TECHNICAL MANUAL MAINTENANCE MANUAL FOR ARMY CH-47D HELICOPTER (1992)

TM 55-1520-240-10

Table 64. Loading Sequence Configuration (Continued)

Warehouse Pallet Configurations

Configuration

Component

Comment

Ramp Extension/Ramp Jacks

Ramp Extension/Ramp Extension

Rollers

Locks

Retractable Flange

5k/10k Rings

Using Straps, Secure Cargo to 5/10k

Rings

Flight

Outboard Rollers

Warehouse Guides

Ramp Extension/Ramp Jacks

Stow in Aircraft

Ramp Extension/Ramp Extension

Rotate Ramp Extension on Ramp,

Rollers

Rollers on Underside

Locks

Retractable Flange

5k/10k Rings

Warehouse Pallet Configurations

Configuration

Component

Comment

Unload

Outboard Rollers

Warehouse Guides

Ramp Extension/Ramp Jacks

In Place as Required

Ramp Extension/Ramp Extension

In Place as Required

Rollers

Locks

Retractable Flange

5k/10k Rings

Wheeled Vehicle Configurations

Configuration

Component

Comment

Load

Outboard Rollers*

Up-Straps on Cabin, Ramp Up

Warehouse Guides

Down

Ramp Extension/Ramp Jacks

No Ramp Extension Jacks, No

Ramp Jack (Ramp on Ground)

Ramp Extension/Ramp Extension

Ramp Extension on Ground, No

Rollers

Locks

Down (Locked)

Retractable Flange

Rotate Outboard (Unlock)

5k/10k Rings

Restraint

Outboard Rollers

Warehouse Guides

Ramp Extension/Ramp Jacks

Ramp Extension/Ramp Extension

Rollers

Locks

Retractable Flange

6-40

TM 55-1520-240-10

CHAPTER 7

PERFORMANCE DATA

SECTION I INTRODUCTION

7-1. Purpose.

limits with an operating cruise guide indicator (CGI).

Airspeed limits with the CGI inoperative are in Chapter

The purpose of this chapter is to provide the best

5. If limits are exceeded, minimize the degree and time.

available performance data for the CH-47D helicopter.

Regular use of this information will enable you to

7-4. Use of Charts.

receive maximum safe utilization from the aircraft.

a. Chart Explanation.

The first page of each section

Although maximum performance is not always required,

regular use of this chapter is recommended for the

describes the chart(s) and explains its use.

following reasons.

b. The primary use of each chart is given in an

example and a guideline is provided to help you follow

a. Knowledge of your performance margin will allow

the route through the chart. The use of a straight edge

you to make better decisions when unexpected condi-

tions or alternate missions are encountered.

(ruler or page edge) and a hard fine point pencil is

recommended to avoid cumulative errors. The majority

b. Situations requiring maximum performance will be

of the charts provide a standard pattern for use as

more readily recognized.

follows: enter first variable on top left scale, move right

c. Familiarity with the data will allow performance to

to the second variable, deflect down at right angles to

be computed more easily and quickly.

the third variable, deflect left at right angles to the

fourth variable, deflect down, etc. until the final variable

d. Experience will be gained in accurately estimating

is read out at the final scale. In addition to the primary

the effects of variables for which data are not presented.

use, other uses of each chart are explained in the text

accompanying each set of performance charts.

7-2. General Data.

The data presented covers the maximum range of

NOTE

conditions and performance that can reasonably be

An example of an auxiliary use of the charts

expected. In each area of performance, the effects of

referenced above is as follows: Although the

altitude, temperature, gross weight (GW), and other

hover chart is primarily arranged to find

parameters relating to that phase of flight are pre-

torque required to hover, by entering torque

sented. In addition to the presented data, your judg-

available as torque required, maximum wheel

ment and experience will be necessary to accurately

height for hover can also be found. In gen-

obtain performance under a given set of circumstances.

eral, any single variable can be found if all

The conditions for the data are listed under the title of

others are known. Also, the tradeoffs be-

each chart. The effects of different conditions are

tween variables can be found. For example,

discussed in the text accompanying each phase of

at a given density altitude (DA) and pressure

performance. Where practical, data is presented at

altitude (PA), you can find the maximum

conservative conditions. However, NO GENERAL

GW capability as free air temperature (FAT)

CONSERVATISM HAS BEEN APPLIED. All perfor-

changes.

mance data presented is within the applicable limits of

the aircraft.

c. Dashed Line Data.

Data beyond conditions for

which tests were conducted, or for which estimates are

CAUTION

used, are shown as dashed lines.

Exceeding operating limits can-cause perma-

7-5. Data Basis.

nent damage to critical components. Over

limit operation can decrease performance,

The type of data used is indicated at the bottom of each

cause immediate failure, or failure on a

performance chart under DATA BASIS. The applica-

subsequent flight.

ble report and date of the data are also given. The data

provided generally is based on one of the following

categories.

7-3. Limits.

a. Flight Test Data.

Data obtained by flight test of

Applicable limit lines are shown on the charts. The

the aircraft by experienced flight test personnel at

dashed lines on the cruise charts are estimated airspeed

precise conditions using sensitive calibrated instruments.

7-1

TM 55-1520-240-10

b. Calculated Data. Data based on tests, but not on

7-7.2. ERFS II Tank Capacity.

flight test of the complete aircraft.

The capacity of the ERFS II tank using pressure refueling

c. Estimated Data. Data based on estimates using

is 805.5 US gallons. If filled using gravity refueling, the ca-

aerodynamic theory or other means but not verified by

pacity is 825.5 US gallons (In both cases 5.5 GALS will be

flight test.

unusable).

7-6.

Specific Conditions.

7-7.3. Amount of Unusable Fuel.

The data presented is accurate only for specific conditions

listed under the title of each chart. Variables for which data

The amount of unusable fuel in each of the ERFS II tanks

are not presented, but which may affect that phase of per-

is 5.5 US gallons of JP-8.

formance, are discussed in the text. Where data is avail-

able or reasonable estimates can be made, the amount

7-7.4. Fuel Transfer Rate.

that each variable affects performance will be given.

The rate at which fuel is transferred from the ERFS II

7-7.

General Conditions.

tanks to the helicopter main fuel tanks is 23 GPM.

In addition to the specific conditions, the following general

conditions are applicable to the performance data.

7-7.5. FARE Transfer Rate.

a. Rigging. All airframe and engine controls are as-

The FARE kit pump is rated at 120 GPM. However, the

sumed to be rigged within allowable tolerances.

configuration of the FARE fuel transfer hose assembly af-

b. Pilot Technique. Normal pilot technique is assumed.

fects this transfer rate. Pressure losses across couplings,

c. Aircraft Variation. Variations in performance be-

filters, and nozzles reduce the flow rate below the rated

tween individual aircraft are known to exist; however, they

value. The rate at which fuel is transferred from the ERFS

are considered to be small and cannot be accounted for

II tanks using the FARE pump and the standard configura-

individually.

tion of the FARE fuel transfer hose assembly is 84 to 88

GPM.

d. Instrument Variations. The data shown in the perfor-

mance charts does not allow for instrument inaccuracies

7-8.

Performance Discrepancies.

or malfunctions.

e. Airspeed Calibrations. The airspeed calibration

Regular use of this chapter will allow you to monitor instru-

ments and other aircraft systems for malfunction, by

chart presents the difference between indicated air speed

comparing actual performance with planned perfor-

(IAS), and calibrated airspeeds (CAS) for different flight

mance. Knowledge will also be gained concerning the ef-

conditions.

fects of variables for which data are not provided, thereby

Except as noted, all data is for a clean configuration

increasing the accuracy of performance predictions.

(all doors installed, without armament).

g. Types of Fuel. All flight performance data is based on

7-9.

Definitions of Abbreviations.

JP-5 fuel. the change in fuel flow and torque available,

Capitalization and punctuation of abbreviations varies,

when using JP-4, JP-8, Aviation gasoline or any other ap-

depending upon the context in which they are used. In

proved fuels, is insignificant.

general, full capital letter abbreviations are used in text

7-7.1. ERFS II Performance Data.

material, charts and illustrations. Periods do not usually

Use of the performance data will enable the operator to re-

follow abbreviations; however, periods are used with ab-

ceive the maximum safe utilization of the ERFS II and

breviations that could be mistaken for whole words if the

FARE kit.

period were omitted.

7-2

Change 14

TM 55-1520-240-10

SECTION Ill MAXIMUM TORQUE AVAILABLE

7-13. Maximum Torque Available (10-Minute Op-

7-16. Maximum Torque Available (30-Minute Op-

eration).

Maximum torque available (l0-minute operation) may

Maximum torque available (30-minute operation) may

be obtained from figure 7-3. Available torque is pre-

be obtained from figure 7-4. Available torque is pre-

sented in terms of pressure altitude and free air tem-

sented in terms of PA and FAT.

perature.

7-17. Use of Chart.

7-14. Use of Chart.

The primary use of the chart is to determine available

engine torque for various combinations of PA and

engine torque for various combinations of pressure

temperature. To determine torque available, it is nec-

altitude and temperature. To determine torque avail-

essary to know pressure altitude and free air tempera-

able, it is necessary to know pressure altitude and free

ture. Enter the left side of the chart at the known

air temperature. Enter the left side of the chart at

pressure altitude, move right to known temperature,

known temperature, move right to known pressure

then down to read intermediate torque available.

altitude, then down to read torque available.

7-18. Conditions.

7-15. Conditions.

The chart is based on a rotor speed of 100%.

7-6

TM 55-1520-240-10

SECTION V HOVER

7-22. DESCRIPTION.

maximum torque available and read wheel height. This

wheel height is the maximum hover height,

The hover chart, figure 7-6, presents torque required to

hover at 100% RRPM at various combinations of PA,

c. The hover charts may also be used to determine

FAT, GW, and wheel height for single and dual engine

maximum GW for hover at a given wheel height, PA,

operation.

and temperature. Enter at known pressure altitude,

move right to the FAT, then move down to the bottom

7-23. Use of Chart.

of the lower grid, and read density altitude. Now enter

a. The primary use of the charts is illustrated by the

lower left grid at maximum torque available. Move up to

wheel height, then move right to density altitude and

example. To determine the torque required to hover, it

read GW. This is the maximum gross weight at which

is necessary to know PA, FAT, GW, and desired wheel

height. Enter the upper right grid at the known pressure

the helicopter will hover.

altitude, move right to the temperature, move down to

7-24. Conditions.

gross weight. Move left to desired wheel height, deflect

down and read torque required for dual engine or single

a. The hover chart is based on calm wind, level

engine operation.

surface, and 100% RRPM.

b. In addition to the primary use, the hover ceiling

b. Hover in ground effect (HIGE) data is based on

charts (fig. 7-7) may be used to predict maximum hover

hovering over a level surface. For normal transition

height. This information is necessary for use of the

from hover to forward flight, the minimum hover wheel

takeoff chart found in figure 7-8. To determine maxi-

height should be

10 feet to prevent ground contact. If

mum hover height, it is necessary to know PA, FAT,

helicopter is to hover over a surface known to be steep,

GW, and maximum torque available. Enter at the

covered with vegetation, or if type of terrain is unknown,

known pressure altitude, move right to FAT, move

the flight should be planned for hover out of ground

down to gross weight, move left to intersection with

effect (HOGE) capability.

7-12

TM 55-1520-240-10

SECTION VI

TAKEOFF

7-25. Description.

required obstacle height, move right to desired true

climbout airspeed, then down and read distance re-

The takeoff chart, figure 7-8, defines distances required

quired to clear obstacle.

to clear obstacles of

50 feet, 100 feet, 150 feet, and

200

feet based upon maximum hover height capability and

b. A hover check should be made prior to takeoff to

true airspeed. The procedure for takeoff is the level

verify hover capability. If winds are present, hover

flight acceleration technique.

capability will be greater than predicted since the hover

chart is based on calm wind conditions.

NOTE

7-27. Conditions.

The maximum hover heights shown are in-

dicative of helicopter performance capability

a. The takeoff chart is based on calm wind conditions.

and do not imply that this hover height must

Since the surface wind velocity and direction cannot be

be maintained through takeoff.

accurately predicted, all takeoff planning should be

based on calm air conditions. Takeoff into the wind will

improve takeoff performance.

7-26. Use of Chart.

The primary use of he chart is illustrated by the

examples.

A tailwind during takeoff and climbout will

increase the distance for obstacle clearance

a. To determine the distance required to clear an

and may prevent a successful takeoff.

obstacle, it is necessary to know maximum hover height

(hover capability), obstacle height, and climbout true

airspeed. Calculation of maximum hover height is de-

b. Takeoff performance data are based on the use of

scribed in Section V, Hover. Enter the chart for the

maximum torque available at 100% RRPM.

7-16

TM 55-1520-240-10

CHAPTER 8

NORMAL PROCEDURES

SECTION I MISSION PLANNING

8-1. Mission Planning.

(7) Visually inspects engine and ramp area for

proper operation.

Mission planning begins when the mission is assigned

and extends to the preflight check of the helicopter. It

(8) Remove chocks and closes ramp door when

includes, but is not limited to, checks of operating limits

called for by the pilots.

and restrictions, weight/balance and loading, perfor-

(9) Observes and gives clearance to pilots during

mance, publications, flight plan, and crew briefings. The

taxi and hover operation. Reports any object or condi-

pilot in command shall ensure compliance with the

tion which would pose a hazard to the helicopter. When

contents of this manual that are applicable to the

the helicopter is being taxied in obstructed areas, the

mission.

flight engineer or other crewmembers may be required

8-2. Aviation Life Support Equipment (ALSE). All

to act as taxi director or blade watchers. Taxi directors

aviation life support equipment required for mission,

and blade watchers must be familiar with CH-47 ground

turning characteristics (fig. 2-3 and 8-l).

e.g., helmets, gloves, survival vests, survival kits, etc.,

shall be checked.

(10) Perform check of ramp area and MAINTE-

NANCE PANEL every 30 minutes of flight.

8-3. Crew Duties/Responsibilities. The minimum

crew required to fly the helicopter is a pilot, copilot, and

8-4. Crew Briefing. A crew briefing shall be con-

flight engineer. Additional crewmembers, as required,

ducted to ensure a thorough understanding of individ-

may be added at the discretion of the commander. The

ual and team responsibilities. The briefing should in-

manner in which each crewmember performs his related

clude, but not be limited to, copilot, mission equipment

duties is the responsibility of the pilot in command.

operator, and ground crew responsibilities and the

a. Pilot. The pilot in command is responsible for all

coordination necessary to complete the mission in the

aspects of mission planning, preflight, and operation of

most efficient manner. A review of visual signals is

the helicopter. He will assign duties and functions to all

desirable when ground guides do not have a direct voice

communications link with the crew.

other crewmembers as required. Prior to or during

preflight, the pilot will brief the crew on the mission,

8-5. Passenger Briefing. The following is a guide

performance data, monitoring of instruments, commu-

that should be used in accomplishing required passen-

nications, emergency procedures, and armament proce-

ger briefings. Items that do not pertain to a specific

dures.

mission may be omitted.

b. Copilot. The copilot must be familiar with the

a. Crew introduction.

pilot’s duties and the duties of the other crew positions.

The copilot will assist the pilot as directed.

b. Equipment.

c. Flight Engineer.

The flight engineer will perform

(1) Personal to include ID tags.

all duties as assigned by the pilot in addition to the

(2) Professional.

following specific duties:

(1) Performs or coordinates maintenance, servic-

(3) Survival.

ing, inspection, loading, and security of the helicopter.

c. Flight Data.

(2) Checks that log book is current and correct.

(1) Route.

(3) Accompanies pilot during preflight inspec-

(2) Altitude.

tion; performs the inspection with the pilot.

(3) Time en route.

(4) Checks the security of each area inspected.

(4) Weather.

(5) Assists in seating and securing passengers;

checks load security.

d. Normal Procedures.

(6) Ensures the helicopter is clear during all

(1) Entry and exit of helicopter.

starting procedures and informs the pilots of any objects

(2) Seating.

which would pose a hazard to the helicopter during all

phases of ground operation.

(3) Seat belts.

8-1

TM 55-1520-240-10

SECTION II

OPERATING PROCEDURES AND MANEUVERS

8-6. Operating Procedures And Maneuvers.

safe helicopter operation are included. The preflight may

be made as comprehensive as conditions warrant at the

This section deals with normal procedures and includes

discretion of the pilot.

all steps necessary to ensure safe and efficient operation

of the helicopter from the time a preflight begins until the

8-11. Before Exterior Check.

flight is completed and the helicopter is parked and se-

*1. Publications-Check DA Forms 2408-12, -13,

cured. Unique feel, characteristics, and reaction of the he-

-14, -18, DD Form 365-4, and DD Form 1896, lo-

licopter during various phases of operation and the tech-

cally required forms and publications, and avail-

niques and procedures used for hovering, takeoff, climb,

ability of operator’s manual (-10), and checklist

etc., are described, including precautions to be observed.

(-CL).

Your flying experience is recognized; therefore, basic

*2. Ignition lock switch-On.

flight principles are avoided. Only the duties of the mini-

mum crew necessary for the actual operation of the heli-

712

EMERGENCY POWER panel-Check trip

copter are included.

indicators and timers.

8-7. Mission Equipment Checks. Mission equipment

712

Topping stops-Check stowed.

checks are contained in Chapter

4, MISSION

5. Cockpit area-Check as follows:

EQUIPMENT. Descriptions of functions, operations, and

effects of controls are covered in Section III, FLIGHT

a. General condition.

CHARACTERISTICS, and are repeated in this section

b. Fire extinguisher-Check seal intact, DD

only when required for emphasis. Checks that must be

Form 1574/1574-1, and security.

performed under adverse environmental conditions,

such as desert and cold weather operations, supplement

c. Jettisonable door release handles/latches.

normal procedures checks in this section and are

d. Sliding windows.

covered in Section IV, ADVERSE ENVIRONMENTAL

*6. Forward transmission-Check oil level, filter but-

CONDITIONS.

ton, and oil cooler condition.

8-8. Symbols Definitions. The checklist includes items

that may not be checked by the flight engineer and that

7. Fuel sample-Check before first flight of the day.

may or may not be installed. These items are annotated

8-12. INTERIOR CHECK.

immediately preceding the check to which they are

8-13. Forward Cabin.

pertinent: F for flight engineer, and 0 to indicate a

requirement if the equipment is installed. The symbol L

1. Flight control closet-Check ILCA actuators for

indicated that a detailed procedure for the step is located

extended jam buttons and thrust idler assem-

in the detailed procedures section of the condensed

blies for bent cracked arms. Check ILCA con-

checklist. When a helicopter is flown on a mission

necting link for cracks or displaced bearings.

requiring intermediate stops, it is not necessary to

2. Heater compartment-Check security of compo-

perform all of the normal checks. The steps that are

nents and winch.

essential for safe helicopter operations on intermediate

3. Emergency escape ax-Check condition and se-

stops are designated as “through flight” checks. An

curity.

asterisk* indicates that performance of steps is

mandatory for all “through-flights” when there has been

4. Cabin door-Check condition and security.

no change in pilot-in-command. The asterisk applies only

5. Avionics equipment-Check security of compo-

to checks performed prior to takeoff. Duties performed by

nents and connections. Determine whether both

individual in copilot station are indicated by a circle

pilots displacement gyros are installed.

around the step number, i.e., 4. Step numbers with no

circles around them may be performed by the aviator in

6. Fire extinguisher-Check seal intact, DD Form

either pilot or copilot’s seat.

1574/1574-1, and security.

8-9. Checklist. Normal procedures are given primarily in

7. Cabin escape panel-Check condition and secu-

checklist form and amplified as necessary in

rity.

accompanying paragraph form when a detailed

8. Transformer-rectifier air intake screens-Check

description of a procedure or maneuver is required. A

both clear. A transformer-rectifier may fail if rags

condensed version of the amplified checklist, omitting all

or other items stowed behind troop seats block

explanatory text, is contained in the Operators and

the air intakes.

Crewmembers Checklist, TM 55-1520-240-CL.

9. Seats, litters, first aid kits, cargo and jettisonable

8-10. Preflight Check. The pilot’s walk-around and

cabin window-Check condition and security.

interior checks are outlined in the following procedures.

The preflight check is not intended to be a detailed

10. Utility hatch door and lower rescue door-Check

mechanical inspection. The steps that are essential for

condition and position as required.

Change 14

8-3

TM 55-1520-240-10

11. Center cargo hook - Check condition and

f. Single Point Pressure Refueling Hose As-

position as required. Check 2,100 psi charge,

sembly - Check connection security;

manual release mechanisms stowed, manual

Unisex valve at ERFS II Tank CLOSE.

release mechanism for proper cam position

g. Electrical Harness - Check connection

and latched.

security of J1.

h. Fuel Quantity Sensing Wiring Harness -

CAUTION

Check connection security of J2.

i. Fuel/Defuel Vent Valve - Check in the

Do not lift or rotate the center cargo hook

into the cabin area or allow the mid hook

CLOSED position.

to lay on the cargo floor or access door

panel during inspection or use. The exces-

WARNING

sive tension placed on the triple emergen-

cy release cable housing assembly may

Failure to remove water and contaminants

partially dislodge the housing and engage

from the ERFS II tank sump could result in

or activate the forward and aft hook emer-

contaminants being transferred to the he-

gency release mechanism. This may

licopter fuel tanks or other aircraft or

cause an inadvertent release of loaded

equipment during FARE operations. If wa-

forward and aft hook assemblies in flight.

ter and contaminants are not removed, a

12. Forward and aft cargo hook release lever -

loss of engine power may result.

Check for security and stowed.

ERFS II Tank Sump Fuel Sample -

13. Forward, center, and aft cargo hook release

Check before first flight of the day.

lever - Check for security and stowed.

Filler Cap - Check in place, closed, and

locked.

13.1

714A

DECU - Check condition and secu-

ERFS II FUEL CONTROL PANEL -

rity.

Check or set as follows:

14. ERFS installed - Check the following:

(a)

Electrical Harness-Helicopter Re-

a. All fuel manifold lines, electrical lines,

ceptacles to Fuel Control Panel -

grounding cables, and vent lines to ensure

Check connection security of J5.

that they are properly secured and con-

(b)

Electrical Harness-Fuel Control

nected.

Panel to Tank Assembly - Check

b. Fuel manifold lines and tiedown straps for

connection security of J1, J2, and J3.

chafing. Tank tiedown straps for security.

(c)

Wiring Harness-Fuel Quantity Sen-

c. Ensure ERFS tanks are properly fueled,

sing - Check connection security of

580 GALLONS MAXIMUM PER TANK.

J4.

d. ERFS tanks for leakage.

(d)

PUMP AC circuit breaker six (6)

14.1

ERFS II installed - For each installed ERFS

each - Check in reset position on

II tank assembly check the following:

TANK 1, TANK 2, and TANK 3 (if

a. Tank Restraint Assembly - Check loca-

installed).

tion and security.

(e)

PANEL POWER circuit breaker -

b. Cavity Overboard Drain - Check connec-

Check in reset position.

tion and security of drain in use. Check

drain not in use is capped.

(f)

PANEL LIGHTING circuit breaker -

Check in reset position.

c. Grounding Cable - Check connection

security.

(g)

PUMP switches - OFF on TANK 1,

d. Vent Hose Assembly - Check connec-

TANK 2, and TANK 3.

tion security.

(h)

PRESS LOW lights three (3) each -

e. Fuel Transfer Hose Assembly - Check

Press to test (Aircraft power must be

connection security; all Unisex valves

on to illuminate).

OPEN.

(i)

REFUEL VALVE - Check CLOSE.

CAUTION

(j)

PANEL illumination switch/rheostat

- OFF.

Failure to close the Unisex valves at the

ERFS II tank end of the single point pres-

(k)

FUEL QUANTITY switch - Set to 1,

sure refueling hose assembly could allow

2, 3, and TOTAL to check fuel quanti-

suctioning of fuel from the helicopter main

ty in each tank (Aircraft power must

fuel tanks during FARE operations.

be on to illuminate).

8-4

Change 18

TM 55-1520-240-10

a. Oil level.

5. Pressure refueling control panel-Check as fol-

lows:

b. Filter button.

a. PWR and LT switches at OFF.

c. Oil cooler.

b. Refueling receptacle cover installed and se-

d. Secure doors.

cured.

11. APU-Check.

c. Landing gear and pressure refueling panel

12. EMERGENCY APU FLUID SHUT OFF VALVE

cover closed and secure.

-Check OPEN.

6. Static port-Check unobstructed.

13. COMPASS FLUX VALVE-Check.

7. Right electrical compartment-Check condition

14. FUEL VALVE CROSSFEED (left)-Check

and security.

CLOSED.

8-18. Forward Cabin.

15. FUEL VALVE #1 ENGINE-Check OPEN.

1. Heater intake, exhaust, and combustor drain

-Check.

16. Fire extinguisher-Check seal intact, DD Form

1574/1574-1 and security.

2. Pilot’s jettisonable door-Check.

8-15. EXTERIOR CHECK.

3. Pilot’s pedal area-Check.

8-16. Aft Cabin.

4. Right AFCS yaw ports-Check.

1. Position light-Check condition.

5. Pitot tubes-Check.

1.1

714A

DECU-Check condition and security.

6. Antennas-Check.

2. Right aft landing gear area-Check condition and

7. Searchlights-Check.

security of all components as follows:

8. Windshield and wipers-Check.

a. Gear support structure.

9. Left AFCS yaw ports-Check.

b. Tire.

10. Copilot’s pedal area-Check.

c. Shock strut extension and static lock stowed.

11. Copilot’s jettisonable door-Check.

d. Power steering actuator and brakes.

8-19. Left Cabin.

e. Fluid lines.

1. Fuselage-Check as other items are checked.

f. Electrical wiring.

2. Left electrical compartment-Check.

g. Ground proximity switch and linkage.

3. Forward landing gear area-Check condition and

security of all components as follows:

h. Swivel lock.

a. Tires.

3. Vent and fluid drain lines-Check unobstructed.

b. Shock strut for extension.

3.1

ERFS II Installed. Aircraft Overboard Drain Out-

c. Brakes.

lets-Check. Check for signs of any fuel seep-

age.

d. Fluid lines.

3.2

ERFS II Installed. Aircraft Overboard Vent Out-

4. Forward and aft cargo hooks-Check hooks clear

lets-Check. Check for signs of excessive fuel

and load beam closed. Electrical harness and re-

venting.

lease cable connected and dust caps stowed. If

8-17. Right Cabin.

hook not installed, check for dust caps on the

electrical and release cable receptacles.

1. Fuselage-Check as other items are checked.

5. Lower anti-collision light-Check condition.

*2. Fuel system-Check as required, caps secured.

6. Static port-Check unobstructed.

3. Position light-Check condition.

*7. Fuel system-Check as required, caps secure.

4. Forward landing gear area-Check condition and

7.1

714A

Engine wash system connectors-Check

security of all components as follows:

condition and security.

a. Tire.

8. Left aft landing gear area-Check condition and

b. Shock strut for extension.

security of all components as follows:

c. Brakes.

a. Gear support structure.

d. Fluid lines.

b. Tire.

Change 14

8-5

TM 55-1520-240-10

c. Shock strut extension and static lock stowed.

*13. Forward rotor (right side)-Check same as aft ro-

tor.

d. Static ground wire contacting the ground.

14.

Forward transmission oil cooler inlet-Check for

e. Fluid lines.

obstructions.

f. Electrical wiring.

15.

Upper boost actuators-Check for extended jam

g. Ground proximity switch and linkage.

indicators and exposed pistons for cleanliness.

h. Brakes.

16.

Forward transmission-Check for foreign objects

i. Swivel lock.

and cooler condition.

9. Vent and fluid drain lines-Check unobstructed.

H 17. Hydraulic compartment-Check as follows:

8-20

Top of Fuselage.

a. Condition and security of lines and coolers.

*1.

No. 2 engine-Check as follows:

b. No. 1 flight control system accumulator for

a. Inlet for foreign objects. Check condition and

proper indication.

security of FOD screens.

*18. Forward rotor (left side)-Check same as aft ro-

b. Oil level and cap secure.

tor.

c. Cowling for security.

19. Brake accumulator pressure-Check 600 to 1400

d. Tailpipe condition and security, presence of

psi.

fuel, oil, and foreign objects.

*20. Pylon fairings, work platforms, and inspection

Anticollision light and formation lights-Check

panels-Check secure.

condition.

21. Top of fuselage-Check for foreign objects.

*3.

Aft rotor (right side)-Check blades for condition

and reservoir oil levels.

CAUTION

O 4.

Droop stop shrouds-Check condition and securi-

Failure to remove fuel vent covers may cause

ty. Check inspection cover closed.

fuel tanks to collapse while in use under

Upper boost actuator-Check for extended jam

certain conditions.

indicators and exposed piston rods for cleanli-

O 22. Remove the fuel vent covers (3) (if installed)

ness.

before using ERFS.

H 6.

Hydraulic compartment-Check as follows:

*8-21

Walk Around Check and Security Brief.

a. Condition and security of lines and coolers.

All access doors-Check secure.

b. No. 2 flight control system accumulator for

proper indication.

Tie down, locking devices, covers, and ground

cables-Removed and secured.

c. Utility reservoir pressurization accumulator for

2500 to 3500 psi charge.

Cockpit, fwd transmission, and fwd cabin area

*7.

Combining transmission area-Check for foreign

soundproofing installed-Check.

objects, and oil coolers for obstructions. Check

NOTE

filter buttons for engines and combining trans-

The cockpit, forward transmission, flight con-

mission.

trol, and avionics compartment soundproofing

*8.

Aft rotor (left side)-Check blades for condition

should be installed during normal aircraft op-

and reservoir oil levels.

eration to reduce noise levels in the crew and

passenger areas and to aid in venting of trans-

O 9.

Droop stop shrouds-Check condition and securi-

mission heat and fumes.

ty.

Crew/passenger briefing-Complete as required.

10.

Upper boost actuator-Check for extended jam

indicators and exposed pistons for cleanliness.

8-22

Before Starting Engines.

*11.

No. 1 engine-Check same as No. 2 engine.

Pedal adjustment-Matched. Check that yaw

12.

Drive shaft area-Check condition and security

pedals are adjusted equally and that adjustment

as follows:

pins are in the same hole position. Uneven pedal

adjustment can cause droop stop pounding dur-

a. Drive shafts, couplings, and mounts.

ing engine start and ground operations.

b. Fluid lines.

Shoulder harness locks-Check operation and

c. Control linkage.

leave unlocked.

d. Foreign objects.

*3.

No. 1 and No. 2 PDPs-Check all circuit breakers

e. Drive shaft fairing.

in and gang bar up.

8-6

Change 14

TM 55-1520-240-10

H 4. Overhead switches and control panels. Set as

r. HYD switches-Set as follows:

follows:

(1) PWR XFER switches-OFF.

*a.

EXT LTG switches-As required.

(2) FLT CONTR switch-BOTH.

*b.

CPLT LTG switches-As required.

(3) BRK STEER switch-ON. Cover down.

COMPASS switch-As required.

TROOP WARN switches-OFF.

(4) RAMP switch-ON.

HTG switches-As required.

(5) RAMP EMER switch-HOLD. Cover

down.

W/S WIPER switch-OFF.

ELECT switches-OFF.

FIRE PULL handles-In.

*h.

LTG switches-As required.

AGENT DISCH switch-Check.

*i.

FUEL CONTR switches-Set as follows:

*7.

XMSN OIL PRESS switch-SCAN.

(1) XFEED switch-OPEN.

*8.

XMSN OIL TEMP switch-SCAN.

(2) REFUEL STA switch-OFF.

*9.

VGI switches-NORM.

(3) L MAIN FUEL PUMP switches-ON.

10.

CYCLIC TRIM switch-AUTO.

(4) All remaining FUEL PUMP switches -

*11. AFCS SYSTEM SEL switch-OFF.

OFF.

*12.

FLARE DISP switch-SAFE.

712

START switches-OFF.

ENG COND levers-STOP.

13.

Avionics equipment-OFF; set as required.

*l.

714A

FADEC switches-Check or set as

O 13.1

HUD-OFF.

follows:

14.

712

EMERG ENG TRIM switches-AUTO;

(1) B/U PWR switch-OFF.

covers down.

(2) LOAD SHARE switch-TRQ.

15.

SWIVEL switch-LOCK.

(3)

1 and 2 PRI/REV switches-PRI.

8-23

Starting Engines.

(4) NR% switch-100.

BATT switch-ON.

*m.

INTR LTG switches-As required.

CAUTION LT TEST switch-TEST. Check that all

*n.

PLT LTG switches-As required.

caution capsules and the two master caution

ANTI-ICE switches-OFF.

lights on the instrument panel come on. Some of

HOIST switches-OFF.

the caution capsules will be on before the system

is checked.

CARGO HOOK switches-Set as follows:

Clocks-Running, Set as required.

(1) MSTR switch-OFF.

(2) HOOK SEL switch-As required.

TROOP WARN ALARM and JUMP LT-Two

bells, two red, two green.

(3) EMERG REL ALL switch-OFF. Cover

down.

*F 5.

Fire guard posted-APU clear to start.

Change 14

8-6.1/(8-6.2 blank)

TM 55-1520-240-10

* 6. APU-Start as follows:

17. Fuel quantity-Check as required.

a. APU switch-RUN for 3 to 5 seconds.

18. Cyclic trim indicators-Check GND position.

b. APU switch -START for 2 seconds, then RUN.

*F 19. Rotor blades-Check position. Make sure that a

rotor blade is not within 30° of the centerline of

NOTE

the fuselage throughout control check.

If the start is not completed, or the APU is

20. AFCS SYSTEM SEL switch-Check as follows:

automatically shut down, wait one minute for

cooling before attempting a restart. Failure to

a. Select individual system and check opposite

allow the APU to cool may cause a premature

AFCS caution capsule remains on.

shutdown on restart due to overtemperature. If

b. Select BOTH and check both AFCS caution

the start is not completed, do not turn the BATT

capsules go out.

switch OFF. Set the APU switch to OFF, check

c. AFCS SYSTEM SEL switch-OFF.

the BITE indicators on the ESU, and record the

display for maintenance.

21. Flight control travel and hydraulics-Check as

follows:

c. APU ON indicating light-Check on.

a. Check each individual flight control hydraulic

d. UTIL HYD SYS caution - Check out. If the

light does not go out within 30 seconds after

system. Check each flight control axis individu-

APU ON indicating light comes on, APU switch

ally and in combination with other axes through

OFF.

full travel for smoothness of motion.

7. APU GEN switch-ON. NO. 1 and 2 RECT

b. Check for corresponding movement of the fore

OFF and L and R FUEL PRESS caution capsules

and aft rotors.

out.

CAUTION

NOTE

If either HYD FLT CONTR caution capsule

If helicopter is parked on a slope greater than

does not go out in 30 seconds after the PWR

4°, longitudinal stick travel may be restricted

XFER switches are set to ON, set PWR

to less than 7 inches forward (up slope) or 4

XFER switch to OFF. Do not fly the helicopter.

inches aft (down slope).

8. PWR XFER-Check

a. PWR XFER 1 and 2 switches- ON. Check

c. Check caution capsules as this check is being

HYD FLT CONTR caution capsules out.

performed. If the flight controls are moved

F b. Pressures normal.

erratically during the control check, unusual

vibrations may be felt.

*F 9. MAINTENANCE PANEL-Check.

d. Check cyclic for freedom of movements in all

a. GND switch-TEST, then RESET.

quadrants. Check for a minimum of 7 inches

O b. GROUND CONTACT indicating lights-

forward and 4 inches aft travel.

check on.

e. Check thrust and pedals individually through

c. Systems-Normal.

full travel for freedom of movement.

* 10. Avionics-On as desired.

f. FLT CONTR switch-BOTH.

O 10.1 HUD-ON

g. Position the cyclic and pedals at neutral, thrust

11. CARGO HOOKS HOIST/WINCH-Check op-

at ground detent.

eration as required. Refer to Chapter 4, Section

21.1

714A

DECU PRESTART BIT-Perform as

III.

follows:

12. SLT-FIL switches-Check and set as required.

a. B/U PWR switch-ON.

13. PARKING BRAKE-Set.

b. Wait until ENG FAIL caution lights go out.

14. CRUISE GUIDE indicator-Check for pointer

c. ENG COND levers-GND.

in white test band when the CGI TEST switch is

at FWD and AFT TEST.

d. DECUs-Check displays read 88.

* 15. Altimeters-Set and check as follows:

21.2 AN/ASN 149 (V) GPS-STARTUP and config-

ure.

a. Barometric altimeter-Set and check.

22.

Avionics-Perform operational check and set as

b. Radar altimeter-ON and set.

required.

16. FIRE DETR switch-TEST. Check fire warning

23.

712

ENGINE BEEP TRIM switch (NO. 1 &

lights on, release switch, and check fire warning

lights out.

2)-DECREASE for 8 seconds.

Change 13

8-7

TM 55-1520-240-10

26.1

714A

P3 bellow-Check as follows:

24. Area-Clear for start.

a. ENG 1 FADEC PRI-REV switch (started eng-

gine )-REV

b. FADES Caution-ON

CAUTION

c. N1-Maximum change +3%.

The flight controls must be manned any time

d. FADEC PRI-REV switch (started engine)-

the helicopter is on the ground with rotors

PRI.

turning.

e. FADEC FAIL Caution-OUT.

f. Repeat for ENG 2.

NOTE

27. Transmission oil pressures-Check for mini-

mum of 7 psi. There is no time limit for ground

Either engine may be started first.

idle operation, provided there is a minimum of 7

25.

712

First engine-Start as follows:

psi oil pressure in each engine transmis-

F a. Clear for start.

sion.

b. L and R FUEL PRESS LIGHTS-Check out.

c. ENG COND lever-STOP.

CAUTION

d. ENG START switch-MTR.

Failure of either engine to accelerate smoothly

NOTE

from ground to flight may be an indication of

a clutch malfunction in the engine transmis-

If engine does not reach 15% but exceeds 10%

sion.

N1 (minimum) and has reached it's maximum

speed, initiate start, but monitor engine and

28. ENG COND levers-FLT. No. 1 and No.2 clear

PTIT for possible hung start and/or excessive

to FLT. Engine acceleration should be smooth

PTIT.

with no surging.

e. Motor engine to a minimum of 15% N1. Set

ENG COND lever-GND; ENG START

switch to START immediately.

CAUTION

f. Release START switch to MTR before PTIT

reaches 200°C. When N1 is 50%, set START

Failure of either engine N1 to accelerate past

switch to OFF. Check STARTER ON light out.

70% N1 may be an indication of a clutch

malfunction in the engine transmission.

g. Engine instruments-Check when stabilized at

ground idle (N1 at 60 to 63%). Check engine oil

29. 712

RPRM-Set as required.

pressure for 20 psi minimum. The engine should

accelerate to ground idle speed within 45 sec-

onds.

NOTE

Delay turning second generator on or off for

CAUTION

two seconds. This delay will give DECU time to

sample power without causing soft fault.

The N2 section of the second engine starts

turning when the first engine is started;

30. GEN 1 and 2 switches-ON.

712

No. 1 & 2

however, the lubrication system of the second

GEN OFF

714A

GEN 1 & 2 caution capsules

engine is driven by the N1 sections which does

out.

not begin to turn until the start sequence is

31. APU GEN switch-OFF.

initiated. Delay in starting the second engine

will result in excessive wear on the N2 bear-

31.1.

714A

DECU START BIT-Perform as follows:

ing package and seal. Start the second engine

a. ENG COND levers-Retard 5 degrees.

within three minutes of the first.

b. DECU display-Check display reads 88.

25.1.

714A

First engine-Start as follows.

a. ENG START switch-Select engine to be

NOTE

started and hold until N1 accelerates to 10%,

If DECU display is other than 88, shutdown

then release switch.

engine being checked and remove all power to

b. Engine should accelerate to ground idle (50 to

DECU by pulling the respective Engine PRI and

59%) within 45 seconds.

REV CONT circuit breakers on the PDP. Reset

c. Transmission oil pressures-Check increasing.

the circuit breakers and repeat the engine start

sequence and DECU fault monitoring check. If

d. Engine oil pressure-Check 5 psi minimum.

26. Second Engine-Start by using the same method

DECU display is other then 88 once again, shut

as first engine.

down helicopter and refer to maintenance.

8-8

Change 13

TM 55-1520-240-10

c. ENG COND levers - FLT.

crease then release. Torque and N1

should return to normal settings.

* 32. PWR XFER 1 and 2 switches - OFF.

b. EMERG ENG TRIM 2 switch - Check

same as No. 1 engine.

* 33. APU switch - OFF. APU ON caution capsule

out.

L 6.1

714A

FADEC Reversionary system

* 34. Systems - Check normal.

Check (First flight of day).

a. FADEC 1 and 2 PRI-REV switches - PRI.

* 35. Transponder - STBY.

b. NR% switch - 100%.

8-24. Engine Ground Operation.

c. FADEC 1 -Check as follows:

L 1. FUEL PUMP and XFEED - Check operation

(1) FADEC 1 PRI-REV switch - REV.

as follows:

(2) FADEC 1 INC-DEC switch - DEC.

a. All FUEL PUMP switches - OFF. Check

Check for decrease in No. 1 engine

L and R FUEL PRESS caution capsules

N1 and torque, and corresponding

should come on.

increase in No. 2 engine N1 and

torque.

b. L AFT MAIN FUEL PUMP switch - ON.

Check L and R FUEL PRESS caution cap-

(3) FADEC 1 INC-DEC switch - INC.

sule should go out. Then switch OFF.

Check for increase in No. 1 engine

N1 and torque, and corresponding

c. Remaining MAIN FUEL PUMP switches

decrease in No. 2 engine N1 and

- Check as in step b. above.

torque.

d. L AFT AUX FUEL PUMP switch - ON.

(4) FADEC 1 PRI-REV switch - PRI.

Check L AUX PRESS light on overhead

f. Repeat check for FADEC 2.

panel comes on, then goes out. Set pump

switch to OFF.

7. Radar altimeters - Check IAW paragraph

2-200.

e. Remaining three AUX FUEL PUMPs -

Check as in step d, except check R AUX

8. Transponder - Check and set.

PRESS light on, then off, for R AUX FUEL

9. Navigation Set DGNS - Perform operational

PUMP switches.

check, confirm waypoint entry and SAS/AS as

required.

FUEL CONTR switches - Set as follows:

*8-25. Before Taxi.

a. All FUEL PUMP switches - ON.

b. XFEED switch CLOSE

- XFEEDS

WARNING

checked closed, light out.

Personnel injury or death may occur and

VGI switches - As required.

damage to airframe and rotor systems will

ANTI-ICE systems - Check as required.

occur if the forward or aft rotor head rotor

blade droop stop(s) are missing or inter-

a. PITOT switch - ON. Physically check for

poser block(s) on the aft rotor head are not

pitot tube and yaw port heat. Then switch

engaged. After engine run-up and before

OFF.

flight, or shutdown if flight is not con-

ducted, the flight engineer will scan the

b. W/S switches - ON. Physically check for

ground in the immediate area of the air-

windshield heat. Then switch OFF.

craft for evidence of detached droop

Flight instruments - Check as follows:

stops.

a. HSI compass cards - Check synchro-

CAUTION

nized. Crosscheck with magnetic com-

pass. Refer to Chapter 3, Section III.

To prevent damage to the cargo hooks and

structure, do not ground taxi over rough

b. Attitude indicators - Adjust as required.

or uneven terrain with the forward and aft

cargo hooks installed.

712

Emergency engine trim system

Check as follows:

1. SWIVEL switch - As required.

a. EMERG ENG TRIM 1 switch - DECR

momentarily. Check torque and N1 de-

2. AFCS switch - As required.

Change 17

8-9

TM 55-1520-240-10

NOTE

8-29. Before Takeoff.

The PAC check may be deferred to the hover

1. Systems - Check indications of the following:

check.

a. Rotor - Check as required.

3.1

714A

Power Assurance Check (PAC) - Per-

b. Torque.

form first flight of day:

c. Engine.

a. NR% switch - 100%.

d. Transmission.

b. ENG 1 ENG COND lever - Adjust.

e. Fuel.

c. THRUST CONT lever - Raise until TRQ reads

60% to 80%. Stabilize for 30 seconds.

712

Master caution panel.

F d. TEST switch ENG 2 - PWR ASSURANCE.

714A

Caution/Advisory panel.

Check DECU display. Compare displayed value

2. PARKING BRAKE As required.

with PAT Trigger Value.

3. AFCS SYSTEM SEL switch - As required.

e. ENG 1 ENG COND lever - FLT.

4. CYCLIC TRIM switch - Check.

f. Repeat check with ENG 2 ENG COND lever.

5. SWIVEL switch - LOCK.

g. THRUST CONT lever - Adjust.

6. Transponder- As required.

4. RRPM - Set as required.

7. Crew, passengers, and mission equipment

8-28. Hover Check. Perform the following check at a

- Check.

hover:

8-30. Normal Takeoff. Refer to TC 1-216 Aircrew

1. Flight controls - Check flight controls for cor

Training Manual (ATM).

rect response.

8-31. Hover Refer to TC 1-216 Aircrew Training Manual

2. Systems instruments - Check normal.

(ATM).

3. Flight instruments - Check as required.

To engage radar altitude hold perform the following:

_________

a. VSI, barometric and radar altimeters - indicate

WARNING

climb and descent.

b. Turn pointers, heading indicators and magnetic

Do not use radar altitude hold in forward

compass-Indicate turns right and left.

flight over terrain. It may not provide ad-

c. Slip indicator - Ball free in race.

equate terrain clearance in rapidly changing

d. Attitude indicator - Indicate nose high, nose

terrain. Use radar altitude hold to maintain a

low, banks left and right.

constant absolute altitude during hover or

forward flight over water. RAD ALT hold

can be used to a maximum of 1,500 feet

absolute altitude.

NOTE

a. Radar altimeter - ON. Check that pointer has

Rapid rotation of the pitch and roll trim knobs

rotated from behind the mask, the digital display

on the attitude indicator may cause abrupt pitch

is lit, and the OFF flag is out of view.

and roll attitude changes with AFCS on.

b. Fly to desired altitude.

e. Airspeed indicator - Check.

c. RAD ALT select on AFCS panel - Press. Check

FO 4. GROUND CONTACT indicating lights check

ENGAGED light ON. The radar altitude hold

-Both off.

feature of the AFCS will maintain a constant

5. AFCS - Check as follows: (First flight of day).

altitude.

a. SYSTEM SEL switch - NO. 1. Check helicop-

d. To select another altitude press the THRUST

ter stable with no abrupt engagement error.

CONT BRAKE TRIGGER. Fly to desired alti

Check NO. 2 AFCS OFF caution on.

tude and release the THRUST CONT BRAKE

b. SYSTEM SEL switch --NO. 2. Check helicop-

TRIGGER. The altitude at the moment the

trigger is released will be the new altitude.

ter stable with no abrupt engagement error.

Check NO. 1 AFCS OFF caution on.

Takeoff over water. Takeoff over water is begun from a

c. SYSTEM SEL switch - Both. Check helicop-

hover height of approximately 30 feet.

ter stabled with no abrupt engagement error.

Align the helicopter with the desired takeoff course at a

Check both AFCS OFF caution capsules extin-

stabilized hover of approximately 30 feet, or an altitude

guished.

permitting safe obstacle clearance. Smoothly apply forward

6. Power - Check. Note torque and N1.

cyclic pressure to level the helicopter and begin acceleration

Change 13

8-11

TM 55-1520-240-10

into effective translational lift (ETL). Control rate of accel-

8-35. Cruise Check.

eration and direction of flight with cyclic and altitude with

1. Fuel Consumption - Check.

thrust. As the aircraft accelerates through ETL, establish a

2. HDG select - As required. Perform the follow-

pitch attitude and apply thrust that will result in a simulta-

ing:

neous gain in altitude and airspeed. Continuous coordinated

a. Rotate HDG knob on the HSI that is to be used

application of control pressures is necessary to maintain

for the referenced heading until the cursor (bug)

rim, heading, flight path, airspeed, and rate of climb.

is aligned with chosen heading.

8-32. Maximum Performance Takeoff. A takeoff that

b. Trim helicopter straight and level (center ball on

demands maximum performance from the aircraft may be

turn and slip indicator) and trim forces (depress

necessary because of various combinations of heavy aircraft

CENTERING DEVICE RELEASE).

loads, restricted performance due to high density altitudes,

barriers that must be cleared, and other terrain features. The

c. CMD SEL switch on HSI MODE SELECT

decision to use either of the following takeoff techniques

panel - Press. Check switch is depressed and

must be based on an evaluation of the conditions and

SEL legend is lit.

aircraft performance.

d. AFCS HDG - Press. Check ENGAGED light

a. Coordinated Climb Takeoff. Align the helicopter with

on. The helicopter will now turn to and capture

he chosen takeoff course at a stabilized hover of approxi-

the heading.

mately 10 feet. Apply forward cyclic pressure smoothly and

e. Heading can be changed by rotating the cursor

gradually while simultaneously increasing thrust to begin a

(bug) to the new heading. The helicopter will

coordinated acceleration and climb. The climb may be made

then turn to the new heading.

vertical with appropriate adjustment of the cyclic control.

f. Cabin door escape panel - Assure that airspeed

Maximum torque available should be applied as the aircraft

is less than 100 KIAS before closing door in

attitude is established that will permit safe obstacle clear-

flight.

ance. The climbout is continued at that attitude and power

NOTE

setting until the obstacle is cleared. After the obstacle is

cleared, adjust aircraft attitude and thrust as required to

Pressing either CENTERING DEVICE RE-

establish a climb at the desired rate and airspeed. Continu-

LEASE switch disengages heading select op-

ous coordinated application of control pressures is neces-

erations

sary to maintain trim, heading, flight path, airspeed, and rate

of climb. Takeoff may be made from the ground by

CAUTION

positioning the cyclic control in neutral, prior to increasing

thrust. Takeoff over water is begun from a hover height of

Radar altitude (RAD ALT) hold can only be

approximately 30 feet and continued as above.

used in forward flight overwater, it cannot be

used in forward flight over terrain.

b. Level Acceleration Takeoff. Align the helicopter with

the chosen takeoff course at a stabilized hover of approxi-

CAUTION

mately 10 feet. Apply forward cyclic pressure smoothly and

gradually while simultaneously increasing thrust to begin

Large pitch inputs will result in rapid gain or

accelerating at approximately 10 feet. Maximum torque

loss of altitude. If altitude hold is on, an

available should be applied prior to accelerating through

over-torque condition can occur during large

ETL. Adjust cyclic stick to maintain desired pitch attitude

pitch-down inputs. Monitor thrust control

throughout acceleration to climb airspeed. Approximately 5

movement and torquemeter during airspeed

knots prior to reaching the selected climb airspeed, gradu-

changes. Also, when operating with altitude

ally release forward cyclic pressure and allow the aircraft to

hold, limit bank angles to 45 degrees maxi-

begin a constant airspeed climb to clear the obstacle. Care

mum. An excessive bank angle may result in

must be taken not to decrease airspeed during the climbout

an altitude loss, and if operating at a high

since this may result in the helicopter descending (falling

through). After the obstacle is cleared, adjust aircraft atti-

gross weight, an overtorque condition.

tude and thrust as required to establish a climb at the desired

3. BARO/RAD altitude hold - As required. Alti-

rate and airspeed. Continuous coordinated application of

tude hold is selected to hold a constant altitude.

control pressures is necessary to maintain trim, heading,

a. When at chosen cruise altitude and airspeed,

flight path, airspeed, and rate of climb. Takeoff may be

press BARO (RAD) ALT switch on AFCS

made from the ground by positioning the cyclic control in

control panel. Check that ENGAGED light is

neutral prior to increasing thrust.

ON. The helicopter will now maintain the se-

Takeoff over water is begun from a hover height of

lected altitude.

approximately 30 feet and continued as above.

b. To change altitude, press the THRUST CONT

8-33.

Slingload.

BRAKE TRIGGER. Fly the helicopter to the

Refer To TC 1-2 16 Aircrew Training Manual (ATM).

desired altitude, then release the THRUST

8-34.

Climb.

CONT BRAKE TRIGGER. The helicopter will

Refer to chapter 7 for recommended airspeeds, power

remain at the altitude at which the trigger was

settings, and fuel flow.

released.

8-12

Change 13

TM 55-1520-240-10

4. Ramp area - The ramp area must be checked

not vary significantly because of GW or CG. As observed

every 30 minutes of flight. (Refer to section I,

from the cockpit, the water level will appear to intersect the

Crew Duties.)

fuselage below the lower nose enclosure.

8-36. DESCENT.

8-40. Running Landing to Water. Running landings

Refer to Chapter 7 for power requirements at selected

can be performed within the limitations shown in chapter 5.,

airspeeds and rates of descent.

but should only be performed during training missions,

actual single-engine conditions when a hovering approach is

8-37.

Before Landing.

not possible, or when atmospheric conditions dictate. Run-

The following checks must be accomplished prior to land-

ning landings for training should only be performed to calm

ing

water (Sea State 1 or less).

1. Systems - Check indications of the following:

Prior to performing a running landing to the water, the

a. Rotor.

PITOT HEAT switch must be ON. The ramp, lower half of

b. Torque.

cabin door, lower rescue door, and drain plugs must be

closed. Landing/searchlights shall be retracted. The ap-

c. Engine.

proach is shallow, and flown at an airspeed that provides

d. Transmission.

safe aircraft control. Prior to water entry, it may be

e. Fuel.

necessary to use the windshield wipers. Entry of the aft

712

Master caution panel.

wheels into the water is easily recognized because the

714A

Caution/Advisory Panel.

helicopter will decelerate noticeably. Touchdown attitude

2. PARKING BRAKE - As required.

should be held constant until the apparent water speed has

3. AFCS control panel - Check as follows:

decreased below 10 knots. At or below 10 knots, the nose

can be lowered to the water by lowering the thrust control

a. AFCS HDG and ALT switches as required.

rod and neutralizing the cyclic stick. A 4- to 5-knot forward

b. CYLIC TRIM switch as required.

speed will result when the helicopter is level and the

c. AFCS selector switch as required.

controls are neutralized with the thrust control at the ground

4. Crew, passengers, and mission equipment-

detent.

Check.

NOTE

8-38. LANDING.

Aft landing gear ground proximity switches are

Refer to FC1-2l6, Aircrew Training Manual (ATM).

not actuated during a water landing. Therefore,

longitudinal cyclic pitch actuators must be

8-39. Landing From a Hover to Water. Prior to

manually set to ground position.

landing, the PITOT HEAT switch must be ON. The ramp,

lower half cabin door, lower rescue door, and drain plugs

When the helicopter is in the water, two-way communica -

must be closed. Landing/searchlights shall be retracted.

tion is lost on system whose antennas are submerged. The

From a stabilized hover, decrease thrust for a smooth rate of

HF radio can be operated.

descent. A vertical descent, rather than a descent with some

8-41. After Landing.

forward movement, will tend to disperse the swirling water

1. AFCS SYSTEM SEL switch - As required.

spray under a no-wind condition. As the aft wheels and then

2. SWIVEL switch - As required.

the fuselage near the water, continue to lower, the thrust

control to ground detent. As more of the fuselage enters the

3. Transponder - As required.

water, buoyancy will level the helicopter attitude.

4. ANTI-ICE switches - OFF.

5. GROUND CONTACT lights check - both on.

NOTE

6. Cyclic trim indicators - Check GND indication.

Aft landing gear ground proximity switches are

not actuated during a water landing. Therefore,

8-42. Engine Shutdown.

longitudinal cyclic pitch actuators must be

manually set to ground position.

CAUTION

Critical flight control components can be

damaged if thrust is not in ground detent.

If contact is made with floating debris, re-

turn to hover and assess damage.

1. Flight Controls - Neutralize. Position the pedals

and cyclic at neutral and the thrust at the ground

As the attitude approaches level, the helicopter will start

detent. Start 2 minutes engine cool-down run

moving forward and stabilize at approximately 4 to 5 knots.

when the THRUST CONT lever is in the detent

This speed will be attained with the controls in neutral and

position and the engine temperatures have stabi-

the thrust control at the ground detent. The water level will

lized.

Change 13

8-13

TM 55-1520-240-10

2. PARKING BRAKE - Set.

serve the rotor tip path of the forward and

aft rotor heads. A rotor blade drooping

3. HTG switches - OFF.

significantly lower than the other blades

indicates a missing droop stop. In this

4. SLT-FIL switches - OFF and stow as required.

case the remaining running engine’s ECL

should be advanced until sufficient rotor

5. AFCS SYSTEM SEL switch - OFF.

RPM is achieved to lift rotor blades off the

stops to insure no blade contact with air-

6. Ramp - As required.

frame and maintenance is contacted to

7. Wheels - Chocked.

prepare aircraft for an emergency shut-

down that will minimize damage to the air-

8. Mission equipment - Safe as required.

craft and injury to personnel.

9. Fire guard - Posted.

NOTE

L 10. APU - Start. For APU starting procedures,

Aft landing gear ground proximity switches

refer to paragraph 8-23.

are not actuated during a water landing.

Therefore, longitudinal cyclic pitch actuators

11. APU GEN switch - ON.

must be manually set to ground position prior

to engine shutdown on the water.

12. GEN 1 and 2 switches - OFF.

13. PWR XFER 1 and 2 switches - ON.

15. ENG COND levers - GND, run engines at

GND for 2 minutes.

14. Cyclic trim indicators - Check GND position,

manually program if necessary.

16. FUEL CONTR switches - Set as follows:

a. XFEED switch - CLOSE.

WARNING

b. FUEL PUMP switches - OFF.

c. REFUEL STA switch - As required.

Personnel injury or death may occur and

damage to the airframe and rotor systems

will occur if the forward or aft rotor head

rotor blade droop stop(s) are missing or

WARNING

interposer block(s) on the aft rotor head

are not engaged. After engine run-up and

Personnel injury or death may occur and

before flight, or shut down if flight is not

damage to the airframe and rotor systems

conducted, the flight engineer will scan

will occur if the forward or aft rotor head

the ground in the immediate area of the

rotor blade droop stop(s) are missing or

aircraft for evidence of detached droop

the interposer blocks on the aft rotor head

stops. Prior to moving engine condition

are not engaged. Prior to moving engine

levers (ECL) from ground to stop, flight

condition levers (ECL) from ground to

engineer will, to the best extent possible,

stop, the flight engineer will, to the best

determine if the interposer blocks on the

extent possible, determine if the interpos-

aft rotor head are in position and that all

er blocks on the aft rotor head are in posi-

forward and aft droop stops are attached.

tion and that all forward and aft droop

If an interposer block or droop stop are not

stops are attached. If an interposer block

in place, the flight engineer will notify the

or droop stop is not in place, the flight

pilot in command. All non-crewmembers

engineer will notify the pilot in command.

will evacuate aircraft to a safe location. If

If interposer blocks appear to be in place

possible, crew will contact maintenance

and no droop stops missing, the flight en-

and attempt to engage interposer block

gineer will clear the pilot to shut down the

with high pressure water stream or pre-

first engine. After the first engine is shut

pare aircraft for shutdown in such a way

down, the flight engineer will observe the

as to minimize damage to aircraft and

rotor tip path of the forward and aft rotor

components and prevent injury to person-

heads. A rotor blade drooping significant-

nel. If interposer blocks appear to be in

ly lower than the other blades indicates a

place and no droop stops are missing, the

missing droop stop.

flight engineer will clear the pilot to shut-

down the first engine. After the first engine

is shut down, the flight engineer will ob-

17. ENG COND levers - STOP.

8-14

Change 17

TECHNICAL MANUAL MAINTENANCE MANUAL FOR ARMY CH-47D HELICOPTER (1992) - page 11