THE TU-134 AIRCRAFT WITH D-30 ENGINES PROVISIONAL INSTRUCTIONS FOR OPERATIONAL FLIGHT AND PILOTING

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP78-03066R000400020001-4
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 296
• Document Creation Date: December 22, 2016
• Document Release Date: April 18, 2012
• Sequence Number: 1
• Content Type: REPORT

Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03
-;ECRET
r
DIRECTORATE OF
PLANS
THE TU-134 AIRCRAFT
WITH D-30 ENGINES
066R000400020001-4
PROVISIONAL INSTRUCTIONS
FOR OPERATIONAL FLIGHT
AND PILOTING
Book 1
2nd Edition
(English-Language Version)
SECRET
50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
S - )?.1- ? R-1]
ro .1.'CiZt?:fG?i-.;
TEE
50X1 -HUM
1J 134
-
WITH V.,-30 ENGINES
PROVISIONAL INSTRUCTIONS
FOR OPERATIONAL FLIGHT
AND PILOTING
BOOK 3.
2nd Edition
Revised Elnd Sipplemnted
By The
USSR MINISTRY OF CIVIL AVIATION
Order N? 625
of
19 Sept 1967
1967
- 3 -
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
NO DISS'A
PROVISIONAL INSTRUCTIONS
Fon OPERATIONAL FLIGHT
AND PILOTING
of the
TU-134 AIRCRAFT
with
D-30 ENGINES
50X1 -HUM
OVERALL
TABLE OF CONTENTS
Source Translated
Text Text
Page Page
No. No.
0-2
0-3
0-4
0-5
0-6
13
,
0-15
0-16
0-17
0-18
1-1
1-2
1-3
1-3
1-5
1-5
1-5
1-5
1-9
1-12
1-12
1-15
1-17
1-17
1-22
1-24a
1-25
1-26a
1-261)
1-26f
Section 1, GENERAL
LEFT-SIDE OVERALL VIEW OF AIRCRAFT 12
List of Section Headings 13
INTRODUCTION TITLE PAGE 14
Section 0 Table of Contents 15
1. GENERAL INFORMATION ON THE AIRCRAFT 16
2. Sheet(s) For Listing Revisions in the Text 20
3. Registration Sheet 21
4. GEOMETRIC SPECIFICATIONS 22
5. Diagram, Aircraft General Views, Figure 0.1 25
6. DEFINITIONS 26
7. Standard Climatic-Condition Curve
(Altitude and Temperature), Figure 0.2 27
8. Farenhcit-to-Centigrade Conversion Graph, Fig. 0.3 28
Section 1, RESTRICTIONS AND PREPARATIONS FOR FLIGHT
Section 1 Table of Contents
Chapter One, FLIGHT RESTRICTIONS
1. Mach-Airspeed Restrictions
2. G-Load Allowances for Vertical Maneuvers
3. Altitude Restrictions
4. Aircraft Trim-Setting Restrictions
5. Aircraft Weight Restrictions/6.Power-P1ant Restriction
7. Various [Other] Restrictions
Chapter Two, FLIGHT PREPARATIONS
1. Calculating the Optimum Flight Mode
2. Calculating Aircraft Fuel Requirements [etc.]
3. Preflight Inspection and Checks bv the Crew
Aircraft Checkout by Copilot
Aircraft YcjuipL.-nt Check by Navigator
Aircraft Checkout by Steward(ess)
The Captain's Checklist
Flight Engineer Preflight Inspection & Preparations
Prescribed Aircraft Inspection & Checkout. Sequnce
End of Section 1
- 02 -
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ITO FCMIGN DISSEM
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2
30
30
33
33
36
36
38
42
42
45
52
52
62
C6
6E,
70
72
20
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18 :
TU-134 Aircraft Manual of Contents
4.. 1 Section 2, EQUIPMENT OPERATION AND FLTING
AIRCRAFT
CIA-RDP78-03066R000400020001-4
(Cont'd)
THE
50X1 -HUM
81
2-1
Chapter One, AIRCRAFT EQUIPMENT OPERATION
82
2-2/6
Section 2 Table of Contents
3
2-7
1. THE POWER PLANT
82
2-7
- The D-30 Engine
82
2-7
- The SPZ-30 Engine Starter System
82
2-7
- Engine-Operation Monitoring Instruments
84
2-9
- Preparing the D-30 Engines for Flight
84
2-10
- Starting the Engines
87
2-13
- Warming-up and Testing the Engines
91
2-19
- Stopping the Engines
98
2-20
- Peculiarities of Engine Operation in Low
Temperatures
100
2-20
- Engine Shut-down During Flight
101
2-21
- Engine Start-up During Flight
103
2-22
- Use of the Engine-Control Levers
104
2-23
2. THE FUEL SYSTEM
105
2-23
- Brief Description
105
2-23
- Fueling the Aircraft
106
2-27
- In-Flight Operation of the Fuel System
111
2-27
3. THE ENGINE LUBRICATION SYSTEM
114
' 30
4. THE FIRE-PROTECTION SYSTEMS
115
5. ELECTRICAL EQUIPMENT OPERATION ON GROUND AND
IN THE AIR
117
2-31
- Aircraft Ground-Source Power Supply
117
2-32
- Voltage Regulation and Adjustment of the
STG-12TMO-1000 Starter-Generator for
Parallel Operation
119
2-34
- Automatic Overvoltage Protection of the
On-Board Electrical Circuitry
122
2-34
Automatic Protection of Electrical Equipment
Circuitry
122
2-36
6. THE HYDRAULIC SYSTEMS
123
2-36
- Brief Description
123
2-37
- Landing-Gear Retraction by Primary Hydraulic
System
125
2-37
- Landing-Gear Extension by Primary Hydraulic
System
125
2-37
- Steering the Forward Landing-Gear Wheels
125
2-38
7. THE 7\IRCRAFT BRAKING SYSTEMS
126
2-38
- Automatic Brake Controls
126
2-38
- Spoiler System Control
127
2-39
Wingf lap Control
127
2-39
- Landing-Flap Control
128
2-39
- Landing Parabrakc [Drogue C1mte3 Control
128
2-39
8. THE COMPRESSED-AIR SYSTEM
128
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NO FOI:',IGN DISS.EM
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NO FO=GN ai=
2-40
2-40
2-40
2-41
TU-134 Aircraft Manual Ta.,--Oe of Contents (Cont'd)
9. DEICERS AND ELECTRICAL HEATING DEVICES
- Brief Description
- Wing, Rudder, and Engine-Cowl Inlet Deicers
- Engine [Interior] Deicers
50X1 -HUM
129
129
130
131
2-41
- Aircraft Deicer System Check
131
2-42
Stabilizer Deicer
132
2-42
- Pitot-Head (PPD) Deicers
132
2-42
- Crew-Cabin Windshield Defrosters
133
2-43
- Using the Windshield Wipers
133
2-43
- Checking Windshield Wiper Operation
134
2-43
10.
OPERATION OF THE AIRCRAFT
134
2-43
- Stabilizer [Trim-Adjustment] Operation
134
2-44
- Aileron Operation
134
2-44
- Aileron Trimtab Operation
135
2-44
- Rudder Operation
135
2-45
- Rudder Trimtab and Trim-Mechanism Operation
136
2-45
- Engagement of Rudder Hydraulic Booster and
Emergency Crossfeed Control Valve
137
2-45
- Elevator Operation
137
2-46
- Elevator Trimtab Operation
138
2-46
- The DR-134M Yaw Damper
138
- 7
- Aircraft Operation Check with [External]
Power Source Engaged
139
_-7.
- Aircraft Operation Check with Engines Operating
140
2-50
11.
HIGH-ALTITUDE [PRESSURIZATION] EQUIPMENT
142
2-50
- Brief Description
142
2-50
- Preflight Equipment Checkout
143
2-52
- In-Flight Equipment Operation
146
2-58
12.
OXYGEN EQUIPMENT
151
2-60
13.
RADIO EQUIPMENT
154
2-60
A. RADIOCOMMUNICATIONS EQUIPMENT
154
2-60
- Intercom and Public-Address System
154
2-61
- "Lotos" and RSIU-51M Command Radiosets
155
2-62
- The (1-RSB-70*) Communications Radio
157
2-63
- Aircraft Emergency Radio
158
2-63
B. RADIONAVIGATION EQUIPMENT
159
2-63
- ARK-11 Automatic Radiocompass
159
2-64
- RV-UM Low-Altitude Radioaltimeter
161
2-65
- "Kurs-MP2" Navigation and Landing System
162
2-65
(a) Preflight System Preparation
162
2-65
(b) Flying Aircraft by VOR System
163
2-66
(c) Landing by the ILS System
165
2-67
(d) Landing Approach with Simultaneous Use
of VOR and ILS Systems
167
2-69
(e) Landing Approach by SP-50 & Put'-4MP Systems
169
2-71a
- RSBN-,-2S Landing and Approach-Navigation System
174
2-71a
(a) Functional Designation
174
2-71a
(b) Flight Along Given Azimuth to and from
a Beacon.
175
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S-E-C-R-E
NO YO-11GN N.SSF2A
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
NO l'013EIGN DI SSE :
2-72
2-73
2-[74)
2-75
2-76
2-76
2-76
2-80
2-81
2-81a
2-32
2-85
2-87
2-07
2-87b/465L
2-87b/465L
2-87c/465L
2-87e/465L
TU-134 Aircraft Manual Table of Contents (Cont'd)
(c) Flight in SRP Submode over Routes with-
out Beacon Installations
(d) Penetrating Clouds by the RSBN-2S Systen
(e) Landing by the "Katet-S" System
(f) Landing by the SP-50 System While Using
both the RSBN-2S and KURS-MP-2 Systems
- The NAS-1A6 Aircraft Navigational System
- Functional Designation
- Preflight Check and Preparation of the
NAS-1A6 System
- In-Flight Use of the NAS-1A6 System
13a. THE KS-8 COURSE-INDICATOR SYSTEM
14. THE BSU-ZP ON-BOARD LANDING APPROACH CONTROL
- Preflight Check of the BSU-ZP System
- In-Flight Operation of the ESU-ZP System
- The AP-6Ye Var. 41 V.K. Autopilot
- Preflight Check of the Autopilot
- In-Flight Use of the Autopilot
- Engagement of the Autopilot
- Using the Autopilot Control Handles
- Using the Autopilot on Straight-Line Sectors
of the Route
- Autopilot Automatic-Update at Next Route
- Autopilot Automatic Conversion to New Flight
Path Paralleling Assigned Route
Correction of On-Route Aircraft Ground Co-
ordinates and Automatic Return to Assigned'
Course upon Discovery of Lateral Deviation
- The "Put'-4MPA" Flight-Director System
THE "PUT14MP" FLIGHT-NAVIGATION SYSTEM
1. Functional Designation
2. Complementary Components
3. Operational Principle. Peculiarities of Landing
Approach by Command Indicator
4. "Put'-4MP" System-Error Warning
5. Operation of the "Put'-4MP" System
- On-Route Flight
15. RADAR EQUIPMENT
- The ROZ-1 Terrain-Scanning Radar
- Preflight Check of ROZ-1 Radar by Navigator
- In-Flight Use of ROZ-1 Radar by Navigator
- The son-64 Radar Transponder and the UVID-30-15*
Electrical Altimeter
- Preflight Check of SOM-64 and UVID-30-15
- In-Flight Use of S014-64 and UVID-30-15
16. THE AUTOMATIC AUASP-3K ANGLE-01.'-ATTACK & OVERLOAD
INDICATOR (Slip-Angle Channel Not Used)
- Preflight Check of the AUASP-3K
- In-Flight Use of the AUASP-3K
1:7a/4 50L
87a/450L
2-87a/450L
2-87b/450L
2-88a 14a.
2-88a
2-88a
2-88a
2-88c
2-88c
2-88c
2-89
2-89
2-29
2-89
2-91
2-91
2-92
2-93
2-.93
2-94
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179
180
183
183
183
189
190
SYSTEM 191
193
197
201
201
205
205
207
208
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217
218
219
219
219
220
222
223
224
225
226
226
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
2-95
1;C' FOEELGi Die
TU-134 Aircraft Manual Table of Contents (Cont'd)
Chapter Two, FLYING THE AIRCRAFT
50X1 -HUM
228
2-95
A. NORMAL FLIGHT CONDITIONS
228
2-95
1. TOWING AIRCRAFT TO TERMINAL AND TO STARTING POSITION
228
2-97
2. TAXIING THE AIRCRAFT
231
2-99
3. PREPARATION FOR FLIGHT
234
2-99
- Preliminary Starting ProcedureS
234
2-100
- Pre Take-off Procedures
236
2-100
4. THE TAKE-OFF
236
2-100
- Taking Off Under Normal Conditions
236
2-102
- Taking Off in a Crosswind
239
-2-102
- Taking Off in a Tailwind
240
2-103
5. GAINING ALTITUDE
240
2-103
6. LEVEL FLIGHT
241
2-104
- Crew Duties During Level Flight
242
2-104
- Duties of the Aircraft Commander
242
2-104
- Duties of the Navigator
242
2-104
- Duties of the Copilot
242
2-104
- Duties of the Steward(es)
245
2-106
7. NIGHT FLYING
245
2-106
- Preparation for Flight
245
2-107
8. PLYING AT MAXIMUM SPEEDS
247
2-107
9. FLYING AT MINIMUM SPEEDS
248
2-107
10. FOUL-WEATHER FLYING
248
2-108
- Recommendations for Avoiding Dangerous Turbulence
249
2-109
- Flying the Aircraft Through Bumpy Air
251
2-111
- Flying the Aircraft During Icing Conditions
254
2-111a
11. THE DESCENT
256
2-112
12. EMERGENCY DESCENT
258
2-113
13. GROUND-GONTROL APPROACH IN INSTRUMENT-LANDING MODE
259
2-114
14. THE LANDING APPROACH AND THE LANDING
260
2-114
- The "Big Box" Landing Approach Method
261
2-117
- Crew Duties During Landing Approach
266
2-118
15. LANDING-ABORT FOR SECOND APPROACH WITH BOTH ENGINES
OPERATING
267
2-119
16. APPROACH AND LANDING IN A CROSSWIND
268
2-119
17. LANDING ON AN ICY RUNWAY
269
2-120
18. TAXIING TO PARK POSITION AND ENGINE SHUTDOWN
270
2-122
B. EMERGENCY FLIGHT CONDITIONS
273
(SpecialSituations)
2-322
1. FAILURE OF ONE ENGINE DURING TAKE-OFF
273
2-123
2. FAILURE OF ONE ENGINE DURING CLIMBOUT
276
2-124
3. FAILURE OF ONE ENGINE DURING FLIGHT
277
2-125
4. FIRE ABOARD THE AIRCRAFT
278
2-126
5. ELECTRICAL EQUIPMENT SYSTEM MALFUNCTIONS
280
2-126
- Short Circuits
280
2-128
- Generator Failure
283
- 6 -
S-E-C-R-E-T
NO Fc.a.-:;:rGN raSSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
NO (E:I(.3NDiS
TU-134 Aircraft Manual Table of Contents (Cont'd)
2-128 6. LANDING GEAR RETRACTION AND EXTENSION SYSTEM MAL-
FUNCTIONS
2-128 - Incomplete Retraction
2-129 - Landing-Gear Extension Malfunctions
2-130 - Emergency Completion of Landing-Gear Extension
2-130 7. POSSIBLE FAILURES OF THE DR-134M YAW DAMPER
2-131 (a) AP-6Ye Autopilot Failures
2-131 8. PEDAL CONTROL OF RUDDER WITHOUT BOOSTER ASSIST
2-131a 9. LANDING WITH NOSEWHEELS RETRACTED
2-132 10. LANDING WITH ONE MAIN BOGIE RETRACTED
2-133 11. FORCED ROUGH-FIELD LANDING
2-133 12. BELLY-LANDING
2-134 13. LANDING WITHOUT EXTENDING LANDING FLAPS
2-134. 14. LANDING APPROACH AND LANDING WITH ONE INOPERATIVE
ENGINE
2-134 15. LANDING ABORT AND SECOND APPROACH WITH ONE ENGINE
INOPERATIVE
2-135 16. LANDING WITH 44-TON MAXIMUM PERMISSIBLE LOAD
2-135 17. GROUND EMERGENCY EVACUATION OF PASSENGERS AND CREW
BY MEANS OF INFLATAELE SLIDES, EMERGENCY CHUTES,
AND (KNOTTED) ESCAPE ROPES
2-137 [End of TU-134 Aircraft Manual Section 21
50X1 -HUM
284
284
285
286
287
288
289
289
291
292
293
294
295
925
296
297
299
[TU-134 Aircraft Manual Section 3 unavailable-for translation)
- 7 -
S-E-C-F.-F.-T
NO F017.;717.GN DISLIE1-1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
NO }0 l( 1)-1_SEV,
0-2
0-15
0-17
0-1C
1-4
1-6
1-7
1-10
1-11
1-13
1-11:
1-16
1-16e
1-18
(2-8)
2-12
2-14
2-16
2-17
2-24
2-26
2-28
.2-51
2-53
TU-134
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Aircraft Manual Tb)e. of Contents (Cont'd)
FIGURES (ILLUSTRATIONS) IN TEXT
0.0 [Undesignated) The Tu-134 Aircraft
0.1 Diagram, General Views of the Aircraft
0.2 Standard Climatic-Conditions Curve
(Altitude and Temperature)
0.3 Farenhoit-to-Centigrade Temperature Con-
versions
1.1 Chart of Permissible Mach,-Airspeed Limits
1.2 Maximum G-load for Vertical Maneuvers
1.3 Shifts in the Center of Gravity Caused
by Consumption of Fuel
TU-134 Aircraft Seating Arrangement
Variations
Figure 1.5 TU-134 Aircraft Fuselage Configuration
to Accommodate 72 Passengers (2nd Series)
Figure 1.6 Selection of Flight-Range Parameters
Figure 1.7 Longitudinal Wind Component (Wind Axis)
Figure 1.8 Determination of Trip-Flight Fuel Re-
quirements
Figure 1.8a Correction Coefficient for Computing
Specific Ranges in Calculating State
Test Results
Figure 1.9 Aircraft [Exterior) Inspection Sequence
Figure 1.4
Figur [2.1] Left-Side Overall View of Engine
Figure 2.2 Engine Warm-up and Testing Chart
Figure 2.3 .Changes in Engine Compressor Second-Stage
Rotor RPM at Ground Idle...
Figure-2.4 Changes in Engine Compressor First-Stage
Rotor RPM Relative to Atmospheric Con-
ditions While in Ground Take-Off Mode
Figure 2.5 Changes in Maximum Attainable Post-Turbine
Gas Temperatures and Second-Stage Rotor
Speeds Relative to Atmospheric Conditions
.While Operating in Ground Take-Off Mode
Figure 2.6 Fuel System Schematic Diagram for Aircraft
up to No. 04-01
Figure 2.7 Fuel Tank Input and Output Sequence Chart
for Aircraft up to No. 04-01
Figure 2.8 Lubrication System Schematic Diagram
Figure 2.9 High-Altitude Equipment System Checks
and Controls
Figure 2.10 Graph Showing Regnlaton Changes in Cabin
Pressures Relative to Flight Altitudes
- 8 -
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ITO 1.007,7IGN rirssEm
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12
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27
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' 31
34
35
40
41
43
44
45
51
54
83
89
92
95
96
107
110
113
144
147
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
SJET
No _FOTEICK
0-2
S-E-C-R-E-T
rio FOY-MI(11i DISSEI.4
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
NO 01UIG'=.1 D1b31,1 50X1-HUM
0-3 SECTION HEADINQS
SECTION 0. INTRODUCTION
SECTION I. FLIGHT RESTRICTIONS 211D PREPARATIONS
SECTION II. EQUIPNENT OPERATION ,AND PLYING THE I\IRCRAFT
' SI, CT LON IT I . FLIGHT CHARACTE RI ST) CS
NO FOREIGN DISSEM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
EC) 3:0:2ETIGT,:
0-4
SECTION 0
INTRODUCTION
S-E-C-R-E-T
10 FOREIGN DISSELI
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
'
I;O 3 c EiG DISS7,1
0-5
SECTION 0
INTRODUCTION
50X1 -HUM
Source
Paae No.
6
8
1.
2.
TABLE OF CONTENTS
Paae No.
GENERAL INFORMATION ON THE AIRCRAFT
Sheet (s) for Listing Revisions in the Text
11
3.
Registration Sheet
12
4.
GEMETRICAL SPECIFICATIONS
15 ?
5.
Diagram, Overall View of Aircraft, Fig. 0.1
16
6.
DEFINITIONS
17
7.
Standard Climatic-Condition Curve
(AltquCe and Temperature), Figure 0.2
18
8.
Temperature Conversion from Farenheit into
Centigrade, Figure 0,3
S-E-C-R-E-T
FOF,EI(11 DISSEM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
S -11 -7] -J.F2
VO CI1.::1CdT ssT..`,1.,1 50X1-HUM
0-6
-4-673-1:7
GENERAL 1N) OR ON THE AIRCRAFT
The TU-134 aircraft with its two D-30 turbojet engines
is designed for transpeiting passengers, luggage, and mail
over short and medium air routes of P600 to 3,500 kilometers.
This aircraft is a low-wing cantilever monoplane of
all-metal construction, with swept wings and tail surfaces,
and with tricycle landing gear.
The principal distinguishing feature of this aircraft
is the installation of its two engines at either side of the
fuselage tailsection. This configuration offers several
advantages, including:
reduction of noise- and vibration-levels in the
passenger compartment;
improvement of wing-surface aerodynamics;
facilitation of power-plant service and maintenance.
?
The high cruising speed (000-900 km/hr), high performance
ceiling altitudes (10,000-11,000 meters), and sophisticated
autopilot, navigational, radio, and radar equipment, and also
its automatic landing-approach equipment, all permit the use
of this aircraft on all international air routes under diffi-
cult weather conditions.
Its great power reserves, extensive power-assist of wing
[control srrfacesl, and reliable brakes assure excellent take-
off and landing characteristics for the aircraft, and substan-
tial atte tion has been devoted to the efficiency and relia-
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--E -C -T
NO r0PaiCT,I DISS1T,1
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
0 -
50X1 -HUM
bility of its controls. The DR-134M yaw damper installed
on this aircraft substantially facilitates handling, es-
pecially during bumpy flight or landing at minimum landing
speeds in strong cross-winds.
The stabilizer on this Fircraft has been made adjustable
so as to provide a range of trim settings during takeoffs.
The main landing gear bogies of the aircraft are of uni-
que design with rocker-type main struts. This design as-
sures smooth shock-absorption during landing and ground turns.
A service door and hatch in the right side of the fuse-
lage provide access to the forward and rear luggage compart-
ments, which are completely isolated from the buffet and pas-
senger compartments.
Flight safety of the aircraft is assured by:
the operational reliability of the D-30 engines;
installation of the engines on fuselage tailsection
pylons;
operational flight ceiling above 10,000 meters al-
titude, i.e., above the cloud zone;
capability of continuing flight with one engine dead;
capability of continuing flight on one dead engine
0-7 at altitudes of 5,500-6,500 meters, with practically no re-
-465L
duction in range and while maintaining normal air-condition-
ing in the passenger compartment.
improved design stability of the pressurized section
of the fuselage, especially at openings for windows, hatolles,
and doors, and of windo%?7glass installation, precluding the
- 17 -
S -17 --R -22
13 I'OLIGi DISSEM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
ri) 17(X:1-XJ.G77
50X1 -HUM
the possibility of e,-,bin deprossurizaiion;
c?1,bility for rapid descent from higher to E-.fer
altitudes (in event of cabin depressurization) with landing
gear extended;
incorporation of emergency backup components in
the primary systems and equipment of the aircraft;
incorporation of de-icing systems for leading-edge
surfaces of wings, tail surfaces, and engine inlets, and for
crew-compartment windows;
provision for rapid evacuation of the aircraft by
both passengers and crew in event of wheels-up landing on
dry land or water. For this purpose, the aircraft is pro-
vided with emergency exits according to ICAO standards and
with special safety equipment (such as escape chute, inflat-
able escape slide, individual life jackets, emergency radio).
The passengers are assured of comfort during flight.
Modern appaintm2nts of the passenger cabin interior, plush
and comfortable seats with adjustable backs, and excellent
sound proofing all contribute to passenger ease and comfort.
The aircraft purchaser has a wide choice of interior
finish and color schemes to choose from.
The passenger cabin is equipped with an intercom radio
system permitting the crew to provide the passengers with
flight information, and a signalling system by means of wIlich
a pa:-senger may summoil steward service, either from his own
seat or from one of the restrooms.
Cei 3 ing-mounted indirect lighting provides prinlary ii-
- 18 -
S-E-C-R-E-T
ro 1.20aGN DISSEM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
PC) FC)-::::3:11T 1-.)IS:717.."
50X1 -HUM
lumination for the passnger eopartments, and as this pri-
mary syster is turned off, service illumination comes on,
besides which each passenger has a personal light (as well
as ventilation outlet) built into the overhead luggage rack.
An artificial microcJimate is maintained in the pas-
senger cabin by means of an air-conditioning system which
maintains a 20?C temperature at all times of year and at
all altitudes. Sea-level air pressure is maintained up
to 6,000 motors altitude. During ascent to higher alti-
tudes, the pressure gradually decreases, maintaining a con-
stant ratio of 0.57 atmospheres between internal and exter-
nal air pressure. At an altitude of 12,000 meters, cabin
pressure is equivalent to atmospheric pressure at 2,400 m.
- 19 -
S-E-C-R-E-T
I0 PGIT,TGY, DI
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
ICU
0-8 SHEET
For Listing Revisions an Supplements by Change
Leaflet or by Bulletin
ILCP
Nos. Date
50X1 -HUM
Change-Sheet or Bulletin NO. Section Cha -
Who Published the Bulletin, ter, Subsec-
and in That eeries tion & Page
1 2
3 4
Who made
--
& record-
ed change
5
- 20 -
EC FaEIGN DILiSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
TO 1G
0-11
REGISTRATION SITE1,1T
TUPOLEV Designed Aircraft
Type TU-134 Passenger Aircraft with
D-30 Engines
Aircraft Manufactured in the USSR,
Identification No.
Design No. Series No.
USSR
Built in 196...
- 21 -
S-E-C-R-E-T
110 l'OPEITT Iff,SSEM
50X1 -HUM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
-T
NO Y'?',51-Lae-j-TLTSSi
50X1 -HUM
0-12 GEO.METRICAL SPECIFICATIONS
465 L
Height of Aircraft
9.02m
Length of Aircraft
35m
Maximum Dian'eter of Fuselage
2.9m
WINGS
Wingspan
29.0m
Wing Sweep Angle
350
Aspect Ratio
7.3m
Wing Area:
Including Protrusion
127.3m2
Excluding Protrusion
115.0m2
Average Aerodynamic Chord
4.318m
Wing Angle of Incidence
+10
AILERONS
Aileron Span
2x5.15
=
10.30m
Area of Setback-Hinge Aileron,
Excluding Blade (nozh)
9.68m2
Area of Flettner-Flap Trimtab,
Excluding Blade (nozh) (two)
2x0.187m2
=
0.374m2
Area of Flettner-Flap,
Excluding Blade (nozh) (two)
2x0.164m2
=
0.328m2
Aileron DefleCtion Angle (up & down)
19?+1?
Aileron Trimtab Deflection Angles,
(up and down)
3?+30'
Flettner-Flap Deflection Angles,
(up and down)
6?+30'
Flettner-Flap and Trimtab Transfer
Ratio
0.31
WINGFLAPS
Span of Wingflaps:
Inner
5.41m
Outer
7.69m
Total Wingf lap Area
22.51n2
Inner Wingflap Deflection Angles:
During Take-off
20? or 100
During Landing
Outer Wingflap Deflection Angles:
During Take-off
18? or 9?
During Landing
350
- 22 -
S-E-C-R-E-T
NO FU.IITIC Gii DI SSE1.1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
. b .
NO 170.1a au 50X1 -HUM
SPOILERS
Total Spoiler Area
Spoiler Deflection Angle
Spoiler Span
0-13 FUSELAGE BELLY FLAP
Bellyflap Area
Bellyflap Extension Angle
Bellyflap Width
HORIZONTAL TAIL SURFACES
4.48m2
52??1'
7.01m
5.32m2
400?1?
02.8m
Horizontal Tail Surface Width 11.8m
Tail Surface Sweep Angle Along the
1/4-Chord tine 380
Stabilizer Surface Area 24.263(m2)
Total Horizontal Tail Surface Area 30.68(1112)
Length of Horizontal Tail Surface 4.54(m)
Stabilizer Trim Setting Angles Relative
to Fuselage Design-Horizontal:
For Take-off up to -4'(-2.5 on UPS*)
For Flight & Landing -1'30'(0 on UPS*)
Elevator Surface Area (two)
6.417m2
Elevator Deflection Angles:
Upward 220?10
Downward 160?10
Elevator Trimtab Area (two)
0.684m2
Elevator Trimtab Deflection Angles:
Cable actuated (up & down) 8?+30'
Electrically actuated (up & down) 4?30'
VERTICAL TAIL SURFACES
Vertical Tail Surface Sweep Angle
Along the 1/4-Chord Line 40?01'
Vertical Tail Surface Area Including
the Dorsal Fillet 21.25m2
Rudder Area 5.7m2
Rudder Deflection Angles (R. & L.):
With Flaps Retracted ?5? [sic?)
With Flaps Extended 250i10
Rudder Flettner-Flap Trimbab Area 0.594m2
Rudder Flettner-Flap Deflection Angles,
(Right and Left) 17?30'?30'
Rudder Trimtab Deflection Angles(REL) 3?30'?30'
Rudder Flettner-Flap Transfer Ratio 0.70
* UPS = Stabilizer Position Indicator
- 93 -
S-Y.1-C-P-H-T
NO FOETIGIC" DISET,1,1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18 : CIA-RDP78-03066R000400020001-4
?
0-14
rio J"ORT.T.G.1;
LANDING GEAR
Iiheelbase (Struts not Compressed)
Wheeltrack (Between Main Landing-Gear
Bogies)
Main-Bogie Wheel Size
Nosewheel Size
Nosewheel [Maximum] Deflection Angle
During Take-off Run and Landing
Nosewheel [Maximum] Steering Angle
During Taxiing
24 -
S-E-C-R-E-T
NO FOI-EIGN DISSEM
13.73m
9.45m
930x305V
660x200V
+5?30'+30' [sic?)
350-110
50X1 -HUM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
LIE.;Y-1`
C.T) jL C.0
? 25 ?
S -E -C -E -T
No FUREIGicf DISSEM
50X1 -HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
yorn-iiGN Din=
50X1 -HUM
DEFINITIONS
Below are given some definitions and terms found
in Section 3, "FLIGHT CHTI.RACTI:RISTICS" [not available for
translation].
Barometric Altitude....... Atmospheric pressure expressed in
units of altitude, as per MSA.
This is obtained by setting the
? fine barometric altimeter scale
at 1013.2 millibars (760 mm Hg).
True Altitude The actual vertical distance be-
tween the lowest point on the
aircraft in level flight and the
corresponding point of reference
on the terrain surface.
Outside Air Temperature... Temperature of the undisturbed
air in the vicinity of the air-
craft. This is determined by
means of the Outside-Air Ther-
mometers.
The total weight of the Aircraft,
including fuel, oil, equipment,
crew, and payload.
Atmosphere The aircraft may be operated in
ambient air temperatures ranging
from -70?C to +45?C.
- 26 -
NO FOPai:IGN I)ISSEM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/18: CIA-RDP78-03066R000400020001-4
NO FOREIGN DISSE7,!
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