BHT-212-MM-02

BHT-212-MM

MODEL

MAINTENANCE MANUAL VOLUME 2

HANDLING AND SERVICING NOTICE The instructions set forth in this manual, as supplemented or modified by Alert Service Bulletins and other directions issued by Bell Helicopter Textron and Airworthiness Directives issued by the Federal Aviation Administration, shall be strictly followed.

COPYRIGHT NOTICE 1997 COPYRIGHT TEXTRONINC. BELL® HELICOPTER

Bell Helicopte A Subsidiaryof TextronInc. POST OFFICE BOX 482 * FORT WORTH,TEXAS 76101

ANDBELLHELICOPTER TEXTRON, A DIVISION OFTEXTRON CANADA LTD. ALLRIGHTS RESERVED

7

REVISION 5

-

JU

25 SEPTEMBER 1997

BHT-212-MM

PROPRIETARY RIGHTS NOTICE These data, excluding Chapter 4, Airworthiness

Limitations,

are

proprietary to Bell Helicopter Textron, Inc. Disclosure, reproduction, or use of these data for any purpose other than helicopter operation and/or maintenance is forbidden without prior written authorization from Bell Helicopter Textron, Inc.

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron P. O. Box 482 Fort Worth, Texas 76101-0482

PN

BHT-212-MM

CHAPTER 6 CONTENTS Paragraph Number 6-1 6-2 6-3

DIMENSIONS AND CHARTS MAINTENANCE PROCEDURES

Title Airframe principal dimensions .................... Airframe reference lines .......................... Stations, waterlines, and buttock lines .........

Chapter/Section Number

Page Number

6-00-00 6-00-00 6-00-00

3 3 3

FIGURES Figure Number 6-1 6-2

Title Principal dim ensions ......................................................... Station diagram ..............................................................

Page Number 4 5

6-00-00

Page 1/2

BHT-212-MM

DIMENSIONS AND CHARTS 6-1.

AIRFRAME PRINCIPAL

3.

WATER LINES (W.L.):

Water lines are

DIMENSIONS.

horizontal planes perpendicular to, and measured along, the vertical axis of the

Figure 6-1 depicts the major dimensions of the helicopter. Due to variations in loading and landing gear deflection, all height dimensions are approximate. With ground handling wheels installed and fully extended, height will be increased by 5.0 in. (12.7 cm).

helicopter. Water line (0) is a plane below the lowest point on the fuselage. Water lines can be used to measure locations as described for station lines.

REFERENCE LINEmeasured 6-3.

STATIONS, WATERLINES, AND

BUTTOCK LINES.

4.

BUTTOCK LINES (B.L.):

Buttock lines

are vertical planes perpendicular to, and to, the left and right along the

ateral axis of the helicopter. Buttock line (0) is the plane at the vertical centerline of the helicopter. Buttock lines can be used to

measure locations as described for station lines.

1. GENERAL: Station lines, including buttock lines, water lines, tailboom and

5.

baggage compartment lines, elevator stations, and main and tail rotor blade stations are used to determine locations on, and within, the helicopter. All such locators lines are measured (in inches) from known points, Therefore, these lines will not be expressed in metric equivalents within this manual.

COMPARTMENT STATION LINES: Baggage compartment station lines are measured from the tailboom fuselage attach point to aft end of baggage compartment. Tailboom station lines are measured from aft end of baggage compartment to center of intermediate gearbox.

2. STATION LINES (F.S.): Stations are vertical planes perpendicular to, and measured along, the longitudinal axis of the

6. ELEVATOR STATION LINES: Elevator station lines (E.S.) are buttock lines extended through the elevator to elevator outboard tips.

TAILBOOM

AND

BAGGAGE

helicopter. Station (0) is a plane usually

Fuselage station lines (F.S.) and tailboom

forward of the nose of the helicopter. Several

stations (B.S.) also apply to the elevator.

stations are marked under the cargo door opening. Several station lines are shown on figure 6-2 at recognizable locations on the

7. VERTICAL FIN STATION LINES (V.F.S.): Vertical fin stations are parallel vertical lines

airframe. Other station locations can be measured from these lines. Tailboom

perpendicular to the center line of the tail rotor shaft, below the leading edge of the

stations, stations within the baggage compartment, and stations along the vertical fin are illustrated in the same manner. These

vertical fin. Fuselage stations also apply to the vertical fin.

stations are perpendicular to the centerline on

8.

the tailboom and fin, as applicable, because these components are mounted at an angle to the horizontal plane of the fuselage.

STATION LINES: Main and tail rotor blade station lines are measured from the center of hub to tip of blade.

MAIN AND TAIL

ROTOR

BLADE

6-00-00 Page 3

57 FT.0.68 IN. (PRIOR TO 30940) 57 FT. 1.68 IN. (30940 AND SUB.) 42 FT. 1.67 IN.

48 FT. NOTE

9 FT.4.48IN.

DIA

-4FT.

2 FT.6.58IN.

12FT.1.0IN.

Vertical dimensions will increase by approximately 1.5 inches when helicopter is empty.

28FT.11.12IN. 12 FT.9.05IN.

9 FT0.5IN.-

14 FT.

11o FLAPPING

(PRIOR TO

12 FT.

6.83 IN.

8F.7I

8 FT.6 IN.

(30940 AND

(PRIOR

30940) 8 3 IN. FT.

1.9 IN. 5 FT.

8 FT 8.4 IN.

GROUND LINE AT MID CG 11,200 LB GROSS WEIGHT

4 FT.

(30940

SUBQ)

EDGE

9 FT. 4.0 IN.

AT 11,200LB GROSSWEIGHT

212-M-6-1 212-900-15P

BHT-212-MM

140.34 116.40 128.32 74.25

92

166

37 BL 4

3 63

BL35

155.06

102

BL3486

178

BL34.23

211.06

3BL ROOFFRAME, 112.80123 129

BL 14 BEAM

BL15.25

BL14 BEAM

W 22

56.24 BL50

WL71.2

DOORBL 12

ENGINE

DOOR

192.85

218

BL 56.24

ROTOR

BL15.16 HELICOPTER

480.165

212-M-6-2-1

Figure 6-2.

Station diagram (sheet 1 of 2)

6-00-00 Page 5

BHT-212-MM

133.048

WL 136.515 -5o 133.506 TRANS

176.82

201.85

221.75 232.99

15246

63.3874.25 74.25

35

WL

98.25 TOP OF 98.25 PYLON

71.48

89.71 WL

6

214.17

TRACK

WL 38 43.40

54.89 ~WL

127.466

5344

FWDCANT

AFT CANT BLKMD.

BLKHD.

WL

WL102.265 WL102.265

TOPOF TAILBOOM TRACK

ATTACH BLK HD. WL 36

TRANS

WL22FLOOR

WL30.046

110.73 480.165 TAILROTOR

488.73

WL 138.378

WL122.05

23.60 244.61

300.81

SHAFT 341.48

420.5 363.54

75.30

17.42 WL 0 243.937

326.63

449.696

212-M-6-2-2

Figure 6-2.

6-00-00 Page 6

Station diagram (sheet 2)

BHT-212-MM

CHAPTER 7 CONTENTS Paragraph Number 7-1 7-2 7-3 7-4

MAINTENANCE PROCEDURES

Title Lifting helicopter ......................... Lifting complete helicopter (mast installed)..... Lifting complete helicopter (mast removed) .... Lifting complete helicopter (transmission

removed) ......... 7-5

LIFTING AND JACKING

........................

.

Lifting tailboom only ............................

Chapter/Section Number

Page Number

7-00-00 7-00-00 7-00-00

3 3 3

7-00-00

3

7-00-00

3

7-00-00

7

JACKING 7-6

Jacking helicopter ................................ FIGURES

Figure Number 7-1 7-2 7-3

Title Hoisting complete helicopter ................................................. Hoisting tailboom ............................................................ Jacking ......................................................................

Page Number 4 6 8

7-00-00 Page 1/2

BHT-212-MM

LIFTING AND JACKING 7-1.

4.

LIFTING HELICOPTER.

7-4. LIFTING COMPLETE HELICOPTER (TRANSMISSION REMOVED).

7-2. LIFTING COMPLETE HELICOPTER (MAST INSTALLED).

1. Attach a suitable hoist to pylon lift link (figure 7-1).

REQUIRED SPECIAL TOOLS REQUIRED NUMBER

204-011-178-001

Hoist slowly with a constant lifting force.

NOMENCLATURE

2.

Clevis

helicopter when hoisting. If lifting beyond reach from ground, use a rope to steady

Station a person at tail skid to steady

helicopter. 1. Attach a 204-011-178-001 hoisting clevis, or equivalent, to eye provided on retaining nut at top of main rotor mast. Connect suitable hoist and take up slack.

3. 7-5.

Hoist slowly with a constant lifting force. LIFTING TAILBOOM ONLY.

2. Station a person at tail skid to steady helicopter

when hoisting.

If lifting beyond

SPECIAL TOOLS REQUIRED

reach from ground, use a rope to steady helicopter. 3.

Hoist slowly with a constant lifting force.

7-3. LIFTING COMPLETE HELICOPTER (MAST REMOVED).

NUMBER

NOMENCLATURE

T101626

Sling assembly

1. Attach sling assembly, T101626, (3, figure 7-2) to suitable hoist and clevis.

SPECIAL TOOLS REQUIRED CAUTION NUMBER

NOMENCLATURE

204-040-929-101

Lift plate and cover

204-011-178-001

Clevis

DO NOT POSITION

STRAP

AREA OF BAGGAGE

IN

COM-

SUITABLE PARTMENT DOOR. STRAPS SHALL BE POSITIONED

AT BULKHEADS TO PREVENT 1.

Install

lift plate

(204-040-929-101

or

DAMAGE TO TAILBOOM SKIN.

equivalent) on transmission.

2. Position straps around tailboom at 2. Attach suitable hoist with clevis (204-011178-001 or equivalent) to lifting eye.

3. Station a person at tail skid to steady helicopter when hoisting. If lifting beyond reach from ground, helicopter.

use a rope to steady

bulkheads forward of vertical fin and aft of baggage door. Position sling at approximate center of gravity to maintain balance.

3. Support weight of tailboom with straps. Take up slack and disconnect tailboom from helicopter (Chapter 53). 7-00-00 Page 3

BHT-212-MM TAIL SKID (REF)

MAIN ROTOR TIE DOWN STRAP (REF)

ROPE (REF)

LIFT PROCEDURE

REMOVED

DETAIL

Figure 7-1.

7-00-00 Page 4

A

Hoisting complete helicopter

4.

Pylon lift link

212-M-7-1 204-011-178A

BHT-212-MM NOTE

CAUTION

For use of support

assembly,

T102012, refer to Chapter 53. ENSURE TAILBOOM ROTATE IN STRAPS 4.

DOES NOT

Hoist tailboom slowly with a steady force.

7-00-00 Page 5

BHT-212-MM

3

BAGGAGECOMPARTMENT DOOR RIGHT SIDE

1.

Hoist (1 Ton min. capacity)

2. 3. 4.

Clevis Sling assembly T101626 Strap NOTE

Position sling assembly on tailboom to maintain balance. CAUTION

A

ENSURE STRAPS (4) ARE POSITIONED AND DOUBLE WRAPPED AT BULKHEADS TO HELP PREVENT TAILBOOM FROM FLIPPING OVER. DO

NOT POSITION

STRAPS (4) IN AREA OF

BAGGAGE COMPARTMENT DOOR. 212-M-7-2

Figure 7-2. Hoisting tailboom

7-00-00 Page 6

BHT-212-MM

JACKING

7-6. JACKING HELICOPTER.

AREA IF WIND VELOCITY EXCEEDS 20 KNOTS. HEAD HELICOPTER WIND WIND.

SPECIAL TOOLS REQUIRED

NUMBER

INTO PREVAILING

PROVIDE SUITABLE SURFACE

NOMENCLATURE

FOR JACKS TO REST ON (LEVEL

Regent No. 988S, or Hydraulic tripod jacks equivalent (4 each, 6000 lb.

HARD SURFACE VALENT).

OR EQUI-

capacity) 1.

Raise helicopter as follows:

10).

WARNING DO NOT ALLOW PERSONNEL TO

b. Place four hydraulic jacks in position under jack point fittings (figure 7-3).

CRAWL INTO OR ONTO HELICOPTER

WHILE

WHILE

HELICOPTER

RAISING

OR

IS

c.

Operate jack handles slowly and evenly

at all four positions, being careful to keep

SUPPORTED ON JACKS. ROPE OFF AREA AND DISPLAY SIGNS

helicopter height.

JACKS".

2.

STATING 'HELICOPTER ON

CAUTION

level, as it is raised to desired

Lower helicopters as follows:

a. Slowly and carefully lower all four jacks simultaneously.

b. Remove jacks and other equipment DO NOT PLACE HELICOPTER ON

JACKS

from area.

IN AN UNSHELTERED

7-00-00 Page 7

BHT-212-MM

BLADE TIEDOWN (REF)

7-00-00 Page 8

SUITABLE BLOCKS R SUPPORT

1. Forward Jack Fitting (2) 2. Aft Jack Fitting (2)

212-M-7-3 212-900-001

Figure 7-3.

7-00-00 Page 8

Jacking

BHT-212-MM

CHAPTER 8 CONTENTS Paragraph Number 8-1 8-2 8-3 8-4 8-5 8-6 8-7 8-8 8-9

WEIGHT AND BALANCE

MAINTENANCE PROCEDURES

Title Weight and balance .............................. Leveling ........................................ Weighing ....................................... Determining center of gravity location .......... Determining amount of ballast required ........ Weight empty center of gravity charts - kits.... Nose ballast installation and removal ............. Tail skid ballast ................................... Weight and balance sample problem .............

Chapter/Section Number

Page Number

8-00-00 8-00-00 8-00-00 8-00-00 8-00-00 8-00-00 8-00-00 8-00-00 8-00-00

3 3 3 5 5 7 8 8 22

FIGURES Figure Number 8-1 8-2 8-3 8-4 8-5 8-6 8-7 8-8 8-9 8-10 8-11 8-12 8-13 8-14 8-15 8-16

Title Leveling ...................................................................... Weight and balance.......................................................... Weight empty center of gravity .............................................. Weight empty center of gravity with emergency flotation, 212-706-021 ...... Weight empty center of gravity with emergency flotation, 212-706-021, and auxiliary fuel tanks, 205-706-044 ........................................... Weight empty center of gravity with emergency flotation, 212-706-021, and auxiliary fuel tanks, 205-706-045 ............................................ Weight empty center of gravity with emergency flotation and auxiliary fuel tanks, 212-899-243 (one 90 and one 20 gallon tank installed)............... Weight empty center of gravity with emergency flotation, 212-706-021, and auxiliary fuel tank, 212-899-243 (one 90 gallon tank installed) .............. Weight empty center of gravity with auxiliary fuel tanks, 205-706-044....... Weight empty center of gravity with auxiliary fuel tanks, 205-706-045....... Weight empty center of gravity with auxiliary fuel tanks, 212-899-243 (one 90 and one 20 gallon tank) .................................................. Weight empty center of gravity with auxiliary fuel, 212-899-243 (one 90 gallon tank installed) ........................................................ Weight empty center of gravity with floats, 205-706-050 ..................... Nose ballast ................................................................. Tail skid ballast .............................................................. . .......................................... Actual weight record sample

Page Number 4 6 9 10 11 12 13 14 15 16 17 18 19 20 21 23

8-00-00 Page 1/2

BHT-212-MM

WEIGHT AND BALANCE 8-1.

WEIGHT AND BALANCE.

3.

Adjust height of jacks to bring plumb bob

exactly over the point where two lines The center of gravity (CG) is considered to be the balancing point of a body for weight and

intersect at 0° on leveling plate. Helicopter is now leveled both longitudinally and laterally.

balance purposes. The helicopter can be compared to a pendulum; the point of

4. Remove plumb bob.

suspension being where the main rotor hub intersects the mast (the pendulum weight being the helicopter). If the pendulum weight is allowed to stop, it will come to rest directly

8-3.

below the suspension point. For example: If

configuration

the CG of a helicopter is aft of the hub-mast intersection, the helicopter will be tail low in flight. The pilot can correct this condition by moving the cyclic control stick forward. If the

WEIGHING.

The helicopter

should

be weighed

in a

as near Weight Empty as

possible NOTE

required movement of the stick is great enough, the pilot will use all available control,

Weight Empty condition is the basic

thus limiting maneuverability and forward

helicopter

speed. Since such loss of maneuverability is unsafe, care shall always be taken to keep

ballast, special equipment, transmission oil, hydraulic fluid,

the helicopter

unusable fuel, and undrainable oil.

operational

center

limits.

of gravity

within

Moving the CG is

accomplished by adding or removing ballast.

together

with seats,

RefertoFAR29.

1. All kits, transmission oil, and hydraulic fluid may remain aboard.

NOTE

For additional weight and balance information, operators in territorial United States shall refer to FAR 29. Operators outside territorial United

States shall refer to information issued by the licensing authority, 8-2.

Ensure baggage compartment is empty.

3. Scale accuracy shall be within plus or minus 1.0 lbs.

4. Position scales in an approximately level area, and check for proper adjustment to zero position.

LEVELING. NOTE NOTE

1.

2.

| CAUTION

Leveling plate (2, figure 8-1) is graduated in increments of 1/4 ° .

WEIGHING

SHOULD

The plate is located on cabin floor

ATTEMPTED

IN AN OPEN AREA

just inside left passenger cargo

BECAUSE

door. A slotted hole in upper door frame is provided for suspension of a plumb bob (1).

EFFECTS OF WIND.

Support helicopter on jacks (Chapter 7).

NOT BE

OF THE ADVERSE

5. Position a scale and jack assembly under each jack pad or under each forward jack pad and one aft jack pad. Raise helicopter clear of floor.

2. Hang plumb bob (1) in slotted opening in door frame with point of plumb bob just above leveling plate (2) on cabin floor. 8-00-00 Page 3

BHT-212-MM

1. 2.

.

Plumb Bob Leveling Plate

Figure 8-1.

8-00-00 Page 4

Leveling

BHT-212-MM

NOTE For electronic scales, ensure load cells and adapters are fastened securely to jacks. Accomplish scale manufacturers recommended warm up time and zero each load cell.

1. This distance from F.S. 0.0 to a line through centers of forward jack pads is called the forward arm. The distance from F.S. 0.0 to a line through the center of aft jack pads is called the aft arm. The forward arm is 61.69 in. (15.64 cm) and the aft arm is 211.58 in. (53.74 cm) (figure 8-2).

6.

Level helicopter (paragraph 8-2).

2. Multiply total net weight of forward scales by forward arm. The product is called forward moment and is expressed in inch pounds

7.

Balance each scale and record its

(in.lbs.).

reading. 3.

Multiply total net weight of aft scales by

8. Lower helicopter to surface. Weigh jacks, blocks, and any other equipment used between scales and helicopter. Deduct this weight (tare) from actual (first) scale readings to obtain net scale weights.

aft arm. This is aft moment in in.lbs. 4 Add forward and aft moments and divide by total "As Weighed" weight. The quotient is helicopter "As Weighed" CG in inches aft of F.S. 0.0.

NOTE

NOTE

For

electronic

scales,

The above procedure may be stated

lower

helicopter and verify each cell returns to zero setting. Variations from zero are considered tare and shall be added or subtracted from readings.

in equation form as follows: As Weighed CG = (Net Wt. Fwd Scales) (61.69) + (Net Wt. Aft Scales) (211.58) = Total Net (As Weighed) Weight

9. Total "As Weighed" weight is the sum of the individual net scale weights. 8-4. DETERMINING CENTER OF GRAVITY LOCATION.

(TABLE I.D.910404)

8-5. DETERMINING AMOUNT OF BALLAST REQUIRED.

1. Weight Empty center of gravity chart (figure 8-3) is to be used for all configurations except when following kits are installed.

.CAUb CAUTIONi

a. Auxiliary Fuel, 205-706-044, THE WEIGHT EMPTY CENTER OF

GRAVITY

CHARTS

b.

Auxiliary Fuel, 205-706-045,

PRESENTED

AS A GUIDE

c.

Auxiliary Fuel, 212-899-243,

d.

Emergency Flotation, 212-706-021,

ARE TO

PROPERLY BALLAST THE IF HELICOPTER HELICOPTER. CANNOT BE BALANCED WITHIN

THESE

RESTRICTIONS,

THE

e. Floats, 205-706-050.

GROSS WEIGHT VERSUS CENTER OF GRAVITY LIMITS PRESENTED

IN THE APPROPRIATE FLIGHT

MANUAL

SHALL

NOT BE

EXCEEDED. GENUINE

BELL PARTS ARE YOUR BEST VALUE

8-00-00

Rev. 3

Page 5

BHT-212-MM 530

479.4 50

0

150

100

REF DATUM FUS STA 0.0

200

250

350

300

FUSSTA 133.5

200

450

400

500

550

7 IN1337

150

WL 136.5 INTERSECTION WL 137.5 -HUB AND MAST PASS.DOOR

100

DRIVE SHAFT

CREW DOOR

18 IN.

50

MAST SERVICE

DECK i

JACK PADS- AFT FUS STA 211.58 CABIN FLOOR

W.L 0 HINGED DOOR POST

-20 ININ. -20 A

JACK PADS - FWD FUS STA 61.69 B

212-M-8-2

Figure 8-2.

Weight and balance

flights, as applicable) then only add sufficient tail ballast, not to exceed 50 lbs. (22.68 kg), to move CG to applicable forward CG limit, if derived weight CG is aft of aft limit, add only sufficient nose ballast, not to exceed limits

NOTE For center of gravity charts applicable when above listed kits are installed, refer to paragraph 8-6. 2. Figure 8-3 has a forward CG limit for VFR flights, a forward CG limit for IFR flights and an aft CG limit. The CG limits are for the

following flight configurations.

specified in figure 8-14, to move CG to aft limit

4.

When Weight

Empty CG is not within

acceptable range shown in figure 8-3, use

a. Line A is forward CG limit for basic or IFR configuration helicopters for VFR flights if adding tail ballast.

following formula to determine amount of ballast required.

approximate = ?

Ballast - arm required ARM

b. Line B is forward CG limit for IFR configuration helicopters adding tail ballast.

on IFR flights

if

c. Line C is aft CG limit for basic or IFR helicopters for IFR or VFR configuration

flights, if adding nose ballast.

3. Actual Weight Empty CG can fall anywhere between aft and forward CG limit (VFR or IFR, whichever is applicable) and be acceptable; however, if derived Weight Empty CG is forward of forward limit (VFR or IFR 8-00-00 Page 6

NOTE

Derived weight and CG are "as weighed" values plus those Weight Empty items which may have been

omitted, and minusthosetems

which are not part of Weight Empty.

is apprd

and of derived weit eigt eie n nter lne on ure 8-3 nearest CG

BHT-212-MM

5. Check derived weight plus ballast and

Actual Weight Empty CG can fall

resultant CG on figure 8-3; add or remove ballast if necessary to arrive at desired CG.

anywhere between aft and forward limit. The dashed section of forward

limit allows a 0.10 in. (2.54 mm) tolerance range for actual CG.

NOTE

For weight and balance sample

flotation,

212-706-021

b. Emergency flotation, 212-706-021, with 205-706-044 auxiliary fuel tanks (figure 8-5).

8-6. WEIGHT EMPTY CENTER OF GRAVITY CHARTS - KITS. 1.

a. Emergency (figure 8-4).

problem, refer to paragraph 8-9.

When any of following kits are installed,

c. Emergency flotation, 212-706-021, with 205-706-045 auxiliary fuel tanks (figure 8-6).

the applicable referenced center of gravity chart shall be used. NOTE

d. Emergency flotation, 212-706-021, with 212-899-243 auxiliary fuel (one 90 gallon and one 20 gallon tank installed) (figure 8-7).

Weight Empty Center of Gravity Charts are guidelines provided by Bell Helicopter Textron to simplify

e. Emergency flotation, 212-706-021, with 212-899-243 auxiliary fuel (one 90 gallon tank installed) (figure 8-8).

ballast computations for the operators.

The limits are derived

f.

Auxiliary fuel tanks, 205-706-044,

using Gross Weight Center of

except when 212-706-021 emergency

Envelope and extreme Gravity. oad i n g forward a n d aft configurations include combinations

flotation or 205-706-050 floats are installed (figure 8-9). The CG limits on figure 8-9 are as follows:

of standard crew and passenger weights and various fuel loadings from the tables. Seating restrictions

and crew weight

(1) Line A is forward CG limit for VFR flights if adding tail ballast.

ranges are

accounted for in the derivations, but loading is baggage compartment not. Whenever a helicopter has a unique

situation such as: Nonstandard seating arrangement, nonstandard

(2) Line B is forward CG limit for IFR flights if adding tail ballast. (3) Line C is aft CG limit for IFR or VFR flights if adding nose ballast.

g. Auxiliary

fuel tanks, 205-706-045,

crew and/or passenger weights, baggage compartment being loaded, or weight empty exceeds chart, the forward and aft extremes for that

except when emergency flotation, 212-706021, or floats, 205-706-050, are installed, figure 8-10. If helicopter is used for IFR flights, Weight Empty should be ballasted to

configuration should be computed

fall within 0.10 in. (2.54 mm) of aft limit,

and checked against Gross Weight

provided ballast limits are not exceeded.

Center of Gravity

helicopter is used for VFR flights, Weight

Envelope to

compute ballast requirements.

The

If

Empty can fall anywhere between aft and

Gross Weight Center of Gravity Envelope is the final authority for

forward limit.

determining ballast requirements. Refer to weight and balance chapter in appropriate BHT-212-FM manual for additional information.

h. Auxiliary fuel tanks, 212-899-243 (one 90 and one 20 gallon tank installed), except when emergency flotation, 212-706-021, or floats, 205-706-050, are installed, figure 8-11. The CG limits on figure 8-11 are as follows: 8-00-00 Page 7

BHT-212-MM

(1) Line A is forward CG limit for VFR flights if adding tail ballast.

TAIL SKID BALLAST.

8-8.

1. Installation (2) Line B is forward CG limit for IFR flights if adding tail ballast. (3) Line C is aft CG limit for IFR or VFR flights if adding nose ballast.

of equipment at forward

stations and nose of helicopter may require addition of ballast (2 and 3, figure 8-15) and/ or inside tail skid (5) to aft section of tailboom (6). 2.

After installation of equipment, a weight

i. Auxiliary fuel, 212-899-243 (one 90 gallon fuel tank installed), except when

and balance check shall be accomplished. Ballast required to correctly locate center of

emergency flotation, 212-706-021, or floats, 205-706-050, are installed, figure 8-12. The CG limits on figure 8-12 are as follows:

gravity should be installed on or in tail skid (5).

(1) Line A is forward CG limit for VFR flights in adding tail ballast.

3. Ballast may be added to a maximum of 50 lbs. (22.68 kg) on and in tail skid. Ballast weights should be installed in a combination

to provide amount required by weight and (2) Line B is forward CG limit for IFR flights if adding tail ballast.

balance check. NOTE Ballast weights (2 and 3) shall be

(3) Line C is aft CG limit for IFR or VFR flights if adding nose ballast.

installed in combination with

j. Floats, 205-706-050 (figure 8-13). The Weight Empty CG may fall anywhere between forward and aft limit. 2.

Use applicable

Service Instructions

for

ballast installation instructions.

washers (1) and clamps (4) on tail skid (figure 8-15).

Ballast, when required, should be

4.

installed on that portion of tail skid located

inside tailboom (figure 8-15) or inside tail skid.

8-7. NOSE BALLAST INSTALLATION AND REMOVAL.

NOTE

1. Determine amount of ballast to be added or removed and moment arm. Refer to figure

When ballast is installed inside tail skid, tail skid shall be filled

8-14 for nose ballast station and butt line

completely full, approximately 15

(B.L.) moment arms. Add or remove nose ballast weight as symmetrically as possible.

lbs. (6.8 kg).

2. If ballast weight must be added, refer to figure 8-14 to determine allowable number of ballast plates in each location. Inspect nose compartment to determine where additional ballast plates may be added. 3. If ballast weight must be removed, inspect nose compartment to determine locations where ballast weight plates may be removed.

Install ballast inside tail skid as follows:

5.

a. Remove weight weight. b. Remove phenolic end of tail skid.

and record tail skid plug from forward

c.

Completely fill tail skid with lead shot.

d.

Install phenolic plug in forward end of

tail skid and reweight tail skid. Determine amount of ballast added (subtract tail skid empty weight from filled tail skid weight). Stencil forward end of tail skid, and inboard 8-00-00 Page 8

BHT-212-MM

170 LB. PILOT SEENOTE 7400

FUSELAGE STATION

-

INCHES

NOTES 2. 1.

Use this chart when 212-706-032 or 212-706-042 float kit is installed. 21 2-M-8-3 Weight ofthegravity This chart to Figure be used 8-3.. for all configurations when following areitiiinstalled. i~i FORWA iili'iliiiRDempty LIMIT ~except ~center iiiiliiis. ililiiiil