icing icing conditions. 2. When ice is visible visible on, or shedding shedding from propeller(s propeller(s), ), spinner(s), spinner(s), or leading edge(s).



Quick Reference 3. Before Before selecting selecting ENG INLET, INLET, when ice has accumulated. accumulated. 4. Immediatel Immediatelyy any time engine flameout flameout occurs as a possible possible result result of ice ingestion. 5. During During approach and landing landing while while in or shortly shortly following following flight in actual or potential icing conditions. 6. During takeoff with standing water, slush or powdery snow on runway. For the purpose of the preceding steps, the following definition applies:

1. Potential Potential icing conditions conditions in precipitation precipitation or visible visible moisture meteometeorological conditions: a. Begin when when the OAT OAT is +5°C (+41°F) (+41°F) or colder colder,, and b. End when the OAT OAT is +10°C (+50°F) (+50°F) or warmer warmer.. NOTE: Above procedures supersede any other POH/AFM procedures which may be contradictory.



NOTE: If icing conditions are entered in flight without the engine anti-icing system having been selected, switch one ENGINE system to ENG INLET position. If the engine runs satisfactorily, switch the second ENGINE system to ENG INLET position and check that the second engine continues to run satisfactorily.

CAUTION: Flight may be limited by duty cycle of the Ignition System (see page 2-5). Do not operate engine inlet heat system longer than 10 seconds if OAT is greater than H=5°C (+ 41°F).

2-7

Operating Temperature Limits (690 A Model)

2-8



Quick Reference Table 2-A; Operating Operating Limitations Limitations Oil Temperature Minimum Starting

-40°C

Minimum Ground Operation

-40°C

Minimum Flight Operation

+55°C

Maximum All Conditions Oil Pressure

Minimum Idle

40 PSIG

Minimum Fl Flight Op Operation <2 <23,000 ft

70 PSIG

Minimum Fl Flight Op Operation >2 >23,000 ft

50 PSIG

Maximum All Conditions Ambient Starting Temperatures

Minimum Maximum

Ambient Operating Temperatures

See Chart, facing page

Fuel: (Aviation Turbine Fuels)

Pesticide Fuel Additive

+110°C

120 PSIG -40 °C +55 °C

AiResearch EMS 53100; ASTM Desig- nation ES2-74 and D1655-68T (Types Jet A, A-I and B): MIL-T-5624G(l) (Grades JP-4 and JP-5); and British Specs D. Eng. R.D. 2482 Issue 2, 2486 issue 2, and 2494 Issue 4. NATO equiv- alents approved. Aviation gasoline MIL-G-5572D, Grade 100LL may be used as an emergency fuel with limitations of 250 gallons per engine for each 100 hours of engine operation. The amount of aviation gasoline used must be entered in the Engine Log Book. See latest revision to Gulfstream Aero- space Service Letter No. 170 for list of approved fuels and temperature limits. See Gulfstream Aerospace Service Letter SI-179.

Oil

Lubricants conforming to MIL 23699A, and MIL-L-7808G are approved for use. See latest revision to General Aviation Division Service Letter No. 170 for a list of approved lubricants.

Engine Inlet Ice Protection

Operate to 10 seconds maximum with ambient temperature above +5°C



2-9

Propellers Two Hartzell propellers with LT 10282H+4 blades and hub model HCB3TN-5FL are installed. The propellers are 3-blade, full feathering, reversible, constant speed. Reverse operation is limited to ground operation only. NOTE: The following restrictions apply to those airplanes which are not equipped with propeller blades LT 10673 or LT 10673(B) per STC SA 546GL or Hartzell Bulletin No. 13l B. See Supplement 17. WARNING:

Positioning of power levers below the flight idle stop in flight is prohibited. Such positioning may lead to loss of air plane control or may result in an engine overspeed condition and consequent loss of engine power.

2-10

Do not move power levers aft of GND IDLE until until indicated speed has decreased to 60 KIAS and both BETA lights are illuminated. No Reverse Allowed Above 60 KIAS. Full reverse up to 500 HP at 90% RPM (minimum) may be initiated below 60 KIAS. Reduce Reverse Thrust proportionately as aircraft aircraft speed decreases.



Quick Reference



2-11

Cockpit Instruments

2-1

2-2

2-2A

2-3

2-4

2-5

2-7

2-8

2-6

2-12



Quick Reference Instrument Markings Engine Tachometer (See Figure 2-1, facing page) 96 - 100% RPM – Green Arc . . . . . . . . . . . . . . . . . . . . NORMAL 101% – Red Line Line . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM MAXIMUM

Operational Limitations Model 690A

Interstage Turbine Temperature (See Figure 2-2) 923°C – Red Line Line . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAKEOFF AKEOFF 1149°C – White or Orange Line Line . . . . . . . . . . . . . . .START LIMIT LIMIT

Exhaust Gas Temperature (See Figure 2-2A) (Installed in place of ITT gage in aircraft modified with TPE-331-10 Engines) 770°C – START . . . . . . . . . . . . . . . . . . . . . . . . . .MAX RED LINE Yellow Arc . . . . . . . . . . . . . . . . . NORMAL OPERATING OPERATING RANGE Per EGT Limit Chart ) ( Per

Engine Gage Unit (See Figure 2-3) Oil Temperature

-40°C – Red Line . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MINIMUM -40 to +55°C – Yellow Yellow Arc . . . . . . . . . . . . . . . . . . . . . . . CAUTION +55 to +110°C +110°C – Green Arc. . . . . . . . . . . . . . . . . . . . . . NORMAL +110°C +110°C – Red Line Line . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM MAXIMUM Oil Pressure - All Altitudes

40 PSI – Red Line . . . . . . . . . . . . . . . . . . . . . . . . . . . . MINIMUM 120 – Red Line . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM Oil Pressure < 23,000 ft.

40 to 70 PSI – Yellow Arc . . . . . . . . . . . . . . . . . . . . . . . CAUTION 50 to 120 PSI – Green Arc . . . . . . . . . . . . . . . . . . . . . . . NORMAL Oil Pressure > 23,000 ft

40 to 50 PSI – Yellow Yellow Arc. . . . . . . . . . . . . . . . . . . . . . . . CAUTION 50 to 120 PSI – Green Arc . . . . . . . . . . . . . . . . . . . . . . . NORMAL Fuel Pressure

15 PSI – Red Line . . . . . . . . . . . . . . . . . . . . . . . . . . . . MINIMUM 15 to 25 PSI – Yellow Yellow Arc . . . . . . . . . . . . . . . . . . . . . . . . CAUTION 25 to 80 PSI – Green Arc . . . . . . . . . . . . . . . . . . . . . . . . NORMAL 80 to 90 PSI – Yellow Yellow Arc . . . . . . . . . . . . . . . . . . . . . . . . CAUTION 90 PSI – Red Line Line . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM MAXIMUM



2-13

Airspeed Indicator For A/C S/N 11249 and subsequent , (See Figure 2-4, page 2-14) 86 Knots Knots – Red Line . . . . . . Minimum Single Engine Continuous 77 to 140 140 Knots Knots – White White Arc . . . . . . . . . . . . . . . Flaps Operat Operational ional 115 Knots – Blue Line . . . . . . . . Single Engine Best Rate-of-Climb Rate-of-Climb 82 to 243 Knots – Green Arc. . . . . . . . . . . . . . . . Normal Operation Maximum allowable pointer set . . . . . .52 Mach; Stop at 243 Knots

For A/C S/N 11100 through 11248, All speeds and color indications are the same, except Maximum Operating Speed is indicated by a red line.

Hydraulic Pressure (See Figure 2-5) 1250 PSI PSI – Red Line Line . . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM MAXIMUM

Vacuum (See Figure 2-6) 3.8 In.Hg – Red Line. . . . . . . . . . . . . . . . . . . . . . . . . . MINIMUM 3.8 to 5.0 In.Hg In.Hg – Green Arc . . . . . . . . . . . . . . . . . . . . NORMAL NORMAL 5.0 In.Hg – Red Line. . . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM

Emergency Gear Extension 425 PSI – Red Line . . . . . . . . . . . . . . . . . . . . . . . . . . . MINIMUM 425 to 525 PSI – Green Arc . . . . . . . . . . . . . . . . . . . . . NORMAL 525 PSI PSI – Red Line Line . . . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM MAXIMUM

Altitude and Differential Pressure (See Figure 2-7) 5.4 PSI PSI – Red Line Line . . . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM MAXIMUM

Shaft Horsepower (See Figure 2-8) 717.5 HP HP – Red Line Line . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM MAXIMUM

2-14



Quick Reference Airspeed Limitations All airspeeds are given in Knots, Calibrated Calibrated Airspeed (KCAS) Maximum Operation (V MO ) . . . . . . . . . . . . . . . . . . . . . . 243 KCAS Maximum Mach Number (M MO ) . . . . . . . . . . . . . . . . . . 0.52 Mach

Maximum Airspeed for 243 KCAS or 0.52 Mach Limitations: Altitude (Feet)

Maximum Airspeed (KCAS)

Sea Level to 19,000

243

21,000

232

23,000

223

25,000

214

27,000

205

29,000

196

31,000

188

CAUTION: Do not make abrupt

Maneuvering Speeds (VA) (Straight line variation between points) A/C Weight (lbs)

Maximum Airspeed (KCAS)

10,250

145

9850

143

9600

141

8750

136

7500

128

6550

121

6000

116

control movements above the maneuvering speeds listed. To do so could result in structural damage and possible loss of the airplane.

Operation

Airspeed (KCAS)

Flaps (V FE ) Full 40° Half 20°

140 180

Landing Gear (V LO )

200

Landing Light Extension (V LE )

156

Minimum Control Speed (V MC )

86 145

Sustained Icing Speed

Flight Load Factors Maxi Maximu mum m - Flap Flaps s UP

Posi Positi tive ve 3.28 3.28 G’s G’s

Nega Negati tive ve 1.31 1.31 G’s G’s

Maximum - Flaps Do Down

Positive 2.00 G’ G’s

Negative 0.00 G’s

Weight and Center of Gravity See Weight and Balance Section (Manufacturers Data, Part III) for Loading Schedule.



2-15

Aircraft Operation Limitation Approved Gross Weight – Center of Gravity Envelope (690 A Model) Operation of the aircraft outside the envelope en velope is prohibited. Envelope must be observed with landing gear extended. Allowance for landing gear retraction is automatic. a utomatic. L.E. MAC 196.00 Inches aft of Datum MAC length 74.5 Inches

2-16



Quick Reference Maximum Weights Ramp

10,300 lbs

Takeoff Jet Fuels

10,250 lbs

Aviation Gas

10,175

Landing

9,600

Zero Fuel

8,750 lbs

C.G. Limits Limits are given for landing gear down. Datum location is 196 inches forward of the wing leading edge e dge and 50 inches forward of fuselage station zero. Forward Limits: 212.93 inches aft of datum (22.72% MAC) at 10,250 1 0,250 lbs. 203.75 inches aft of datum (10.40% MAC) at 7,500 7 ,500 lbs. 203.75 inches aft of datum (10.40% MAC) at 6,749 6 ,749 lbs. Straight Straight line variation between points. Aft Limits: Limits: 218.7 inches aft of datum (30.47% MAC) at 10,250 10 ,250 lbs. 217.98 inches aft of datum (29.50% MAC) at 6,278 6 ,278 lbs. Variation between points: Inches aft of datum = 219.84 - (11,653 (11,653 ÷ Weight) Weight) Minimum Flying Weight: Weight: 214.575 inches aft of datum (24.93% MAC) at 6000 lbs. Straight Straight line variation between points.

Maneuvers This airplane must be operated as a normal category airplane. Acrobatic maneuvers, including spins, are unauthorized. Up to 560 feet altitude loss may occur during recovery from full stall.

Airstart Limitations Minimum Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100 KCAS Maximum Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KCAS Maximum approved altitude for airstarts airstarts . . . . . . 20, 000 feet MSL



2-17

Altitude Limitations Maximum approved altitude with Type A and A-1 aviation turbine fuel is 31,000 feet MSL. Maximum approved altitude with Type B aviation turbine fuel is 25,000 feet MSL. Maximum approved altitude using aviation gasoline: With fuel fuel boost pumps inoperative. . . . . . . . . . . . . . . . . 10,000 ft With With fuel boost boost pumps operatin operating g . . . . . . . . . . . . . . . . . . 25,000 ft

Cabin Pressurization Maximum approved cabin differential pressure is 5.4 PSI. The relief setting is 5.2 ± 0.1 PSI. Pressurization is prohibited during takeoff or landing.

Battery Temperature Monitor A/C with NiCad Batteries: Both Both batteries must must be deep cycled prior to the next flight if the battery select switch is positioned to either the 1 or 2 positions.

Ice Protection Ambient temperatures must be below +5° C for continuous operation of ice protection heat. Intentional stalls are prohibited when wing and empennage boots are operated. Do not operate wing and empennage boots during takeoff and landing .

Elevator Trim The TRIM annunciator on the annunciator panel is set to illuminate when elevator trim is not in takeoff range. This annunciator system must be operational.

2-18



Quick Reference Placards

THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY TYPE IN COMPLIANCE WITH THE AIRPLANE MANUAL. ACROBATICS AND INTENTIONAL SPINS ARE PROHIBITED.

AIRSPEED LIMITATIONS MAX GEAR EXTENDED: 200 KNOTS MIN CONTROL ONE ENGINE: 86 KNOTS

SHUT OFF LEFT ENGINE WHEN ENTERING AND LEAVING CABIN.

MAX FULL MANEUVERING: 145 KNOTS

AUTOPILOT MUST BE OPERATED IN ACCORDANCE WITH APPROVED FLIGHT MANUAL.

FLAP EXTENSION: 20° FLAPS – MAX 180 KNOTS 40° FLAPS – MAX 140 KNOTS

ICE PROTECTION ELECTRIC HEATERS: GND. CHECK 30 SEC. MAX DO NOT OPERATE BOOTS DURING T.O AND LDG.

CAUTION DO NOT SMOKE OR IGNITE FLAME WITH OXYGEN SYSTEM IN USE.

Located at left side of pilot compartment. comp artment.

LANDING L

R

PROP SYNC EXTEND

ON

O F F OFF OFF

MUST BE OFF DURING TAKEOFF AND LANDING

RETRACT

DO NOT EXTEND ABOVE 156 KNOTS Located on overhead switch panel below LANDING switches.


Located on quadrant to the right of condition levers


2-19

Placards (con’t) WINDSHIELD OFF WHEN USING STANDBY COMPASS

MAX A/S 243 232 223 214 205 196 188

ALT ALT X1000 S.L -19 21 23 25 27 29 31

Located near standby compass

WARNING

Located near pilot’ p ilot’ss airspeed indicator. indicator. Effective Aircraft: S/N 11100 through 11248. NOTE: Placard not required when changing to Max. Allowable Airspeed Indicator.

FOR AVIATION EMERGENCY USE ONLY ONLY UNLICENSED OPERATION UNLAWFUL OPERATION IN VIOLATION OF FCC RULES SUBJECT TO FINE OR LICENSE REVOCATION

Located adjacent to Emergency Locator Transmitter Switch (if installed)

MODE

AUTO TEMP

AUTO OFF/RAM

OVER -

AIR

OXYGEN

RIDE

PUSH AND ROTATE

WARM

COOL

REMOVE DOOR WHEN OPERATING ABOVE 25,000 FT. FLT. ALT PRESSURIZATION NOT PERMITTED

Located to the right of oxygen door knob S/N 11100 through 11248, 11250 though 11268

DURING TAKEOFF AND LANDING

Located on environmental panel.

STATIC SOURCE ADJUST TO 22,500 22,500 FT ALTITUDE AL TITUDE MINIMUM

Located above oxygen regulator S/N 11249, 11269 and subsequent

2-20

PRIMARY

CAUTION USE AIRSPEED AND ALTIMETER CALIBRATION WHEN USING ALTERNATE SOURCE

ALTERNATE

Located at left side of pilot compartment (Applicable to airplanes which have not had Service Letter No. 323 complied with.)



Quick Reference

General Limitations

Powerplant Engine Two Garrett AiResearch engines: - TPE331-5-251 TPE331-5-251K K (S/N (S/N 11350 11350 through through 11542, 11542, except except 11431) 11431)

Model 690 B

- TPE 331331-5-2 5-252K 52K (S/N (S/N 11431 11431,, 11543 11543 and and subsequ subsequent ent))

Engine Operation Limitations Condition

I TT ° C

RPM Percent

SHP

Time Limit

Oil Temp °C

Takeoff

923

100

717.5

None

+55 to +110

Max Continuous

923

100

717.5

None

+55 to +110

Max Climb

923

100

717.5

None

+55 to +110

Maximum Cruise

905

96 to 100

717.5

None

+55 to +110

1149

---

---

1 Second

-40 Minimum

Starting ALL

--

100.5 to 101.0

---

5 Minutes

-40 to +93

ALL

--

101.0 to 105.5

---

30 Seconds

-40 to +93

ALL

--

105.5 to 106.0

---

5 Seconds

-40 to +93

Engine RPM: Avoid operation between 18 and 28 percent RPM except for transients occurring during start and shutdown.

Reverse Power Limitations: Condition levers must be set at HIGH RPM when using thrust during landing. Do not raise flight idle latches latches until nose gear has been lowered to to the runway. Do not enter enter reverse reverse power power range range until until both BETA BETA light lightss are illumi illuminate nated. d. Full Reverse is limited to speed less than 90 KIAS, at or above 95% RPM. Posit Position ion power power lever lever at GND GND IDLE IDLE until until speed speed is reduce reduced d to to 90 90 KIA KIAS. S. Do not allow RPM to decrease below 95% while in reverse. Return power levers to GND IDLE if engine speed drops below 95% RPM. NOTE: The following restrictions apply to those airplanes which are not equipped with propeller blades LT 10673 or LT 10673(B) per STC SA 546GL or Hartzell Bulletin No. 13l B. See Supplement 16.

Do not move power levers aft of GND IDLE IDLE until indicated speed has decreased to 60 KIAS and both BETA lights are illuminated. No Reverse Allowed Above 60 KIAS. Full reverse up to 500 HP at 90% RPM (minimum) may be initiated below 60 KIAS. Reduce Reverse Thrust proportionately as aircraft aircraft speed decreases.



WARNING:

Positioning of power levers below the flight idle stop in flight is prohibited. Such positioning may lead to loss of air plane control or may result in an engine overspeed condition and consequent loss of engine power.

2-21

Ignition Override Time Limits: 1. Engines Engines equipped with with ignition ignition units P/N 868962-2, 868962-2, manufactured manufactured by Simmonds, or P/N 868962-2, manufactured by Bendix, without Garrett Turbine Engine Co. SB75-0004 incorporated: a. 1 Minute Minute On follow followed ed by 1 Minute Minute Off Off —or— 2 Minutes On followed by 2 Minutes Off, Followed by 2 more Minutes On Followed by 23 Minutes Off —or— b. 5 Minutes Minutes On followed followed by 55 Minute Minutess Off. Off. 2. Engines equipped equipped with with ignition ignition units P/N P/N 868962-2, manufactu manufactured red by Bendix, Bendix, with with Garre Garrett tt Turbi Turbine ne Engi Engine ne Co. Co. SB75SB75-0004 0004 incorpo incorporat rated: ed: Duty cycle of up to two hours continuous duty. The total total time “on” cannot exceed two hours without two hours “off.” The two hours ent. “on” can be either continuous or intermitt ent. NOTE: If ambient OAT is above 50°F (+10°C), observe duty cycle per step 1 above.

3. Engines equipped with with ignition ignition units units P/N 868962-3, 868962-3, manufactured manufactured by by Bendi Bendix, x, withou withoutt Garret Garrettt Tur Turbin binee Engi Engine ne Co. SB SB7575-000 0004 4 inco incorp rpora orated ted:: Duty cycle of up to one hour continuous co ntinuous duty. The total time “on” cannot exceed one hour without one hour “off.” The one hour “on” can be either continuous or intermittent. 4. Engines equipped equipped with ignition units units P/N 868962-3 manufactured by by Bendix Bendix,, with with Garret Garrettt Turbi Turbine ne Engine Engine Co. SB7 5-0004 5-0004 incorp incorpora orated ted:: Duty cycle is unlimited when wh en ambient OAT is less than + 50°F (+ 10°C). NOTE: If ambient OAT is above +50°F (+10°C), observe duty cycle of one hour continuous duty as noted in step 3.

2-22



Quick Reference Flight in Icing Conditions Compliance with the following Limitations meets the requirements of Paragraph (a) of Airworthiness Directive No. 86-24-12, dated 28 November 1986. The requirements of Paragraph (a) of AD. of AD. 86-24-12 are superseded by Paragraph (b) and no longer apply when Custom Kit No. 139 (Auto-Ignition System) is installed. The IGN OVRD switch shall be selected to IGN OVRD position during all operations in actual or potential icing conditions described as follows: 1. During During takeoff takeoff and climb out in actual or potential potential icing icing conditions. 2. When ice is visible visible on, or shedding shedding from propeller(s propeller(s), ), spinner(s) spinner(s),, or leading edge(s). 3. Before Before selecting selecting ENG INLET, INLET, when ice has accumulated. accumulated.

NOTE: If icing conditions are entered in flight without the engine anti-icing system having been selected, switch one ENGINE system to ENG INLET position. If the engine runs satisfactoril y, switch the second ENGINE system to ENG INLET position and check that the second engine continues to run satisfactorily.

4. Immediatel Immediatelyy anytime engine engine flameout occurs occurs as a possible possible result result of ice ingestion. 5. During During approach and landing landing while while in or shortly shortly following following flight in actual or potential icing conditions. 6. During takeoff with standing water, slush or powdery snow on runway. For the purpose of the preceding steps, the following definition applies:

1. Potential Potential icing conditions conditions in precipitation precipitation or visible visible moisture meteometeorological conditions: a. Begin when when the OAT OAT is +5°C (+41°F) (+41°F) or colder colder,, and b. End when the OAT OAT is +10°C (+50°F) (+50°F) or warmer warmer.. NOTE: Above procedures supersede any other POH/AFM procedures which may be contradictory.

CAUTION: Flight may be limited by duty cycle of the Ignition System (see page 2-22). Do not operate engine inlet heat system longer than 10 seconds if OAT is greater than H=5°C (+ 41°F).

Ice Protection: Ambient temperatures must be below +5°C for continuous operation if ice protection heat. Intentional stalls are prohibited when wing and empennage boots are operated. Do not operate wing and empennage boots during takeoff and landing. Engine Inlet Ice Protection:

Operation for longer than ten seconds with ambient temperature above +50° is prohibited.



2-23

Operating Temperature Limits (690 B Model)

2-24



Quick Reference Operating Limitations Oil Temperature Minimum Starting

-40°C

Minimum Ground Operation

-40°C

Minimum Flight Operation

+55°C

Maximum All Conditions Oil Pressure

+110°C

Minimum Idle

40 PSI

Minimum Flight Operation < 23,000 ft

70 PSI

Minimum Flight Operation > 23,000 ft

50 PSI

Maximum All Conditions Oil

Lubricants conforming to MIL 23699A, and MIL-L-7808G are approved for use. See Section VIII of Manufacturer’s Pilot’s Operating Handbook for a list of approved lubricants.

Fuel Pressure

Minimum Maximum

Fuel: (Aviation Turbine Fuels)

AiResearch EMS 53100; ASTM Desig- nation ES2-74 and D1655-68T (Types Jet A, A-I and B): MIL-T-5624G(l) (Grades JP-4 and JP-5); and British Specs D. Eng. R.D. 2482 Issue 2, 2486 issue 2, and 2494 Issue 4. NATO equiv- alents approved. Aviation gasoline MIL-G-5572D, Grade 100LL may be used as an emergency fuel with limitations of 250 gallons per engine for each 100 hours of engine operation. The amount of aviation gasoline used must be entered in the Engine Log Book.

120 PSI

15 PSI 90 PSI

See Section of Manufacture’s Pilot’s Operating Handbook for list of approved fuels and temperature limits. Engine Inlet Ice Protection

Operate to 10 seconds maximum with ambient temperature above +5°C



2-25

Propellers: Two Hartzell propellers with LT 10282H+4 blades and hub model HC16-B3TN-5FL are installed. The propellers are 3-blade, full feathering, reversible, constant speed.

Restrictions: Reverse operation is limited to ground operation only.

Diameter: Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 inches Maximum. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 106 inches

Blade Angles (at 30 inch Station): Reverse. Reverse . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -8 (± 0.5)° Start Start Locks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +2.5 (± 0.2)° Low. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +13.5 (±0.5)° Feather. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .+90 (±0.5)°

Propeller Speed Restrictions:

2-26

RPM Range

Time Limit

1591

None

1599 – 1607

5 Minutes

1607 – 1679

30 Seconds

1679 – 1686

5 Seconds



Quick Reference General Types of Operation This aircraft may be operated under the following conditions when the appropriate equipment required by Federal Aviation Regulations is installed and operable: 

Day or Night



VFR or IFR



Flight into known Icing Conditions is approved.

Operational Limitations Model 690B

Altitude Limitations Maximum approved altitude with Type A and A-1 aviation turbine fuel is 31,000 feet MSL. Maximum approved app roved altitude with Type B (JP-4 or JP-5) aviation turbine fuel: With fuel boost pumps pumps inoperative. . . . . . . . . . . . 25,000 ft MSL With fuel boost pumps operating . . . . . . . . . . . . . 31,000 ft MSL Maximum approved altitude using aviation gasoline: With fuel fuel boost pumps inoperative. . . . . . . . . . . . . . . . . 10,000 ft With With fuel boost boost pumps operati operating ng . . . . . . . . . . . . . . . . . . 25,000 ft

Cabin Pressurization Maximum cabin differential differential pressure . . . . . . . . . . . . . . . . 5.4 PSI Relief setting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.2 ± 0.1 PSI Pressurization is prohibited prohibited during takeoff or landing.

Maximum Seating Limits Maximum number of seating . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 (Pilot plus 9 passengers)



2-27

690A B Training Manual

Recommend Documents