MAINTENANCE INSTRUCTIONS NO. II

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80T00246A062100090001-2
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 70
• Document Creation Date: December 22, 2016
• Document Release Date: December 6, 2011
• Sequence Number: 1
• Content Type: REPORT

Declassified in Part -Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
Declassified in Part -Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
 Declassified in Part -Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
MAINTENANCE INSTRUCTIONS
No. 11
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I. Inspections and maintenance operations on the
siroraft a}tould be performed in ootaPliance alth the present
Maintenance Inatructiona~ Foutine i:a+.ntenance Inatruc-
tions~ dircraft Operating and ?.:aintenanco Instz?uotiona na
xell as rith relevant inatruotions and bulletin;, in
effect.
2. L}:zinten;uzce operations rr,3~4od to the aircraft,
enGinear ermament~ radio, radar and aircraft oqulprcnt
s}could be performed at fixed 2ntervals de`er:;:ir:cd b~ t}:e
number of flying; hours, i. e, every 255, 50+5, and
100?10 fiyin~: hours. It ahould be noted tha. 50-hoar
maintenance should inoludc 25-}sour msi.ntenrince oper;alona
and 100-hour r~aintenanec should include 2~-};our ar:3
50-hour opcratior:a.
3. if the enr;ine or ot}:ar units of the ::Lcr;~2t have
bean replaced, r.:;tirten;u;ce :ror;t related to thc::c t:^.i.s
ahould be cr~z?ried o::. ;tfter ;, co:t::?n n:L:ccr o' il;~ir.t;
hour:, i.c. ;:ftcr 25+5~ 5p?; ,u~d 1C0~10 fl:r::? h-~:z?a.
this o;:ac csi:,tenr:r:ee or~~r:~tio::~ oar t':o r,o::l., it ~t:~ll~u?
en~;ino or unit i:ai? by Pc:rfo:ced ?e? oS r.^,, c::ae.
rl. .~,
~. to cr,auz?c troubla-free o,cr;i?icn e* :~ire::.~
t^ateriel under diverse cli::.r.tlo ce;::~:t'1o:;. (~'xv_.:'1:?;.
hunidityi duat~ eto.)r or :?:en ,:cci.^;c :;1*::ior:i ,::.:- ?
oith~?: a::n fro. fl:; 1:..:~_
s::1c. _ ,,. ., .
(lnadlr.~? i,e.u. o. ~z.;-,_:~?at .:~ ,
use) ";;en t}:o or,rit:ua }u... t: - _ _.. Y
~~6~..
henvler Iowa t:;;on ir~r?rl:~t?:1 vr:?"..F of .;~~: :-1~:.
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o
organisation ~~d unit commanders are entitled wi~
rigirc of ic:;uing orders on performance of maintenance
operations in all or individual aircraft oa? units
thereof ahead of time, in conformity with the present
baintenance Instructions No.21.
5. Prior to forwarding the aircraft for maintenance
it should be inspected according to the postflight inspec-
tion progr:l;, and a list of defects should be drawn up,
The discovered defects should be corrected by the
aircraft. and ground crews except for the defects which
can be eliminated during maintenance work only.
6. Before proceeding ~+itl, maintenance operations,
unload the seat ejection gun, after which the aircraft
should be inspected by the heads of the maintenance
1.'roups together wit
h the aircraft mechanic
scope of the postflight ins-?ecti
r on
.
7. All tl,e a ?
arfrau,e units except for the turbo-
oooler~ stabilizer emergency unit ~~,~ eleotriC
mechanism and wheel bearings should be lubricated with
i~41A~?I9Ia*-20~ lubricant
. The turbc-cooler should be
lubrieatecI with CY.~-122-14 oil, the AIIC-? mechanism -
with OI{~-122-12 oil, and the wheel bearings - with
HR-50 lubrioai,t. Cables enclosed in flexible metal
eheathir~ should be lubricated with LiK-8 oil or
transformer oil.
8? Corroded seotions of cables should be wiped with
kerosene-soat.:ed rags, then with dry rags and coated
with IfuATYltd-201 lubricant.
9. All maintenance work on the aircraft should be
performed with serviceable and maa?lced tools
Before and after m and accessories.
aircraft aintenance operations on the
oheck the tools against a special check list
to Prevent their loss or inadvertent leaving in the
aircraft,.
10. Before inspection and maintenance work on the
aircraft, remove dirt, dust, and old Lubricant from the
external surfaces of the aircraft unitsr arm?ur~ent, radio,
radar and aircraft equipment and their wiring and linkage.
11. Ball bearings of a closed type must be neither
packed with grease norti~ashed; they must only be raped and
coated with a thin layer of lubricant on the outside.
12. Inspection of the aircraft should be carried out
in a definite sequence shown in Inspection Ftouto (Fig.l);
the engine should be run up in accordance c~itli the Engine
Testing Chart (Fig,2).
13. Tho squibs of the spat ejection gun, canopy
jettisoning gu.n and fire extinguishing system should be
replaced every 12 months.
1~~. Before the beginning OP an inspeotion or maintenance
work on the aircraft take necessary preoautions tp prevent
accidental Firing, dropping of tanks, retraction oP landing
gears and undue functioning oP the eleetz?ic unlts which may
result in an accident or destruotion pf the aircraft materiel.
For this purpose, open the oockpit and, without olimb-
in, do the Yollo;iing:
(a) make sure that the seat ejection gun is locked by
the main and ground safety latches and that the face screen
handle, ejection levers on the arm-rests and the spring
mechanism levers are locked;
(b) check crhether the oanopy independent jettisoninG
handle is in the CL~'i:D (3~:It;~l.i'!0) position and locked;
(e) check whether the bo:ab jettisoning and fire
control buttons are closed r~ith pr~teo-cive caps ~~ d clips;
(d) eee that the L.G, control is loc:;cd in tae neutral
position;
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(e) cheek whether the storage battery and all electric
switches are OFF (circuit breakers located under the Ft, H.
organic glass panel may be turned OI+ except the AR1:lisD-SAF
(B3Fb~-HEB3PEIB) circuit breaker). L7:en irts-tzllinE; the drop
tanks on theaircraft do not etritch Ot; the battor~? and the
ground power supply source until the installation?of both
tanks is completed;
(f) check vrhether the Al~Sh'I) circuit is 03+1' (safoty pin
is in),
15. Adjustu:ent and checking of the seat ejection gun
firm,- link_:ge as well as test ejections by mezns of dummy
cartridges should be carried out by the armourers together
With the opcr~:tors prom the aircraft maintenance group..
klhen the seat is removed between the specified
maintenance intervals the seat ejection linkage should be
inspected b, the aircraft mechanic together with the
armourers prom the ground crew. The ejection gun should be
loaded vrith squibs acid duu,my cartridges (for tost ejections)
and unloaded by the armourer.
lu, Before proceeding ti~+ith maintenance work unload
the rocket armaments 3KCP--46, magazine and the seat ejec-
tion gun. All the operations related tp repairs prepara-
tion and adjustment op the ejection gun on tho ground
should be performed with the squibs removed.
17, ':hen the air craft engines are runnings the
personnel must keep at least 15 m. away from the front part
op the intake ducts,
13. pn aircraft with controlled stabilizer it
allowed to switch on the APY x) is pot
without switchin mechanism control unit
AHG4 electric mo hanism driviO, hydraulic booster 'or
a
The mechanism referred to hero and hereunder as
"A~ mech:uiism~' is the variablo ratio automatic boost
control unit.
19. All the openings in the aircraft units and pipes
uncovered during disassembly should be immediately closed
frith plugs or P.V,C. covers.
2C, To avoid emptying of the internal chambers of the
engine pumps open the filler neck of Ilo.l tank before
draining it and build up a pertain pressuro in the fuel
system (by the use of Iao,l tank pump) after rtihich close
the fuel cut-off cocks and drain the fuel.
21. t;hen performing maintenance operations in the
engine compartment (with the engines installed) observe the
following:
(a) all operations must be performed only with tools
secured by strin~,s~
(b) take necessary measures to prevent the removed
units and fastening parts from falling into the compartment;
for this purpose spread a clean. cloth around the unit
being serviced;
(o) all assembly and disassembly work should be
performed with closed air blow-off bands.
22. If the engine lubricating system has been drained,
fill the engine r~ith oil to the normal level before starting
spin the cold engine two or threo times then start it;
after stopping the engines check the oil level and add
oil to bring its level to 10.5 - 11 lit. mark.
23. Flhen starting the er~ine~ it is not alloti~ed to
leave the air blow-off band olased as this may pause engine
hunting during starting or operation or at intermediate
speeds.
24. Before carrying out any work in the ti?rclls of tho
landing gears wing flaps and air bralcea~ reduce pressura in
the hydraulic system do-~u to zeros srritoh off the c,toi?~~e
battery anal shift the air brake srritoh to the 1?.'il'~"DTD
(Bb1IIYll~HO) position,
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25. ti~'hen inspecting the air brakes do not extend thess
by pressin? the button looated on tho aircraft control stick;
" the air braY.es should be extended only by means of the stiiitch
located on the engine control lever. Failure to observe these
rulas may ca;,3e spontaneous closing of air brakes and lead
to ~m accident.
2F. }Iaving opened the sliding section of the canopy
2rom outsides shift the external opening handle to the
initial (,depressed) position; with the canopy open do not
switch 0}, the canopy pressurization cock,
27. The canopy glasses and rubber parts Should be
protected from sunlight by putting a special cover. on
the canopy of the parked aircraft.
2B. It is not alloti+ed to remove the canopy from the
airoraft together with t},c interloclaag cable.
Ylhen carrying out any r?~ork in the oookpit with opened
or removed oanopy, place safety caps on the rods oY the
oanopy remover pneumatic gun.
29. h'hile loading or unloading the airoraft armament,
plaoo a red danger ta;; or a red light 3 to 5 m. ahead of the
airoraft nose. In addition, whop installing the rocke?tn
into the pots a red danger tag or lamp should be placed
also behind the :aircraft tail unit. The tag or lamp
indicates that personnel are not allowed to approaoh the
nose or the tail part of the aircraft.
30. It is not allowed to start the engines moro than
tour owes in suooession including cold cpinnin,;; after fGus
st:u?tings mako a 30-minute interval.
31. Before atcu?ting the engine for the first time
at,d each timu after disooimecting the engine Suel system Or
replaoing tho fuel system units as tirell as whop them are
reasons to suppose ghat the fuel system fe air-bound, the
system should be prir,ed; fn this case the engine should he
started with open hatches; having checked the c~?s-twn for
tightness, close the h~.itches in the engine oompar?tment.
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Inspect and check the follo~+ing:
Intake ducts 1 (h'ig.l)
1. Look for shell holes and foreign objects.
Fuselage nose section. 2
2. Look for deformations and damaged sections of the
skin.
3. Checl, condition and attachment of the Pitot tube rod
and TII-15G impact pressure tube.
4. Look Por leaks in the de-icing system.
5. hiake sure that the armament and radio equipment
access hatches are closed.
Upper nose compartment 3
6. Check for any foreign objects in the compartment.
7. Inspect condition 6f the nose gear mechanical
position indicator.
t;ose Boar q
8. Check inflation. of the nose Mheel tyre be measuring
ite deflection r+hicii should be from 10 to 15 mm.
9. Check whether the grounding cable ie properly
secured in its socket.
Fig.1. Jnspection Route
1 -intake ducts: 2-fuseloge nose
section; 3-upper nose compartment;
4-nose gear; 5-main londrnq ear, R.H.
sttrubt; 6 -starboard ::!inq ? ~ -fuselage,
s ar card side; 8 -tor! r3rii 4 -jet
nozzles; !0 -t'useloge, port side ;
f1-port trinq ? 12 -morn landing g9ear
L. H.strut? 1 ilroin/ng fue?1 sedtmenf
from No l tonk ? 14 - refue11m9 the
olrcraff; IS-c6ckpit.
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10. Look for leakage oY A1:tI~10 oil from the shimmy
damper.
11. Check the pressure of air (nitrogen) in the shocY.
absorber (by parking; compression) and look Yor leakage
oY A6tP-10 oil on the surface oY tho rod.
12. Look. Yor. A,',tP-10 oil leaks from the nose gear
retractinL cylinder.
13. Lool: for Ai:t1~-10 oil leaks from the units
pipes and hoses in the nose gear ti+ell. Inspect condition of
pipe flan;ing and check fastening of the oxygen cylinders.
14. Checlc fastening and functioning of the none gear
15. Check inflation of the vrheel tyre by its deflection
which should be from 3U to 40 mm. At sub-zero temperatures
of the outside air, make sure there is no ice under the
brake shces (as far as thin can be checked visually ).
16. Check the pressure of air or nitrcgcn in the shock
absorber (by the degree of parking oompression) and look
for AA.tI'-10 oil leaks throu?;h the shook absorber scaling
collars.
17. Look Yor A!.tP-10 oil lealca from the strut rntraat-
ing oylinder.
18. Check vrhettier the ~uplocY.s of the strut and vrheel
door are open. Inspect the condition and attaohrant of the
L.G. doors (on the vrings~ strut and t;heel).
I9. Look for A`,'P-10 oil leeks frets unita~ hoses and
pipes looated in the strut v;ell
Sty r*~~~'?'~..?'~''~.. ~;
20. Check vcnet,tE:r~tite rring hatch lid:, tu?a rcliab?.y
closed, loo''=s Yor A;?.P-10 oil lc:a?:a Trots tits aileron
hydraulio booster rateh and in3peet atta:n::.:~nt of tho
serodyn~~i~ stall fence.
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21. Examine condition of the main landing gear strut
mechanioai position indicator.
22. Check for fuel leaks from the drop tank.
Fusel;t~e~ stns?board side 7
23. Check whether the hatch lids are reliably closed.
24. Inspect the position of the air by-pass shutters or.
the lid of the R.H. hatch in the engine compartment.
25. Look for A~,~P-10 oil and fuel leaks (with opened
engine hatches and during short-term operation of the pumps of
2Yos 1~ 2, 3 and 4 tanks).
26. Check tkie vent pipe connections for cleanliness.
27. IDlake sure that the tuel shut-oft cocks and the
air blow-oft band are open..
c~osin~;~ check for proper looking and reliable closing of the
drag chute door locks and cable look; the c>3ble must not~be
slack and it must be securely fastened in the clamps; the
door locY, closed position stops should be located opposite
the marks on the fuselage.
34. Carry out the inspeotion in the same way as
prescribed fer the starboard wing(See Pass 20 - 221.
35. Check position of the aileron trim tab in keeping
frith the inscription on the tab.
Main landinY; gear, L.H. strut 12
36. Inspect in the same way as it is prescribed for
the R.H. strut (See Pass 15 - 19).
fail unit 8
28. Inspect condition of the stabilizer and look for
any foreign articles between the fillet and the stabilizer.
29. Check the tail unit hatch lids for reliable olosing.
30. Check condition of the trailing edge or position of
the rudder trim tab (if any) in keeping with the inscription
on tho tab.
Jet nozzles 9
31. Look for any foreign articles and for A~,1r 10
oil leaks frcm the pipes and cylinders controlling the het nozzle
shutters check whether the nozzle shutters open easily and
oheck their position (the shutters should oooupy the AUG&tE2dTED
position).
Fuselagoi port side 10
32, Inspeotion should be parried out in the same way
as prescribed for the starboard side(3ee Paraa 23 - 2?).
33. Examine the. drag ohute hatch doors for reliable
Checking fuel quality fn No.l tank 1~
37. Drain fuel sediment through drain cocks of iJo.l
tank and makd sure it oontains no water or f orei~n matter.
Note_ Draining of fuel sediment from other points of
the system intended to drain fuel and sediment
should be oarried out not less than t~?~ice a
year (in spring and tall).
3B. Shut the drain cocks and look them securely.
Checking aircraft for servicing 14
Open the hatches and. do the following:
39. Check the :smount of main fuel in the aircraft by
the fuel level in Pio.l tank; when o'~ec'~in{~ the amount of fuel
in the tanks, make a note of the readings of 'the fuel flotir
meter,
The fuel level in the fuselage tanks and drop tanks east
J ~~`ica i o; /.t I:t L~ ' _ L~ +: +` [ 1i l \ I T l' . L 7i 4 : i ~
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- 19 -
be 20 - 30 mm and 10 - 20 mm below the lower edge oY the Miller
neck in summer and wintery respectively.
40. Check the amount oY Yuel in the starting system. The
fuel level in the tank should be 40 mm belo:v the lower edge
oY the Miller necks both in minter and summer.
41. Check the amount of oil in the ~lubrieating system.
The oil level in the tanks should be at the height of 10.5 -
11 lit, mark: on the ~~ JI " and ~~ II " dipsticks Yor the port and
starboard en~in.es~ respectively. Ground operation oY the engine
is permitted with no less than 7 lit. oY oil in the tank.
42. Check the amount oY oil in the hydraulic system. At
zero pressure in the systems with retracted wing Ylaps and air
brakes the level of AE4P-10 oil in the tanks should be within
the marks on the dipstick.
43. Check the amount of alcohol in the de-icing system.
The tank should contain not less than 3 lit. of alcohol.
44. Close the Miller caps and hatch lids after checking
the amount oY fuel and oil in the aircraYt systems.
Cockpit 15
45. ChecY, canopy glasses for absenoe oY cracks and see
that the organic glass is perfectly transparent; inspect the
deicing maniYold Yor cleanliness. Check condition of the
pressurization hose and its coating.
46. Checlc the ;u?esstu^e in the ai_ :'ottle oP the canopy
pressurization system (rated pressure 5L kg/om2) anal in the
oanopy jettisoning bottle (rated pressure .'. - 130 kg/em2)
and make sure the emergency raok is properl;; +ocked.
47. Inspect oondition oY the pilots harness and its lock-
ing mechanism on the pilots seat; see that the face screens
seat arm-resta~ L.G. look emergency openinc; handles and the
flexible pin of Ajj-3 autom'-tia pressure unit are locked;
inspeot condition of the snap hook attaching AA-3 unit
halyard to No.7 game; straighten out the straps.
48. Check whether the blocking devices of the o~inopy and
jettisoning mechanism are properly locked.
49. Climb into the cockpit and check for smooth closing
and opening of the sliding section oY the canopy and see that
it is reliably locked in the foremost and rearmost positions.
Check the canopy locks Yor reliable closing acid maye sure the
canopy lock control levers and the canopy independent jettisoning;
handle are duly locked and tottered.
50. Check con~tition of the enginc.? control levera~
reliabilit,-r oY their locking on the stops and ease of movement,
51. Check functioning of the brake system by pressing the
wheel brake lever and pedals; examine the air vent holes
located in YII-30 relief valves Yor cleanliness.
No, t-e,,,: At subzero temperatures oY ambient air make sure
tY,at the brake shoes respond to depression oY the
brake lever.
52. After starting and warming up the engines work
the aircraft control stick right and leYt (with disconnected
hydraulio boosters) and depress the pedal to make sure that
the ailerorLS and the rudder are fully deflected in the necessary
directions without knocking and jamming and that the ,
resistance oY the spring-Peel mechanism is felt on the control
stick.
53. Check functioning oY the main hydraulic system and
hydraulic booster system.
54. Check operation oY the stabilizer control ay stem
(together with the aircraft equipment mochaniss).
55. Check deflection oY the aileron trim tab. A~'ter the
oheek, set the tab to the position eorrespon.ding to the insc~^in--
tion on it.
56. Check vhother the landing gear and wing ~].ap e~.?rgcrcy
opening oooka are tightly closed and looked With typo FC_;
wire of 0.5 mm diameter. Check whether the oaps oY th3 r
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SHUT oFF Cocx (H~PEKP~IBHO_"i RPAH) closing buttons are locked
with brass wire of 0.25 mm diameter.
57. Look for foreign objects and water in the cockpit;
in winters look for any ice especially under the pilot's
seat (inspect through hatches in the seat). Remove the covers
from the A~1,-5 pressure unit and from the wing flap control
panel.
58. Cheek the pressure of air in the main air system
(11U-130 kg/cra2)s landing goat emergency system (50 kg/cm2)
and wing flap emergency system (110 - 130 kg/cm2),
5g, Check operc:tion of the A~j-S control button; after beir.~
depressed the button should return to the initial position.
Under icing conditionss check functioniz~ of the de-icing
system.
6U. After all the specialists have inspected the aircraft,
cheek whether all thehatch lids removed during inspection are
reliably closed; turn OFN all the switches in the cockpit
which have been turned OIt during preflight operations.
61. Before the pilot climbs into the cockpits remove the
cable with ground stops (except the atop in the ejeoi~ion gun
headrests remove the safety pin of the ARL'fED circuit and
set the Pitot tube rod to a horizontal position. After the
pilot has occupied his seat remove the stop Pram the ejection
gun headrest.
Performa7~ce of aircraft engines should be cheol;ed in
accordance with the Engine Testing Chart (A'ig,2) as foilo~?rs:
0 - 2 - starting of enF;ines; time required for gaining
a speed 100 r.p.m, less than low speed - not or-er 80 sec,;
permissible short--term increase in temperature of gases (Tg) -
not ovor 850?C.
1 ter On aircraft with controlled stabilizers the
starboard engine should be started first.
Mazrmum
70400
10000
B3o0
IBOo
sroo
Fig.2. Engine Testing Chart
Symbols: N-normoi rating; M-maximum rating;
~-augmented rating,?
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1 - 2 "Idling rating" fn the oourse of 1 minute at
4100200 r.p.m.t gas temperature T$ - not more than 650?C;
oil pressure pilot lamp not burning.
3 - 4 (31 - 41) - checking the cockpit pressurization
and supercharging systom.
5 - 6 -bring engine speed to 10400 ? 50 r.p.m. (and
run it at this speed during 0.5 - 1.5 min,); check operation
of the hydraulic system and generators. L7hile engine speed
is beiuE; increased to 10400 ? 50 r.p.m.~ betti~een 4500 and
'6500 r.p.m. the shutters oY the het nozzle should move Yrom
.the starting AUGh:LNTED position to the rroRrnAL (IiOi.LIH11Jt)
position.
" 7 - 8 NORMAL rating ( maximum speed ? 5U r.p.m.~ gas
temperature - not over 550?C; oil pressure pilot 1 amp not
burning),
8 - 9 11i}~CIPiilD4 (fdAHC14~.QA7t.) rating (at this speed the
'engine should be run not more than 10 sec.; engine speed is
..equal to maximum speed + 50 r.p.m.; gas temperature not
-over 650?C~ oil pressiu e pilot lamp nOt burning).
Caution. The enE;ine should be run at maximum rating
not earlier than 1 minute aYter it has reaohed
idling rating.
9 - 10 - augmented rating (at this Bpeed the engine
should be run not in exoess oY 10 seoe; AUG?;iETrTFD (~OPCA"~)
pilot lamp burning; engine speed equals to maximo~ speed = 50 r.p.m.;
"gas temperature not over 650?C at an ambient temperature
below +15oC~ and not over 680oC at an 2mbient te;aporature
of +15oC and highex; oil pressure pilot la;np n.ot burning).
A short-term increase its. speed up t0 11,600 r.p.m. is
allowed during not more than 3 - 5 seconds; tl:e aYterburt~er
may be snitched on aYter.keepinE; the engine control lever
in the L4ATCII:N"uI rating; position in the course oY not less
,than 3 see. The AUG.:1~irTZ;D rating oY the en ?inc- shctild bo
oheeked.every 10 days (12 during tnis period the a~'cei~il~~'~nner
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was inoperative) on a spot speoially assigned for this
1?'Pone.
Deicing augmented rating measure the aotual drop of gas
temperature. The permissible gas temperature drop with
respect to the stable rating is not over 20?C and the
temperature ir.cre .^e -not over 5?C.
IY the t;as temperature drop exceeds 20?C~ the time
should be increased fclr shifting the jet nozzle shutters from
the ?w;iCIidULt to GUG1.iEIiT1:D position which should be not more
tlian 2.5 sec.
If the ircrease in the f;:ss temperature exceeds 5?C~
re,?uce trc shutter :shifting time to 1.2 - 2.5 seconds.
lU - 11 - 12 -checking operation of the engine at
iuterr.:edi:ae ratings; 11 -opening of the air blow-off band
(n 9900_100 r'P?m- for engines IJo. I'72625b incl. and
n= 9700_100 r'p'1D? for engines from Ito. P726257 on)?
12 - 13 - checking; warmed up engine at idling rGtinp,
(n .+ 4200 - 43 CC r.p?m. at anbient temperature of +30?II;
4175 - 4275 r.p.m. at +15?C; 4150 - 4250 r.p.m. at 0?C;
4125 - 4225 r?p.In. at - 15?C; 4100 - 4200 r.p.m. at -30?C;
g;,n te~;peratui?c; not over f;SU?C; oil pressure pilot limp
not burr.in,'-).
14 - 15 - c}leckin~ controllability of the erLgine from
n ?= N30o r.p.m. to nora:,l speed (from 9000 ? 200 r.p.m. to
ntu?mal sl:ecl for s;r.~;inca of tllc 5th series, and from
9500_200 r'p??? for en~,inecl of the E,th caries). The enf;inc
r.p.~;. r..tl~t not l;u; behind the movcnent of the c:r.l;inc
control lever 12 the T:stter !a allifted in ore direction in
no lvaa th:sll 15 occ.
IG - 23 - oheckir~ t}/v el~,ine pick-up, ^'he tine required
for thr cr0lre to .Fain ncraal ai~cl c h?o:a n f?300 r. p. n.
(n goCO = 200 r.p.r,.~ r, 9000 tSCur.p.::. or 95oC_200r'p?n?)
ohould by g - 12 aec. 7R:en the en~,iur control lever is coved
durirsg 1.5 - 2 seoonda from the lots apecd atop consecutively
to P10RPrIAb, b:AXIL1Ui1 and AUG.:SEWTED .positions, tIse el:trine
ahould gain mll.;ciu:w:: speed during not more than 9 - 12 se:c.;
9 - 13 sec. (or 11 - 15 sc:c. for the engin }:,r/cm2 in the burster !-~?draulic system (by the
ground h~d_*?sulic pump); thij should turn OFF the AIIC-4
mecY~anism and enl;a~;e the hydraulic booster. Increase the
pressure in the system up to 13~?7 kg/cm2 and disengage the
hydraulic pump;
- rc9uce the pressure in the booster hydraulic systen
down to 50+` kg/cm2 by the back-and-forth movement of the
control stick; this must snitch the stabilizer over to the
emergency electric control which brill be indicated by the
change in the speed of the control stick deflection and by
the operating noise of the GdyC-2 electric motor; at a pressu:
+2 2
of 50 kg/em the HB3i~1 valve will closes the BY-14I,SC
hydraulic booster rill disengage and the actuating cylinders
will switch ON the ~?yc-2 motor of the stabilizer emergency
control system
.
40. Coat the rod of the APy
layer oP ~'1AT61~I-201 lubricant.
41. Pack the external bearings of the stabilizer beams
with u1~IATYItd-201 lubricant, -
42. K'ash~ inspect and lubricate (in situ) the attach-
ment fittings of the rudder and ailerons.
43. FIaving serviced the hydraulic boosters and the
hydraulio system, test (together xith aircraft specialists).
the aircraft controls r=rith the hydraulio boosters engaged
While ohecking the main (hydraulic) and emergency
(eleotric) stabilizer control systems soe that the
aircraft control stick moves smoothly taithout "creepage"
and perks; soe that the resistance of the spring-feel mecha-
nism is felt on the stick.
ithon checking the emergency (electric) stabilizer
oontrol systemr soe that the time for complete travel of the
stabilizer with the APY rod 1n the long-arm position is
about T sec.y the free travel of the aircraft control sttok
at the long-arm position of the APJ' mechanism resulting
from the movement of the hydraulio booster slide valve and
the rod of the ~P-5 pick-up should be 11?2 mrn.
~fhile checking the stabilizer control by the
hydraulic boosters make sure that during smooth movement
of the oontrol stick the rod of the '.(~`'S pick-up does not
operate the witch.
Ifs ho~vever~ the switch operatos~ ohock to see vhether
the main slide valve of the bydraulic booster is ~nmmed. If
the hydraulic booster is in ordor~ replace the rod with
the ~-J pick-up; the lorgth of the rod with the AP-5
pick-up must remain the same (adjust by means of the
end-piece scre~'red into the pick-up).
Having replaoed the AP-5 pink-up cheek operation oY
the emergency (electric) system and the stabilizer maximum
deflection angles at the long arm oP the APY mechanism;
the stabilizer deflection angles must be adJusted by chas-
ing the length of the rod with the ~-5 pick-up; the
distance from the pick-up butt end to the centre of the
ad~ustin~; and-piece opening should not exceed 46 r.~.
1J1th the APY mechanism shifted to the LL~NNAI. ~;;R~;O%)
positions Frith the Ate' rod s~~iteh in the SEOcii 11L;:.i ~`~r0
N7E~~0) position and ti71th the aircraft control stick cshiitcd
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forward or back, .make sure that the stick is heavily loaded
and the stabilizer deflection angles are reduced.
Hydraulic boosters
4A. Flipe the aileron hydraulic booster Frith a cloth
li~tly socked Nith clean nor.-ethylated gasoline and lnspect
the booster and its attachments.
rake sure th:,.t the working rod of the hydraulic booster
bus no chippirf;, ~;allinl; or nicks, that the rod end-piece
ru'id head :u?e rcli::oly locked by the lock nut, and that there
are r,o ci;p.s e_f corrosion on the exposed butt ends of the
slide valve anti b:srel.
R~crfic:?+ of operating fluid along the ~rorking surfaces
oi' the hydr:ulic booster is allowed ~rithin the follotiving
114ats: ~?rith t},e booster inoperative and zero pressure in the
hydraulic cy.^.tc:n -not >ZOre than 5 drops per hours with
the Looater wor!:in~; a:,d a normal operating pressure in the
hydraulic s;;stcm -not over 3 - 4 drops per minute
incrc;aed lca:;t+-c t}:reut;h rubber seals caused by an interval
ir, op,:ratic:; r,.r.~ bc: elir.,irated by operating the hydrauli0
booatcr ~(~sitL ti:u l:;;clr;;ulic system under pressure).
45, l::upect the ot,~.bili~cr. hydraulic booster in the
a:u?:o tirr.y ac i~rv.^,~?ri~cd Yor the aileron booster.
4G. C}.eor, locdir:;; of t}re hinges of the hydraulic boost~~
head a.^,c~c.'~ly. b'?:;:e auto there is no longitudinal play in
tl.c hi::,res p. t!:c cain slide ?r~:1ve chain (with zero pressure
in ti.e 'rydraulic aystcr.. ;;nd tho Hain slid? valve 1pel,3d).
If pl7y !s c!;:covcreJ, r~covc tho hydraulic boost or fi'Ca
the alrcr~cSt :u:;i t:,,vc it rup;;lred. Itenovo the acroen fi3~JS:,
1r.nt:blled 1r: :}.~ r.iP~lec eS t}:u pipe unions feodir: o~.~rc:~~in,;
Slu1A i:,to t?.~: boactc. a; L:sroct tho filters a,,~d cash th-,:~ in
c1~1: no::wt?yluto! A~ruolice.
If the removed filters are found dirty perform the
folloti~ing additional operations:
- remove the hydraulic booster from the aircraft;
- drain the fluid from the bcoster into a clean vessel.
I3 the fluid is clean (free of dark aedi:aont, card, etc.),
wash the booster under press?,u?e, without disa_sseWblinc? it,
wash the filter t~ith clean A';h-10 oil and pat the booster
back in the aircraft. If the dr:uned fluid is cont:aar?aed,
the booster should be foi^..arc!ecl to a repair arLw.i~atio^ for
overhaul, vrashing and cheekin~;. (before inatallin~ a ne?s
hydraulic booster, r+arh the booster h;:draullc system ai:d
fill it tiaith Presh opcratint; fluid);
- havint, installed the h;~dr::ulie boeoter in the
aircraft, with tl.e hydraulic s.: at~n urier presslLe (before
conncetin~ the control rod), c}:cck for presence of thy:
suction force of the r..an alic!~ v:,lve (?.rit}, t},ia Sn vi c7
shift the assn slide v:av,; out of the booatcr ::rd let it ~,o;
under the attics of the suction i'oree tLe slide valve :rill
be pulled in thereby ?ovir;~; the ::or~:iu,; ro3);
- connect tl:.. rods to t,:u :.:; ir:.r:lic booatcr, _, ,;~~ tj:..
booatcr ::nu chi ck iLr,.: t ic:.ir.,; of the nlrorn.'t eC~ ?roln.
,totes 1. before ira alias:, t!:~. fil:~r, eL~?c'- tor.}itio::
of ti.e 111tcr ccr~.:n .+ir_a uit:; c. .. ;::1.',1?..
2. 1:i lc?...: cr..biir.,~, t}:c pi; _ u::ic:.W ...' .. c`.....-
1r.,: t}.. filto ;, !: .11 ,... , 1; ~_ .... - "~
?t ti: 1 '':~? 't: .~ :?
CCT'L:C1
...Se'. is L; ...
~:
ine olc.:r r.:
nc:+ one;.
._ } rcj^i .:~
:1 1
..,: :,e c
~:~
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46b. Disjoin the tail section of the fuselage. H2vind
performed operations listed in Perri l:oc - 52a, connect
the tail section.
2hc belts securing the af~~erburner pipe attachment
shrckles s':ould '~c- coated with oildag.
hoc. Inspect the units, pipes and vent holes of all the
stems loc~a o?1o3:=od by
means oY light and aural signals):
- warning receivers by the buzzer;
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- range finder3 by locking on (gloving of indicator lanps~
and releasing (extinctior. of irdioator lamps) of the reflected
signals ni.th released and depressed RIrLEASE (C~PCC) button
(Funetionirg of the ran;;e finder should be checked jointly
eith the ar~:ou.~ er).
fl. Snitch Olt the AD1~rD circuit before the flight and
deenergise it after the flight.
- radio eCmp-gsa: by rooeiving signals and checking the
bearings oS tho homing and broadornting stations in all the
eubrangos;
- radio altimeter; by deflection of altimeter painter
after st~;tohing ON and changing the tangos;
- markar set: by any kind aF simulator.
Radar Bauipment
Check the Polloti~ine:
9. Fuselac;e:, condition. and rastening of the radio set a
antenna, Pairings of the radio compass loop and of the marker ~
set antenna. See that there is no kerosene oil or moisture '
inside the fairings.
10. Yin~r;s fastening and condition oP the radio altimeter
aatenna?U .
11. Nose comnartments? out~rard appearance and Fastening ~?
of units.
12. Cockpit; omnidirectional antenna of the radio compass
and its lead_in; outnard appearance and fastening of units,
light and pointer-type indicators; serviceability of the
equipment supplied either Prom the main or from the stand-by
converters, and proper functioning of switches and knobs if
the equipment was not used in flight or its operation teas
reported defective.
Having finished the checks set all the enitohos acid
knobs to their initial positions and awi+~r n~~ +i.., ~,..,~?-,~,.,t.
- radio set: by establishing ?oo~nunioation Frith a groul?d ~ ~
station or a station of anothor aircraft in all ohannel3;
---?-~~a~===~y o= the equipment moot be oheekeA ns fol-
13. Blake sure the ARLiSD circuit is deenergised.
Cheol: the Following:
la. Fuaela~es fastening and oondition of the range finder
and responder antennae.
15. Fin: oondition of the warning receiver antenna
fairing.
lb. Fuselage aomy~rtms?~ts: euternal condition and
fastening of units.
17. Cos it: looking of the safety cap of the AE%lED
button; serviceability of the equipment supplied either From
the main of from the stand-by converter and proper operation
of the switches and knob3 if the equipment was not used in
flight or was reported defective.
Upon termination of the oheoks~ set all tho ewitahes
and ]mobs to their initial positions and switch OFF tho
equipment. ui ment should b? oh9oked as
Serviceability of the eq P
f ollosts t
- responder: by the signals at a gsst~d staticn or
any kind of simulator (aoouraoY of coding should be C~~o-::,3
by moans of light aitd aural signaln);
- :warning roceiver: by the bu~eflr:
- tango Finder: by a spooial t~ster?
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I,fAII1TF,IiANCE OPERATIONS `
~:
Description of maintenance operations'
1. Check the oondition and attachments
of the antenna.
2. Inspect screening of oables P.V.C.
tubes of feeders, oable and unit bonding
strips, fastening of oables and feeders.
~. Remove the receiver-transmitter
and rectifier from the aircraft. Inspect
the wiring, parts, releys~ seating of
tubes and orystals in the holders. Dress
down the burnt relay oontaots.
4. The following performance
oharaoteristics should be oheoked on the
teat at and:
- ourrent in the artificial antenna;
transmitter modulation percentage and
sensitivity of receiver;
- calibration of the receiver scale
and functioning of automatic frequency
oontrol,
5. Cheek oondition of plug connector
pins and pinholes (do not d~sasser:ble the
sealed oonneo~ors). Install the raoeiver-
transnittor mad rectifier on the aircraft.
6. Chook whether the union nuts of
plug oonnootors end feeders are properly
tightened.
Diain cent
intervals (in
f lying_houra)
25?5 S0?51100_10
10. Check oondition and fastening of
antenna, its lead-in and loop fairing. Inspoot
the desiooator oartridge.
11. Ex2mine the screening and fastening
of oables, bonding strips of cables and
units.
12. Remove the receiver from the air-
craft and check oondition of wiring, parts,
relays and seating of tubs in the holders.
13. Remove the loop unit from the
aircraft sad service it as follo~.?s:
- replaoe lubrioant in the loop ball
bearings:
- clean the loop brushes e.'.d slip
~ rings;
f~ - replaos lubricant ~ the bill bear-
; ~ ings of the eng?na rac~oticn Boax Ap"-?~7'
?. Cheek attachments and shock-proofing
of units.
8. Check functioning of the radio set
in the scope of preliminary operations.
9. Cheek the follo~ring pr_rformance
characteristics (on the aircraft or on a
stand):.
- ourrent in artificial antenna; modula-
tion percentage of transmitter and sensitivity
of reoeiver~
- calibration of receiver scale and
functioning of automatio frequency control.
Radio_Comuas
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- remove dust, dirt and silica gel
crystals from the loop unit.
14. Qheck the receiver on the stand for
the following characteristics: sensitivity
of reoeiver (20 microvolts), accuracy of
graduation (j2.5~), maximum homing
sensitivity (50 microvolts/m., 250 mioro-
volte).
15. Check condition of the plug con-
neotor pins. and pinholes (de not open the
sealed plug connectors). Install the
reoeiver and the loop unit on the air-
craft.
16. Check tightening of plug oonneotor
union nuts.
17. Check fastening and ?shook-proof-
ing oP units.
18. Check functioning of the radio
compass in the scope of preliminary opera-
tions.
19. Oheok the following performance
oharaateristios (on aircraft or on stand):
sensitivity of reoeiver (20 microvolts),
accuracy of graduation (?2.5;x) and maximum
homing sensitivity (50 microvolts/m.).
Ra io timeter
20. Remove the antennae from the air-
craft. Olean the antenna mounting places.
Reinstall the antennae and paint the edges
of the antenna bases.
41. Check screening of cables, Y.V.C.
tubes of the feedrers, bon3ing strips of
cables and units, fastening of cables and
feeders.
22. Remove the receiver-transmitter and
converter from the aircraft. Check condi-
tion of Firing, parts, relays and seating
of tubes in the tube holders.
~3. Blow the inner spaces of the
converter. Clean the commutator-and-brush
assemblies and replace lubricant in the
ball bearings.
24. Check the following characteristics
on the stand: sensitivity ((30 - 70 decibels)
and calibration of the radio altimeter.
25. Cheolc condition of plug connector
pins and pinholes (do not open the sealed
plug connecters). Install the reoeiver-
transmitter and converter on the aircraft.
26. Check tightening of the plug con-
nector and feeder union nuts.
27. Check fastening and shook-proofing
of the radio altimeter units, fastening
and condition of the at~tenrae.
28. Check functioning of the radio
altimeter in the scope oP preflight
operations.
29. Check the radio altimeter on the
stand for sensitivity (80 decibels) and
calibration.
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L'tarke_r S t
30. Cheok fastening and condition Of tb3
antenna fairing.
31. Check screening of oables, P,Y.C.
tube of the feeder, bonding strips of
oables and units and fastening of eable8
and the feeder.
32. Remove the reoeiver from th@ aix-
craft. Check oondition of wiring, parts
relays and seating of tubes in the tube
holders.
33. Check on the stand the sensitivity,
tuning frequency, and relay operating
and release ou='renta.
34. Cheok oondition of the plug con-
neotor pins anti pinhholes (do not open
the sealed plug connectors). Install tho
reoeiv@r on the aircraft,
35. Cheok tightening of union nuts
of the oable and feeder plug oonnootors.
36. Cheok fastening and shock-proofing
of unit.
37. Check funotioning of the reoeiver
in the soope of preliminary operations.
38. Cheok the following oharaoteristics
(on the airoraft or on a stand):
- sensitivity by the diatanoe (1 - 3 m.
betc~een the reooiver and simulator antennae,
and tuning froquenoy (?5 bio/s).
Responder
39. Cheok oondition and fastening of
the antenna.
40. Remove the responder from the air-
craft. Check oondition of wiring, parts,
relays and seating of tubes in the tube '
holders.
Q1. Clean the surfaces of the swinginP
mechanism and lubricate the rod roller.
h2. Blom the inside spaces of the
oonverter. Clean the coAmutator-and-brush
assemblies and replace lubricant in open
ball bearings.
43. Check soreening of oables, P.Y.C.
tube of feeder, bonding strips oP cables
and units, fastening of cables and feeder.
Inspect wiring of the AEP.iED oircuit, check
the voltage and its polarity on the pins
of the ARuIED plug.
44.Check on the stand the following
performance oharaoteristics: frequency
range, powers duration of pulses, coding
of signals and sensitivity of reoeiver.
45. Check oondition of plug connector
pins and pinholes (do not op3n the sealed
plug oor~neotora). Install the responder on
airpprof ~~.
4b. Check tightening of plug conneotor
union nuts.
47. Check fastening and shock-proofing
of the units.
48. Cheos frnetioning oY the responder
in the scops of prefli~~zt operations.
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49. Check the following charaoter-
istios (on the aircraft or on a stand):
frequency range, coding of signals and
sensitivity by the distance (2 - 5 m.)
between the responder antenna and
indicating instrument.
rail :7arnin~ Receiver
50. Cheok condition of the antenna
fairing.
51. Cheok fastening, and shock-prooi-
ing of the units.
52. Remove No.l and No.2 units from
the airoraft. Cheok the wiring and
restore protective ooating, if neoes-
sary.
53. Check sensitivity of the reoeiver
by means of test instruments.
54. Install No.l and No.2 units on
the aircraft.
55. Estimate the sensitivity by the
distance between the antenna and buzzer.
56. Cheok functioning of the reoeiver
in the soope of preflight operations.
Rana- e~Finder
57. Chock condition and fastening of
the antenna.
58. Cheok soroening of cables, P.V.C.
tubes of feeders cable and unit bonding
striFs~ fastening of cables and feeders.
59. Remove the receiving-transmitting
unit, range unit, power unit and antenna
from the aircraft. Dress the antenna mount-
in, place. Open the units, insect the wir-
ing, parts, relays, and seating of tubes
in the holders.
60. Check the following charaoteristics
(on the aircraft or on a stand):
- po~~er of transmitter; .
- sensitivity of reception circuit;
- oalibration by corner reflector;
- sealing of the receiving-transmitting
unit.
61. Check condition of plug connector
pins end pinholes (do not open the
sealed plug connectorsj.
62. Check tightening of union nuts on
cable conneotors and feeders.
63. Check fastening and shook-proof-
ing of units and reliability of locks
fastening the receiving-transmitting
unit to the housing.
64. Cheok functioning of the range
tinder in the scope of preliminary
operations.
Conv~ s
65. Remove the converters from the
aircraft blo;~ their inside, clean the
commutator-Und-b,?.uush assemblies and
replace lubxica~t in the ball bearings.
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66. Cheok the output voltage of the
oonverters on the stand and install tha
oonverters on the aircraft,
6?. Cheok tho output voltage of the
oonverters on the aircraft.
btAIi1TENA3iCE OF RADIO AND RADAR BQUIPi31;r1T
ON AIRCRAFT KEPT IN STORAGE
Everv 10?2 Data
1. Perform operations presoribed in "Preflight Operations?
Soction.
Every 30-+. Dana
2. Chook oondition oi' dooicoators.
3. Per~'orm operations presoribed in 10Preliminary Opera-
tions" Soctlon.
Every 3 ttonths 4 10 Days
_.....
4. Check condition of dcaiecatora.
5. Perforp operations proscribed 1n "Prelimin~.ry Opera-
tior.~" Scotion.
AIRCRAFT E^L'ITLIL2:T
ELECTRIC EQTJIYLtE2iT
PREFLIGHT OPERATIONS
Do the following:
Uys'aer Tdose Comx~artnent.
1. Inspect and ohook faateninr, of tha airoraft atoraLe
battery, plug oonnecter, and Qent pipo.
Note: If the storage battery han boon ro~ovod iroa
the airoraft, ohook tha state of ito charge,
oondition of the surfaoo of tho soaling cowpo~dr
fastening of the eleotrio oabl?? to the battor~
terrainals~ndf oonneotoitito the oirorrjt1,n~trortho
airoraft a
Nose_G~^:r
2. Chock the oondition and yastoning of t`=o oxtern?~l.
bf th 1~~..a;;, ~ ,c..^.
light lndicuora Eho:7ing tho pociticn `
3 Ch3aJt $he t2Vi11~Ii~ fcr prcJ:or tr..t-_">'S .=?^. co:.~i-
tion of its lc :~
4. fi~.ts~:'~s tao
e~itcli~~.
^!!.` 4 .
its 1n:~ta~va.~.
~? ~aG`.3--ii. of airir.-~ .- ce.. _ .
~litlU~ %S';1 1~~
Q ~%..
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 Declassified in Part - Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
7. Check the oondition and fastening of the terminal
switches. -
8. Check the attachment of wiring and condition of its
insulation.
Starboard 9Jin~
9. Check the condition and cleanliness of the navigation
light filter and static discharger.
10. Check the roiidition and cleanliness of the navigation
light lend.
Main Landing C~,e~ar~ L.S. Strut
11. Cheok the oondition and fastening oY the landing
guar position external light indicators.
12. Check the oondition and attachment of the terminal
switches.
13. Inspaot tho attachment of wiring and oondition of
ita insulation.
Port uinQ
14. Chock the oondition and cleanliness of the naviga-
tion light filter and static discharger.
Fuselaro? port Stde
1G. Check the attachment and condition of the
light lons.
oeknit
1G. Cheok the storage battery voltago at a lo~.d t:ric3
the noninal valuo; the voltage should be not unc;~r 2A V (it
is roocr~3ndod to chock battery voltago with tho Qf~-2
booator puap en~nged).
17. Cheok fastening of the AP9~OQ ultra-violet lip
and gJ[CPK-45 cockpit lamp fittinf;s and oondition of their
electr3o cri-ri.ngr Check condition of the caps and light filters
of the pivot iaTps.
18. 5~:~tch OI? the ground source of electric poner rnd
check the follot~ingi
lAmps~
Oondition of L.G. position indicating lamps, fire-alar~
and generator pilot 2~ps;
oondition of pilot Ianps in "Tableau-6";
- funotiioning of AHO navigation 31U?G ultra-violet,
and coClcpit larr~ps;
- operation of the booster and fuel transfer pumps and
pressure signal units]
heating of the Pitot tubo and TII-15G tube;
functioning of the air-distributor cock of the cockpit
superoharginb system;
- functioning of the throttle control lever lnterloclzl~?3
devices in accordance With velocity head (to be perfcz'r3d
togethar with the instru^ent aechanio);
- functioning o~ the aex'odynaaio trim tab electric
aeohaniym;
- functioning and oondition o4 pilot laaps of !!~ unity
"trim tab effect", operation of stabilizer rlootrio oortrol
units; sia~ultaneouoly with thoBe operations tho s+lbili~~r
control systom must be ohecl;od by the aircraft c^ohanic.
Having o~?xried out tho operaticro ro2a:e3 to pry."-1:''~t
preparation of olectrio. oquiT ::c;zt~ a^':o ct~: o ti: all t:.o
:' t i-: o
power consr~ ~:::~ ~':d tha aircraft b:.ttory rso C:'.'9 ^--
trim tabs ara mhif~ced to neutral.
27o?e: t'iuilo rroi ^ain, th3 el~aow'o~o C:,-:1.'=-::t Sc, t'..
-''- 2~ ~f
_~? n:.t ili~nt~ it is^1?c~-.: ;:3 tc c._: o:::_ ~ _- ~ ,
.., ..
7, 12~ 17 m^-u lt3 if ~':_' F.ilc: Y:?_-s r,~ :c- . ,.._
b t:ia c ~ ;-~:~.ca oP i;~:i:,.
a :, ~;
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 Declassified in Part - Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
pgELIgIIP?ARY OPERdTIONS
IJpper Ids a C~mpartrent
19. Cheek condition of battery sealing compo~:nd, filler
Daps, heat-insulation of battery container, elec+,rolyte level,
reliability of connections of electric cables to battery
terminals under load.
20. CI!eck storage battery attachments.
21. Check reliability of contact in the container plug
connector, ti?~,htening and looking of the latter.
22: Check reliability of battery minus wire connootion
to the aircraft fuselage.
23. Check tightening of nuts and condition of cable
insulation at TII-400 fuse in the storage battery circuit.
24. Inspect the storage battery vent system.
25. Check the fastening, operation and smooth movement
of the rods of the L.G, position terminal switches and
independent snitching Oti of the control stick spring-feel
mechanism.
26. Check the condition and fastening of the L.G. position
external light indicators.
27. Cheek fastening of the tazilight and condition of
its lens.
28. Examine the attachment of wiring and condition of
its insulation.
29. Inspoot fastening of the inertia oontao'tor and of
dheel brake autocatic air-eleetrio release valve,
i1 n L.,n~in! Gear. R.H. Strut
30. Cheek the terminal evitchoa for reliability of
fastening and eorreot alp ration and far smooth sliding of
the rod.
31. Cheek ooaditian and attachment of the L.G. position
ezterr-al light indicators.
32. Cheek fastening of the inertia oontaotor and Wheel
brake auto>natio air-eleetrio release valve.
33. Inspect the eleotria wiring for condition of at-
tachment and insulation.
Starboard Ming
...
34, Check serviceability of TAHO position light
fittings+ cleanliness of the light filters and static dis-
charger.
35. Cheek the Bring flap terminal e~ritoh for reliable
fastening and operation..
Fuselage. Starboard Side
36. Cheek the aondition and fastening of the eleetrio
air distributor (Unit 525), wins flap oook+ eleetrio
valve 9I{-4a and reliable connections and attaahr..snt of
nirit~.
37. Check condition of insulation and f~tne compartment.
electric wiring in the fuselage and in the engi
Tail Unit
38. Check condition and fastening of the navigation light
fittings and 1?ns.
Fusels ^~~ Pn~?'~'b_,~d
39. Check the condition and fastening of the L.G. cool:,
,. starting Panel+ and inopect
eleatrio val~^ 31~-r$+
eleatrio. r,'`~3a for reliable aonncctions and f11in.ing.
40. I~c3r pot t}ie b~'ol'='d oleo i~ xo suPl yrelay box and
41. lk:,~lne fay~senin3 of F~':-2C03
s+iro oa-~,.:eotior~..
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42. Check fastening of the landing hoadlight and condi-
tion of its lens.
43. Check condition oY insulation and attaohrsant of
electric wiring in the fuselage and in the engine compartment.
Pc-t 17ing
44. Ciieclc condition of bAHO position light fittings
and cleanliness of its light filter. Examine the static
discharger.
45. Check fastening and operation of the wing flap
retracted position terminal ssvitch~ and of intermediate posi-
tion push-button snitches (jointly with the aircraft IIochanie).
Main Landing Gear. L.F. Strut
46. Proceed as prescribed for the R.H. strut (Pares 30-33).
47. Check voltage of the aircraft storage b3ttory (with
the IlHB-2 booster pumps corking).
48. Chock attachments of the electric panela~ pilot lamp
fittings, PY~O ultra-violet light theostats~ APY~C:~
ultra-violet lamp fittings and H7ICPIt cookpit illt~esination
fittings.
49. Check the condition and attachment of electric wiring.
50. Switch ON the ground electric supply and ohocs the
follor~ing;
- operation of the electric control ~~chfanZ~mj
- functioning of the booster and transfer fuel pt-~_3
. and pressure tr2sning units]
- heating of Pitot tube and TA-15S tubs;
- oondition of AHO navigation y~0 ul.tr~iol?t
and oock~it illumination 1~p3,
- Yussetioning of the L.G. position indlcators~ fire-alarm
indioatora and gefiErator operation indioatoraa
- oondition and functioning of the L.G. external posi-
tion indicators;
- oondition of the pilot lamps in ?Tableau 6";
- functioning of the ring flap and air brake position
ind io at ore ;
? operation of the air distributor cock of the cockpit
supercharging systeaj
- functioning of the cookpit air temperature regulator.
51. Check oondition of the AP9 unit and "trig tab
effect" pilot lamps.
52. Check functioning of the stabilit~i~meleotriocontrol
electric unit and.op~ration of the APY
mechanism when the latter is controlled by the hand switch.
Notoa_ 1. Simultaneously With operations preacribed
in Pares 51 and 52 the aircraft mochanio
must o$eok the at 8n~loampldin~oabout funotion-
2. If the pilot has
ing of the stabilizer oontrols~ shook opera-
tion of the stab113zer emergency control
oleotrio mechanism in the scope of 25_5 dour
maintenance.
3. I3o not perform the checks described in Para.52
if the pilot h~ e'1to7~hsdsea.thcse GYste~a in
flight for tra4.nin~ P P
Da nof~ switch ON the APY unit oleotrio
~?er-~,.;~?~ i t~rnir~ 0:1 the
meohani m without prov_e~.sly
by olio t~,as b~1 or AIIC-4 0100 ~??So
EY-14E.~C drat.
G3chznism.
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Having oarried out preliminary opsrations, make sure 10. Airblast the battery container vent pipe.
that all the electrio oonsumers and the airoraft storage bat-
tery are OFF and the trim tab and "trim tab effeot" eleotria tto_ tet Routine maintenance of the storage battery should
mechanisms are set to neutral. ~ be performed in accordance with Eattery Operating
Instructions.
Fver,~r , 25+5 Flvinr? Hours
Starter-Generator, Diff erential-t3inimum Relay, Carbon
4oltage Itesulator, and ballast Resistor
1. Checlc fastening of the starter-generators and condi-
tion of coolin~y air intakes.
2. Examine condition of the oommutator?
3. Check eleotrie wires for reliable oonnection:
4. Airblast the generator inner spaces (at 1.5 - 2 kg/om2).
5. During starting oheck the time required for the.
engine to reach the low speed rating. This work should be
dono 3ointly with the aircraft meohanic.
6. Check the fastening and tightening of the oontaot
olamp bolts and oondition of solder on wire terminals on
the panels of the carbon voltage regulator, differential
minimum relay and ballast resistor.
7. Check the condition and fastoning of units, attachment
and insulation of eleotrie tivires in power units.
6. 141th the engines ^rorking check the setting of voltage
regulators and parallel operation of generators. This
should be dono together with the airoraft mechanio.
Ai~rraft Storage Battryv
9. Ibcamino the storage battery oontainer znd attaoi;r.:3nts,
the plug oonneotor and the eleotrie crires inside tie
oontainer. Cheek insulation resistanoe of the bat~ery o~ataines
plug oonneotor. The insulation rosistEnoe ahonld ba noi: less
than 20 mogohras.
Contaotors and Eclays
11. Check visually the oondition, attachaents and conreo-
tione of eleotrie mires. relay
12. Check fastening of the PIIA-u00A (It".-2000
boxes, oondition of crire insulation and reliability of their
attaohment.
13. Cheek oondition and fastoning of thermal avritohes,
starting and afterburner ignition coils.
Rleotrio Control L;eohaaibcw.
14. Check the external condition and fastening of the
electric mechanisms, trim .tab controls, "trim tab effeot
controls'~coakpit air distributor cock and A11C (stabilizer
emergency oontrol). automatio
15. Check the long and short arms of the APY
eotively.
unit, which should be 96?,3 and 50~ mm resp
f funetionin? of the APY
16. Check acouracy o ) of pressure
follow-up system at a slo? change (60 - 90 sec.
in the dynu~1io oh4:~ber of Pitot tube oorr~oPyr~~'~too a
change in indioQted air speed from Q60 ~ 5
8ft0 - 93o ki~/hr and back; during this chec:' tre p='e= "~ ~ in
the static ohs^bcr~ of tubes ohculd b~ at the ,t?.':os,^,I'erlo
pressure level. The nu-~bor of the AP'J unit op=r :tic~~~
should bs not lc~:~ tilsn 1B? `ic:~ a+ a co:.at^.::
ate altitt::i eCy?."'a' _, yi.
17. Checl: fo'r Gcci r v,,. ~.- a,
io oY~.e:.1 of ,,;.c :...
dynamio pit es~va o in tl:c d;/~' ',
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transmitter corresponding to an indicated air speed of 680 to
930 km/hr.
The correction should ensure operation of the AP3t unit
when difference in altitude does not exceed ?300 m. at
5000 m,and ?350 m. at 10,000 m. The number of oFarations
should be betsreen 13 and 47. The allowance for correction is
increased after 100 and 200 hours of the APy unit opera-
tion up to ?350 m. and ~?400 m. respectively at an altitude
oS 5000 m. and up to ?1100 and ?500 m. respectively at 10000 n.
Tlsrninz. Automatic operation of the AFY unit should
be checked with hydraulic booster BY-14t~C
AIIC electric mechanism snitched ON.
be carried out jointly with the instrument
mechanic.
The altitude correction together with velocity
head should be checked at a vacuum in the
static chamber of the altitude correction trans-
mitter and at the atmospheric pressure in the
static chamber of the velocity head transmitter.
18. Check wire connections in the plug connectors and
the fastening of wires.
(lead Lampe
19. Check external condition and fastening of the
electric control mechanism and landing head lamp,
20. Inspect external oondltion and fastening of the
taxilight.
21. Oheok tightening of plug connectors condition of
insulation and fastening of wires.
Cock~A1r Tem ep ratur~ R~.~ul=tor
22. Check external condition and fastening of the
refulator in the cockpit.
kiroraft Electric ;Iet~~rork
23. Check fast~niirs of the plug conn,.ctors~ tight,:ninC
of the union nuts of the plug conn::ctors and wninusN connect-
ors~ their. to clang rand condition of bands flanging clamps
r.nd clamp gaslc.:ts. n.ls
24. Check visually the oondltion of thy: clectrlo`~P^thcr'
s~+itch gear mechanisms and their ano;.aratusas; hno~ry
1n the course of 2 - 3
l.avo them open to ~'Y ~ strips of electric units.
25. Chock the bonding
26. Check the mechanical portion of automatic circuit
breakers s~vitchos~ Y~0 ultra-violet lamp rheostats and
their buttons by turning them Old and OFF by h'.r'd? Check
the reliability of their attachments.
27. Check fastening of the terminal s~+itchos of the
L.G. struts ~ving flaps and air brakes.
28. Vorking together with the aircraft mochcnic check
the Yolloeing:
-.functioning of the inertia contactors and the
electric-air valve of 5rot~nozzlecshuttersicithltheLen;,Sncs
- control of the ~
inoperative;
- operation of the engine afterburner units;
- control of the spring'fcel mechanism;
- time required for complete s~ritching of the air
distributor from ono lino to the other (1t should be ?ithin
20 and q.0 sec,)'> each terminal svritch rod and pressure
- alignment of lid to correct
device; particular attention should be p~
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a3~ustment of the terminal switches of the wing flap inter-
mediate positions.
29. Having completed the routine maintenance operations,
check the electric eouipment under current in the scope of
preliminary operations.
Eberv 0:5 Fl~rinfi Hours
:tarter-Generator, Differential Minimum Relay and Carbon
Yolta.ce }?egulator
30. Reu:ove the starter-generator, check condition and
fnztenin3 of the brush sprini;s, spring pressure, condition
of the brus}i current-or+rrying crires~ height of brushes and
smoothnc:s of their movement in the brush holders; examine
condition of the commutator and dress it, if necessary, with
glass paper ho.1b0 - 220, The height of brushes should be
not under 17 mm. It should be measured on the higher side
of the brush.
3$. Check whether the generator voltage meets the specirica-
tions at 6000, 8000 and 10000 r.p.m. of the engine shaft.
The Generator voltage must be within 27 - 29.5 volts.
35. The starter-generator cutting-in voltage.
36, The engine shaft speeds at r~hich the starter-generator
is out ins and out tof the aircraft network.
37. Using telephones, listen to ore ration of voltage
regulators and make sure there is no sparking; between the
regulator carbon plates.
38. Cheok the external condition and fasterinG of the
differential minimum relay.
39. Cheok fastening of the carboy. volts'c rc;,?ulators
and conditlon of their shock-absorbing cushions.
h0. Cheok reliability of the relay and contactor oporo-
tion?
41. 17orking together with the aircraft mechanic, chock
functioning of the starting system at ell ratiness ata"tin6
on the ground and in the air, and spinning the engine by
the starter-generator.
Note: F'hen e~easuring the height of brushes, take into
account the degree of their gear. For example, if
after 50 hours of operation the brush height eras
reduced from 2; am dorm to 19 mm, this set of
bruahor, should be replaced by a nee: one. During
hif;h-altitude flif;ht the pormiFeible wear oi'
bru:a}:e:: a: ter 50 hours of operation 1s not
over 3.', r..r_,
31. 7nstn1l the otarter-gcrorntor on the en,;ine and
cheer it :'or rolia~le fastening.
32. ('heck t}.c r,labilitp tr:ancfornor wire aontaats end
its attacr.:~eaa fcr reliable operation.
3:}. Cheek v1un;-ily t?ac co..^.ditior: ^r.d attnc}::~crtn oT
thu cor.l.a:acra in t}:o po,rcr u:~1ts.
St^rtin~; Coils
42. Cheok funotioninL, of the coil.
43. Check condition or the breaker poi"~"+ if the
contacts are heavily v~orn, carry out 1C~~-}.oar ro1tir.e r..oi::~
tenanoe op~r3tion~.
unit)
,..,?i .. 1,_.
? ;~ c...
alt_ }Z n..~~V3 t}:: pll'; or..] ti:: C:._'3? .. _ -
for p.~~c->:3 ci 4.t,.-,1 1?.;_;? . , _
`.. ..
45. :: ~ -:':.~ ..o t.~~ ~---
.., ~ ,.
.
cot t; ~.
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 Declassified in Part -Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
48. Check point operation of tho transfer pumps and pres-
sure signal units.
AI:~ _ EJ~ec+.r?,c~l_1_techanism (Stabilizer Emergency Control)
h9. Open the r~o`or hood a:~d cheek condition of the com-
mutatcr~ bruilhos~ brush springs and brush holders and ease
oY brush movement in the brush holders; determine the degree
of brush wear. Replaoe tho brushes crhoso height has reduoed
to 12 mm.
F.xterral I,irhts au Sirrnale
50. Cheok tellable conneotion and oondition of wires
lerzdin~ to the head lamps taxilight~ tail and aide naviga-
tion lights and to the external L.G. position irdioators.
51. Cheok vi:,ually the external condition of sealing
~;asketo and of side lamp, tail lamp and head lamp fittings.
Air Distributor Iilectrio l.Ie.;hanism (Unit 525 and The~-
52. I)lor, the insido ohaober of the air distributor motor
with ooapre:,sed air (at a preaeure of 1 to 1.5 kg/om2).
Droop tho contaots of ~:r~-451' therMO3tat.
Alrcrnft .",'octric T.otr~ork
53. Ir..poat the screened sootiona of tho elootric notrork
and n~Y.o ruro th:tit cot~rl brnidin? is i!ttaot and th;:t ti.o
serooned noo*.lons nrn roli:rbly conr.coted to ono ~.nother n::;l
to the airara;t furol;r^u.
54, I':ra!rc tl:e ~:lrirt; in the olootrio pan3ls and ce:3 io1
p nols ~ i^.atunir.:; of niruc 1n the tcrZinals; UirL:t?~:,t tl:a
inaldo :,^~c.~?:~ of cleo`.^?c an4 eortrol p;u7ala.
55. l:r.~; pot lnsulation of nll tiro oxposed ceotiof,3 cl .'"?o
olcotrlo not?.:ors.
5(,? Cheok external oondition and fastening of the arLmeter
shunts. of the FP.A-200A relay
57? ppen the protootive housing
box and oheck oondition of oontacta and reliability of ~rire
oonrections.
58. Cheok fastening and oonneetions of the electric wires
~ well as oondition of wire lnsulation at the iIl-40p fuse
of the storage battery oircuiolnts where minus wires of cur-
5g. Check condition of p
rent sources and consumers are conneoted to the iusclare.
Hvey;ra~uli^ Cock Flectromaa*.nets
60. Cheok tightening and locking of union nuts and
reliability of oonneotions of minus wires to the tuselnr/:.
gverv 10010 Flyir~8 H~~?
..n,1 r~lr~on
Stagy ~n:~rator. Dlfferertial !tins- ^,ytr^1 n^1'';=.---~5..~.-
Yoltare Refiulatyor
Remove tho starter-Generator acrd rotate tho ~~.tur?
61. c~o?~c tho protootivo
by hand to sea that it is not ~ar..ain~;. H "
--^utator; i? neon:~c~r!?
band and shook oondition of the ?~,rer :.o. 1E~0 - "~? r,;oo~~
dross tho oo~nutator crith glsoa p? ?'
oondition of tho bruohea and brush sgrinCo'
62. Ro~r:ove the differential mii,i:-~:.- roln_r '-r.C `'x?'':="^
it on the outaido. .~ r .2 ; ,!!~.`111ty
r ~ volts `
yt,~~~,~ it : ~,~ Q'.e~
63. Check tiro ca~ -?.,
,,,.:.c:C"?
oy
oY oFxr.ticn oY ti:~ r~l=',' `nd Y.~. a^;.~r_...1'1
^~~ tV J _j ^.T l
'?'
'ct
`
`~?
V
a
~~
.~
?.,
_ r:..;r
t;:
~.r
off
is cu
c1: :~ ~?"
t0 C'~C~ ._,? i 7~~ J o .? ?? ~
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 py Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
del Yt?r El,eotrio Liotors
starter-benerator, differential minimua relay, carbon voltage
regulator, and parallel operation of the generators. This work
should be performed together vrith the aircraft mechanic.
St_ actin C~ oils.
67. Remove the starting coils and check on the fo11o5~ing;
- external oondition of the coils; '?
- condition of the broaker points; dress the contact points
if necessary, and adjust the current in the primary coil;
- check the primary current. This should be not less
than 1.75 A for the HIiI:t-lA coil and for the KII-z1E1 and the
KD-zlral sail units.
Electric Control Hiechanisms
68. Check the external oondition of the commutator, brush
holders, brush springs and brushes, kieasure the brush height.
6~. Remove brush dust from the electric motor ps~rts using
compressed air at a pressure of 1 to 1.5 kg/om2.
70. Check the accuracy of programmatic operation of the
eleotrie mechanisms, measure the consumed current and the
operating time oS the meohan4sm.
Head Lamps
71. Check the external oondition and fastening of the
taxilight. Remove the landing head lamp together with the
eleotrie control mechanism and examine the commutator, brush
holders, brush springs and brushes.
72. Airblast the eleotrie motor inside at
of 1 to 1.5 kg/om2.
73. bleasure the consumed curront, aaouraoy of progra~matio
operation and the operating time.
74. Chock the aiming of the taxilight and landing head
lamp in situ against the reference marks.
75. OPon tho ppoteotlve hoods and lock for any fuel
penetrating insido the motors.
76. Oheok oondition of the commutator brushes.
77. Remove brush dust from the proTeogi~ a of i,toll~.5ykd/om2.
notor inside with compressed a1r at a p
Note: Operations prescribed in Paras 75 - 77 should be
pert ormed upon expiration of the aSanufacturex'3
terms of guanantee for the meohanisna 1n question.
Stares del
78. Remove the starting panel and check on the fo2lo.tiing:
- condition of wiring and fastening of the units;
the motor commutator and brushes and of
- oondition of al regulator (to be performod
oontaots of the timer centrifug ~ ar~tee);
upon expiration of the Man~aotariaeQOntavtor oontaots;
- condition of the relay the starting cycle;
- time for completion of
- current consumed by the panel.
ommutatin E uq.~---- ration,
79. Reliability of the relay and contactor oPo n and
their fastening and condition of the eleatrio wirin?
protective hoods.
Airc~ft Eleot~ t~'ork en ooan?otora.
80. Condition of ordinrrY and sealod p1L~
81. Tightoning of the eloo^rio ols~p scram.
tho giro ternin~ls.
y and oondition. of ~ d ^T~~~~.-~?6a
82. FGn,,onir_S ositicn irdaa='~tor door3 ?=~~,s ~.n3
83. 0'r~n the L.G? p oa Yittsr. for cle~nliL~^
(TABII4~S) end. chock th.."r
proper fasteni.:ag.
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Declassified in Part - Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
84. Open the filter covers, inspect the mounting, bloc,
with compressed air and oheck the reliability of wire
tions
;ide Piavic~:~??on Light and Tail Light Fittings
85. Examine the condition and cleanliness of the fittings
and sealing gaskets.
86. Check the reliability of the wire connections.
Stora~:e Eattery Container
87. Check condition of the battery container, felt warm
ing, plug connector, insulation of wires and wire terminals.
Repair the felt warming packets, it necessary.
MAINTENANCE~OF ELECTRIC EQUIPt1ENT OF AIRCRAFT
KEPT IN STORAGE
Every 10~ Dave
Every 30 ?5 Days
2. Perform the preliminary operations and oheck
serviceability of the entire electric equipment under current
supplied Srom the ground source of electric poser.
L~rery 3 pdonths ~ 10 Davs
3. Opon the electric and other panels and check condition
of the wiring and its oonneotions.
4. Inspect and chock the plug connectors.
5. Check the minus wires for reliable connection to the
iuscla~;e.
6. Check serviceability of the entire electric equipment
under current supplied from the ground source of electric
power.
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 9. Check the amou
bination plus; ccnr,ectcr,
o
ne
'
m
10. Remove the plug from the c
Mall the upper panel and check it for reliability of con-
ction.
11. Check the oxygen set for the Following:
INSTRUP.tP2TTS APID 0}.'YGEN BUUIPT;i~~IT
- ti~,htness of the H.P. oxygen system;
- tightness of the L.P. oxygen system; .
ressure
PRBFLIGHT OPLRATIOPtS
a
Fuselage Nose Section
- functioning of the oxygen unit at an overp
nd without it; of the pull-out cable of the
- condition and fastening
connector;
t
l
l
c
cu
ug
ombination p
ls on the bai
1. Check fastening of the Pitot tube and TII tube
- oxygen pressure and condition of sea
transmitters. This work should be performed together with o
the aircraft mechanic.
xygen unit; en hoses;
-'fastening of the oxYg psi-
- condition of the oxygen unit remote controls, P
their avvement;
Cookrit
2. Check fastening of the instilament panel and of the
instruments on it.,
3. Check location of the instrument pointers.
tions of the handles and amoot}lneas of
-- functioning of the oxygen unit, oonditior. thi~hrevork
pilots suit and f ittings at excessive pressure; ?uit.
should be done Frith the pilot wearing the anti-B
ft for the nor_t
4. Check functioning oft
Notes: 1. ;Thile preparing the eirara
flight, perform operations listed in Pares 1-g,
about oper1-
t
- gyroscopic instruments;
s
it the pilot has no complain
en equip-
d oxyP
- ongine control instruments;
,
tlon of the lnstrum?nts an
d dofoctivo by
- compass;
ment. The instruments reporto
in the soopo of
- aircraft clock.
the pilot should be chocked
tion^s ?
5. Set the altimotex pointers to zero and check the
relation betweon the readings of the barometric pressure
scale and the pressure of the day.
`,i: Y_-at
the proliminarY oPerm
2. preflight preparation of the oxYGVn eQ'
(pares 10 and 11) should bo porfor;~cd rester
tho engines and oarrylnL out the
F?D
t
6. Check the tightness of the static and full pressure
systems of the Pitot and Tl1 tubes. .
-
testing
preflight operations by all the :~iror
~ts.
l~
i
7. Check accuracy of airspeed indicator roadings
.
a
gpec
300,
750 and 1000 ltin/hr divisions of the scalp.
8. Position of the aeleator cock of the Pitot and TII
tube full pressuro system.
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nt of oxygen in the cylinders.
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Fuselage Nose 3eotion
12. Check fastening of the Pitot and TII tubes; check
for presence of covers and red danger tags. This work should
be performed together r:ith the aircraft mechanic.
13. Cheok reliability of attachment and condition of the
pipes and rubber canvas hoses and settlers of the
.static and full pressure systems of the Pitot and TII tubes
in the nose gear compartment and at the point ,here the rod
bends.
14. Check fasteninb oi' the oxygen cylinders and pipes
and absenoe of dust and dirt.
15. Facamine condition of the oxygen charging pipe union.
Fuselage
16. Check fastening of the pressure indicators.
17. Look for fuel accumulation in the potontiometer
chamber of the fuel content gauge transmitter.
Cockpit
18. Check fastening and shock-proofing of the instr9zmont
panel and instruments.
19. Cheok functioning of the eleotrio
under current.
20. Take a note of the position of the instrument
pointers.
' 21. Determine the amount of oxygen in the bottle (re-
charge the bottle, if necessary).
22. Check the oxygen equipnant for tho f ollo:~ing!
oxygen system,
- tightness of the L.P. oxygen system;
- fastening of the
for overpressure
oxygen unit, oxygen valve, oxygen
gauge, oxygen unit remote control
~:dioa
panel, and oombination plug connector;
.. condition and fastening of the oombination plug
ector Fire.
n
23. Remove the upper Panel of the combination plug oon-
neotor and install the lid.
MAINTENAIZCE OPERATICPI
~erY 25+5 Fl~_iovre
Ir_s?rument P~?1
the middle L.H. seotion of the instrument
1. Sc+ing down
panel, inspect it and oheck the follo~~ing: that
- external oondition of the instruments (make sure
the dial glasses
bodies and dial glasses are intact,
the gauge ointers are not bent or ~ammod,
fastened, the p ointers);
are securely off the dials and p
the luminous oompound has not come oheck faatenin~; of the
behind the instrument panel: disoonncot
of pipes, wiring and units;
instruments, mounting the electric instruments, check
the plug oonnectors of of the plugs and sookets.
condition of cont conneotorseand make sure the union nuts ~sre
Connect the Plug d aottered; t arel,
securely tightened an roofing of the inotrumen P
- fastening and shock-p be coated with
ides and rods (the latter must
condition of ~
utMTYIiR-201 lubricant) ? of the full- ~~d'
ubber hoses
2. Disconnect the oanvas r 1 e ions of the instru-
2
static praseure systems from tha pdP TII tuba:. and frog
the Pitot ~ ..cod uir at 0.5 - 1 kg/~.}
wants, gunsi~;ht, from
other units. Ploy the piP~a alth compra?
pressure.
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Declassified in Part - Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
After blocring make sure the rubber osiva~hiroiitsandeto
securely fastened to the instrumente~ 8uf1 ~
the Pitot and TII tubes.
3. Check condition of moisture settlers of the Pitot
and TII tubes and remove condensate if any.
y. ~3ake sure the fuel oonsumption gauge scale is rotat-
ing smoothly.
Transmitters oY Bn ine Control Instruments
5. Check fastening of transmitters of the fuel oontent
gauge, fuel flocrmeter, tachometer and thermocouples; examine
the gas flow openings for oleanliness and position of the
thermocouple slots.
6.Check wire and pipe oonneetiona.
7. Disoonnect the plug connectors, ohecY. oondition of
oontact surfaces of the plugs and sockets. Conneot the plug
oonnectors and make sure the union nuts are securely
tightened and locked.
Artificial horizon
8. Ma1ce sure the art ifioial horizon does not brush
against any ob~eot behind tho instrument panel.
9. Remove the artifioial horizon from the airora~t~
inspect it and oheok the following:
- oorreot setting of the aide-slip indioatox;
- funotioning of the starting button and the airplane
silhouette handle;
- operating moment of the bi-metal relay;
- lateral correction switching ON and O1'I' anglos;
- operational readiness of the instrument;
.. time of gyroscope ereotion from top,lli:g;
- ourrent oonsumed in eaoh phase;
- stability of tho gyrosoopo vrith lateral oorreotion
switohed off;
- instrument error during imitation
tiona (~sinCovers and loops);
- insulation resistance.
R~~nte Gvromalnetic Compass
10. Check the following:
.. fasteninn of units and condition of the gyro unit and
~plif ier shock-proofing cushions;
- remote transmission error;
- comps rate of slaving;
transmitter lag;
.. fluotuation of indicator pointer in the slaved posi-
Gyr~ ction Compass
11. Check the following:
- fastening of units; lator;
- position of amplifier sensitivity rem
- funotioning of the oemPa~si
.+ compass rate of slaving; etio oource soale.
- amoothicoss of movement of the magn
oration of the gyrosoopio instrumonts and
12. Cheok op
engine oontrol instruments.
0 .nnn Equ1 ment
of all oxygen units, oondition and
13. Fastening and hose soaling rubber gasY.ets.
i es, hoses, ease of unecupling.
attachment of P P lug oonneotcr for
Check the combination p
ly.. Using tho ~'~ installation oheoic the follo~r n,~,:
.. tightness of the H.P? system;
p~ system under the oondltions
. tightness of the L?
oY vacuum and e:ceeasive pressure;
Declassified in Part - Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
 Declassified in Part - Sanitized Copy Approved for Release 2011/12/06 :CIA-RDP80T00246A062100090001-2
- iltl -
.- operation of the oxygen equipment under increased and
normal press~u?e;
- tightness of the pipe line supplying the pilot+s anti-g
suit blrsc?ders. .
21. Check the otzrrent consumed by the converter, and A.C.
voltage on its lead-out.
?.?. Remove the oonverter and examine the oor^nutator and
brushes. Airb:.ast the converter inside at a prossure of 0.5
to 1 kg/cm`.
1~. Condition of the oxygen remote control system.
Yilo+.':: Harness Automatic Unbuc:ainrr Device
1G. L`oinect tirain of operation of the device.
Every 50+5 Flying Hours
Aneroid-~,lembrane Instruments
17. Remove tl~e altimeter, airspeed indioator, altitude
and pxonsure drop indioator, variometer, mach~c2ter and check
on tho follotivings
- external oondition and fastening of the dial glasses;
- tightness of the body;
- basin orror;
- variation;
- smOOthT1eJJ of pointer movement.
After installing the instruments on the instrument panel,
mako earn v;hethor the rubber oanvas hos:;~ aro prayerly oon-
neoted to the instruuments and oheolt the statio and full pres-
?ure systoc~ for tightness.
18. Rene;r the altimeter and airspeed indicator oorreotion
oharts.
Remote Gvrc^~~tnetio Co^~ngss
19. Incpoct the plug oonneotors~ ohock the resist~noe
bot~7een the pluL; oonnootor pins of tho transit+;er and gyro
unit.
20. Choolt tho indioator error and variation Aith rozp~o'~
to the tra.*~seiitter overy 300.
Gyro-Induction Conp_ass
Check the following:
23. Induction compass transmitter:
- traces of fluid on the transmitter surfaoe and on the
plug oonneotor pins; oonneotor pins B,
.. insulation resistance betcreen plug
p and ~ and transmitter body. o unit plug
2t~. Compass gyro unit: resisAanc~ae~'C0s end B. A and B
pins 3 and K, ~ and ~' A and B.
and bet:ceen plug oonnnetor socket pins A and br
5 and B.
25. Compass indioator: osoillations and displacenont of
the magnetic course movinL; scale with the eneinos ctorkinE~
2G. Function box:
- tightening of all nuts on the olac~p bolts;
- condition of fuse;
- fastening of terpinal blocks of olnmp bolts.
27. Compass Ps a oouplete unit:
- serviceability;
- fast slaving op?od; ., ^zetic oo~u~o
- spooth?~o:%s of rove..ent of the indioator r ?:.?
scale.
.~. P? ~ .-, t'.c :.nit i c~tt, ir.~, :.
28. ..~.,
lb:~ii ~:
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- condition of corsautator-and-brush assenbly. B1oP the
instr~ulent in: ide erith cor~pressed air at a pressure oP
0.5 - 1 kb/cm2;
- sensitivity of the Snstrament at an angular rotation
speed of 6 and 18 deU/~eo.;
- symmetry of pointer defleotion;
- sluggishness and damping of the i~;dicator polnter.
~~-_~ Electric Turn Indicator
29. ltemove the instrument, inspect it and check on the
following:
- condition of the oommutator-and-brush assenbly.
Blow the instrument in:~ide with compressed air at a pres-
sure of 0.5 - 1 kE,/om2;
- sensitivity of the instrument at an angular rotation
speed of 0.6 and 1.5 deg/seo.;
- instrument error at 15?, 30 and Aso banks with angular
speeds of 1.1, 2.3 and 4 deg/sec.;
- instrument error at variations o3 supply voltage within
IOS~ of the nominal va7.ue;
-- misalicu-nment cf the pointer with the zero division of
tho soale;
- lag of the pointer;
- time required for returning of the pointer from tho
extreme position;
- deflection of the pointer from the zero division
at ?98 roll.
30. Inspeot the ooni:aot surfaces of the plug conneci:o,:.
31. Remove the indioator. end transmitters, Inspect them
and oheok tho following;
. basso error of the set;
- pointer oscillations;
.. stopping of the pointers short of the zero;
- baJ.ance of the indioator moving eyster~;
- value of interphase voltages on the transmitter clamps.
32. Inspect the oontact surfaces of the plug oonneotors.
Prese~:se ^arr_ir_~ Units
33. Remove tho pressure warning units, inspoot them and
oheok on the following:
.. v