Emergency Exits and Evacuation Routes C-40 15 1

WELCOME TO TECHNICAL ORDER 00-105E-9, 1 FEBRUARY 2006, REVISION 11. THIS IS SEGMENT 6 COVERING CHAPTER 6 FROM THE C-21 TO THE C-40.

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WRITTEN CORRESPONDENCE:

HQ AFCESA/CEXF ATTN: Fire and Emergency Services Egress Manager 139 Barnes Drive Suite 1 Tyndall AFB, Florida 32403-5319

E-MAIL: [email protected]

INTERNET: HQ AFCESA Fire and Emergency Services PUBLIC WEB PAGE: http://www.afcesa.af.mil/CEX/cexf/index.asp Safety Supplements: http://www.afcesa.af.mil/CEX/cexf/_firemgt.asp

PHONE: (850) 283-6150 DSN 523-6150

FAX: (850) 283-6383 DSN 523-6383

For technical order improvements, correcting procedures, and other inquiries, please use the above media most convenient. SEGMENT 6 INFORMATION CHANGE NOTICE This page is provided to notifiy the user of any informational changes made to Technical Order 00-105E-9 in this Segment and the current Revision. Informational changes will be referenced in the Adobe Reader’s Bookmark tool as a designator symbol illustrated as a <[C]> for quick reference to the right of the affected aircraft. The user shall insure the most current information contained in this TO is used for his operation. Retaining out of date rescue information can negatively affect the user’s operability and outcome of emergencies. If the user prints out pages his unit requires, the user shall print the affected page(s), remove and destroy the existing page(s), and insert the newly printed page(s) in the binder provided for that purpose. A Master of this TO shall be retained in the unit’s library for reference, future printing requirements and inspections.

CHAPTER AIRCRAFT PAGE EXPLANATION OF CHANGE None. TO 00-105E-9 NOTE

Chapter 6 contains emergency rescue and mishap response information for the following aircraft:

USAF C-5 USAF C-7 USAF (V)C-9A/C USAF C-12C/D/F USAF C-12J USAF C-17A USAF C-18 USAF C-18D USAF C-20 USAF C-20H USAF C-21 USAF C-22B USAF C-23A USAF C-26 USAF C-27A USAF C-32A USAF C-37A USAF C-38A USAF C-40 USAF C-130 USAF C-130J USAF C-135 USAF NC-135W USAF RC-135S USAF RC-135U USAF RC-135V/W USAF TC-135S USAF TC-135W USAF WC-135C USAF WC-135W USAF (V)C-137 USAF C-141 USAF NC-141A USAF C-212 USAF KC-10A

Chapter 6 Cover C-21. T.O. 00-105E-9 SPECIAL TOOLS/EQUIPMENT C-21

1 Power Rescue Saw AIRCRAFT ENTRY

1. NORMAL ENTRY FUSELAGE TANK a. Lift handle and rotate handle clockwise to 200 US GALS release upper half of door. FUEL TIPTANK 175.3 US OXYGEN b. Raise upper door. GALS CYLINDER c. Rotate lower door handle, located in interior center of lower door, to the open BATTERIES position. FERRY TANK d. Release safety catch, located on left end 191 US GALSIN of lower door, and gently lower door to full CABIN WHEN open position. INSTALLED 187.1 US GALS

2. EMERGENCY ENTRY

NOTE: WING FUEL Emergency escape window is the fourth 1a TANK window on the right side. EXTERIOR UPPER a. Depress button marked PUSH and rotate DOOR handle down. HANDLE

b. Push the window into cabin.

3. CUT-IN

NOTE: Do not attempt to chop windshield. 2a EMERGENCY ESCAPE a. Cut around side windows as required. WINDOW HANDLE 1c INTERIOR UPPER DOOR EMERGENCY EXIT HANDLE RELEASE HANDLE & TURN 1d SAFETY CATCH C-21. T.O. 00-105E-9 ENGINE SHUTDOWN AND 1b C-21 2 AIRCREW EXTRACTION ENGINE FIRE T-HANDLES 1. ENGINE SHUTDOWN

a. Simultaneously lift locking mechanism and pull Thrust Levers AFT into the cut-off position.

b. Pull Engine Fire T-Handles, located on upper portion of pilot’s instrument panel.

c. Place battery (2) switches, located on lower left of pilot’s instrument panel, to the OFF position.

2. AIRCREW EXTRACTION

a. Unlatch lap belts and remove shoulder harness from crewmember(s).

NOTE: Passenger seats are equipped with lap belts only.

1a THRUST LEVERS

1a CUT-OFF POSITION 1a LOCKING MECHANISMS

1c BATTERY SWITCHES T.O. 00-105E-9 C-22B. AIRCRAFT DANGER AREAS C-22B

1 JT8D TURBOFAN ENGINE HAZARD AREAS AT IDLE THRUST

AXIAL DISTANCE BEHIND AIRCRAFT FEET 0 30 60 90 120 150

0 10 20 30 40

METERS INTAKE DANGER AREAS

M F 10 100 MPH 50 MPH 30 18 FEET (161 KMPH) (80 KMPH) 20 5 10 0 0 10 5 20 18 FEET 200 0 F 100 0 F (93 0 C) (38 0 C) 30 10 INTAKE DANGER AREAS DISTANCE FROM AIRCRAFT CENTERLINE

4 FEET

NOSE COWL FORWARD EDGE T.O. 00-105E-9 C-22B. AIRCRAFT DANGER AREAS-Continued C-22B JT8D TURBOFAN ENGINE HAZARD AREAS 2 AT TAKEOFF THRUST

AXIAL DISTANCE BEHIND AIRCRAFT

FEET 0 50 100 150 200 250 300

0 10 20 30 40 50 60 70 80 90 100

METERS

50 MPH (80 KMPH) 100 MPH (TO 512 FT M 150 MPH F 400 MPH 300 MPH 200 MPH (161 KMPH) 157M) 10 (240 KMPH) (644 KMPH) (483 KMPH) (322 KMPH) 30 25 FEET 20 5 10 0 0 10 5 20 INTAKE DANGER AREAS 30 0 0 10 25 FEET 0 0 100 F (38 C) 300 0 F 200 F 150 F 0 0 DISTANCE FROM (1490 C) (93 C) (65 C) AIRCRAFT CENTERLINE T.O. 00-105E-9 C-22B. AIRCRAFT DANGER AREAS-Continued C-22B WHEEL AND/OR BRAKE FIRES: 3 Wheels are equipped with fusible plugs designed to melt and deflate the tire when the temperature is excessive. Use of BCF (halon) is preferred if tires are pressurized. Dry chemical, fog, or foam are acceptable. If all tires are deflated, any fire extinguishing agent may APU POWER be used. Cool down time for hot brakes is 40 minutes minimum. PLANT APU EXHAUST

WARNING

Approach landing gear from forward or aft of wheel when fighting a wheel fire as wheels and tires may explode.

NOTE: • Radar systems are not normally operated during ground operations of the aircraft. Be aware that radar may be running during an emergency, but does not pose a threat if exposure is minimal. APU INTAKE

• The APU is located between the left and right wheel wells. The intake is in the LH wheel well and the exhaust is in the top rear wing root area of the right wing. LEFT AND RIGHT MAIN LANDING GEAR WHEEL WELL • The main and APU batteries are located in the pressurized electronic equipment compartment access door. The battery is BATTERY CONNECTION equipped with a 115 degree F. temperature switch. Disconnect the battery cable by loosening the hand knob and lifting the plug off of the terminals.

MAIN BATTERY

ACCESS DOOR

APU BATTERY T.O. 00-105E-9 C-22B. AIRCRAFT FLAMMABLE MATERIAL C-22B NOTE: 4 Crew and passenger oxygen bottles are located in the forward baggage compartment just aft of the door. Each bottle has a shutoff valve located on the top of the bottle.

AFT CARGO FUEL TANKS (OPTIONAL) (860 US GALS) (1070 US GALS)

HYDRAULIC RESERVOIR FORWARD CARGO FUEL TANKS (AIRSTAIR PASSAGE) (OPTIONAL) (810 US GALS) OXYGEN VENT SURGE TANK (810 US GALS) BOTTLES (PORTABLE) FUEL LINES FUEL TANK (US GALS) 1793 APU(WHEEL HYDRAULIC ACCUMULATOR WELL) (AIRSTAIR PASSAGE)

FIRE EXT PORT (OUTBD ENG ONLY) OXYGEN BOTTLES ENGINE OIL TANK (TYPICAL) (PORTABLE) HYDRAULIC ACCUMULATOR(WHEEL WELL)) OXYGEN BOTTLES (PASSENGER 4094 AND CREW) APU EMERGENCY CONTROL PANEL (LEFT WHEEL WELL AREA)

1793 FUEL TANK

FUEL TANK OXYGEN VENT SURGE TANK BOTTLE (PORTABLE) OXYGEN BOTTLE (PORTABLE) T.O. 00-105E-9 C-22B. AIRCRAFT EMERGENCY RESCUE ACCESS C-22B NOTE: 5 The C-22B is a Boeing 727-100 airframe. Model differences for the 100, 200 and 200F are depicted.

AFT ENTRY DOOR (OPENS FROM INSIDE OF THE AFT- CHOP OUT AREAS STAIRS AREA) (AIRSTAIR MUST FIRST BE LOWERED)

AFT AIRSTAIR EXTERIOR OVERWING ESCAPE HATCHES CONTROL PANEL OPER- ATING INSTRUCTIONS ON ACCESS PANEL

AFT AIRSTAIR CHOP OUT AREA

GALLEY DOOR (MOVED AFT EXIT DOORS (REMOVED FORWARD ON MODEL ON 100 AND 200F MODELS) 200 - REMOVED ON 200F)

FORWARD ENTRY DOOR OVERWING ESCAPE HATCHES

CHOP OUT AREA FLIGHT DECK CARGO DOOR SLIDING WINDOW 5 FT 8 IN (FLOOR LEVEL TO GROUND, WHEELS RETRACTED)

9 FT 1 IN (FLOOR LEVEL TO GROUND, WHEELS EXTENDED) T.O. 00-105E-9 C-22B. AIRCRAFT EMERGENCY AND LAVATORY C-22B Fire Extinguisher (Thermal)

6 SAFETY EQUIPMENT Smoke Detector FORWARD ENTRY DOOR Slide Press Gauge FORWARD STORAGE COMPARTMENT Fire Extinguisher (water) (LPU (2) Signal Kit EEBD Emergency Flashlights

OVERHEAD BIN (Row 1) OVERHEAD BIN (Row 2) First Aid Kit OXYGEN BOTTLES (2) Megaphone

BULKHEAD Life Raft (2) GALLEY GALLEY Fire Extinguisher (HALON) Firefighter’s Gloves EEBD GALLEY DOOR Slide Press Gauge OVERHEAD BIN (Row 7) Light Switches First Aid Kit Water Quantity Gauge Compressor Switch

OVERHEAD EXITS OVERHEAD EXITS Escape Ropes Escape Ropes

OVERHEAD BIN (Row 17) LPU Demo (2) AFT CABIN WALL Megaphone Fire Extinguisher (HALON) First Aid Kit AFT STORAGE COMPARTMENT EEBD VIP Kit AFT CABIN WALL LPU (3) Oxygen Bottles (2) LAVATORY Barrier Strap Fire Extinguisher (Thermal) Smoke Detector AFT JUMPSEAT AREA AIRSTAIR AREA Emergency Light Switch Aft Airstair Control Fire Extinguisher (Water) Emergency Flashlight (2) T.O. 00-105E-9 C-22B. SKIN PENETRATION POINTS C-22B 7

NOTE: The C-22B is a 727-100 model. T.O. 00-105E-9 C-22B. SKIN PENETRATION POINTS-Continued C-22B

8 ENGINE PENETRATION POINTS LEFT SIDE OF ENGINE RIGHT SIDE OF ENGINE T.O. 00-105E-9 C-22B. SPECIAL TOOLS/EQUIPMENT Aircraft Dimensions C-22B Power Rescue Saw Length 153’ 2”

9 12 Foot Ladder Wing span 108’ 0” VENT Fire Drill II Height 34’ 0” SURGE AIRCRAFT ENTRY TANK 1. NORMAL ENTRY

WARNING

If Forward Entry Door is used for rescue, passenger escape chute-slide will be actuated if not disconnected from inside. WING FUEL TANK a. RIGHT FORWARD ENTRY DOOR - Pull handle outward, OXYGEN rotate clockwise and pull door outward to open position. BOTTLES

2. EMERGENCY ENTRY BATTERIES a. OVERWING ESCAPE HATCHES - Push panel in, located 1a, 2b 2d top center of hatches, and push hatches inward and up. EXTERNAL HANDLE DOOR HANDLE b. FORWARD ENTRY DOOR - Pull external handle, located on entry door, outward; rotate clockwise and pull door out CUT-IN to open position. AREAS c. MID GALLEY DOOR - Pull external handle, located on galley door right forward side outward; rotate counterclockwise and pull door out to open position. d. AFT EXIT DOORS - Pull lower end of handle, located top MID GALLEY DOOR AIRCRAFT CROSS SECTION center of door left side of fuselage, outward; rotate clock (RIGHT SIDE ONLY) AFT DOOR EXIT wise and pull door outward. (Turn handle counterclockwise AFT ENTRY DOOR on doors located on right ride of fuselage.) e. AIRSTAIR ENTRY DOOR - Depress latch on access door, located right side aft fuselage, and pull handle down to release stairway. (Stairway can jack aircraft up for passen- AFT AIRSTAIR ger escape in a no-gear situation.) FORWARD 3a EMERGENCY OVERWING f. AFT ENTRY DOOR - Rotate handle, located on aft entry ENTRYDOOR ESCAPE HATCHES door, clockwise and push door inward. 2a HYDRAULIC PANEL 3. CUT-IN HANDPUMP 2c a. Cut tenth window aft from crew compartment and fifth EXTERNAL window forward from tail section as last resort. HANDLE AIRSTAIR DOOR RELEASE HANDLE NOTE: Oxygen, rafts, flashlights, and fire extinguishers are located in overhead compartments. T.O. 00-105E-9 C-22B. ENGINE AND APU SHUTDOWN C-22B

10 1. ENGINE AND APU SHUTDOWN

a. Retard throttles or thrust levers, located on pilot’s center console, to the CLOSED position.

b. Restart start levers, located on pilot’s center 1f console, to IDLE CUTOFF position. BATTERY 1c SWITCH ENGINE FIRE T-HANDLES c. In case of engine fire, pull engine fire T-handle, located on center ceiling control panel or on 1d pilot’s light shield, for appropriate engine. Acti- APU vate discharge switches as necessary. FIRE SWITCH

d. In case of APU fire, pull APU fire switch located on rear flight deck wall. Activate discharge switch as necessary. NOTE: OPTIONAL LOCATION FOR e. Place Master Switch, located on rear flight deck T-HANDLES IS ON THE wall, down to OFF position. PILOT’S LIGHT SHIELD.

1e f. Locate Battery Switch, located on upper left flight MASTER engineer’s panel, lift switch guard up and place SWITCH switch in OFF position.

1a THRUST LEVERS

REAR FLIGHT DECK WALL 1b ENGINE START LEVERS CUTOFF POSITION T.O. 00-105E-9 C-22B. AIRCREW EXTRACTION C-22B 2. AIRCREW EXTRACTION 11

NOTE: If seat tracks are not damaged during crash landing, use adjustable seat control SHOULDER HARNESSES handles to retract seats to aft position. ARMREST ADJUSTMENTS Third crewmember may have to be ex- tracted first to make room for the pilot and LAP AND co-pilot seat adjustments. CROTCH BELT a. Unlatch lap belt and remove shoulder harness from pilot and co-pilot by rotating ROTARY the rotary buckle. BUCKLE

b. For easier extraction, use seat adjustments for fore and aft, vertical, recline, and inside armrest. SEAT SEAT DIAS STOP c. Unlatch lap belt and remove shoulder VERTICAL harness from flight engineer or third ADJUSTMENT crewmember by rotating the rotary buckle. RECLINE ADJUSTMENT SEAT FORE AND AFT ADJUSTMENT TRACK d. For easier extraction, use seat adjustments for fore and aft, vertical, and swivel SWIVEL SHOULDER HARNESS SWIVEL 360 DEGREE for facing positions. Depress swivel seat CONTROL VERTICAL TRAVEL IN 30 DEGREE control handle and rotate seat clockwise LEVER CONTROL INCREMENTS OF so that crewmember faces aft. LEVER ADJUSTMENT

e. Passenger seats are equipped with lap belts only. LAP BELT ROTARY BUCKLE NOTE: CROTCH BELT Co-pilot’s seat controls located opposite. C-23A. T.O. 00-105E-9 SKIN PENETRATION POINTS C-23A 1

FUSELAGE (BOTH SIDES) AFT OF AND BELOW THE TRAILING EDGE OF THE WING

AFT FUSELAGE (LEFT SIDE) FORWARD OF DOOR ON LEFT SIDE AT APPROXIMATELY F.S. 370 IN LINE WITH THE VERTICAL CENTER OF THE DOOR.

ENGINE NACELLES (OUTBOARD SIDE EACH ENGINE) BELOW THE ENGINE CENTERLINE. FORWARD FUSELAGE (BOTH SIDES) AFT IN LINE WITH THE WING’S LEADING EDGE. OF FORWARD DOOR AT APPROXIMATELY F.S. 153 IN LINE WITH THE VERTICAL CENTER OF THE DOOR WINDOW. C-23A. T.O. 00-105E-9 SPECIAL TOOLS/EQUIPMENT C-23A Power Rescue Saw

2 14 Foot Ladder Fire Drill II

AIRCRAFT ENTRY BATTERIES 1. NORMAL ENTRY 336 a. Turn handle on main cabin entry door clockwise 336 and pull to open. EMERGENCY BATTERY b. Turn handle on forward cargo loading door clockwise and pull to open.

2. EMERGENCY ENTRY OXYGEN BOTTLES a. Turn handle on any of two forward emergency exits left and right clockwise and pull to open. 3a 2b EMERGENCY CUT-IN AREAS FLIGHT COMPARTMENT b. Turn handle on flight compartment emergency EMERGENCY EXIT HANDLE exit clockwise and pull to jettison.

c. Turn handle on main cabin entry door clockwise and pull to open.

d. Turn handle on forward cargo loading door 1a , 2c clockwise and pull to open. MAIN CABIN ENTRY DOOR HANDLE

3. CUT-IN

a. Cut-in area each fuselage side aft of wing. 1b, 2d FORWARD CARGO DOOR HANDLE 2a LEFT FORWARD FUSELAGE 2a EMERGENCY DOOR HANDLE RIGHT FORWARD FUSELAGE EMERGENCY DOOR HANDLE C-23A. T.O. 00-105E-9 ENGINE SHUTDOWN AND C-23A 1b 3 AIRCREW EXTRACTION 1a LP VALVE LEVERS FUEL CONDITION LEVERS 1. ENGINE SHUTDOWN

a. Retard fuel levers, located on center console, to OFF position.

b. Retard LP valve levers, located in overhead console, to SHUT position.

c. If fire buttons are illuminated or if there is evidence of fire in the vicinity of the engines, actuate the Fire Extinguisher Push Buttons located in the center overhead engine services CENTER CONSOLE panel. OVERHEAD d. Place electrical master switch, located left CONSOLE overhead electrical switch panel, to OFF position.

2. AIRCREW EXTRACTION

a. Unlatch lap belts and remove shoulder harness from crewmembers.

NOTE: Passenger seats are equipped with lap belts only.

1c 1d EXTINGUISHER MASTER SWITCH PUSH BUTTONS

LEFT OVERHEAD ELECTRICAL SWITCH PANEL C-26. T.O. 00-105E-9 AIRCRAFT DIMENSIONS C-26 1 WING SPAN 57 FT 0 IN (17.37M)

LENGTH 59 FT 4.25 IN (18.09 M)

HEIGHT 16 FT 8 IN 5.08 M) C-26. T.O. 00-105E-9 AIRCRAFT HAZARDS C-26

2 NOTE: The C-26 is a joint service aircraft used by the USAF, US Army, US Navy, and State Department for drug interdiction. CAWI SWITCH RH CAWI ALCOHOL-WATER (AWI) FLUID MIXTURE LH CAWI CAWI MANIFOLD The C-26 (SA 227-DC model) uses an alcohol-water mixture MANIFOLD PRESSURE SWITCH CAWI composition (CAWI system) with a quantity of 14 US gallons or CAWI PRESSURE 54 liters. The mixture is Methyl Alcohol 40% and water 60%. SHUTOFF REGULATOR SWITCH Prior to flight the CAWI tank will be full. The interconnected CENTER VALVE DRAIN VALVES storage tanks are located between the fuselage lower skin and PEDESTAL the wing belly panel. Common plumbing is routed through each CAWI wing leading edge to each engine. PRESSURE SWITCH WARNING CAWI CAWI Methyl Alcohol (Methanol) is a violent poison and can not be LH TANK RH TANK made non-poisonous. In case of accidental contact, flush with water immediately. Methanol vapors are toxic and RH ENGINE extremely flammable. Do not smoke, generate sparks, or LH ENGINE expose Methanol to open flame. CAWI DISTRIBUTION OXYGEN BOTTLE AND SHUTOFF VALVE LOCATION SYSTEM

The C-26 (SA 227-DC) contains one oxygen bottle located beneath the equipment rack aft of the aft cargo compartment bulkhead. Oxygen lines are routed to the pilot and co-pilot and EQUIPMENT along the right side of the fuselage to the passengers. A shut-off RACK valve is located on each regulator.

EQUIPMENT RACK OXYGEN SHUTOFF VALVE

OXYGEN 49 CU. FT. SHUTOFF OXYGEN VALVE OXYGEN BOTTLE EQUIPMENT BOTTLE RACK C-26. T.O. 00-105E-9 AIRCRAFT HAZARDS-Continued C-26 3 1. BATTERY DISCONNECT

NOTE: Aircraft is equipped with two 24 volt 23 Ah Ni/Cd batteries.

a. Remove battery access panels from upper surface of 1a left and right inboard wing. ACCESS PANEL b. Disconnect main battery quick disconnect by turning battery (TYPICAL) disconnect knob counterclockwise.

c. Disconnect minor battery quick disconnects by turning 1c connectors counterclockwise. 1b MINOR DISCONNECT BATTERY 1b (TYPICAL) BATTERY DISCONNECT

1b DISCONNECT KNOB

1c MINOR DISCONNECTS C-26. T.O. 00-105E-9 SPECIAL TOOLS/EQUIPMENT NOTE: FUEL TANKS Power Rescue Saw C-26 4 Oxygen system (324 US GALS EACH) 6 Foot Ladder is 1850 PSI. OPTIONAL AIRCRAFT ENTRY- SA226/227 MODELS BULKHEAD ESCAPE 1. NORMAL/EMERGENCY ENTRY HATCHES a. Push in on forward end of entry door handle. Door is located on forward left side of aircraft. BATTERIES OXYGEN-49 CU.FT ENGINE OIL BOTTLE (SA227) b. Rotate entry door handle down, clockwise, to open. AFT CARGO OXYGEN COMPARTMENT (SA226) c. Pull out on door handle. (Door is hinged at the bottom and DOOR will rotate out from the top). 1a ENGINE HYDRAULIC FORWARD 2. CARGO DOOR AND PASSENGER BULKHEAD OIL 4 US RESERVOIR ENTRY DOOR GALS 8 US GALS 5 FT. WINGTIP EXTENSION a. The cargo door handle operates same as the forward (SA227 ONLY) entry door handle. Cargo door must be lifted up to open. Cargo door is located on aft left side of aircraft. 1a

b. Optional bulkhead separates passenger compartment FORWARD ENTRY DOOR and cargo compartment. The bulkhead may be remov- HANDLE CLOSED able and may contain a door. Can also be used as an emergency entry and exit. 1a 3. CUT-IN FORWARD ENTRY DOOR a. Cut along window lines. There are no cut-in marks 1a HANDLE OPEN painted on the aircraft. The area 14 inches above FORWARD ENTRY and 3 inches below the window will offer the least DOOR WITH STEPS resistance for forced entry.

2a CARGO 2b DOOR REMOVABLE PASSENGER BULKHEAD WITH DOOR C-26. T.O. 00-105E-9 EMERGENCY EXITS AND C-26 5 PERSONNEL EGRESS 1. EMERGENCY EXITS

NOTE: Escape hatches (windows) cannot be opened from outside the aircraft. Two hatches are located on the overwing right side and one hatch is located on the overwing left side of aircraft. Do not use as an entry.

a. Pull emergency handle, located above each emergency EMERGENCY EXIT HATCH WINDOWS exit hatch window. (RT SIDE VIEW)

b. Pull hatch inward and place to the side or discard outside. Hatch opening can now serve as an exit for passengers and an entry point for rescue team members. 1a 2. PERSONNEL EGRESS EMERGENCY EXIT HATCH NOTE: HANDLE Although not recognized by the FAA as an emergency exit, the cargo door (which can be opened from inside the aircraft) is available as an emergency exit.

WARNING

Do not use main entry door for emergency exit if left engine 2a is still running. Personnel can walk into path of rotating PERSONNEL propellers causing serious injury or death. EGRESS ROUTES a. Pesonnel can egress through main entry doorway, and three emergency exits over the wings.

b. As an alternative, if time permits, remove the aft cargo compartment bulkhead or open cargo compartment door 2a and open the cargo doorway and exit. Cargo/baggage may CARGO have to moved out of the way to exit. COMPARTMENT EXIT C-26. T.O. 00-105E-9 ENGINE SHUTDOWN C-26

6 1. ENGINE SHUTDOWN

a. Ensure at least one battery switch is ON (forward position). Battery switches are located straight forward of pilot’s control column.

b. Push stop buttons, located below left instrument panel. (Approx. 5 inches to right of battery switches.) 1b STOP c. Place both battery switches to OFF (center) BUTTONS position. 1a, 1c BATTERY SWITCHES d. Pull both engine stop and feather knobs, located on center pedestal just below engine controls, full aft. Controls are red.

1d ENGINE STOP AND FEATHER KNOBS C-26. T.O. 00-105E-9 CABIN CONFIGURATION C-26 7 AND AIRCREW EXTRACTION 1. CABIN CONFIGURATION 530.810” BAGGAGE DOOR 305.00” CARGO a. C-26A typical interior cabin configuration and TOILET arrangement. Accomodation: flight deck: 2, ESCAPE ESCAPE NET passenger compartment: 18.

2. AIRCREW EXTRACTION 1 2 3 4 5 6 7 8 9 10

NOTE: 25” ESCAPE Crew seat armrests can be lowered by AVIONICS 30” 53” PASSENGER EQUIPMENT depressing a latch under the arm rest. BAY BAGGAGE SEAT CARGO ENTRANCE RACK AND DOOR PITCH DOOR GALLEY a. Unlatch pilot and co-pilot lap belts and shoulder harness (es)

b. Unlatch passenger lap belts.

NOTE: If seat tracks are not damaged due to crash, 5 FT 1/4 IN seat adjustment levers, located inboard of each seat at floor level, can be used to retract seat to full aft position. Passenger seats may or may ROWS 2 - 9 ROW 10 CARGO DOOR not be equipped with shoulder harnesses. (TYPICAL) T.O. 00-105E-9 C-27A 34’ 7” (10570) 15’ 6” (4750) 12’ 0” (3668) 18’ 5” (5650) ELEV AXIS HORIZ 15’ 6” (4750) SKIN PENETRATION POINT (LEFT SIDE) SKIN PENETRATION LANDING GEAR MAX EXT 74’ 5” (22700) 20’ 5” (6235) SKIN PENETRATION POINTS 11’ 7” 11’ (3560) 94’ 2” (28700) 40’ 7” (12400) NOTE: are in feet/inches (in millimeters). All dimensions AIRCRAFT DIMENSIONS AND SKIN PENETRATION POINTS PENETRATION SKIN AND DIMENSIONS AIRCRAFT C-27A.1 T.O. 00-105E-9 C-27A H APU TURBINE DISK E ENGINE PROPELLER DISK F STARTER B PROPELLER BLAST C ENGINE EXHAUST GASES D APU EXHAUST GASES G ENGINE TURBINE DISK A PROPELLER ZONE DISINTEGRATION 0 PROPELLER SUCTION AND BLAST ENGINE EXHAUST APU ENGINE EXHAUST DISTANCE FEET 0 4 25 50 100 DISTANCE TEMPERATURE C 500 130 50 C 500 TEMPERATURE AIRCRAFT HAZARDS INFORMATION HAZARDS AIRCRAFT C-27A. 2 T.O. 00-105E-9 C-27A OF AIRCRAFT RADOME 7 FEET 180 DEGREES MPEL BOUNDARY MAXIMUM PERMISSIBLE EXPOSURE LEVEL (MPEL) EXPOSURE MAXIMUM PERMISSIBLE radiation level the envelope in which the In order to avoid of 10 mW per Government standard exceeds the U.S. the should remain beyond all personnel square centimeter, to The distance in the illustration below. distance indicated upon the basis of the the MPEL boundary is calculated the system, rated output largest antenna available with in the non-rotating or boresight power of the transmitter and a scanning beam, the power position of the antenna. With is significantly reduced. density of the MPEL boundary AIRCRAFT HAZARDS INFORMATION-Continued HAZARDS AIRCRAFT C-27A. 3 T.O. 00-105E-9 C-27A NO. OF PLACES 12 NO. OF PLACES 12 TYPE OF SEAT 6 DOUBLE TYPE OF SEAT 6 DOUBLE TYPE OF SEAT ROW B ROW A ROW B ROW A TROOP TRANSPORT CONFIGURATION TROOP TRANSPORT MAXIMUM 34 SEATS FRAME 9 11 13 15 18 20 23 25 27b 29 31 33 13 15 18 20 FRAME 9 11 NUMBER OF SEATS PER COMPARTMENT NUMBER OF SEATS I L M N C D E F G H COMPARTMENTS O TROOP TRANSPORT 2 4 4 4 4 4 4 2 4 2 CONFIGURATION 2 4 4 4 4 4 2 PARATROOP CONFIGURATION COMPARTMENTS C D E F G H I K L M N COMPARTMENTS NUMBER OF SEATS PER ROW IN PARATROOP CONFIGURATION NUMBER OF SEAT PER ROW IN NUMBER OF SEAT CONFIGURATION PER ROW IN PARATROOP NUMBER OF SEATS CONFIGURATION MAXIMUM TROOP PARATROOP 24 SEATS CONFIGURATION TROOP TRANSPORT ROW A ROW A NO. OF PLACES 17 7 DOUBLE TYPE OF SEAT 3 SINGLE ROW B ROW B NO. OF PLACES 17 7 DOUBLE TYPE OF SEAT 3 SINGLE AIRCRAFT CONFIGURATIONS AIRCRAFT C-27A.4 T.O. 00-105E-9 C-27A MATERIAL TRANSPORT CONFIGURATION TRANSPORT MATERIAL TROOP SEATS ON THE RAMP ON TROOP SEATS (SINGLE TYPE) TROOP SEAT SIDE ROWS TROOP SEAT TROOP TRANSPORT CONFIGURATION TROOP TRANSPORT - 32 PERSONNEL TROOP/PASSENGERS AIRCRAFT CONFIGURATIONS-Continued AIRCRAFT C-27A.5 T.O. 00-105E-9 C-27A PERSONNEL SEATS ROWS OF STRETCHERS AEROMEDICAL EVACUATION CONFIGURATION AEROMEDICAL EVACUATION AEROMEDICAL - 24 LITTERS AND 5 ATTENDEES STATIC LINE ANCHOR CABLE RETRIEVAL WINCH RETRIEVAL RETRIEVAL WINCH RETRIEVAL PARATROOP AIRDROP CONFIGURATION PARATROOP - 24 PERSONNEL PARATROOPERS AIRCRAFT CONFIGURATIONS-Continued AIRCRAFT C-27A.6 T.O. 00-105E-9 C-27A LT MAIN FUEL TANK - 898 US GALS FUEL TANK MAIN LT CARGO DOOR LT AUX. FUEL TANK - 687 US GALS TANK AUX. FUEL LT PARATROOP DOOR PARATROOP 1b PARATROOP DOOR UNLOCK HANDLE BATTERY COMPARTMENT BATTERY ELECTRICAL GROUND CONNECTION OXYGEN CONVERTERS HYDRAULIC GROUND CONNECTION CARGO COMPARTMENT APU CREW ENTRANCE DOOR PARA- TROOP DOOR EMERGENCY EXITS EMERGENCY NOTE: 3170 US GALS. FUEL - TOTAL 1a EXTERNAL CONTROL HANDLE INSTRUMENT PANEL MAIN & AUXILIARY FUEL TANKS PILOT’S & CO-PILOT’S SEATS THIRD CREW MEMBER’S SEAT WEATHER & WEATHER SEARCH RADAR crew entrance door, located bottom crew entrance door, Door is equipped with a center of door. stairway. the fuse- on the right and left sides of fairings. lage, behind the landing gear the The doors are opened by rotating unlocking handle clockwise and pushing (or pulling) inward and sliding the doors upward. backbone. The located on the aircraft’s unlock handles are located at center of each hatch and can be unlocked by depressing two throttle buttons and rotating the handle clockwise. Hatches are hinged and will open inward. of aircraft opposite crew entrance door, can be opened by depressing hatch button and rotating hinged lever downwards to unlock the hatch bolts. Hatch is hinged and will open inward. SPECIAL TOOLS/EQUIPMENT SPECIAL Rescue Saw Power Fire Drill II AIRCRAFT ENTRY ENTRY 1. NORMAL a. on the Pull the external control handle b. located The two paratroops doors are 2. EMERGENCY ENTRY a. are three upper exit hatches There b. exit hatch, located on right side A toilet C-27A.7 T.O. 00-105E-9 C-27A ESCAPE ROUTE 3a CARGO RAMP 1 EMERGENCY ENTRY 1. ROTATE HANDLE TO OPEN POSITION. 2. PUSH DOOR INWARD TO STOPS. 3. FORCE DOOR OVER STOPS BY PUSHING UPWARD AND INWARD ON LOWER DOOR SURFACE. OPEN CLOSED PULL & TURN 4b TROOP DOOR (EXTERIOR) CLOSED OPEN 2a TURN PULL & TURN CLOSED 1 EXITS ON GROUND EXITS IN FLIGHT 2c OPEN 2b 4a TROOP DOOR (INTERIOR) unlocked, by pulling a ring located on the upper aft unlocked, by pulling a ring part of each window. defined by black paratroop door on the fuselage corner markings. counterclockwise, push door inward to stops, and force door over stops by pushing upward and inward on lower door surface. handle and rotate clockwise, pull door inwards using upper left hand hold, and force door over stops by pulling upward and inward on lower door surface. AIRCRAFT ENTRY-Continued AIRCRAFT NOTE: hatches are installed, entry through If pip-pins accomplished. Pip-pins prevent cannot be before opening. They will be removed accidental flight. c.once Flight compartment windows can be removed 3. CUT-IN a. rear of each cut-in areas are provided to the Two DOOR OPERATION 4. PARATROOP a. from the outside, rotate center handle Unlocking b. from the inside, raise and turn center Unlocking NOTE: All aircraft doors and hatches (with the exception windows that can be and copilot’s of pilot’s opened from the inside) can be opened both from inside and outside and for this reason can be used both to evacuate the aircraft in case of emergency, and to carry out rescue operations from the outside. C-27A. 8 T.O. 00-105E-9 C-27A FORWARD VIEW FORWARD OF MOUNTED LADDERS LEADING TO EMERGENCY OPENING HATCH RELEASE LEVER LOWER END OF LADDER DETAIL LADDER STUDS FASTENING LADDER HOLD-DOWN UPPER END OF LADDER DETAIL WARNING down. (See detail A.) down. (See detail (See detail B.) fastening studs on the floor. AIRCRAFT ENTRY-Continued AIRCRAFT Upper exit hatches open inward and can cause head injuries if allowed to free fall. 5. EMERGENCY HATCH ACCESS LADDER ACCESS HATCH 5. EMERGENCY INSTALLATION a. hold at the ladder into the ladder Insert the upper end b. Push the ladder upward. c. Align with the fastening studs on the floor. d. it engages with the Push the ladder downward until NOTE: at each upper exit Escape ropes are provided hatch. Length of rope is approximately 20 ft. C-27A. 9 T.O. 00-105E-9 C-27A PROPELLER CONDITION AND ENGINE CONDITION BATTERY SWITCH BATTERY FIRE “T” HANDLES head console. handle does pulling the FIRE PULL sector, system. not operate the propeller feathering CAUTION If the engine is at a high power setting, pulling the FIRE PULL handle or placing the PROP will cause an COND lever to FEATHER condition. OVERTORQUE persists, to discharge agent. ENGINE SHUTDOWN AND SHUTDOWN ENGINE EXTRACTION AIRCREW 1. ENGINE SHUTDOWN 1. ENGINE a.located at center over- Pull Fire T-handles NOTE: is in the REVERSE When the POWER lever b. COND lever in feather position. Place PROP. c. position. Place ENG. COND lever in STOP d. FIRE T-handles, if a fire indication Push e. SWITCH to OFF. the BATTERY Place f. Extract personnel and evacuate aircraft. C-27A.10 T.O. 00-105E-9 C-27A LATRINE LOADMASTER SEAT PILOT SEAT CO-PILOT SEAT OBERSERVER/INSTRUCTOR SEAT OBERSERVER/INSTRUCTOR dial at the center hook-up point for the pilot/ dial at the center seats. copilot and observer/instructor by adjusting the Extraction can be made easier position. Ob- crew seats to the fully outboard be adjusted fully aft, server/instructor seat should then reposition seat fully extract crewmember, of pilot and forward allowing room for extraction copilot. Passengers do not have shoulder harnesses. Release passengers from two point seat belts. 2. AIRCREW EXTRACTION rotating the four point harnesses by a. Release the from his seat by b. Release the loadmaster seat belt. releasing the two point c. d. AIRCREW EXTRACTION-Continued AIRCREW C-27A.11 T.O. 00-105E-9 C-27A HARNESS REEL RECLINE CONTROL VERTICAL ADJUSTMENT CONTROL LUMBAR CONTROL UP/DOWN THIRD CREW MEMBER’S SEAT (UPPER AND LOWER GRAPHIC) ADJUSTABLE THIGH SUPPORT ARMREST ADJUSTMENT CONTROL ROTATION CONTROL HORIZONTAL ADJUSTMENT CONTROL LUMBAR CONTROL IN/OUT HARNESS REEL LOCK CONTROL THIGH SUPPORT CONTROL HARNESS REEL RECLINE CONTROL VERTICAL ADJUSTMENT CONTROL THIGH LOCK CONTROL LUMBAR CONTROL UP/DOWN PILOT’S AND CO-PILOT’S SEAT (UPPER AND LOWER GRAPHIC) TRANSVERSAL ADJUSTMENT CONTROL ARMREST ADJUSTMENT CONTROL SPRUNG THIGH WITH UP SUPPORT CONTROL STOP LUMBAR CONTROL IN/OUT HARNESS REEL LOCK CONTROL LONGITUDINAL ADJUSTMENT CONTROL THIGH SUPPORT CONTROL AIRCREW SEATS AIRCREW C-27A.12 T.O. 00-105E-9 C-27A DETAIL THERAPEUTIC OXYGEN PSI 50 MEDICAL OXYGEN DISTRIBUTION POINT HAND SIDE (1) LT HAND SIDE (1) RT DETAIL HEAT EXCHANGER HEAT DETAIL DETAIL LIQUID OXYGEN CONVERTERS MEDICAL OXYGEN AND REGULATOR SHUT-OFF VALVE Aircraft is equipped with a total of six flares: 3 green and 3 red. Class C explosive. Aircraft is equipped with a pyrotechnic pistol that is used to fire the above signal flares. The location of the pistol is housed in a compartment closed by a small door on the right side of the cockpit above the main circuit breaker panel. EXTINGUISHER CARTRIDGES The right, left engines and APU are equipped with extinguisher bottles explosive cartridges. These cartridges are 1.4 rated. Extinguishers utilize Halon 1211. AEROMEDICAL OXYGEN SYSTEM AEROMEDICAL 02 BOTTLES PORTABLE in the aircraft. Five portable 02 bottles are in the cargo Three in the cockpit and two in the latrine compartment, one located mounting and one in the two additional rear of the locations located in the right cargo compartment. AIRCRAFT EXPLOSIVES 1. AIRCRAFT FLARES.( Not pictured.) a. b. 2. (Not pictured.) a. 1. a. location. See details A-D for component 2. a. AEROMEDICAL OXYGEN SYSTEM OXYGEN AEROMEDICAL AND PORTABLE COMPONENTS LOCATIONS O2 BOTTLES C-27A.13 C-32A.

T.O. 00-105E-9 AIRCRAFT PAINT SCHEME C-32A

1 C-32A.

T.O. 00-105E-9 AIRCRAFT DIMENSIONS C-32A 124 ‘ 10” 2 (38.05M)

50 ‘ (15.24M)

15 ‘ 4” (4.67M)

34” 24” (0.86M) (0.61M) 24 ‘ (7.32M)

BS BS 159 2022 155 ‘ 3” (47.32M) 93 ” (2.36M) 44 ‘ 3” (13.49M) TO 45’ 1” (13.74M)

45” (1.14M) 19 ‘ 4” 60 ‘ 0” 18 ‘ 7” (5.89M) (18.29M) (5.66M) TO 153 ‘ 10” 19’ 8” (46.89M) (5.99M) C-32A.

T.O. 00-105E-9 AIRCRAFT DIMENSIONS-Continued C-32A

3 125‘ 5” (38.23M) NO. 2 CARGO DOOR 44” H X 55” W 104‘ 10” (1.12M X 1.40M) (31.78M) APPROXIMATE CLEAR OPENING (RIGHT SIDE) 98‘ 10” 45‘ 11” (29.87M) (14.00M) 35‘ 11” (10.95M) NO. 4 PASSENGER DOOR NO. 1 CARGO DOOR 30” W X 72” H 42.5” H X 55” W (1.08M X 1.40M) (0.76M X 1.83M) APPROXIMATE OPENING (RIGHT SIDE) (LEFT AND RIGHT SIDE) 15‘ 8” (4.78M) NO. 1 PASSENGER DOOR 30” W X 65” H (0.76M X 1.65M) (RIGHT SIDE)

21‘ 3” 24.14” (0.61M) (6.48M) 16‘ 7” MAXIMUM (5.05M) NO. 3 EMERGENCY EXIT 9.7” (0.25M) 24” W X 52” H MINIMUM NO. 1 PASSENGER DOOR (0.61M X 1.32M) 33” W X 72” H (0.84M X 1.83M) (LEFT AND RIGHT SIDE) (LEFT SIDE) NO. 2 PASSENGER DOOR 33” W X 72” H (0.84M X 1.83M) (LEFT AND RIGHT SIDE) PW2000 SERIES 54‘ 6” (16.61M) RB211-535 SERIES 55‘ 3” (16.84M)

89‘ 9” (27.36M) 68” (1.73M) 152‘ 11” (46.61M) C-32A.

T.O. 00-105E-9 SKIN PENETRATION POINTS C-32A

4 NOTE: This aircraft is the same as a Boeing 757-200. The C-32A is the official USAF designation for Vice Presidential transport. It has been modified and configured to accommodate his staff, a distinguished visitor stateroom, a conference area, a business class and general #2 #1 seating. See the INTERIOR ARRANGEMENT page for specifics.

CARGO DOORS

18”

PENETRATION POINT HANDLE FWD C-32A.

T.O. 00-105E-9 SKIN PENETRATION POINTS-Continued C-32A

757-200 (PW 2037 757-200 (PW 2037

PENETRATION POINTS PENETRATION POINTS

PENETRATION POINTS 8” PENETRATION POINTS 8” WING FRONT FRONT 18” MOUNT 18” MOUNT INLET

CL REAR REAR CL MOUNT MOUNT

CL NACELLE

PRESSURE RELIEF DOOR

CORE COWL 30” CL 30” THRUST REVERSER COWL 1.5” X 8” VENT AT BL.0 FAN COWL USE FOR FIRE EXTINGUISHER CL ACCESS TO FAN COMPARTMENT OIL TANK FILLER DOOR 1.5” X 8” VENT AT BL.0 USE FOR FIRE EXTINGUISHER ACCESS TO FAN COMPARTMENT

ENGINE NACELLE ENGINE NACELLE

LEFT SIDE VIEW RIGHT SIDE VIEW C-32A.

T.O. 00-105E-9 AIRCRAFT HAZARDS C-32A JET ENGINE INTAKE/EXHAUST AREAS AT IDLE

WARNING

· If surface wind is reported greater than 25 knots, increase distance of intake boundary by 20%.

· If ramp surfaces are slippery, additional precautions such as cleaning the ramp will be necessary to provide personnel safety. SEE DETAIL A 175’ (53.34M)

EXHAUST HAZARD AREA

DETAIL A 5’ (1.52M)

ENTRY CORRIDOR

0 ENTRY 45 RADIUS CORRIDOR 9’ (2.74M)

INLET HAZARD AREA C-32A.

T.O. 00-105E-9 AIRCRAFT HAZARDS-Continued C-32A

7 JET ENGINE INTAKE/EXHAUST AREAS AT FORWARD BREAKAWAY AND TAKEOFF THRUST

WARNING

· If surface wind is reported greater than 25 knots, increase distance of intake boundary by 20%.

· If ramp surfaces are slippery, additional precautions such as cleaning the ramp will be necessary to provide personnel safety.

SEE DETAIL A · Ground personnel must stand clear of these TAKE OFF 1900’ (579.12M) hazardous zones and maintain communica- FORWARD 400’ (121.02M) tion with flight compartment personnel BREAKAWAY during engine running. EXHAUST HAZARD AREA

DETAIL A 7’ (2.13M)

ENTRY CORRIDOR

0 RADIUS ENTRY 45 15’ (4.88M) CORRIDOR

INLET HAZARD AREA C-32A.

T.O. 00-105E-9 AIRCRAFT HAZARDS-Continued C-32A JET ENGINE REVERSE IDLE

WARNING

· If ramp surfaces are slippery, additional precautions such as cleaning the ramp will be necessary to provide personnel safety.

· Ground personnel must stand clear of these hazardous zones and maintain communication with flight compartment personnel during engine running.

CAUTION

For maintenance, engine operation in reverse thrust is limited to minimum idle power.

RADIUS 76’ (22.86M)

30’ (9.14M) 0 45 C-32A.

T.O. 00-105E-9 AIRCRAFT HAZARDS-Continued C-32A

.9 RADIATION HAZARDS

NOTE: MAXIMUM PERMISSIBLE EXPOSURE LEVEL (MPEL)

In order to avoid the envelope in which the radiation level may exceed the U.S. Government standard of MPEL BOUNDARY 10 miliwatt per square centimeter, all personnel should remain beyond the distance indicated in the illustration. The distance to the MPEL boundary is determined by calculating the near field/far field intersection per FAA Advisory Circular 20-68B. C OF AIRCRAFT WARNING L

The C-32A radome generates microwave radiation. 13.4’ Improper use or exposure may cause serious bodily (4.03M) injury. Maintain prescribed safe distance when standing in front of a radiating antenna. Never expose eyes or any part of the body to an unterminated wave- guide.

The HF-9000 High-Frequency Communications System can cause serious burns from direct contact when the system is transmitting. Do not touch the RF output RADOME terminal on the antenna coupler, the antenna lead-in wire, the insulated feedthrough, or the antenna itself. 0 When operated into an antenna, it may produce electro- 240 magnetic fields near the antenna that exceed OSHA recom mended maximum limits.

DO NOT operate the Airborne Weather Radar (AWR) during refueling of the aircraft nor when within 300 feet (91.44 meters) of other refueling operations. MPEL BOUNDARY DO NOT operate the AWR within 15 feet (4.57meters) of ground personnel or containers holding flammable or explosive material. C-32A.

T.O. 00-105E-9 AIRCRAFT HAZARDS-Continued C-32A

10 JET ENGINE EXHAUST WAKES

NOTE: Measurement in feet.

GROUND IDLE CONDITION 20

40 160 140 120 100 80 60 20 60 40 0 20 40 60 80 100 120 140

BREAKAWAY CONDITION 20

60 80 160 140 120 100 100 0 20 40 60 80 100 120 140

MAXIMUM TAKEOFF CONDITION 25

165 375 305 235 25 95 166 235 0 20 40 60 80 100 120 C-32A.

T.O. 00-105E-9 AIRCRAFT HAZARDS-Continued C-32A

11 AUXILIARY POWER UNIT EXHAUST WAKE

NOTE: HEIGHT Measurement in feet. 40 C APU EXHAUST GAS VELOCITY L

20 16.6 10 64 FT/SEC 255 FT/SEC 127 FT/SEC 32 FT/SEC 0 DISTANCE 0 10 20 30 40 50 60

FT/SEC -MPH X 1.487 1 MPH = 1.609 KM/HR

APU EXHAUST GAS TEMPERATURE 0 0 200 F 0 0 300 F 1200 F 500 F +5 CL 0 WIDTH -5

DISTANCE 0 10 20 30 40 C-32A.

T.O. 00-105E-9 AIRCRAFT HAZARDS-Continued C-32A

12 JET ENGINE NOISE AREAS NOTE: ______1,969 LBS OF THRUST 1000 FT ------6,300 LBS OF THRUST ------36,800 LBS OF THRUST 800 FT METRIC CONVERSION: 1FT= .3048M 80dBA 1LB= 0.4536KG

70dBA 600 FT

80dBA 400 FT 90dBA 90dBA 100dBA

100dBA

200 FT 110dBA 100dBA 400 FT

600 FT

60dBA

800 FT

1000 FT C-32A.

T.O. 00-105E-9 AIRCRAFT HAZARDS-Continued C-32A

13 FIRE EXTINGUISHING SYSTEM PYROTECHNIC CARTRIDGES AND LOCATIONS

PRESSURE SWITCH SAFETY RELIEF AND FILLER PORT

GROUND TEST PUSHBUTTON OR HEX KEY ENGINE FIRE BOTTLES (4)

DISCHARGE PORT

SQUIB SQUIB

ELECTRICAL CONNECTOR TYPICAL FIRE EXTINGUISHER BOTTLE

STATION 1040

STATION 2005

STATION 1360 STATION 1600

ZONES 313, 314 ZONES 151, 152

CARGO FIRE BOTTLES (2) APU FIRE BOTTLES (2) C-32A.

T.O. 00-105E-9 AIRFRAME MATERIALS C-32A STRUCTURE AND COMPOSITES

14 TIP FAIRING NOTE: RUDDER AND ELEVATORS The airframe materials for the C-32A are titanium, titanium alloy, carbon fibre, carbon- AILERONS SPOILERS FACING (GRAVEL PROTECTION) reinforced aramid-fiberglass, aramid and AFT FLAPS carbon epoxy preimpregnated raw material.

LEGEND: MAIN LANDING STRUT LE Leading edge GEAR DOORS TE Trailing edge APU INLET FAIRING FIXED LOWER CARBON-ARAMID (HYBRID) LE PANELS ARAMID CARBON-ARAMID- THRUST REVERSER FIBERGLASS (HYBRID) TRANSLATING SLEEVES THRUST REVERSER (FIXED STRUCTURE) FAN COWLS (HYBRID)

NOSE LANDING GEAR DOORS FLAP TRACK FAIRINGS (6)

WING/BODY FORWARD FAIRING

FIXED TE PANEL WING BODY (TYPICAL) FIXED TE PANELS UPPER/LOWER AFT FAIRING WING MAIN LANDING GEAR DOORS C-32A.

T.O. 00-105E-9 EMERGENCY RESCUE ACCESS C-32A

15 2” BAND OF GRAY COLOR AROUND ALL DOORS AND HATCHES OPERABLE FROM OUTSIDE OF THE AIRCRAFT

ENTRY DOORS APU ACCESS CHOP OUT LOCATIONS

CHOP OUT EMERGENCY EXITS LOCATIONS CARGO DOOR (COMBI) CARGO DOOR (RT SIDE) OPERATING INSTRUCTIONS ON DOOR ENTRY DOORS

ENTRY DOORS

AVERAGE DISTANCE- FLOOR LEVEL TO GROUND: WHEELS RETRACTED: 6 FT 6 IN WHEELS EXTENDED: 13 FT C-32A.

T.O. 00-105E-9 EXTERIOR ARRANGEMENT C-32A

16 ANTENNA LOCATIONS VHF L ADF LOOP SENSER R HF L & HF R VOR L & R SATCOM LOW GPS ANTENNA GAIN ANTENNA (2) ADF LOOP SENSER L L & R

UHF SATCOM IFF/ATC TOP LOCALIZER SATCOM HIGH C TACAN GAIN ANTENNA (2) STA STA TCAS 900 1180 ANTENNA TOP STA 440 WEATHER RADAR

STA STA UHF NATS 1720 2005.2 MARKER VHF R STA LOCALIZER GLIDE SCOPE DME R L & R L & R BEACON 1150 UHF COMM VHF C DME L GLIDE SCOPE C TCAS ANTENNA BOTTOM RCVR RADIO ALTIMETER L/C/R

TACAN TRANSMITTER RADIO ALTIMETER L/C/R

IFF/ATC BOTTOM ANTENNA LEGEND ADF = AUTOMATIC DIRECTION FINDER NATS = NORTH ATLANTIC TRACK SYSTEM DME L = DISTANCE MEASURING EQUIPMENT LEFT RCVR RADIO ALTIMETER = RECEIVER RADIO ALTIMETER DME R = DISTANCE MEASURING EQUIPMENT RIGHT TCAS ANTENNA BOTTOM = TRAFFIC COLLISION AVOIDANCE BOTTOM GLIDE SCOPE C = GLIDE SCOPE CENTER TCAS ANTENNA TOP = TRAFFIC COLLISION AVOIDANCE TOP GLIDE SCOPE L = GLIDE SCOPE LEFT TACAN = TACTICAL AIR NAVIGATION GLIDE SCOPE R = GLIDE SCOPE RIGHT UHF = ULTRA HIGH FREQUENCY GPS = GLOBAL POSITIONING SYSTEM UHF SATCOM = ULTRA HIGH FREQUENCY SATELITE COMMUNICATION HF L = HIGH FREQUENCY LEFT VHF R = VERY HIGH FREQUENCY RIGHT HF R = HIGH FREQUENCY RIGHT VHF L = VERY HIGH FREQUENCY LEFT IFF/ATC BOTTOM = IDENTIFY FRIEND OR FOE/AIR TRAFFIC CONTROL BOTTOM VHF C = VERY HIGH FREQUENCY CENTER IFF/ATC TOP = IDENTIFY FRIEND OR FOE/AIR TRAFFIC CONTROL TOP VOR L = VHF OMNI RANGE LEFT LOCALIZER C = LOCALIZER CENTER VOR R = VHF OMNI RANGE RIGHT LOCALIZER L = LOCALIZER LEFT WEATHER RADAR = WEATHER RADAR LOCALIZER R = LOCALIZER RIGHT C-32A.

T.O. 00-105E-9 INTERIOR ARRANGEMENT AND CAPACITY C-32A

17 EFFECTIVITY: TYPICAL ARRANGEMENT 56 TOTAL PASSENGERS WITH 7 ATTENDANTS (NEXT CABIN MOD: 3 YEARS)

CREW AREA: 10 BUSINESS CLASS CONFERENCE AREA: 42 IN. PITCH 8 PASSENGERS

G S S G G L L L L C S C

GENERAL SEATING: 1 STAFF DISTINGUISHED VISITOR 32 BUSINESS CLASS - 42 IN. PITCH WORK AREA STATEROOM: 5 PASSENGERS

C: CLOSET G: GALLEY FORWARD L: LAVATORY EXITS S: STOWAGE

EFFECTIVITY: TAIL # 99-0004 ONLY

CREW REST DOCUMENT AREA CENTER

S S G G L G

L L L C C

CSO STATION DISTINGUISHED CONFERENCE STAFF REAR PASSENGER AREA STATEROOM AREA SEATING C-32A.

T.O. 00-105E-9 LOWER CARGO DOORS AND COMPARTMENTS C-32A

18 NOTE: Measurements are given in inches (centimeters).

STATION 590 STATION 1490 CL OF THE CARGO DOOR CL OF THE CARGO DOOR AFT CARGO COMPARTMENT

NO.2 CARGO DOOR 44 H X 55 W (112 X 140) FORWARD CARGO COMPARTMENT

[1] THIS DOOR IS INSTALLED ON NO.1 CARGO DOOR SOME INITIAL AIRCRAFT 42.5 H X 55 W (108 X 140) C-32A.

T.O. 00-105E-9 SPECIAL TOOLS/EQUIPMENT Power Rescue Saw C-32A

19 35 Foot Ladder Fire Drill II AIRCRAFT ENTRY SURGE RT MAIN FUEL TANK APU 1. NORMAL/EMERGENCY TANK HYDRAULIC RESERVOIR (RT WHEEL WELL) a. To open entry and service doors: push OXYGEN handle release latch. BOTTLE DRY BAY APU FUEL LINE b. Pull butterfly handle from recess and rotate 2170 NO. 3 EMERGENCY EXIT 180 degrees in direction of “open” arrow. HYDRAULIC RESERVOIR (LT WING FILLET) CENTER FUEL 6900 HYDRAULIC RESERVOIR (LT WHEEL WELL) c. Pull door outward. TANK APU EMERGENCY CONTROL PANEL 2170 LT MAIN FUEL TANK d. To open overwing escape hatches (if LOCATED ON THE installed): lift lower portion of handle NOSE GEAR SURGE TANK away from the side of the aircraft. ENGINE OIL TANK (LT ON RT 1a e. Continue to raise handle to the pull up CREW OXYGEN SIDE OF EACH ENGINE) HANDLE position. BOTTLE (RT SIDE, RELEASE FWD CARGO PORTABLE PORTABLE LATCH COMPARTMENT, OXYGEN OXYGEN f. Push hatch inward and upward. AFT OF DOOR) BOTTLE (ON BOTTLE 1b BULKHEAD (FWD g. To open number 3 emergency exit: BEHIND PASSENGER push on “push” panel to gain access PILOT) CABIN) to handle.

h. Pull handle forward and outward. 1d

NOTE: LIFT AND PUSH UP HANDLE AFT · Escape slide disarms automatically when BATTERY door or hatch is opened from the outside, AFT except No. 3 emergency exit. CARGO DOOR · Cockpit windows cannot be opened from the outside. P P U U 1g, 1h MAIN BATTERY 2. CUT-IN L S L H

a. Cut along window lines as last WARNING: FOR EMERGENCY USE ONLY Stand to side of door and pull handle. Door falls resort. outward and down. Escape slide inflates immediately. NOSE GEAR COMPARTMENT ACCESS DOOR C-32A.

T.O. 00-105E-9 AIRSTAIR OPERATION C-32A

20 1. AIRSTAIR OPERATION The airstair is manually moved from the closet to the deployed position in the doorway and from the deploy position back to the closet. Once the airstair is in the deploy position it is hydraulically operated and electri- cally controlled. A control box for the operation of the airstair and step lights is mounted adjacent to the door entry. A micro switch. located under the floor will be depressed by the FWD latch pen fitting enabling a “READY” light to illuminate on the control panel signify- ing that the airstair is locked in place and safe to extend. Pressing and holding the ‘EXTEND” switch will provide power to an electric motor that will drive the hydraulic pump. When the “LATCH “ light illuminates the “EXTEND” switch may be released and the airstair will continue to extend by gravity. To retract the airstair, simply push and hold the “RETRACT” switch until the airstair is fully retracted. Once fully retracted it may be placed back in the closet and secured. The “POWER ON” switch/light indicates power is available. Power is HYDRAULIC COMPONENTS provided from three battery bus circuit breakers located ARE LOCATED UNDER THE on the P6 panel and through an electrical connector UPPER STAIR SEGMENT receptacle adjacent the door opening. While electrical power is connected and available the airstair segments may be illuminated by pressing the “AIRSTAIRS LIGHTS” switch.

CAUTION

Airstair deployment is limited to winds and/or gusts below 30 knots.

NOTE: While moving stair through door opening, be advised of possible rubbing impact with decorative doorframe.

The control panel is made up of six indicating lights. The center lights provide indication only and the fwd and aft lights are switchlights that also provide control. C-32A.

T.O. 00-105E-9 ENGINE, APU SHUTDOWN AND AIRCREW EXTRACTION C-32A

21 1. ENGINE SHUTDOWN

a. Retard thrust levers, located on pilot’s center 1e console, to RETARD position. APU CONTROL SWITCH b. Place fuel control switches, located on pilot’s center 1f console under thrust levers, to CUT OFF position. BATTERY SWITCH NOTE: c. In case of engine fire, pull engine fire switches, ON SYMBOL IS REMOVED located on pilot’s center console. Turn left or right to release agent. If not illuminated, push and hold 1a the button under the switch to release. THRUST LEVERS

d. In case of APU fire, pull APU fire switch, located on pilot’s center console to the right of the engine fire switches. Turn switch up or down to release agent. If not illuminated, push and hold the button under the switch to release.

e. Rotate APU control switch, located on pilot’s overhead panel to OFF.

f. Press battery switch, located on pilot’s overhead center panel left side, to OFF.

2. AIRCREW EXTRACTION 1b a. Unlatch lap belts and remove shoulder harness from FUEL CONTROL crewmembers. SWITCHES

b. Depress control handles and rotate flight engineer’s seat from left to right. 1c 1d APU FIRE c. Passenger seats are equipped with lap belts only. ENGINE FIRE SWITCHES SWITCH NOTE: If seat tracks are not damaged during crash landing, use adjustable seat control to retract seats to aft position. CRITICAL SWITCH LOCATIONS AND THEIR OPERATION ARE SHOWN WITH THE EXPANDED VIEWS OF THE CONTROL MODULES C-37A.

T.O. 00-105E-9 AIRCRAFT PAINT SCHEME C-37A

1 C-37A.

T.O. 00-105E-9 AIRCRAFT DIMENSIONS C-37A

2 GENERAL DATA

Wing Area 1136.5 Sq. Ft. Aspect Ratio 6.89 Quarter Chord Sweep 27.00 degrees Taper Ratio 0.268 MAC 171.19 In. WINGSPAN 88.50 FT(1062.00 IN) Horizontal Tail Area 260.85 Sq. Ft. Vertical Tail Area 155.00 Sq. Ft.

Cabin Length 51.08 Ft. Total Volumn 1,902 Cu. Ft. Cabin Volumn 1,681 Cu. Ft.

Engine (2ea) BR710-48 Takeoff Thrust - SLS 14,465 lb. (Installed)

Max Takeoff Gross Wt. 89,000 lb Max Zero Fuel Wt. 53,300 lb Max Usable Fuel Wt. 41,000 lb Manf’’s Bare Wt. Empty 38,000 lb

OVERALL WINGSPAN 93.47 FT(1121.69 IN)

OVERALL HEIGHT 25.30 FT(303.64 IN)

OVERALL LENGTH 96.40 FT(1156.82 IN) C-37A.

T.O. 00-105E-9 AIRCRAFT DANGER AREAS C-37A

3 INLET AND EXHAUST

NOTE: · The C-37A is a Gulfstream V airframe modified for USAF missions, similiar to the C-20. Its purpose is a Presidential, VP, or VIP, small airframe carrier. It will land where Air Force One or the C-32A (757-200) can not.

· Depending on the type of operation being carried out, the following areas of the aircraft are to be considered danger or caution areas. These areas are intended as a general reference for ramp and rescue personnel.

BMW Rolls-Royce AeroEngine

FRONT ECC THERMAL MOUNT FIRE PROTECTION FIRE BOX ZONE 2 BOX

FIRE ZONE 1 C-37A.

T.O. 00-105E-9 AIRCRAFT DANGER AREAS C-37A HF-9000 AND RADAR DANGERS

WARNING

The *HF-9000 High-Frequency Communications System can cause serious burns from direct contact when the system is transmitting. Do SATCOM (SPACE not touch the RF output terminal on the antenna PROVISIONS) coupler, the antenna lead-in wire, the insulated ATC #1 LH SIDE *HF feedthrough, or the antenna itself. When ATC #2 RH SIDE ADF operated into an antenna, it may produce electromagnetic fields near the antenna that exceed OSHA recommended TCAS VHF #2 FM ENTERTAINMENT maximum limits. GPS#2 GPS#1

AIRBORNE WEATHER RADAR (AWR)

GLIDE VOR/LOCALIZER SCOPE VHF #1 TCAS MARKER BEACON DME#1 TX 2 RADIO ALTIMETER TX 1 RADIO DME #2 WARNING TRANSMITTER ATC #1 LH SIDE RX 2 RADIO TRANSMITER DO NOT operate the Airborne Weather Radar ATC #2 RH SIDE RX 1 RADIO (AWR) during refueling of the aircraft nor when ALTIMETER within 300 feet (91.44 meters) of other refueling operations.

WARNING

DO NOT operate the AWR within 15 feet (4.57 meters) of ground personnel or containers holding flammable or explosive material. C-37A.

T.O. 00-105E-9 AIRFRAME MATERIALS C-37A

5 NOTE: Ailerons on A/C 521 & 542 are metal- EPOXY FIBERGLASS riveted sheet metal. EPOXY GRAPHITE NOTE: Composite materials are used extensively BONDED ALUMINUM ELEVATOR TRIM TAB on this aircraft (Gulfstream V) to save weight KEVLAR and increase strength. Composite materials include metallic and non-metallic structures for VERTICAL OUTLET bulkheads, doors, flight controls, floor panels, FAIRING fairings, nacelles, panels, pylons, radome, tailcone, and winglets. ELEVATOR WINGLET PYLON

ECS RAM AIRSCOOP KEVLAR FAN AFT PRESSURE BLANKET RUDDER BULKHEAD

TAILCONE SPOILERS EXHAUST UNIT AUXILIARY PRESSURE FAN COWL DOOR BULKHEAD INLET CABIN FLOOR FILLET PANEL AILERON TAB RADOME AILERON

MAIN LANDING GEAR STRUT DOOR

MAIN LANDING GEAR DOOR NOSE LANDING GEAR STRUT DOOR

NOSE LANDING GEAR DOORS C-37A.

T.O. 00-105E-9 FLAMMABLE FLUIDS AND COMPONENTS C-37A

TAIL ACCESS DOOR HYDRAULIC RESERVOIRS APU/ENGINE FIRE EXTINGUISHER ENGINE OIL L&R BATTERIES (2) FIRE ACCESS FIRE ACCESS SCREEN SCREEN PRESSURE BULKHEAD (BOTTOM OF NACELLES) LAVATORY APU

WING TANKS (TOTAL CAPACITY 6,150 U.S. GALS.)

EMERGENCY CUTOUTS TOP OF FUSELAGE (CAA/MILITARY REQUIREMENTS) PASSENGER COMPARTMENT

FIRE EXTINGUISHER OXYGEN BOTTLES (PORTABLE & WATER) FIRE EXTINGUISHER (PORTABLE) C-37A.

T.O. 00-105E-9 SPECIAL TOOLS/EQUIPMENT Power Rescue Saw C-37A

7 12 Foot Ladder Fire Drill II AIRCRAFT ENTRY

1. NORMAL ENTRY a. Push inner latch handle. BAGGAGE DOOR HANDLE WITH PUSH BUTTON b. Pull out latch handle. RELEASE

WARNING OXYGEN Door is hinged at bottom and will fall open SERVICE rapidly, especially if door was closed PANEL manually without hydraulic pressure.

c. Pull door open.

d. Main door will not open fully with landing gear up.

2. EMERGENCY ENTRY 2b EMERGENCY WINDOW NOTE: EXIT RELEASE - 2 PER SIDE Two emergency exits are located on each side of the aircraft. EMERGENCY ESCAPE a. Push button to open access panel. LIGHTS

b. Pull handle, located inside access panel AIRSTAIR DOOR 2a up to release window and push window STAIRLIGHT, ETC. ACCESS PANEL in. BATTERY SWITCH

3. CUT-IN 1a INNER LATCH HANDLE CAUTION 1b Windshield panels cannot be chopped or LATCH HANDLE broken out.

a. Cut fuselage as required. MAIN DOOR C-37A.

T.O. 00-105E-9 AIRCRAFT ENTRY-Continued C-37A MAIN ENTRANCE DOOR, INTERIOR AND EXTERIOR 8 BAGGAGE COMPARTMENT DOORS

MAIN ENTRANCE DOOR BAGGAGE DOOR 40,000FT WARNING PANEL

BAGGAGE DOOR INDICATION SWITCH

BAGGAGE DOOR LATCH (OPEN) EXTERIOR BAGGAGE BAGGAGE COMPARTMENT DOOR HANDLE DOOR

INTERNAL BAGGAGE DOOR BAGGAGE DOOR LATCH (CLOSED) ALTERNATIVE ENTRY INTO AIRCRAFT BY USING EXTERIOR AND INTERIOR BAGGAGE COMPARTMENT DOORS C-37A.

T.O. 00-105E-9 AIRCRAFT ENTRY-Continued C-37A

9 TAIL COMPARTMENT AND LADDER

LOCKING PINS Used to secure ladder in adjusted COUNTERBALANCE SYSTEM positions. Holds door up after it has been locked. Door is pulled down against force of counterbalance. When in the full down position, two jury rods lock to the overcenter position to a latch mounted on the door.

LADDER INSTRUCTIONS 1. To lower ladder, remove 2 pip RETRACTED POSITION pins thru door brackets at lower end of door.

POSITION “A”- Boiler room, baggage 2. Lift ladder up and aft to clear door wing RH nacelle oil filler and latch housing, then lower. cowling access. TAIL COMPARTMENT DOOR HANDLE 3. Lower bottom extension and Flush mounted handle releases door reinstall pip pins thru door locking mechanism. POSITION “B”- Cowling access LH brackets. (fully extended). 4. To remove ladder, follow step POSITION “C”- RH nacelle oil filler and cowling access LH (fully extended). 1 and 2, then lower. Ladder tracks are aligned with rollers, then pull. C-37A.

T.O. 00-105E-9 ENGINE AND APU SHUTDOWN C-37A

10 NOTE: Each fire handle is capable of rotation to two positions after placement in the OUT position. The positions are labeled DISCH 1 for the right fire bottle and DISH 2 for the left fire bottle. When it is necessary to discharge a fire bottle, ALWAYS use DISCH 1 first. This will discharge extinguishing agent from the RIGHT fire bottle, preserving the LEFT fire bottle for APU protection. Only the LEFT fire bottle can be used for APU protection. 1b NOTE: APU PANEL 3a The Fire Detection and Warning System detects overheat or fire in APU the engines, engine pylons, APU, and passenger/tail areas. MASTER

1. ENGINE and APU FIRES

NOTE: Appropriate handle will be illuminated red indicating fire. 1a, 2b Fire extinguishing systems receives its power from the EMERGENCY CONTROL main batteries. DO NOT push battery switches to OFF L-HANDLE (TYPICAL) 2d until engine/APU shutdown is complete. ELECTRICAL MASTER BATTERY SWITCHES a. In case of engine fire, pulling the fire L-handle located on the forward portion of the flightdeck center pedestal, shuts off the engine generator, fuel, hydraulic fluid to and from the associated engine.

b. In case of APU fire, select the APU MASTER to Off. Depress the APU FIRE EXT switch to discharge the LEFT fire bottle into the 2a APU enclosure. THROTTLES ON CENTER PEDESTAL 2. ENGINE SHUTDOWN 2c CREW AND PASSENGER a. Pull throttles, located on the center pedestal, to the shut position. OXYGEN SYSTEMS b. Pull fire L-handles (do not rotate if no fire), located to right and left of the throttles. c. Turn oxygen switches to OFF. d. Push main battery switches to OFF.

3. APU SHUTDOWN

a. Place APU Master to OFF. C-37A.

T.O. 00-105E-9 AIRCREW EXTRACTION C-37A

11 1. AIRCREW EXTRACTION SHOULDER a. Disconnect restraints by rotating HARNESSES SHOULDER rotary buckle in either direction. HARNESSES

b. Position seats using various 1a control handles to position LAP LUMBAR ROTARY BUCKLE crewmember for extraction. BELT CONTROL DISCONNECT UP/DOWN c. Passenger seats are equipped HANDLE LUMBAR CONTROL with seat belts only. UP/DOWN HANDLE

CROTCH BELT THIGH SUPPORT CONTROL HANDLE

PILOT’/COPILOT’S SEATS

30 DEG RECLINE 3 DEG MIN RECLINE OBSERVER’S SEAT HARNESS REEL HARNESS REEL LOCK CONTROL TRACK LOCK CONTROL

ARMREST ADJUSTMENT CONTROL SEAT RAISED TILT CONTROL HANDLE 3.1 SEAT LOWERED

VERTICAL ADJUSTMENT RECLINE CONTROL CONTROL (ON FAR SIDE) C-37A.

T.O. 00-105E-9 INTERIOR CABIN CONFIGURATION C-37A

EMERGENCY STAFF EXIT WORK FAX MACHINE/PAPER SHREDDER/ 12 MAN MAGAZINE/ 30 GALLON CREW 1 CU FT SAFE/COMPUTER PRINTER/ LIFE 14.2” LCD ATLAS VACUUM WATER REST RAFT RACK CLOSET TANK SYSTEM STU 111 RADIO TELEPHONE MONITOR 14.2” LCD GALLEY

ELECTRONIC EQUIPMENT AUX RACK 99.00”

BAGGAGE REMOVAL CREW ELECTRONIC COAT ROD MAIN LAV EQUIPMENT ENTRANCE BAGGAGE DOOR NET

POCKET GALLEY STORAGE DOOR 14.2” 12 MAN 14.2” DOORS ANNEX VANITY ACTUATOR LCD LIFE LCD ENTERTAINMENT/ AREA MAGAZINE/ RAFT JUMP STORAGE ATLAS SEAT RACK EMERGENCY EXIT C-38A.

T.O. 00-105E-9 PAINT SCHEME C-38A

1 C-38A.

T.O. 00-105E-9 AIRCRAFT DIMENSIONS C-38A

21 FT (6.40 m)

54 FT 7 IN (16.64 m)

18 FT 2 IN (5.54 m)

55 FT 7 IN (16.94 m) C-38A.

T.O. 00-105E-9 AIRCRAFT DANGER AREAS C-38A

3 INLET AND EXHAUST

NOTE: The C-38A or Astra is an Israeli built aircraft for the US Air Force. The aircraft’s mission is to replace the older C-21 and augment the C-9 Nightingale medivac, target towing, photo-reconaissance, threat simulation and flight inspection missions. The C-38A can be configured with the SPECTRUM AEROMED 500 LP WARNING modular life support for air evacuation. This aircraft is also known commercially as the Astra SPX BIZ-Jet. If blast deflector is not available, area WARNING must be clear 100 feet aft of aircraft.

Do not operate engines with emergency exits removed or left left engine above idle with cabin entrance door open. Ground and rescue personnel should wear ear protection during engine operation.

12 FT

40 FT

Distance from engine exhaust to blast deflector. C-38A.

T.O. 00-105E-9 AIRCRAFT DANGER AREAS NOTE: C-38A

4 HF-9000 AND RADAR DANGERS TOTAL FUEL WITH EXTENSION -1,245.3 US GALS EXTENSION OF 100 US GALS IS OPTIONAL WARNING FUEL TYPE - JP-8

The *HF-9000 High-Frequency Communications LEFT SIDE VIEW System can cause serious burns from direct AWR & AVIONICS contact when the system is transmitting. Do APU not touch the RF output terminal on the antenna EXHAUST coupler, the antenna lead-in wire, the insulated APU AND feedthrough, or the antenna itself. When operated ACFT SERVICING into an antenna, it may produce electromagnetic BAGGAGE fields near the antenna that exceed OSHA recom- COMPARTMENT EMERGENCY OXYGEN mended maximum limits. EXIT (BOTH SIDES) HYDRAULIC RESERVOIR CYLINDER MAIN CABIN BATTERY 3390cc 3300 PSI 77 CU FT ENTRANCE WARNING (MOD 6OO2) (UNDER CENTRAL LOWER CENTRAL UPPER EXTENSION The Airborne Weather Radar (AWR) WXR-840 or AVIONICS FUEL TANK 169 FUEL TANK FUEL TANK the Turbulence Weather Radar System TWR-850 RACK) US GALS 555.2 US GALS 100 GALS (OPTIONAL) safe distance for human exposure to radiation is 2 feet (0.65 meters). Ground and rescue personnel should take necessary and reasonable precautions to ensure that personnel and equipment sensitive to microwave radiation are kept safely beyond this distance while within the illumination pattern.

WARNING

Oil Handling - Prolonged contact with MIL-L-5606 oils may cause skin rash. The areas of skin and clothing COLLECTOR contacting this oil should be thoroughly washed FUEL BOXES 4.9 US GALS (2) immediately. Areas in which this oil is used shall be adequately vented to reduce mist and fumes to a WING FUEL TANK minimum. 563.4 US GALS (2)

WARNING

Frequent skin contact with MOBIL 254 lubricating oils may result in permanent paralysis, since this oil contains an additive that is poisonous and readily absorbed through the skin. Do not allow this oil to remain on the skin longer than necessary. BOTTOM VIEW C-38A.

T.O. 00-105E-9 AIRCRAFT DANGER AREAS-Continued C-38A

5 OXYGEN AND HYDRAULIC SYSTEMS OXYGEN PRESSURE NOTE: PASSENGER OXYGEN SWITCH Oxygen system is pressurized to 65 CONTROL PANEL to 95 psig through a pressure reducer, (FWD OF RH CONSOLE) which directly feeds the crew system. The passenger system is fed through an altitude control regulator. There is ALTITUDE PRESSURE no third or therapeutic subsystem on SWITCH this model. PRESSURE REDUCER REGULATOR WARNING

Wear chemical goggles and protective PASSENGER MASK STOWAGE OXYGEN gloves. Hydraulic fluid may cause eye, COMPARTMENTS (OXYGEN FLOW CYLINDER nose and skin irritation. Avoid prolonged AT 70 PSI, ACTIVATED AT 1850 PSIG breathing or repeated contact with skin. OXYGEN SHUTOFF 13,500 +/- 500 FEET) (RH SIDE OF NOSE VALVE (Valve must be COMPARTMENT) NOTE: FILLER closed when system is Hydraulic fluid for the main system is OVERBOARD VALVE not in use.) contained in a reservoir located in the DISCHARGE LINE rear left side of the baggage compart- PRESSURE ment at station 390. The reservoir has PRESSURE TRANSMITTER a fluid capacity of 3890 cc and sup- SWITCH AIR plies fluid to operate the ailerons, PRESSURE wheel brakes, landing gear, nose wheel NO.1 MANIFOLD REGULATOR steering and air brakes. Maximum pressure is 3300 psi.

RETURN FILTER AUXILIARY RESERVOIR PRESSURE FILTER RETURN FILTER PRESSURE MAIN MANIFOLD ASSEMBLY FILTER BLEEDER VALVE FIRE SHUTOFF VALVE MAIN RESERVOIR ELECTRIC MOTOR C-38A.

T.O. 00-105E-9 COMPOSITE MATERIALS C-38A NOTE:

6 KEVLAR/FOAM The structures are fabricated from ALUMINUM SHEET BONDED aluminum alloy, alloy steels, stainless KEVLAR steel, titanium and the list composites. GRAPHITE/KEVLAR/AL H/C GRAPHITE/KEVLAR/NOMEX KEVLAR/NOMEX GRAPHITE/EPOXY/NOMEX KEVLAR/AL H/C C-38A.

T.O. 00-105E-9 SPECIAL TOOLS/EQUIPMENT NOTE: Power Rescue Saw 2 CREW C-38A 7 Fire Drill II 6 PASSENGERS (9-SPX Version) AIRCRAFT ENTRY 1a EMERGENCY EXIT (BOTH SIDES) NOTE: MAIN ENTRANCE The main entrance/airstair for crew and passengers can be opened from the inside or outside when the cabin is depressurized.

1. NORMAL ENTRY BAGGAGE COMPARTMENT AIRSTAIR a. To open the main entrance, located on the left forward fuselage, rotate the external locking handle, and unlock EMERGENCY EXIT the door. Operation of the door handle will deflate the 2a CABIN door seal. Door will open outward pivoting on two EMERGENCY AREA AFT CABIN hinges in the lower door sill in a dampened free fall. EXIT OXYGEN EMERGENCY EMERGENCY BOX 2. EMERGENCY ENTRY FILLER EXIT GROUND VALVE AREA a. Use step 1a for main entrance.

b. Remove either emergency plug-type exit doors, located over each wing, by using the corresponding PUSH 1a handle at center top of door. The emergency doors open AIRSTAIR inward. Do not place door into egress path. EMERGENCY EXIT EMERGENCY EXIT GROUND AREA 2a CABIN AREA 2b c. To remove emergency door internally, pull off the cover to EMERGENCY EXTERNAL PUSH 2c expose the EXIT-PULL handle, located at the top center of EXIT HANDLE the door, pull handle and door inward. Do not place door EXIT DOOR LOCKING PINS into egress path. PULL HANLDLE 3. CUT-IN HINGES 2c THRESHOLD PANEL a. Cut-in as required. COVER HANDRAIL ASSEMBLY 1a OUTSIDE DOOR HANDLE 1a AIRSTAIR ASSEMBLY INSIDE INSIDE DOOR VIEW HANDLE INFLATABLE SEAL DOOR REST C-38A.

T.O. 00-105E-9 AIRCRAFT ENTRY-Continued C-38A CABIN ARRANGEMENT AND EMERGENCY EQUIPMENT

NOTE: The configuration to the right is for VIP/ PORTABLE FIRE personnel transport. The illustrations EXTINGUISHER below depict the SPECTRUM AERO- MED LP 500. The two pictures below depict two types of systems possibly installed. Passenger seats are removed for air evacuation.

FLASHLIGHT

INFANT TRANSPORT DECK

PORTABLE FIRE EXTINGUISHER

PORTABLE FIRE EXTINGUISHER SPECTRUM 500 LP FOR ADULTS AND FIRST AID KIT C-38A.

T.O. 00-105E-9 ENGINE/APU SHUTDOWN FIRE DETECTION PANEL C-38A 1. ENGINE SHUTDOWN

NOTE: If engine or APU is on fire, do place battery switch to OFF. Battery power is required to operate the fire suppression system.

a. Pull thruster levers to CUT-OFF position.

NOTE: Each engine nacelle has a fire detection and extinguishing system. There are two zones, the accessories and cumbustor sections. If FIRE light comes on, a fire in zone 1 is present. If OVERHT light comes on, a fire in zone 2 is present. If either FIRE or OVERHT light comes on together with the corresponding light within 1b, 1c PRESS TO TEST pushbutton, the warning FIRE INDICATORS should be considered false.

b. In case of an engine fire, the FIRE light will illuminate. Press the appropriate FIRE/ 1e OVERHT pushbutton. OXYGEN SHUTOFF c. If the FIRE light stays on, press ARM/EMPTY VALVE pushbutton. If fire does not go out within 30 seconds, press the remaining ARM/EMPTY pushbutton.

d. Place BATT MASTER switch to OFF. 1a THRUSTER LEVERS e. Turn off oxygen shutoff valve if time allows. 1d, 2c 2b MASTER BATTERY SWITCH 2. APU SHUTDOWN FIRE PUSH SWITCH a. Press the APU FIRE PUSH switch, located on the copilot’s instrument panel, to arm the fire extinguishing system and close the fuel 2a shutoff valve. FIRE EXTINGUISHER PUSHBUTTON b. In case of fire, press the FIRE EXT pushbutton.

c. Place BATT MASTER switch to OFF. C- 40.

T.O. 00-105E-9 AIRCRAFT PAINT SCHEME C-40 1 APPLICABILITY: USN C-40A (C-9 REPLACEMENT) C- 40.

T.O. 00-105E-9 AIRCRAFT PAINT SCHEME C-40 2 APPLICABILITY: USAF C-40B (VIP TRANSPORT) C- 40.

T.O. 00-105E-9 AIRCRAFT PAINT SCHEME #1 C-40 3 APPLICABILITY: USAF C-40C (C-22 REPLACEMENT) C- 40.

T.O. 00-105E-9 AIRCRAFT PAINT SCHEME #2 C-40 4 APPLICABILITY: USAF C-40C (C-22 REPLACEMENT) C- 40.

T.O. 00-105E-9 AIRCRAFT DIMENSIONS C-40 5 EFFECTIVITY: 737-700 WITH WINGLETS

110’ 4” (33.63m)

34’ 0” (10.36m)

15’ 10” (4.83m)

12’ 4” (3.76m)

105’ 7” (32.18m)

75’ 6” (23.01m) 41’ 3”

41’ 4” (12.60m) 13’ 5” (4.09m) 117’ 5”(35.79m) 47’ 1” (14.35m)

APPROX 8’ (2.44m) METERS 0 2 4 6 18’ 9” (5.72m) FEET 0 5 10 15 20 25 C- 40.

T.O. 00-105E-9 737-600/700/800 MAIN FUEL TANKS WITH C-40 6 C-40 AUXILIARY TANKS LOCATIONS FUEL CAPACITY: 6878 US GALS

1 AUXILIARY FUEL TANK LOCATIONS - 3 AFT/2 FWD FOR C-40A/B/C

WINGLETS (AS INSTALLED)

AUXILIARY POWER VENT SURGE TANK UNIT AND OIL TANK

SYSTEM A & B AND STANDBY HYDRAULIC RESERVOIRS IN FUEL WHEEL WELL TANK #2 1288 GAL PORTABLE OXGEN BOTTLES (4876 LITRES) LOCATED VARIES THROUGH- (BOTH #1 & #2 OUT PASSENGER CABIN SAME AMOUNT) APU FUEL LINE APU EMERGENCY CONTROL PANEL CREW OXYGEN BOTTLE 1 LOCATED IN RT WHEEL WELL AREA FWD CARGO AREA HYDRAULIC BRAKE ACCUMULATORS IN WHEEL WELL 1 FUEL TANK #1 PORTABLE OXYGEN BOTTLE BEHIND WINGLET FIRST OFFICER OR CO-PILOT CENTER FUEL TANK 4299 GAL (16273 LITRES) ENGINE OIL TANK RT SIDE EACH ENGINE C- 40.

T.O. 00-105E-9 C-40A CABIN CONFIGURATIONS ALL PASSENGER CONFIGURATION WITH FOUR (4) FLIGHT ATTENDANT STATIONS C-40 7 The C-40A aicraft configuration is a modified 737-700 IGW/QC (Quick Change) jetliner which increases the logistical capabilities of the U.S. Navy’s worldwide fleet. It can be configured as an all-passenger, all-cargo or combination of the two. Designated C-40A, the aircraft will be used for the Navy Unique Fleet Essential Airlift (NUFEA) mission, transporting ALL CARGO CONFIGURATION WITH FOUR (4) FLIGHT ATTENDANT STATIONS both passengers and cargo around the world. The C-40A can operate in three configurations: an all-passenger (121) configuration, an all- cargo configuration of up to eight pallets, or a combination (or “combi”) configuration that will accommodate up to 70 passengers and three cargo pallets.

OPERATIONAL DOORS (4 PLACES) COMBI CONFIGURATION WITH FOUR (4) FLIGHT ATTENDANT STATIONS

C-40A EXTERIOR PASSENGER DOOR HANDLE ONLY

CARGO PASSENGER CONFIGURATION CONFIGURATION (ALL DOORS) (ALL DOORS)

COMBI CONFIGURATION COMBI CONFIGURATION (FWD DOORS) (AFT DOORS) C- 40.

T.O. 00-105E-9 C-40B CABIN CONFIGURATION C-40 8 The C-40B aircraft configuration is a 737-700 IGW OPERATIONAL DOORS (4 PLACES) (Increased Gross Weight). This aircraft is specifi- EMERGENCY EXITS (2 OVER WINGS) cally designed for VIP transport operated by the USAF. WINDOWS

26 Total Passengers and 11 Crew* BLOCKED WINDOWS * Available Crew Seats: 4 Crew Rest Seats 4 Flight Attendant Seats 3 Flightdeck Seats 1 CSO Seat

C-40B STATION LOCATIONS STA 1016.00 STA 975.00 STA 827.00 STA 847.00 STA 867.00 STA 887.00 STA 907.00 STA 927.00 STA 949.00 STA 993.00 STA 807.00 STA 500B.00 STA 767.00 STA 787.00 STA 500A.00 STA 500C.00 STA 747.00 STA 344.00 STA 360.00 STA 380.00 STA 420.00 STA 440.00 STA 500.00 STA 685.00 STA 706.00 STA 727.00 STA 727E.00 STA 270.00 STA 400.00 STA 460.00 STA 500D.00 STA 627.50 STA 639.00 STA 663.75 STA 480.00 STA 520.00 STA 616.00 STA 727C.00 STA 727D.00 STA 291.00 STA 314.00 STA 332.10 STA 540.00 STA 559.00 STA 601.00 STA 727A.00 STA 727B.00 STA 578.00

DOOR CLOSURE CURTAIN (L&R) (ACOUSTIC-THERMO BARRIER) CREW REST AREA (4 PLACES) HI-LOW VIDEO MONITOR BI-FOLD TABLE (DOOR REMAINS ACTIVATED) (44 INCH PITCH) (3 PLACES) AVIONICS RACKS

DS TMU TMU DS TMU TMU DS

OT OT SCANNER OT

GO GO PRINTER GO SHELVES HW HW HW OA OA OA G1 UG G2 G2A UG UG SE SE SE E E E OVERHEAD BINS BERTHING DIVAN DS LAV A OT A G GO A A1 1F FAX/ HW LAV A 7 PRINTER OA UG D SE E CSO SAFE 14-BUSINESS 8 - DISTIGUISHED VISITOR CUSTOM DESIGNED UNIT CONSOLE SHREDDER (BELOW 42 “ PRINTER) BIN CLASS CONFERENCE COMPARTMENT (IN LIEU OF CSO STATION SUPPLIED (FURNISHINGS SHOWN FOR 80 “ BIN IN BBI “KIT”) SPATIAL REFERENCE ONLY, ACTUAL SHAPES,COUNTER - TOPS, ETC, TBD BY IPT) C- 40.

T.O. 00-105E-9 C-40C CABIN CONFIGURATION C-40

9 NOTE: OPERATIONAL DOORS The C-40C illustrated here is the current and EMERGENCY EXITS proposed cabin configuration. This is the low volume with Divan configuration. WINDOWS

CURRENT CONFIGURATION 44 Total Passengers 8 Conference 4 Crew Seating

PROPOSED CONFIGURATION 40 Total Passengers 34 B/C Passengers 6 Conference 4 Crew Seating

ADDED CROSS-AISLE CURTAIN INDEPENDENT AREA ADDED LAV F AND REVISED G7 LIGHTING CONTROL (LOSS OF 2 SEATS) C- 40.

T.O. 00-105E-9 COMPOSITE MATERIALS LOCATIONS C-40

GRAPHITE WINGLETS TRAILING EDGE PANELS (AS INSTALLED)

FIBERGLASS RUDDER

FIBERGLASS/ TAIL CONE AILERON GRAPHITE ELEVATOR AILERON TAB DORSAL FIN

FLAP TRACK FAIRINGS

WING-TO-BODY FAIRING INBOARD AND OUTBOARD FIXED TRAILING EDGE

RADOME

OUTBOARD FIXED LEADING EDGE INBOARD FIXED LEADING THRUST REVERSER (FIBERGLASS) EDGE LOWER SKIN PANEL NOSE LANDING GEAR (FIBERGLASS) DOOR (GRAPHITE) C- 40.

T.O. 00-105E-9 SPECIAL TOOLS/EQUIPMENT 1c 1a C-40 Power Rescue Saw EMERGENCY OVERWING EXIT HATCHES 11 FWD AND AFT SERVICE DOOR 12 Foot Ladder EXTERNAL HANDLE (RT SIDE) PUSH PANEL (BOTH SIDES) Fire Drill II 1b SLIDING WINDOW AIRCRAFT ENTRY EXTERNAL ACCESS -600/-700/-800 BOEING BUSINESS JET SERIES DOOR

1. NORMAL/EMERGENCY ENTRY

CAUTION

When passenger and service doors are opened from outside, chutes will automatically deploy. 1b AFT ENTRY a. Push in top center panel on overwing escape hatches, 1b DOOR located on both fuselage sides. Push hatch inward and FWD ENTRY upward. DOOR b. Pull handle on forward and aft entry doors, located left side of fuselage, outward and rotate clockwise. Pull 1b doors outward. FWD AND AFT 4a c. Pull handle on right forward and aft service doors, out- ENTRY DOOR CUT-IN AREAS ward and rotate counterclockwise. Pull doors outward. EXTERNAL HANDLE (LT SIDE) 2. PILOT’S SLIDING WINDOW (RH & LH) CARGO AND RH ONLY PASSENGER AIRCRAFT 3a CARGO DOOR a. To open window from outside: push in external access DECAL WITH door. INSTRUCTIONS b. Pull external release handle and slide window open.

3. CARGO DOOR OPERATION (IF INSTALLED)

a. To open cargo door 1, unlock the external door handle. b. Verify unlocked light is illuminated. c. Hold the UP TO CANOPY switch in position until door motion stops.

4. CUT-IN

a. Cut into fuselage as the last resort. Metal cutting portable power equipement is required. Use caution BATTERY IS ACCESSIBLE when cutting due to passenger location in relation to E/E COMPARTMENT FROM FWD CARGO cutting location. ACCESS DOOR COMPARTMENT C- 40.

T.O. 00-105E-9 ENGINE SHUTDOWN C-40 12 1. ENGINE SHUTDOWN OR a. Retard thrust levers, located on pilot’s center console, to RETARD position. 1f b. Retard engine start levers, located on pilot’s BATTERY console, to CUT OFF position. SWITCH 1e c. In case of engine fire, pull appropriate engine APU MASTER SWITCH fire T-handles, located on center console forward of thrust levers. Turn right or left to 1a discharge agent. If not illuminated, push and THRUST hold the button under the switch to release. LEVERS

d. In case of APU fire, pull the APU fire T-handle, located on center console forward of thrust levers. Turn right or left to discharge agent.

e. Place APU master switch up to OFF position 1d OR OFF position. (Switch type can vary.) APU FIRE SWITCH f. Lift guard and place battery switch, located on pilot’s center overhead panel, to OFF position. 1b ENGINE START LEVERS

1c ENGINE FIRE T-HANDLES C- 40.

T.O. 00-105E-9 AIRCREW EXTRACTION 1c C-40 13 1. AIRCREW EXTRACTION SHOULDER HARNESSES NOTE: 1b Due to the possibilty of several configurations for ARMRESTS seating and cargo, the following seat arrangements may or may not be encountered. The flight deck configuration is fixed with two seats. There is no flight engineer seat. If seat tracks are not damaged during crash landing use adjustable seat control handles to retract seats to aft position. 1c LAP BELT a. FLIGHTDECK SEATS - Unlatch lap belt and remove shoulder harness from the pilot and co-pilot. Use horizontal adjustment handle on pilot’s and copilot’s FLIGHTDECK WITH TWO SEATS 1b seat, and swivel adjustment handle to position seats. ARMREST ADJUSTMENT b. Raise armrests to up position and depress armrest adjustment release under pilot’s and copilot’s armrests, and raise up to position. 1a HORIZONTAL 1c c. Rotate lap belt release mechanism, remove shoulder ADJUSTMENT CROTCH harness and crotch strap (as applicable). HANDLE STRAP d. CONSOLE SEATS - These seats may be equipped with a shoulder harness and lap belt. Unlatch restraints as necessary to free occupants. 1b ARMREST e. PASSENGER’S SEATS - Passengers seats are equipped with lap belts only. Lift center latch connecting 1c 1c both sides of belt to release occupant. SHOULDER HARNESS LAP BELT

1c 1a CROTCH SWIVEL STRAP ADJUSTMENT HANDLE FORE AND AFT RELEASE TYPICAL CONSOLE SEAT LEVERS (IF INSTALLED) C- 40.

T.O. 00-105E-9 EMERGENCY RESCUE ACCESS C-40 14 1. EMERGENCY RESCUE ACCESS

a. Use the two forward entry doors.

b. Use the two overwing escape doors. WINGLETS (AS INSTALLED) c. Use the two aft service doors.

1c AFT SERVICE DOOR

1b AFT CARGO RT DOOR OVERWING ESCAPE DOORS OPERATING INSTRUCTIONS ON DOOR

1c AFT ENTRY DOOR “CHOP OUT” AREAS FWD RT CARGO DOOR OPERATING INSTRUCTIONS “CHOP OUT” AREAS ON DOOR

1a FWD SERVICE DOOR WINGLETS (AS INSTALLED)

CARGO DOOR (IF INSTALLED) “CHOP OUT” AREAS LOCATED BETWEEN WING FRONT SPAR AND ESCAPE HATCH (THREE BAYS) BELOW PILOT’S SLIDING 1a WINDOWS AND ABOVE FLOORS WINDOW AVERAGE DISTANCE - FWD ENTRY DOOR FLOOR LEVEL TO GROUND WHEELS RETRACTED: 5 FT WHEELS EXTENDED: 8 FT. 6 IN. C- 40.

T.O. 00-105E-9 EMERGENCY EXITS AND EVACUATION ROUTES C-40 15 1. EMERGENCY EXITS AND EVACUATION ROUTES

a. Use the two forward entry, two overwing escape, two aft service doors, or the two forward flightdeck sliding windows as emergency exits.

b. The sliding #2 window emergency exits are equipped with stowed ropes or straps used to lower personnel who choose these exits. These windows can be opened externally as well as internally. To open either window, depress trigger, turn handle back and inboard. Slide window until it locks in the open position.

c. Use the evacuation route closest to your location. Some doors are equipped with emergency chutes that are automatically deployed when a door or hatch are opened from the inside.

1a, 1b SLIDING WINDOW EMERGENCY EXIT