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

MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

Table 1. Airworthiness Limitations Schedule (Cont.)

Finite Life

Mandatory

Component

Part Number

Model

Hours

Inspection

(1)

(2)

(1)

Hours

Drive Shafts, Couplings and Clutches

Drive shaft, main rotor transmission

369D/E/F

369A5510

3790

Coupling, main transmission drive shaft

369D/E/F/FF

369H5660

4300

500N

369H5660

3200

Overrunning clutch assembly

369D/E/F/FF

369F5450−501

On Cond.

100

(24)

500/600N

Sprag assembly, overrunning clutch

369D/E/F/FF

369A5364

(3)

300

(10)

369D25351

500N

369D25351

(3)

300

(10)

369D/E/F/FF

369F5456

(3)

300

(17)

500/600N

Drive shaft, fan

500N

500N5200

2620

600N

500N5200

1200

(36)

Drive shaft, tail rotor

369D/E

369D25518

13900

369F/FF

369DSK152−11

13900

369D25518−503

14610

Coupling − tail rotor drive shaft (Bendix)

369D/E/F

369A5501

4980

(NOTE: Not certified on 369FF Model)

(9)

369H92564

(7)

4980

Anti−Torque System

Gearshaft assembly, tail rotor input

369D/E

369D25434

12000

369D25434−3

12000

Gearshaft assembly, tail rotor input

369F/FF

369D25434

3365

369D25434−3

3365

Gearshaft, tail rotor output pinion

369D/E/F/FF

369D25430

7290

369D25430−5

7290

Blade assembly, tail rotor

369D/E

369D21613

5200

369D21613−11

5140

369D21613−31

5140

369D21613−41

5140

369D21613−51

5140

369D21613−61

5140

369D21613−71

5140

369D21640−501

(38)

400

369D21640−503

(38)

5140

369D21640−505

(38)

5140

369D21640−507

(38)

5140

369F/FF

369D21606

5140

369D21642−501

(38)

400

369D21642−503

(38)

5140

369D21642−505

(38)

5140

369D21642−507

(38)

5140

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Table 1. Airworthiness Limitations Schedule (Cont.)

Finite Life

Mandatory

Component

Part Number

Model

Hours

Inspection

(1)

(2)

(1)

Hours

Blade assembly, tail rotor

369D/E

369D21615

10000

(optional 4−blade)

369D21641−501

(38)

400

369D21641−503

(38)

10000

369D21641−505

(38)

10000

369D21641−507

(38)

10000

Hub, tail rotor

369D/E/F/FF

369A1725

3450

Retention strap assembly, tail rotor

369D/E/F

369A1706

5100

369FF

369A1706−507

5100

369A1706−509

5100

Blade assembly, NOTAR fan

500N

500N5310−15

7500

500N5310−19

7500

500N5310−23

7500

Blade assembly, NOTAR fan

600N

500N5310−19

12500

500N5310−23

12500

Hub, fan

500N

500N5352−7

7500

500N5352−9

7500

600N

500N5352−9

7500

Tension−Torsion Strap, NOTAR®

500N

500N5311−5

(43)(44)

600N

Shaft, NOTAR fan support

600N

500N5357−13

4000

Pitch plate assembly

500/600N

500N5363−7

7500

Tube assembly, fan pitch

500N

500N7113−3

600

(18)

Rotating cone assembly

500N

500N3740−1

10000

500N3740−41

10000

500N3740−81

10000

600N

500N3740−61

10000

500N3740−71

10000

Tailboom

Bolts, tailboom attach

369D/E/F/FF

MS21250−06014

21950

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Table 1. Airworthiness Limitations Schedule (Cont.)

Finite Life

Mandatory

Component

Part Number

Model

Hours

Inspection

(1)

(2)

(1)

Hours

Tailboom assembly

369D/E

369D23500

10300

369F/FF

369D23500−507

10300

Tailboom assembly

500N

500N3500−19

10204

100

(14)

500N3500−29

10204

500N3500−501

10204

500N3600−501

10204

100

(14)

600N

600N3500−503

2500

(25)

600N3500−505

5900

600N3500−507

1000

600N3500−509

6000

(19)

600N3500−511

6000

(19)

600N3500−513

2500

(25)

600N3500−515

5900

600N3500−517

1000

Empennage fittings

600N

500N3530−7/8

On Cond.

100

(26)

500N3530−9/10

On Cond.

100

(26)

Vertical stabilizer assembly

369D/E

369D23600

12700

369F/FF

369D23600−505

3388

Torque tube, horizontal stabilizer

500N

500N3950−5

5000

600N

500N3950−7

3000

(45)

500N3950−9

3000

(45)

600N3950−1

400

600N3950−3

1000

Horizontal stabilizer assembly

369D

(12)

369D23601

7700

369E

(12)

421−087−505

7700

421−087−905

(13)

7700

369F/FF (12)

421−087−503

7700

421−087−903

(13)

7700

600N

500N3910−25

10000

(19)

500N3910−27

10000

(19)

Controls

Longitudinal idler bellcrank assembly

369D

369A7301

6500

369A7301−501

6500

369E/F/FF

369A7301−501

6500

500N

369A7301−501

2870

Idler assembly, longitudinal pitch mixer

369D/E/F/FF

369A7603

13600

500N

369A7603

6050

Longitudinal control rod

500N

369A7011−13

7740

369A7011−15

7740

Socket, cyclic stick

600N

369A7141

1000

(27)

Cyclic tube assembly

600N

369D27132−503

1200

(27)

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Table 1. Airworthiness Limitations Schedule (Cont.)

Finite Life

Mandatory

Component

Part Number

Model

Hours

Inspection

(1)

(2)

(1)

Hours

Housing, collective stick

600N

369A7347

450

Tube, collective pitch control

600N

369A7348

400

Tube assembly, collective pitch (pilot)

600N

369H7354−3

600

Socket, cyclic stick

600N

369A7802

1000

(27)

Tube, collective pitch (co−pilot)

600N

369A7809

1800

Housing, collective stick

600N

369A7820

450

Housing, collective stick

600N

369H7837

450

Tube assembly, collective pitch (co−pilot)

600N

369H7838−3

1000

Fuselage Sta. 75 controls support bracket

600N

369N2608−11

6000

(41)

600N2608−9

Unlimited

Airframe

Landing gear brace

600N

600N6010−17/19

5900

(28)

Landing gear strut

600N

600N6022−7

696

(29)

600N6022−8

696

(29)

600N6022−9

696

(29)

600N6022−10

696

(29)

600N6022−11

696

(29)

600N6022−12

696

(29)

600N6022−13

696

(29)

600N6022−14

696

(29)

Landing gear foot

600N

600N6043−3

3900

(30)

Floats

Squib cartridge, used on Emergency float

369D/E/F/FF

12552−1

5 years

kit 369D292473−5, −6, −9, −10, −11, −12

500N

(Holex, Inc.)

NOTE: Life is based from original date of

281993

5 years

manufacture.

(Walter Kidde)

12754−1

5 years

(Holex, Inc.)

5003527

5 years

(Tavco)

Stabilizer support, utility float

369D/E

369D292036

3190

369DSK66

3190

NOTES:

(1) Life−limited components interchanged between models or configurations must be restricted to the lowest

service life indicated for the models or configurations affected. Life−limited components removed at

retirement are to be mutilated/destroyed or conspicuously marked to prevent inadvertent return to service.

Parts are applicable only on models under which a service life is listed.

Life−limited components cannot be altered or permanently marked in any manner without compromising

the part integrity. Part tagging or other record keeping system is required.

Related component records must be updated each time component is removed from service.

(2) Service life shown for the basic (no dash number) part numbers apply to all dash numbered versions

unless otherwise indicated.

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(3)

With no cargo hook attached: − No retirement life assigned (Ref. Sec. 05−10−00, Component Overhaul or

Recommended Replacement Schedule).

With cargo hook attached and no separate log: − 1800 hours.

With cargo hook attached and with separate log: − 1800 hours of external load operating time when logged

separately.

(For 369D/E/F/FF helicopters with 369A5364 or 369D25351 sprag assembly, Refer to AD 90−19−02.)

(4)

Inspect in accordance with Main Rotor Strap Pack Lamination Inspection at 100−hour intervals, or 25−hour

intervals if 2 laminates (369D/E/F/FF − 500N) or 1 laminate (600N) have failed in any one leg or tongue

area of any strap assembly. A single cracked laminate between the shoes at the outboard end of a strap

pack is cause for rejection of the hub assembly

369D/E/F/FF − 500N: (Ref. Sec. 62−20−00, Main Rotor Strap Pack Lamination Inspection).

600N: (Ref. Sec. 62−20−60, Main Rotor Strap Pack Lamination Inspection).

(For 369D/E/F/FF helicopters, refer to AD 89−02−01.)

(5)

The 369D21100−513, −515, 516, 517 and −523 main rotor blades are not interchangeable with any earlier

configuration blades (Basic, −505 or −509); however, the −505 and −509 blades are interchangeable and

the −513 and −515 blades are interchangeable. The −505 and −509 configuration blades may be modified

to the −513M configuration, which is fully compatible with the −513 blade. (For information concerning

modification, contact MDHI Customer Service Department.)

(6)

For the 369D/E helicopters, the 369D21120−501, −503 main rotor blade has all the same inspections and

interchangeability as the 369D21100−517 main rotor blade.

For the 369F/FF − 500N helicopters, the 369D21121−501, −503 main rotor blade has all the same

inspections and interchangeability as the 369D21102−517 main rotor blade.

For the 600N helicopters, the 369D21121−501, −503 main rotor blade has all the same inspections and

interchangeability as the 369D21102−523 main rotor blade.

(7)

Used with 369H90123 Rotor Brake Kit.

(8)

Inspect main rotor drive shaft every 300 hours (Ref. Sec. 63−10−00, Main Rotor Drive Shaft Inspection

(300 Hour)) (Reference AD 81−26−01).

(9)

Failsafe device, P/N 369D25530 bolt and 369D25531 socket, must be used at both ends of tail rotor

driveshaft in accordance with Tail Rotor Drive Shaft Installation with Bendix Couplings (Reference AD

86−20−07).

(10)

For helicopters equipped with a cargo hook, inspect overrunning clutch sprag assembly P/N 369D25351,

clutch inner race P/N 369A5353 and outer race 369A5352 every 300 hours (Ref. C.O.M., Sec. 63−10−10,

Overrunning Clutch Sprag Inspection (300 Hour)). To establish time in service, either clutch total time with

hook attached or a separate and permanent log of external load operating time per CFR 91.417, may be

used.

(For 369D/E/F/FF helicopters with 369A5364 or 369D25351 sprag assembly, Refer to AD 90−19−02.)

(11)

Inspect main rotor blade root fittings and main rotor lead−lag link assemblies every 25 hours in accordance

with Main Rotor Blade Upper and Lower Root Fitting Attach Lug and Lead−Lag Link Attach Lug Inspection

(25 Hour) and every 100 hours in accordance with Main Rotor Blade Upper and Lower Root, Fitting Attach

Lug and Lead−Lag Link Attach Lug Inspection (100 Hour) (Ref. Sec. 62−10−00) (Reference AD

95−03−13).

(12)

Tip plates, tip weights (where applicable) and attaching hardware have no retirement life and may be

reused on replacement horizontal stabilizers.

(13)

421−087−903 and −905 require the addition of tip plates, tip weights and attaching hardware before

installation.

(14)

Inspect the three upper slot bridges for cracks (Ref. Sec. 05−20−00).

(15)

Inspect main rotor drive shaft every 300 hours (Ref. Sec. 63−10−00, Main Rotor Drive Shaft Inspection

(300 Hour)).

(16)

Inspect for deterioration every 600 hours up to a total time of 4200 hours and every 300 hours thereafter

until deterioration is sufficient to retire assembly

369D/E/FF − 500N: (Ref. Sec. 62−20−00, Main Rotor Damper and Attachments Inspection)

600N: (Ref. Sec. 62−20−60, Main Rotor Damper and Attachments Inspection).

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(17)

For helicopters equipped with a cargo hook, inspect overrunning clutch sprag assembly P/N 369F5456,

clutch inner race P/N 369F5455 and outer race 369F5453 every 300 hours. To establish time in service,

either clutch total time with hook attached or a separate and permanent log of external load operating time

may be used.

(18)

500N7113−11 tube assembly, fan pitch is an On−Condition part and replaces the 500N7113−3 tube

assembly.

(19)

Interim hours: life extension testing in progress.

(20)

Inspect upper and lower blade root fittings every 100 hours in accordance with Main Rotor Blade Upper

and Lower Root, Fitting Attach Lug and Lead−Lag Link Attach Lug Inspection (100 Hour) (Ref. Sec.

62−10−00)

(For 369D/E/F/FF − 500N helicopters, Reference AD 96−10−09).

(21)

Main rotor blades, P/N 369D21102−517 with S/N 1976 thru 2100, 2106 thru 2115 are not to be installed on

600N helicopter (Reference Service Bulletin SB600N−007R2) (Reference AD 98−15−26).

(22)

Inspect main rotor blades with 600 or more hours of operation every 25 hours of helicopter operation with a

10X magnifying glass for cracking of the lower surface of the blade emanating from the root fitting and

doubler at the inboard end of the blade and to detect debonding between the blade root end fitting and

doubler if missing or cracked adhesive or paint is observed. (Reference Service Bulletins SB369D−195R3,

SB369E−088R3, SB369F−075R3, SB500N−015R3) (Reference AD 98−15−26).

(23)

Perform Main Rotor Blade Upper and Lower Root, Fitting Attach Lug and Lead−Lag Link Attach Lug

Inspection (25 Hour) up to a total time of 500 hours and every 15 hours thereafter and every 100 hours in

accordance with Main Rotor Blade Upper and Lower Root Fitting, Attach Lug and Lead−Lag Link Attach

Lug Inspection (100 Hour) (Ref. Sec. 62−10−00) until retirement of 369H1203−BSC and −21 Lead−Lag

Link Assembly. (Reference AD 95−03−13).

(24)

Inspect clutch retainer and bearing carrier for evidence of spinning and/or wear (Ref. Sec. 05−20−20).

(25)

The 600N3500−503 tailboom may be reworked to a 600N3500−505 tailboom, and the 600N3500−513

tailboom may be reworked to a 600N3500−515 tailboom by modifying the attachment fittings to all−steel

fittings.

(26)

(Ref. Sec. 05−20−00) Using a flashlight and 10X magnifying glass, inspect horizontal stabilizer mounting

brackets for cracks (pay particular attention to the forward inboard legs) (Ref. Tailboom Inspection).

(27)

Sockets must be inspected for cracks every eight hours after the initial 100 hour inspection.

(28)

Log all landings: Brace life is limited to 35400 logged landings or 5900 hours flight time if landing are not

logged (assumed six landings per one hour of flight time).

(29)

Log all landings: Strut life is limited to 4170 logged landings or 696 hours flight time if landing are not

logged (assumed six landings per one hour of flight time).

(30)

Log all landings: Foot life is limited to 23780 logged landings or 3900 hours flight time if landing are not

logged (assumed six landings per one hour of flight time).

(31)

The following main rotor blades have a finite life of 2,500 hours or 15,000 torque events*, whichever occurs

first;

P/N 369D21100−517 with S/N H664, H665, H667, H669, H671, H672, H674, H676, H679, H680, H683

thru H724, H726 thru H999 and J000 thru J039, J041 thru J055 and

P/N 369D21102−517 with S/N 1976 thru 2100, 2106 thru 2115.

* TORQUE EVENT (TE) − A TE is recorded for every transition from forward flight to a hover (Reference

Service Bulletins SB369D−195R3, SB369E−088R3, SB369F−075R3, SB500N−015R3).

(32)

RIN = (200 x Hrs.) + (52 x TE).

(33)

RIN = (160 x Hrs.) + (24 x TE).

(34)

RIN = (153 x Hrs.) + (3 x TE).

(35)

RIN = (50 x Hrs.) + (3 x TE).

(36)

RIN = (768 x Hrs.) + (11 x TE).

(37)

After accumulation of 750 flight hours and 13,720 TE, perform Main Rotor Blade Torque Event Inspection

(Ref. Sec. 62−10−00) every 35 flight hours or 200 TE’s (whichever occurs first).

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(38)

The 369D21640−501, −503, −505, −507 tail rotor blades are two−way interchangeable with the 369D21613

tail rotor blades in sets of two only.

The 369D21641−501, −503, −505, −507 tail rotor blades are two−way interchangeable with the 369D21615

tail rotor blades in sets of two only (installed on the same inboard or outboard hub).

The 369D21642−501, −503, −505, −507 tail rotor blades are two−way interchangeable with the 369D21606

tail rotor blades in sets of two only.

(39)

The 369H1203−BSC, −11, −21, −31, −51 and −61 lead lag link assemblies can only be installed using the

369H1235−BSC bearing.

(40)

The 369H1203−53 lead lag link assembly can only be installed using the 369H1235−1 bearing.

(41)

The 369N2608−11 Control Support Bracket must be removed from 600N helicopters equipped with YSAS

(Ref. SB600N−040).

(42)

RIN = (29 x Hrs.) + (1 x TE).

(43)

The tension−torsion straps have a 5−year calendar life that starts the day the package is opened (Ref.

Sect 64−25−30). If the date the package was opened is unknown, the 5−year calendar life is based on the

manufacturing cure date.

For straps installed before 06 March 2008 on Model 500N helicopters serial numbers LN−001 thru LN−105

and Model 600N helicopters serial numbers RN003 thru RN074, the initial calendar replacement is based

on the cure date on the strap. Refer to Table 2 to find the expiration date.

(44)

500N5311−5 straps previously installed on MD900 helicopters are life limited to 2,500 hours when installed

on 500N and 600N series helicopters.

(45)

Use only on 600N helicopters without a yaw stability augmentation system (YSAS) (Pre−TB600N−006R1).

Table 2. Tension−Torsion Strap Expiration Date

Manufacturers Cure Date

Expiration Date

Before 03/1999

09/2008

03/1999 thru 02/2001

03/2009

03/2001 thru 02/2005

03/2010

03/2005 thru 02/2008

Cure Date Plus 5 Years

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MAINTENANCE MANUAL

UK CAA ALS SUPPLEMENT

1. UK CAA Airworthiness Limitations

Section Supplement

NOTE:

D The following components are further

limited when helicopters are operating

under UK CAA TC.

D Refer to 04-00-00 for all other Compo

nent Mandatory Replacement Times and

Component Mandatory Inspections.

Airworthiness Limitations

Component Mandatory Replacement Schedule

Component

Part Number

Finite Life

Mandatory

(1)

(2)

Hours (RIN)

Inspection

(1)

Hours

Main Rotor System

Drive shaft, main rotor

600N5510

14000

(1,000,000)

(3)

Tailboom

Tailboom assembly

600N3500−503

800

(4)

NOTES:

(1) Life−limited components interchanged between models or configurations must be restricted to the lowest

service life indicated for the models or configurations affected. Life−limited components removed at

retirement are to be destroyed or conspicuously marked to prevent inadvertent return to service. Parts are

applicable only on models under which a service life is listed.

(2) Service life shown for the basic (no dash number) part numbers apply to all dash numbered versions

unless otherwise indicated.

(3) RIN = (50xHrs.) + (3xTE)

(4) The 600N3500−503 tailboom may be reworked to a 600N3500−505 tailboom by modifying the attachment

fittings to all steel fittings.

REVISION:

DATE

FAA SIGNATURE AND DATE *

Initial Issue:

24 May 2000

* FAA approval in behalf of UK CAA per letter, Winnert to Wang, Ref. 9/33/0649/A26479, Dated 2 May 2000.

Page 1

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MAINTENANCE MANUAL

TABLE OF CONTENTS

Para/Figure/Table

Title

Page

05-00-00 Continued Airworthiness

Checks/Inspections

1. General Description of Inspections

A. Airworthiness Limitations

B. Continued Airworthiness

2. Documentation

A. Records of Aircraft Inspection

B. Additional Documentation

3. Visual Inspection Criteria

A. General Visual Inspection

05-10-00 Continued Airworthiness

Component Overhaul/Recommended Replacement

1. Component Overhaul or Recommended Replacement Schedule

Table 1. Component Overhaul Schedule

Table 2. Component Recommended Replacement Schedule

Table 3. Kamatics Component Overhaul Schedule

05-20-00 Continued Airworthiness

100-Hour or Annual Inspection Checklist

100-Hour or Annual Inspection

Table 1. 100-Hour or Annual Inspection

2. Retirement Index Numbers Attachment

Table 2. Permanent Record of Retirement Index Numbers/Torque Events

05-20-10 Continued Airworthiness

300-Hour Inspection Checklist

300-Hour Inspection

Table 1. 300-Hour Inspection

05-20-15 Continued Airworthiness

Yearly Inspection Checklist

1. Yearly Inspection

Table 1. Yearly Inspection

05-20-20 Continued Airworthiness

Special Inspections

1. Special Inspection Hourly and Calendar

Table 1. Special Inspections Hourly

Table 2. Special Inspections Calendar

Page i

05 Contents

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MAINTENANCE MANUAL

CONTINUED AIRWORTHINESS

CHECKS/INSPECTIONS

1. General Description of Inspections

(1). COMPONENT OVERHAUL/RE

COMMENDED REPLACEMENT

The following Continued Airworthiness

(Ref. Sec. 05-10-00) is a schedule for

Sections specify inspections and other main

the overhaul and recommended replace

tenance required under the Federal Aviation

ment of components and/or assemblies

Regulations unless an alternative program has

and scheduled maintenance checks.

been FAA approved.

(2).

100-HOUR OR ANNUAL INSPEC

NOTE: Because this manual pertains to MDHI

TION CHECKLIST (Ref. Sec.

model 369D, 369E, 369FF, 500N and 600N

05-20-00) is a schedule of inspections

helicopters (including the basic 500MD con

that must be accomplished every 100

figuration), it may contain inspection re

hours of helicopter operation or on a

quirements applicable to specific equipment

12-month (annual) basis.

not installed on individual helicopters.

An Annual Inspection is required on

When this situation is encountered, require

this helicopter for continued airworthi

ments that are not applicable should be dis

ness and may be accomplished in

regarded.

combination with a 100-hour inspec

tion.

The inspection intervals designated herein are

the maximum allowable and should not be

NOTE:

exceeded. When unusual local conditions, such

D To comply with the requirements of ser

as environmental conditions, utilization, etc.

vice bulletins which have been incorpor

dictate, it is the prerogative and responsibility

ated into the appropriate maintenance

of the operator to increase the scope and

and inspection manuals, the latest

frequency of the inspections as necessary to

100-Hour or Annual Inspection must be

ensure safe operation. Each item shall conform

used.

with the FAA Requirements, A.D.'s and

Manufacturer Bulletins and Letters. Over

D Refer to applicable Rolls-Royce Engine

flying the inspection interval, or any change

Operation and Maintenance Manual (Ref.

desired to the requirements of this chapter,

Table 201, 01-00-00) for detailed require

may be requested through the local aviation

ments on inspection of the engine.

regulatory authority.

(3).

300-HOUR INSPECTION CHECK

A. Airworthiness Limitations

LIST (Ref. Sec. 05-20-10) is a schedule

of inspections that must be accom

Refer to section 04-00-00 for mandatory

plished every 300 hours of helicopter

inspections and component mandatory

operation.

retirement schedule.

(4). YEARLY INSPECTION CHECK

B. Continued Airworthiness

LIST (Ref. Sec. 05-20-15) is a schedule

of inspections that must be accom

This section contains the requirements for

plished on a yearly basis.

Component Overhaul/Recommended Replace

ment, 100-Hour or Annual Inspection Check

(5). SPECIAL INSPECTIONS (Ref. Sec.

list, 300-Hour Inspection Checklist, Special

05-20-20) consist of inspections that

Inspection Schedule and Conditional Inspec

are contingent upon elapsed flight time

tions.

or calendar time.

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(a). Special Inspections Hourly should

shall include a visual examination of the area,

be referred to for additional inspec

component, detail, assembly, or installation

tion requirements that must be

and its surrounding environment, as well as

performed at specified periodic

any associated equipment within the immedi

hourly intervals.

ate vicinity, using any inspection aids con

sidered necessary.

(b). Special Inspections Calendar

should be referred to for additional

A. General Visual Inspection

inspection requirements that must be

A visual inspection that will detect obvious

performed at specified periodic

unsatisfactory conditions/discrepancies. This

calendar intervals.

type of inspection may require cleaning,

(6). CONDITIONAL INSPECTIONS (Ref.

removal of fillets, fairings, access panels/doors,

Sec. 05-50-00) includes inspection

etc.

requirements for unusual or other

(1). Metal parts (all metal parts, bodies, or

specific conditions or circumstances

casings of units in systems and in

that might occur.

electrical, instrument, and radio

installations, ducting, tubing, rods, and

2. Documentation

bellcranks). Inspect for the following:

A. Records of Aircraft Inspection

(a). Cleanliness, external signs of dam

age, leaks, overheating, discharge, or

(1). Aviation regulatory agencies require

fluid contamination.

pilot's, mechanics, owners and operat

ors to be familiar with, and to maintain

(b). Obstruction of drainage or vent holes.

records of aircraft maintenance,

inspections and repairs. This includes,

(c). Correct seating and sealing of

but is not limited to, Airworthiness

fairings and serviceability of fasten

Directives, Manufacturers Notices,

ers.

Scheduled Inspections and Time/Cycle

(d). Security of attachment, fasteners,

limited-life components.

and connections.

B. Additional Documentation

(e). Distortion, dents, scores, chafing,

pulled or missing fasteners, rivets,

(1). Additional documentation is required to

bolts, or screws.

be available, or inside the aircraft,

during operation. This documentation

(f). Signs of cracks or wear.

includes: Airworthiness and Registra

tion Certificates, Rotorcraft Flight

(g). Separation of bond.

Manual, Weight and Balance informa

(h). Failure of welds or spot welds.

tion and Radio Permits. It is important

that all required documentation be

(i). Deterioration of protective treatment

reviewed and revised as necessary

and corrosion.

during regular inspections, mainten

(2). Composite, rubber, fabric, fiberglass,

ance and operation of the helicopter.

and plastic parts (coverings, ducting,

3. Visual Inspection Criteria

flexible hoses, flexible mountings, seals,

insulation of electrical cables, windows,

Any time an area of the helicopter is visible

etc.). Inspect for the following:

during an inspection or maintenance action,

(a). Cleanliness, cracks, cuts, chafing,

the following ”Visual Inspection Criteria” shall

kinking, twisting, crushing, or

be accomplished without requiring disas

contraction -(sufficient free length).

sembly or removal of adjacent equipment

unless otherwise specified. It will normally

(b). Damage, delamination, or deteriora

apply to those areas, surfaces, or items which

tion.

become visible by the removal or opening of

access doors, panels, fairings, or cowlings. It

(c). Crazing.

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(d). Loss of flexibility (other than fabric

(b). If protective covers are required to be

covered component).

removed, check for cleanliness,

scoring, pitting or burning of con

(e). Overheating.

tacts, brushes for condition, and

security of exposed contacts.

(f). Fluid saturation.

(c). Overheating.

(3). Control System Components. Inspect

(d). Fluid contamination.

for the following:

NOTE:

For detailed Wiring Inspection criteria,

refer to CSP-HMI-3, Section 96-00-00.

(a). Correct alignment, no binding.

(5). Wire harness. Inspect for the following:

(b). Distortion, signs of bowing, scoring,

chafing, fraying, kinking, signs of

(a). Routing, contact with structure,

wear, flattening, cracks, or loose

proper support and protection.

fasteners.

(b). Strain at termination points, free

movement of shock-mounted or

(c). Deterioration of protective treatment

hinged equipment and proper slack

or corrosion.

for equipment installation and

maintenance.

(d). Electrical bonding correctly posi

tioned, undamaged, and secure.

(6). Inside fuel cell areas. Inspect for the

following:

(e). Attachments, end connections, and

(a). Leaks, cleanliness, foreign objects,

locking devices secure.

cracks.

(4). Electrical components (circuit protec

(b). Components for security and general

tion devices, wiring, connectors, plugs,

condition.

motors, generators, actuators, relays,

(c). Plumbing, and wiring for security,

solenoids, and contacts). Inspect for the

and general condition.

following:

(7). Markings, labels, and placards. Inspect

(a). Cleanliness, obvious damage, corro

for the following:

sion, security of attachments and

connections.

(a). Legibility and security of attachment.

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CONTINUED AIRWORTHINESS

COMPONENT OVERHAUL/RECOMMENDED REPLACEMENT

1. Component Overhaul or Recommended

overhaul/exchange. Any shaft or coupling

Replacement Schedule

removed for After Main Rotor Drive System

Sudden Stoppage - Level 2, conditional

Table 1 is the Overhaul Schedule. The listed

inspection requirements (Ref. CSP-HMI-2,

components or assemblies should be removed

05-50-00, Table 1) is not eligible for overhaul

from the helicopter and overhauled at inter

or exchange.

vals specified.

Neither the assignment of an airworthiness

Table 2 is the Recommended Replacement

life to a component nor failure to assign an

Schedule. The listed components should be

airworthiness life constitutes a warranty of

removed from the helicopter and scrapped at

any kind. The only warranty applicable to the

intervals specified.

helicopter and any components is that

Table 3 is the Kamatics Component Overhaul

warranty included in the Purchase Agreement

Schedule. The listed shafts and couplings

for the helicopter or the component.

should be removed from the rotorcraft and

overhauled at the interval specified. To be

NOTE: Hours for the 369F Model helicopters

eligible for the program, the shaft or coupling

will be the same as the 369FF unless other

must be serviceable before return to MDHI for

wise noted.

Table 1. Component Overhaul Schedule

Component (1)

Model

Part Number (2)

Hours

Main rotor transmission assembly

369D/E/FF − 500N

369D25100

3000

369D25100

4000

(12)

369D/E/FF − 500N

369F5100

5000

600N

369F5100

3000

Main rotor swashplate assembly

369D/E/FF − 500N

369D27609

2770

(3)(9)

600N

600N7630−3

2700

(4)(9)

Main rotor hub assembly

369D/E/FF − 500N

369D21200

2770

(7)(9)

600N

600N1200

2700

(7)(9)

Landing gear damper

369D/E/FF − 500N

369D26300

On Cond.

(6)

369D26301

On Cond.

(6)

600N

600N6300

On Cond.

(6)

Overrunning clutch assembly

369D/E/FF − 500N

369A5350−603

1800

(5)

369A5350−605

1800

(5)

369D/E/FF − 500/600N

369F5450

1800

(10)(11)

Tail rotor transmission

369D/E

369D25400

4800

369FF

3365

369D/E

369D25300

4800

Starter/Generator

(8)

369D/E − 500N

369A4550

1200

369FF − 600N

369D28550

1200

NOTES:

(1) Components interchanged between models or configurations must be restricted to the lowest service life

indicated for the models or configurations affected. Components removed at retirement are to be destroyed

or conspicuously marked to prevent inadvertent return to service. Parts are applicable only on models

under which a service life is listed.

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(2)

Service life shown for basic part number applied to all dash−numbered versions unless otherwise

indicated.

(3)

Bearing assembly must be relubricated every 2 years or 2770 hours, whichever occurs first (Ref.

CSP−COM−5, Sec. 62−30−10).

(4)

Bearing assembly must be relubricated every 2 years or 2700 hours, whichever occurs first (Ref.

CSP−COM−5, Sec. 62−30−60).

(5)

Under some operating conditions, overrunning clutch splines may need to be regreased more often than at

the 100−hour intervals and bearings may need to be regreased more often than at the 300−hour intervals.

With no cargo hook attached, inspect and regrease splines every 100 hours and bearing every 300 hours

(Ref. Sec. 63−10−00, Installation of Overrunning Clutch Subassembly and CSP−COM−5, Ball Bearing

Inspection and Grease Repack).

With cargo hook attached, inspect sprag assembly, inner race and outer race every 300 hours or 300 hours

of actual hook time when logged separately as per FAR 91.417, regrease clutch splines every 100 hours

and bearing every 300 hours (Ref. Sec. 63−10−00, Installation of Overrunning Clutch Subassembly and

CSP−COM−5, Ball Bearing Inspection and Grease Repack).

(6)

When inspected per Landing Gear Damper Inspection (Ref. Sec. 32−10−00 for 369D/E/FF − 500N, or Sec.

32−10−60 for 600N).

(7)

Use only main rotor hubs overhauled by MDHI or approved MDHI Licensees.

(8)

Refer to data plate to determine start/generator manufacturer.

(9)

The shelf life of bearings preserved with grease is limited to 4 years.

(10)

Regrease overrunning clutch bearings every 300 hours (Ref. CSP−COM−5, Sec. 63−10−15).

(11)

Interim hours: life extension testing in progress.

(12)

The 369D25100 main rotor transmission overhaul time may be extended from a mandatory 3000 hour

overhaul time to a mandatory 4000 hour overhaul time, provided, the transmission is operated with Mobil

SHC626 since last overhaul.

The transmission shall not exceed 3000 hours if cargo hook time has reached a quantity of 750 hours.

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Table 2. Component Recommended Replacement Schedule

Component (1)

Model

Part Number (2)

Hours

Tail rotor swashplate (duplex) bearings

369D/E/FF

369D21832

On Cond.

(3)(9)

Fan support bearing

500/600N

500N5364

2400

(8)(9)

Pitch plate bearing

500/600N

500N7120

2400

(8)(9)

Thrust bearing cup, upper

369D/E/FF − 500N

369D21255

On Cond.

(3)(9)

Thrust bearing cone, upper

369D/E/FF − 500N

369D21254

On Cond.

(3)(9)

Thrust bearing cup, upper

600N

369D21255

600

(5)(9)

Thrust bearing cone, upper

600N

369D21254

600

(5)(9)

Thrust bearing cup, lower

369D/E/FF − 500N

369D21257

On Cond.

(3)(9)

Thrust bearing cone, lower

369D/E/FF − 500N

369D21256

On Cond.

(3)(9)

Thrust bearing cup, lower

600N

369D21257

5400

(4)(9)

Thrust bearing cone, lower

600N

369D21256

5400

(4)(9)

Bearings, oil cooler blower

369D/E/FF − 500/600N

369H5655−3

1200

369D/E/FF − 500/600N

369H5655−5

1200

Belt, oil cooler blower

369D/E/FF − 500N

369D25623

1200

600N

93920219

1200

Cyclic stick trim switch

(7)

369D/E/FF − 500N

A218−100646−02

1000

NOTES:

(1) Limited−life or scheduled replacement components interchanged between models or configurations must

be restricted to the lowest service life indicated for the models or configurations affected. Limited−life or

scheduled replacement components removed at retirement are to be destroyed or conspicuously marked

to prevent inadvertent return to service. Parts are applicable only on models under which a service life is

listed.

(2) Service life shown for basic part number applied to all dash−numbered versions unless otherwise

indicated.

(3) Bearing assembly must be relubricated every 2 years or 2770 hours, whichever occurs first (Ref. Sec.

64−30−00, Tail Rotor Swashplate Bearing Regreasing).

(4) Bearing assembly must be relubricated every 2 years or 2700 hours, whichever occurs first (Ref. Sec.

62−20−60, Main Rotor Hub Tapered Bearing Grease Repack, Inspection and Replacement).

(5) Bearing assembly must be relubricated every 2 years or 300 hours, whichever occurs first (Ref. Sec.

62−20−60, Main Rotor Hub Upper Bearing Grease Repack, Inspection and Replacement).

(6) Deleted

(7) Installed in 369D27133 grip assembly made by Guardian Electric Co., PN A218966714−00 (Ref. Sec.

67−10−20, Cyclic Stick Grip Switch Replacement (Standard Grip)).

(8) Bearing assembly must be relubricated every 2 years or 1200 hours, whichever occurs first (Ref. Sec.

64−25−30, Anti−Torque Fan Bearing Regreasing).

(9) The shelf life of bearings preserved with grease is limited to 4 years.

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Table 3. Kamatics Component Overhaul Schedule

Component

Part Number

Serial Number (3)

Initial TBO Date

Next Overhaul

Interconnecting Shaft

369D25515

0001 thru 0535

2010 − 2011

2021

(1)

Interconnecting Shaft

369D25515

0536 thru 1070

2012

2022

(1)

Interconnect Shaft

500N5215

0001 thru 0516

2013

2023

(1)

Interconnect Shaft

500N5215

0517 thru 1017

2014

2024

(1)

Interconnect Shaft

500N5215

1018 thru 1550

2015

2025

(1)

Interconnect Shaft

500N5215

1551 thru 1667

2016

2026

(1)

Interconnect Shaft

500N5215

1668 thru 1777

2017

2027

(1)

Interconnect Shaft

500N5215

1776 thru 1824 (2)

2018

2028

(1)