PERIODIC SERVICING PROCEDURES FOR SOVIET IL-14 [CRATE] AIRCRAFT EQUIPPED WITH ASH-82T ENGINES

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80-00247A000700080001-4
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 65
• Document Creation Date: December 27, 2016
• Document Release Date: January 8, 2014
• Sequence Number: 1
• Publication Date: July 24, 1964
• Content Type: REPORT

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CENTRAL INTELLIGENCE AGENCY
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This material contains information affecting the National Defense of the United States Within the meaning of the Espionage Laws, Title
18, U.S.C. Secs. 793 and 794, the transmission or revelation of which in any manner to an unauthorized person is prohibited by law.
COUNTRY USSR
SUBJECT
DATE OF
INFO.
PLACE &
DATE ACQ.
S-E-C-R-E-T
NO FOREIGN DISSEM
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Periodic Servicing Procedures
for Soviet IL-14 [GRATE]
Aircraft Equipped with ASh-82T
Engines
THIS IS UNEVALUATED
REPORT
DATE DISTR. 21/ July 1964
NO. PAGES
REFERENCES
1
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INFORMATION. SOURCE GRADINGS ARE DEFINITIVE. APPRAISAL OF CONTENT IS TENTATIVE.
English-language Soviet manual
entitled 1L-14 Aircraft, Complete List of Periodical
50X1-HUM.
Servicing Proceduresl
in Prague in 1959.
The manual was published
Distribution of Attachment: (for retention)
Army: 1 copy
Air: 1 copy
NO FOREIGN DISSEM
STATE I DIA I ARMY I NAVY I AIR
I NSA
I)( NIC
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GROUP I
Excluded horn automatic
downgrading and
declassification
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(Note: Field distribution indicated by "#".)
NFORMATION _REPORT INFORMATION REPORT.
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IfdENNIIDIMI ?
COMPLE?TE 1415 T
? 0.7 FE12 I OD I CAL =IV C YG ? PR 0 CT;DURES
FOR THE 11-14 AIRCRAFT WITH J&-82T
SE R
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General Instruction.
? . 1/ When carrying out the Periodical savicing procedures
it is necessary .to follev ?the order and technology stated in?
the inotruCtions for operation and technical .w.intentnce of
avitAional equipment., '
IV The :periodiCal servicing procr:dures of .the airframe,
eligines, electrical installation, instruments and.radio equip -
merit have to be effected. with regard to the flight hOurs of the
aircraft after each 25 4 5..5o 4 5, Ioo 4 lo and 300 4 lo
flight hours.
A/ In order to secure a troublefree operation of the, air-
craft in different climatic conditions 4 its bases /consiae -
a-able humidity, dust, etc./ in case of intensive operation of
different units /increased number of? landings/. and also in case
of longer interruptions in flight activities Or replacement of
engines, the responsible engineer is entitled to ren;Ier instruc-
tions for effecting of extraordinary proPedures'on all or SQUu
of the aircraft /units/ in accordance vith'the,presont complete
lint of periodical servicing procedurer.,
? 4/ In case of premature removement of engine or xeplce-
ment of some unit, the first servicing procedures of the newly
installed engine or unit should be effected before the appointed
tit,e simultaneously'with the accomplishing of the next Upurl
servicing procedures of the air'craft and further on after each
25 4 5, So4 5, loo lo, 3oo lo flight hours of the aircraft
calculated from the instant Of the first servicing proeueures.
5/ Tho replAcement of the pro-cartridges in the operating
. ?
heads of the fire extinguishing system bottles should be tffeoted
? S
ND F:a;.1EIC,IN DTSSEM ?
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after one year.
? V The hydraulic mixture? in the hydr&ulic system should
be exchanged after! .years..
? '7,7 The control tests of the aircraft air storage bottleb,
of the fire extinguishing system bottles and the oxygen h6ttles
should bu effected in terms indicated by the high prsurt, in-
spection official .on the bottles.
8/ In all assuMblies of the. aircraft airframe, ungine,
special equipment where thu use of tho,NK-.3o, G01-54, All?-7o,
GSA lubricants is foreseen, the CIATIM-2o1 grease may be appli,.:d
as veil..
E
Pre.-flight Proparation.
Thf:r pre-flight preparation of tht aircraft includes the
checking of the actual obndition of the aircraft and th accomp-
lishing of nrocedurcs required tor the preparation of aircraft
for the prospective flight.
rreparatory tiorke.
1/ ,Drain tho depcsits from the drain points of the fuel .
system. Thu- draining should be carried cut till the complete.
removement of water and fuel .contaminations froM the. sumps.
ClOse and lock the draining 'cooks.
-?,/ At tilt.: temperature of thE-, outsiae air of minus
grees of Centigrade and 'below that value. effect the warming up
of theingines according to the requirements of instruction
for operation.
V Untie the aircraft 'and check whether chcks are placed
under the lalding gear wheels and whether fire pxinguishing
means are in the near of 'MC aircraft.
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NO FORE:PM
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41 gemove the fiiator tlaMp from the rudder, the plugs from.
Htht; draining pipes of the fuel system, from the air intakes of .
the aircraft beating system and frem the anti-icers.
5/ Remove the :covers from the aircraft, engines, propellers
pressure heds and remove the vessels from below the engine co
lingo.
?
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Pre-flight Inspection of th ircraft by.
the Flight Engineer..
In order to ensure full inspection and for reduction of t1.1,'
time required for the inspection, carry out same according to.a
determined route.
Check the condition of. the starboard Tower unit
1/ Inspect the propeller, heater, distributing ring :%nd
check for dmage, proper locking and .Jil.leakge from the cylin-
der group of the propeller.
'2/ Check the atthchment of acces:.ories on the engine crank-
case nose part.
3/ Check the cowlings for leakage of'oil and fuel, for
correct cleing of locks and the air intake filter for foulinz
of the nosh.
4/ Check by mean of the metering pin the quantity of oil
in the oil tank and be sure of the relir,ble closing of the filler
neck cover.
'5/ Check through the filler necks of thefuel tanks t1.0
quantity of fuel and after this close tightly the covers. and the .
?
rubber caps of the. filler necks. Yu water or dirt shou1d be in
? the tubber cups of the fuel tanks filler necks. Imptct the up-
per surface of the ring and check th4 accesk3 hole covers for
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preper cl)sing and the win 4 upper skin for damage.
Check.the starboard landing gear installation
and engine nacelle.
? 6/ Inspect the righthand shock-absorbing strut of 'the
ding gear andl check for leakage of :mixture through the scaling,
make sure that the depression of the shock-absorbing strut equals
18J - 230 mm., Be sure .that the link of the leg attachment_ to
the lock of retracted position readily rotates roubd itz axle.
7/ Check the wheel tyres and hoses of the, brakin7 system.
for clunge, the tyres for normal depression At normal 6'roys.'
:weight the depression of the tyres should.be 55 - 65 mi:v!,
In case of necessity inflate the tyres to the. normal
pressure of air, rhich should be 4.8 - 5.2 .kg per sq.cm..
8/ Open the access door te the landing.gear extended posi-
tion lock and check the lock for proper closing, Make cure that.
the safety pin is fitted in the latch, that. the springs, th.
cables of the locks control and the teiminalswitches are not
damaGed.
.9/ Open the landing gear don-et inspect in the nacelle the
aacessories, pipe-lines, the hoses of the hydraulic, fuel, oil
and pneumetic systems and check for leeks and external, damages..
Chock the correct locking of the drain cocks and the attachment
of the accessories.
10/ Check the fuel Presence in the container of the primer.
? 11/ Be sure that the upper lock of thel?a/wing gear is oven,
that the springs, the cable of the lock control and the terminal
switches are not damaged.. Cl)se the doors.
Check the landing gear nose intallation:
12/ Inspect the nose. shockbe 14-11)(1n4VOUt of the landing:
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eear.end check for leaks of mixture through the selings. In -
opect th hiy aampenero and be Sure that no leaks of hye.rau-
lie mixture and damages occur..Actordinfs te the metering -.0im
check th(ldharging of the shimmy dampeners.? The uetering pins
should protrude over the cover by 6,5 - 12,5 mm. Be sure that
the link of the leg attachment to the retracted positien lock
readily rotates round its axle.
.13/ Chuck whether the landing gear upper 1pck is opened, ?
whether the springs, the cable of the cnntrol and the end switch
are not damaged.
14/ Check the condition of the nose wheel for dunage of
tyre and its depression. /At normal gross weight the deprescfon
of the tyre should be 45 - 55 mm/. If necessary, inflate the tyres
to the normal pressure of air, rhich should be 4.3 ke per
sq.Cm.
is/ Inspect and check the port power unit! landing .guar and .
nacelle in the eami. sequence and extent as stated above.
Check the wing lower part:
16/ Inspect the port detachable part of ring /ring outer
section/ from below and check for external damare. of the skin
of wing, wing flap, aileron and f the knuckle joints of hinge
brackets, be, sure that the. inspection doors. are closed tightly
and that the landing. floed-lights an.:. position lights are not
damaged, that the draining pipes .of the fuel .tanks are not fouled.
Check the covers of the fuel tanks access heles for lealcS of.
petrol.
17/ Inspect the lower skin of the centre section and wine fillets, fillets, check for external damage snd tight closiw: of
access doors. -s EcRT
? NO FOREIGN DISSEM
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Then inset the starbc.arart of ving in the sane
extent and sequence.
InSpect the fusela0:::-
18/ Inspect the fuselage noscpart and check. for..damrle
of skin,. elase of the landing floodlights, the pressure head and
the aerial installation.
.19/ Inspect the lefthahd board of the fuselage and check
for external clana.;o of skfn and fillets.
2o/ Inspect the tail plane, fin, rudders :..nd trim tabs and
, check for external damages and integrity of the tail light pro-
tectivc: cap.
.21/ Inspect the skin of ?the righthand border of the fuselai:!,
and be .sure that the access.doorr of the parachute fl.rc c..nr
.tainers c.rd the access doer of the water closet bowl n.re clouce..
Cheek the tail section and the rear cargo cunpartment:
22/ inter the :3ircraftc inspect the tail section and the
rear cargo .compartment and cheek for foreign matter and rater
accumulation. Be sure of the control cables correct condition.
Check the lock of the cargo compartment access dour for proper
Closing.
Check the passengers cabin:
23/Inspect the entrance door, vindevisv emergency exit
hatches and check for damage, reliable .closing of lucks of the
emergency exit hatches and for foreign 'matter in the cabin.
Chuck the fastening of the furniture. Be sure?A: the presence
of transportable fire -extinguishers c.nd oi their Sealing.
Check the front cargo compartment and the hydraulic o4otiont
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.FOEEIO DISSEM.
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4.
24 Inspeot and check:
- for foreign matter.
- for reliable closing of the front cargo compartment
access door,
- the level of fluid in the hydraulic system reservoir,
for leakage of fluid from the.rebervoir, pipe-lines connections
and hydraulie accumulators und for external .damages of theo,
units,
- the 03U-4 fire e:tinguishers, the board fire extin-
uisher and the integrity of their sealingr.
25/ .Open the protecting cover, inspect and check the. tnnk,
units, pipelines and connections of the fluid anti-ioer.system.
Check the tank for presence o; spilkit. Close the cover.
Check the flight compartmenti
26/ inspect f.nd check:
- the pop hatch and its attachment, the condition of
the safety cable and damper,
- the ,charging vith air of the emergency bottle for.
the extension of the landing gear nose leg and of the bottle of
.1.1ergency braking; ,the air pressure in the bottle should?be
minimum 120 kg per sq.cm. kake sure that the handle of the hy0-
raulic system hand pumps selector valve is in the position
"Yormal system", the removable RKG-1 handle is in "routch posi-
tion and the lower part of the handle and the lever of the locks
control is in extreue front pCsition /according to flight di,
ruction/. Be sure that the handle of the landing gear selector
valve is lucked in position "Extended" and the handle of the
-wing flaps selector valve is in positiOn 01Zetracted".
27/ Be sure that all circuit breakers /AZS/ are ON and
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.connect the ground battery aart to. the. electric system of the
airerait. In 'case that same in not available twitch on the air-? ?
craft storage batteries.' The tension on the electric syntem
should be miniiiium 24 volts Ahen unr.el to load/.
28/ Check the correct function Of the instruments acoordin
to the readings of the indicators having engaged tht elc.ctrio
-feed by the svitch on the switch-board of the pilots. Adjust
the indicator pointers of the altimeters to zero and collto the
readings on the scales of the instruzents ,A.th the actual atme
spherical pressure. The eafference in the rer,.di
..nGe shou10.
exceed ? 3 in of mercury.
2V Check the zero position of pointers of the vc:riowcters.
Collc.te the board clock.
'3o/ Check the proper aondition of the.electric warning.
tyvtem of the landing coat, wing flaps, shutters and doors.
. ?
31/ Check accordine; to the road ince of the fuel (,uvntity
E;euges and the l oil gauges the ooniormity with the quantity of
fuel and Oil and collate with the actual quantity of fuel ?vna
oil in the tanks., if necessary.
.32/ Check: by .euccessive'engrzement and disenagemnt for
short periods the operation of the 'electric w.onuniems: of thc:
.corling gills, oil cooler ehuttere, duet filters and booster -
pumps. ,
ff0M: When the 'engines are covered do not engige th,:: mechanisms
of the gills and oil cooler shutters .in order to avoid.dee ?
of same..
?. 33/ Check the operation of the light and oound si6na1 systesi
of the landing gear.
. 34/ Check by short-term onGag6mtnt and 'disengagement the
.?
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operation of the electro-meobanisme of control of the anti-leer
uci heatinc,- system flaps, of the pumps for the delivery of anti-
fre;ze fluid, the operation'of the electrio,heating of the frort
glasses and of the pressure head / in case that flight in ice
forming conditions is expected/. The current required fjr heatin
of one !.:;lase should not exceed 40 A.
35/ Before night flight check the illumination'of the in -
strumerte, equipment and oabinu,.the correct condition of BAT:0,
and ARIMOL Check by short-term engagement the correct condition
of taxying and landing lights. Chock the funttioning of the hr14cl.
flOodlight and the Ti.rs(,nce of sinal flx.res ahd eiGnal-
line; pistol.
36/. Uncleck the rudders, ailerons, throttle control levers,
.the narking brakes and check the operation and displacement of
rudders, ailerons and trim 'tabs, and especially ftr seizing and
tight travel. Set the trim tabs into neutral position.
57/ Cheek the circuit of the emergency pritching-off of ?
accumulator 'batteries by all of the emergency svitch.
38/ Check the oy)erction of engines, propellers and fuel
cooks control by movini; the ,control handles into ext-re Lw pcJei-
tionz, - the motien should be smooth without ecizing.
69/ Check the condition of lasses of the movable ?
lAndolic an; their locks.
4o/ Cheek the seats of the pilots and the operation of the
adjusting mechanisms and locks.'
,41/ Check whether epare fuses and electric lamps are pro-
Nided.
42/ Prior. to starting of the engines set the parking brake. ?
?At this the pressure ,in the .hydraulic aocum4ator of brakes.-
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'should be not 'below 75 kg per sq.cm, and in the brake ccording
to the reading') of the pressure i:auges 18 - 3o kc per sq.cm.
Lffect the ?tatting and?test run of the engines =galling
o the instruction for operation.
De sure Of the correct condition of the aircraft 'Awl report
on its readiness.
1're-flight Incpection of the Radio-equipment
by the Radio .-.op(Tator.
V Check the Condition and attachment of the aircraft atrt le,
the correct condition and oleanneco of aerial-, partition-, 3nd
through-insulatora, and the correct condition of the aerial? .
damping. Clean the aerials from dust and oil.
2/ Inspect and check the outside condition and attachrunt
,of the radio-equipment, the correctness of panels and boatle,
the ready operation of the remote control driven, the int:Ames
of the control instrumenta and the corroctneuS of the 1101,111s
? 1340heck the correct condition of the circuit for destruc-
tion of the identificator and incert?the explosien fork
socket it:Explosion?.
4/ Chock ?the attachment of the aircraft inside inle:o
the aerials and be sure f their reliable attachment to the .
through-ihnulators and to the terminals of the mdio-equirment
? V Check the fusers inetAaed in the radio equipment for
reliable attachment and the presence of the foreseen spare fuses.? ?
V Check the precence of the necessary number of span,
'radio valves.
V Check with running engines the operation of the eommuni?'
cation- and. ohort-wave commanding radio stations. ',hen ohec1in6
vn ?,
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be eure of the normal.. operation and tuning of the transmitters.
pina ,of.th possibility af monitering and. lintening other tra
miCsion. Be alb() sure that the hindranco in the receiving is
neglizible. Chock the correct contectica of the aircrat inter- .
communication system.
8/ Check the oPeratlon and correct incttalation'of the (1.),;1
of identificator.
' When testini; tho,radio- and radio-teohnidal equipment through
the.greund sources af feeding, the tension dhould be not lose
than 27.6 Volts.
Pre?flight Ins:yection?of the Aircraft Xquipmont
by the ravigator.
l/ Check the outside' condition of ths navigation equipment,
the ? preeenco of the cerrection Ciarams to the airspeed indice..tver,
'altimeter, com2aii. Do sure of the exact indication of. thu 04z.
craft clock.
2/ Check by outpide inspection the condition and ettachilent''.
of the radio-navigational cquipMent, the correct condition of ite.
aerials and of the aircraft inside Inlets of aerials.
S/?Clieck the presence ef.the netessary number of spare fueofr.
4/7ith running eninen /or through the airfield source.r)f,
feeding/ check the eporation of all the navigational equipMent:
the c2erat1on of the radio-couptscAs and of the lan:Ang equip-
ment, Switch on the,remoie-indication gyro...magnetic compass
/DGMK-3/ and collate its readingivith the magnetio'oompass /N1-11/
ftho difference in readings should not eXceed 2 degrees/. Switch
? - I
' on the artificial horizon and the electrical aro-right-left
, indicator 1/O1C-.48/. Check the correct heating of the .presoure
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NO FOREIGN DISSEM
-heads according to the warning lights.:
Pre-flight Inspection of the Aircraft
.by the Pilot.
After having received reports from the air-crew on the con--
1
dition of theiaircraft the commander of the Aircraft has tti in-
spect and cheOk the condition of the aircraft in the following
:sequence:
1/ Cheek,to be sure that the propeller blades and the en -
gine,oerlings:are not damaged and the locks of the cowlings
closed. Check the engine cowlings for leaks of oil :trld petrol.
2/ Check by outside inspection the wheel tyres to be sure
that they are inflated to normal pressure and that they shove no
signs of outside damage, that the depression of the shozkebsor
?
bing struts is normal, and that the dampers of the nose shock-
absorbing strut are norwaly charged.
3/ Inspect the wing, fuselage. and tail unit. Be our. th,A
the pressure head, the landing lights and avrials are not d.
' maged, and that the clamps, pins and. plugs are removed.
Be sure that, the aircraft surface hat: been cleaned.
,11/ Be sure thretthe dirlocation of the load end passengers ?
- corresponds with the permissible oentre adjustment and that the
cargo is fastened,in a reliable way.
5/ Adjust the seat and -pedals according to stature. Switclk
on the accumulator battery and check the charging tAth.petrol
.,and oil. Check the condition of the cabin vindows.
.Check the general condition of the instruments on the
Instrument panel by svitching :en the electric feed. Set Um
pointers of the altimetera to zero and collate the readAngs of
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pressure Mfference in readings. should not exceed 4 3
Check the zerz. !position of the variemeters.
A/ Try the operation of the rudders, check.the neutral ?
position of the trim tabs according to the warning lights and
to the mechanical indicator.- Check the. operation of thc-electro.r
mechanisms of ailerons and of th mechanical contrcl of ?tlevator
trim tabs After having accomplished this sct them into neutral
position.
7,/'Check the proper ?setting of the radio. identificr.tion
.If necessary, check the operation of the landing equipment. The:
checking of the landing equipment should be effected throUgh.thc
airfield source of feeding at the tendion of min4um 27.b volts.
Cheek -rith running.Ungines the operation of the commanding r10
station, of th(, radio-altimeter and of the SIM /Aircraft intercom-
mgnication system/.
Preparation Of.the.Aircraft for Repeated-Plight.
It is to be effected at short-term parking of the A.rcraft
on 'an intermeiary airfield on 'a track flight of the aircraft or
on the inspection line of the aircraft . in the startinc:-area
after one flight into zone. or after 4 - .5 circuit flying'.
The air-crev switches off the engines and,ohecks the fol. -
loving:
1/ The condition of the landing gear:
- inflation. and depression of the 'heel tyres and checks
the tyres for damage and the wheel rims for overheating,
- depression Of the .shock-absorbing Struts,
- leakage of the.hydraulic fluid at unions, accessories
and hoses ef the wheels brakincsystem,
-
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Declassified in Part- Sanitized Copy Approved for Release 2014/01/08: CIA-RDP80-00247A000700080001-4
T
NO eJ4NdlLal
?
- thelandind gear for mechanical damage.
1/ The cOnditionof accessories, in the engine no.oclls:.
--for traces of petrol or oil leakage from the acces -
-eurius and union o of thefuel and oil cyte,
- for mechanical damage of electric leads, pipe-linen
accessories f the systume .of the laningear and engine
nacelle ,'.00re
? .../L.//? I -11UNi
3/ The condition of the power unite:
- for damage of propellers, leakage of oil from below.
the' packing of the propellers and accessories in the front part
of .the engines,
check the nozzlue for leakage of petrol ane tho reli-
able attachment A the conductors to the epark.plUge,
? check the engine cowlings for luakage of petrol, oil ?
or hydraulic fluid,
- check the oil coolure for (1.7.mage and lecke of oil,
open the smn11 eide owls of the enj.nos and check
the mounting A. engine6 and accessories for leakac;u of petrol,,
'oil or hydraulic fluid and after having done this cleee the cowls.
4/ Thu condition of the aircraft airframe:
- fer?deformation, nicks.and perforation of tho ekin
Appecially of the wing flap?/,
? - for leaks of putreL on the panels of the fuel tank?
and in the draining pipes,
- for traces of leakage of the hydraulic fluid on the
1-1er skin of the fuselage nose Part,
- all access exora for proper olosing,
? - for damage of control surfaces, ailerons and. trim 'Labe.
5/ Check the charging of the aircraft with fuel and 01 ,
[
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&mai
Declassified' in Part - Sanitized Copy Approved for Release 2014/01/08 : CIA-RDP80-00247A000700080001-4
T
NO F'OBETC,11 DISEM
? - 16 ? 50X1-HUN
through the filler necke and according to the indicatOre. Re-
plenish the aircraft for the expected. flight, if necessary.
0
0YOTE: When flyinG circuits. it is necessary,- after a rough lan-
ding, to stop the airorE;ft on the inspection line, switch off
/stop/ the engines and check the condition of landing installa-
tion, airframe assemblies and power units .which have ben sub
jested to overloads. .Check the.air-tiehtness of the petrol-,
oil-, and hydraulic systems. Until this inspection has been ac-
complishe(1 the aircraft i3 not permitted to a repeated.flight.
After flight Prepardlon..
It is to be carried out after the end of the flight day'
/night/. Removing of defects is tu be effected after the after-
flight 'inspection has been accomplished. ?
Preltminary Procedures.
1/ After the aircraft has taxied-to the parking area,..
stop the engines, sritch 3ff.the accumulator batteries aid
the fire seeks. Lock the landing gear selector valve in
the position "Extended", the handle for locking of the contrsly
and parking brakes set into position "ON".
2/ Place wheel chocke:under the landing gear wheels, put
the fixator clamp on the rudder.
3/ Open the accesY doors of the landing i:;ear extended pc
pition 1,eks and after having maft sure that the leeks are close
fit safety pins into the looks.
:Lift the side covers of the engine cowlings, removk: the,
2.oirer: cowls, open the?landing.gear doers and all easily deta
chable access hole overs necessary for the inspection.'
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? --
Inirat
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? SECRET
q() '0'')RETCN DISSEm
- 17 -
When-removing and opening the oor1ings and access. doors.
attention to ensuring that they. shevoo treoos of leakage of
petrol, oiler hydraulic dluid and 'check the .correct condition
of the oovlings and. access doors.
5/ Defore the engine cools down drain o.6 1.o.1 of oll
from .the oil sump through the funnel prOvidedvith mesh I:. 24
MC holes in .1sq.cm./i inspect same and make. sure that the
oil does not contain metallie ?chips and;other metallic contami-
nations.
6/ Clean the aircraft 'airframe, the poi:4r units rInd
gear from dust and dirt. Rinse from?outpide the honeycomLF of.
the oil coolers.
?Prior to tho cleaning be sure that the rinsed assemblies
and accessories of the-ircraft show no traces of lea3:%ge of oil,
petrol or hydraulic fluid. In case that such traces are rever:).:A,
determine the cause of leakage.?Clen the. lavat:,ry.
7,/ Persons rho are not members of the air-crew. awl are
rying out the after-flight .preparation .of the itircraft should
receive from the air-c:cev notes on the operation of the airomft
equipment in flight and on all revealed defects.
After-flight Inspeotion'of.tile Aircraft
and Power Units.
1/ Inspect the propellers and oheck the folloving:
- the reliability of the. propeller attachment on the en-,
gine shaft and on the- blades in the propeller hub as A:ell.as the
looking. of the oil duct nut,
- chock for nicks, cracks, hollows and deep .rsortriqes
on the propeller.blades and the Setting of the blades aocord1r.
to the marks / 222/,
50X1 -HUN
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tasiom
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?
NO 1O9EIGN DISSEA
- 16 - 50X1-HUN
:check the reliability of attachMent of the antifreuze.
fluid duet pipe, the condition 'ring for damge .
and -fouling of the. .pipes, and the condition Of the clamps tmd
? their:taietying,
. ^ check for leakage of oil from belov the cylinder nrt,
the rear cone, and the rubber sealing sccIcets of the binder.
2/ Inspect the 'engine and their accessories and check tilt,.
? the flan g of the thrust bearing, the reliability cf
? its attachment and 'ec.fetying, the plugs on the crankcase nose
part and the attachment bolts of the nose part to the _crankcase
middle part,
?
- the comtant slieedsovern:Jr, the fittings and pipe-lines
of the selector valves, the plugs on the housing of the reductr
ths, reliability of attachment, safetying and check also fcr
leaks from the unions,
the rollers and cables of the regulater contra, -their
attadhment'and safetying,
r the collector of Ignition - the attachment .of detachable
leadr and adaptors, the Itli.ability f the collector attrchment
and the attachment of the adapters to the spark plugs,
- nozzles and YV-82T Pipes - for eventual interference,
-
leakage in. the unions and the reliability attachment.
- the magnetto and the starting coils - the reliability
of attachment and leaks of oll from belov the flanges,
- the cylinders and deflectcrs for reliable attatihment,
int otness of the safetyinE;, for leak of oil from bolo.the
Under flanges, the valve' housings and casings of the rock?q
arms., puoh-pull rods and for traces of overheating,
,
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4.1
Declassified in Part- Sanitized Copy Approved forRelease2014/01/08 : CIA-RDP80-00247A000700080001-4
C
FORE
- ,19
- the int;Ae pipes fr reliable attachment,
- the front oil 9u 4? for attaChment, Iealw.go of oil ?from
the ?joints and the condition of the eafetying,
-.thy engine mount fur cracks 'in the rine and .brace as-
? sembliest fur reliable attachment of engine to the mount cnil of ?
the?mount to the enzine'nacelle, for cracks and defurmctfon rn..1 .
?integrity of safetying,
the 2:4V-82T. pump for reliable attachx:.ert of the pump :..nd
Tilletto for interf.ering of pipes and freedom of motion of the
limb lever,
- the oil pump Ash-GSV, the hydraulic pump 118h-13,, tbe
fuel pump A-V, the accyF.sorieigf the feathering system /the
431 pump, the D-2500A and AVP.-4 electromotors/, their pipe-lines,
hosea and fittings,
7 the'reliability of .attachment and the integrity of lok-
? king of the .joints, unionsm 'Of pfi;ee, hoses ana fittin6n for
.of potrolooil or hydraulic fluid, for nutual intyrfering,.
hollows and cracks, ?
- the power generating unit and starter for reliable.
attachment and safetying,
-.the oil cooler and its girder - for cracks, intactnusg
.of safetying, for leakage of oil and by sure of the correct OtAt-?
dition of the doors control Muchtmism,
-.the throttle housing for condition of screws limitinc.
the turn of the flap, the intactness of eafetying of:the control
pugh-pull rod of flap and RS-24M..
4 the de-aerator for cracks, attachment, integrity and
cleanness of the drain
^ th(:, mesh of the dust filter for cracks and dirt,
?
50X1 -HUM
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IMO
Declassified in Part - Sanitized Copy Approved for Release 2014/01/08: CIA-RDP80-00247A000700080001-4
NO FOREIGN DISSFAI
. - the brackets, ?push-pull rods and.doors of cowlings,
meallanismb'vf the tors control for damage,. integrity of safe -
tying of the push-pull rods ,and the locks,
- the engine oil sump for 'reliable attachment, for cracks
and leaks .of oil,
- the exhaust collector 'for cracks, wear in unions, for ?
saeging of sections and breaking through of eases in unions, In-
terference of the engine section detr%ils,.
- the bodies of the silk and mesh filters for cracks,
fuel leakage from the unions and reliability of attachment and
eafetying,
- oil tank, hoses olid pipes in the engine nacelle for
reliability of attachment, integrity of safetyine, for damaee
.and leaks, condition of durite hOses and clamps,
- the eneine centrols for clarinet, interference of.Iin
kage, rollers and belloranks, for integrity of looking/ check
throughout the yhele.range of displamment/,.
- build up pressure in the fuel. system 1.3 - 1.e kg pr
sq.cm. and check. for leakage paying special attention to the ir7-
tiehtness of the /04A-V fuel pump sevling /for loakacc from the ,
draining pipe/. '
? ? 3/ Inspect the engine nacelles and their fittings and? phzek::','?1
- the doors of the main landine'gear and locks; the ]
.mechanism of the doors control for damagee and fouling; recti-
.1inearity-of push-pull rods and condition of the fireproof bulkr? ?
head, .
- the fire cock, the BC booster fuel pump, the aoces-
Sories on the hy4rau1ic panel and the accessories of the engine
priming system for reliability of attachment, ,..fetyinC.
, ; -
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50X1 -HUM
fer -
? NMI '
. .
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S E C R 1. ., ., / 7> 'r/1?1/, ~ii ? /
NO. FOREiGIN DI.5E11 .
trces..of leaks and for.attachaent of pi.de-lines,
:scoussories of the elctric system -and_tlectric loads
or rellablf, attachment and LAilinc,
?
-, the control oc.ble r2r?dmage, fouling -and integrity
yr the'turrbuckleE sarctying,
...drain the deposits frou the draining cocks of the
suLr,)-filiers.
4/ Inspect the main landing gear, their-section, and chec:
? - the wheel tyres:for'cracks, cute, lAinctures, svellinz;
'displacement of tyres /according to oarks/, fpr the inf1atin of?
the tyres /normal 5 4 e.2 kg per sq.cp/, and'cle:dressiori /55. -
- the wheel ,drums for cracks, traces :of overheatin6, tt
Anchment of the druus on the axle, integrity of fittincs and
leakage,
? the braking heses, the. hydraulic selector valve for
reliability of attachments, 1:ear and traces of leakage,.
- the shockvabsorbinc struts for normal du1ruesi,141
/13o - 23o raLV, for leakage, damage of filler rchs; ,letermine
according to .tiie traces on the inner cylinders the maximum stroke
on landing. in case th:t the stroke exceeded 290 mm chuck by
ueans of ;.ressure gauge thee inflation with air and recharge the
strut, ,
- the cross-bean, brace, torque. link .c.nd the loc:r rr!
sembly for damege, crack', greasing, check the condition of th
housing, floating piston valve, pie-line for leaks, clracksand..:
, fouling,
wrench,
-the.freedom of rEmolution of the torque link bolt by
- the locks of the extended and retracted position of
? C," .
? ?
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50X1 -HUM
1
Declassified in Part - Sanitized Copy Approved for Release 2014/01/08: CIA-RDP80-00247A000700080001-4
f/f re ,f "
SECRET
VO FORF,IC,14 DISSFY
.- .
:thc landing gear for damage of Ppringo and cables, for foulinc
:Jf locks, proper lubrior.tion and reliability of the terminal -
switches /Up and Down switches/ attachment,
- the hydraulic actuating cylinders of the landing gear
for reliabilityHof nttachment and for .damage or leakage.
5/ Inspect the landing gear nose leg, its section Acli/
and chock:
- the wheel tyre for cracks, cuts, punctureo, swelling,
displacement of the tyre, for nornr,1 pressure in the tyre /4.3 -
4.8 kg per sq.cM./ its denression 45 - 55 1r.1/,
. the wheel drun for damage, integrity of the axle safe-
tying in the fork,
?
- the chock-absorbing Strut for normal depression /170 -
26o um/, for leakage and damage of the filler necks,
- the fork, torque link and the coupling oi the shimmy
dampers with the movable yoke for damages, .cracics, lubrication,
integrity of safetying and reliability of attachment,
- the shimmy dampers fur correct charging / the pin
should :protrude. over the cover by 6.5 - 12.5 mm/, for leakqL:e
an damage /at the temperature. of minus 2o degreee of Centirv.d.
tht permissible. protruding of the pin is 'minimum 3.5 mm/, .
- the orose-beam, braces' attachment assemblies, door:::
and their' control mechanisms,for damage, cracks, correct sate -
tying' rlid lubrication,
- the ready turning of the torque link bolt by wrench,
? the locks of the landing gear retracted and exteneed
, position for damaEx of springs and cablee, for :fouling of lookc,
lubrication, reliable attachment of the terminal svitches and
the correctness. of safttying
_
Declassified in Part - Sanitized Copy Approved for Release 2014/01/08 : CIA-RDP80-00247A00070008nnn1-4
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Declassified in Part - Sanitized Copy Approved for Release 2014/01/08: CIA-RDP80-00247A000700080001-4
S,.E C R
PU P.013.jiG1,1DISSul
the hydraulie actuating cylinders of the main and
emergency system Of the landing gear for reliability of attach
tient, damne or leakage,
. accesSories, .pillo-lines and hoses the hydro-pneu -
natio system for leaks, weer ane other eamage and fer correct
condition 4f- the safetying.
8/ Inspect the centre section and chock:
the skin' for deformation, loosening or shear of rivets
and screws,
attaahment angles of the engine- nacelles to the centre'
section for reliability- et attachment and for cracks,
- wing flaps for damage of the. kin, correct condition
of the hinge brackets, proper lubrication of the assemblies and
correct condition of the bafetying.
7/ Inspect' the wing an check:
- the skin -for deformation, loosening. or shear of rivets
and acres,
- access hole covers for integrity of rttachment, cracks,
and 'correct condition ef the easily detachable access.Coer locks,
- the ailerons for integrity of skin, attachment of the
balance weights, fur cracks in the hinge assemblies and -
pull rods, proper lubrication of the hinges, condition of the
trim tab for damage, and seizing Uuring motion,
- the ailerons and trin tabs control. for sufficient
tension of the c,bles, correct c'.)neitien of the rollers. ,I.,,,l.bell-
cranks.and for reliable safetying,
-the pPmels of the fuel tanks for traces of leakagcr.,
clemness.of the draining pipes, integrity of screllia an their
loosening, check the condition of the oil tanks ahd fuel tanks
filler necks,
50X1-HUN
Declassified in Part - Sanitized Copy Approved for Release 2014/01/08: CIA-RDP80-00247A00070008mn1-4
'MEOW
Declassified in Part - Sanitized Copy Approved for Release 2014/01/08 : CIA-RDP80-00247A000700080001-4
NO FORXICP. DS:774
-.the fillets of the oentre.section to.the fuselage for
I;resunee of screws and fLa? their loosening as well as for (la -
1
mages 'an ClenOM'Cif the fillets,
^ the Odlaust pipes for reliable attachment ani oracks,,
- the landing floedlights am2, pordtion lights fyr da -
nr.zu ..of slackening of Attachment,
8/ Inspect the fuselage and check;
--the skin for deformations-slackening or shear of rivets
and screw,
- the entrance door, loadinc doers am:. the rT.o. doer
for damsze, tight cleSing and correct cendition of the locks,
the fairings, fillets and :7Ar intakes for reliability
,attacihment, deformation or slackening of attachments,.
- the aerial meets for ;....amai;e and reliability of at
tachment.
9/ Inspect the tail unit anti check:
.the skin of the fin. and 'tail plane for deformation,
- the hinge brackets of the control surfaces for cracks,
proper lubrication of the hinges, or plays and integrity of
safetying,
- the elevators, the rudder arid the .trim tabs for damao
holes and cracks, for slackuning or rotting of the fabric skit,
attachment of -the static balance veights, for interference of
the rudder .and elevator leading edges vith the trailing edges
of the fin and tail plcxe,,
-,the tail lizht for reliability of attachnent.
lo/ Inspect the inside tail section of the fuselage
check:
The
The control of the rudders:
? (.;
Declassified in Part-Sanitized Copy Approved for Release 2014/01/08 : CIA-RDP80-00247A000700080001-4
50X1-HUN
Declassified in Part- Sanitized Copy Approved forRelease2014/01/08 : CIA-RDP80-00247A000700080001-4
(.;
Fni-mcN
;
cables, rollers and brackets of their attachment fL,r
mar, tearing of cable strings, damage of the turnbuckles, cr
root condition of the safetying, sufficient?tension and correct
revolvin of the rollers,
- the pipe-lines of the fin rald tail plane taiti-ieur
for dama6e,
- the tube .of th:: rudder and the locking Mechanisn fr
damozes, integrity of attnclunont and safetying, fur fereico
ter in the section and the proper arrangeMent of the technicra.
11/ Inspect the passengers' cabin,f.,..nd check:
- the inner skin and the furniture Lfur damage or fou-
ling and for reliability of the vAtaohment of furniture,
- emergency exit hatches, vindows for damage, correct
condition of lockso.reliability of their safetyin and their
tegrity of blinds,
- the individual ventilation system, the ceilings. ,
for correct condition, for dauc.ge and deformation
- the fire extinguishers for integrity of attachm,nt''
and proper condition of thu sealire.
12/ Inspect the flight compartment and the service see
tion ;and check.:
- the emergency hatch for correct attachmcnt,'inte,7rity
of cable and of the 'shock absorbers,
- the hydraulic .reservoir for reliability zf.attach
ment, leaks, fluid level /according to the Measurin 1c.se and
table/t
- the -hydraulic aceumu1tto4, the tire extinguisher
'bottles for reliability of attachment, proper dondition of .
L?.
Declassified in Part - Sanitized Copy Approved for Release 2014)01/08: CIA-RDP80-00247A000700080001-4
50?X1-HUN
?
?
1w...wad
Declassified in Part- Sanitized Copy Approved forRelease2014/01/08 : CIA-RDP80-00247A000700080001-4
SECRYJ
NO FOREIGN ,DISSE;;,
- -
suaing..ahdofor leaks,
- the oabin glazin5.for.intezrity of the glasses, oor-
-Xect condition of the peep?windows v.na ;bake and for relinilit,.
of attachment of 'the glaso'olcanree
the sent? of the airworew fur reliability cf attnoh-.
ment, for damage and.cleannsbs of.runnert,
?
- the Control organs .of the aircraft and potur units ?
for seizing and tight travel /prior unlock/, -for foulin- of the
controls; then look the controls,
- check rhether the flaps of the heating are. anti-icer
equipment are cic.sed,
the ci4ntra1 board for fouling oi the livers, inte?:rity
indict torr: and dials, svitchee and instruments, for Verei..:n
matter inside the board.
After-flight Servicinz of the Electric Ecjiiprient.
1
V Check the accumulator batteries unr load cf 12 A,
when the tension in belcm 24 volts pass same for charginJ;.
8ritch off the accumulator batteriee.
2/ In the engine section chock:
- the rower generatine units, the reliability of their
:'..ttachment, be sure of thJ correct condition (111(1 tight fittin,.:
of the pretectin6. strips and of the Eafetying of their Clamping
. bolts, the condition and reliability of coupling of pipc-lineE; ?
of the power generating units cOoling system,
-.the electric mechanisms of the c,r1 gills, the elect-
ri.o starters, the electro-magnetic pri1.iri cocks and Of the
fonthering pumps. Be sure of the tight fitting of the protey
ting strips ani oapt of the cocks'and of the?currect condition
?
50X1 -HUM
un
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? bialW
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SEC T7?74,,
? NO FOREIGH f:MM
- 27 -
of the st,fvtying, cheek the str.rting coils,
- the Condition of the hoses of clootric leads., the
reliaility of their cittachment, relia141ity1of cou;ling aiqe
nttachment oi the plug- an('.-socket joints of the fireproof
bulkheae.. and at the .coccef,ories,
- the Condition of the fire svitchee=bdies, the relia-,
hilitY of their attachment :,,nd connection.
- the attachment of the terminals ef minus lead of th'
power generating units ant', of the starter.
.5,/ In the lnnding aer sectir;ne check':
- the distributinc devices for attnchment ot tpc; iu
stalation and connection the lers to tie fuses, relr,y anj,.
distributing mains, be sure that all dirt and oil has been re .L
move,
- the electro-motor of the feathering pump, the elect-
ric mechanism of the oil coolei shutters, the fuel pumps and .
tho electro-mechanisms of ?priming,
- be sure that the Correct condition and tight fitting,
of the insulating tapes of the electromoters, of the reliatole
attachMent of mechanisms and correct condition of locking;
clean the, accessories from dirt and oil,
- the reliable attachment of the electric ledr, their-
condition, the reliability, of engagement into the fitting and
Plug-and-socket connections, the reliability of attachment and
coupling at the parts of the plug-and-socket connections and
their safetying,
- for mechanical damage of ES-7 ballar,t resistors, the
reliable.,contact of the short pin rith th(,: aircraft body and
the coupling of the E-25A compensating
NO. i)1;;;
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mium
Declassified in Part - Sanitized Copy 'Approved for Release 2014/01/08: CIA-RDP80-00247A000700080001-4
stotRET
FOBETO DISSEU
?
50X1 -HUM
the correct condition and reliable attachment oi the
terminal- /Up and Down/ switches of the main and nose lf,nling
gear, the correct condition of the safetying, the proper condi-
tion of the. rubber'sealings and remov::1 of fouling,
- the attachment of electro-mechanism of the anti-icer ?
flvps-control,
thO oorroot conditlt,o of tho rressure
integrity of their sLfetxing.
4/ In the; centre neetion and in the in .check:
- the attachment of the installation /optill the central
switchboard and the accumulator paneW c.nd th couplihg of
to fuses, shunts of the ammeters,.relayry and ditributing mirO,
ty'Ae attachment of the electro-mechrmism of cabin vent fl.:T con-
trol. Be Oure that the Automatic circuit brenker is switched on,
-.the intakes for -accumulator cont:dnere vent, be sure
of their correct condition and clePnness,
- the pAro /position lights/ and head-.1ight:4 't)i sure
f correct condition and cleanness of their glatinc. 13ulbs rith
sagging 'filament or with darkened clss,hrve.to be replaced,
the attaehment of terminals of the main and neL;ativ(,?
leads.
? 5/ In the cabin of the radio-operator check:
- whether OA circuit breakers are switched on c.nd in
cOrrect condition, check the integrity and prepernees of the
fuses, the attachment and dampinc oi the t:::.rbin volt6c regu
laters paid the outside condition of the m(;:asuring instruments
and the installation for control on, the switchboard:,,
the attachment and damping of the glass heating. automat,?
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r
_
MOM
Declassified in Part - Sanitized Copy Approved for Release 2014/01/08: CIA-RDP80-00247A000700080001-4 -
SEC 11 //!//
"1 '
110
the. accuvtenesc of operation Of the switchte of
. electric devices,
- the condition ofthe electric leads /open the central
switchboard/ and the coupling of the torminr.ls to the automatic
cirOuit brtakero,
el In the flight compartment check:
- the correct .operation of the Switches and selector
?
switches on the switch-boards and panels of the acct000ries
oontrol,
? the.ekttachmert of the. K-5oD contactors? Rnd of the
automat of the propellers. feathering,
- the integrity of signal and control lamps of the fire-
extinguishing installation, the correct condition of the control
.knob n and of the safety plates,
- the integrity and tightenin of the bonding strips
attachment of the knobs of rheostats and UFO lamps.
7/ Test the ulectric equipment. under tension /through the
'airfield battery cart/:'
- the functioning of the electrofmechanisms of cowl
gills, of the oil cooler shutters, ? of dust filters, trin tabs
air flaps of the heating and anti-icing system, the E.ccuracy of
operation of the switches, selector switches with respect to
purpose and the correct reading of the pointer indicators
'and of the light sinal Oystem,
- the illuminating and light-signpl equipment: the. fit-
tinge of the illumination and of the ultraviolet irradiation of
the instruments and operating places of the air-crew, the cti-
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S E C T
NO I, OREI ?T?
- 3o .
ling lamps of the passengers cabin and auxilliary rooms, fit -
tins of'individuna illumination, the divre-sic,nal systet4.an.
also the inteority of bulbs and protective glasses,.their .
nese -rd prc...r operation of the: svitches, rheoFtats and buttons
'of%thcir circuita,
N ?
th6.oerrect operation of th electric heatin.: of thc
L...;lnns /the current pover sheltie. n6t exceed 40 A .hen one 0.e.s
heatine has been enaed/,
- the correct oper,Aion of the her liehte and BANO
position li6hts/1.
- the correct operation of the licht and sound sic:nal '
?
?
.system of the landinuemr
- the operation cf the electric pumps for telivery
fluid to the '2,ropel1ers canoTy glazine, and the correct cor,.
dition of rheostv.ts ?-nci. their circuits /check tozether' rith the
flihtni;ineer at oharcek:'..-sysitems/. ?
. .
After-fliEht Servicine of the Aadio-equipment.
],/ Take out th plus of the "LW unit ? from the
feeding socket and insert Some into the ,false socket.
2/ Be sure of the meoh;lnical
merit and cleanness of:
- the attachment assemblies of the aerials /,I,Aasts,
yokes!,
? caps,
correctness, 'reliable attach-
- the?throuch-linFtantors t'.nd their 'anti-icer shields,
- the leads, -hinge insulators, dampers and anti - leer'.
- the dipoles and the pin-like, emeroency aerial,
7 the f-.Ccess hole covers 'of the imide-fusulge aeritas.
,
1. ? 'NC)
---? , ?
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T ?? ; - /IT
- -
of the raaio compasses and radio-marker-receiver.
Remove dust and dirt from the aerials.
3/ In the tail section check the correct condition, re -
'liable attachment and cleanness of shock-absorbine: frames, hou-
sings. and front panels of -the radio-equipment and their bonding.,
be sure that the ? union nuts of the hich frequency cables and
of the cables for feeding of the equipment are .tightened. Be
sure of intactness, of the sealing.
4/ In the radio-operator' s cabin and service section ehec.r
the correct condition, reliable attachment, cleanness, and
condition o.f. damping of the equipment, working crystals of tho
Commandingradio.F:tation, dehumidifier of the loop aerials of
radio compasses, the reliable connection of.the high fre:quency
feeders and feeding. cctles, the condition of the main and emer-
gency aerials inlets and,their connection t3 the aerial switches,
through insulators, and to the. equipment.
5/ In the:flight compartment check the correct condition,
cleanness and reliable attachment uf instruments., panels,boards,
switches, and drives of the remote control of the radio-equipment,
fuses in the control paneler?of the radio-compasses and their
'vocordance with the nominal current, be sure that all foreign
matters have been removed.
6/ Check the operation of all radio-installations by sub
?sequent engagement throu6h the airfield source of current from
all places of their use, in all versions and ways of operation
and at all frequency subranges.Jie'sure of the normal operation
of all controls of the equipment; of the control instruments
.and proper.illumination of the dials.
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SECRET
NO FOREI ::prT Sf EM
?50X1 -HUM
Afterfflight Servicing of the Instrument
Equipment..
. 3,/ In the fliht compo.rtment and passerpjer cnbin check;
- the Condition Of the instruments./hy outside im7:?es-
.tiont, be sure Of the correct adjustment of dials of the baro 7
etric pressure of eltii.cters and of the settinL; of the vario -
ncterlointera to zero,
? writch on the electric supply ,and according to the :;c-
sition of the pointers make sure that the electric instruments
arc in ?carrect condition, ripe the.lasees of the instruments en.L.
the inttrument panel clean from -dust,
- the operation of the c3ckS for ent;agement of the citPtic
not cf the pressure head and of the servo-units of the auto= -
io pilot, be sure in the correct condition of the electric hoc.,
ting of the pressure head,
?- the. operation of the electric gyroscopic instruments.
ollate the readings of the remote control :;yromagnetic compass
ith the readings of the magnetic compass / the permissible if -
erence with calculation of the eeviation 4 2 degrees/, be cure
I the correct condition of the individual 'illumination of the
nstruments,
- the presence of the correction diagrams for the navi-
'ational instruments and the time of their validity.
2/ In the section of the'landing gear nose leg check:
? for leaks of oil from the unions of pipe-lines?at.thL..
uts of stuffing.boxes of the automatic pilot servo-units, for
Jroper tightening and safetying of the? stuffing box flute and
nion nuts of the *re-lines and for correct- Condition of the
mtomatic pilot pipelines,
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(.;
NO FOREIGN fAnam /77.-ft
- the cables of the automatic pilot follow-up system
for seizing of,rollers, tearing of strings and sagging of cal)les,
, for ,Cracks and breaks of the ttxtolite plate and for
correct condition of guide links of the automatic. pilot servo -
units,
the transmitter of the landing gear position indleator
and be sure of reliable coupling of its push-pull rod with the
landing gear tang and .of absence of plays at the push-pull rods?
connections, of reliable tightening and integrity of safetying
of the plug-and=pocket connection union nut.
A/ In the sections of the main landing gear check:
the correct condition of pipe-lines of the pneumatic
system for the supply of automatic pilot and pressure - vacuum
gauges,
- the transmitters of the landing gear positi3n electric
indicstura and the oleotric indicators of the oil coolers -shut-
ters position, the reliable connection of the push-pull-rodE.with
the tangs of the transaitters and eyes on the liinding ,gevr and
on the oil 'cooler shutters, be mire that there is no play at
the connections of the push-pull rods and that the attachment of
?'..the tange. on the transmitters is reliable,
- the reliability of the Pick-Ups of the electric oil
gauges and fuel .pressure gauges attachment to the fire-prof
bulk-heads,
- the reliable tightening and safetying of union .nuts of -
the pipe'-lines and plug-and-socket cpnneotione,.
- the condition.of the vacuum regulator mesh.
4/ In. the engine sections-check:
- the power generatiits of the. electric tachometers,
? S C
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1j, F0,-.(t;Ici 7
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be sure of their reliable attachment on the engines, check for
leaks of oil from below the generator units flanges, thtt,tiO. -
tening and safetying'of nuts of the plug-and-socket connections,
- the 'reliable attachment' and integrity of safet::ing of?
pick-ups of the oil temperature gauges and .of. the union nuts of?.
their plug-and-socket connections the cOndition and attachmnt
ot the UPRN-1 transmitters,
-? for breaks, cracks, deformation, wear and slackening
An the connections of .pipe-lines of the automatic pilot pneuma-
tic system, of the system of. the pressure-vacuum gauges and of the
electric pressure gauges of fuel,
- for grindings and tears of the armoured hoses of the
electric pressure gauges of oil, be sure of. the reliable faste-
-ning of armouring in the terminals, for damage of the hoses at-
tachment to the pumps and.to,the transmitters of.thc?instruments,
- the, transmitters of the electric indicators of the
cowling gills position and be sure of the reliable coupling, and'.
for plays at the couplings Of the push-pull rods with the tangs
of the transmitters and with the 'cowling gills-,
the correct condition and properness of tightening of
the bonding Strips and minus leads of the electric instruments,
Concluding Procedures.
1/.Remedy the defects revealed in flight and during the
after-flight inspection.
2/ Check. the proper condition of the fuel end lubricants
the cleanness of filters of fuel and oil filling car r%nd reple-
nish the fuel and oil system of the airCraft.
3/ Moor the aircraft on the parking place and set the fi
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e A T,To
YO VOITY,G71
-
xator clamp on the rudder. .
4/ Plate covers on the aircraft end engines.
5/ Arrange the.toOls and ground equipment.
Periodical Servicing Procedures.
The periodical servicing procedures have to bt carried out.
only after inspection in the extent of the after-flight prepara-
tion has been accomplished.
. After each 25 4 5 flight hours of the aircraft
3,/ Cheek the condition and rinse the filter of the
constant speed governor.
2/ Check the condition of the mesh and. Silk fuel filters,
rinse the filters, After reinstallation check the fuel symtem
for Fir-tightness under the pressure of 1.3 - 1.8 kg per so. cm.
After Eath 5c 4 5 Flight Hours of the Aircraft
Power Units
1/ Carry out the 25 h:urs Servicing prc:cedures.
2/ Check the cndition of the oil filters:
- of the front oil pump /11FS719-1/ the ruar oil pumr.
/ITS-19/ nnd of thu 1417-82 pump. When revealing c.,nfider0)1e
ling /752_ of the a.rea and of thc 1V-82 liltur mesh, it "
,necessary to check the, condition and rinse the oil filter of
RS-2414 mixture. governor. .
Check the magnetic plugs. of the front oil pumps - he sur-
that they are not fouled, damaged and Contain no metallic
rr-
titles.
Prior to reinstalling rinse the filters with fuel and grea
bc
with the YIC-22 or 113.2o oil.
?OTE: Inspection c.,.nd rinsing, of the oil filters have to be.
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go imlEum Dl
? .,
fectud also after replacing of units and pipe-lines of the oil
system.
5/ Check the condition of, the control of throttle valves,
?
censtant speed governors,. mkxture controls, cJwling gills, oil
cooler shutters, cross-fed'valvt;s and fire cocks, dust filters
and flaps? of the heating syktem.
Be sure of the. accordance .of the reading of indicators with
'the position of leers and switches On the panel, engines and le-
cessories.
? Check the correct position of cables on the rollers, for
tears of cable strings and for their interference with the de -
tails.of aocessories and for rear .and seizing of the rollers.
Restore the lubrication /CIATIM-2o1/ in the hingc, joints of
the engine control.
4/ Check the airvtightness of the oil dilution system cock.
At the temperrpire of the outside air above lo degrees of Centi-
grade the dilution system should ,be disconnected and choked.
5/ After accomplishing cf the periodical serv cing procc
dures test-run the engines, be sur1 their .correct Dperation
and then open the side cowlings, the landing gear doors and be
sure that all systems of the power unit are
NOTE: 5o hours servicing procedures for the porer units 1/;.v-,; to
be accomplished also after the first test-run of the newly in
stalled engine and additionally 'it is necessary in this case to
.w...xry out the fulloring procedures:
1,/ Check the condition, and rinse the mesh fuel filter of
the NV-85 pump and the oil filter of the 115.44p. mixture governor
/ri:thout.regard to the condition of the iM-82 oil filter/.
2/ Tighten the nut of the propeller ppinner. Effect the
tightening only on .cooled-down engine'.
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NO FOREI;;N DISSE
37 -
Airframe.
1/Restore the lubrication in all frictioning.aseembliers
of the landing gear and doors meohaniSms. Check carefully the
condition of the welded asiemblies and teNuS of the landing gear
meonanisme and landing gear hinge assemblies, be sure that there
are no crackaand damages. Recharge the lubricating nipples of
the journals. Check the value of the axial clearance in the
coupling of levers of the nose leg torque link. The total clea
ranee should be 0.1 - 0.3 mm.
2/ Check the value of clec.rance 'between the braking blocks
nnd the vheel lining; The clearance should be 0.3 - 0.4 mm.
3/ Ainstand inspect the locks of the landing gear exten -
ded and.retrapted position and the mechanisms of the locks control,
,cables, rollers' and belloranks. Be. sure that no tears of cable
strings occur, neither eeizing and wear of rollers, corrosion,.
cracks and damage .of the safetying.
Apply freEh CIATIM-2o1 grease on the frictioning Furfc,ces
of the locks and of the machaniems of the ? locks control.
? 4/ Check the?pPeration?of the emergency braking system. For
this purpose press. the ?braking' lever nki be sure/by clostayvtiCn
through the slot/ of the correct operation of the floating pi -
eton valves. After checking press 2 - 3 times the brake pedals
in order to return the floating piston valves into working po
sition. The time of the full braking should be 0.8 - 1 second.
of the unbraking 1 - 1,5 seconds.
5,/ Turn by 2 - 3 revolutions the filters of the hydraulic
system for cleaning purpoeep. Set the handles of the filters
paralelly to the aircraft axle and lock them.
Check..the fluid level in the multipliers of the brakes
.0J1
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