HANDBOOK OF MAINTENANCE INSTRUCTIONS FOR MDHI 369D/E/FF-500/600N HELICOPTERS (ISSUED: 1990)

CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

(10). For aircraft 369D; 001 & subs, 369E;

nose up/nose down attitude, perform

0001 thru 0528, 369FF; 0001 thru 0114

damper extension check.

and 500N; 001 thru 077: Remove plug

button from underside of fairing

NOTE:

assembly. Using a bright light and 10X

D The landing gear damper assemblies are

magnifying glass, inspect rivet hole in

to be checked at a helicopter gross weight

underside of strut for cracks. If crack is

of 1925 - 2075 pounds (874 - 942 kg) at a

found, strut must be scrapped and

longitudinal CG of approximately 103, ex

serviceable strut installed.

clusive of skid mounted flotation gear.

The empty weight of the 369D with full

4. Landing Gear Damper Inspection

fuel, but no passengers or cargo, is 1775 -

1925 pounds (806 - 874 kg). Therefore

(Ref. Table 601, Table 602 and Figure 401)

achieve the test configuration by adding

75 pounds (34 kg) of ballast to both sides

of the cabin floor, just aft of the tail rotor

NOTE: It is normal for a thin hydraulic oil film

pedals, 150 pounds (68 kg) total. Place the

to remain on damper as a result of wiping

helicopter on a smooth concrete or equiva

contact with piston seal. Newly-installed

lent surface (not asphalt).

dampers may also have slight oil seepage

from oil trapped in end cap threads during

D Dampers which have been modified (win

damper assembly. Neither of these should

terized) for cold weather operation are to

be considered damper leakage or cause for

be checked out no more than 30°F (-1°C)

damper replacement.

above the coldest temperature at which

the helicopter is operated.

(1). Inspect for hydraulic oil leakage. If

leakage is visible, wipe oil from damper

(a).

Raise and lower tailboom above and

after last flight of the day. Re-inspect

below the normal at-rest position

the following day for oil leakage. If

three times. On the last cycle, allow

leakage persists, perform bench check

the tailboom to slowly settle to the

(Ref. COM).

at-rest position.

(2). With helicopter on jacks, inspect

(b).

Measure and record dimension from

damper assemblies for evidence of

upper end cap to upper end of barrel

bearing looseness in upper and lower

on all four damper assemblies.

caps, worn bearings (excessive radial

(c).

Repeat steps (a). and (b). two more

play), loose or cracked caps and oil

times.

leakage. Any misalignment of torque

stripes on caps, piston and barrel

(d).

Lower and raise tailboom below and

indicates loosening of caps. Replace

above the normal at-rest position

immediately and repair removed

three times. On the last cycle, allow

damper.

the tailboom to slowly rise to the

at-rest position.

(3). Inspect damper attaching hardware for

security.

(e).

Measure and record dimension from

upper end cap to upper end of barrel

NOTE: Dampers which have been modified

on all four damper assemblies.

(winterized) for cold weather operation are

to be checked at not more than 30°F above

(f).

Repeat steps (d). and (e). two more

the coldest temperature at which the heli

times.

copter is operated.

(g).

Determine average extension from all

(4). Inspect landing gear dampers for

six readings for each damper assem

condition by observing stance of

bly. Remove and overhaul any

helicopter (normal stance is slightly

damper assembly not meeting

nose up). If stance indicates excessive

dimensions (Ref. Table 601).

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CSP-HMI-2

MAINTENANCE MANUAL

NOTE: If two damper assemblies fail to meet

(4). Inspect safety walk tape for condition

the minimum extension (Ref. Table 601), re

and security. Replace unserviceable

place the damper having the greater

tape.

amount of deflection with a known service

(5). Inspect fairing seal for condition.

able damper and repeat steps (a). thru (g). If

the original damper again fails to meet

(6). Install landing gear fairing assembly.

minimum extension requirements, replace

it with the known serviceable damper, rein

6. Landing Gear Fairing Inspection

stall the first damper and repeat steps (a).

thru (g). This will determine whether one or

(Ref. Figure 802)

both dampers require overhaul. For owners

and operators having suitable equipment,

(1). Inspect fairing support brackets for

any damper not meeting minimum exten

security of attachment to strut, cracks

sion requirements can be bench-checked by

and deformation.

applying a single load and measuring the

(2). Inspect fairing-to-skid seal for deterio

deflection when compressed. (Ref. Table 602

ration and bonding.

for load and compression requirements.)

Dampers meeting specifications in

(3). Inspect fuselage rubbing plate for

Table 602 may be returned to service if oth

security of bond and excessive wear.

er defects are not noted.

(4). On forward fairings (aft fairings with

5. Cabin Entry Step Inspection

steps attached to struts), inspect fairing

(Ref. Figure 801)

step seal for deterioration and bonding.

(1). Remove landing gear fairing assembly.

Table 601. Minimum Damper Extension

(2). Inspect step-to-strut attachment for

Standard Landing Gear

Extended Landing Gear

loose attaching hardware by checking

(in/cm)

for relative motion between mating

parts.

Aft

3.40 / 8.64

Aft

3.20 / 8.13

(3). Inspect welded joint of step for cracks.

Fwd

3.25 / 8.26

Fwd

2.90 / 7.37

Table 602. Landing Gear Damper Bench Test Requirements

Damper P/N (1)

Test Load

Compression Stroke

Pounds

(kg)

Inches

(mm/cm)

369D26300

(2)

1200

(545)

0.80

(20.32 mm)

369D26300−31

1320 ±100

(599 ±45)

0.80

(20.32 mm)

3780 ±400

(1716 ±182)

2.75

(6.99 cm)

369D26301

(2)

1700

(772)

0.80

(20.32 mm)

369D26301−31

1900 ±100

(863 ±45)

0.80

(20.32 mm)

3950 ±400

(1793 ±182)

2.75

(6.99 cm)

NOTES:

(1) Conduct all tests at 70 ±2° F except as noted.

(2) Cold−soak winterized dampers at 0 ±3° F for 24 hours minimum before testing.

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CSP-HMI-2

MAINTENANCE MANUAL

LANDING GEAR SYSTEM

REPAIRS

1. Landing Gear System Repairs

NOTE: Following applies to early configuration

landing gear skids. Installation differences

(Ref. Figure 801) For more extensive repairs,

for current configuration landing gear skids

refer to CSP-SRM-6.

are noted in Figure 801.

(1).

Repair scratches and nicks by smooth

(1). Remove abrasion strip. Drill out rivets

ing sharp edges.

securing adapter sleeve and remove

residue from end of tube.

(2).

Repair elongated, enlarged or worn

holes in strut fittings, either inboard or

(2). Coat mating surface of replacement

outboard.

sleeve with a thin coat of sealing

compound (CM425) and install in skid

(3).

Repair bolt holes at large end of brace

tube with 9.06 inch (23.012 cm) over

that attaches to strut.

hang (Ref. Figure 801).

(4).

Replace strut; if cracked, if dents in

(3). Drill holes for replacement rivets and

strut exceed 0.060 inch (1.524 mm)

abrasion strip attachment bolt.

depth or if scratched and repaired area

depth would exceed 0.010 inch (0.254

(4). Coat replacement rivets with primer

mm) when measured to surrounding

(CM318) and install while wet; Main

unrepaired surface.

tain 9.06 inch (23.012 cm) overhang

during installation.

(5).

Replace defective or badly damaged

(5). Install replacement plug in sleeve 4

fairing.

inches (10.16 cm) inside skid from aft

(6).

Repair fairing fiberglass damage, such

end). Secure in place with bead of

as small tears or punctures that do not

sealant.

impair the telescoping action of the

(6). Install aft abrasion strip.

fairing.

3. Abrasion Strip Replacement

(7).

Replace cracked, dented or distorted

braces.

(Ref. Figure 801)

(8).

Repair or replace damaged skid tube.

Consumable Materials

(9).

Replace center beam-to-landing-gear

(Ref. Section 91−00−00)

attachment bearings that exceed 0.040

Item

Nomenclature

inch (1.016 mm) axial play.

CM209

Zinc chromate putty

(10).

Repair loose or defective rivets securing

CM318

Primer

foot to bearing; replace defective

CM425

Sealing compound

bearing.

2. Skid Adapter Sleeve Replacement

(1). Remove bolts securing defective

abrasion strip(s) to skid.

(Ref. Figure 801)

(2). Remove screws securing abrasion strip

to skid extension sleeve. Completely

Consumable Materials

remove any residual zinc chromate

(Ref. Section 91−00−00)

putty.

Item

Nomenclature

(3). Apply putty (CM209) to any bare metal.

CM318

Primer

CM425

Sealing compound

(4). Coat new screws or bolts for replace

ment abrasion strip with primer

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MD Helicopters, Inc.

MAINTENANCE MANUAL

(CM318) and install while primer is

edges of abrasion strip next to skid tube

still wet.

with an approximate 0.060 inch (1.524

mm) bead (fillet) of sealing compound

(5). After installation, seal all of parting

(CM425) to make watertight.

Table 801. Maximum Damage Limits − Landing Gear Components

Dents

Nicks

Scratches

Cracks

Holes

Component

in / mm

Skid tube (2)

0.200 / 5.08

0.010 / 0.254, from aft side of

(Same as for

No cracks

0.250 / 6.350

(1)

aft strut to 10 inches (25.4 cm)

nicks) (1)

allowed

(1) (3)

forward of the strut, with

cleanup not exceeding 0.015 /

0.381; 0.015 / 0.381 if forward

of that point to start of curved

section, with cleanup not

exceeding 0.020 / 0.508 (1)

Forward foot

0.060 / 1.524

0.010 / 0.254

No cracks

No holes

allowed

Strut

0.060 / 1.524

(1)

No cracks

No holes

allowed

Brace

0.050 / 1.270

0.010 / 0.254

0.005 / 0.127

No cracks

No holes

allowed

Damper assembly

0.060 / 1.524

0.010 / 0.254

No cracks

No holes

allowed

Fittings

0.010 / 0.254

No cracks

No holes

allowed

Aft foot

0.060 / 1.524

0.010 / 0.254

No cracks

No holes

allowed

Foot bearing

0.010 / 0.254

No cracks

No Holes

allowed

Indexing plug

0.040 / 1.016

No cracks

No holes

allowed

Skid extension

0.010 / 0.254

0.010 / 0.254 (4)

0.010 / 0.254

No cracks

No holes

(4)

allowed

NOTES:

(1) For other repair data, refer to CSP−SRM−6.

(2) Repair of minor skid tube damage aft of rear strut and on forward (curved) section is not required, but

surface finish must be restored.

(3) Hole must be plugged with correct size blind rivet.

(4) No damage is allowed on skid extension where skid and sleeve are attached.

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CSP-HMI-2

MAINTENANCE MANUAL

BONDING JUMPER

CENTER BEAM

DAMPER

CLAMP

FAIRING BRACKET

(8 PLCS)

STRUT

BOLT

NUT

DAMPER

ABRASION STRIP

BOLT

RIVET

FOOT

(TYP)

GROUND HANDLING

SPACER

FITTINGS

BRACE

STRUT

CABIN ENTRY

SAFETY WALK

ABRASION STRIP

STEP

TAPE

BOLT

NONSKID TAPE

NUT

SKID TUBE

FOOT

BOLT AND WASHER

NUTPLATE

BOLT

(4 PLCS) (NOTE 1)

SKID POSITION

RIVNUT

LIGHT

ABRASION STRIP

WASHER

NUT

NUTPLATE

FOOT

RIVNUT

STEP

BOLT

FORWARD

ABRASION STRIP

RIVNUT

NUTPLATE

FOOT

FITTING

SCREW

RIVET

RIVNUT

(TYP)

LOCKWASHER

BRACKET

RIVET

EARLY

CURRENT

NUTPLATE

CONFIGURATION

NUTPLATE/RIVNUT ATTACHMENT

EXTENDED

FOR ABRASION STRIP MOUNTING

LANDING GEAR

G32-1002-1A

Figure 801. Landing Gear Repairs (Sheet 1 of 2)

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MD Helicopters, Inc.

MAINTENANCE MANUAL

RIVET

SPACER

BOLT

FOOT

WASHER

SPACER

FOOT

RIVET

SCREW

EARLY

CURRENT

CONFIGURATION

PIN RIVET

RIVETS (UPPER BRACKET)

HUCKBOLTS (LOWER BRACKET)

(NOTES 3 AND 6)

PACKING

FAIRING

(NOTES 5 AND 6)

BRACKET

SKID EXTENSION

SLEEVE

FOOT

BOLT

SKID ADAPTER

INDEXING

SLEEVE

PLUG

COLLAR

RIVET

ABRASION

DOUBLER

STRIP

SCREW

FORWARD FAIRING

PLUG

ATTACHMENT

BEARING

EARLY CONFIGURATION

SKID

COLLAR

PLUG

FOOT

NUT

WASHER

SKID ADAPTER

SLEEVE

BEARING

RIVET

SPACER

NOTES:

SKID

BOLT AND WASHER 4 PLACES. 8 PLACES ON

EXTENSION

EARLY CONFIGURATION.

SLEEVE

BOLT

HUCKBOLT 4 PLACES. 8 PLACES ON EARLY

CONFIGURATION.

INSTALL NEW RIVETS WITH WET PRIMER

CURRENT CONFIGURATION

SKID

SCREW

(CM318).

3/16 INCH (4.7625 MM) WELDING ROD OR

SKID TUBE ADAPTER AND PIVOT COMPONENTS

OTHER SUITABLE DEVICE (4 PLACES).

FORWARD FAIRING ONLY.

HUCKBOLT HEAD COUNTERSUNK INSIDE

Figure 801. Landing Gear Repairs (Sheet 2 of 2)

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CSP-HMI-2

MAINTENANCE MANUAL

4. Ground Handling Fitting Replacement

fiberglass repair limits, the fillet and fairing

must be removed.

(Ref. Figure 801)

Consumable Materials

(Ref. Section 91−00−00)

Item

Nomenclature

Item

Nomenclature

CM418

Cement, epoxy

CM209

Zinc chromate putty

CM318

Primer

(1).

Replace an excessively damaged lower

CM425

Sealing compound

fairing.

(2).

Replace damaged fairing bracket or

(1). Drill out rivets securing defective

lower guide. Remove rivets, locate new

fitting.

part and install blind rivets. Use next

larger size rivets if mating holes in

(2). Coat mating surfaces with zinc chro

strut are enlarged.

mate putty (CM209) and install

replacement fitting in place.

(3).

Replace damaged guide/pin assembly or

guide half if guide is cracked, pins are

(3). Coat new rivets with primer (CM318)

bent or badly worn or teflon pad is loose

and install while primer is wet.

or badly worn.

(4). Seal edges with an approximate 0.060

(4).

Replace springs that are badly worn or

(1.524 mm) inch bead of sealing

rusty, or if free length is less than 8.72

compound (CM425) for waterproofing.

inches.

5. Safety Walk Tape Replacement

(5).

Replace fillet if teflon strip is loose or

badly worn.

(Ref. Figure 801)

(6).

Replace damaged strut bracket.

Remove rivets, locate new part and

Consumable Materials

install blind rivets. Use next larger size

(Ref. Section 91−00−00)

rivets if mating holes in strut are

Item

Nomenclature

enlarged.

CM220

Naphtha aliphatic

(7).

Replace unserviceable rubber seals; use

CM724

Tape, non-slip

cement (CM418).

7. Landing Gear Fairing Fillet Modification

(1). Carefully pull or scrape away damaged

tape.

The following is a procedure for modifying the

landing gear fairing fillet for easy removal and

(2). Remove all residual adhesive from skid

better access to the landing gear struts.

tube by wiping with a clean cloth

wetted by naphtha (CM220).

(1). Remove fillet from upper part of fairing

assembly (Ref. Landing Gear Fairing

(3). Install new tape (CM724) and press

Removal).

firmly into place. Expel air bubbles

while pressing down tape.

(2). Enlarge existing holes in fairing fillets

and fillet guides to 0.220 - 0.230 inch

6. Landing Gear Fairing Repair

(5.588 - 5.842 mm).

(Ref. Figure 802) Repair fairings according to

(3). Install A1133-4-3 Nut-Clips on fillet

SRM. If upper fairing is damaged beyond

guides over enlarged holes.

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MAINTENANCE MANUAL

(4). Reinstall fillets using NAS603-6P

(b). If no cracks are noted, install new

screws and AN960KD10L washers

369H6023-3 bushing in hole with

through fillet into fairing guides.

wet primer.

(5). Secure trailing edge of fillet using

B. Landing Gear Strut with No Bushing

NAS603-6P screws, AN960KD10L

Installed

washers and MS21042-3 nuts (washer

under screw head and nut).

(1). Ream out top hole (DIM. A) to

0.5308-0.5313 inch (13.482-13.495

(6). Finish reinstalling fillet (Ref. Landing

mm) and ream out bottom hole (DIM.

Gear Fairing Installation).

B) to 0.4995-0.50 inch (12.687-12.70

mm).

8. Landing Gear Strut Drag Brace Hole

Repair

(2). Perform fluorescent penetrant inspec

tion of reworked areas for cracks.

(Ref. Figure 601) The following procedure is for

repair of the bolt hole in the landing gear strut

(a). If any cracks are noted, rework strut

where the drag brace attaches. This rework is

per step (3).

for either elongated or cracks in the bolt hole

area (Ref. Landing Gear Strut Inspection).

(b). If no cracks are noted, install new

369H6002-11 bushing in hole with

Consumable Materials

wet primer (CM318).

(Ref. Section 91−00−00)

(3). Ream out top hole (DIM. A) to

Item

Nomenclature

0.5608-0.5613 inch (12.244-14.257

CM318

Primer

mm) and ream out bottom hole (DIM.

B) to 0.5295-0.530 inch (13.449-13.462

A. Landing Gear Strut with Bushing

mm).

Installed

(4). Perform fluorescent penetrant inspec

(1). Ream out top hole (DIM. A) to

tion of reworked areas for cracks.

0.5608-0.5613 inch (12.244-14.257

mm) and ream out bottom hole (DIM.

(a). If any cracks are noted, procede with

B) to 0.5295-0.530 inch (13.449-13.462

step (5).

mm).

(b). If no cracks are found around drag

(2). Perform fluorescent penetrant inspec

brace attach hole in strut and hole is

tion of reworked areas for cracks.

not elongated, install new

369H6023-1 bushing in hole with

(a). If any cracks are noted, rework strut

wet primer (CM318).

per step (3).

(5). Ream out top hole (DIM. A) to

(b). If no cracks are noted, install new

0.5908-0.5913 inch (15.006-15.019

369H6023-1 bushing in hole with

mm) and ream out bottom hole (DIM.

wet primer (CM318).

B) to 0.5595-0.560 inch (14.211-14.224

(3). Ream out top hole (DIM. A) to

mm).

0.5908-0.5913 inch (15.006-15.019

(6). Perform fluorescent penetrant inspec

mm) and ream out bottom hole (DIM.

tion of reworked areas for cracks.

B) to 0.5595-0.560 inch (14.211-14.224

mm).

(7). If crack is found, strut must be

(4). Perform fluorescent penetrant inspec

scrapped and serviceable strut

tion of reworked areas for cracks.

installed.

(a). If crack is found, strut must be

(8). If no cracks are noted, install new

scrapped and serviceable strut

369H6023-3 bushing in hole with wet

installed.

primer.

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CSP-HMI-2

MAINTENANCE MANUAL

CHAFING PAD

TEFLON STRIP

FILLET

(NOTE 3)

RIVETS

RETAINING BLOCKS

AND CLAMP

NOTE 4

0.35 INCH (8.89 MM)

TEFLON PAD

FAIRING TO LOWER GUIDE

UPPER

(INSIDE GUIDES)

0.80 INCH (20.32 MM)

(NOTE 1)

FAIRING

UPPER FAIRING

UPPER GUIDE

(NOTE 3)

PIN ASSEMBLY,

0.35 INCH (8.89 MM)

LOWER FAIRING

INNER GUIDE HALF

RIVET

AND SPRINGS

(FWD FAIRING, 1 RIVET)

OUTER GUIDE HALF

(AFT FAIRING, 2 RIVETS)

UPPER AND LOWER FAIRING

1-7/16 INCH (3.65 CM)

RIVETS

INSTALLATION

DOUBLER (TYP)

(NOTE 2)

LOWER FAIRING

LOWER GUIDE

(NOTE 3)

RIVETS (UPPER BRACKET)

(NOTE 1)

HUCKBOLTS (LOWER BRACKET)

(NOTES 2 AND 8)

3/4 INCH (19.05 MM)

RIVET

DOUBLER (TYP)

(2 PLCS)

SCREW, WASHER

HOLE

(4 PLACES)

AND SEAL

(NOTES 6, 7)

1/2 X 3/4 INCH

FAIRING

DOUBLER

BRACKET

(TYP)

FORWARD FAIRING

SKID

ATTACHMENT

SKID C

COVER (EXTENDED

LANDING GEAR ONLY)

NUTPLATE

NOTES:

(9 PLCS)

BONDED AREA; USE EPOXY ADHESIVE (CM411).

INSTALL NEW RIVETS WITH WET PRIMER (CM318).

REFER TO CSP-SRM-6 FOR FIBERGLASS REPAIR.

CLAMP FILLET AND FAIRING TRAILING EDGES DURING INSTALLATION

OF FILLET RIVETS.

PENCILED CENTERLINE ALONG FLANGE.

3/16 INCH (4.7625 MM) WELDED ROD OR OTHER SUITABLE DEVICE.

WASHER

FORWARD FAIRING ONLY.

(9 PLCS)

HUCKBOLT HEAD COUNTERSUNK INSIDE STRUT; NO PORTION OF HEAD

RIVET

(18 PLCS)

TO PROTRUDE INSIDE STRUT.

SCREW

DIMENSIONS FOR BRACKET AND GUIDE LOCATIONS ON NEW STRUT

(9 PLCS)

G32-1003A

INSTALLATION

Figure 802. Landing Gear Fairing Repairs

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CSP-HMI-2

MAINTENANCE MANUAL

EXTENDED LANDING GEAR

INITIAL INSTALLATION

1. Extended Landing Gear Initial Installation

for reuse. Remove skid assemblies with

foot assemblies attached.

The following instructions are for both left and

B. Standard Landing Gear Disassembly

right landing gear assemblies.

Complete disassembly of landing gear is not

(1). Identify all components, including

required; however, certain items must be

attaching hardware, or components

removed.

removed for access to work area.

Protect components from damage and

(1). On current configuration standard

foreign matter until installed.

landing gear, disassemble as follows:

(a). Remove bolt, washer and nut attach

(2). Ensure all cockpit electrical switches

ing aft foot assembly and skid

are OFF.

extension to skid tubes.

NOTE: Ensure BATT-OFF-EXT switch is

(b). Remove bolts and washers attaching

OFF.

forward foot assembly to skid tubes.

(3). Using jacking or hoisting methods,

(2). On early configuration standard

raise helicopter clear of ground.

landing gear, disassemble as follows:

(a). Remove screws and abrasion strip at

A. Standard Landing Gear Removal

aft section of skid tubes.

Removal of complete landing gear is not

(b). Remove bolts attaching skid exten

required.

sion, indexing plug and aft foot

assembly to skid tube.

(1). Open engine access doors.

(c). Remove bolts and washers attaching

(2). Remove hardware attaching aft damper

forward foot assembly to skid tube.

assemblies to fuselage fittings and

C. Extended Landing Gear Assembly

landing gear struts; remove aft damper

assemblies. Retain attaching hardware

Extended landing gear is shipped with as

for reuse.

many parts assembled as practical; however,

certain items require assembly at installation.

(3). Remove screws attaching position light

assemblies to skid assembles. Retain

Early configuration forward foot assembly and

screws for reuse. Disconnect electrical

skid tube have an eight-hole mounting

harness and remove position light

pattern; current configuration foot assembly

assemblies.

and skid tube have a four-bolt mounting

pattern.

(4). Remove hardware that secures trailing

edge of forward and aft lower fairings.

Consumable Materials

Remove hardware attaching lower

(Ref. Section 91−00−00)

fairings to strut assemblies. Carefully

Item

Nomenclature

spread trailing edge of lower fairings

CM318

Primer

and remove in forward direction.

CM425

Sealing compound

NOTE: If preload condition prevents removal of

skid assemblies, disconnect forward foot as

(1). If early foot assembly is used with

semblies from skid assemblies to eliminate

current skid tube:

preload.

(a). Drill out four rivets (48, Figure 902)

(5). Remove ABC bolts from forward and aft

and remove two spacers (49) from

strut assemblies. Retain ABC hardware

skid tube.

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MAINTENANCE MANUAL

Legend (Ref. Figure 901)

Bolt (MS21250−04006)

30.

Doubler (369D26031)

Washer (MS20002C4)

31.

Bearing (369D26030−1 LH)

Foot assy (369D292113−1 LH FWD)

(369D26030−2 RH)

(369D292113−2 RH FWD)

32.

Foot (369D29113−3 LH AFT)

Screw (NAS1403−1)

(369D29113−4 RH AFT)

Lockwasher (MS35338−43)

33.

Skid assy (369D292114)

Bracket (369H92111−11)

34.

Bolt (NAS1223C1)

Rivet (NAS1921M04−03)

35.

Washer (HS306−222)

Nutplate (369H92507)

36.

Abrasion strip (369H92583)

Rivet (CCR26455−3−5)

37.

Abrasion strip (369H6102)

10.

Nutplate (NAS1068A3)

38.

Tape (369D292114−3)

11.

Foot (369D29113−3 LH FWD)

39.

Tube assy (369D292114−5)

(369D29113−4 RH FWD)

40.

Screw (NAS1190C3P3)

12.

Bolt (NAS1223C1)

41.

Rivet (NAS1921M04−03)

13.

Washer (HS306−222)

42.

Nutplate (369H92507)

14.

Abrasion strip (369H6102)

43.

Rivet (NAS1919M04−03)

15.

Screw (NAS56HK3−6)

44.

Fitting (369A6107−3)

16.

Bolt (NAS1223C8P)

45.

Rivet (NAS1399D4−4)

17.

Extension assy (369D26038)

46.

Spacer (369A6100−7)

18.

Index plug (369D26037)

47.

Spacer (369A6100−5)

19.

Foot assy (369D292111−101 LH AFT)

48.

Rivet (NAS1399C5−3)

(369D292111−102 RH AFT)

49.

Rivet (NAS1399C5−2)

20.

Screw (NAS1403−1)

50.

Rivet (NAS1398C5−3)

21.

Lockwasher (MS35338−43)

51.

Rivet (NAS1398C5−2)

22.

Bracket (369H92111−11)

52.

Plug (369D26040)

23.

Rivet (ML5100M4−3)

53.

Adapter sleeve (369D26032)

24.

Nutplate (369H92507)

54.

Tube (369D292115)

25.

Rivet (MS20605AD3C3)

55.

Nut (MS21045−5)

26.

Nutplate (NAS1068A3)

56.

Washer (AN960KD513)

27.

Pin rivet (HL3375K8A6)

57.

Bolt (NAS1305−36)

28.

Packing (H53113E142)

58.

Step assy (369D292028)

29.

Rivet (MS20426AD4)

59.

Screw (1030−428−8M)

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

Legend (Ref. Figure 902)

Bolt (MS2125004006)

30.

Nutplate (NAS1068A3)

Washer (MS20002C4)

31.

Pin rivet (HL3375K8A6)

Foot assy. (369D292113−103 LH FWD)

32.

Pin rivet (HL3375K8A6)

(369D292113−104 RH FWD)

33.

Bearing (369D26010−1 LH)

(369D292113−101 LH FWD)

(369D26010−2 RH)

(369D292113−102 RH FWD)

34.

Foot (369D292113−5 LH AFT)

Screw (NAS1403−1)

(369D292113−6 RH AFT)

Screw (NAS1403−5)

35.

Skid assy (369D292114−101/−103)

Lockwasher (MS35338−43)

36.

Bolt (NAS1223C1 (−101 assy))

Bracket (369H92111−11)

(NAS1223C4 (−103 assy))

Rivet (NAS1921M04−03)

37.

Washer (HS306−222)

Nutplate (369H92507)

38.

Abrasion strip (369H92583)

10.

Rivnut (NAS1329C3KB180)

39.

Tape (369D292114−3)

11.

Rivnut (CCR26455−3−5)

40.

Tube assy (369D292114−7/−9)

12.

Nutplate (NAS1068A3)

41.

Screw (NAS1190C3P3 (−101 assy))

13.

Foot (369D292113−5 LH FWD)

(NAS1130C3P8 (−103 assy))

(369D292113−6 RH FWD)

42.

Rivet (NAS1921M04−03)

14.

Bolt (NAS1223C1 (−101 assy))

43.

Nutplate (369H92507)

(NAS1223C5 (−103 assy))

44.

Rivnut (C2R1947−1)

15.

Washer (HS306−222)

45.

Rivnut (C2R1947−2)

16.

Bolt (NAS1104−44)

46.

Rivet (NAS1919M04−03)

17.

Spacer (369D26013)

47.

Fitting (369A6107−3)

18.

Nut (NAS21042−4)

48.

Rivet (NAS1399D4−4)

19.

Abrasion strip (369H6102)

49.

Spacer (369D26014)

20.

Extension assy (369D26045)

50.

Spacer (369D26015)

21.

Foot assy (369D292111−105 LH AFT)

51.

Rivet (NAS1399C5−3)

(369D292111−106 RH AFT)

52.

Rivet (NAS1399C5−2)

(369D292111−103 LH AFT)

53.

Rivet (NAS1398C5−3)

(369D292111−104 RH AFT)

54.

Rivet (NAS1398C5−2)

22.

Screw (NAS1403−1)

55.

Plug (369D26040)

23.

Screw (NAS1403−5)

56.

Adapter sleeve (369D26012)

24.

Lockwasher (MS35338−43)

57.

Tube (369D292115)

25.

Bracket (369H92111−11)

58.

Nut (MS21045−5)

26.

Rivet (ML5100−M4−3)

59.

Washer (AN960KD516)

27.

Nutplate (369H92507)

60.

Bolt (NAS1305−36)

28.

Rivnut (NAS1329C3KB180)

61.

Step (369D292028)

29.

Rivet (MS20605AD3C3)

62.

Screw (1030−428−8M)

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Revision 19

CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

(b). Apply primer (CM318) to replace

(b). Coat screw (15) and bolts (16) with

ment spacers (47, Figure 901) and

primer and install.

install into skid tube with four

(3). Coat mating surface of abrasion strip

NAS1399D4-4 rivets.

and hardware with primer.

(c). Position foot assembly on skid tube

(a). Position abrasion strip (14) on aft

and locate center four holes.

section of skid tube.

(d). Mark holes and drill the needed

(b). Install abrasion strip using bolts (12)

0.254 - 0.260 inch (6.452 - 6.604

and washers (13).

mm) holes as required.

(c). Seal mating edge of abrasion strip

(2). If current foot assembly is used with

with 0.060 inch (1.524 mm) bead of

early skid tube:

sealing compound (CM425).

(a). Fill center four holes with sealing

E. Current Configuration Extended Landing

compound (CM425).

Gear Skid Tube Assembly Buildup

(Ref. Figure 903)

(3). Attach extended wire harness to

position light and install light in

forward end of skid tube (Ref.

Consumable Materials

Figure 903) using screws retained from

(Ref. Section 91−00−00)

standard landing gear.

Item

Nomenclature

CM318

Primer

D. Early Configuration Extended Landing

CM425

Sealing compound

Gear Assembly Buildup

(Ref. Figure 901)

(1). Coat mating surface of forward foot

assembly (3) and skid tube (57) with

Consumable Materials

primer (CM318).

(Ref. Section 91−00−00)

(a). Position forward foot assembly on

Item

Nomenclature

skid tube.

CM318

Primer

(b). Apply primer to bolts (1) and washers

CM425

Sealing compound

(2) and install; torque bolts to 80 -

100 inch-pounds (9.04 - 11.30

(1). Coat mating surface of forward foot

Nm).

assembly (3) and skid tube (54) with

(2). Coat mating surfaces of aft foot assem

primer (CM318).

bly (21) and extension (20) with primer.

Position extension and aft foot assem

(a). Position forward foot assembly on

bly on adapter sleeve (56).

skid tube.

(3). Coat mating surface of abrasion strip

(b). Apply primer to bolts (1) and washers

(19) and hardware with primer and

(2) and install; torque bolts to 80 -

position on extension (20).

100 inch-pounds (9.04 - 11.30

Nm).

(a). Install aft foot assembly (21), exten

sion (20) and abrasion strip (19)

(2). Coat mating surfaces of extension (17),

using bolts (14 and 16), washers (15),

indexing plug (18) and aft foot assembly

spacer (17) and nut (18).

(32) with primer.

(b). Seal mating edge of abrasion strip

(a). Position indexing plug, aft foot

with 0.060 inch (1.524 mm) bead of

assembly and extension on skid tube.

sealing compound (CM425).

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

F. Extended Landing Gear Installation

(6). Route extended wire harness from

position light through forward foot

(Ref. Figure 901)

assembly.

(a). Attach wire with splice (CM812);

Consumable Materials

cover splice with silicon tube

(Ref. Section 91−00−00)

(CM612) and tie tube with strap

Item

Nomenclature

(CM703).

CM318

Primer

CM420

Sealant

(b). Cover entire length of extended

CM612

Tube, silicone

electrical harness with vinyl sleeve

(CM613).

CM613

Sleeve, vinyl

CM703

Tie strap

(7). Install extended landing gear aft

CM812

Splice, knife

damper assemblies using serviceable

N/A

Wire, AWG 20, 47108-B-20

hardware removed from standard

landing gear (Ref. Landing Gear

Damper Replacement).

(1). Align foot and skid assembly with strut

assembly.

(8). Apply 0.060 inch (1.524 mm) bead of

sealant (CM420) to mating edge of foot

(2). Slide foot assembly into strut assembly.

assemblies and strut assemblies.

(3). Coat ABC bolts with primer (CM318).

(9). Install fairings (Ref. Landing Gear

(4). While primer is wet, install ABC bolts;

Fairing Replacement).

torque bolts to 40 - 60 inch-pounds

G. Weight and Balance

(4.52 - 6.78 Nm).

Weight and balance changes that result from

(5). Seal ABC bolts with sealant (CM420).

installation of extended landing gear are listed

NOTE: Leave a minimum of one full service

in Table 901. After installation of extended

loop in electrical harness to ensure that ten

landing gear, incorporate changes to helicopter

sion is not applied to position lights, if

weight and balance record as instructed in

installed.

Section 08-10-00.

Table 901. Weight and Balance Data

Weight

Arm

Moment

lbs (kg)

in.

(cm)

in.−lb/100 (kg mm/100)

Added

+94

(+42.638)

92.3

(234.44)

+86.8

(+10000.04)

Removed

−73

(−33.112)

97.0

(246.38)

−70.8

(−815.70)

Change

+21

(+9.525)

76.0

(193.04)

+16.0

(+184.34)

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

LANDING GEAR SYSTEM

DESCRIPTION AND OPERATION

1. Landing Gear System

structure. Aft damper assemblies are attached

to oleo support fittings in the engine compart

The landing gear consists of two strut-

ment.

mounted, shock-dampened skids aligned

longitudinally along the helicopter fuselage.

The damper assemblies are approximately

Both right and left skids pivot as the damper

12.19 (31 cm) inches long when extended and

assemblies extend and retract. Replaceable

8.94 (22.7 cm) inches long when compressed.

abrasion strips are installed on each skid to

The dampers are nozzle-type and consist of a

retard wear on hard surfaces.

barrel, upper and lower mounting cap and a

piston.

A. Skid

Damper exterior surfaces are painted white for

Landing gear skids provide helicopter rest

the standard gear and black for the extended

mounts. Skid tubes are constructed from

gear as an aid to identification and for surface

seamless, extruded aluminum alloy tubing.

protection.

Abrasion strips attached to undersides of skid

tubes retard wear and damage. Ground

A damper must be replaced if damaged, or if

handling bolts, bolted through the skid tubes,

loss of hydraulic oil occurs.

are the ground handling attach points. An

D. Entry Step

adapter sleeve at the aft end of skid tube

provides a nonrigid mount for the aft foot

Entry steps mounted on the forward landing

bearing and skid extension.

gear struts allow for easy access into the cabin.

The landing gear step is covered with non-skid

B. Strut

tape and attached to the landing gear strut

The landing gear struts attach to the fuselage

with rivets.

center beam. Landing gear braces between the

E. Fairing

landing gear strut and fuselage center beam

prevent shearing of the strut and keep the

Aluminum fairings on each strut reduce

strut in alignment with the landing gear. At

aerodynamic drag during flight. The fairings

the lower ends of the struts, foot-shaped

extend from the fuselage to the skids to form

components attach the landing gear skids to

streamlined enclosures for the landing gear

the struts. Feet for the aft strut are bearing-

struts. Each fairing assembly is constructed of

mounted to provide a nonrigid and pivotal

three main parts: a fillet, an mid and lower

mount.

fairing. The fillet is spring-loaded to remain in

firm contact with a plastic rubbing plate that

C. Damper

is bonded and riveted to the fuselage. The

Landing gear assemblies are equipped with

fairing is secured to the landing gear and

front and rear damper assemblies. Dampers

telescopes up inside the fillet to allow move

absorb vertical shock to landing gear struts

ment of the strut as the landing gear dampers

during helicopter landings and help prevent

compress or extend. A seal on the bottom edge

ground resonance. Front damper assemblies

of the fairing forms a fillet between the fairing

are attached to oleo attachment fittings on the

and the skid tube. Forward fairings also have

outboard side of the pilot's compartment seat

openings for cabin entry steps.

Page 1

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

LANDING GEAR SYSTEM

SERVICING

1. Landing Gear Damper Nitrogen Servicing

servicing hose-schrader valve connec

tion.

(Ref. Figure 301) Service landing gear damp

ers equipped with schrader valve according to

(6). While the nitrogen is still flowing,

the following steps.

tighten servicing hose. Allow nitrogen

pressure to build to the value according

Do not recharge a damper if

to part and dash number of damper

CAUTION

there is evidence of fluid leak

(Ref. Table 301).

age. Recharging of damper will cause fur

To prevent damage to damper or

ther leakage of both gas and damper fluid,

CAUTION

loss of damper fluid do not open

posing a danger to the helicopter.

schrader valve without pressurizing the

(1). Place helicopter on jacks or hoist and

servicing line. If fluid loss occurs, damper

will require overhaul.

elevate until dampers are fully ex

tended..

(7). Once pressure level is reached, open

schrader valve by turning outside nut

(2). For forward damper servicing, remove

counter clockwise. Allow system and

foot support fairings located in passen

damper pressure to equalize for a

ger compartment. For aft damper

minimum of 2 minutes. If slightly over

servicing, open engine access doors.

pressurized, bleed off excess very

slowly.

(3). Remove cap from schrader valve and

connect servicing hose, but do not

(8). Close schrader valve by turning the

tighten.

outside nut clockwise. Torque nut to 50

- 60 inch pounds (5.65 - 6.78 Nm).

(4). Ensure low side of nitrogen pressure

Remove servicing hose and install valve

regulator is backed off to the unpres

cap finger-tight.

surized position. Slowly open the high

pressure nitrogen bottle valve.

(9). Remove aircraft from jacks or hoist.

(5). Slowly turn regulator control until

(10). Inspect damper for leakage approxi

nitrogen begins to flow at the loose

mately two hours after servicing.

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CSP-HMI-2

MAINTENANCE MANUAL

Table 301. Nitrogen Recharge Pressure

Ambient Temperature

600N6050−33

600N6050−31

° F (° C)

Psig (kPa)

−40 (−40)

263 (1813)

151 (1041)

−35 (−37)

268 (1848)

153 (1055)

−30 (−34)

272 (1875)

156 (1076)

−25 (−32)

277 (1910)

158 (1089)

−20 (−29)

281 (1937)

161 (1110)

−15 (−26)

286 (1972)

163 (1124)

−10 (−23)

291 (2006)

166 (1145)

−5 (−21)

295 (2034)

169 (1165)

0 (−18)

300 (2068)

171 (1179)

5 (−15)

305 (2103)

174 (1200)

10 (−12)

310 (2137)

177 (1220)

15 (−9)

315 (2172)

179 (1234)

20 (−7)

320 (2206)

182 (1255)

25 (−4)

325 (2241)

185 (1276)

30 (−1)

330 (2275)

188 (1296)

35 (2)

335 (2310)

191 (1317)

40 (4)

340 (2344)

194 (1338)

45 (7)

345 (2379)

197 (1358)

50 (10)

351 (2420)

199 (1372)

55 (13)

356 (2455)

202 (1393)

60 (16)

361 (2489)

205 (1413)

65 (18)

367 (2530)

208 (1434)

70 (21)

372 (2565)

211 (1455)

75 (24)

378 (2606)

215 (1482)

80 (27)

383 (2641)

218 (1503)

85 (29)

389 (2682)

221 (1524)

90 (32)

395 (2723)

224 (1544)

95 (35)

400 (2758)

227 (1565)

100 (38)

406 (2799)

230 (1586)

105 (41)

412 (2841)

234 (1613)

110 (43)

418 (2882)

237 (1634)

115 (46)

424 (2923)

240 (1655)

120 (49)

430 (2965)

244 (1682)

125 (52)

436 (3006)

247 (1703)

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CSP-HMI-2

MAINTENANCE MANUAL

LANDING GEAR SYSTEM

REMOVAL/INSTALLATION

1. Landing Gear Strut Replacement

(10). Gently work strut around bearing in

fuselage support fitting and remove.

(Ref. Figure 401)

B. Landing Gear Strut Installation

Consumable Materials

(1). For access to forward brace, strut and

(Ref. Section 91−00−00)

damper, open compartment access

Item

Nomenclature

doors.

CM318

Primer

(2). For access to aft landing gear attach

CM729

Tape, masking, pressure sensitive

ment points, open engine access doors.

NOTE: New bushings must be installed when

A. Landing Gear Strut Removal

installing struts. Torquing of the bolt will

press bushing into place.

NOTE: For component disassembly, refer to

(3). Gently work struts around bearings in

applicable section. For removal, two persons

fuselage support fittings.

are needed.

(4). Install attaching hardware with new

(1). Jack up or hoist helicopter until skid

bushing coated with wet primer

assemblies clear surface by 10 - 20

(CM318).

inches (25 - 50 cm) (Ref. Sec.

07-00-00).

(5). Torque nut to 85 - 110 inch-pounds

(9.60 - 12.43 Nm) plus drag torque

(2). Remove skid assemblies (Ref. Landing

and install cotter pin.

Gear Skid Replacement).

(6). Check for minimum 0.010 inch (0.254

(3). Pull strut fairing fillet downward

mm) gap between washer and airframe

against spring tension and secure with

clevis at slotted bushing.

tape (CM729).

NOTE: Install forward damper upper bolts

NOTE: Bushings must be removed from strut

with bolt heads facing aft. Install all other

to enable strut to clear bearing in fuselage

damper bolts with bolt head facing forward.

support fittings.

(7). Install damper (Ref. Landing Gear

(4). For access to forward brace, strut and

Damper Replacement).

damper, open compartment access

(8). Align inboard end of each brace with

doors.

mating bearing in fuselage supporting

fitting and install attaching hardware.

(5). For access to aft landing gear attach

ment points, open engine access doors.

(9). Torque nut to 60 - 85 inch-pounds

(6.78 - 9.60 Nm) plus drag torque

(6). Disconnect brace and damper from

and install cotter pin.

strut.

(10). Check for minimum 0.010 inch (0.254

(7). Remove hardware from strut pivot

mm) gap between washer and airframe

point.

clevis at slotted bushing.

(8). Use an ezy-out to pull both bushings

(11). Secure electrical bonding jumpers to

from strut clevis at pivot point.

airframe.

(9). Remove electrical bonding jumper

(12). Align outboard end of each brace with

attaching aft strut to airframe.

mating holes in strut.

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MAINTENANCE MANUAL

Do not over-tighten brace-to-

(2). Install replacement damper in upper

CAUTION

strut hardware.

and lower mounting position with

attaching hardware. Ensure bushings

(13). Attach brace to strut with attaching

are in place.

hardware.

(14). Torque nut to 2 - 10 inch-pounds

NOTE: Install forward damper upper bolts

(0.226 - 1.13 Nm) plus drag torque

with bolt heads facing aft. Install all other

and install cotter pin.

damper bolts with bolt head facing forward.

(15). Reinstall skid assemblies (Ref. Landing

Gear Skid Replacement).

(3).

Align forward upper damper bearing

with airframe and install attaching

(16). Remove skid supports, lower helicopter,

hardware.

and remove jacks.

(17). Close or replace all access doors.

(4).

Torque nuts to 60 - 85 inch-pounds

(6.78 - 9.60 Nm) plus drag torque

and install cotter pin.

2. Landing Gear Damper Replacement

(Ref. Figure 401)

(5).

Check for minimum 0.010 inch (0.254

mm) gap between washer and airframe

A. Landing Gear Damper Removal

clevis at slotted bushing.

(1). Jack up or hoist helicopter on level

surface until landing gear skids just

(6).

Align aft upper damper bearing with

clear resting surface.

airframe and install attaching hard

ware.

(2). For forward damper removal, remove

footwell fairings located in passenger

compartment. For access for aft damper

(7).

Torque nuts to 95 - 110 inch-pounds

removal, open engine access doors.

(10.73 - 12.43 Nm) plus drag torque

and install cotter pin.

(3). Remove hardware (except bushings)

attaching damper assemblies to

fuselage attachment fittings and

(8).

Check for minimum 0.010 inch (0.254

landing gear struts.

mm) gap between washer and airframe

clevis at slotted bushing.

(4). Remove damper from aircraft.

B. Landing Gear Damper Installation

(9).

Align lower bearing of damper (forward

and aft) with mating holes in strut and

(1). Jack up or hoist helicopter on level

install attaching hardware.

surface until landing gear skids (Ref.

Sec. 7-00) just clear resting surface.

(10).

Torque nut to 95 - 110 inch-pounds

NOTE:

(10.73 - 12.43 Nm) plus drag torque

D Always be sure that replacement damper

and install cotter pin.

is correct for the helicopter.

D Check for proper alignment of cap torque

(11).

Check for minimum 0.010 inch (0.254

stripes before installation.

mm) gap between washer and airframe

clevis at slotted bushing.

D Install aft dampers with schrader valves

facing aft.

D Install fwd dampers with schrader valves

(12).

Install footwell fairings and close

facing forward.

engine access doors.

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CSP-HMI-2

MAINTENANCE MANUAL

REF. AFT

FOOT ASSEMBLY

LANDING GEAR

SKID

REF. FRONT

ABRASION

FOOT ASSEMBLY

STRIP

ABRASION

STRIP

ABRASION

STRIP

ABRASION

STRIP

AFT BRACE

ASSEMBLY

AFT DAMPER

ASSEMBLY

FUSELAGE

FITTING

FRONT DAMPER

ASSEMBLY

AFT STRUT

ASSEMBLY

BONDING

FRONT STRUT

JUMPER

ASSEMBLY

FRONT BRACE

ASSEMBLY

REF. AFT

BRACE ASSEMBLY

DAMPER ASSEMBLY

REF. FRONT

REF. AFT

DAMPER ASSEMBLY

STRUT

ASSEMBLY

REF. FRONT

MID FAIRING

STRUT

ASSEMBLY

MID FAIRING

BOLT

STEP

WASHER

LOWER FAIRING

ASSEMBLY

NUT

LOWER FAIRING

BOLT

WASHER

NUT

6G32-046B

Figure 401. Landing Gear and Damper Installation

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MAINTENANCE MANUAL

3. Landing Gear Skid Replacement

(b). Open underfloor compartment or

engine compartment doors for access

(Ref. Figure 401)

to strut cutout in fuselage skin. Have

an assistant push down on upper

A. Landing Gear Skid Removal

guide with suitable tool (wood dowel

or equivalent), to relieve spring

(1). Jack up or hoist helicopter until skid

tension.

assemblies clear surface by 10 - 20

(c). With spring tension off guide, remove

inches (Ref. Sec. 07-00).

screws attaching fillet to upper guide.

Slowly relax dowel pressure on guide

(2). Remove mid and lower fairings.

until springs fully expand.

(3). Remove bolts attaching forward and aft

(d). Carefully spread fillet at trailing

feet to forward and aft struts.

edge and remove in forward direc

tion.

(4). Simultaneously, slide front and rear

feet from struts.

(3). Remove mid fairing as follows.

(a). Remove hardware that secure

B. Landing Gear Skid Installation

trailing edge of mid fairing.

(1). Simultaneously, slide front and rear

(b). Remove hardware that secure fairing

feet onto struts.

to strut bracket.

(2). Install bolts attaching forward and aft

(c). Carefully spread trailing edge of

feet to forward and aft struts; torque

fairing and remove in forward

bolts to 95 - 110 inch-pounds (10.73 -

direction.

12.43 Nm) plus drag torque.

B. Landing Gear Fairing Installation

(3). Install mid and lower fairings.

(Ref. Figure 402 and Figure 403) Following

instructions apply to all four fairing assem

4. Landing Gear Fairing Replacement

blies.

(1). Install mid fairing as follows.

A. Landing Gear Fairing Removal

(a). Assemble upper guide, pin assembly,

(Ref. Figure 402 and Figure 403) The following

inner guide half, outer guide half,

instructions are typical for and apply to all

springs and lower support on landing

four fairing assemblies.

gear strut (guide pins must be

installed through matching holes of

(1). Remove lower fairing from fairing

lower guide).

assembly as follows.

(b). Wedge temporary holding device

(a). Remove attaching hardware that

between upper guide and strut to

secures lower fairing to two strut

keep pins engaged.

brackets, and that secures trailing

NOTE: Use two small wood blocks or any simi

edge of lower fairing.

lar suitable means to keep springs com

pressed. Device used must be small enough

(b). Carefully spread trailing edge of

to be removed through strut cutout in skin

lower fairing and remove in forward

after fillet is assembled.

direction.

(c). Carefully spread trailing edge of

(2). Remove fillet from upper fairing

fairing and position fairing on strut

assembly as follows.

bracket(s) and lower guide.

(a). Remove hardware that secure

(d). Install hardware in top hole of

trailing edge of fillet.

trailing edge of mid fairing.

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MAINTENANCE MANUAL

(2). Install fillet as follows.

(e). Check for smooth telescoping action

of fairing into fillet by manually

sliding fillet up and down several

(a). Carefully spread trailing edge of fillet

times.

and position about upper guide.

(f). Close access doors.

(b). Have an assistant remove temporary

(3). Install lower fairing as follows.

holding device and push down on

upper guide with suitable tool (wood

(a). Carefully spread trailing edge of

dowel, etc).

fairing and position under the mid

fairing and over the lower strut

bracket.

(c). Install hardware securing fillet to

upper guide.

(b). Secure to upper and lower strut

brackets with hardware.

(d). Install hardware to secure fillet

(c). Secure fairing trailing edge with

trailing edge together.

attaching hardware.

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MAINTENANCE MANUAL

LANDING GEAR SYSTEM

INSPECTION/CHECK

1. Landing Gear Inspection

(2).

Remove lower fairing from two-piece

fairing assembly.

(Ref. Figure 401)

(3).

Inspect skid for dents. If dents exceed a

depth of 0.20 inch (5.08 mm), they will

NOTE: If landing gear is installed, perform in

require repair.

spection with helicopter skids clear of

ground.

(4).

Inspect for punctures and cracks.

(1). Inspect skids, skid abrasion strips,

(5).

Perform fluorescent-penetrant inspec

struts, feet, braces and fairings for

tion of all crack areas, and of those

dents, cracks, loose components or

areas adjacent to all punctures. These

rivets, loose nuts and for missing

areas will require repair.

hardware.

(6).

Inspect from aft end of tube to a point

(2). Inspect skid-to-foot and foot-to-strut

10 inches (25.4 cm) forward of aft strut

attachments for loose bolts. Check aft

for scratches and nicks.

foot-to-bearing rivet installation for

security.

(7).

Inspect from forward end of tube to 10

inches (25.4 cm) forward of aft strut for

(3). Using 10X glass and bright light,

scratches and nicks. If scratches and

visually inspect area at, around and

nicks exceed a length of 0.25 inch (6.35

between foot-to-strut attach bolts not

mm) and a depth of 0.020 inch (0.508

covered by sealant for cracks and

mm), they will require repair.

corrosion.

(8).

Inspect abrasion strips for minimum

thickness of 0.040 inch (1 mm), damage

NOTE: If cracks or corrosion other than light

and for loose bolts and screws.

surface corrosion is found, replace affected

part.

(9).

Check skid extension rivet attachment

for security.

(4). Inspect keel beam areas where the

strut assemblies attach for loose

(10).

Check condition of plug installed in

bearings, condition of hardware and

skid extension.

strut adapters.

(11).

Check aft foot bearing and extension for

(5). Check condition of beaded seal around

wear, damage and corrosion.

edges of all rigid-mounted skid tube

components.

3. Landing Gear Strut Inspection

(Ref. Table 801)

2. Landing Gear Skid Inspection

(1). Repair elongated, enlarged or worn

(Ref. Figure 401)

holes in strut, either inboard or out

board (Ref. SRM).

NOTE: If landing gear assembly has not been

removed from helicopter, perform following

(2). Replace strut if cracked; if dents in

steps (1). and (2). before proceeding with in

strut exceed 0.060 inch (1.524 mm)

spection.

depth; or, if scratches and repair area

depth would exceed 0.010 inch (0.254

(1). Jack helicopter until landing gear

mm) when measured to surrounding

dampers are fully extended.

unrepaired surface.

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MAINTENANCE MANUAL

4. Landing Gear Damper Inspection

(d). Lower and raise tailboom below and

above the normal at-rest position

three times. On the last cycle, allow

(Ref. Table 601 and Figure 401)

the tailboom to slowly rise to the

at-rest position.

NOTE: It is normal for a thin hydraulic oil film

to remain on damper as a result of wiping

(e). Measure and record dimension from

contact with piston seal. Newly-installed

bottom of upper end cap to top of

dampers may also have slight oil seepage

barrel on all four damper assemblies.

from oil trapped in end cap threads during

(f). Repeat steps (d). and (e). two more

damper assembly. Neither of these should

times.

be considered damper leakage or cause for

damper replacement.

(g). Determine average extension from all

six readings for each damper assem

(1). Inspect for hydraulic oil leakage. If

bly. Remove and overhaul any

leakage is visible, wipe oil from damper

damper assembly not meeting

after last flight of the day. Re-inspect

dimensions (Ref. Table 601).

the following day for oil leakage. If

NOTE: If two damper assemblies fail to meet

leakage persists, replace damper.

the minimum extension (Ref. Table 601), re

place the damper having the greater

(2). With helicopter on jacks, inspect

amount of deflection with a known service

damper assemblies for evidence of

able damper and repeat steps (a). thru (g). If

bearing looseness in upper and lower

the original damper again fails to meet

caps, worn bearings (excessive radial

minimum extension requirements, replace

play), loose or cracked caps and oil

it with the known serviceable damper, rein

leakage. Any misalignment of torque

stall the first damper and repeat steps (a).

stripes on caps, piston and barrel

thru (g). This will determine whether one or

indicates loosening of caps. Replace

both dampers require overhaul. For owners

immediately and repair removed

and operators having suitable equipment,

damper.

any damper not meeting minimum exten

sion requirements can be bench-checked.

(3). Inspect damper attaching hardware for

Dampers meeting specifications may be re

security.

turned to service if other defects are not

noted.

NOTE: The landing gear damper assemblies

5. Forward Cabin Entry Step Inspection

are to be checked at a helicopter gross

weight of 2130 - 2230 pounds (967 - 1012

(1). Remove landing gear fairing assembly.

kg) at a longitudinal CG of 94 ±1, exclusive

(2). Inspect step-to-strut attachment for

of skid mounted flotation gear. Place the he

loose attaching hardware by checking

licopter on a smooth concrete or equivalent

for relative motion between mating

surface (not asphalt).

parts.

(3). Inspect welded joint of step for cracks.

(a). Raise and lower tailboom above and

below the normal at-rest position

(4). Inspect safety walk tape for condition

three times. On the last cycle, allow

and security. Replace unserviceable

the tailboom to slowly settle to the

tape.

at-rest position.

(5). Install landing gear fairing assembly.

(b). Measure and record dimension from

6. Landing Gear Fairing Inspection

bottom of upper end cap to top of

(Ref. Figure 402)

barrel on all four damper assemblies.

(1). Inspect fairing support brackets for

(c). Repeat steps (a). and (b). two more

security of attachment to strut, cracks

times.

and deformation.

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MAINTENANCE MANUAL

LANDING GEAR SYSTEM

REPAIRS

Landing Gear System Repairs

(3). Install new abrasion strip. Torque bolts

to 12 - 15 inch-pounds (1.36 - 1.69

(1).

Repair scratches and nicks by smooth

Nm) plus drag torque.

ing sharp edges.

(4). After installation, seal around bolts and

(2).

Repair elongated, enlarged or worn

all of parting edges of abrasion strip

holes in strut, either inboard or out

next to skid tube with an approximate

board.

0.060 inch (1.524 mm) bead (fillet) of

sealing compound (CM426) to make

(3).

Repair bolt holes at large end of brace

watertight.

that attaches to strut.

3. Ground Handling Bolt Replacement

(4).

Replace strut; if cracked, if dents in

strut exceed 0.060 inch (1.524 mm)

(Ref. Figure 401)

depth or if scratched and repaired area

depth would exceed 0.010 inch (0.254

(1). Remove nut, washers and spacer from

mm) when measured to surrounding

skid tube.

unrepaired surface.

(2). Slide bolt with washers and spacer from

(5).

Replace defective or badly damaged

skid tube.

fairing.

(3). Install, in order, bolt, washer, new

(6).

Replace cracked, dented or distorted

spacer and washer through skid tube

braces.

from outside-to-inside.

(7).

Repair or replace damaged skid tube.

(4). Install, in order, washer, spacer, washer

and nut onto bolt. Torque nut to 10 - 20

(8).

Replace center beam-to-landing gear

inch-pounds (1.13 - 2.26 Nm) plus

attachment bearings that exceed 0.040

drag torque.

inch (1.016 mm) axial play.

4. Safety Walk Tape Replacement

(9).

Repair loose or defective pins and nuts

securing foot to bearing; replace

(Ref. Figure 401)

defective bearing.

Consumable Materials

Abrasion Strip Replacement

(Ref. Section 91−00−00)

Item

Nomenclature

(Ref. Figure 401)

CM220

Naphtha aliphatic

CM724

Tape, non-slip

Consumable Materials

(Ref. Section 91−00−00)

Item

Nomenclature

(1). Carefully pull or scrape away damaged

CM426

Sealing compound

tape.

(2). Remove all residual adhesive from step

(1). Remove bolts securing defective

by wiping with a clean cloth wetted by

abrasion strip(s) to skid.

naphtha (CM220).

(2). Remove bolts securing abrasion strip to

(3). Install new tape (CM724) and press

skid extension. Completely remove any

firmly into place. Expel air bubbles

residual sealant.

while pressing down tape.

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MD Helicopters, Inc.

MAINTENANCE MANUAL

5. Landing Gear Fairing Repair

(3). Replace damaged guide/pin assembly or

guide half if guide is cracked, pins are

bent or badly worn.

(Ref. Figure 402)

(4). Replace springs that are badly worn or

Consumable Materials

rusty, or if free length is less than 8.72

(Ref. Section 91−00−00)

inches (22.149 cm).

Item

Nomenclature

CM412

Adhesive, bonding, vulcanized

(5). Replace fillet if teflon strip is loose or

badly worn.

(1). Replace an excessively damaged lower

(6). Replace damaged strut bracket.

fairing.

Remove rivets, locate new part and

install blind rivets. Use next larger size

rivets if mating holes in strut are

(2). Replace damaged fairing bracket or

enlarged.

lower guide. Remove rivets, locate new

part and install blind rivets. Use next

larger size rivets if mating holes in

(7). Replace unserviceable rubber seals; use

strut are enlarged.

adhesive (CM412).

Table 801. Maximum Damage Limits − Landing Gear Components

Dents

Nicks

Scratches

Cracks

Holes

Component

in / mm

Skid tube (2)

0.200 / 5.08

0.010 / 0.254, from aft side of

(Same as for

No cracks

0.250 / 6.350

(1)

aft strut to 10 inches (25.4 cm).

nicks) (1)

allowed

(1) (3)

forward of the strut, with

cleanup not exceeding 0.015 /

0.381; 0.015 / 0.381 if forward

of that point to start of curved

section, with cleanup not

exceeding 0.020 / 0.508 (1)

Forward foot

0.060 / 1.524

0.010 / 0.254

No cracks

No holes

allowed

Strut

0.060 / 1.524

(1)

No cracks

No holes

allowed

Brace

0.050 / 1.270

0.010 / 0.254

0.005 / 0.127

No cracks

No holes

allowed

Damper assembly

0.060 / 1.524

0.010 / 0.254

No cracks

No holes

(5)

allowed

Fittings

0.010 / 0.254

No cracks

No holes

allowed

Aft foot

0.060 / 1.524

0.010 / 0.254

No cracks

No holes

allowed

Foot bearing

0.010 / 0.254

No cracks

No Holes

allowed

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MAINTENANCE MANUAL

Table 801. Maximum Damage Limits − Landing Gear Components

Dents

Nicks

Scratches

Cracks

Holes

Component

in / mm

Skid extension

0.010 / 0.254

0.010 / 0.254 (4)

0.010 / 0.254

No cracks

No holes

(4)

allowed

NOTES:

(1) For other repair data, refer to CSP−SRM−6.

(2) Repair of minor skid tube damage on forward (curved) section is not required, but surface finish must be

restored.

(3) Hole must be plugged with correct size blind rivet.

(4) No damage is allowed on skid extension where skid and sleeve are attached.

(5) No dents allowed in damper barrel.

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MAINTENANCE MANUAL

GROUND HANDLING WHEELS

MAINTENANCE PRACTICES

1. Ground Handling Wheel Assembly

(2). With ground handling wheels in the

retracted position, align and engage the

The standard ground handling wheel assem

skid fittings.

blies provide a means of moving the helicopter

by hand or by towing.

NOTE: Slide wheel assembly for and aft to en

sure locking mechanism is securely locked

The special ground handling wheel assemblies

into place.

for use with helicopters equipped with

emergency or utility floats provide a means of

(3). Install jack handle over the wheel

moving the helicopter by hand only.

assembly socket, install lock pin and

rotate handle downward to lower the

A. Ground Handling Wheel Description and

wheels and raise the helicopter.

Operation

Hold downward pressure on

(1).

Standard ground handling wheel

WARNING

jack handle until the extend

assembly consists of one detachable

lock snaps into locked position. If the

jack handle and two two-wheeled

lock is not properly engaged and the

jacking assemblies that can be

handle is released, the upward swing of

straddle-mounted to the left and right

the handle could cause serious person

landing gear skids by use of existing

al injury.

ground handling wheel fittings. The

wheels are manually lowered with a

(4). Check that the extend lock is engaged;

detachable jack handle and are held in

then release downward pressure and

the down position (helicopter raised on

remove jack handle.

wheels) by a mechanical lock. The

jacking assemblies are equipped with

(5). Install second ground handling wheel

two tow bar attach fittings for towing.

assembly on the other skid in the same

(2).

Special ground handling wheels are

manner.

needed in place of standard ground

handling wheel assemblies for moving a

3. Special Ground Handling Wheel

helicopter equipped with emergency or

Installation and Use

utility floats. These wheel assemblies

are specially designed for use with

(Ref. Figure 201)

emergency floats and raise the landing

skids higher off the ground than

Damage may result from push

CAUTION

standard ground handling wheels. A

ing up and/or pulling down on

channel provides support for the

the tail boom to facilitate installation of spe

underside of the landing gear skid. A

cial ground handling wheels.

rubber pad on the channel furnishes

sufficient skid retaining friction

NOTE: When the helicopter is jacked from one

without need for attachment of wheel

side only, a cushion saddle-type support

assembly to skid. Guards above the

should be placed under the tail boom at the

wheel on each side of the channel

jacking pad location for extra stability.

prevent wheel chafing of floats.

(1). Install and use special ground handling

Standard Ground Handling Wheel

wheel assemblies as follows.

Installation and Use

(a). Jack up one side of the helicopter for

(1). Position ground handling wheel

clearance to place ground handling

assembly over the skid tube at the

wheel assembly under the landing

location of the skid fittings.

gear skid.

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MAINTENANCE MANUAL

WHEEL ASSEMBLY

HANDLE

G32-4001

Figure 201. Ground Handling Wheel Assembly (Standard)

(b). Position ground handling wheel

(6). To remove axle shaft from housing,

assembly below the ground handling

remove roll pin and slide shaft from

fittings, which is the approximate

housing.

center of gravity (CG) point.

5. Standard Ground Handling Wheel

Re−assembly (Early Configuration)

4. Standard Ground Handling Wheel

Disassembly (Early Configuration)

(1). If previously removed, install axle shaft

into housing and secure with roll pin.

(1). Remove cotter pin and washer from

axle shaft and slide hub-and-wheel

(2). Using suitable bearing press, install

assembly off axle.

bearings in hub.

(2). Remove three nuts securing wheel to

(3). Install washer, hub assembly and

hub.

washer on axle. Shim hub assembly,

0.010 inch maximum, using AB2578-24

Severe personal injury or

washers, as required, between bearing

WARNING

damage to property can oc

and outer washer and install cotter pin.

cur if tire is not deflated before at

(4). Using talcum powder, insert tube into

tempting to separate wheel halves.

tire and install on wheel halves.

(3). Deflate tire and remove six nuts,

(5). Secure wheel halves together using six

washers and screws securing wheel

screws, washers and nuts.

halves.

(6). Inflate tire in accordance with man

(4). Remove tire and tube from wheel.

ufacturers specifications.

(5). Using suitable bearing press, remove

(7). Install wheel on hub assembly using

bearings from hub.

three nuts and washers.

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MAINTENANCE MANUAL

6. Standard Ground Handling Wheel

(7). Secure wheel halves together using six

Disassembly (Current Configuration)

screws, washers and nuts.

(Ref. Figure 202)

(8). Inflate tire in accordance with man

ufacturers specifications.

(1). Remove three nuts and washers

(9). Install wheel on hub assembly using

securing wheel and tire assembly to

three nuts and washers.

hub and axle assembly.

8. Standard Ground Handling Wheel

(2). Remove dust cap, cotter pin, nut and

Servicing

washers from hub and axle assembly.

At regular intervals, Ground Handling Wheel

Severe personal injury or

Assemblies should be maintained to provide

WARNING

damage to property can oc

safe use and longer life of components.

cur if tire is not deflated before at

tempting to separate wheel halves.

(1). Ensure tire pressure is within manufac

turer's specifications.

(3). Deflate tire and remove six nuts,

washers and screws securing wheel

(2). Grease bearing using MIL-G-81322,

halves.

Mobil Grease 28 or alternate grease

MIL-G-25537, Aero Shell using

(4). Remove tire and tube from wheel.

available grease zerk (primary method)

or hand pack (alternate method).

Do not remove spacer from hub

CAUTION

body. Spacer is a close tolerance

(3). Remove excess play of hub-to-axle by

press fit and should not be removed.

inserting AB2578-24 washers, as

required, between bearing and outer

(5). Remove seal, bearings and races from

washer to maintain 0.010-inch axial

hub body.

play.

(6). To remove axle shaft from housing,

9. Special Ground Handling Wheel

remove roll pin and slide shaft from

Disassembly

housing.

(Ref. Figure 204)

7. Standard Ground Handling Wheel

(1). Remove cotter pin, nut and washer and

Re−assembly (Current Configuration)

remove wheel assembly.

(Ref. Figure 202)

(2). To remove axle shaft, remove slotted

pin and slide shaft from housing.

(1). If previously removed, install axle into

(3). Using suitable bearing press, remove

housing and secure with roll pin.

bearings from hub.

(2). Install races, bearings and seal in hub.

10. Special Ground Handling Wheel

(3). Install hub assembly on axle shaft and

Re−assembly

secure with washer and nut.

(Ref. Figure 204)

(4). Tighten nut until there is a maximum

(1). Insert axle shaft into housing and

of 0.010 inch axial play. Remove excess

insert slotted pin.

axial play by inserting AB2578-24

washers, as required, between bearing

(2). Using suitable bearing press, install

and outer washer.

bearings into hub.

(5). Install cotter pin and dust cap.

(3). Install wheel on axle using washer, nut

and cotter pin. Adjust axial play, 0.010

(6). Using talcum powder, insert tube into

inch maximum, using AN960C1016

tire and install on wheel halves.

washers as required.

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MAINTENANCE MANUAL

11. Special Ground Handling Wheel Servicing

solid rubber tires and therefore require no

servicing.

(Ref. Figure 204) The special ground handling

wheel assemblies have sealed bearings and

SKID TUBE

RUBBER PAD

(NOTE 1)

SKID FITTING

(REF) (NOTE 2)

GUARD

FAIRING

WELD SUPPORT

STRUT

EMERGENCY FLOAT

CONTAINMENT COVER

SHAFT

RUBBER TREAD WHEEL

NOTES:

LANDING GEAR SKID TUBE UNDERSIDE RESTS ON

CAUTION: BE SURE THAT FLOAT CONTAINMENT

RUBBER PAD AND IS SUPPORTED BY WELD SUPPORT

COVER CLEARS AND IS NOT PINCHED BY

WITHOUT RESTAINING ATTACHMENT.

HANDLING WHEEL ASSEMBLY.

NOT USED WITH GROUND HANDLING WHEELS SHOWN.

MAXIMUM LOAD RATE 800 LBS. (363 KG) AT 8 RPM.

G32-4000A

Figure 203. Special Ground Handling Wheel Assembly (Float Type)

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CSP-HMI-2

MAINTENANCE MANUAL

GROUND HANDLING WHEELS

MAINTENANCE PRACTICES

1. Ground Handling Wheel Assembly

The jack retains a vertical position

during raising and lowering of the

The standard ground handling wheel assem

wheels.

blies provide a means of moving the helicopter

The ram of the jack is in constant

by hand or by towing.

contact with the upper cross frame of

the main body, providing vertical

A. Ground Handling Wheel Assembly

pumping leverage forcing the wheels

Description and Operation

down.

The ground handling wheel set consists of two

(4). Attach Cradle and Main Frame Body:

dual wheel assemblies, which are designed to

support a fully equipped helicopter. The wheel

The attach cradle is attached to the

assembly consists of two pneumatic tires, rims,

main frame body by means of two pins

spindles, hydraulic jack and attach cradle.

with cotter pins. The contoured cradle

is slotted to lock onto the skids.

(1). Tires:

2. Ground Handling Wheel Assembly

Maintenance

The tires are 10 ply with a maximum

rating of 1120 lb at 65 psi (508 kg at

(1). Ensure tire pressure is within manufac

448 kPa).

turer's specifications.

(2). Rims:

(2). Inspect tires for wear and cuts, none

allowed.

The rim rotates on a spindle by means

(3). Inspect wheels for cracks and defects,

of inner and outer tapered roller

none allowed.

bearings with an external grease fitting

on the hub for periodic servicing.

(4). At regular intervals, repack wheel

bearings and grease spindle assembly

(3). Hydraulic Jacks:

guides.

A six ton jack is held in place on the

(5). At regular intervals, inspect hydraulic

main frame by a support plate.

jacks for proper fluid levels.

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CSP-HMI-2

MAINTENANCE MANUAL

UTILITY FLOAT SYSTEM

MAINTENANCE PRACTICES

1. Utility Float Description and Operation

0.5 psig (3.447 kPa) for each compart

ment.

Utility floats consists of neoprene airtight

(3). Place BATTERY-OFF-EXT PWR

chambers separated by internal walls that

switch at BATTERY. Actuate POS LT

provide six individual watertight compart

switch to the ON position. Observe that

ments. Skid attachment strips (girts), bonded

left and right position lights illuminate.

to underside of floats, are bolted to landing

Place all switches at OFF position.

gear skids and extensions. Floats are inflated

to a normal operating pressure of 2.0 psig (14

2. Utility Float Inspection

kPa). Relief valves release air pressure if

compartment pressure becomes excessive. A

(1). Inspect float chambers for correct air

stabilizer assembly is attached at the aft end

pressure.

of the skid tube extension.

(2). Inspect float bags for abrasion and

NOTE: If a helicopter with utility floats is tilted

chafing.

back on the tail skid to install ground handl

(3). Inspect pressure relief and fill valves

ing wheels, approximately 1 pint (0.437 li

for condition and closure.

ter) of oil is trapped in the tail rotor trans

mission. This condition gives a false sight

A. Skid Tube and Extension Assembly

plug oil level indication immediately after

Inspection

return to a level attitude. After ground ru

nup, oil level indication is normal.

Inspection of skid tube and extension assembly

is identical to that described in Sec. 32-10-00.

A. Utility Float Operational Check

B. Utility Float Repair

With helicopter on the ground and utility

Repair materials and information are avail

floats inflated to normal operating pressure,

able from the float manufacturer. Make

perform the following operational checks:

repairs to utility floats using materials

according to manufacturer's instructions.

(1). Check all float compartments for 2.0

psig (14 kPa).

3. Utility Float Troubleshooting

NOTE: Changes in atmospheric pressure, and

Refer to Table 201 for troubleshooting informa

temperature of float compartments affects

tion. Troubles presented are listed in order of

pressure gage readings. A temperature

possible occurrence during performance of

change of 1 degree equals 0.032 psig (0.2206

operational check. This information is pro

kPa).

vided to aid in isolating faults found during

operational check or normal operation of the

(2). Check for pressure drop with pressure

system. The fault is then removed by repair or

gage that indicates 0 - 15 psi (0 - 103

replacement to return the system to trouble-

kPa), graduated in 0.5 psi (3.447 kPa)

free operation. Troubleshooting and repair of

increments. Maximum allowable

internal components of the float is beyond the

pressure drop in 24 hours is limited to

scope of this section.

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Table 201. Troubleshooting Utility Floats

Symptom

Probable Trouble

Corrective Action

Low air pressure

Damaged float

Repair float.

Defective fill valve

Replace fill valve.

Defective pressure relief valve

Replace pressure relief valve.

Position lights do not

POS LT switch not at ON position

Actuate switch to ON position.

illuminate

Position light lamp defective

Replace lamp.

Defective electrical wire splice

Repair electrical splice.

4. Utility Float Replacement

B. Utility Float Installation

(Ref. Figure 201)

Consumable Materials

(Ref. Section 91−00−00)

A. Utility Float Removal

Item

Nomenclature

CM209

Zinc chromate putty

Prior to removal of utility floats, jack or hoist

CM318

Primer

helicopter until landing gear dampers are fully

CM425

Sealing compound

extended and landing gear skid tubes are at

least six inches (15cm) from ground. Skid and

CM717

Tape, pressure sensitive

fairing assemblies must be removed to remove

float assemblies Ref. Sec. 32-10-00).

NOTE: Prior to assembly, apply

primer

(CM318) to all mating surfaces.

Maintain helicopter in level at

CAUTION

titude during jacking or hoist

(1). On early configuration extended

ing. Do not raise one side of helicopter at a

landing gear, coat abrasion strip with

time.

zinc chromate putty (CM209) and

install using screws.

(1). Remove position light cover screws,

(2). Install bolt covers using existing screws

then remove cover. Remove position

and wrap with two overlapping layers

light mounting screws and position

of tape (CM717).

light. Retain electrical wire for installa

tion.

(3). Install tyrap bracket on forward struts.

(4). Align extension and bearing sleeve

(2). Remove bolts and washers attaching

holes; install rivets using wet primer

stabilizer assembly to aft section of

(CM318).

floats.

(5). On early configuration extended

(3). Open fill valve at each of six float

landing gear, install skid tube extension

chambers. A suction device such as a

as follows:

vacuum cleaner speeds air evacuation.

(a). Install indexing plug in float kit

extension tube.

(4). Remove bolts, washers, gravel guards

and abrasion strip attaching float to

(b). Align indexing plug tabs with slots in

skid assembly and skid extension.

foot bearing sleeve on helicopter;

install indexing plug and forward end

(5). Depress float around strut assemblies

of extension tube over bearing sleeve.

and pull float free from skid tube

Use care not to damage packing

assembly and skid extension.

during installation.

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(c). Align bolt holes in bearing sleeve,

bolts to 25 - 35 inch-pounds (2.82 -

indexing plug and extension tube;

3.95 Nm).

install rivets with wet primer.

(9). Connect wiring to position light then

(d). Coat mating surfaces of abrasion

install position light with screws.

strip with zinc chromate putty.

Install cover and secure with screws.

(e). Install abrasion strip on extension

5. Skid Tube Extension Replacement

tube with rivets and wet primer.

(Ref. Figure 901)

(f). Seal all edges of abrasion strip with

A. Skid Tube Extension Removal

approximately 0.060 (1.524 mm) bead

of sealing compound (CM425).

(1). Remove bolts and washers; then

remove stabilizer support from aft end

(6). Position floats on skid and extension

of skid extension.

assembly. Align bolt holes in float girt

and skid assembly. Secure floats in

(2). Remove bolts and nuts attaching

place using gravel guards, abrasion

extension to skid tube assembly.

strips, bolts and washers. Coat bolts

and washers with primer and torque to

(3). Separate skid extension from skid tube.

25 - 35 inch-pounds (2.82 - 3.95

B. Skid Tube Extension Installation

Nm).

(1). Insert skid extension into aft section of

(7). Position stabilizer cap on skid tube

skid tube.

extension. Coat mating surfaces with

sealing compound and secure with bolts

(2). Align bolt holes and secure in place

and washers.

using bolts and nuts as applicable.

(8). Position stabilizer assembly on aft

(3). Position stabilizer support on aft end of

section of skid extension and secure in

skid extension and secure in place

place using bolts and washers. Torque

using bolts and washers.

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MAINTENANCE MANUAL

UTILITY FLOAT SYSTEM

INITIAL INSTALLATION

1. Utility Float Initial Installation

(6). Remove cargo compartment and aft

landing gear steps.

The utility float kit may not be installed in

combination with the following:

NOTE: Passenger steps,

369D26505 and

Passenger steps

369D292028, may not be installed in combi

Hoist kit

nation with utility floats. Upon removal of

Litter kit

369D292028 step assembly, install

Four-bladed tail rotor

PLT210-10-3 bolts (2 per assembly) coated

with sealing compound (CM425) into holes

A. Preparation for Installation

where step attaching hardware was located.

(7). Remove hardware that secures trailing

Consumable Materials

edge of lower fairings to strut assem

(Ref. Section 91−00−00)

blies. Carefully spread trailing edge of

Item

Nomenclature

lower fairings and remove fairings.

CM425

Sealing compound

NOTE: If preload condition prevents removal of

skid assemblies, disconnect one brace as

Instructions in the following paragraphs are

sembly from skid assemblies to eliminate

applicable to both left and right landing gear

preload (Ref. Sec. 32-10-00).

assemblies. Preparation for installation of

utility floats includes the following:

(8). Remove ABC bolts from forward and aft

NOTE: Make sure that the BATT-OFF-EXT

strut assemblies (Ref. Sec. 32-10-00).

switch is set to OFF.

Retain ABC hardware for reuse.

Remove skid assemblies with foot

(1).

Check all cockpit electrical switches in

assemblies attached.

the OFF position.

B. Disassembly of Extended Landing Gear

(2).

Identify all components, including

attaching hardware, or components

(Ref. Figure 901) Complete disassembly of

removed for access to work areas.

landing gear is not required; however, certain

Protect components from damage and

items must be removed.

foreign matter until installed.

(3).

Using jacking or hoisting methods,

Consumable Materials

raise helicopter 6 inches (15 cm) clear of

(Ref. Section 91−00−00)

ground.

Item

Nomenclature

CM318

Primer

(4).

Remove landing gear (Ref. Sec.

32-10-00). Removal of landing gear is

identical to that described in Sec.

(1). Remove screws from float attach

32-10-00, except that removal of

fittings.

complete landing gear is not required.

Remove extended landing gear accord

(2). Remove bolts and abrasion strip from

ing to Sec. 32-10-00, except as follows:

skid extension.

(5).

Remove screws attaching position light

assemblies to skid assemblies. Retain

(3). Remove bolts attaching skid tube

screws for reuse. Disconnect electrical

extension.

harness and remove position light

assemblies.

(4). Remove skid tube extension.

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NOTE: When installing the 369D292808-17

D. Landing Gear Skid Extension Assembly

and -18 extension tubes, it will be necessary

(Ref. Figure 903)

to remove and replace the 369D26012 or the

369D26012-5 sleeve adapter with a new -5

(undrilled at aft end) sleeve adapter (Ref.

Consumable Materials

Sec. 32-10-00).

(Ref. Section 91−00−00)

Item

Nomenclature

(5). Remove bolts attaching abrasion strip

CM209

Zinc chromate putty

to skid tube. Do not remove abrasion

CM318

Primer

strips. Retain four bolts for reuse.

CM425

Sealing compound

(6). Remove fairing attach brackets from

foot assemblies. Coat screws and

(1). On all types of landing gear skid tube

washers with primer (CM318) and

extensions:

reinstall screws and washers.

(a). Coat mating surfaces of the correct

plug with zinc chromate putty

C. Landing Gear Strut Modification

(CM209); assemble plug to tube with

rivets coated with primer (CM318).

(Ref. Figure 902) For modification of landing

Seal edges with sealing compound

gear strut assemblies to accommodate installa

(CM425).

tion of utility floats and return to extended

(b). Coat mating surface of support

landing gear configuration when utility floats

assembly and tube with zinc chro

are removed, perform the following:

mate putty; install using bolts and

washers.

Consumable Materials

(2). Assembly of landing gear skid exten

(Ref. Section 91−00−00)

sion (369D292808-17 and -18) on

Item

Nomenclature

current configuration landing gear:

CM318

Primer

NOTE: The 369D292808-17 and -18 skid tube

CM425

Sealing compound

extension assemblies may only be installed

on extended skid gear having new (un

drilled) 369D26012-5 adapter, sleeve-skid

(1). Using drill motor and number 15 drill

installed. For replacing the 369D26012 ba

bit, drill two holes through lower

sic sleeve with the -5 sleeve (Ref. Sec.

fairing attach brackets and aft wall of

32-10-00).

landing gear strut assemblies (view A).

Enlarge holes to 0.250 inch (6.350 mm)

(a). Insert skid tube extension on to -5

diameter using 1/4 inch (6.35 mm) drill

adapter sleeve. Align skid tube

bit.

rivnut centerline with extension tube

rivnut centerline. Secure both

(2). Using number 30 drill bit, drill out

assemblies with a suitable fixture.

huckbolts attaching bracket to strut.

(b). Mark and match drill eight 0.1945 -

Remove bracket. Seal huckbolt attach

0.1965 inch (4.9403 - 4.9911 mm)

holes in strut with sealing compound

diameter holes through tube and

(CM425). Coat bare metal with primer

sleeve (use locations and dimensions

(CM318).

as stated in Figure 903); separate

skid tube extension from adapter

(3). Remove rivets attaching nutplates

sleeve.

(view B).

(c). Countersink holes, 100° x 0.378 -

NOTE: When floats are removed from landing

0.385 inch (100° x 9.6012 - 9.779

gear assembly, modified foot assembly

mm) diameter in skid tube extension,

brackets may be reinstalled by using screws

deburr and apply primer to bare

and washers.

metal surfaces.

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HANDBOOK OF MAINTENANCE INSTRUCTIONS FOR MDHI 369D/E/FF-500/600N HELICOPTERS (ISSUED: 1990) - page 13