r-813 737-400 afms

7765 NW 54th ST Miami, FL 33166

B737-300/400

FLIGHT CREW OPERATIONS MANUAL

SUPPLEMENT

When equipped with

CARGO DOOR AND CLASS “E” CARGO

COMPARTMENT INSTALLATION

AEI REPORT R-932

This supplement must be attached to the applicable Flight Crew Operations Manual when the airplane is modified with the installation of the Aeronautical Engineers Inc. Cargo Door and Class “E” Cargo Compartment in accordance with

STC ST01827LA

The information contained in this supplement supersedes the basic manual only in those areas listed herein. For Limitations, Procedures, and Performance information not contained in this Supplement, consult the basic Airplane Flight Manual and other approved supplements.

Revision G

Oct 15, 2021

RELEASED 10/15/2021

737-300/400 Flight Crew Operations Manual

Supplement

TABLE OF CONTENTS

TABLE OF CONTENTS ...............................................1 SECTION 0 – PREFACE ............................................ 2 SECTION 1 - CERTIFICATE LIMITATIONS ................ 6 SECTION 2 - NORMAL PROCEDURES ..................... 12 SECTION 3 - NON-NORMAL PROCEDURES ............ 23 SECTION 4 - SYSTEM DESCRIPTION ...................... 32 SECTION 5 - EMERGENCY EQUIPMENT ................. 38

This supplement is divided into five sections: System Description, which contains descriptive airplane system information for components modified by the cargo conversion, Certificate Limitations, Emergency Procedures, Normal Procedures, which contain detailed procedures for operating the components added or modified by the cargo conversion, and Performance.

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737-300/400 Flight Crew Operations Manual Supplement

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SECTION 0 - PREFACE

0.1 GENERAL

This manual consists of two documents which contain the required supplemental information required for the operation of the 737-300/400 airplane with cargo door conversion. The first document, the Quick Reference Handbook (QRH) supplement, contains emergency procedures extracted from the operating procedures section in this second document, the Flight Crew Operations Manual Supplement.


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0.2 REVISION RECORD

REV PAGES DATE DESCRIPTION

- 1-38 July 16,

2013 Initial Issue

A 39-42 Sep 24,

2013 Added Emergency

Equipment Location

B ALL Oct 23, 2013 Added Fig. 6o

C 36-38 Sep 16,

2014 Added O2 Tables for

115 ft3 Tanks

D

34-39

Sep 14,

2016

Added O2 Tables for 39 ft3 cylinder and single 39, 76, 115 cylinders, updated all O2 tables

D 34-39 Sep 14,

2016 Added O2 Tables for 39 ft3 cylinder and single

E 30 Nov. 30

2016 Revised §4.2.5.d to

clarify door inspection

F

ALL

Jun 07, 2021

Added 737-300 aircraft to this FCOM including Center Circuit Breakers

to Appendix 31-33

G

26, 27

Oct 15, 2021

Updating 3.3 Main

Cargo Door Warning


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0.3 LIST OF EFFECTIVE PAGES

Page Date Page Date

1 Oct 15, 2021 21 Oct 15, 2021

2 Oct 15, 2021 22 Oct 15, 2021

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SECTION 1 - CERTIFICATE LIMITATIONS

1.1 MAIN DECK CARGO DOOR

WIND LIMIT

Do not open MAIN DECK CARGO DOOR in actual or anticipated winds exceeding 45 knots.

GROUND HANDLING

Aircraft is not to be taxied, towed or jacked unless the MAIN DECK CARGO DOOR is in the fully closed and latched position.

1.2 MAIN DECK CARGO COMPARTMENT SMOKE

DETECTOR SYSTEM

Preflight inspection of the system is required prior to each flight, or each series of flights by the same crew on the same day. See Normal Procedures section of this supplement.

Flight with freight in the Main Deck Cargo Compartment without at least one air conditioning pack operating is prohibited.

1.4 SECONDARY MAIN LANDING GEAR POSITION

INDICATING SYSTEM

Preflight inspection of the system is required prior to each flight or each series of flights by the same crew on the same day. See Normal Procedures section of this supplement under Miscellaneous Annunciators.

.


SECTION 1 - CERTIFICATE LIMITATIONS (Continued)

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1.1 CENTER OF GRAVITY ENVELOPE - B737-300

The forward center of gravity limit is moved aft for higher weights. Refer to the AEI Weight & Balance Control Loading Manual Supplement, Report No. R-778 Revision S, dated May 15, 2020 or later approved Revision for revised C.G. Envelopes with forward C.G. cutback

1.2 CENTER OF GRAVITY ENVELOPE – B737-400

The forward center of gravity limit is moved aft for higher weight. See Figures 6a through 6n on the following pages for the new envelope. Determine C.G. envelope chart applicability by using the MTOW limit for the aircraft as defined in the FAA approved Flight Manual and the corresponding chart in this supplement.



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1.3 MINIMUM OPERATING WEIGHT

Minimum Operating Weight 737-300 is 74,628 pounds. Minimum Operating Weight 737-400 is 78,000 pounds.

1.4 WEIGHT & BALANCE CONTROL AND LOADING

LIMITATIONS

Refer to the Weight and Balance control and loading Manual supplements as follows:

B737-300 Refer to AEI Report No. R-778 Revision T dated Jan 20, 2021 or later approved Revision

B737-400 Refer to AEI Report No. R-809 Revision R dated May 15,2020 or later approved Revision

1.5 MAIN CARGO COMPARTMENT AIR SUPPLY SHUTOFF

Functionally operate the Main Cargo Compartment Air Supply Shutoff Valve to insure proper operation, prior to each flight, or each series of flights by the same crew on the same day. See Normal Procedures section of this supplement.

1.6 SUPERNUMERARIES

Passengers known as “supernumeraries” may be carried in the area between the flight deck and the 9G barrier subject to the following limitations:



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For flights conducted in accordance with the United States Federal Aviation Regulations: The supernumeraries are limited to the categories specified in §§121.583(a)(1) through 121.583(a)(7).

For flights conducted in accordance with European Aviation Safety Agency (EASA) regulations: Supernumeraries are limited to the category of persons set forth below:

a. Crew members; b. Employees of the aircraft operator; c. Inspectors or other authorized by EASA

d. Any person who is determined by the aircraft operator to be necessary for:

(1) The safety of the flight (2) The safe handling of animals; (3) The security of valuable of

confidential cargo; (4) The preservation of fragile or

perishable cargo; (5) The loading or unloading of cargo; (6) The iteration of special equipment

for loading or unloading; or, (7) The safe handling of hazardous

materials.

e. Persons traveling to or from an assignment by the operator involving a function escribed in subsection d, above; or

f. Such other persons authorized by the Operational Authority regulating the aircraft operator



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1. For flights conducted in accordance with the regulations other than the United States or EASA.

a. Such other persons authorized by the Operational Authority regulating the aircraft operator

2. A maximum of four supernumeraries may occupy the area aft of the flight deck and forward of the 9G bulkhead. The total maximum occupancy of the airplane is limited to six persons, including the flight crew (two on- duty flight crew members, and up to four off-duty flight crew members, observers, or supernumeraries).

3. Supernumeraries are prohibited from being in the cargo area during any flight operation. The pre-flight briefing must inform supernumeraries of this requirement. If supernumeraries are on the aircraft, one must sit in the seat adjacent to the communications phone and warning lights and be trained to communicate cockpit instructions to all other supernumeraries on board.

4. Prior to each flight, a flight crew member must brief each supernumerary on the use of exits, including instructions to inspect the ground to determine whether a safe landing can be achieved before using an assist means and emergency equipment.

5. The operator must determine that each supernumerary is physically able and trained to accomplish the necessary emergency procedures.



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6. The supernumeraries must be trained in the use of the oxygen units. The supernumeraries must also be trained in making the determination whether oxygen is being delivered to the dispensing units.

7. Decompression Alert: An automatically activated aural and visual decompression alert must be provided and immediately recognizable throughout the supernumerary seating area to notify supernumeraries when to don oxygen masks. The pre-flight briefing must include training in the meaning of the alert, and the response to the alert (i.e., procedures for donning the mask and activating the flow of oxygen).

8. Turbulence, Alert: A flight crew activated visual alert, which is recognized in the supernumerary seating area, must be installed to indicate that, in the event of turbulence, or predicted turbulence, persons must return to their seats. Appropriate procedures and limitations must be established to ensure that, at the onset of turbulence, the flight crew alerts the supernumeraries to return to their seats. The pre-flight briefing must explain these alerts to the supernumeraries.


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SECTION 2 – NORMAL PROCEDURES

2.1 VB SPEED (Design speed for maximum gust intensity.)

VB = 264 KIAS or 0.65 Mach whichever is lower.


PRE-FLIGHT CHECK

1. Aircraft Ground Power Bus is active.

2. With the cargo door in the fully open position, verify the indicator lights on the Control and Relay Box and Pilot and First Officer’s instrument panels are illuminated.

3. Close door per normal operating procedure, below. As the door moves to the fully closed position, monitor the door and lights on the Pilot’s, First Officer’s instrument panel and Control and Relay Box to verify:

a. Main Cargo Door Not Closed light is extinguished

b. Hooks Unlocked and Latches Unlocked lights are extinguished

c. Latch Lock Pin Not Engaged light is extinguished

d. Vent Door Open light is extinguished e. All cargo door related lights on the Control and

Relay Box and cockpit instrument panel are extinguished

4. Return the cargo door Master Power Switch to the OFF position and put the switch guard down.


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SECTION 2 – NORMAL PROCEDURES (Continued)

5. From the exterior of the aircraft verify:

a. Through the forward and aft View Ports that

the lock pins are through the latches b. Through the upper View Port, the black and

yellow flag is visible c. The Vent Doors are fully closed and flush with

the cargo door d. The cargo door is flush with the surrounding

fuselage

TO OPEN MAIN DECK CARGO DOOR (Ground operation

only)

1. Turn the Power Master Control Switch, on the Cargo Door Control Panel, to the ON position. Upon selecting the cargo door control to the door OPEN position, the vent doors open and the lock system retracts. The Master Door Warning Light on the Control and Relay Box and the Cargo Door Warning Lights on the cockpit instrument panels will illuminate.

2. Select OPEN on the Door Control Switch. The motor and pump will operate, building hydraulic pressure through the electrically positioned control valve, and supply pressure to the door OPEN hydraulic lines. The latches unlatch and the door opens. When the door reaches its full up position, a micro switch will shut off power to the pump, stopping the door. Return the Door Control Switch to the neutral position. All Cargo Door Warning Lights should be illuminated under this condition.

4. Switch the Master Power Control Switch OFF and put the guard down.


SECTION 2 - NORMAL PROCEDURES (Continued)

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TO CLOSE MAIN DECK CARGO DOOR (Ground operation

only)

1. Turn the Power Master Control Switch to the ON position.

2. Select CLOSE on the Door Control Switch.

This will activate the pump, sending pressure through the closing lines of the cargo door, and through the electrically positioned selector valve.

a. The door will reach the closed position, extinguishing the “Main Cargo Door Not Closed” light on the control panel.

b. When the door has reached its full down position, the torque tube rotates and the latch hooks move down onto the spools, then move over center, pulling the cargo door into the latched position, and extinguishing both the “Hooks Unlocked”, and “Latches Unlocked” lights on the control panel.

c. The Gang Bar actuator then operates. This pushes the lock pins into place in all latches and closes the two vent doors simultaneously.

3. Verify all Door Warning lights on the Control and Relay Box and on the cockpit instrument panel are extinguished.

4. Move the Door Control Switch to the center position and the Power Master Control Switch to the OFF position and lower the guard over the switch



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DETECTOR SYSTEM

PRE-FLIGHT CHECK

Main Deck Cargo Compartment Smoke Detector Panel. 1. Press-To-Test Switch .................. PRESS and HOLD 2. Verify 12 smoke detector lights ................. ON 3. Verify both MAIN CARGO SMOKE (red) lights .... ON

Note: The MAIN CARGO SMOKE (red) lights are located on each pilots’ lower instrument panel.

2.4 MISCELLANEOUS ANNUNCIATORS

PRE-FLIGHT CHECK-COCKPIT

Press-To-Test each of the following annunciators

1. CARGO DOOR (P/CP) 2. CARGO DOOR ARMED 3. CABIN AIR SHUTOFF CLOSED

4. SECONDARY MAIN LANDING GEAR DOWN AND LOCKED INDICATORS (2 lights)

Note: These lamps must be tested by Press-to-Test as they are not integrated into the cockpit annunciator test Circuit.



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2.5 MAIN DECK CARGO COMPARTMENT AIR SUPPLY

SHUTOFF

PRE-FLIGHT OPERATIONAL CHECK

Cabin Air Shutoff Control Panel. 1. Cabin Air Shutoff Switch- Guard……UP 2. Cabin Air Shutoff Control Switch ...... CLOSED 3. Verify Cabin Air Shutoff CLOSED Indicator (Amber) 4. light .................................................. ON 5. Cabin Air Shutoff Control Switch ...... OPEN 6. Cabin Air Shutoff Switch Switch-Guard…DOWN 7. Verify Cabin Air Shutoff CLOSED Indicator (Amber)

light ....... OFF

2.6 PRE-FLIGHT BRIEFING

If supernumeraries are to be carried on the flight, the captain shall ensure each supernumerary is briefed on: the proper use of seat belts; two-way communications; emergency equipment; exits; emergency procedures; use of oxygen equipment; the meaning of the decompression alert and the procedures for donning the oxygen mask and activating the flow of oxygen; the meaning of the turbulence alert and response thereto; that the Class E compartment may not be accessed during flight; that the smoke barrier must remain closed during flight; and that smoking is not allowed on the aircraft.



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2.7 FLIGHT CREW OXYGEN SYSTEM

PRE-FLIGHT CHECK

1. Check flight crew oxygen system pressure based on number of crew and flight duration to ensure minimum

2. required pressure is available in accordance with tables below.



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Required Pressure (PSI) for One (1) 39 + One (1) 76.5 Cubic Foot Cylinder

60 minutes on 100% Oxygen at 25,000 FT

Bottle Temperature Number of Crew Using Oxygen

°C °F 2 3 4

50 122 500 710 920

45 113 495 700 905

40 104 490 690 895

35 95 480 680 880

30 86 475 670 865

25 77 470 660 855

20 68 465 650 840

15 59 455 645 830

10 50 450 635 815

5 41 445 625 800

0 32 435 615 790

-5 23 430 605 775

-10 14 425 595 765




°C °F 2 3 4

50 122 630 875 1110

45 113 625 865 1090

40 104 615 850 1075

35 95 605 840 1060

30 86 600 825 1045

25 77 590 815 1030

20 68 580 800 1015

15 59 570 790 995

10 50 565 775 980

5 41 555 765 965

0 32 545 755 950

-5 23 540 740 935

-10 14 530 730 920




°C °F 2 3 4

50 122 815 1140 1450

45 113 800 1120 1430

40 104 790 1105 1405

35 95 780 1090 1385

30 86 770 1075 1365

25 77 755 1055 1345

20 68 745 1040 1325

15 59 735 1025 1300

10 50 725 1010 1280

5 41 710 990 1260

0 32 700 975 1240

-5 23 690 960 1215

-10 14 680 945 1195



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°C °F 2 3 4

50 122 335 460 590

45 113 330 455 580

40 104 330 450 570

35 95 325 445 565

30 86 320 440 555

25 77 315 435 550

20 68 315 425 540

15 59 310 420 535

10 50 305 415 525

5 41 300 410 520

0 32 300 405 510

-5 23 295 400 500

-10 14 290 390 495




°C °F 2 3 4

50 122 415 560 700

45 113 410 555 695

40 104 405 545 685

35 95 400 540 675

30 86 395 530 665

25 77 390 525 655

20 68 385 515 645

15 59 380 510 635

10 50 375 505 625

5 41 370 495 615

0 32 365 490 605

-5 23 360 480 595

-10 14 355 475 590




°C °F 2 3 4

50 122 525 720 910

45 113 520 710 895

40 104 510 700 885

35 95 505 690 870

30 86 495 680 855

25 77 490 670 845

20 68 485 660 830

15 59 475 650 820

10 50 470 640 805

5 41 465 630 795

0 32 455 620 780

-5 23 450 610 770

-10 14 445 600 755



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Required Pressure (PSI) for One (1) 39 Cubic Foot Cylinder



°C °F 2 3

50 122 1335 1950

45 113 1315 1915

40 104 1290 1885

35 95 1270 1855 30 86 1250 1825

25 77 1230 1795

20 68 1210 1765 15 59 1190 1735

10 50 1170 1705 5 41 1150 1675

0 32 1130 1645

-5 23 1110 1615

-10 14 1090 1585

(60 minute min pressure is based on mimimum supply volume required by Boeing AFM)




°C °F 2

50 122 1705

45 113 1680

40 104 1655

35 95 1630 30 86 1605

25 77 1580

20 68 1555 15 59 1530

10 50 1505 5 41 1480

0 32 1455

-5 23 1430

-10 14 1405


SECTION 2- NORMAL PROCEDURES (Continued) Required Pressure (PSI) for One (1) 76 Cubic Foot Cylinder


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°C °F 2 3 4

50 122 735 1050 1370

45 113 725 1035 1345

40 104 715 1020 1325

35 95 700 1005 1300

30 86 690 990 1280

25 77 680 970 1260

20 68 670 955 1240

15 59 655 940 1220

10 50 645 920 1200

5 41 635 905 1175

0 32 620 890 1155

-5 23 610 875 1130

-10 14 600 860 1110





°C °F 2 3 4

50 122 910 1280 1630

45 113 900 1260 1605

40 104 885 1240 1580

35 95 870 1220 1560

30 86 860 1205 1535

25 77 845 1185 1510

20 68 835 1165 1485

15 59 820 1150 1465

10 50 810 1130 1440

5 41 795 1110 1415

0 32 785 1095 1390

-5 23 770 1075 1365

-10 14 755 1055 1345




°C °F 2 3

50 122 1185 1675 45 113 1170 1650

40 104 1150 1625

35 95 1135 1600 30 86 1115 1575

25 77 1100 1550

20 68 1085 1530 15 59 1065 1505

10 50 1050 1480

5 41 1030 1455 0 32 1015 1430

-5 23 1000 1405

-10 14 980 1380


SECTION 2 - NORMAL PROCEDURES (Continued) Required Pressure (PSI) for One (1) 115 Cubic Foot Cylinder


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°C °F 2 3 4

50 122 530 735 945

45 113 520 725 930

40 104 510 715 915

35 95 505 700 900

30 86 495 690 885

25 77 485 680 870

20 68 480 670 860

15 59 470 655 840

10 50 460 645 830

5 41 455 635 815

0 32 445 620 800

-5 23 440 610 785

-10 14 430 600 770





°C °F 2 3 4

50 122 635 880 1115

45 113 625 865 1095

40 104 615 855 1080

35 95 610 840 1065

30 86 600 830 1050

25 77 590 815 1035

20 68 585 805 1015

15 59 575 790 1000

10 50 565 780 985

5 41 555 770 970

0 32 550 755 955

-5 23 540 745 940

-10 14 530 730 920




°C °F 2 3 4

50 122 815 1145 1455

45 113 805 1125 1435

40 104 795 1110 1415

35 95 785 1095 1390

30 86 770 1075 1370

25 77 760 1060 1350

20 68 750 1045 1330

15 59 740 1030 1305

10 50 725 1010 1285

5 41 715 995 1265

0 32 705 980 1245

-5 23 690 965 1220

-10 14 680 945 1200


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CAUTION: AFTER LANDING, KEEP COCKPIT DOOR AND

WINDOWS CLOSED UNTIL READY TO EGRESS.

SECTION 3 NON-NORMAL PROCEDURES

3.1 CARGO SMOKE ANNUNCIATORS (RED) ILLUMINATE

1. Oxygen Masks and Regulators ......................... ON, 100% 2. Smoke Goggles (If required)… ............................. ON 3. Crew Communications ................................... ESTABLISH 4. Cabin Air Shutoff Valve ................................. CLOSED 5. Cabin Air Shutoff CLOSED light. ....................VERIFY ON 6. Isolation Valve ............................................... CLOSED 7. Left or Right Air Conditioning Pack ................. AUTO 8. Associated Engine Bleed Switch .................... VERIFY ON 9. Associated Engine Thrust… ............................ MIN 70 % N1 10. Other Air Conditioning Pack .......................... OFF 11. Cabin Air Recirculating fan(s)1 .................................. OFF 12. Cockpit Air Conditioning Outlets .....................OPEN 13. Land as soon as possible. If a suitable airport is not

immediately available, manually control the cabin altitude to 20,000 to 25,000 ft. until decent to the first suitable

14. Upon departing 20,000 ft., in the landing descent, 15. depressurize the airplane completely. 16. Pressurization Mode Selector ......... MANUAL (AC or DC) 17. Outflow Valve Switch ......... OPEN, TO SET REQUIRED

CABIN PRESSURE.

1NOTE: This step only applies to aircraft on which the recirculation fan(s) is active and operational.

3.2 ONE OR BOTH MAIN LANDING GEAR POSITION

INDICATORS SHOW UNSAFE

1. Verify the Gear Handle is DOWN. 2. Verify Secondary Main Gear Down and Locked

Indicators, on aft P5 overhead panel, are illuminated green. Main Landing Gear is down and locked as long as:


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WARNING: DO NOT ATTEMPT TO OPERATE CARGO DOOR DURING

TAKEOFF, IN FLIGHT OR DURING LANDING.

SECTION 3 NON-NORMAL PROCEDURES (Continued)

3. At least one green landing gear indicator (center panel or overhead panel) is illuminated for the left gear main and for the right main gear.

4. If lights are not illuminated, follow standard flight manual procedures for unsafe landing gear.

3.3 MAIN CARGO DOOR WARNING LIGHT(S) LLUMINATE

MAIN CARGO DOOR WARNING DURING TAKEOFF (BEFORE V1)

Main Cargo Door Warning Light(s) Illuminates with or without Takeoff Configuration Warning Horn 1. Abort takeoff

MAIN CARGO DOOR WARNING DURING TAKEOFF (AFTER V1)

Main Cargo Door Warning Light(s) Illuminates with or without Takeoff Configuration Warning Horn 1. Continue takeoff 2. Do not pressurize 3. Return to departure airport 4. Plan to land at nearest suitable airport


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SECTION 3- NON-NORMAL PROCEDURES (Continued)

MAIN CARGO DOOR WARNING DURING FLIGHT

Main Cargo Door Warning Light(s) Illuminates 1. Don oxygen masks 2. Establish crew communications 3. Passenger Oxygen ON (if required) 4. Depressurize

5. Descend to lowest safe altitude or 10,000 FT whichever is higher

6. Plan to land at nearest suitable airport

Condition: One or both of the Main Cargo Door Warning light(s) Illuminate.

Warning! Do not attempt to operate cargo door during

takeoff, in flight or during landing.

Main Cargo Door Warning Light(s) Illuminate with or without Takeoff Configuration Warning Horn during takeoff, before V1:

Abort Takeoff

Main Cargo Door Warning Light(s) Illuminate with or without Takeoff Configuration Warning horn during

Takeoff, after V1:

Continue takeoff. Do not pressurize. Return to departure airport Plan to land at nearest suitable airport.


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Airplane has reached the planned cruise altitude:

>> Go to step 7

Airplane has not reached planned cruise altitude:

Do not continue the climb

Reset FLT ALT indicator to the actual airplane

altitude

>> Go to step 7

7. LAND ALT Indicator… ................ 9000 feet

Minimum safe altitude is at or below 9000 feet:

>> Go to step 8

Minimum safe altitude is between 9000 feet and 13,000

feet:

>> Go to step 10

Minimum safe altitude is at or above 13,000 feet:

>> Go to step 10

8. Descend to 9000 feet

9. Maintain a cabin differential pressure of 0 psi by limiting

flight altitude to 9000 feet

>> Go to step 15

10. Descend to the minimum safe altitude

11. Land ALT indicator. .Select a higher altitude (maximum

13,000 feet) to maintain a cabin differential pressure of

0 psi

NOTE: The intermittent cabin altitude/configuration warning

horn will sound and the CABIN ALTITUDE lights (if

installed and operative) will illuminate at a cabin

altitude of approximately 10,000 feet.

>>Go to step 15


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12. Descend to the minimum safe altitude.

13. Pressurization mode selector MAN

NOTE: Use momentary actuation of the outflow valve

switch to avoid large and rapid pressurization

changes.

14. Outflow VALVE switch Move to OPEN until the

outflow VALVE indication shows fully open to

depressurize the airplane.

NOTE: The intermittent cabin altitude/configuration warning

horn will sound and the CABIN ALTITUDE lights (if

installed and operative) will illuminate at a cabin

altitude of approximately 10,000 feet.

15. Plan to land at the nearest suitable airport.

16. When the cabin altitude is at or below 10,000 feet:

Oxygen masks may be removed.


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SECTION 4 – SYSTEM DESCRIPTION


The Main Deck Cargo Door is operated by a hydraulic/electrical system independent of the ship’s systems. Electrical power for the hydraulic pump is supplied from the Battery Bus. The hydraulic/electrical system is operated from a Main Deck Cargo Door Control and Relay Box located on the front of the 9g cargo barrier. The door is provided with a Collective Locking System and a system of micro switches which indicate whether the door is closed, the latches are activated and the lock pins are engaged. There are door-warning lights on the Control and Relay Box (see Fig. 2), and on the pilot’s and copilot’s instrument panels (see Fig. 1).

In the cockpit, there is one Cargo Door (red) annunciator on the lower instrument panel in front of each pilot, and one Cargo Door Armed annunciator in the top center of the instrument panel, above the engine instruments. The Cargo


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MAIN

CARGO

SMOKE

CARGO

DOOR

SECTION 4 SYSTEM DESCRIPTION (Continued)

Door Annunciators illuminate any time the door is not closed and locked. The Cargo Door Armed annunciator illuminates any time the cargo door Power Master Control switch on the Control and Relay Box is in the ON position.

The Cargo Door warning system is connected in parallel to the existing aircraft Takeoff Configuration Warning. If during take-off roll the cargo door is not properly closed, latched and locked, the Takeoff Warning intermittent horn will sound.

Three exterior View Ports are installed to visually verify from outside the airplane that the cargo door is latched and locked (see Fig. 7). The cargo door is equipped with two vent doors to prevent cabin pressurization unless the cargo door is fully closed, latched and locked. The main deck cargo door is electrically un-powered in flight.

Fig. 1. Cargo Door and Cargo Smoke annunciators


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SECTION 4 – SYSTEM DESCRIPTION (Continued)


DETECTOR SYSTEM

Twelve smoke detectors are mounted in the main deck cargo compartment ceiling and are connected to the Main Deck Cargo Smoke Detection System panel. This panel is located in the cockpit aft P5 overhead panel (see Fig. 3). Cargo Smoke Annunciator (red) lights are located at the bottom of the captain’s and first officers’ instrument panels (see Fig. 1). These two red lights are Press-to-Test lamps and do not dim. The smoke detection system is armed when the No. 2 Main DC bus is energized. Each smoke detector contains an illuminated internal lamp and a light sensor. When the air passing through a detector unit reaches a predetermined smoke density, the internal lamp illumination is reflected on the sensor and a signal is sent to the respective cargo smoke indicator light. The lights remain on until the smoke clears from the detector housing.


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SECTION 4– SYSTEM DESCRIPTION (Continued)

MAIN DECK CARGO DOOR CONTROL AND RELAY BOX

Fig. 2


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The Main Deck Cargo Smoke Detection System panel contains twelve individual numbered Smoke Detector lights to indicate which detector(s) has sensed smoke (see Fig. 3).The lights are numbered 1 through 12, and correspond to detectors from front to rear of the main deck cargo compartment. A smoke detector test switch is located on the panel to enable a test of the smoke detectors and lights. When this switch is pressed-to-test, the Smoke Detection System lights illuminate, the two Main Cargo Smoke (red) annunciators also illuminate, one in front of each pilot (see Fig. 3).

Fig. 3.


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4.2 MAIN CARGO COMPARTMENT AIR SUPPLY

SHUTOFF SYSTEM

The Main Cargo Compartment Air Supply Shut-off System uses two valves to close off the supply of ECS air from the mix manifold to the main cargo compartment during smoke emergencies. The shut-off valves are powered from the No. 2 DC Main bus. The valves are controlled by a guarded, OPEN/CLOSED switch located on the cockpit aft P5 overhead panel (see Fig. 4). An adjacent amber light illuminates when the valves are CLOSED. The valves must remain in the OPEN position during all normal operating conditions. In the CLOSED position all airflow to the main cabin is shut off and airflow only continues to the flight deck.

Fig. 4.


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SECTION 4 – SYSTEM DESCRIPTION (Continued)

4.3 SECONDARY MAIN LANDING GEAR POSITION

INDICATING SYSTEM

A Secondary Main Landing Gear Position Indication System has been installed on the cockpit overhead P5 panel to provide the flight crew a back-up means of verifying that the main landing gear is down and locked. This system is provided because the cabin-located main landing gear viewing port is not accessible in flight. The panel consists of two green press-to-test lights to show when the gear is down and locked (see Fig. 5). Each main landing gear has a separate back-up gear down and locked sensor to support these Secondary indicators.

Fig. 5

APPENDIX


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CIRCUIT BREAKERS - B737-300

The following circuit breakers were changed, as indicated, by the Passenger to Freighter conversion:

Circuit Breakers Added - AC

LABEL AMPS CIRCUIT BREAKER

PANEL

CABIN LIGHTS 10.0 P18-3 CABIN LIGHTS 10.0 P18-3

FLOOD LIGHT 5.0 P18-3

ENTRY AREA LIGHTS 5.0 P18-3

Circuit Breakers Added - DC

LABEL AMPS CIRCUIT BREAKER PANEL

CARGO DOOR CONTROL

7.5 P6-2

LIGHTS, CONTROL 3.0 P18-3

CARGO DOOR INDICATION

5.0 P6-2

SMOKE DETECTOR 5.0 P6-2

CABIN CONTROL 5.0 P6-1

HYDRAULIC PUMP 80.0 J9 (BATT SHIELD) TCAS / GPWS SPKR 1.0 P18-1

SEC MLG 2.0 P18-1


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CIRCUIT BREAKERS - B737-300 (Continued)

GALLEY SYSTEM NO. 1 50.0 P6-11


LAV MIRROR LIGHT, AFT 5.0 P18-3

LEFT READING 10.0 P18-3

VACUUM CLEANER RECPTACLE, FWD

10.0 P18-4

CEILING LTS, LEFT 10.0 P18-3

CEILING LTS, CONT 3.0 P18-3

GALLEY LTS 5.0 P18-3

CEILING LTS, RIGHT 10.0 P18-3

VACUUM CLEANER RECPTACLE, AFT

10.0 P18-4

WINDOW LIGHTS, LEFT 7.0 P18-3

WINDOW LIGHTS, RIGHT

7.0 P18-3

BRIGHT, ENTRY LIGHTS 3.0 P18-3

NIGHT LTS CONTROL 3.0 P18-3 CEILING LT BRT CONT 3.0 P18-3

NO SMOKING SIGNS 5.0 P18-3

GND SERV NIGHT LTS CONT

3.0 P18-3

LAV C FLUSH MOTOR 3.0 P18-4

CEILING LIGHTS, RH 10.0 P18-3

LAVATORY “C” WATER HEATER

5.0 P18-4

RIGHT READING 10.0 P18-3


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Circuit Breakers Removed – DC (Collared)

LABEL AMPS CIRCUIT

BREAKER

PANEL 28 VOLT SVCE OUTLET 5.0 P6-3

WATER QTY IND 5.0 P18-4

PASSENGER OXYGEN - RIGHT

5.0 P18-3

CIRCUIT BREAKERS – B737-400

The following circuit breakers were changed, as indicated, by the Passenger to Freighter conversion:

Circuit Breakers Added - AC


CABIN LIGHTS 10.0 P18-3



FLOOD LIGHT 5.0 P18-3

ENTRY AREA LIGHTS 5.0 P18-3



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Circuit Breakers Added - DC


CARGO DOOR CONTROL

7.5 P6-2

CARGO DOOR INDICATION

5.0 P6-2

SMOKE DETECTOR 5.0 P6-1

CABIN CONTROL 5.0 P6-1

SEC MLG 2.0 P6-1

TCAS / GPWS SPKR 1.0 P18-1

LIGHTS, CONTROL 3.0 P18-3

HYDRAULIC PUMP 80.0 J9 (BATT SHIELD)



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Circuit Breakers Removed – AC (Collared)

LABEL AMP S

CIRCUIT BREAKER PANEL



LAV MIRROR LIGHT, AFT

5.0 P18-3

LEFT READING 10.0 P18-3

VACUUM CLEANER RECPTACLE, FWD

10.0 P18-4

CEILING LTS, LEFT 10.0 P18-3

CEILING LTS, CONT 3.0 P18-3

GALLEY LTS 5.0 P18-3

CEILING LTS, RIGHT 10.0 P18-3

VACUUM CLEANER RECPTACLE, AFT-4

10.0 P18-4

WINDOW LIGHTS, LEFT 7.0 P18-3

WINDOW LIGHTS, RIGHT

7.0 P18-3

BRT, ENTRY LTS 3.0 P18-3

NIGHT LTS CONTROL 3.0 P18-3

CEILING LIGHTS, CONT 3.0 P18-3

NO SMOKING SIGNS 5.0 P18-3

GND SERV NIGHT LTS CONT

3.0 P18-3

LAV C FLUSH MOTOR 3.0 P18-4

CEILING LIGHTS, RH 10.0 P18-3

LAVATORY “C” WARER HEATER

5.0 P18-4

RIGHT READING 10.0 P18-3



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Circuit Breakers Removed – DC (Collared)

LABEL AMPS CIRCUIT BREAKER

PANEL

28 VOLT SVCE OUTLET 5.0 P6-3

WATER QTY IND 5.0 P18-4

PASSENGER OXYGEN - RIGHT

5.0 P18-3


MAIN DECK CARGO DOOR EXTERNAL VIEWPORTS

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Fig. 7


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EMERGENCY EQUIPMENT LOCATION

Fig 1 Emergency Equipment Supernumerary Area - Two Passengers


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EMERGENCY EQUIPMENT LOCATION (Continued)

Fig 2 Emergency Equipment Supernumerary Area - Four Passengers

r-813 737-400 afms

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