RFP-Attachment8 FCF CGTO6CF.pdf

CGTO 1C−130H−6CF

1 NOVEMBER 2005

COAST GUA

TECHNICAL MANUAL

ACCEPTANCE AND/OR FUNCTIONAL CHECK

FLIGHT

(ACF/FCF)

PROCEDURES

C−130H

USCG SERIES AIRCRAFT

COMMANDING OFFICERS ARE RESPONSIBLE FOR BRINGING THIS PUBLICATION TO THE

ATTENTION OF ALL AFFECTED PERSONNEL.

DISTRIBUTION STATEMENT − Distribution authorized to U.S. Government agencies and their contrac-tors (Administrative or Operational Use) (1 NOVEMBER 2005). Other requests for this document shall be referred to Commanding Officer, CG Aircraft Repair and Supply Center, Technical Publications Cell, Eliza-beth City, NC 27909.

PUBLISHED UNDER THE AUTHORITY OF THE COMMANDANT OF THE

UNITED STATES COAST GUARD

CGTO 1C−130H−6CF dated 1 November 2005 supersedes all previous versions in their entirety. Destroy all copies of CGTO 1C−130−6CF not dated 1 November 2005.

1 NOVEMBER 2005

COAST GUA

TECHNICAL MANUAL

ACCEPTANCE AND/OR FUNCTIONAL CHECK

FLIGHT

(ACF/FCF)

PROCEDURES

C−130H

USCG SERIES AIRCRAFT

COMMANDING OFFICERS ARE RESPONSIBLE FOR BRINGING THIS PUBLICATION TO THE

ATTENTION OF ALL AFFECTED PERSONNEL.

DISTRIBUTION STATEMENT − Distribution authorized to U.S. Government agencies and their contrac-tors (Administrative or Operational Use) (1 NOVEMBER 2005). Other requests for this document shall be referred to Commanding Officer, CG Aircraft Repair and Supply Center, Technical Publications Cell, Eliza-beth City, NC 27909.

PUBLISHED UNDER THE AUTHORITY OF THE COMMANDANT OF THE

UNITED STATES COAST GUARD

CGTO 1C−130H−6CF dated 1 November 2005 supersedes all previous versions in their entirety. Destroy all copies of CGTO 1C−130−6CF not dated 1 November 2005.

A USCG

Title 0

A 0

Highlights 1/2 blank 0

Record of Revisions 1/2 blank 0.

i−iv 0

1−58 blank 0

LIST OF EFFECTIVE PAGES

DATES OF ISSUE FOR ORIGINAL AND CHANGE PAGES ARE :

Original 0 1 November 2005

Page No.

Change No.

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 70, CONSISTING OF THE FOLLOWING:

UPON RECEIPT OF THE SECOND AND SUBSEQUENT CHANGES TO THIS TECHNICAL ORDER, PERSON- NEL RESPONSIBLE FOR MAINTAINING THIS PUBLICATION IN CURRENT STATUS WILL ASCERTAIN THAT

ALL PREVIOUS CHANGES HAVE BEEN RECEIVED AND INCORPORATED. ACTION SHOULD BE TAKEN

PROMPTLY IF THE PUBLICATION IS INCOMPLETE.

ADDITIONAL COPIES OF THIS PUBLICATION MAY BE ORDERED FROM THE AIRCRAFT REPAIR

AND SUPPLY CENTER (ARSC) UTILIZING THE TECHNICAL INFORMATION MANAGEMENT AND

ORDERING SYSTEM (TIMOS). THE ORDER WILL BE SUBMITTED THROUGH YOUR UNIT’S TIMOS

OPERATOR.

Page No.

Change No. *

NOTE The portion of the text affected by changes is indicated by a vertical line in the outer margins of the page.

*Zero in this column indicates an original page.

ACCEPTANCE AND/OR FUNCTIONAL CHECK

FLIGHT PROCEDURES

CGTO 1C−130H−6CF

HIGHLIGHTS

To: Holders of CGTO 1C−130H−6CF, ACCEPTANCE AND/OR FUNCTIONAL CHECK FLIGHT (ACF/FCF) PROCE-

DURES MANUAL

Highlights: Manual Revision dated 1 November 2005.

Comments regarding the contents of this manual, including those of an editorial nature, are encouraged and should be forwarded to ARSC Technical Publications Cell. Technical changes to this manual should be accomplished via the CG−22 process.

REVISED PAGES DESCRIPTION OF MATERIAL ADDED / REVISED

List of Effective Pages Revised to reflect revision date.

Highlights Highlights pages describe the current changes made to an existing manual and very often contain information not repeated elsewhere in the manual. Highlights pages provide a historical record of the revisions to a manual and should be inserted directly behind the title page of the affected manual until superseded by the Highlights pages for the next revision.

Record of Revisions The Record of Revisions page shall be inserted in sequence after the Highlights page.

This page provides a readily available record of the status of the affected manual.

PAGE CG−22

NO.

DESCRIPTION OF CHANGE

ALL Removed CG−4377 form reference and replaced with EAL (Electronic Aircraft Logbook).

ALL Removed many of the references to specific aircraft series since most planes have been modified to operate the same. Also have changed the manual reference to add the “H” series to the name: CGTO 1C−130H−6CF.

11 Removed Autopilot (E−4) (if installed) paragraphs.

11 Removed Flaps (without GPWS) paragraph.

11 Dropped (GPWS installed) from Flaps (GPWS installed) paragraph header.

16/30 Removed note on 1500 series for UHF operation without external power.

17/31 Removed note that referenced the C−12 compass.

20 Removed Electrical system check along with the remaining subparagraphs.

25 Added to paragraph 167.v.: Torque and RPM.....“Checked” (E) and new note about torque.

28 Added new paragraph: Chip Detector......ON/Checked. Also added subparagraph : a. Check that all LEDs illuminate.

29 Removed paragraph: 248. Pitot heat....Checked (with LM) and all subparagraphs and note.

41 Added new item: Chip Detector....ON/Checked.

43 Removed Autopilot Check (E−4 Autopilot) paragraph and all the associated sub-paragraphs, note and cautions.

48 Changed Subparagraph 405.g. to read: At the onset of buffet or 98% RPM of any engine, note airspeeds and execute recovery. Also made this change to 405.m.

51 Removed note for checking voltage and frequency of generator before switching it to ON.

CGTO: 1C−130H−AVILSP

HIGHLIGHTS

52 Dropped (if VS equipped) from FCS−105 Descent Check (if VS equipped) para-graph header.

57 Dropped (if installed) from Ground Proximity Warning System (GPWS) (if installed) paragraph header.

57 Removed paragraph 438. Radome heat.....OFF. No longer installed.

58 Removed ILS Coupled Approach (E−4 Autopilot) paragraph and following asso-ciated subparagraphs.

58 Dropped (FCS−105 equipped) from ILS Coupled Approach (FCS−105 equipped) from paragraph header.

60 Removed paragraph 466. Radar altimeter (1500 series).......“OFF”.

ACCEPTANCE AND/OR FUNCTIONAL CHECK FLIGHT

(ACF/FCF) PROCEDURES MANUAL

CGTO 1C−130H−6CF

RECORD OF REVISIONS

PAGE 1/(2 BLANK)

RECORD OF REVISIONS

REV

NO.

REV DATE INSERT

DATE

INSERT

BY

NOVEMBER 1/05

REV

NO.

REV DATE INSERT

DATE

INSERT

BY

C.G.T.O. 1C−130H−6CF

i

TABLE OF CONTENTS

GROUND CHECKS (PREFLIGHT) 5

BEFORE INTERIOR INSPECTION 5

INTERIOR AND TOP OF AIRPLANE INSPECTION 5

FLIGHT DECK INSPECTION 5

EXTERIOR INSPECTION 15

COCKPIT CHECKLIST 15

BEFORE STARTING ENGINES CHECKLIST 16

ENGINE RUN UP CHECKLIST 17

ENGINE SHUTDOWN CHECKLIST 25

BEFORE LEAVING THE AIRPLANE CHECKLIST 25

DEBRIEFING 25

FLIGHT CHECKS (PREFLIGHT) 25

BEFORE INTERIOR INSPECTION 26

INTERIOR AND TOP OF AIRPLANE INSPECTION 26

FLIGHT DECK INSPECTION 26

EXTERIOR INSPECTION 27

COCKPIT CHECKLIST 28

BEFORE TAKEOFF 28

BEFORE STARTING ENGINES CHECKLIST 28

BEFORE TAKEOFF CHECKLIST 30

ENGINE RUN UP CHECKLIST 33

LINEUP CHECKLIST 33

TAKEOFF 33

AFTER TAKEOFF 34

AFTER TAKEOFF CHECKLIST 34

CLIMB 35

CLIMB CHECKS 35

CRUISE 39

CRUISE CHECKS 39

DESCENT 44

DESCENT CHECKLIST 44

BEFORE LANDING 54

BEFORE LANDING CHECKLIST 54

LANDING 56

ii

LANDING CHECKS 56

AFTER LANDING 56

AFTER LANDING (AFTER COMPLETION OF LANDING ROLL) CHECKLIST 56

ENGINE SHUTDOWN CHECKLIST 57

BEFORE LEAVING THE AIRPLANE CHECKLIST 57

DEBRIEFING 57

iii

INTRODUCTION

PURPOSE

1. The purpose of this manual is to:

a. Provide the procedures necessary to perform a complete Acceptance Check Flight (ACF) or Functional Check Flight (FCF) of United States Coast Guard C−130H airplanes.

b. Ensure proper completion of a single func-tional check by providing crews with equip-ment operating procedures, limits, pressure readings, and conditions to be noted and/or recorded.

c. Provide maintenance and flight crews with procedures emphasizing how a system or component will be checked while applying predetermined criteria.

d. Provide coverage of equipment that is pecu-liar to a specific airplane.

FORMAT AND CONTENT

1. The procedures in this manual are divided into two sections − Ground Checks and Flight Checks. The ground checks contain the required system and equipment checks that need to be accomplished prior to the ACF/FCF. The flight checks are not designed to be accomplished concurrent with the ground checks. Each checklist is complete and is formatted to stand alone.

2. The procedures in this manual are presented in a challenge and response checklist format. Pilot, Copilot, and Flight Engineer aircrew checklist procedures from CGTO 1C−130H−1 have been combined with specific ACF/FCF system and equipment checks to provide a single−source document for conducting an ACF/FCF. The manual is designed so that additional aircrew members (Navigator, Loadmaster, Radio Operator) will use their CGTO 1C−130H−1 normal aircrew checklists.

The CGTO 1C−130H−1 normal aircrew checklist items for Pilot, Copilot, and Flight Engineer are identified by circled numbers.

3. All items from the Before Starting Engines Checklist through the Engine Shutdown Checklist have verbal responses required.

4. Expanded or detailed information for the conduct of specific systems/equipment checks is provided where necessary. Amplified information pertaining to the circled items incorporated in this manual is found in CGTO 1C−130H−1.

5. Refer to CGTO 1C−130H−1 for definition/ explanation of capital letters, quotation marks, commas, and virgules.

INSTRUCTIONS

1. These procedures will be used when and as directed by COMDTINST M13020.1 (series) Aeronautical Engineering Maintenance Management Manual.

Descriptions of check flights are as follows:

a. ACF. Includes flight tests for performance and operation of systems/equipment to verify contractual conformance. This is applicable to all airplanes on production, maintenance, or modification (PDM) contracts.

b. FCF. Flight tests conducted for other than contractual conformance. FCF missions are flown to check the operation of selected sys-tems or equipment that require flight verifica-tion. Full ACF/FCF profiles are flown when required.

2. When full ACF/FCF profiles are flown, the pilot, copilot, and flight engineer will use this manual in lieu of the CGTO 1C−130H−1 aircrew checklists.

When an FCF is flown to check only selected systems, equipment, or areas of performance, the flight crew may be briefed to employ their normal aircrew checklists, using specific procedures in this manual only during the checks of the specific items requiring the FCF.

3. The checklist is designed to be read by a single crewmember. Each crewmember will complete the functions applicable to his position and respond, as shown, when the check is complete. Spoken responses are identified in quotation marks with the crewmember(s) responding identified in parentheses. For “As required” or “State setting” responses, the actual position, setting, or operating status of the system will be given as the response.

Sub−items of a procedure which require action by more than one crew position, list the crew position(s) responsible for specific actions identified in parentheses.

Flight engineer items, or system checks not re-quiring coordination, may be accomplished prior to the challenge, as practical, beginning with the Before Starting Engines checklist through the Af-ter Landing checklist. This does not preclude re-sponse to the checklist when the item is called out.

iv

The Navigator and Radio Operator, if aboard, will use their normal aircrew checklists, CGTO 1C−130H−1CL−2 and CGTO 1C−130H−1CL−4, as applicable. They will place into operation and check their equipment in accordance with CGTO 1C−130H−1.

The loadmaster will use the loadmaster checklist, CGTO 1C−130H−1CL−3; performing duties in accordance with CGTO 1C−130H−1 and assist-ing with ACF/FCF checks as directed.

4. Upon satisfactory completion of the ACF/FCF, the Aircraft Commander will sign the certification in the space provided in the EAL, or other approved form, to certify that the required checks have been completed. Discrepancies discovered during the course of an ACF/FCF will be recorded in the EAL or other approved form.

5. Data recorded during functional checks will be entered on MPC 056000.0 and filed in the EAL or other approved form.

6. The procedures in this manual incorporate and/or supplement the normal procedures contained in CGTO 1C−130H−1. It may be necessary during some specific ACF/FCF checks to vary from normal procedures to verify settings, automatic functions, or backup systems. When a conflict exists, the procedures contained herein prevail while the particular check is being conducted, and normal procedures from CGTO 1C−130H−1 will resume upon completion of the check. Emergency actions or operations will be conducted in accordance with

CGTO 1C−130H−1.

ACF/FCF PROFILE CHART

The ACF/FCF Flight Profile Chart provides a rec-ommended profile for conduct of a typical flight.

(See figure 1.) Although the profile chart dis-plays a logical sequence for conduct of systems/ equipment checks, it is recognized that circum-stances may require deviation from the listed sequence. Factors such as weather, air traffic, available altitudes, etc., must be considered by the aircrew in deciding how the actual profile will be flown.

ACF/FCF Profile Chart

COUPLED ILS

LEADING EDGE ANTI−ICING

NEGATIVE TORQUE SYSTEM

FLIGHT INSTRUMENTS

ALTITUDE ALERTER

FCS 105 VERTICAL MODES

COMMUNICATIONS AND NAVIGATION SYSTEMS

PROPELLER AND ENGINE ANTI−ICE

FUEL SYSTEM

OUTFLOW VALVE

ENGINE POWER

FUEL GRAVITY FEED

PRESSURIZATION

PROPELLERS

APU

NESA

IFF AND ENCODING ALTIMETER

AUTO PILOT

CRUISE ALTITUDE 17,000’ TO 26,000’ MSL

CRUISE CHECKS

DESCENT CHECKS

STALLS

PROPELLER FEATHERING

TRIM CHECK

MAXIMUM AIRSPEEDCLIMB CHECKS

AFTER TAKEOFF CHECKS

RADAR ALTIMETER

PRESSURIZATION AND AIR CONDITIONING

SAFETY CHECK

GPWS

GO AROUND

BEFORE LANDING CHECKLIST

DESCENT CHECKLIST

FLAP WARNING

RAMP AND DOOR

LANDING GEAR

FIELD ELEVATIONGPWS

AFTER LANDING

Figure 1.

PROPELLER REVERSING

BRAKES AND ANTI−SKID

AFTER LANDING, ENGINE SHUTDOWN

BEFORE LEAVING AIRPLANE

DEBRIEFING

THIS PROFILE CONTAINS SUGGESTED

ALTITUDES FOR PERFORMING EACH

CHECK. DEVIATIONS ARE PERMISSIBLE

CHECKING AT SPECIFIED ALTITUDES/

SEQUENCE.

IF WEATHER, TRAFFIC, ETC., PREVENT

BEFORE TAKEOFF

BRIEFING

AIRCRAFT FORMS

PREFLIGHT CHECKS

COCKPIT CHECKLIST

BEFORE STARTING ENGINES CHECKLIST

BEFORE TAKEOFF CHECKLIST

ENGINE RUN UP CHECKLIST

LINEUP CHECKLIST

300’ TO 2,500’

200’ TO 400’ AGL

10,000’ TO 14,000’

TAKEOFF

4,000’ TO 6,000’

ACF/FCF SYSTEMS CHECKS QUICK REFERENCE INDEX

Phase of Flight/Subject Page Number

AFTER LANDING 56

AFTER TAKEOFF 34

GPWS (Don’t Sink) Check 34

Pressurization 34

Radar Altimeter 34

BEFORE LANDING 54

Go Around 55

GPWS Glide Slope Warnings 55

ILS Coupled Approaches 54

BEFORE TAKEOFF 28

Brakes 32

Hydraulic Systems 30

Nose Wheel Steering 32

Propeller and Engine Anti−Icing 37

CLIMB 35

Altitude Alerter Climb Checks 36

FCS−105 Climb Check 36

Flight Instruments 36

Fuel System 38

Leading Edge Anti−Icing System 35

Negative Torque Systems 35

Pilots’ Communication and Navigation Systems 37

Pressurization (Automatic) and Outflow Valve 38

CRUISE 39

Auxiliary Power Unit 42

Cabin Pressurization Leak Check 40

Engine Power Check 39

Flight Control System (FCS−105) 41

Fuel Gravity Feed 39

IFF and Encoding Altimeter 43

Low Cabin Air Pressure Warning System 42

Pressurization (Manual) and Safety Valve 40

Underfloor Heat System 42

Phase of Flight/Subject Page Number

Windshield Anti−Icing System (HI) 43

Windshield Anti−Icing System (NORMAL) 42

DESCENT 44

Altitude Alerter Descent Checks 48

Cargo Ramp and Door Check 52

FCS−105 Descent Check 49

Ground Proximity Warning System (GPWS) 53

Landing Gear Checks 50

Maximum Airspeed Check 44

Propeller Feathering and Engine Airstart Checks 46

Stall Characteristics 45

Wing Flap Normal Operation 49

FLIGHT CHECKS (PREFLIGHT) 25

GROUND CHECKS (PREFLIGHT) 5

AC Bus Tie (if installed) 6

Air Conditioning and Pressurization Systems 24

Air Deflector Doors 13

Airplane Doors and Door Warning System 9

Engine Bleed Air, Bleed Air Divider, and Wing Isolation Valves 6

Flaps and GPWS 11

Flight Control System (FCS 105) 12

Flight Controls 12

Fuel Governing, Pitchlock, and Engine Power Checks 22

Hydraulic Control Boost Shutoff Switches and Valves 19

Hydraulic Suction Boost Pumps 8, 19

Left Exterior Lights 13

Low Speed Ground Idle Buttons 8

Oil Cooler Flaps 8

Pitot Heat 14

Pressurization System Safety Valve 7

Propeller Droop Check 21

Propeller Reindexing 22

Propeller Static Feather Check 14

Propulsion System Checks 20

3/(4 blank)

Phase of Flight/Subject Page Number

Right Exterior Lights 14

Wing Flaps Emergency Operation 8

LANDING 56

Brakes and Anti−Skid 56

Propeller Reversing 56

TAKEOFF 33

GROUND CHECKS (PREFLIGHT)

These checklists incorporate those briefings, inspec-tions, and airplane system checks required to prepare the airplane for the flight portion of the ACF/FCF. The checklist is designed to be read by a single crewmember who normally will occupy the copilot seat during the per-formance of these checks. Checks requiring coordi-nated, combined actions list the crew position responsi-ble for specific portions of the check identified in parentheses, i.e., (E) (LM). Checklist items referring to

(P) or (CP) are intended to be completed by the crew-member occupying the position at pilot or copilot.

1 ACF/FCF ground run briefing Completed

The briefing will be conducted by Quality Assurance personnel with particular emphasis on areas in which major maintenance was performed or areas where the completion of maintenance requires the ACF/FCF.

BEFORE INTERIOR INSPECTION

EAL/Forms Checked

Prior to entrance Checked

INTERIOR AND TOP OF AIRPLANE INSPECTION

Crew entrance area Checked

Cargo compartment area − left side Checked

Ramp area − left side Checked

Ramp area − right side Checked

Cargo compartment area− right side Checked

Top of airplane Checked

FLIGHT DECK INSPECTION

Hydraulic panel Set

Landing gear lever DN

IFF (APX−100) OFF

Copilot’s portable oxygen bottle and refiller hose Checked

Alarm bell Checked (with LM)

Jump signals Checked (with LM)

Feather valve and NTS check switch NORMAL

Copilot’s circuit breaker panel Checked

Navigator ’s station Checked

a. TAS probe heater switch OFF

Radio operator’s station Checked

Life raft release handles IN, Shear−wired

Oxygen system pressure Checked

Miscellaneous and emergency equipment Checked

Galley switches OFF

Crew entrance−door jettison handle NORMAL, Shear−wired

Note

The fuel governing check switch guards should be safetied if use is not anticipated.

Fuel governing check switches NORMAL

Pressurization test valves OPEN, Safetied

Emergency depressurization handle IN, Shear−wired

Pilot’s circuit breaker panel Checked

Pilot’s portable oxygen bottle and refiller hose Checked

Air conditioning panel Set

GTC/APU panel Set

Anti−icing panel Set

Flare launcher panel Checked

Wing and engine bleed air valves and switches Set

Fuel panel Set

TCAS Standby

ADS control panel switch OFF

Electrical panel Set

Fire handles and test panel IN, Checked

CDNU ON

Radio (VHF) ON, Checked

Chip Detector ON, Checked

a. Check that all LEDs illuminate for approxi-mately 7 to 10 seconds and then extinguish.

GTC/APU Checked

Bleed air system Checked Leak down time “Recorded” (E)

ATM and generator/APU generator Checked,.

ON

46 AC bus tie (if installed) Checked

a. AC bus tie switch ON

(1) Check that the MAIN AC OFF light is extinguished and that the AC bus tie SW ON light is illuminated.

b. AC bus tie switch OFF

(1) Check that the MAIN AC OFF light is illuminated and the AC bus tie SW ON light is extinguished.

Note

If external AC power is available, the ATM/ APU generator may be turned off at this time and the ATM switch placed to STOP. Place ex-ternal AC power switch to EXT AC PWR.

47 Engine bleed air, bleed air divider, and wing isolation valves Checked

This check will be coordinated and performed with the loadmaster.

a. ATM generator and ATM OFF, STOP (E).

b. Bleed air manifold Pressurized

c. Bleed air divider and wing isolation valves “OPEN” (LM)

d. Engine bleed air, valve/regulator switches CLOSE/OFF (E)

e. Clear No. 1 engine “No. 1 Clear” (LM). .

f. No. 1 ground start switch START (E)

Note

The loadmaster should observe the propeller for rotation. If propeller rotates, it is an indication of leakage past the engine bleed air shutoff valve/regulator. Perform an operational check of the bleed air system in accordance with T.O.

1C−130H−2−21JG−10−1, as applicable.

g. No. 1 engine ground start switch Released (E)

h. Repeat steps e., f., and g. for the remaining engines.

i. Engine bleed air valve switches OPEN/OVRD (E)

Perform steps j. through n. for airplanes with bleed air di-vider valve. For airplanes not equipped with bleed air di-vider valve, proceed with step o.

j. Bleed air divider valve switch CLOSE (E)

k. Clear No. 3 engine “No. 3 Clear” (LM). . .

l. No. 3 engine ground start switch START (E)

Note

The loadmaster should observe the propeller for rotation. If propeller rotates, it is an indication of leakage past the bleed air divider valve. Per-form an operational check of the bleed air sys-tem in accordance with T.O.

1C−130H−2−21JG−10−1, as applicable.

m. No. 3 engine ground start switch Released (E)

n. Bleed air divider valve switch OPEN (E). .

o. Wing isolation valve switches CLOSE (E)

p. Clear No. 2 engine “No. 2 Clear” (LM). . .

q. No. 2 engine ground start switch START (E)

Note

The loadmaster should observe the propeller for rotation. If propeller rotates, it is an indication of leakage past the left wing isolation valve.

Perform an operational check of the bleed air system in accordance with T.O.

1C−130H−2−21JG−10−1, as applicable.

r. No. 2 engine ground start switch Released (E)

s. Clear No. 3 engine “No. 3 Clear” (LM). . .

t. No. 3 engine ground start switch START (E)

Note

The loadmaster should observe the propeller for rotation. If propeller rotates, it is an indication of leakage past the right wing isolation valve.

Perform an operational check of the bleed air system in accordance with T.O.

1C−130H−2−21JG−10−1, as applicable.

u. No. 3 engine ground start switch Released (E)

v. Engine bleed air valve switches CLOSE/OFF (E)

w. ATM and ATM generator ON, Checked, ON (E)

x. Wing isolation valves OPEN (LM)

48 Pressurization system safety valve Checked. . .

This check will be coordinated and performed with the loadmaster.

a. Bleed air manifold Pressurized (E)

b. Air conditioning shutoff switches NORMAL

c. Air conditioning master switch AUTO PRESS (E)

(1) Ensure safety valve is closed. (LM)

d. Emergency depressurization switch EMERGENCY

DEPRESSURIZATION (E)

Observe that the safety valve opens and airflow from the flight deck and cargo compartment air conditioners ceases. (LM)

e. Emergency depressurization switch NORMAL (E)

Observe that the safety valve closes and airflow from the flight deck and cargo compartment air conditioners be-gins. (LM)

f. Air conditioning master switch NO PRESS (E)

Observe that the safety valve opens. (LM)

g. Air conditioning master switch MAN PRESS (E)

Observe that the safety valve closes. (LM)

h. Air conditioning master switch AUX VENT (E)

Observe that the safety valve opens. (LM)

i. Air conditioning master switch OFF (E). . .

Observe that the safety valve closes. (LM)

49 ATM and generator/APU and generator As required

Note

If external AC power is available, the ATM gen-erator, ATM, and GTC (or APU generator and APU) may be shut down at this time.

50 Low speed ground idle buttons Checked

a. Throttles GROUND IDLE

b. Ground idle buttons LOW SPEED

Advance throttles until low speed ground idle buttons pop out. Throttles should be aligned and at approximate-ly 30 degrees throttle position. Return throttles to

GROUND IDLE.

c. Ground idle buttons LOW SPEED

Retard throttles until low speed ground idle buttons pop out. Throttles should be aligned and at approximately 9 degrees throttle position. Return throttles to GROUND

IDLE.

Generator disconnect Checked

Inverter systems Checked

Fuel quantity and distribution Checked

Fuel system Checked

Surface boost shutoff switches ON, Shear−wired

56 Oil cooler flaps Checked

a. Place the oil cooler flaps switches to AUTO- MATIC, manual CLOSE, and manual OPEN positions, and observe cooler flap operation with the position indicator.

b. Open the cooler flaps fully and return the oil cooler flap switches to FIXED.

Warning press−to−test lights Checked

58 Hydraulic suction boost pumps Checked, OFF

a. Place utility and booster system suction boost pump switches to ON. Note that the suction pump low pressure lights are extin-guished. Return switches to OFF.

59 All hydraulic systems pressure Depleted

a. Pump brake pedals to deplete all hydraulic system pressure before opening or closing the ground test valve.

CAUTION

When positioning the hydraulic ground test valve to either the opened or closed position, be sure the handle is moved through its full arc of travel and the internal ball detent in the valve engages. The engagement of the ball detent can be felt in the handle. If this is not done, exces-sive return line pressures can cause damage to hydraulic motors.

60 Hydraulic ground test valve “Open” (LM)

61 Cargo door and ramp controls “NEUT, 6N”(LM)

WARNING

If the cargo door and/or ramp manual con-trol handle/knob is in other than NEUT/6N, the door/ramp may open/close when the auxiliary hydraulic pump is turned on, caus-ing injury to personnel in the area.

62 Wing flaps emergency operation Checked

Check wing flap emergency operation using the follow-ing procedures:

a. Ensure the wing flaps are up, the flap lever is up, and hydraulic pressures are depleted.

Pull wing flap control circuit breaker. (E)

b. Establish communications between the flight station and crewmember (LM) sta-tioned at the forward face of the left wheel well. The flight engineer and loadmaster will coordinate the remaining steps. (E) (LM)

c. Remove the handcrank from the stowed position. Engage the handcrank on the input shaft. (LM)

d. Place the flap control handle to the full DN position.

e. Pull the manual shift “T” handle and rotate 1/8 turn counterclockwise. Handle travel shall not exceed 2 (�0.25) inches. The force required to pull the handle shall not exceed 120 pounds.

f. Remove the pin from the emergency exten-sion stub shaft.

g. Use a torque wrench on the emergency extension stub shaft to extend flaps to the full down position.

h. Observe operation of the flaps. Torque shall not exceed 100 inch−pounds, and flaps shall move smoothly with no evidence of binding.

When the flaps reach the full down position, the slip clutch shall release at a torque value of between 460 to 510 inch−pounds on manual gearbox P/N 2196D or between 350 and 475 inch−pounds on gearbox P/N 2196E.

i. Place the flap control handle to the full up position.

j. Use a torque wrench on the emergency extension stub shaft to retract flaps to the full up position.

k. Observe operation of flaps. Torque shall not exceed 100 inch−pounds, and flaps shall move smoothly with no evidence of binding.

When the flaps reach the full up position, the slip clutch shall release at a torque of between 460 and 510 inch−pounds on manual gearbox P/N 2196D or between 350 and 475 inch−pounds on gearbox P/N 2196E.

l. Return the manual shift “T” handle to its nor-mal position by rotating 1/8 turn clockwise and pushing in.

m. Verify proper positioning of the drive gear by rotating the manual operation stub shaft slowly one turn each way. No appreciable force shall be needed to rotate the stub shaft.

The torque shaft shall not rotate.

n. Rotate input shaft several turns to assure manual drive disengagement. (LM)

o. Replace pin in the input shaft, remove the hand−crank, and return it to the stowed posi-tion. (LM)

p. Flap lever UP (E)

q. Auxiliary hydraulic pump ON (E)

CAUTION

When manual override button is first depressed, after shifting from manual to hydraulic drive, observe the utility hydraulic pressure and flap position indicator. A drop in pressure with no flap movement indicates a failure of the flap normal drive to reengage. If this happens, re-lease manual override button immediately.

Failure to observe this caution may result in damage to the flap drive unit.

r. Ensure wing flaps are clear. Extend the wing flaps to the 50 percent position in 10 percent increments, using the wing flap selector valve manual override LOWER button.

Visually check flaps at 50 percent position. (LM)

s. Retract flaps to full up position using the wing flap selector valve manual override RAISE button. Visually check flaps full up. (LM)

t. Auxiliary hydraulic pump OFF (E)

u. Wing flap control circuit breaker Reset (E)

63 Airplane doors and door warning system Checked

Check the doors and door warning system using the fol-lowing procedures:

a. Station loadmaster inside the airplane on in-terphone. (E) (LM)

b. Close all airplane doors. (LM)

c. Ensure that the master and all individual door warning lights are extinguished. (E) (LM)

d. Open crew entrance door. Check that the master and crew entrance door warning lights illuminate. (E) (LM)

e. With crew entrance door open, move crew entrance door handle to closed. The master and crew entrance door warning lights should remain illuminated. Depress and hold the door closed switch located at the aft upper corner of the door opening. The mas-ter and crew entrance door warning lights should be extinguished. Move crew entrance door handle to open. The master and crew entrance door warning lights should be illu-minated. Release the door open switch.

Place the crew entrance door master door warning light shutoff switch to OFF and ob-serve that the master door warning light ex-tinguishes. (E) (LM)

f. Open left paratroop door. The master and left paratroop door warning lights should illumi-nate. Place the left paratroop master door warning light switch to OFF. The master door warning light should extinguish. Re-turn master door warning light shutoff switch to NORMAL. The master and left paratroop door warning lights should illuminate. Close left paratroop door and observe that the mas-ter and left paratroop door warning lights ex-tinguish. (E) (LM)

g. Repeat step f. for right paratroop door.

h. Ensure ramp and door controls are in 6N and NEUT and that ramp support arms are con-nected. (LM)

i. Using the controls at the ramp and door con-trol panel, place the auxiliary hydraulic pump switch to ON and the door control switch to OPEN. The cargo door should move toward the open position, and the mas-ter and ramp door warning lights should illu-minate. Place the door control switch to CLOSE. The cargo door should close, and the master door warning lights should extin-guish. (E) (LM)

j. Place the ramp control switch to LOWER.

The ramp should move toward open and the master and ramp warning lights should illu-minate. Place the ramp control switch to

RAISE. The ramp should close and the mas-ter and ramp door warning lights should ex-tinguish. (E) (LM)

k. Hold the door and ramp control switches to OPEN and LOWER until the cargo door is open and locked and the ramp is lowered to the full extension of the ramp support arms.

The master ramp door, and ramp warning lights, the airdrop position light on the ramp and door control panel, and the ramp and door open light on the ADS panels should be illuminated. (E) (LM)

l. Place the “ramp door” and “ramp” master door warning light shutoff switches to OFF.

The master door warning light should extinguish. Place the “ramp door” master door warning light shutoff switch to NOR- MAL. The master door warning light should illuminate. Place the “ramp” master door warning light shutoff switch to OFF. The master door warning light should extinguish.

Place the “ramp” master door warning light shutoff switch to NORMAL. The master door warning light should illuminate. Place the “ramp door” master door warning light shutoff switch to NORMAL. The master door warning light should remain illumi-nated. (E) (LM)

m. Place the door and ramp control switches to CLOSE and RAISE, until the cargo door and ramp are closed and locked. The master door warning lights for ramp door and ramp, and the airdrop position ramp and door open lights should be extinguished. Place auxilia-ry hydraulic pump switch to

OFF. (E) (LM)

n. Return the crew entrance door master door warning light shutoff switch to NORMAL.

The master door warning light should illumi-nate. (E) (LM)

64 Auxiliary hydraulic pump switch ON

ADI warning flags Checked

Note

During the flaps checks, check the flap indica-tor readings with flap lever at UP, 50 PER- CENT, and DN. The flap indicator should read UP (�0) with flaps UP, 50 (�8) with flaps at 50 PERCENT, and DOWN (�7) with flaps

DN.

66 Flaps (GPWS installed) Clear, DN 100 percent, checked

Note

Movement of the flaps is essential at this time to perform an operational check of the Ground Proximity Warning System (GPWS), and to en-able detection of hydraulic leaks or malfunc-tions during the walk−around inspection.

a. Set the GPWS FLAPS and WHEELS over-ride switches to NORM.

b. Set the flap control between 0 and 35 percent.

c. Press and hold the pilot’s PULL UP/GPWS Test annunciator/switch. The following re-sults should be observed:

(1) Both BELOW GS annunciators illuminate.

(2) The GPWS INOP annunciator illuminates.

(3) The “GLIDE SLOPE” aural warning is heard over the flight station loudspeaker and pilot and copilot headsets.

(4) Both “PULL UP” annunciators flash.

(5) The “WHOOP WHOOP PULL UP” aural warning is heard over the flight station loudspeaker and pilot and copilot headsets.

d. Release the pilot’s PULL UP/GPWS Test an-nunciator/switch after the second “whoop whoop pull up” aural warning. Results:

(1) The “WHOOP WHOOP PULL UP” aural warning is heard once more, with increased volume.

(2) Aural warnings cease and all GPWS annunciators extinguish.

e. Set the GPWS FLAPS and WHEELS over-ride switches to OVRD.

f. Press and hold the pilot’s PULL UP/GPWS Test annunciator/switch. The following re-sults should be observed:

(1) Both GPWS OVRD annunciators illuminate.

(2) Both PULL UP annunciators remain extinguished.

(3) The GPWS INOP annunciator illuminates.

(4) Both GS annunciators illuminate.

(5) The “GLIDE SLOPE” aural warning is heard once over the flight station loudspeaker and pilot and copilot headsets.

g. Release the pilot’s PULL UP/GPWS Test an-nunciator/switch. All GPWS annunciators extinguish.

h. Return GPWS FLAPS and WHEELS over-ride switch to NORM.

i. Set the flap control lever beyond 40 percent.

j. Press and hold the pilot’s PULL UP/GPWS Test annunciator/switch. The following re-sults should be observed:

(1) Both BELOW GS annunciators illuminate.

(2) The GPWS INOP annunciator illuminates.

(3) The “GLIDE SLOPE” aural warning is heard once over the flight station loudspeaker and pilot and copilot headsets.

k. Release the pilot’s PULL UP/GPWS Test an-nunciator/switch. All GPWS annunciators extinguish.

l. Repeat steps d. through k. using the copilot’s PULL UP/GPWS Test annunciator/switch.

m. Press the GPWS INOP annunciator. It should illuminate. Release and it should ex-tinguish.

n. Press and hold AL−101 RADALT test switch. After a nominal 5 seconds, ensure the GPWS INOP annunciator illuminates.

Release Radalt test switch.

o. Set flap lever to DN (100 percent).

67 Flight controls Checked (with LM)

a. Check for free and correct movement of all flight controls.

Trim tabs Checked (with LM)

a. Check direction and movement of all tabs and coordination with the indicators. Check the elevator tab runaway override feature.

Position the elevator tab power switch to EMER and check emergency elevator tab trim control. Check for no trim with power switch in OFF, then return switch to NOR- MAL. Zero trim tabs.

b. On aircraft with dual elevator tab switches installed, actuate the switches on each con-trol wheel one switch at a time in both NOSE UP and NOSE DOWN directions. Check that no trim tab movement occurs.

69 Flight control system (FCS 105) Checked

Note

� Airflow that opposes control surfaces in flight is ab-sent during preflight. It is possible to get maximum control surface deflection if an autopilot command remains active for any appreciable time. When using the turn and pitch controls, move them only as re-quired to check control operation, then return them to center.

� Copilot’s AC instrument switch and the elevator tab power switch must be in the NORMAL position. If

G/A annunciator light(s) is illuminated, press P/S or SYN push button (as applicable) on corresponding control wheel to extinguish the light.

a. Check the flight control system’s mode an-nunciator lights and HSI miles display (0888).

b. Test both attitude director indicators. Check that the attitude display indicates a change of 10 (�3) degrees pitch−up and 20 (�5) de-grees right bank, and that the gyro warning flag comes into view.

c. Set both heading markers to the lubber line.

d. Center all flight controls.

e. Engage autopilot.

f. Relax centering force on column. Observe that elevator trim tab is driving nose up and that both ELEV TRIM annunciator lights are illuminated.

g. Slowly exert a back force on the control col-umn until a nose down trim direction is observed, hold this column position. Press and hold the TRIM MONITOR TEST switch. Check that the TRIM FAIL warning annunciator light starts flashing, the ELEV TRIM annunciator light remains illuminated and the elevator trim tab begins driving in the nose up direction. Release TRIM MON- ITOR TEST switch and observe that the TRIM FAIL light extinguishes, the ELEV TRIM light remains illuminated, and the ele-vator trim tab again moves in the nose down direction. Relax back force until control column is centered.

h. Depress HDG and ALT push button on both FLT SEL panels. Depress AP CPLD push button on No. 1 FLT SEL panel. Check that the pilot’s AP CPLD annunciator light illu-minates. Check that the pilot’s and copilot’s HDG and ALT HOLD annunciator lights il-luminate.

i. Slowly move pilot’s heading marker 10 de-grees right and left of the lubber line. Check that the control wheel turns right and left and the attitude director indicator command bars indicate right and left bank commands ap-propriately. Return heading marker to lubber line.

j. Depress AP CPLD push button on No. 2 FLT SEL panel. Check that the copilot’s AP CPLD annunciator light illuminates and the pilot’s extinguishes.

k. Slowly move copilot’s heading marker 10 degrees right and left of the lubber line.

Check that the control wheel turns right and left and the attitude director indicator com-mand bars indicate right and left bank com-mands appropriately. Return heading mark-er to lubber line.

l. Depress copilot’s G/A push button. Check the following:

(1) YD and AP switches move to

DISENGAGED.

(2) Copilot’s command bars indicate a 7−degree pitch−up command above zero attitude reference.

(3) Copilot’s G/A annunciator light illuminates.

(4) Both AP DISENG annunciator lights illuminate.

(5) Copilot’s HDG and ALT HOLD annunciator lights extinguish.

m. Depress the copilot’s P/S or SYN push but-ton. The G/A annunciator light will extin-guish, and the copilot’s ADI command bars will be removed from view.

n. Engage the autopilot.

o. Repeat steps l. and m., substituting the word “pilot’s” for “copilot’s.”

p. Engage the autopilot and depress the HDG, AP CPLD and any vertical mode (except ALT SEL) push buttons on No. 1 FLT SEL panel. Slowly rotate the AP pitch control to-ward UP. After aft column movement, rotate the AP pitch control toward DN. Release AP pitch control when the column starts for-ward. Check that the vertical mode disen-gages and its annunciator light extinguishes when the AP pitch control is moved from neutral.

q. Slowly rotate AP turn control to the right.

After right control wheel movement is ob-served, rotate AP turn control left past the center detent. After control wheel rotates left past center, use turn control to return the con-trol wheel to the center. Check that HDG and AP CPLD annunciator lights are extin-guished.

r. Depress pilot’s autopilot release switch. The AP and YD switches will move to the DIS- ENGAGED position and the AP DISENG annunciator lights will illuminate.

s. Engage the autopilot.

t. Repeat step r. using copilot’s release.

Depress the AP DISENG RESET switch and check that AP DISENG annunciator lights extinguish.

Zero the elevator trim tab.

70 Auxiliary hydraulic pump switch OFF

All hydraulic systems pressure Depleted

72 Hydraulic ground test valve “Closed”

(LM)

73 Air deflector doors OPEN, CLOSE, OFF

(check operation with LM)

74 Left exterior lights Checked (with LM)

a. Empennage navigation lights

b. Wing tip navigation light

c. Anti−collision lights

d. Leading edge light

e. Landing light

f. Taxi light

g. Upper navigation light

75 Pitot heat Checked (with LM)

CAUTION

Prior to checking pitot heat, ensure pitot covers have been removed.

a. Pilot’s pitot heat switch ON (E)

b. On airplanes without the Rosemount system, check that the pilot’s pitot tube element is heating. On airplanes with the Rosemount system, check that the No. 1 (upper left) and No. 3 (lower right) pitot tube elements are heating and the pilot’s pitot heat off light is extinguished. (E) (LM)

Note

The pilot’s and copilot’s pitot heat off lights il-luminate to indicate the respective system is turned off. Illumination of a light with the sys-tem turned on indicates an element in the re-spective system is inoperative.

c. Pilot’s pitot heat switch OFF (E)

d. Repeat steps a., b., and c., substituting the word “copilot’s” for “pilot’s,” and ensuring in step b. that the copilot’s pitot heat switch causes the No. 2 (upper right) and No. 4 (low-er left) pitot tube elements to heat.

76 Right exterior lights Checked (with LM)

a. Wing tip navigation light

b. Leading edge light

c. Landing light

d. Taxi light

e. Lower navigation light

77 Propeller static feather check Complete

Check each propeller using the following procedures:

CAUTION

Do not perform static feather check if engine oil temperature is 0 �C (32 �F) or below. If blade angle movement must be attempted, preheat propellers prior to beginning movement.

a. Place feather valve and NTS check switch to VALVE position.

b. Assure all fuel boost pumps are in the OFF position.

c. Place No. 1 throttle in MAXIMUM RE-

VERSE.

d. Place No. 1 condition lever to AIR START until propeller blade angle moves to max re-verse. Return condition lever to GROUND

STOP.

CAUTION

If the feather override button does not pop out within 5 seconds after completion of feather cycle, pull it out manually to shut off the pump.

Maintenance action is required prior to flight.

e. Pull No. 1 fire handle. The feather override button should pull in, the amber light in the button should illuminate, and the propeller should feather. The feather override button should pop out at completion of feather cycle. The propeller should move from re-verse to feather in a maximum time of 25 sec-onds.

f. Place No. 1 fuel boost pump switch to ON and monitor the No. 1 fuel low pressure light for a minimum of 30 seconds. The fuel low pressure light should remain illuminated as long as the fire handle is pulled.

g. Reset No. 1 fire handle, note that the No. 1 fuel low pressure light extinguishes, then place No. 1 fuel boost pump switch to OFF.

CAUTION

If the feather override button does not pop out within 5 seconds after completion of feather cycle, pull it out manually to shut off the pump.

Maintenance action is required prior to flight.

h. Place No. 1 condition lever to FEATHER.

Feather override button should pull in, amber light in button should illuminate, and feather valve light should illuminate. Feather override button should pop out in 5 seconds.

i. Place No. 1 throttle in GROUND IDLE posi-tion.

Note

When coming out of feather, observe that the propeller blades hesitate momentarily at flight idle blade angle (during retraction of low pitch mechanical stop) before continuing to ground idle blade angle.

j. Place No. 1 condition lever to AIR START.

Propeller blade angle should move to ground idle.

k. Return condition lever to GROUND STOP position.

l. Repeat steps b. through k. for remaining pro-pellers.

m. Place feather valve and NTS check switch to

NORMAL.

All unnecessary equipment OFF

Emergency exit light extinguish switch (if power is off) Depressed

EXTERIOR INSPECTION

Walk−Around Inspection

Conduct a walk−around inspection, following the route shown in CGTO 1C−130H−1. Check the exterior struc-ture of the airplane, including flight controls and flaps, for general condition and fluid leaks. Pay particular attention to the security of panels, doors, and wing lead-ing edge sections which may have been removed and re− installed during maintenance. If not previously checked by maintenance, a work stand/ladder will be required to check the engine inlets, exhaust areas, and the external tank caps. If required, these items may be accomplished at any time during the preflight inspection.

Nose section Checked

Forward fuselage, right side, and bottom Checked

Right wheel well area and center fuselage Checked

Right wing area Checked

Aft fuselage and empennage area Checked. . .

Left wing area Checked

Left wheel well area and center fuselage Checked

Forward fuselage, left side, and bottom Checked

COCKPIT CHECKLIST

Note

This checklist will be completed by the flight engineer prior to the BEFORE STARTING EN- GINES checklist. A crewmember will remain at the airplane after completion of this check-list. If this checklist is completed and the air-plane does not fly, complete the ENGINE SHUTDOWN checklist and the BEFORE LEAVING THE AIRPLANE checklist before securing the airplane.

NLG pin, pitot covers, dust excluders, duct plugs, and ground wires Removed

Radio operator’s panel (when R is not aboard) Checked

Navigator ’s panel (when N is not aboard) Set

a. TAS probe heater switch OFF

Circuit breakers Checked

Propeller panel Set

GPWS override switches (if installed) NORMAL

Paratroop panels Set

Air conditioning panel Set

GTC/APU panel Set

Anti−icing panel Set

Engine bleed air switches CLOSE/OFF

Fuel panel Set

Fire handles IN

Oil cooler flap switches As required

Landing gear lever DN

IFF master switch(es) STANDBY

Condition levers GROUND STOP

Throttles GROUND IDLE

Synchrophase master switch OFF

TD control valve switches AUTO

CDNU ON

Radios (as required) ON (if power is available)

BEFORE STARTING ENGINES CHECKLIST

Cockpit checklist “Complete” (E)

Forms “Checked” (P)

NLG lock and pitot covers “Removed” (E)

Safety belt “Fastened” (P) (CP)

Electrical control panel “Set” (E)

Radio (UHF or VHF) “Checked,.

(state radio) is primary” (CP)

Clear GTC/APU “Clear” (LM)

Start GTC/APU “Set” (E)

a. GTC/APU control switch START, RUN. .

Note

Allow 1−minute warmup of GTC/APU before applying bleed air load.

b. Bleed air valve switch OPEN, pressure up

ATM and generator/ APU generator “As required” (E)

Lights “Set” (P) (CP)

(E) (LM)

Inverters “Set” (E)

Fuel “Checked” (P)

Note

Remaining radios and navigational equipment may be turned on for warmup at this time, pro-vided external AC power is available.

Autopilot “OFF/

DISENGAGED” (CP)

Flap lever “Set” (CP)

Compass systems Checked

Note MAG heading sources are as follows: INS #1 provides MAG heading to the pilot’s HSI, navi-gator’s L/H BDHI, and copilot’s BDHI and RMI. INS #2 provides MAG heading to the co-pilot’s HSI, navigator’s R/H BDHI, and pilot’s BDHI and RMI.

a. The HSI compass card displays magnetic heading information when the Nav Selector Switch is positioned to any of the Nav sources other than INS 1 or INS 2. When INS 1 or INS 2 is selected, only true heading information will be displayed on the HSI compass card.

b. Check the wet compass against the INS’s magnetic heading outputs displayed on the RMI, BDHI, or HSI +/−5.

Note

The aircraft magnetic deviation card should be taken into consideration when checking the ac-curacy of the wet compass. If the wet compass is out of limits on the ramp, recheck wet com-pass in level flight.

c. Aircraft with dual LN−100 RINU systems “Checked, (state. . .

MAG heading of L/H and

R/H BDHI)” (N/E). .

(Verify navigator position BDHIs agree within 2.0 degrees. No. 1 and No. 2 INS CDU headings should agree within 0.4 de-gree.)

“Checked, (state MAG heading of HSI)” (P)

(NAV Select to VOR/ILS No. 1, verify pi-lot’s HSI agrees within 2.0 degrees of navi-gator’s L/H BDHI.)

“Checked, (state MAG heading of HSI)” (CP)

(NAV Select to VOR/ILS No. 2, verify copi-lot’s HSI agrees within 2.0 degrees of navi-gator’s R/H BDHI.)

Altimeters “Set (state setting and reading)” (CP) (P). . .

(N/E)

Ramp and door “Closed” (LM)

INS “Set” NAV #1 and #2 (N/E)

Hydraulic panel “Set” (CP)

Parking brake “Set, remove chocks” (if taxi required) (P). .

Note

Engine starts are made with enrichment normal to check system operation.

Fuel enrichment switches “NORMAL” (E)

Ground idle buttons “LOW SPEED” (E). . .

Ground run briefing “Complete” (P)

Chocks “As required” (LM)

Before starting engines checks “Complete” (E) (N)

(R) (LM)

(CP)

ENGINE RUN−UP CHECKLIST

The engine run checklist combines starting engines, before taxi, and engine run up operations, with systems checks required for ACF/FCF.

Note

Because of the close coordination required during some of the more detailed checks, it is important that crewmembers involved in a specific check thoroughly review all sub− items/−steps, prior to initiating accomplish-ment of the checklist item.

Clear No. 3 engine “No. 3 clear” (LM) “Turning No. 3” (P). .

a. Engine bleed air switch OPEN/OVRD (E).

b. Engine condition lever RUN (P)

Note

The flight engineer will call engine start se-quence items as they occur.

c. Engine ground start switch START (P). . .

d. Hydraulic systems Checked (CP)

During engine start the copilot will check the hydraulic systems as follows:

(1) Monitor hydraulic pressure during engine start. When the engine−driven pump pressure warning light extinguishes (approximately 1,000 PSI), immediately actuate the flight controls to deplete pressure below 1,000 PSI, and note that the engine pump pressure warning light illuminates. Stop flight control actuation and allow pressure to increase normally.

Note

When starting No. 2 and No. 3 engines, the No.

1 and No. 4 engine pump pressure warning lights should remain illuminated, indicating proper operation of the No. 1 and No. 4 pump isolation check−valves. The check−valves for No. 2 and No. 3 engines are checked in flight during the propeller feathering check.

(2) After the engine being started is on speed and the hydraulic pressure has stabilized, check the hydraulic pump by actuating the flight controls while that pump is the only source of pressure to its system.

Note

Normal operating hydraulic pressure should be indicated within 30 seconds after on speed.

This pressure may not be reached if the control column is in the full forward position, due to normal internal bypass of fluid in the elevator boost package. Pulling the column off its stop 2 to 3 inches will eliminate this bypass.

e. Low speed ground idle button (after engine has stabilized at low speed) NORMAL (E)

f. Fuel enrichment switch OFF (E)

After…