ROBINSON F\44e

MAINTENANCtr MANI.]ALAND INSTRUCTIONS FORCONTINUED AIRWORTHINESS

I

ROBINSON HELICOPTER COMPANY, TORRANCE. CALIFORNIA

FIG|BINEiCIN

MATNTENANeE MANUAL CONTENTS

MOEIEL

F|44

ClassS Revision Serviceform ComponentReturn/Authorization form Recommended ChangeReportform Limited Warranties 1.000 2.000 3.000 Ge n e ra l Inspection Life-Limited Componentsand OverhaulSchedules AirworthinessLimitations 4.000 5.000 6.0O0 7.000 8.000 9.000 10.000 1 1.000 12.00O 13.0O0 14.000 15.000 16.000 17.000 Airframe Landing ar Ge Powerplant DriveTrain FlightControls Rotor Systems Ri g g i n g T ra ck a n d B a l ance , Heating,Ventilation,and Air Conditioning Fuel System I nstru me n ts Electrical and Avionics Systems Furnishings S p e ci a T o o l s l Re vi si o n o g L

13: Change OCT2006

ill

FIOBINSCIN

MATNTENANeE MANUAL

MoE EL pt44

blank IntentionallY

iv

C h a n g e1 3 : O C T 2 0 O o

FIClBINSiclN

MATNTENANcE MANUALClassS Revision Service

MODEL

F|44

ClassS revision to is this manual service required ensure remains current. ClassS subscribers will receivefuture issuesof the followingfor a periodof one year:

Safety Notices to Revisions R44 Pilot'sOperating Handbook R44 ServiceBulletins R44 Service Letters Revisions R44 Maintenance to Manual& lllustrated PartsCatalog lf you wish to order class s revisionservice,pleasesend a check {drawn on U.s. bank} o r mo n e y o r d e rfo r U S $ 3 0 .0 0to : R OB INSON HELICOPTER COMPANY Attn: Publications 2901 Airport Drive T o r r a n c eC A 9 0 5 0 5 - 6 1 5 , 1 UNITED STATES

v

Pleaseprint your name,completeaddress, and phonenumberin the spaceprovided below and returnthis page with your check or money order.

JtL

m8

lf you own an R44 helicopter, pleaseindicateship seriarnumber

Change 7r O6iDec 99

v

Robinson Helicopter tRHCI Go. 2901 Airport Drive T o r r a n c e ,A 9 0 5 0 5 - 6 1 1 5 , S A C U

Phone: 539-0508 {31O} F a x :( 3 1 0 ) 3 9 - 5 1 9 8 5 FAA CRS YV3RO1 2M

COMPONENT RETURN/AUTHORIZATIONA copy of this form must accompanyANY parts or componentsreturned to RobinsonHelicopterGompany. A.O.G. to I acceptthe expediting charge($50.00 U.S., $60.00 Foreign), insurethat work is commenced within (1) work day.

SUBMITTED BY: Name: CompanyTelephone: Email: COMPONENT DATA: Component Part No: or SerialNo: Hours in Service: Date of last repair: Reason return: for

ContactName: Fax No:

ROTORCRAFT DATA: Rotorcraft S/N: Total Hours: Registration No: Registered Owner:

R22

R44

WORKREOUESTED:None (seewarrantyclaim section) Overhaulin accordance with RHC price list Core credit. Core chargedon RHCinvoiceno. WARRANTYCLAIM: work requested replaceunderwarranty or _Perform part purchased RHCinvoiceno. credit. Replacement on _lssue THE ABOVE WARRANTYIS BASEDON: Rotorcraftlistedabove is under warranty w C o m p o n e np u rch a se d i th i n one ( 1) yearon RHCinvoiceno. t INFORMATION: SHIPPING Address: Carrier: URGENT SHIPNEXTDAY AIR URGENT SHIP2ND DAY AIR Repairestimateonly Repairas necessary, cost not to exceed $

I certifv that the above componentand rotorcraft data is correct in accordancewith FAR 91.417 and hereby materials. the above work to'be comoletedincludinq of RHC authorize orocurement and installation necessarv employeesmay operatethe compondntat my risk foi tne purposeof testing, adjusting,inspeclion, delivery. or RHC is not responsible loss or damageto the componentin case of theft, fire, accident,or any other causes for beyond the control of RHC. A mechanic'slien on the componentto securethe amount of repairsand storage and charges herebygranted.Any component is left at RHCbeyondsix monthswill be considered abandoned will be disposed . I agreeto pay the full amount in cash upon deliveryof the component.RHC will retainall scrapped of parts.The abovecost estimatemay not be exceeded or replaced without my approval.

PRINT NAME: SIGNATURE:Change13r OCT 2006 RSF 205 REV F

DATE:

vrc

FIGIBINSCIN

MATNTENANcE MANUALR OB IN S ON HELICOPTER COM PANY PUBLICATIONS T E C H NICAL

M(fElEL

Fl44

R E C OMMENDED CHANGE REPORT Periodicrevisionsof this manual will be made to incorporate the latest information.lf, in the opinion of the reader,any informationhas been omitted or requiresclarification or correction,pleasedirect your comments to RHC using this form {or a duplicate}.Such informationwill be includedin future revisions. Send recommendations to: Technical Support Robinson Helicopter Company 2901 Airport Drive T o rra n ceCalifor nia , 15 90505- 61 STATES UNITED P h o n e :( 3 1 0 ) 5 3 9 - 0 5 0 8 Fax: { 3 1 0 )5 3 9 - 5 1 9 8 ldentification: He l i c o p t e M o d e l : r Ser ial Num ber :

!

-

Remarks/Recommendations:

Change 7: OB Dec 99

tx

ROBINSON HELICOPTER COMPANY, INC. LIMITED AIRCRAFT WARRANTY Effective R22 S/N 3318 & on; R44 S/N | 2O2 & on RobinsonHelicopter Company, lnc. (hereafter referred to as RHC) warrants each new helicopter to be free from defects in material and workmanship appearing within two years from the date of delivery from the RHC factory or during the first one thousand (lOO0 hours of operation, whichever event occurs first; provided, the aircraft has been subjected to normal use and service. This Warranty is limited to repair or replacement on an exchange basis, as selected by RHC, of any part, which upon examination bV RHC is deemed to have been defective when the aircraft left the factory. A new warranty period is not established for parts replaced under the terms of this Warranty. Such replacement parts are warranted only for the remainder of the original warranty period. This Warranty shall not apply to any helicopter or part which has been repaired or altered outside the factory, and which, in RHC's judgment, has affected the performance or reliability of the helicopter or part. This Warranty shall not apply to any helicopter or part which has been subject to corrosion, misttse,negligence or accident, nor to any parts normally replaced during routine maintenance, such as, air cleaners, skid shoes,rod end or spherical bearings,light bulbs, ete. This Warranty shall not apply to any helicopter, which has been crated for shipping unless sueh crating is performed by RHC. RHC is not responsible for the cost of shippingparts under the terms of this Warranty. However, RHC will credit the RHC Dealership, which sold and delivered the new helicopter to its original owner, with an allowance for labor performed by that Dealership for removing and reinstalling the defective part. No credit will be issued for trouble-shooting. RHC makes no Warranty with respect to batteries, instruments, avionics or other trade accessories since they are usually warranted separately by their respective manufacturers. New aircraft are equipped with new engines which have a separate Lycoming limited warranty. ADDITIONAL WARRANTY FOR MAIN & TAIL GEARBOXES ln addition to the warranty specified above, an extended pro-rated warranty shall apply to the main and tail gearboxes for the first 22OO hours of service or three years from the date of manufacture, whichever event occurs first. During this period, if a gearbox must be overhauled due to failure of a part which was defective when it left the factory, RHC will pro-rate the cost of the overhaul by dividing the hours in service bV 22OO or the months in service by thirty-six (36), whichever fraction is greater. THE FORGOING WARRANTY IS EXCLUSIVE AND IS GIVEN AND ACCEPTED IN LIEU OF ANY AND ALL OTHER WARRANTIES AND REPRESENTATIONS. EXPRESS. IMPLIED. OR STATUTORY. WHETHER WRITTEN OR ORAL, INCLUDING WITHOUT LIMITATION FITNESS FOA A PARTICULAR ANY IMPLIED WARRANTIES OF MERCHANTABILITY. PURPOSE OR TRADE USAGE, THE REMEDIES OF THE BUYER SHALL BE LIMITED TO THOSE PROVIDED HEREIN. IN NO EVENT WILL THE MANUFACTURER BE LIABLE FOR LOSSES FESULTING FROM TOSS OF USE OF THE HELICOPTER. COLLATERAL, CONSEAUENTIAL OR SPECIAL DAMAGES, OR ANY OTHER COSTS. Warranty adjustments with respeet to any helicopter or parts manufactured by RHC will be made only upon compliance with the following procedure: (1) The defective part or assembly, together with a written Warranty Claim, must be returned to RHC not later than thirty (3O) days after discovery of the defect nor more than thirty (3O16sr" after expiration of the Warranty period. RHC will, after inspection, determine whether the material or part was defective when it left the factory and will respond accordingly. Final determination of a Warranty adjustmenf resfs with RHC.ROBINSON HELICOPTER COMPANY. INC. 29Ol Airport Drive Torrance, California 90505 U.S.A.

A

Effective 1 February 2OO3

Change9: FEB2OO3

X]

COMPANY'INC. HELICOPTER ROBINSON WARRANTY PARTS LIMITEDRHq warrants each new helicopter RobinsonHelicopter company, lnc. (hereafter referred to as one year from the .within part to be free from defects in material and workmanship appearing(l O)q hours of operation' thousand date of detivery from the RHC factory i, Jirirg the firs.tone proviAeJ, iie p"art has been subiecte-dto normal use and service' whichever event occurs first; as basis-, selected bY BHC' of This warranty is limited to repair or replacement on an exchange defective when the part left nV-hii it de.e.1t9d have been any part, which upon .to for "*u.in'ation period'is not established parts reppcgd under the terms of this the factory. A new warranty parts,r" iurrunted only for'the remainder of the originalwarrantY Warranty. Suchreplacement reinstallation of parts under for period. RHC is not responsible th.tecost of removing, shipping, or which has been repaired This warranty shattno-t ipply'io the terms of this wiiiritv. "hy.partaffected the perfarmance in RHC's iudgment, has or altered outside ln" fu"tory, anA iiici, i'nail not appty {o any part which has been subiect to or retiabirity of the part. This warranlyparts.normally replace! !u1ing- routine corrosion, misuse, negligence or accident, nor to any rod eid or spherical bearings, light bulbs, etc' ikid uii ai, c,teaners, maintenan"", "hor", "u"h avionics or other trade aceessories RHC makesno warranty with respectto batteries,instruments, manufacturers' since they are urrutly warranted separately by their respective ADDITIONAL WARRANTY FOR MAIN & TAIL GEARBOXES pro-rated warranty shall applY.to the tn addition to the warrantY specified above, an extended or three years from the date of main and tail gearbor", ior'the first )2OtO hours of service period' if a gearbox must be overhauled manufacture, whichever event o""uu irrt. During thls it teft the factory, RHC will pro-rate the cost due to failure or a pari which was dife,ctive whei the months in service by thirty-six of the overhaul by dividing the houis ii ""lrui"" by 22oo or (36), whichever fraction is greater.

oF ANy ANDALLorHER wARRiiiifes-nno REPRESENTATIONS' LtMtrATtoN wt.THour 'rnEnciaNTABiLITy, oR srATUToRy, qHETHERwRiiiEi oc oa,a, N0LU_D\NG FtrNE-lsoi FoR A PART,,ULAR ANy tMpLtEDwARRANTtEs 9HALLBELtMtrEDTo or rHE BUYER (tsAGE,rnE'tiEuEoiies puRposE nRADE oR BE pRovtDED HEREIN. w'aii-Ev-Eni wttt THE MANUFACTURER LIABLE THosE COLLATERAL' oF THEHELI0OPTER' FoR LossEsaEsuLTtNGFRIM'ioss- o'r usE cosrs' oR coNsEaUENnAI-oi ipecnL DAMAGES, ANY oTHERby RHC will be ma Warranty adjustments with respect to anY helicopter or parts manufactured onty upon compliance with the following procedure: (1) Claim' must be The defective part or assembly, together wilh a written Warranty (3O) days after discovery of the defect nor returned to RHC not later than thirty period' more than thirty (3O) days after expiration of the Warranty part was defective RHC will, after inspection, determine whether the material or Finat determination of a when it teft the factory ana iitt respond accordingly. Warranty adiustmenf resfs with RHC'

AND ACCEPTED IN LIEU THE FORGOING WARRANTY IS EXCLUSIVE AA!? IS GIVEN IMPLIED' ExPREss'

do

e)

Ol June 06

ROBINSONHELICOPTERCOMPANY' INC. 2901 AirPort Dfive Torrance, California 90505 U-S.A'

xil

Change13: OCT 2006

1. GENERAL

FICIEINEiCIN

MATNTENANeE MANUAL SECTION 1 GENERAL

MOE EL 1l'44

1.OOO INTRODUCTION1 . 0 0 1 M a n u a lN o ta ti o n s 1 . 0 0 2 M a n u a lR e vi si o n s 1.003 Maintenance Authorization 1.004 OverhaulAuthorization 1.O05 CustomerSupport 1 . 0 0 6 Ex t ern aD i me n si o n s l 1.OO7 VersionDescription 1 .1O OH E L I C OP T ES E R V IC IN G R O 1 . 1 0 1 S c h e d u l e d i n te n a n ce n d Inspections Ma a 1. 1 0 5 C a l i b ra ti o n f T o o l s o 1 . 11 O L u b ri ca ti o n Ge n e ra l 1.1 15 Chip DetectorCleaning 1 . 1 2 O M a i n R o to rGe a rb o x ra i nand Flush D 1. 1 3 0 T a i l Ro to rGe a rb o x ra i na nd Flush D 1 . 1 4 0 C l u tch -A ctu a toL o w e r B e ar ing r Lubr ication 1 . 15 0 D e fu e l i n g 1. 1 6 0 S t o r a g e 1 .170 HydraulicReservoir FilterReplacement 1. 1 8 0 D r a in i n g n d F l u sh i n g yd r aulic a H System 1 . 1 9 0 B l e ed i n g yd ra u l i c yste m H S 1 . 2 0 0 H A N D L | N G , J A C K | N G ,O t S T t N G , E V E L T NA N D W E | G H | N G H L G 1 . 2 1 O G r o u n dH a n d l i n g 1 . 2 1 1 G r o u n dH a n d l i n g e e l sl nstallation Standar d Wh Landing Gear 1 . 2 1 2 G r o u n dH a n d l i n g e e l sInstallation FloatShip Landing Wh Gear 1 . 2 1 3 M o vi n gth e H e l i co p teo n Gr oundHandling heels r W 1 . 2 1 4 M a i n R o to rB l a d eT i e -D o wns 1.215 Parking 1.216 Trailering

C h a n g e 3 : O C T2 0 O o 1

Page f .i

FIClBINSiclN

MAINTENANcE

MANUAL

MtfE

EL ]I44

JACK 1.200 HANDLING,

(CONt,d) AND WEIGHING LEVELING, HOISTING,

'1.22OJacking, Hoisting,and Leveling a 1 . 2 3 O W e i g h i n g n d C G C a l cu l a ti on WeighingProcedures 1.231 Helicopter 1.24O BallastInstallation R T 1 . 3 O 0 F AS T EN E R OR OU E E OU IR EM ENTS 1.31O General 1.32O StandardTorques l 1 . 3 3 O S p e ci a T o rq u e s LIST MATERIALS 1.4OO APPROVED 1. 4 1 O Pa i n tS tri P P e rs a 1 . 4 2 O S o l v e n ts n d C l e a n e rs a 1 . 4 3 O F i l l e rs n d P u ttY 1 . 4 4 O T o r qu eS e a l 1.45O Primers 1 . 4 5 5 P o w d e rC o a t 1 . 4 6 0 P a i nts 1 . 4 7 O L u b r i ca n ts a 1 . 4 8 O Ad h e si ve s n d S e a l a n ts 1.490 StorageLimits 1 . 5 O O( R E S E R V E D ) 1 . 6 0 0 P A R TI N T E R C H A N GE A B IL ITY R T R G, FO 1 . 7 O O I N S T R U C T I O N S RU N C R A T I N G ,E A S S E M B L I NA N D F L I G H T E S T I N G 4 4 H S E R I E S E L IC OP T E R S ( DATA)PLATES IDENTIFICATION C R E P L AC E ME N TOMP ON E NT

Pag ef . i i

14: JUL 2008 Change

FICIBINSiEIN

MATNTENANcE MANUALSECTION 1 GENERAL

MOEIEL

F'44

1.OOO INTRODUCTIONThis manualcontainsreferencematerialnecessary the properservicing,maintenance. for and handlingof the R44-series helicopter.This manual is to be used in conjunctionwith the R44 and R44 ll Pilot'sOperatingHandbooks(POH),R44 lllustrated PartsCatalog(lPC), R44 ServiceBulletins,R44 ServiceLetters,Lycoming0-5401 lO-540 Operator'sManuals publications, and enginemaintenance by and applicable technicaldata supplied component manufacturers. As necessary, Service Bulletins are issued by Robinson Helicopter Company (RHC), Lycoming, and component manufacturers.Service Bulletin compliance is mandatory. RecentR44 ServiceBulletins(SB)and ServiceLetters(SL)are available the internetat on RecentLycomingServiceBulletins available www.lycoming. at www.robinsonheli.com. are textron.com and recent Teledyne Continental Motors (TCM) ignition systems Service Bulletins at are available www.tcmlink.com. O Always read instructions completelybefore beginning task. a 1.001 ManualNotations The following notationswill be found throughoutthe manual: WARNING Personal injury or death can result if a WARNING is not followed. CAUTION Equipment damagecan result if a CAUTIONis not followed.

NOTEexplanation. A NOTEprovidesemphasisor supplementary 1.002 ManualRevisions Beforeusing this manual, be sure it includesall current revisions.A list of all applicable be in revisions contained Section17.OOO. a new manualis purchased, sureto complete is lf found in the front of the manual;this will insure and mail the revisionserviceapplication publication that you receiverevisionsfor a one-yearperiod.A list of all current Robinson revisions can be accessed the internetat www.robinsonheli.com. on Authorization 1.003 Maintenance completeda factoryOnly appropriately certificatedmechanicsthat have successfully sponsoredmaintenancecourse, or are under direcr!supervisionof such mechanic, may perform maintenance, in repairs,or inspectionEiescribed this manual. The daily preflightmay be accomplished the above-stated mechanicsor pilot/ownerafter careful by study of the appropriatesections of the Pilot's OperatingHandbook,Some preventive maintenancemay be performed by the pilot after receivingappropriateinstructionsin Regulations. with the Pilot'sOperating FederalAviation accordance Handbook applicable and C h a n g e1 4 : JU L 2 OO8 P a g e1 . 1

FIclBINEiClN

MAINTENANeE MANUAL

MI)EIEL ]n44

1.004 OverhaulAuthorization that have completedspecialRHC factory certificatedmechanics Only appropriately and and possessspecia.ltools technical coursesfor overhluringipecific components or repair major o"ti-i"ppii"o uv CnCuj" authorizebto disassembleand overhaul componentsas requiredby Section3. 1.005 CustomerSuPPort .

T e l e p h on e : (3 1 0 ) 5 3 9 -0 5 0 8 - Main Switchboar d ( 3 1 0 )5 3 9 - 5 1 9 8 Fax: TechnicalSuPPort: E-mail:

E sio xten n'

customerservicb@robinsonheli'com 208

Po?'" ro b s h I m ltr1o l"iil#J.9ifl: [H"J$"ii"3iri, roin on ei.coChris Sennett,ts3@robinsonhe.li'com

Includethe following informationwhen contactingTechnicalSupport: model Helicopter H e l i co p tese ri a ln u mb e r r total time (TT) Helicopter time since overhaul(TSOH) Helicoirter Componentname ComponentPart number time since repairor sinceoverhaul Comironent Parts Ordering: - par -[l-isp a re s@ro b insonheli.com tsilndacc- epsor yor der ing E - ma i l : (habla'espafiol), cs2@robinsonheli.com Catry Obando Extension, 216 Lea 6ass, cs3@robinsonheli.com cs4@r obinsonheli.com 2 2 2 Ja cki eGaspar o, cs5@r obinsonheli.com 2 O7 Je a n n eShaw, 245 SandraAure, cs6@robinsonheli.com 2O4 Sandy Nuffez,cs7@robinsonheli.com ReturnedParts: All parts returned to Robinson HelicopterCompany must have.an attached 205) to avoid delaysin processing. form ('RSF ComponentReturnAuthorization in the front of this manual. Return parts to: A copy of the form is included Attn: RepairStation Com pany HelicoPter Robinson 2901 Airport Drive 1 Torrance,California 9 0 5 0 5 - 6 1 5 UNITEDSTATES Subscriptionsand Factory MaintenanceTraining Courses: ad1@robinsonheli.com E-mail: Kohler Ex te n si o n : 2 0 9 Ma l l o rY P a g e1 . 2 1 Change 4: JUL 2008

FIclBINSclN

MAINTENANeE

MANUAL

MOEIEL

F'44

1.OOO EXTERNAL DIIIENSIONS

R O T O RR A D 1 9 8 I N .

(30 INCHES t'tINIMUM TAIL SKID HEIGHT I'IEASURED FROM LEVEL GROUND UP)

353 lN. 459 IN. OVERALL

29 lN, I

Fla4 & Fl44 II IEXTERNAL IMENSIONS D

.Y

I I

I I

1 2 9 I N . STANDARD LANDING GEAR. 1 3 0 . 5I t . FLoAT HrGH (EXTENDED) 0R LANDING GEAR)

C h a n g e1 O :J U L 2 O O 4

P a g e1 . 3

FIClBINEiclN

MAINTENANcE

MANUAL

MODEL1f,'44

DlllENsloNs (conr'o) r.006 EXTERNAL

353 lN. 459 IN. OVERALL

Fl44&rrot(44 Clq',r- II(shown with fixed utilitYfloats) D EXTERNAL IMENSIONS

P a g e1 . 3 A

C h a n g e1 O :J U L 2 O O 4

FIC|BINEiG|N

MATNTENANcE MANuAL

MOEIEL

]l,44

1.007 VersionDescription (alsosee Type CertificateData Sheet in Section3) R44, "Astro": 4-digit serial numbers 0002, OOO4 thru 0760. Textron Lycoming O-54O-F185engine derated to 2Ob horsepower maximum horsepower; 225 horsepower 5-minute takeoff rating. Manual controls (electricautomatic trim and groundadjustable collective trim). Grossweight 24OO pounds.14-volt electrical systemstandard; 28-volt optional.optionalhydraulic cyclic & collectivecontrolb. Based "Astro". Fixedor pop-outfloat landing on gear.Additional corrosionprotection.Auxiliaryhorizontalstabilizer installedat base of lower verticalstabilizer. Drainvalvesinstailedin chin. Additional navigationlights atop mast fairing on fixed froat versions. Marine radio package optional. optional hydraulic cyclic & collectivecontrols. Hydraulic cyclic & collective controls standard. Adjustabre pilot-side pedals.Serialnumber0761 and higher. WARNING R44 ll (fuel injectedl helicopters require two A2Ob-7 forks, A600-6 manifold pressule gage, two C0Ob-8 main rotor blade & spindle assemblies (two C016-5 main rotor blades & two C157-2 pitch horns), COO6-5main rotor gearbox, COO8-4tail rotor assembly {two CO29-2 tail rotor blades),two C016-5 main rotor blades,CA17-4swashplate,three C121-31 push-pull tubes, two C2O3-5 yokes, C2O4-2arm (stainlesssteel, lowerl, C2O4-3 arm tstainlesssteel, upper!, CT9Z-4 dual tachometer, D201-5 support weldment (forward hydraulic servos), and D2O4-8 suppoft weldment (aft hydraulicservo). R 4 4 l l , " R a ve nl l " : 5 -d i g i tser ialnum ber s1OOO1& later .Longerchor d main r otor blades.Textron LycominglO-540-AE1A5fuel-injected engine derated to 2O5 horsepower maximum continuous power; 245 horsepowerS-minutetakeoff rating. Gross weight 2bOO pounds. 28-volt electricalsystem. Solid-statemagneto start booster. Second oil cooler. Roundedtip main and tail rotor b l a d e s.

R44 "Clipplr", "C l i p p e r " : l

R44, "Raven", "R a v e nl "

R 4 4 l l , " C l i p p e r l " : S i mi l a r R44 "Clipper ", l to but basedon "Ravenll" InstrumentTrainer: R44 or R44 ll configurationwith 1O-holeinstrument panel. VMC operations only. E. N . G .(E l e ctro n i c R44 or R44 ll configuration. 28-volt electricalsystem. NoseN e w s Ga th e ri n g ): mountedgyro-stabilized camerawith tailcone-mounted battery. Standardmicrowavecapability. Police: R44 or R44 ll configuration. 28-volt electrical system.Includes searchlight,police radio package, and nose-mountedgyrostabilized infrared-capablecamera with tailcone-mounted battery. Optionalmicrowavecapability. Change 4: JUL 2008 1 P a g e1 . 3 B

FIGIBINSCIN

MAINTENANeE

MANUAL

MC'E'EL

F|44

R 1 . 1 O O H E L I COP T ES E R V IC IN G a Ma 1 . 1 0 1 S c he d u l e d i n te n a n ce nd Inspections to in and furthermaintenance inspections addition the following require Somehelicopters Coniult aircraft maintenance records, new f,eiicopt.lq. minimum requ-ii6nie-irt-i-toi and Limitations., Airworthiness ServiceBulet'riisJ$Bi;-;"i;iion reguiaiiori+_nirworthiness

to listed Publications aresubject revision. Direii'r"'iAijii;;;ii"riiTC ippiiEJuitltV-F l i g h tT i m e First 29 hours:

Change oil and filter and inspect oil suction screen and filter per Lycoming SB48OE. Check alternatorbelt tension per Lycoming ServiceInstruction{Sl}1 1 298' Inspect and service engine per Lycoming Operator's Manual, EverybO hours: oil, oil fi l ter , AD S l 1 O8 OCa n d ( as r equir ed) 2008- 06- 51. Change , and inspect oil suction screen and removed filter per Lycoming S B 4 8 OE . Drain and flush gearboxe's per Sections 1'120 & 1 . 1 3 0 . First 1Oo-hour Check engine exhaust valve guide clearance per LVcominO lnspection: a sB388C. per Lycoming Ev e r y1 O 0 h o u rs: Inspectper Section2.400. Inspectand serviceengine ( Sl1 s8366, Sl1O8OB, 1298, andSB342E l O- 540 Manual, o p e ra to r,s only). As required,inspect and serviceTCM ignitioncomponents p e r T C M 5 8 6 438. f hydr au l i ci l ter per C Every30O hours: L u b ri ca te 181- 3 bear ing Section1.14O.Replace v al v e p e r S e cti o n1 .170. Inspectvalvesand check engineexhaus t per LycomingSB3O1B,SB388C, and Ope r ator 's g u i d e cl e a ra nce Manual. per Sections1 .120 & 1.130. C l ean Every5OOhours: D ra i n a n d fl u sh gear boxes per Section 1.115. Verify magneto drive gearbox chip detectors iushion pliability. Service collective spring assembly (manual inspectand service controfsonly) per Section8.221. As required, TCM ignitioncomponentsper TCM 58658 and 586634' per Section2-7OO. Every22OOhours: Overhaulhelicopter (in Calendar additionto precedingrequirements) Every4 months: Change oil, oil filter, and inspect oil suction screen and removed filter per LycomingSB48OE. Ev e r y1 2 mo n th s: Inspectper Section2.400. Cleangearboxchip detectorsper Section locatortransmitter(ELT)per 14 CFRPart 1 .1 15. Inspectemergency 91.2O7.Inspectoptionalpop-outfloats per Section5.630. per Every24 months: T e st a n d i n specttr ansponder 14 CFRPar t91' 413' per Section1.140. Inspectoptio nalpopC L u b ri ca te 1 81- 3 bear ing Every3 years: cylinder' test pressure out floats per Section5.640. Hydrostatic OverhaulTCM magnetosper TCM 586438. Verify magnetodrive Every4 years: cu sh i o np l i a bility. and limitedoverhaulper Section2.600, Perform 12-yearinspection E v e r y1 2 y e a r s : l o r o ve rh a u per Section2.7OO.

P a g e1 . 3 C

1 Change 4: JUL 2008

FIC|BINEIC|N

MATNTENANeE MANUAL

MOE,EL

F.44

1.105 Calibration Tools of The dimensionsand tolerancesgiven in this maintenancemanual are critical. RHC recommendsmeasuringtools be calibratedat least once a year. This includestorque and balancing wrenches,micrometers, calipers, dial indicators, springscales,protractors equipment. WARNING Proper torque is critical. Always use calibrated wrenches and undamaged, properly lubricated (where applicable) hardware. Ensure all clamping surfaces are clean, and clamp only bare metal or wet-primed surfaces. lmproper tolque or dirty or painted clamping surfaces may result in loss of clamp-up, hardware or and prematurefailure. 1 . 1 1 0 L u b ri ca ti o n Ge n e ra l Most bearings in the R44 are sealed or self-lubricated and do not require periodic lubrication; bearings with specificlubrication intervals noted in Section1.101 . Engine are lubricationrequirementsare contained in the Pilot's OperatingHandbook, Lycoming Operator'sManual and LycomingServiceInstructionNo. 1O14 (currentrevision).Main and tail rotor gearboxesrequireadditional when indicatedby sight plug reading. oil WARNING The only approved lubricant for use in the main rotor and tail rotor qearboxesis Robinson A257-2lubricant. When a new or overhauled gearboxis installed, must be drainedand flushedafter the it first 4 hours of flight or first chip light, whicheveroccurs first, and again at the next 1OO-hour inspectionafter installation. Thereafter, drain and flush gearboxes intervals at per Section 1.101. Additionally, changegearboxoil and cleansight plug glasswhenever oil becomesso dirty that its level cannot be determined.

C h a n g e1 3 : OC T 2 0 0 6

P a g e1 . 3 D

FIGIBINEION

MAINTENANeE MANUAL

MIfEIEL

H44

1 .1 15 Chip DetectorCleaninq on film of varnishcan accumulate a Duringnormalgearboxoperation,an insulating chip dltector,s magneticprobe and preventgearboxchip warning light illumination. CleanchiP detectorbY: securingchip detector. Disconnecr 1. Removeand discardsafety wire (if applicable) locatedseveralinchesfrom chip detector. chip detectorwiring at quick-disconnect For tail rotor gearbox,place containerbeneathto catch oil. Removechip detector from gearbox. by 2. Cleanand scrub chip detector with a toothbrushand cleaningsolvent,followed air drying with compressed or a lint-freecloth' wiring, 3. Check chip detector circuit function by connectingchip detectorelectrical magnetic probe to turning MASTERswitch on, and groundingdetector's central gearboxchip warning light illuminates.Turn MASttb airframe. Verify appropriate switch off . chip detector per Section 1.330 and 4. Installchip detector. Torque threaded-type wiring as required. safety wire. Ty-rap chip detectorelectrical by grounding b. Turn on MASTER switch. Check chip detector circuit function warning light detector,s center terminal and verifying appropriategearbox chip illuminates.Turn MASTERswitch off' | DrainAnd Flush 1.120 Main RotorGearbox To drain and flush main rotor gearbox: RPMto warm main rotor gearbox two to five minutesat 60-700/o 1. Groundrun helicopter oil.

located approximately1o inches 2. Disconnectchip detector wiring at quick-disconnect gearboxsump from chip detector. Cut safety *ir" r"ruring chip detectorto main rotor chip detectors). to attach bolt (not applicable quick-release 3. Removechip detector. Do not removechip detectorhousing' NOTE After removing chip detector, check for oil leaking from chip detector housing. Leakage indicates housing is defective and installmain rotor occurs,immediately lf must be replaced. leakage gearboxdrain assemblyto minimizeoil spillage' P a g e1 . 4

o

C h a n g e1 3 : O C T 2 0 0 6

FIGIBINSEIN

MATNTENANcE MANUAL

MC'EIEL

F'44

1.120 Main Rotor GearboxDrainand Flush(cont'd) 4, Drain oil by installingmain rotor gearboxdrain assemblyin chip detector housing with drain hose overboard into a suitable container. Slide wedge under drain assemblyto open valve (seeFigure1-2l'. 5. Remove drain assembly.Removeand discard safety wire securing gearbox filler plug. Removeplug.

6 . Fill gearboxwith SAE3O,SAE4O,SAE50,or SAE20W5Ostraight mineralengineoilto level indicated by decal adjacentto sight gage.

7 . Installfiller plug, tighten, but do not safety wire. 8 . Groundrun helicopter approximately minutesat 60-700/o for five RPM. 9 . After shutting down helicopter, drain gearboxusingdrain assembly. 1 0 . Removedrain assembly.Removeand discardsafety wire on chip detectorhousing.Remove chip detector housing and immediatelyplace a small container under gearboxto catch any residual oil. 1 1 . C l e an ch i p d e te cto r w i th a toothbr ushand cleaningsolvent per Section 1.115. Compressed or maskingtape may also be used to removedebris but scrubbing air with solventis mandatory removeany varnishaccumulation. not use a magnet to Do to removedebris.Cleanand visuallyinspectchip detectorhousing.

1 2 . Verify chip detectorfunction by connectingelectricalleads,turning Master switchon, and touchingdetector'scentralmagneticprobeto horizontal firewall. MR CHIP warning light should illuminate. Disconnect wires. electrical

1 3 . Installchip detector housinginto main rotor gearbox.Torque per Section 1.330.and safety wire. 14. Installchip detectorinto chip detectorhousing.Torquethreaded-type chip detector per Section1.330 and safetywire. Connectchip detectorelectrical wires and ty-rap. 15. As required, removesight gage and cleanwith solvent. Reinstall sight gage,torque per Section 1.330, and safety wire. 16. Removefiller plug. Fill gearboxwith RobinsonA257-2 lubricantto level indicated on decal. Rotate rotor system by hand severalrevolutionsand pull down tailcone severaltimes. Recheckgearboxoil level.Adjust as necessary. 1 7 . T o r q u efi l l e rp l u g p e r S e cti on1.33O( safetywir e not r equir ed) . C h a n g e1 3 : OC T 2 OOo P a g e1 . 5

FlclBINEiON

MATNTENANcE MANUAL

MOEIEL

H44

I I

{cont'd) andFlush Drain Gearbox 1.120 MainRotor by. switch. check chip detec.tor .opera.tion. grounding--dglqlt9f: 1g. Turn on MASTER Turnoff MASTER tijtrt iltuminates. warning centerterminallnJu"iiiving MCCHIF switch.

\87260 CHIP DETECTOR

DETECTOR HOUSING

\-\,----= .r,J

r\+\'\

FOR87260 ASSEMBLY MTO54.1DRAIN CHIPDETECTOR "OUtCK-RELEASE" OR WEDGE GEARBOX MTO53-1MAIN ROTOR FORA7260 DRAINASSEMBLY CHIPDETECTOR THREADED

G G F I G U R 1 - 2 D R A I N I NM A I NR O T O R E A R B O X E

P a g e1 . 6

Change1 3 : O C T 2 0 0 6

FICIEIINSICIN

MATNTENANcE MANUAL

MOEIEL

R44

1 .130 Tail Rotor GearboxDrainand Flush 1. Groundrun helicopter approximately for five minutesat 60-7o0/o RPMto warm tail rotor gearboxoil. located approximately11 2. Disconnect chip detector wiring at quick-disconnect . inchesfrom chip detector. 3. Removeand discardsafety wire securingchip detectorto sight gage. 4. Placea containerundertail rotor gearboxto catch oil and removechip detector. 5. Removeand discardsafety wire securingfiller-ventplug to sight gage. Remove I filler-ventplug. 6. lnstall chip detector, torque per Section 1.330, but do not safety wire. Add I approximatelyfive ounces of SAE3O, SAE4O, SAE5O, or SAE20W5O straight I m i n e r a l n g i n eo i l . e 7. Installfiller plug, tighten, but do not safety wire. five minutes. 8. Groundrun helicopter 60-7Oo/o at RPMfor approximately 9. After shutting down helicopter, removechip detectorand drain mineraloil. 1O. Cleanand scrub chip detectorwith a toothbrushand cleaningsolvent. Compressed I air or maskingtape may also be used to removedebrisbut scrubbingwith solvent is mandatoryto remove varnish accumulation.Do not use a magnet to remove debris. 1 1 . Connectchip detectorwiring. Turnon Masterswitch. Checkchip detectoroperation b y g r o u n d i n g e te cto r'sce n te rter minal; CHIPwar ninglight shouldillum i nate. d TR Turn off Master switch and disconnectchip detectorwiring. 12. Indtall chip detector, torque per Section 1.330, and safety wire. Connect chip as detector wiring and securewith Ty-raps@ required. sight g?g,torque 13. As required, removesight gage and cleanwith solvent. Reinstall p e r S e c ti o n1 .3 3 O,a n d sa fe ty wir e. CAUTION Tail rotor gearboxsight plug glassmust indicatecorrectoil level w h e n a i rcra fti s o n l e ve lqr ound. 14. Filfgearboxwith RobinsonA257-2lubricant levelindicatedby sight glass decal. I to I l n s t a l lf i l l e r-ve n p l u g ,to rq u ep er Section1,330, and safety wir e. t Tur 1 5 . T u r n o n Ma ste rsw i tch . C h e ckchip detectoroper ation. n off Masterswitc h. I I I

C h a n g e 3 : O C T2 0 0 6 1

P a g e1 . 7

FICIEIINSCIN

MAINTENANcE

MANUAL

MOE EL ]t44

;ee (c_ommerciaily avpirabre, section with 4-b gramsof A2b7-12grease 1 . Fiilsyringe a inside syringe i""f''iiS mm)lonbspice tillt of Note:b grams grease . rlO 1.47O1. diameter' (16 mm) inner rilov,iiitt i o.os inch may sc.r.eyv be covered housing. screw from left side of c181-3 bearing screw' lt is not necessary 2 . Remove to by Telatemp;,e.ove Telate.p .f itquiied to adcess easebearing access' to Telatemp.-;.t;t"';ii cowfingriiay be removed replace 3 . Using syringe,inject greasethrough screw hole'set screw and screw, or,Ihorltughly,glean. lnstall 8289-3 self-sealingcross-head B27o-2o :9119nt, wet epoxy screw hote threa"d;;"d i"n"n lnrtull set screw q!!n.g set screw only until screw primer, or wet tin?-.iiio."aie'primei on tfrreaOs'Tig6ten h i s f l u s h w i th b e a ri n g o u si n g '

in kit Svrinqe suitable for the following procedureis included ftot RHC Cuttottt Sttui* [l'-i i"5; "u.iiiuit

l-

o

cavity. Tightening Set screw hote is throughto bearing.housing can result in set further thai flush-with-housing ;;i r;;* damaging internal bearing assemblY tii"t i'ib-nta"iing and RPM for two minutes,shut down, inspect bearing' a 5 . G r o u n dru n h e l i co p te r t 1 0 2olo grease' and clean off anY escaPed 6 . I n s t a l la ft co w l i n g ,i f re mo ved' 1 . 15 O D e fu e l i n g WARNING No smoking Defueling must be done in a well-ventilatedarea'

;iifriil"i 6d'i;;i oi treticopt

be Low-fuelsendercheck (seeSection12.27O1maY Performed when defuelinghelicoPter' flexiblefuel line at car bur etor ' 1 . T u r n f u e l va l ve o ff a n d d i sconnect r containerGr oundcontaine' toher icopteand tur n . 2 . p r a c ee n d o f fu e r ri n ei n a su itabr e f u e l v al ve o n . to repeat as necessary complete 3. Turn fuel valve off when the containeris full and draining. 1 .330, and tor questr ipe' 4. Attach fuel line to carburetor,tor queper Section C h a n g e1 4 : J U L 2 0 0 8 P a g e1 . 8

FIEIBINSCIN1. 1 6 0 St o r a se

MATNTENANeE MANuAL

MOEIEL

F|44

For long-term (greaterthan 3O days) storage: 1 . Defuelaircraftper Section 1 .150. 2. Cleanaircraftper Section8 of R44 Pilot'sOperatingHandbook. 3. Paintor wax bare metal areasof main and tail rotor blades. 4. Apply suitablenon-dryingcorrosionpreventative compound to C166 clutch shaft adjacentto seals(whereshaft entersand exits upper sheave). 5. Preserve engine in accordance with Lycoming Service Letter L180 (current revision). 6. Remove battery and periodicallycheck and adjust, as required, battery charge status. Check fluid level and specific gravity of non-sealedbatteries. environment. 7. Store aircraftin a protected,dry (dehumidified) inspectaircraftfor corrosionand correct as required. 8. Periodically R r 1 . 1 7 0 H v dra u l i c e se rvo iF i l te rReplacem ent CAUTION of Cleanliness hydraulic fluid is vital to propersystem operation. Use only clean f luid from sealed containers and avoid contamination from dirty funnels,tubing, etc. 1 . Removeand discardsafety wire from filter cap. Removefilter cap from bottom of hydraulicreservoir.

2 . Removefilter and examine.lf debrisis found, use a magnet to determineif ferrousor non-ferrous. NOTE filter again Ferrousdebrismay indicatepump damage.Replace after one flight hour. lf more ferrous debris is found, replace hydraulicpump per Section 8 and flush hydraulicsystem per S e cti o n1 .18 0 .

3 . Cfeanfifter cap and replaceO-ring packing.Lubricatenew O-ring with 4257-15f l u i d ( s e eS e cti o n1 .4 7 0 1 . Install 4 . Lubricate O-ringin new filter with A257-15fluid and installfilter in reservoir. per Section 1.330, and safety wire. filter cap, torque 5. Adjust reservoirfluid level as required.Install filler-vent and torque per Section 1.330. Safety wiring filler-ventis not required.

C h a n g e 3 : O C T2 0 0 6 1

P a g e1 . 8 A

FICIBINSICIN

MAINTENANtrE

MANUAL(seeFigure 8-1A)

MOE'EL

F|44

of Cleanliness hydraulicfluid is vital to propersystem operation' and ti1iialior r.it"O containers avoidcontamination Ur" ";iy;f"un funnels,tubing, etc. from dirty

Drain and flush hydraulicsystem if oil turns dark, or emits bad

filler-vent. reservoir 1. Remove pump at hydlaqlic D5O0-1 fluid for container contaminated beneath 2. placea one-liter T-fittings'-Allow suctionandpressure itot..puTq mainrotor gearbox. Remove of smallamount clean Pour "u-pJ tine 'tri" in ,"r"-oiito orjin ir.riorgh"Su"iion intocontainer. fluid line line. Pressure wittj purge suction S"Jti"n i.i7Ot inio r"i"ruoirto nzSj-15ftuid ariin in followingstepwhenfiltercap is removed'filter per Section 1'17O' ace 3 . Repf hydraulicreservoir test pump to T.2 e 4. See Figur 1-2A. ConnectMT384 (or similar)O.S-1 gpm hydraulic. connection' iitti,.tb;;; p"rj. OSOO-1 fittittgt ai" Ait"t"nt sizesto ensurecorrect fluid. Fill reservoirwith A257-15 fluid' hydraulic 5 . Disposeof drained,contaminated forwardelbow and placeend in empty container returnline servo'hydr;;ii; at reservoir 6 . Disconnect (usecap from pump for contaminated T-fitting). assembly flrio. Cap elbow on reservoir

7 . Activate hydraulictest pump and inspecthydraulicsystem for leakage'fully and move-cyc_l'1c forward. Then simultaneglsly fully raisecotlective 8 . Simultaneously fluid level and fill as coliectiveand move cyciic iutty gft: . Monitor reservoir friiliil;i until i"qlitiO. Repeat-pioceOurJ ieturn linefluid into containeris clean. WARNING Stay clear of moving flight controls. Hydraulicforces can cause fully g. Simultaneously 'Monitor aft then simgltaneously-{ully fuily raisecollectiveand move cycLic fluid level and fill as reservoir tor*ard.. inl moue .y"li" iuliv lower cottectirie fluid into containeris clean. i'"ifrir"O. nepelipio"eduru irntil retdrnline forward elbow. Torque B-nut per Section 1 '33O 10. Connectservo return tineto reservoir and torque striPe. systemper Section1.190. 1 1. Bleedhydraulic procedure. lf filter 12. Removeand inspectfilter. lf debrisis found, repeat drain and flush & 5' per is clean,reinstali Section1.170, steps4 Change13: O C T 2006 P a g e1 . 8 B

FICIEIINSiCIN

MAINTEI\ANcE

MANUAL

M(fEIEL

14.44

1.190 Bleeding (seeFigure1-2Al Hydraulic System1. Disconnect cap on Db00-1 hydrau.licpump pressure (aft) T-fitting and connect pressure tine from MT3g4 hfdrautic te.st'ptimp (or iimiiar o.e_i.z gpm-unit). Pressure and suctionfittings are-different sizesto assurecorrectconnection]' 2. Remove reservoir filler-vent and cover hole with finger to prevent fluid toss. Disconnectcap on. hydraulicpump suction (forward)f-i''i:ting-ani nyOrauft test pump suction line. Fillreservoir required. "onnr"t as

3 . Activatehydraulic pumpandinspect leakage. test for 4. s.imu.ltaneous.ly - I-rlly raise collective and move cyclic fullv forward then simultaneously lowercollective movecyclicfully aft. Rep'eat fully and procedure ten times. WARstay clear of moving flight contrors. Hydraulicforces can cause Inturv. 5 . Simultaneously fully raise collective and move gvclic futly aft then simultaneously fully lower collectiveand move cyclic futly forward.' Repeatprocedure times. ten 6 . shut off hydraulic test pump. verify no leaksin hydraulicsystem. 7 . Cover reservoirfiller-venthote with finger to, preventfluid loss. Disconnecthydraulic test pump suction line from D5O0-1.pumpforward T-fitting and install cap. 'forque cap per Section1.330 and torquestripe. 8 . Disco.nnect hydraulictest qump pressureline from D5OO-1pump aft T-fitting and installcap. Torquecap per Seciion 1.330 and torque stripe. 9 . 49jy"^tre_se_rvoir level as required. tnstallfitler-ventand torque per Section fluid_ 1.330. Safety wire is not required.

C h a n g e 0 : JU L 2 0 0 4 1

P a g e1 . 8 C

F|E|BINSiEIN

MAINTENANcE

MANUAL

MOEIELF44

!:

=ll

:t ll

(115 VAC,60 Hzl MT384-l, or MT384-2 (208-230 VAC, 5O Hzl TESTPUMP HYDRAULIC

' ..ti

l?r.rrr

I I I

I I

r'',/

I I -Z(\.

\

'":.7=

jrii " ID500-1 HYDRAULIC PUMP PRESSURE

1-2A FIGURE

P a g e1 . 8 D

7: Change 06 Dec99

FIGIBINSCIN

MAINTENANeE MANUAL

MtlOELH'44

AND WEIGHING LEVELING, HOISTING. JACKING, 1.200 HANDLING, Handling 1.210 Ground WheelsInstallation 1.211 GroundHandling pin locking andsliding the by the a) Extend handle depressing handle out the handle untilthe pin snapsintothe outerhole.Holdhandle in spindle its lowestposition. Insert andwheelwith the protruding on into supportmounted skid {seeFigure1-3}. Spindle NOTE the spindles has not settledon its skidscompletely, lf helicopter may not go in all the way. In this case,pull down on the tail cone to the to spread gearenough allowinstallation.

spindleis all the way in with the bl Make sure that the protruding pastthe insideof the support(seeFigure widenedend completely 1-34).

and lock wheel in c) Pull handleover centerto raise helicopter (seeFigure position 1-4).

CAUTION When loweringthe helicopter, handlehas a tendency the to snapover.

NOTE pressure. 70 psi maximum inflation tire

l s s u e d1 1 J u n 9 3 :

P a g e1 . 9

FICIBINSiCIN

MATNTENANeE MANUAL

MOEIEL'|'44

F I G U R1 - 3 E

F I GU R1 -3 A E

SPINDLE SUPPORT

1FIGURE 4

P a g e1 . 1 O

l s s u e d1 1 J u n 9 3 :

FIGIBINSC|N

MAINTENANci

MANUAL

MO6ELF44

(cont'dl 1.210 GroundHandling Gear wheels- Floatship Landing Handling 1.212 Ground INSTALLATION: , Align aft blocks adiacentto mark on skid tube and position forward blocks to removecord slack.SKIDS

a)

Pulltail down. lnseft forward blocks at their lower height underboth skids. Pushtail uP. lnsert rear blocks at their lower heightunderboth skids at marks. Pulltail down. Move forward blocksinward to their upper heightundei skid tubes. Pushtail up. Sliderear blocks out (upperheight of rear blocks is not used)and insertwheels underskids at rear marks. NOTE Wheelsmay be placeda few inchesforward to reduceforce to required pull down. tail e) Pulltail down and remove forward blocks.Hl

/\l.-! t, _. f I

\,/ FBOTTBLOCK POSTTIONS

bl

c)

:l

/>SKIDS FRONT ELOCK POSITIoNS

\/

d)

INSTALLATION WHEELS HANDLING SHIPqROUND F IGU R 1 -3 8 FLOAT EChange4: 1 Jun 97

P a g e1 . 1 0 A

FIClEIINSlclN

MATNTENANcE MANUAL

M('EIEL1f,,44

Gear{cont'd} Wheels FloatShipLanding 1.212 GroundHandling REMOVAL: a) Pulltail down. Insert forward blocksat their upperheightat forward marks underskids.

c,, >SKIDS

\/

FBOUT BLOCK PO$T|ol|S

b)

Pushtail up. Removewheels and insert rear blocksat their lower height (upperheight on rear blocks is not used) at marks.sKtos

cl

Pulltail down. Positionforward blocksunder skids at their lower height.

FROlIT BLOCK POSITIONS

d)

Pushtail up. Removerear blocks.

e)

Pulltail down. Removefront blocks.

WHEELS REMOVAL SHIPGROUND 1-3C FLOAT FIGURE

P a g e1 . 1 0 8

Change 1 Jun 97 4:

FICIBINEiCIN

MATNTENANeE MANUAL

MC'EIEL

F'44

1 . 2 1 3 M o vi n gth e H e l i co p teo n Gr oundHandling heels r W Moving the helicopteron ground handlingwheels requirestwo people:one personto holdthe tail down and steer by holdingthe tail rotor gearboxand anotherpersonto push on primarystructure. The steel tube frame insidethe aft cowl door may be used as a hand hold for pushing. Keepfeet clear of skid tubes during ground handling. CAUTION Do not move helicopterby grippingtail rotor guard, outboard portionof horizontal stabilizer, rotor, or tail rotor controls. tail 1 . 2 1 4 M ai n R o to rB l a d eT i e -D o wns InstallMT29O-2main rotor bladetie-downsas shown in Figure1-5. Tie-downstrapsare installedby removingslackfrom linesto preventblade movement. CAUTION Overtightening tie-down strapscan damagemain rotor blades. 1.215 Parkins Referto Section8 of the R44 Pilot's Operating Handbookfor parkingprocedures. 1.216 Trailering Trailering R44 is not normally the Mosttrailers largeenoughto accomodate recommended. the helicopterare designedfor much heavier loads; the trailer's springs and shock will not function properlywhen lightly-loaded.lf traileringis unavoidable the absorbers should be observed: following precautions 1. Loadtrailerwith ballastuntil it is at the averageweight it is designedto carry. 2. Supporttailcone,taking care to preventchafing or abrasionat the support point. 3. Removemain rotor blades. lf not practical remove,supportthe main rotor blades to so they will not bear on droop stops. Locate supports about 5 feet in from blade tips. Supportsmust be cushioned preventblade damage. to 4. Restrain rotor to preventteetering. tail

C h a n g e1 3 : OC T 2 0 0 6

P a g e1 . 11

FIC|BINSiEIN

MAINTENANeE

MANUAL

MODEL

]I44

. THE DETAIL TIE AROUND ABOVETHE BRACKET

CAUTION OvertighteningTie'Down straps can blades.

TAIL CONEIN FRONT WRAPAROUND TO TAIL CONE AROUND OF LIGHT, THENWRAPAROUND BACKOF LIGHT; BASETO ATTACHVELCRO.

1-5 MAIN ROTORBLADETIE-DOWW FIGURE

P a g e1 . 1 2

C h a n g e1 3 : O C T 2 0 0 6

FICIBINSCIN

MATNTENANeE MANUAL

MOE'EL F|44

(cont'd) 1.216 Trailering e) Protect helicopter's windshield, tail rotor and other vulnerable parts from highway debrisdamage. damage,with particular I inspectaircraftfor possible f) After trailering,.thoroughly attention to the steel tube structure and rotor systems. 1.220 Jacking, Hoistingand Leveling jacking is accomplished placinga jack undereach end of the aft cross by 1. Helicopter elbow fittings. tube 1 inch inboardof

CAUTION Care must be taken to preventthe helicopterfrom becoming from jacks. dislodged2. Hoist helicopterusing MT527-1 helicopterlifting fixture as shown in Figure 1-6A, holesin main or by passingone-inchdiametersoft nylon rope throughthe lightening rotor hub and forming a double loop per Figure 1-68. Ropemust have a minimum tensilestrengthof 2,50O lb. 3. Levelhelicopterusing either of the following methods: a. Levelingusing tailconeand aft landinggear cross tube: 1) Placea propellerprotractoron top of forward bay of tailcone.When tailcone is 0.7 degreesnose down ship is leveledlongitudinally. 2) Level helicopter longitudinallyby placing shims under landing gear skid tu b e s. 3) Verify aft cross tube is not bent. Place a bubble level in center of aft cross tube. 4) Levelhelicopterlaterallyby placingshims under landinggear skid tubes. levelper steps 1) and 2) above. Repeatsteps 1) through 5) Rechecklongitudinal 4) as required.

NOTE1 Jacks may be used underaft cross-tube inch inboard from elbows.

1 Change 2: JUL 2005

P a g e1 . 1 3

FICIBINSGIN -L vr[527HELICOPTER LIFTING FIXTURE

MAINTENANcE MANUAL

MODEL

F|44

1.6A HELICOPTER FIGURE

HOISTING

lj

TAIL ROTORBOX TAILCONE\

\t1.68 HELICOPTER FIGURE HOISTIN G ;URE RE

o

-\..

f-\-

/o)

o

rfr:;

ffi 1o1FIGURE 7

VERTICAL FIREWALL

AFT INSERT TUBEINTO HOLE FiREI.IALL OF VERTICAL

AT IN WATER TUBE BELLY CABiN

C.G. HELICOPTER DETERMINATION

P a g e1 . 1 4

Change3: 5 MaY 95

FICIB|NSiCIN

MATNTENANcE MANuAL{cont'd}

MIIEIEL

F44

b. Levelingat the main rotor hub: 1. Rotatemain rotor until teeter hinge bolt is alignedwith longitudinal axis of helicopter. Placea bubbleleverat locationmarked ,,level here',.

NOTEhinqe bolt.

Levelmust be on top of mainrotor hub and parallel teeter to

2 . Levelhelicopterlongitudinally placingshims under landinggear skid bytubes.

3 . Rotatemain rotor until teeter hinge bolt is alignedwith lateralaxis ofhelicopter.

4 . Levelhelicopterlaterallyby placingshims under landinggear skid tubes. NOTE Jacksmay be usedunderaft crosstube 1 inchfrom elbow.5. Rechecklongitudinal level per precedingsteps. Repeatsteps as requiredto level helicopter.

C h a n g e1 3 : O C T 2 O O o

P a g e1 . 15

FlClElINEiClN

MAINTENANcE MANUAL

MlfElEL

F44

1 . 2 3 0 W e ish i n ga n d C .G. C a l cu l ation

Data form in the Pilot's and Balance ListAtreight The Equipment continuous Operaiing Handbookmust be used to maintain a weight and bqlanc recordof the helicopter's

Level must be on top of main rotor hub and parallelto teeter

r 1 . 2 3 1 H e l i co p teWe i g h i n gP rocedur e and both fuel tank sumps' g 1 . D r a i na l l fu e l , i n cl u d i n g a s colator to and gear boxes full m ar ks' fl 2 . F i l len g i n eo i l , h yd ra u l i c uid { if applicable) , 3 . l n s ta l la n d se cu rea l l d o o rs. 4. level and center cyclic Position main rotor blades fore/aft and approximately stick.

BalanceData form are 5. Be sure all checkeditems on Equipmentlist/Weightand i i n s ta l l e dn th e i r p ro p e rl o c ations' Cor r ectform as required. such as charts, tools 6. Be sure aircraft is clean and remove any foreign items r a gs. or

w of helicopter hi l e i t 7 . H o i st a i rcra ftp e r se cti o n 1.22O. Haveone per sonholdtail is being hoistedto stabilizeaircraft' fore and aft, raiseboth blad", ofl 8. With main rotor bladesorientedapproximately droop stops to allow hub to freely teeter' measuredifference L With aircraft hangingfreely and steadily,use a water level and cabin belly at vertical in verticalheight between centerlineof tail rotor gearboxand firewall. Referto Figure1-7. Recordheight differenceto nearesttenth of inch: inches(no ballast)

P a g e1 . 16

Change1 4 : J U L 2 O O B

FIclBINSiclN

MATNTENANcE MANuAL

MOEIEL

'''44

1.231 Helicopter (cont'd) WeighingProcedure 1O. Determineuncorrected longitudinal centerof gravity: 114.34 - t0.32 x (difference height,from Step g)l = in 't1. inches

Place a 1OOO-pound capacity scale under each skid. Locate center of scales approximately inchesforward of groundhandlingwheel mount centerline. six

12. Lower aircraft until it rests entirely on scales. Aircraft must be well balancedon scales before releasingtail. Be sure aircraft is tevel laterallyby placing level on center of aft landinggear crosstube. 13. Determineuncorrected empty weight: Right Scaleindication plus Left Scaleindication + minus Tare (such as lifting fixture, if installed) Uncorrected EmptyWeight = 14. Determine with f ull fuel and 150 lb pilot: CG [(CGfrom Step tO) x (emptyweight from Step 13)] + 3gg4o (emptyweight from Step 13) + 451.2

tbtb

tb

inches

15. lf CG f rom Step 14 is greater than 102.5 inches, determine required nose ballastas follows: [ ( C Gt r o m S te p 1 O - 1 0 2 .S )x (e

ht fromStep13)J - 74oB

95.5

bl

Roundballastweightup to nearest 0.2b lb and install nose ballast per Section 1.240. Record actual noseballast installed:tb

Repeat steps 7 thru 15 and revisemeasurements calculations. and

C h a n g e1 4 : J U L 2 0 0 8

P a g e1 . 1 7

FICIBINSCIN

MAINTENANeE

MANUAL

M('EIEL

F44

(cont'd) Procedure fuel: unusable 16. Adjust weight and balanceto correctfor drained

ITEM Shipas weighed

WEIGHT (tb) X(from Step 13)

CG (inchesfrom datum)

MOMENT (in.-lb)

(fromStep 1O) 96.0

fuel Add unusable basic empty Helicopter and CG (includes weight fuel and full oil) unusable

+7.2

+691

*_

*cG location(arm)is determined dividingtotal moment by total weight' by Datum is located 1OOinchesforward of main rotor centerline

CAUTION Followingany modificationwhich moves empty cG aft, calculate lf calculation weight und buluncewith 150 lb pilot and full fuel' in nose to shows CG aft of aft limit, fixed ballastmust be installed Section 2 of comply with minimum solo pilot weight limitationin Handbook. the Pilot'sOPer centerof gravityusingstep 13 data: lateral 17. Determine (RightScale- Left Scale) L a t e r aC G A r m = l (RightScale + Left Scale) x 41.2O = inch

P a g e1 . 1 8

1 Change 4: JUL 2008

FIClElINSiClN

MATNTENANeE MANuAL

MC'EIEL

F'44

1.24O Fixed BallastInstallation 1. Removescrews securingupper consoleand open console. 2. Removelandinglight retainerand landinglights. 3. lf requiredby Section 1.231, installappropriate batlastjrer Figure 1-8, 1-8A, or 1 - 8 8 , a s a p p l i ca b l e .

NOTE Maximum allowable ballast 1 0 is s.

4. Torqueboltsper section1.32o andtorquestripeper Figure 2-1.5 . Closeand secureupper console. landinglights and retainer. Functioncheck landinglights. 6 . Reinstall

i! /--- --oo---

'li,(.".,,' -A\.,'i '', eT:i-fjl'..^',)i_--l:;-... t. .

MS21o42L3/-\

'{Rrs\

(4 ptaces)

*oo

rq \./ i"r \\

\ NASl't49F0332P WASHER (4 places)

.-'

r\\l \l

Grl ll \\ \)

il

A941-2 BALLAST PLATE

( 0.25 b) r

A941-3 BALLAST PLATE ( 1 . 0 0t b )

c361-1 C O N S O LP A N E L E {Ref )*2 threadsminimumbeyondnut.

FIGURE FIXED 1-8 BALLAST INSTALLATION (with -holeballasr platesl C h a n g e 4 : J U L2 O O 8 1P a g e1 . 19

FIclEtINSCIN

MAINTENANCE

MANUAL

MOE'EL

1t44

(cont'd) 1.240 Fixed BallastInstallation

ii:tQ ,':::"j -'-'$[=i\""1'.(.---,)-'.-I t

';f,MS21 '\NUT\

o42Lg(4 Places)

t )

-s\\ 'l-'

\.'. i "r. i tt. tr\. \. \

\.'.'.. '.. i 4,

,/0,,,' \ \

\ NASl 149F0332P WASHER (8 Places)

Sf

\l'

'.-

"-.. l:

b'\ 'tl''-r

Q)-,. G,

t-

\\

tl..--l

!

\A941-2 BALLASTPLATE (0.25lb)'.

li

tt.

---

.-a\ . --'r - \\'=))-.

'j.'-o)-'

or NAS6603*BOLT (4 places)

A941-3 BALLASTPLATE ( 1 . O 0l b )

NASl 149FO332P WASHER

c361-1 C O N S O LP A N E L E (Ref )

*Select NAS42B-3A bolt length as requiredfor 2 threads minimum beyond nut' Se|ectNAS66o3bo|t|engthasrequiredfor2|o4threadsbeyondnut.

1.8A FIXEDBALLASTINSTALLATION FIGURE (with 6-hole ballast Plates)

P a g e1 . 1 9 A

1 Change 4: JUL 2OOB

FIclBINSiClN

MATNTENANcE MANUAL

MOEIEL

F,44

(cont'd) L240 Filqd Ballast_lnstallation

c 3 6 1 PANEL

7A941-6

/,1

FORWARD

*Boft length as requiredfor 2-4 threads beyond nutplate.

FIGURE 1-8B FIXED BALLAST INSTALLATION (with 2-holeballastplates,required wirh H.l.D.landinglightsl

C h a n g e1 4 : J U L 2 O O 8

P a g e1 . 1 9 8

F|clEIINSiclN

MAINTENANeE MANUAL

MOEIEL

844

REOUIREMENTS TOROUE FASTENER 1.3OO

P r o p e r t o r q u e i s c r i t i c a | . A | w a y s u s e c a applicablelr hardware.n d (where | i b r a t e d w e n c h e s a undamaged, proplii/ -fuUricated_. climp-only bare metal Ensureall clampingsurfacesare clean' and

nloq -iq'lll : I gi*v* p or wet- rimedt uftil" J' r".' in'los,ot-ctamp-up, 1 :,:.l,ii:t"^1 or hardware i.,"v ,"ruii ;i#;il'Hil.]"loart damaqe, and Premature t

1. 3 1 0 G e n e r a l fistedin Section 1.320 unlessotherwise shail be torquedto standarddry.va.rues Fasteners to torque value by 10o/o account soecified.rf torque-ir'"ppfiLl-uv *ri'gii"j nJt,]ncr"as" 6t-hi;h;; friction at boltheadand shank' Forexample,thetorquewre.nchsettingforanNASl3O5boltusedwithanNASl063 nutplateib determinedas follows: 240 in.- l b tor queper Table 1 5 N A S 1 3 O 5b o l t (5 i n d i ca te s /1 6 i nch size)dr y 24 in .- l b bolt head Add 1O% becaut"-i"tqJi must be appliedat 264lnLE Torque wrench setting B33o stampednuts on at criticalfasteners. -r.'i"ir'inismq A secondaryrockingmechanismis required and heticopter, are

on in ''ost areas thespecific (parnuts) ur"JX"oriiuoi^r9."i.i"e serve fasteners' for ;;;;;J;;tlo.t ingmechanisms tpc per torqued TabteT.-in" tistsa inspgction.by Assembly of flight controls is criticaland requires. the insta||er is -;;f. qua|ifiedpe]son. lr '""ond pers.on not avai|ab|e, " prror to inspecting fright control drust take a #ffi*"

bolts have higher Never substituteAN bolts for NAS bolts. NAS tensile strength.

or lost' would A critical fasteneris one which, if removed. jointsin Thisincludes ;;";;;ai;; tii" oplruiionot trt" heficopter. structural joints in the primarycontio"l';;;i;;' "lq l"li?il:{" ear, and drive sYStqlL , th e b i rfra me l a n d iin after palnut installation a stripe Torque seal (paint)is appliedto all criticalfasteners boih nuts. ontothe component tro,i'ir,'" irii"n"r,, q;'io;i-t'iit^"udracrosr extending ot bolt can be detected (referenceFigure 2-1). An_y,rbd.qu"nt rotatio;-;-th;-nut 1.460. given in section visually.npprou"olour"" tbr t-qud seal is must appreciably has deteriorated Any nut damageddue to handlingor whose nut drag b e r e p l a ce d . 1 Change 4: JUL 2008 P a g e1 . 2 O

FICIBINSiCIN

MATNTENANeE MANuAL

MOEIEL

H44

1 . 3 1 0 G e n e r a{l c o n t ' d ) WARNING Two threads minimum must be exposed beyond nut on any installation to insure proper locking of fastener. Four threads maximum may be exposed. More than,fourthibads exposedmay allow nut to seat against bolt shank, resultingin insufficientjoint clamping. Torquingrequirements: 1. Bolt and nut are to be cleanand dry exceptwhen assemblyprocedure specifies antiseizeor thread-locking compound.

2 . lf chatteringor jerking occurs,disassemble re-torquefastener. and 3 . lf specialadapterswhich changeeffective length of torque wrench are used, finaltorque value must be calculated usingformulabelow. threadengagement requires 4. Proper 2-4 threadsbeyondprimaryself-locking (palnuts nut excepted). 5. Torque wrenchesmust be calibrated annually, when dropped,or when a calibration error is suspected.WHENUSING TOROUE A WRENCH ADAFTER WHICH CHANGES THEDISTANCE FROM THETOROUE WRENCH TO DRIVE THEADAPTER DRIVE, APPLY THEFOLLOWING TO THECORRECTED FORMULAS MAINTAIN TOROUE HEADING: T. Y. L. E. TOROUE ACTUAL. {DESIRED} (INDICATED} APPARENT TOROUE EFFECTIVE LENGTH LEVER EFFECT1VE LENGTH EXTENSION OF

200 pin when work is completed. Avoid excessive heat lq"Lilg degreesF) as thermal relief valve will activate. Perform1OOhour or Annual inspectionper Section2.410. 2.410 InspectionProcedures and Checklist R44 SerialNo.: Registration No.: Hourmeterlndication: Aircraft Total Time: 1. Tail Rotor PedalBearingBlocks NOTE Do not removepedalbearingblockcoverplates(1) unlessfunction check of pedals indicates possibleproblem with pedal bearing blocks. To removecover plates(1) peel back carpetingand removescrews holding plates.Use an inspection light and mirrorto inspectbearingblocks. Inspect play is 0.080 inch and loosenes5 play. Maximumallowable for condition or axiallyand 0.030 inch radially. Inspectall weld areasin pedalcontrols. Change13: OCT 2006 P a g e . 13 2 Technician name: Technician Certificate number:

FIGIBINEiC|N

MAINTENANeE

MANUAL

MOEIEL

FI44

./

,ffico-PILOT'S SEAT 10..48\ 4Hil

3E

co-PlLoTsSEAT

4I (ENGONLY)

,,$ARD FORW

PANELS AND INSPECTION 2.4 ACCESS FIGUREP a g e2 . 1 4

Change1 3 : O C T2 0 0 6

FICIBINSiCIN

MATNTENANeE MANUAL

MOE'EL

N44

-*--.Ho--"/

BATTERY TAILCONE (POLICE ENG and versions only)

l=m6B

:J

PANELS FIGURE2-4A ACCESSAND INSPECTIONNUMBER PART NUMBERDESCRIPTION NUMBER PART NUMBER DESCRIPTION Face (ENGonly) 4r D3B3-1 Deflector(LH) 1 81B9-4 (RH) A412-2 and Cover and Deflector Seat BackAssy (RH) 5 C003-10 8189-2 Seat Back Assy (LH) 1 co03-1 CowlingAssy (LH) 6A c337- 1 ConsoleAssy 2 8050 CowlingAssy (RH) 6 B c378- 1 Cover Assy 3A c445-1 Cowling Assy - Belly 6C DO41-1 3 B c445-3 Cover

3C 3D 3E 4A 48 4C 4D 4E 4F 4G 4H 4H

c444-1 c398-1 c794-1 c680-1 c461-1 c464-1 c463-1 co54-1 c474-2 c474-1 c794-2 c794-3 c794-2 c794-3

Cover CoverAssy Panel Cover Assy Cover Tray Cover Cover Assy Cover Cover Panel(without scoop) PanelAssy (with scoop) Panel(without scoop) PanelAssy (with scoop)

6D 7A

DO40-1 DA42-4 DO42-4

Aft Cowling Assy Door Assy Door Assy TailconeCowling Assy Plug Assy Cover Mast FairingAssy Fairing Assy (FWD,RH) FairingAssy (FWD, LH) FairingAssy (AFT, RH) FairingAssy (AFT, RH) Circuit BreakerPanel Fairing(lnframetrics Camera) (FSlCamera) Fairing

C706-1 A231-1 4558-2 C261,1 co82-2 c082-3 co82-4 co82-5 11 C045 12 D412-1 (Police or ships) D347-1

78 8A 88 I 10

Ch a n g e1 3 : OC T 2 0 0 6

2 Page .15

FIClElINSiClN

MAINTENANcE MANUAL

MIfEIEL

F|44

and Checklist(cont'd) 2.410 InspectionProcedures 2. Upper Gonsole(21 Console(2), is openedby removingone screw on each side. With console open, inspectthe following: Pitot-static system: check pitot and static lines for cracking,chafing, for pinchingor kinking. check all-connections security. Flightand EngineGages: Checkall gaugesfor security' Inspectwiring and connectionson all gages. RadioTray(sl: Checkconditionand security. for portionsof TR pedal assemblies Tail Rotor Controls:Check accessible defects. Verify operatingclearance. (3Cl' Sto.p.Go.ver -' 3. RemoveForward Tunnel Covers (3A & 3Bl, -Gyclic (3D1,and ForwardBdllyPanel(3El Cover inUoirAColtective NOTE on lf radio antennasare installed removedpanels,disconnect lead and any groundwire. Pullrespecliveradio circuit Removed"' "nt"tnt andtaq ciicuit-Ureaker "Antenna with Ur"ili". Cyclic Box Assembly: Inspect lYclic box assemblyfor defects' Check (deterioration, ;i;ldsiop sheetrrtli ass"inblyfor cracksand otherdefects distortion,loose rivets, corrosion). Cyclic Stick Assembly: Inspectcyclic stick assemblyfor defects' Inspect welds for cracks. CAUTION (manualcontrolsl

strainq.?9.9s,.9r coatingprotecting Do not disturbclearsilicone or wiringwill disable stra-in-gages to .ti."f't"a *iiing. Any damage trim system.Cyclic Trim (manualcontrolsl: Turn masterand cyclic trim switches on. stop tP :!9l uld_check stop to stop and longitudinally Mbve cyclic iateratty Cr'ecirtrim moiors, springsand elastic cords for rbtliri ljp"iiti.i" oi tiirn ci"arunlu from atl wire bundlesand fuselagestructure during movement and at travel limits. Cyclic LateralTrim Actuator (manuatcontrolsl: Turn master and cyclic trim switches on.--Fu;h ;^d hold cyclic stick againstright stop until motor cyclic stick to left stop to compresssprlng' stops then turn trim off . Moverod il;p;"i expoieO ponion of st'tuttfor wear and.galling.Do not glga.sq on bearingis seH-lubricating. springassemblies, neu H una'subse{ueniCOSO-t Checksecurityof attachmentto inipi,ti CtbO-t S'uiuthanespacbr{s--topl. cyclic pivot. C.130-13 controls): Insp.ect Cyclic LongitudinalTrim Actuator (man-ual cyclic stick' u*thin" rfacer trioii. bfteit=

oScrew Retainer Washer Nut Tape

INSTALLATION 4-1 WINDSHIELD FIGURE(1.H.) Windshield Retainer (R.H.) Windshield AN526832R7 c367-5 AN960-81 NAS1291-08 c367-11

1 2 3 4 5 6 7 I I 10 11

c 2 7 4 - 1 ,1 3 * c367-10 c274-2,-4*

Stiffener c367-12 (R.H.) Retainer c367-8 Retainer c367-7 (L.H.) Retainer c367-6 2 A N 5 2 6 C 8 3 2 R 1 Screw Retainer c366-2 Bracket c366-5 A N 5 2 6 C 8 3 2 R 9 Screw

Page 4.2

1 Change 1: JA N 2005

FIclB|NEiClN

MATNTENANeE MANUAL

MC'E'EL

F|44

4.120 Windshield Assembly The C274 windshieldis made of transparentacrylic set in a weather-tightsiliconesealer and is screwed to cabin structure. 4.121 Windshield Removala

1. Remove forwarddoor and hinges. NOTE To prevent scratching windshield, a protective cover should be taped to the inside and outside of the windshield prior to removal. 2. Removescrews and side retainerholdingwindshield. 3. Reinstall hingesand doors for cabin structuresupportwith window removed. 4. Removescrews and retainers(upper,lower and middle)holdingwindshield. 5. Cleansiliconesealantfrom retainers. 6. Cleansiliconesealantfrom windshieldfor re-installation. 4. 122 WindshieldRepl_acement 1. Removeall old sealanton cabin and retainers they are to be reused. if 2. Clecoall window retainingstrips in place,checkingfor properalignment. 3. Installhingesand doors in door frames and secure.Removebottom and center retainingstrips, leavingside retainingstrip to hold door and door frame in position. 4. Hold windshieldin place by hand, and align it with frame according contourof to frame and windshield. 5. Mark windshieldfor trim using non-permanent marker,such as greasepencilor masking tape. 6. Trim to mark. A band saw is recommended.Bandsaw bladeshouldcontainat least 24 teeth per inch.

Ch a n g e 3 : O C T 2 0 0 6 1

Page4.3

FIclBINEiClN

MAINTENANGE MANUAL

MOEIEL

FI44

(cont'd) 4.1 22 WindshieldReplacement

of Tape cardboard to band saw table to prevent scratching of saw blade and windshield. Saw-cat.iull' to preventbinding crackingwindshield. 7. Hold windshieldin placeand check for fit. Re-trimas necessary' smooth' 8. After windshieldis fitted, carefullysand or scrapeedges Installation' 9. See Section4.123 Windshield

4.123 Windshield hqlallqilg!and windshield' a) Removeall old sealantfrom cabin,retainers wide white polyvinyl with A7o1 -4314-inch b) Tapebottom and aft edgesof windshield taPe (3M #47U. chloride c) Installwindshieldand cleco retainerstrips' tape' This will d) Mask windshieldalong edge of retainerstrips with 1/2" masking strips. of on catch siliconerubbersqueeze-out installation retainer e) RemoveretainerstriPs. entire edge of f) To ensurea properseal,run a beadof B27O-4siliconerubberalong tape line. lower) g) while holdingwindshieldin place, cleco retainerstrips (center,upper and into place. Then tighten h) With doors installedand closed, tighten center retainer strip first. tighten nuts upper and lower retainingstrips. A secondpersonwill be requiredto insideshiP. i) j) strips are secure'removedoor and hinges When center,upperand lower retaining for side striP installation. lnstallside retainerstriP.

all hingesand door. Ensure fastenersare tight. k) Reinstall f) Fiffany gap betweenretainerand window with B27O-4sealant'

Page4.4

Change13: OCT 2006

FIclBINEiClN

MATNTENANeE MANUAL

MCIE'EL

]l.44

4.123 WindshieldInstallation {cont'd) m) n) Removemasking tape next to retainers. Be careful not to smear wet sealant. Cleanany sealantoff windshield after it has been allowedto dry.

4.1 30 Door Removaland Installation 4 . 1 3 1 D o o r R e mo va l 1. 2. 3. 4. Disconnect door(s)gas.spring holdingdoor full open and lifting up firmly aft by on gas spring'sinner attach point. Removecotter pins and/or cotter rings from both hinge pins. Removedoor by openinglatch and lifting door to disengage hinges. lf required, door hingesmay be removedby removingmountingscrews.

4 . 1 3 2 D o o r In sta l l a ti o n 1. 2. 3. I n s ta l ld o o r h i n g e si f re moved. I n s ta l ld o o r b y a l i g n i n g i ngepins and slidedoor down to engagehinges . h Installcotter pins or rings in both hingepins of door. WARNING Failureto install a cotter pin or ring in each door's two hinge ns mav allow door to depart aircraft in fliqht. 4. Reconnect door's gas spring. aft

4 . 1 4 0 F a i ri n g C o w l i n ga n d In sp ection , Panels MS27O39COB screws are used for fastening all removablecowlings and inspection panels. 4 . 1 4 1 En g i n e o w l i n g C Enginecowling includesleft-handand right-hand belly cowling cowling assemblies, assembly,and the aft cowling assembly. The lower edge of both engine cowling assemblies are supported by removable channels. The air intake hose is attachedto right engineside panelassembly, which may be removedor connectedthrough door in panel. Lower left slat in aft cowling assemblymay be removed for accessto clean out anything that may have fallen through slats.

Ch a n g e1 4 : J UL 2 OOB

Pa ge4.5

FICIBINEiCIN

MAINTENANGE MANUAL

MOE EL F|44

4 , 1 4 2 M a st F a i ri n g

for must be installed fli rotor gearbox at swashplate The c261 mast fairing upper rib is mountedto main gearboxmast assembly' tube assembly. t-owei rib is clampedto main rotor The pitot tube is mountedon lower front of mast fairing. throughgrommetsin lower rib and attach to middle The fuel tank vents are installed is push- pulltube m ounted r i b o f m a st fa i ri n g .T h e C 6 6 5 -2guideJttttOl' for C121- 5 tube' preloadon push-pull to to center rib. lt shouldbe adjusted minimize 4 . 1 4 3 U p p e rC o w l i n g behind and below auxiliary cowling above horizontalfirewall includes DO42doors cowling' tank, cg47 panelsaroundmast tube, and c706-1 tailcone

All cowlins must be installeO &fllight.

Page4.6

C h a n g e1 4 : J U L 2 0 0 8

FICIBINSCIN

MATNTENANeE MANUAL

MOEIEL

F|44

4.144 CabinInspection Panels CAUTION panelsmust be instalted riight.All tnspection for panelsmay be left off for run-up.All must be installed flight. for

panelsincludethe following: The cabin inspection 1. 2. 3. 4. 5. 6. C794-1forwardbellypanelandC794-3aft bellypanelassembly. C465-1and C465-2att seat back panels. C474-1 panel between the aft seat backs and C474-2 panel betweenthe aft seats. C463-1 cover underthe C464-1 tray. C445-1 and C445-3 covers between the forward seats and CM4-1 cyclic box cover. C461-1 collective crosstube cover behindthe left forward seat.

Change 1 Jun 97 4:

Page4.7

F|CIE|INEiCIN

MAINTENANeE MANUAL

MOEIEL

F'44T

WARNING All welded steel tube frames used in the R44 are stress outside Robinson are iJii"ueO.ruo-weiO-iepairs permissible ComPanY. HelicoPter on The followingsteeltube framesare required the R44z C02O-1 UpperFrameAssemblY L.H. AssemblY, CO46-1 LowerFrame R.H. CO46-2 LowerFrameAssemblY, CO46-3 Strut AssemblY C237-1 FrameAssemblY L.H. Assembly, 4.210 LowerFrame Removal 4.211 Frame all a) Remove cowling. b) Removemain rotor gearbox,includingboth fuel tanks, per Section 7.110. per and tailcone clutchassembly, SectionO powerplant, including c) Remove 6.110. d) Removebatteryand batterybox. Panel. e) Removeleft aft seatback tligur" a-?Lt DetailsD, rhe f) Disconnect threeforwardmounting_.pointq (Figure 4-28, DetailH). point E, anOF) and tne at mounting gearmountingbolt' g) Disconnect left aft NAS1307landing the 604-2bolt and the C722-2 capscrew connectingJhg the h) Remove NASO 4-2, DetailsA & frameto'ine foweifettlrime aisemOly(Figure upper B).

P a g e4 . 8

Change4: 1 J un 97

FICIE|INEiCIN

MATNTENANeE MANUAL

MC'EIEL ]''44

NAS6604-2 BoLT (2 AN960-4161 WASHERREQ'0.) NUT NAS679A4 (2 PL'CS. ) c020-1 UPPER FRME c046-2 LOt,IER FMME

BoLT NAS6604-2 '0. (4 I.IASHERREQ ) AN95O-4161 (2 REQ',D.) NUT NAS679A4

c046-6 TUBE

NAS6604-2 BoLT (2 WASHER REq,D.) AN960-5161 (2 AN96O-4161 WASHER R E Q ' , D . NAS679A5 ) NUT NAS679A4 NUT (2 PL,CS.) (3 PL'CS.) c020-1UPPER FRAI4E /\ /

NAS6605.21 BOLT

c722-z scREbr +l Mszooozclo *rT-/BoLT NAS6605-4 (2 I'IASHER R E Q ' D ) 4N960-5161 NAS679A5 NUT (4 PL'CS. )

.\

I

.

LO!\lER FRME

or WASHER AN960-416 4J.61 AS REQUIRED SHIMMING FOR (2 MAXTMUM)

FRAME INSTALLATION TUBE 4-2 STEEL FIGURE

Change : 15 Jun98 5

Page4,9

FIC|BINSiCIN

MAINTENANcEB0LT NAS6604-2 (2 ttAsHER REQ'D-) Ang6o-qrot

MANUAL

MOEIEL ]r44

c632-1ANGLE

NUT NAS679A4 (2 PL',C) . S

BoLT NA.S6604-4 (2 WASHER R E Q ' 0 . ) AN96O-4161 NUT NAS679A4

(z pr-'cs. )

BoLT NAS6604-2 (2 !',ASHERREq'D.) Anioo-qtotNUT NAS679A4 (2 PL'CS.)

c046-1 L0l,lER FRAME

BoLT NAS6604-3 (2 WASHERREQ'D.) AN960-4161 NUT NAS679A4 (2 PL',CS.) BoLT NAS6604-3 E R A N 9 5 0 - 4 1W1 S H ( 2R E Q ' D . ) 6ANUT NAS679A4 (4 PL'CS. )

NAS66O4-2 BOLT (2 I,IASHER REQ.D. ) AN960.4161I

NUT NAS579A4

(z PL'cs.)

t

B0LT NAs6605-24NUT NAS679A5 (2 PL'CS. )

(2 D. [ijei[:iroi t^tnsHrnREQ')

BoLT NAS6605-23 E A N 9 6 0 - 5 1W1 S H ( 2RR E Q ' D . ) 6A NUT NAS679A5

INSTALLATION FRAME TUBE 4-2A STEEL FIGURE

P a g e4 . 1 O

l s s u e d1 1 J u n 9 3 :

FIClEIINsic|Nc046-3 STRUT

MAINTENANGE

MANUAL

MOEIEL H,44

@'c046-2 LO!||ER FRA}IE ltAs6605-4BoLT (2 NASg5O-5161 WASHER R E q ' 0 . ) . . . NAS679A5 NUT a B33O-16 PALNUT

Y\

BENT TUBE c237-l FRAME

tii t' t \ \ \

\

c020-1UPPER FMME

(R.H. c384-6 ANGLE ) (1.H., SHol,lN) c384-7 ANCLE

c020-1 c141-4WASHER REQ'D.) (2UPPER FRAME NAS679A7 NUT 8330.21PALNUT (4 PL'CS. )

BoLT NAS6607-24

-r c237BOLT NAS66O5.4 c046-1 WASHER AN96O-5161 LOl,|ER NUT NAS679A5 FRAME 8330.16 PALNUT (2 PL'CS. ) VIEI,I LOOKING FORI.IARD ( 1 . H) .FRAME

o/

c023-1 TAIL CONE ASSEMBLY

INSTALLATION FRAME TAIL CONE AND T FIGURE-28 STEEL UBE 4

2: Change 12 Dec 94

Pa ge4.11

FIGIEIINSiC|N

MAINTENANeE MANUAL

MOE EL F'44

(cont'dl 4,211 FrameRemoval il I I | 'il the left frame assemblY' Remove

RemovetheCOl4-7landinggearsupportandD31O-5cowlingbracketfrom the left frame assemblY'

4.212 FrameInstallation gnlisto-5 cowling bracketper al Installthe col4-7 landinggears-upqgft Figuie5-1, DetailB. Torqueper Section1'3zo' B, -D;E; Installall hardwareper Figure4-2, Detailall b) Positionframefor installation. Fisure +2B., oetait H. Install ind' F;;"d Fiqure+z1:;-D;iaits beforetorquing. ha-rdware

c l T o r q u e a l l N A S 6 6 0 0 b - o - ! t s p e r S e c t i othe3 2 0 ' T g firewallP C 7 ? 2 - 2 C a p n l ' c385-1 l q g " : h doubler screw per secii6n-i.$o-lrio-tateii wire to wire. with 0.b41 inchdiametermountingbolt per Figure5-1, DetailB, and landin_g-gear d) InstallNAS66O7 torqueper Section1.320. per el Installpowerplant Section6.120' fl fnstalltailconeper Section4,312, gl Installmain rotor gearboxper Section7 '12O' per hl fnstallclutch assembly Section7'22O' il il InstallbatterYbox and battery. is Verify all mountinghardware torquedand instatlleft aft seat back panel'

kl lnstallall cowling.

4 Page .12

2: Change 12Dec 94

FICIBINSCIN

MATNTENANeEMANuAL

MOEIEL F44

4.22O Lower FrameAssemblv. R.H. 4.221 FrameRemoval a) Removeall cowlipg. bl Remove mainrotor gearbox, including both fuel tanks,per Section7.110. pow_erplqnt, cl Remove including tailcone,CO46-3strut, and clutch assembly, per Section 6.110. dl Removeright rear seatback. el Disconnectthe aft NAS66O7landinggear nxrunting bolt from the right landinggearsupport. fl Disconnect tv\roforward mountingpoints (Figure+2A, DetailsC and the El.

gl Removethe NAS66O4-2bolt and the C722-2 cap screw connectingthe upperframe to the lower right frame assembly(Figure4-2, DetailsA and Bl. hl Rernove right frame assembly. the il gearsupportandthe D310-6bracketfrom the Remove C014-7landing the right frame assembly.

4.222 FrameInstallation al Installthe CO14-7landinggearsupportand D310-6 bracketper Figure 5-1. Torqueper Section1.320. bl Positionframe for installation.Installall hardwareper Figure4-2, Details A and B and Figure+2A, DetailsC and E. Install all hardwarebefore torquing. c) Torque all NAS66fi) bolts per Section 1.32O. Torque the c722-2 eap screw per Section 1.33O and safety wire to the C385-1 firewall doubler with O.041 inch diametersafety wire.

Change 12 Dec 94 2:

Page 4,13

FICIBINSCIN

MAINTENANcEMANUAL

MtfEIELF,44

(cont'd) 4,222 FrameInstallation

, bolt per Figure5-1 and torqueper landinggearrK)unting dl InstallNAS66O7 Section1.320. per e) Installpowerplant Section6'120' fl Installtailconeper Section 4'312' gl fnstall main rotor gearboxper Section7 '12O' per hl lnstallclutch assembly SectionT'22O'

is hardware torquedand installright aft seat back o i) Verify all mountingPanel. il Installall cowling.

4.23O UpnerFrameAssembly 4.231 FrameRemoval powerplantmust and Beforethe upperframe is disconnected removed,the be either removedor supported' CAUTION Extensivedamageto the firewall and lower frame isiembties *itidccui ii powerplantis not supported is or if suPPort dislodged. all al Remove cowling. b) Removeclutch assemblyper Section7 '21O' both fuel tanks, per section7'110' including mainrotor gearbox, cl Remove tailconeper Section4.311' dl Remove or e) Supportpowerplant removeper Section6'11O'

P a g e4 . 1 4

2: Change 12 Dec 94

FICIBINEIC|N

MATNTENANeE MANUAL

MOtrlEL H'44

(cont'dl 4.231 FrameRemoval f) Remove right and left aft seat backsand panelbetweenseatbacks. the

g) Remove per C316-1uftperbellcrank Section 8.531 and remove C121the 15 push-pull tube. h) Removethe C723 bulkhead assemblies the aft end of the horizontal at firewall. i) it Remove NAS6605-4boltsat the aft outboard the corners the horizontal of firewall(Figure 4-2B., DetailsH). Remove NAS6600 bolts and the C722-2cap screwsshown in Figure all 4-2, DetailsA and B.

k) Remove upperframe. l) assembly Remove and 4331-4 bellcrank C329-1bearing blockassembly from upperframe.

4.232 FrameInstallation pointsof all sealant, grease oil. Install and frameand mounting a) Clean upper screws,AN960-8L using AN5O9-8R11 C329-1 bearingblock assembly washers, nuts, 3 places. Install and NAS1291-08 per A331-4 bellcrank assembly Section8.542. lnstall all hardwareper Figure4-2, b) Positionupperframe for installation. before DetailsA and B and Figure+2B, DetailH. Installall hardware torquing. c) Torqueall NAS66OO bolts per Section 1.320. Torque the C722-2 cap screwsper Section1.330 and safety wire to the C385-1 firewalldoubler with 0.041 inch diameter wire. a fuel seepage. to sealant prevent d) Sealfirewalts using B27O-1 assemblies. e) Install the C723 bulkhead per the 8.532andinstall C121bellcrank Section f) Install C316-1upper the 15 push-pull tube. per g) fnstallpowerplant, removed, Sections 6.120. if per h) fnstall 4.312. tailcone Section

1 Change : 2 Jul93

Page .15 4

I

F|ClBINSiclN

MAINTENANeE MANUAL

MOEIELFI44

(cont'dl 4.292 Framelnstallation j2O' il lnstallmain rotor gearboxper section7 per i) Installclutchassembly SectionT'22O' aft seat back and k) Verify all mountinghardwareis torquedand install centerPanels. ll Installall cowling. and lnstallation 4.24O- Strut AssemblvRemoval To removethe C046-3 strut: a)Removerightenginesidepane|andaftenginecow|ing. lower frames' b) Supportenginefrom below to reducethe load on the c}Removeupperand|owermountingbo|tsandremovestrut. To installthe strut: G and as a) Installstrut and hardware shown in Figure4'2F.,Details bl Torquebolts PerSection1'320' enginesuPPorts' c) Remove d) Installcowling. AND EMPENNAGE 4.300 TAILCONE 4.31O Tailcone Removal 4.311 Tailcone a) Removec7o6-1 tailconecowlingand DO4O-1 cowlingassemblies' .tft light,and chipdetector) strobe,tail position wiring (antenna, b) Disconnect to tailcone. c) Mark tail rotor drive shaft and A947-2 flex plate for reinstallation. H'

P a g e4 . 1 6

Change4: 1 J un 97

FIClBINEiclN

MATNTENANcE MANUAL

MtfEtEL

F'44

4 . 3 1 1 T a i l co n e e mo va (co n t' d) R l d) Disconnecttail rotor drive shaft at intermediateflex plate. Use a rag or foam rubber to support and protect forward end of drive shaft in taitcone. e) Disconnect forward end of C121-17 push-pull tube. f) Remove four bolts that hold tailcone to steel tube frame (see Figure 4-28, D e ta i ll l . g) Carefullyremovetailcone. 4 . 3 1 2 T a i l co n e sta l l a ti o n ' In 1. Verify C237-1 frame assembly installed upperframe with bent tube down is in and tabs to right per Figure 4-28. Verify tail rotor drive shaft damper bearing i s i n co rre ctp o si ti o np e r Figur e7- 11.

2 . Install tailcone onto upper frame. Ensure wiring exiting tailcone forward

frame is not pinched.Standard torque bolts per Section1.320. Installiralnuts, standardtorque per Section 1.320, and torque stripe per Figure2-1. shown in Figure8-14. Standard torque bolt per Section1.320. Installpalnut, standardtorque per Section 1.32O,and torque stripe per Figure2-1.

3 . Connect C121-17 att push-pulltube to A331-4 intermediatebellcrankas

4 . Installand shim intermediate flex plate per Section7.330. 5 . Checktail rotor drive shaft runout per Section7.34O. 6 . PullStrobecircuitbreaker. for Connectelectrical tail connections strobe,antenna,positionlight, and TR chip detector.Individually test and verify correct function of tail positionlight and TR chip light circuits.Turn NAV LTS switch off. strobe light. 8 . Ty-rap wiring as required. 9 . InstallC7O6tailconecowling and D04O aft cowling assemblies.

7 . Push Strobe circuit breakerin. Individually test and verify correctfunction of

Ch a n g e1 4 : JUL 2OO8

Page .17 4

FICIBINBCIN

MAINTENANcE

MANUAL

MOE EL F44

R 4 . 3 1 3 T a i l co n e e P a i r refinishing. Repairstotai|coneare|imitedtob|endingoutscratchesand

D E N T SIN T A T L C ON E : inch deep, Dent minimumbottom radius:O'125 No dents greaterthan O.O3O inch. fotut affecteddiameter: 1.25 inch max' stations:4 inches One dent p"r rtriioi, ,nini-ur dirtun"e between No sharp iricksor cracks allowed' repair'

to iiJv-onoir1r""li-iti reprui"t"il"on. or return RHcfor0 . 0 1 Oi n c h d e e P (Lessthan 15o from tailconecenterline)

Q Tailcone

inch deep O.OO5 ( M o r et h a n 1 5 o f r o m tailconecenterline)

L S T AI L C ON E C R A T C H IMITS: are to relative tailconecenterline orientation Allowablescratchdepthsconsidering of of RHcreplacemert thatsection scratche" asshown. radi us ' O.1Oinch blend oui; mu st Oe' UTenOed ,"e r ninim um t a i l co n e . S cra tch e s "*"""iiili;iir;q;i* A 4 . 3 2 O E m p e n n a g e sse mb l Y e 4 . 3 2 1 E mP e n n a g R e mo va l a ) Re mo veD O7 9 -1ta i l ro tor guar d' ta b ) Di sco n n e ct i l p o si ti o nlight wir e' c)Removetwoattachbo|tsattailconecastingand a sse mb l Y . P a g e4 . 1 8 r em ove empennage

1 Change 4: JUL 2OO8

FIC|ElINSiclN

MATNTENANcE MANUAL

MIfEIEL

F44

4.322 Empennage Installation 1. Installempennage assemblyonto tailconecasting. 2. Install attachingbolts with washers as requiredunder each nut to maintain properthread engagement. Standardtorque bolts per Section1.320. Install 'palnuts, standardtorque per Section 1.320, and torque stripe per Figure2-1. 3 . Co n n e ctta i l p o si ti o n l i ght wir e and install MS21919 clam ps for tai l r otor gearboxchip detector and position light wiring. Ty-rap wiring as required. Individuallytest and verify correct function of tail position light and TR chip light circuits. 4. Installtail rotor guard per Section4.330. 4.323 VerticalStabilizer Replacement 1. RemoveDO79tail rotor guard if replacing lower verticalstabilizer. 2. Removefour bolts and screw at trailingedge and removeverticalstabilizer. 3. C554 clip at trailingedge may be reusedby drillingout two rivets. 4. Fit new verticalstabilizer. Fileskin as required a 0.030-to-0.120inch gap for to horizontal stabilizer. 5. Installverticalstabilizer.Attach C554 clip to horizontal stabilizer.Match drill clip to vertical stabilizerwith #30 drill and rivet using MS2047OAD4rivets; N A S 1 9 1 9 B 0 4 S l i n d ri vet is optional for war dhole. b in 6. Specialtorque verticalstabilizer attach bolts per Section 1.330 and torque stri p ep e r F i g u re -1 . 2 7. lf removed,installtail rotor guard per Section4.330.

C h a n g e1 4 : J U L 2 0 0 8

P a g e4 . 1 9

FICIEIINSiC|N

MAINTENANcE MANUAL

MOE EL ]''44

Replacement Stabilizer 4.325 Horizontal lower vertical.stabilizers' 1. RemoveDO79-1tail rotor guard and upperand remove N1S21919clamps from 2. Disconnect tail position light wiring and horizontalstabilizer. stabilizer' 3. Removehorizontal usingNASl 149F0663Pwashersundereach nut stabilizer 4. Installnew horizontal EqiqnA nut' Torquebolts per Section1'32O' as requireAiii i:qthreads per Figure2-1' """pot"O Installpatnuts,torque p"t S"5i''J;l:420, ;nd torque stripe to p'QS.Q, O'12o-inch 5. Fit vertical stabilizersto horizontalstabilizer'.Verity stabilizerskins' File clearancebetween horizontJl'rtunirirriskin and vertibal skin(s)as required' verticalstabilizer inch in attachingho-lgs C554clips.anddrill a O'144 6. Align horizontalstabilizer stabilizer. Deburr hole and diameter hole through traitini-;ff" bi rroiirontal stabilizer' fasten clips to horizontal per section 1'330 and torque 7. Special torque erglt vertical stabilizerbolts s t r i P eP e r F i g u re2 -1 . clamps for tail rotor 8 . Connect tail position light wiring and install MS?1919 "*a test and verifv

il;;il

correct tunctton of tail positionlight and TR chip circuits'

ir,ip-o"tJ;i;;

nosilgnlight *i,'ns. lndividuallv

9 . Installtail rotor guard per Section4'330' 4.326 F | o a t S h i p ( R 4 4 C | i p p e r ) c o s o S t a b i | i z e r R e m o v a | 1 . R e mo vescre w sfro m D O81- 2block and r em oveblock' Rem ove and remove block38p screw tror uii,'fower frolein DO81-4block assembly assemblY. NAS1351- 4-

when both NAS1351 are Tail skid and float stabilizer unsecured stabilizer' Cut sealantaroundedgesof attach bracketsand removefloat fr om Step 1 i n aft l n se rt N A S 1 3 5 1 -4 -3 6 Pscr ew ( note differ ent lenqth inJtutt in vertical stabilizerwith lower hole of DO81-4 block uttttitt'.;g w N A d i 1 4 g F o 4 1 6 P a sherand M S2104214nut' -4-51P (note differentlglg^!\f1om Step 4 . fnstall DO81-2 block with NAS1351 MS21O42 L4nut' 1 scre w i n u p p e i -tro l e. install nltgOO- + tGLwasher and both NAS1351 Torque taii -and toioiliaro's sleeve. Ensureblocks rrr .iun1ping torque stripe' per Section 1.32O ""i"*t screwin Dogl -2 block'slower holeandtorqueto 40 in.-lb. 5 . lnstallNAS1352-3-14p

Page 4.2O

T o rq u e N A S 1 3 5 2 -3 -14P( shor t)scr ew last to obtain Proper of clamping tail rotor guard. Change

JUL 2OO8

FIC|BINSICIN

MATNTENANcE MANuAL

MOEIEL]l'44

4.327 FloatShip (R214 ClipperlC050 Stabilizer Instalation a) Remove NASl352-3-14P screwfrom DO81-2 block'sldwer hole.Remove NAS1351-4-51P screwfrom DO81-2 block'supperholeand remove Oioir.. Remove NASl351-4-36P screwfrom aft lowdr holein DO81-+ UloctLnO ,. removeblock. NOTE Tail skid is unsecured when both NAS1351screws are removed. b) Installfloat stabilizer. cl InstallNASl3Sl-4-38P screw{note length different fromstepa} in aft lower holeof DO81-4 blockandinstall blockon vertical stabilizer wiin Rrug6o-41 6L washerand MS21042L4 nut. dl Install D081-2btockwith NAS1351-4-S3p (notedifferent lengthfrom step a) screw in upperhole.lnstallAN96O-416L washerand MS2-1O4-2L4 nui. Ensure blocks clamping rotorguard's are tail sleeve.Torque bothNAS1351 screwsper Section1.320. e) Install NAS1352-3-14P screwin D081-2 lowerholeandtorque 40 block's to in.-lb. NOTE It is important torqueNAS1352-3-14p (short) to screwlast to obtainproperclamping tail rotor guard. of 4.330 Tail RotorGuardReplacement a) b) O c)dl e)

,

Loosen two screwsthroughDO81-2 blockholdingD079-1tail rotor guardto verticalstabilizer. Remove two boltsthroughforwardend of guard. Remove rotor guard. tailBeforeinstallinga new tail rotor guard,verify that a D081-1 spacer is properly positionedinsideD082-1 tube assembly. Slide new tail rotor guard under DO81-2block at verticalstabilizerand fasten forward end to D082-1 tube assemblyat