CS-61-048
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CCJNVAJR MODEL. m
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PRO I
A I E
FLIGHT U A L
Ijdel 30
The certi i le limitations, Operating Procedures and
Performance ormation included in this Provisional
Flight Manual, (a issued under the requirements of spe-
cial Civil Air Re ulation number SR-425C, dated June 6,
1961), do not r lect the final values, data and informa-
tion thaf wilj/be effective on a fully type certificated
/"" " airplane.
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GCJNVAJR MODEL- 53 e
FLIGHT MANUAL-
PROVISIONAL
AIRPLANE FLIGHT MANUAL "
For The ·-, ..
CONVAIR 990
(Model 30 ) "·--.., ,
TURBOJET, AFT FAN, TRANSPORT, ..4
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AIRPLANE '"·... "·-
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This airplane must be operated in conipliance with
the Certificate Limitat/ions, Section 1, contained
herein. A copy of this Provisional Flight Manual,
composed of Secti'Qiis 1 through k, or its equivalent,
must be carried in each provisionally certificated
airplane at all times and be readily available to
the flight crew. "
Airplane Registration No.
, Serial No.
%
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Oct. 2O/61 Page i
Code K

CCJNVAIR MODEL. 3 m
FLIGHT MANUAL.
FLIGHT MANUAL FORMAT INFORMATION
The Flight Nnual applicable to a specific version of a Model 30 (Convair 990)
airplane is composed of basic pages and may also include some pages applicable
only to that version. Identification of pages is accomplished as follows:
MODEL CODE EXAMPLE
30 (Basic ) K , 1-16
" Code K
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ThC'LIST'OF EFFECTIVE PAGES in the front of each Flight Manual itemizes all the
curre'ntiy effective pages required to construct a Flight Manual for the
airplanes.,noted in the page headings.
A solid bl-aek line in the page margin indicates the portion of the text
affected by t"he current revision.
Page ii
Oct. 20/6i Code K

CCJNVAIR MODEL- 3 e
FLIGHT MANUAL.
LIST OF EFFECTIVE PAGES
model 30 Airplane Serial Numbers: I through 55
PAGE
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Page iii
Nov. 3/61 Code K

CCJNVAIR MODEL- 53 !
FLIGHT MANUAL-
LIST OF EFFECTIVE PAGES
model 30 Airplane Serial Numbers : I through 55
PAGE CODE DATE PAGE CODE DATE PAGE CODE DATE
4-2f5 K oct. 20/61
4-26 K oct. 20/61 "-
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4-2j' K oct. 20/61
4-28 K Oct. 20/61 b '"' .. .'
4-29 K oct. 20/61 ':",':....., .,. . .. ,,,'
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Page iv
Nov. 3/61 Code K

0
CCJNVAJR MODEL. 3 e
FLIGHT MANUAL.
LIST OF EFFECTIVE PAGES
MODEL 3Q Airplane Serial Numbers : I through 55
PAGE CODE DATE PAGE CODE DATE PAGE CODE DATE
" S)""'
. ,,))7)"
Page v
Oct. 2O/6i Code K

GONVAJR MODEL- 53 m
FLIGHT MANUAL.
LOG OF REVISIONS
REV
NO. DATE PAGE NUMBERS DESCRIPTION
I Nov. 3/6i iii, iv, vi, 1-25, 1-31, Revision for Provisional Type
1-38, ECL-I, and 2-9 Certificate .
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Nov. 3/6i Code K

0
CCJNVAIR MODEL- 3 m
FLIGHT MANUAL.
LOG OF REVISIONS
0
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NO. DATE PAGE NUMBERS DESCRIPTION
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Page vii
Oct. 2O/6i Code K

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H

CCJNVAJR MODEL- 3 m
FLIGHT MANUAL.
TABLE OF CONTENTS
SECTION I, CERTIFICATE LIMITATIONS
Type of Airplane Operation.... ·
Maximum Operating Altitude................
Flight Crew .... ················
Weight Limitations, Maximum Structural
Center of Gravity Limits ·
Takeoff Climb Weight Limits, Preamble.........
Takeoff Climb Weight Limits, Second Se=ent, CHart.........
Approach Climb Weight Limits, Preamble.... ·····
Approach Climb Weight Limits, Chart.....................···
A11owable Takeoff Weight Permitted By Avai able Runway Length,
Preamble.................··
Allowable Takeoff Weight Permitted by vaila e Runway
Length, Chart................... ...· ············
Power Plant Limitations.............. .7"ttz~ ...... ... ··········
Operating Limits....... ... ... ············· ············
Engine Starters......· ·······"Y""b
Fuel Types·········· ········"">'y" """'""""""""""""°"""
Oil Types ···· ···················
Engine Thrust Reve e imitations.... ............········
Engine Anti-lee te L. itations..... ..... ·
Engine Bleed A'r Limits. ... .........·····················
EXhaust Gas mperature Lir9;$s EGT),5 gine Starting.......
EXhaust Gas Temperature t' its GY), Takeoff..............
Minimum Takeciff EPR C drt... ...m....
Minimum Takeot Fan ced Chart,.........
Engine Rotor S ee Units..... ·················
Power Setting C rt for Maxi Continuous Power,Clinib.....
Minimum Fan Speed art,for aximum Continuous Climb.......
CIT Conversion Chart, tftic Air Temperature...............
CIT Conversion art, R Air Temperature..................
Fuel Sys:tem Limitations ·...···························
.' Fuel Telnperature""E,-" its......................·.············
Fuel jettison Limitations.............· ········
Boost and Trarlqfer Pump Limitations..................······
Fuel Loading LQitations.....................··.···········
Fuel System Opfation Limitations
C.G. Limitations with Trapped Center Section Fuel..........
Fuel Balance Limitations..............·····················
Inflight Asymmetric Fuel Distribution Limits...............
Oil System Limitations ················
Airplane Takeoff ·........·····························
Takeoff Procedure, All Engines Operating ····
Takeoff Procedure, Engine Failure During Takeoff...........
Three Engine Takeoff Procedure Requirements................
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1-3
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1-7
1-9
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1-12
1-13
1-1'1
1-15
1-i6
1-17
1-18
1-i9
1-20
1-21
1-21
1-21
1-21
1-22
>25
1-25
1-26
1-26
IA27
1-28
1-28
1-29
1-29
I-i
Oct. 20/6i Code K

CCJNVAJR MODEL- 3 m
FLIGHT MANUAL.
SECTION I, CERTIFICATE LIMITATIONS (CONT. )
Airspeed Limitations....................... ·.·0....0. i-yj
Never EXceed Speed........................................ 1-30
Normal Operating Speed.................................... 1-30
Gust Penetration Spccd...............................o.... 1-30
Flaps and Slats Extended Speeds........................... 1-30
Maneuvering Speed......................................... 1-31
Speed Stability Limitation.............A,<.............. 1-31
Landing Gear Operating Speeds .: ............. 1-3J-
Landing Gear EXtended Speed......... .................... -31
Landing Light Extension Speed......... ..,, ....... 1-3J_
Fuel jettison Speed..............······ ····7~,··· ····· 1-3i
Inboard Spoilers When Used for i» gitudin 'Contr01m<···· 1-32
Minimum Control Speed.............. ...................... 1-32
Mdxirnurn Speed With Windshield Anti-Fo Inope ative........ 1-32
Landing Gear Door Speed Limitation...... ..... ........... 1-32
Power Rudder Failure Limit"S"eed-.-^_z=.... .... 1-32
Instrument Color Codes /":'N·. ·....."==.::::::.... 1-33
X
Engine Instruments·· ", 1-33
Flight Instruments.. ""·. Iy··· ·· 1-33
Flap and Stabilizer rim IndicatoZsq:·"4""'""°·········· 1-33
Airspeed Instrumenti': 'X, " 1-33
Operational Lilnitations"y<"""""" '""""'""'"°"'r ······ 1U3
Takeoff Limitagj-on±.··. =' ," 1-33
Landing Limit ions..
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1-31l
Enroute Lint" ations.......... ..b......................... i-g
/
Critical Crosswind Lruitations..................................... i-g
Temperature QperatlpnaFLimits .................. 1-35
Flight Load Accele ati-o,n Minitations............................... 1-36
Horizontal Stabiliz r Settings for Takeoff......................... 1-36
Design Maneuvering Sp ed ............................ 1-37
Hydraulic Sy,stem Limita,ion.... ...................... 1-38
Speedbrak"/Aµ'Z-Ler Systeih Limitation ................ 1-38
Autopilo and>¥aw"0amp,er Limitations............................... 1-38
Windshi d HeatLilnitauoEl. .................... 1-38
Rain earing Syst Limitatibns................................... 1-3(3
Cabin Pressurization 'mitations................................... 1-39
Normal Static Pressure S tem Limitations.......................... 1-39
Failure of Pilo 's Normal Static Pressure System.......... 1-39
,,/ Fai].uEe of Cop'Iot's Normal Static Pressure System........ 1-39
,·" Electrical'System Limitations with Electric Driven Freon Units..... I-ho
blectrica1 System Limitations with Pneumatic Driven Freon Units.... 1-40
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I-ii
Oct. 20/6i Code K

CCJNVAJR MODEL. 3 m
FLIGHT MANUAL.
Certificate
Limitations
SECTION ONE
CERTIFICATE LIMITATIONS
Operation of this airplane in conformance with the Certificate
Limitations contained in Section 1 of this Provisional Airplane
Flight Manual is required by law.
TYPE OF AIRPLANE OPERATION
This airplane is provisionally certificated under the appropriate portions uf'
CAR 4b and SR-LQ2B and in accordance with the requifements of Special Civil Air
Regulation SR-425C, dated June 6, 1961. Operation is permiY.ed as follovs when
the required equipment is installed and operating:
1. Night
".,
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2. Instrument (IFR) ""-,
3. Icing Conditions . .
4. Overwater (When flares and sur-uiva1 cquijxnent as required
by CAR )lb.)4C2, kb.645 anci"H:646 are installed
and approveCt by F.A.A.)
MAXIMUM OPERATING ALTITUDE
The maximum operating altitude for this airplane is It} ,000 feet.
./
FLIGHT CREW ,/ ·
I'
A minimum flight crew consist;ing of Pilot , "Copilot and Flight Ekigineer
is required. , ""'. -
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WEIGHT LIMITATIONS , MAXIIBjM shucTURAL "'
..
This airplane must .be operated in aCcordance with the performance charts
included in Section i, " certifiCate LIMITATIONS, of this Provisional Flight
,,
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Ramp Weight. . . . . .. .. .: ·.: . . .. . .. . . . . . .. . . ,2I-f7,C'cO pounds
Take,&f "Wei9ht. . .. .. .. .. . . . . . .. . .. . . . . . ..246,200 pounds (21 Ply Tires)
" ""- -, 24ONOO pounds (22 Ply Tires)
." .' "" .. /'
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Landing Weight. . . . .: . . .: . . . . . . . . . . . . . . . . .202, 000 pounds
/'
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, ' Zero Ftie,1 'Weight. . . . . . .. .. . .. . . . . . .. . .. . .i6O, DOD pounds
.' @,TE,:, ' All beight in excess of i6O,OOO pounds must consist of fuel
.' and all 'weight in excess of 202,000 pounds must consist of
' jettisonable fuel.
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Oct. 20/6i Code K

CXJNVAIR MODEL- 3 m
FLIGHT MANUAL.
Certificate
Limitations
CENTER OF GRAVITY LIMITS
Center of gravity travel due to fuel usage, passenger movement and other items
is controlled by the Approved Mading Schedules and MEtster Equipment List,
Convair Reports ZW-3Q-29, "Weight and Balance Report for Airplane Number
(Registration Number)", and Z,M-3Q-O69, "piaster Equipment List Model 30", the
limitations of which must be used for all operations.
NOTE: Retraction of the landing gear moves the CG forward approximately 0.2 %
"""" of the M.A.C.
Y TAKEOFF PROHIBITED WITHIN
SHADED AREA.
250,000
240,000
23ojjoo
220,000
210,000
UJ
€ 200,000
O
: 190,00O
E4
S 180,000
§
g 170,000
g i6O,OOo
150,000
i40,000
130,000
120,000
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MAXIMUM TAKEOFF
GROSS WEIGHT
#6,200 pounds
"TAKEOFF IN THIS
AREA REQUIRES
i2!t PLY TIRES
MAXIMUM LANDING
GROSS WEIGHT
202,000 POUNDS
MAXIMUM ZERO FUEL
WEIGHT
160,000 POUNDS
MINIMUM GROSS
WEIGHT
125 ,000 POUNDS
110,000 "' ' I ' "'""" '""' "' ' ' """ '
1)1 16 18 20 22 24 26 28 30 32
CC - % M.A.C.
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8s6 861 866 871 876 881. 886 89i 896 901
FUSELAGE STATION - INCHES
1~2
Oct. 20/61 Code K

GCJNVAJR MODEL 3 e
FLIGHT MANUAL.
TAKEOFF CLIMB - WEIGHT LIMITS
Certificate
Limitations
REGULATION
Paragraph 4T.120("b) of SRJL22B.
One Engine Inoperative Climb Takeoff, landing gear retracted.
The second segment climb is the only veight limiting takeoff climb. See the
TAKEOFF WEIGHT LIMITS - SECOND SEGMENT CLIMB chart on the"fQ11owing page.
--.
In the takeoff configuration at the point in the takeoff flight path where the
landing gear is fully retracted, the steady gradient ot climb, withQut beiaCfit
of ground effect, shall not be less than 3.0 percent. '. ' " ' ."
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AIRPLANE CONFIGURATION '"" .., ·...
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I. Landing gear retracted. '·,., "....,
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2. Takeoff flap position (10°). "'"'""""'-·--.-.::Z,.
3. Any engine inoperative.
If. The remaining engines at takeoff power available at a height of 400 feet
above the takeoff surface. ",
5. Speed = Y2· (See PERFORMANCE INFORMATION Section 4,)"'""-.,,,
',
DETERMINATION OF MAXIMUM ALLOWABLE TAKEOFF WEIGHTS /"'
,/ ,/
I. Determine what the rnaximujµ"a11owab1e takeoff gross weight will be as dictat-
ed by the amount of available runway length from the data presented in the
ALLOWABLE TAKEOFF WEIGHT PERMITTED BY AVAILABLE RUNWAY LENGTH chart, (in
this Section). Enter t'he"curve with the amount of runway available and the
runway slope, adjust foE riinway wind coinponCnt, pressure altitude and
temperature, and read thC maximum a11owabte gross weight for takeoff under
the governing physical conditions. A numerical example of the procedure is
presented on the chart. '
,/
2. Determine whether Ute desired takeoff gross weigAit is within the climb
gradient i&its for takeoff climb', with 10° flaps and landing gear
retracted, from the takEoff WEIGHT LIMITS - SECOND SEGMENT CLIMB chart on
the following page, '-.,,
,
I' I
/
r
/'
1.-3
Oct. 20/61 Code K

CCJNVAIF? MODEL. 53 W
FLIGHT MANUAL.
Certificate
Limitations
TAKEOFF WEIGHT LIMITS
SECOND SEGMENT CLIMB
10 Degree Flaps
NOTE: Based on 3% climb gradient at 1.2 YS.
IQ
9
8
m"
E-l
E
6
C)
A
I
g 5
F-t
E-l
a 4
E
UJ
2 3
A
2
I
..
0
' ' ' '" ' ' ' ' " ' ' '" ""K '"_"""
"
: I ' : : : ' . : : W i .
' 1 ' '--" ' ' ' -', "
-- '- --I --; · '- -:--- ---:-- -'I' '-- - ---i--- -I . -- :- · -·1 - ·--1-"--1
· A : : . ' ' : : . :
, t
V · ,
_"_"T__"_ "" : '"" ' ·-· ---- --- --- '---— -·- -- . -. . ... :..-. ..... .. ' , .:_ ...:1_ ...;.. . _..J.._ .__:_-.- --.;... -...L.:.-J
i
'I 6', : i
' : : . : i : . : : '..
. ,
'" .|3> ' '
,-)- ' : ) ' ) ,
) )' )jj))a)- _:_-' , ' ' :)
, ' 1 " r?' ' , ' " 1' ' I ' I ' '" 'i -," 'D """' ; " " i"' :'".""" i' " ,,
' ) I ii, ( iX ']( , "-t , ' _ !", ' ' j:j" ")
""'" ' ' ?" - - ' ' i ' E I I
-..i--- ----i-- ; -, -- -.- 'a- " · ' '---' '" ' " I ' ' '" ' "'"' " """- Z ' -"i
. ,
t_ "a i i, i ' ) , I , : ' -E '-i
. e ' . ... .- . : .. , .' ,. ""· ... . . :.... I-..- --S? " · -· -·-1
(
i
— — - ' " ' i" CC
S'
""")""')"1 ')" ') ) " i "')' "'""""""" 't""')"""""""""'""'
) ) :----)--1 , -'i" -."' .) )y:7ij '"j;x;JgI'W-? i
·' ' '": - ···---- ---- -- ...._:-. ....:.... .. ':... .. .:. . , . . .. .. ; ... .... . . _: F-l H ....... .
:j-j4--' :"' ,),j('---i-"'"')"1)")"':j"t ")'
?!":'):'"-' :1 ''-.,:,'':'-)": " ,,!.. -')..-)'--),,,7)).,'-j).,- -')..)---""7J",,)1:J:, ,,):)):'!
·': ')" -.["" -t ' -;:"' " ; """ )"" ')N i"' '4"' 'j;)))i ..")':) ""S")'")))
--i-- ':. '":,) 'i" "",;-- p"j i "i'----- '""" "j:: "i' Y'(:-;"1' 4, ,' ,' ,, :u> ,,, ':i,
170 ]-80 ]_90 200 210 220 230
GROSS WEIGHT - 1000 POUNDS
240 250
1-4
Oct. 20/61 Code K

CXJNVAIF? MODEL- 3 m
FLIGHT MANUAL-
APPROACH CLIMB WEIGHT LIMITS
Certificate
Limitations
REGULATION
Paragraph 4T.i2O(d) of SRJL22B.
Approach: In the approach configuration corresponding with the normal all
engines operating procedure such that YS related to this configuration does not
exceed 110 percent of the YS corresponding with the relqted landing configur-
ation, the steady gradient of climb shall not be less thdn.2.1 percent for two
"
engine airplanes and not less than 2.7 percent for four engijste airplanes wi'th:
'C- '"- I'
""-.... ,.
1. The critical engine inoperative, the remai;iug"eneines"'bReratSd: at
the available takeoff thrust; '" ."' """ " >"""'
"µ
2. The weight equal to the maximum 1andingweight;v',
3. A climb speed established by the applicant in connection with normal
landing procedures, except that it shall net exceed 1.5 YS·
AIRPLANE CONFIGURATION
I. Landing gear up.
2. Flaps 36°.
3. Three engines ope ating al; takeoi'" tkjrusfµ
_.1/
1-5
Oct. 20/61 Code K

Certificate
Limitations
CCJNVAJR MODEL- 3 m
FLIGHT MANUAL. '
APPROACH CLIMB WEIGHT LIMITS
Three Engines Operatine
Gear Up - 36° Flaps
LO
9
8
'7
t
8
A
i
a
g
E
R-i
b
5
h
3
I)
"""y:"
].40
':; 'i' X -'1' |1'! ""' 'I '!"| I'! !"" i"' "l'"i 'i:i"!' :i!:l!" "' :':!:|!!'!
· . K
, . . . , , . . . . , . . . .. , .. . .
. .., . .. .
i A ' 7 ;
I .
, . '. " : I ' .:
I
0
"r
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t
::1"' :: ,: , , , 1 "t,,, , "X i
'.i" ' :"· , I " . ' i ! "": ,,
. . i ·
-._.,, , _ , ._-- ,.--. .. : I '-i, .'
1 ' ,n , )
. i . . . . . . ..... . . . . .
. i. .: ¶ ": " ""' ' , . ' ,?,, , , i ! ' g"-j
'"""") '"' )-,)') ' ))")"' ")) '_) _ " ': '"":))
.... i.,,...|"1-^! , i Y , , . .:"·,,.: ", i·. qz'
' ' 1 i?4 ' ,i ' " i K' ej" """"j i i:=
'i': ! : . i .% : "·
. I . ' " :.. ' ' "' A "- " I
' k ' i . ?"3 .. . . _. . . . . i L, · ' ' ' : ; ~ : t
|.i·1a ,..,. ? ', ,':). : , ' N"t
¶ · ·- - + . - t t . I : -- . ·1 . L . - .- . . , - . . . , , . .. . . -
"' " ") j: )i..)),)::"j ,:- :"':', ' )lj),)
'":, ','"i"i.j.'""'l )'1' --, l)""--) ) '1') '.)" ,"'l'j
' I " ' . .: , ,.'1. '. .'..'. . '.' cl' ' : ...i . , ' i. .. .i . ' "
' F-l ··- ·-'1
.....".,"".:":4,),):))::l'")') )).- ':')l)'"'))'j' i (lj
"i' ,"i,,' ' 'i-' "'" -. - ·' "
,
» i ' ! "I " "' . "!: " !, I
' !" " ' ' ,"'- i "C' "' " ""' ""3e""' 3 i " E' '
: '., '. i i ' I · " : .: . '.'I:::: ' ' :. :1
-"i'""i'"':j ": .. -- ; ' - '- -· ·' ' · - - : ::. : ::!.'iii i:,.'. . ,i::'-:-- ..: i.> -!if.---
I : " - i I : . . . . . . . ., . , .. . . .i . .
·):'--.',L--.-.i-)-,-..-.-"i: ",'---.·-).' -.'('')(I):J
. i .I... . ......... ....:' ': i:.:::... ... ' ' .. ... . ....I. :::1:.- ._. ,..-. _..-.....
:"."'"")""'"' )' ' ") "' "Nj '""'N,_'),): '
i i : i ) ' '! !" "" ' !" "' 'i"
L50 i60 1"(0 IBO IBO
GROSS WEIGHT - 1-000 POUNDS
200 210
I-O
Oct. 20/61 Code K

CCJNVAIR MODEL- 3 m
FLIGHT MANUAL.
Certificate
Limitations
ALLOWABLE TAKEOFF WEIGHT PERMITIED BY AVAILABLE RUNWAY LENGTH
REGULATION
Paragraph 4T.123 (3)·
Accelerate-Stop Distance, Takeoff Distance
The minimum distances required for takeoff shall be estabjished at which com-
pliance is shown with the generally applicable provisions "of, this regulation and
".
.
with paragraphs 4T.115 and JtT.LL7(a) · '"i";-- '", ,/
r'
I
' '
. ' ..
/'
P
.
Paragraph IT .115 . ' "" 7- . .. ,·
. ., .
.. ,
Accelerate-Stop Distance
(a) The accelerate-stop distance shall be the sum of the fcjl1uyiing:
(I) The distance required
start to the speed YI.
(2) Assuming the critical
required to bring the
ponding with the speed
"-—~._..
to acce1 .r te the airplane from a standing
enginjto faii""'at the speed YI , the distance
airpj/ane to a full smp from the point corres-
YI · "---.
", "·-.
Paragraph 4T.ll7(a)· ,)
1/
I
t
The takeoff distance shall be the greater cjf the.dij'fances established in
accordance with subparagraphs (I) and (2)· "
(I) The horizontal distance along the takeoff path from the start of the
takeoff to the phint where the airplane attains a height of 35 feet
above the takeoff surface, (one engine assumed to fail at Y1)·
(2) A distance equal to 115 percent of the horizontal distance along the
takeoff path with all engines operating from the start of takeoff to
the point where the airplane attains a height of 35 feet above the
takeoff surface.
Airplane Configuration
1. Accelerate-stop distance:
a(. From brake release to Vj speed
/"^
' " (I").. Takeoff thrust on four engines
(2) U'keoff flap position (10°)
b. Fran YI speed to stop
' (I) Idle power on three engines, one engine inoperative.
1-7
Oct. 20/61 Code K

CDNJVAIR MODEL- 3 e
FLIGHT MANUAL
Certificate
Limitations
(2) Wing spoilers fully extended.
(3) Maximum braking. (Anti-skid operating)
2. Takeoff distance
a. Engine failure at YI
(I) Takeoff thrust on four engines to Vj speed. At YI speeCi one out-
board engine becomes inoperative and remains""-qo throughout the re-
maining takeoff distance. "'
(2) Takeoff flap position (j-cf ) · t-...
(3 ) Lan:ing gear r;traction initiated after 1 rt"a£f °): , ,/
b. ALI engines operating " ~~
..
(I) Me same configuration as for the engine ,ailur"e, at YI case above
except that all engines are assumed to be bperattu,g at takeoff
thrust throughout the takeoff d·i,sta,nce . x. '
" . "---- ',
..
r' '"..' ". "~~b.
Procedure s ..""" '" .,. ""-,,
C
r . X
,·' "- . "
""
I
The accelerate-stop and takeoff proc:Cdures are de'scr"±ked on page
"' , ,, ',
A Chart of the ALLOWABLE TAKEOFF j/EIGKT PERMITTED BY XVR"LABIE RUNWAY LENGTH is
presented on the following pagg""'"" An exanipje of the us . of the chart is pre-
sented below and the soIution/tor the example. is ind" ated on the chart.
I'
'K,.
X,,
'X
Example : " ',
Field 1engtlr, ""'E ., 80'0q. fe'et
Runway slope '·g ""I%, upiii11 ·"
Wind Component ' = 1'C)'..knots heaANind
Ambient Temperature =' · 80 degi€es F
Pres sui'e-·--a1titude ""t 2000- feet
/""">,, """ -.,
The maximum allowable gross Weight'. under the above conditions is 190,050 pounds
at the start of takeoff , based upon- optimum f ield length.
(
I) '"<: ""'""" ",r
""%
%
%
"
1-8
Oct. 20/61 Code K

UPHILL 2 5
RUNWAY 0 t
SLOPE - %
DOWNHILL 2
60
HEADWIND .
40
WIND
KNOTS 20 "
TAILWIND 0 '
10 "
6
A ,'A I" A i3, :' p" " "' - " '· " " :' "'L"" .- ,.UU,, r' '" G""
. .,
, 4
. .
':;)t:):,')iI2w
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: t. .. .
i ! : - ; - ' - ' -- ; ' - ' "-- ' ---
,
I :' ::: 1 :.': :' "" ' "" : . : ; V" ' ' "' ' : : : .
.... . .., ,
'"t""_:')'z'gjjll/
"'-;d^·'-"" -··" ' " ·"" ~ ':-__ " · ,~
j ! , ' :
" ---.J.... ...-:.... .- -.---- - . .-. - ·- -i. -. . L. . ....- .. . - . - :
" ::-· : '-'-I
! ' '""
""::::!::!i!:: :-i ' "!""""""'" ""! ' ' ' ' " ' ":"
,!: :;j' : j,i!:,,, ::
' , I, ) ' 1 !
... ij: i!:' !;"t ,.,,
j: j,,;i !"i':!!' !' i, ' i i ' ' ,. I"" "" : "" " i ' " ' · - !
11,j:::::::,F.,,,:::):::, ,,; ,,i.,. ,,..,I, : : ,. ' , :
zi)'. |ii' '-i :ii|' .:i! ! '
I
Z I i ' I G 'I °F
,:.::::; ;: ' :::: ::.': " " "'"' ' ' " "' ',,cS?°' " "' ' ·" '"'"' """ " ""
:'iij:::: .: :::: :::'1'.·' ' d ·"8"".+, , ,' ' i I
"")"'"""" "i"" ", ' ' -t9 :>;I
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,;::· :j"" ,. . . . . . . I . : i
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i ., .,,,!jj, ...!,... I -.·- --yCLdZ:i =::"
—-· --- —
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:/yCi<1 ---= . - ::
:"' i' " I ' ' "' ' ' ' "
' '>"' -Z
1?qi:: " ) ' ' i ' ' ' ' ' '>

CCJNVAIR MODEL- 3 e
FLIGHT MANUAL.
Certificate
Information
14
ALLOWABLE TAKEOFF WEIGHT PERMITTED
BY AVAILABLE RUNWAY LENGTH
Nose and Main Wheel Brakes Operative
~
K,d ·..- . . ,-..! ..|,,1 .. ,.'·¶1· ==m r-·j-·--· ·--0
i '";"' '" !i' ..,~=::::1.-. ....I , .t.:: LO DEGREE TAKEOFF
, , , .:':.'::: ::::::. ::::1:."" ""' "'
---·F·.· · -.t..:- -:.::
"Km i i "",' "Z:.-,!e!, "= ,, iiiiii ':ii:i:,' Anti-Skid Qperat
0 t
--·- - . ' :" ..I... .' ..:::::: " '::::.
~1 '
. , ' . :: :j:::: ::-: t '::2 :'::::::: ::-- i -:::
, ., ,, , . , . , ., , ,., . , , . . .
: i I : : :::.1 ::: :::.,.... ...., ... ....... . '"" ""'" "" ""' . _ r :": "' ":" "" " ' ':1""" :?" ° "" ""°" '"" "'
:
: i .
I
. .
. .,..i.... ::::1::' ::::1:. . :::::::: :::: - .-·. · dTp +?." · ·-P t—o r+·-·+P P.. rl !00~--F—" —-·— T···· bO"
po K ~r P
·· · ·P·- · -· ·· · -· ·· ··' ··- - ·' ·- -· ·· - ' ··- -T·· - ··+ --··- ·· ·· -·"- ·-r· ·~:E:—H—-+~"· -·"— -·· +°" " ..TA "= ""
· · I ' . . - , ... .. ...,... . . .. .... ... ·.... .,,.. ,. ,.
t E.jk , ,|,—1,-—·©
~ rr· p ·— ·
¥ '___ g ^""' ,<" i ,ar:.'!:!!! '"ii!::' "j;;;; z::ii::: - ·!i:ii ,=,-.1. --r "-'=""=; ='""""" " "Z Its :..' j"?. . " ;:t:
i - - ·· · - · · - · p · . -· . - - · - - · · ? · · - · - - · - - · - ··p —· —.· r- ·4—^w —·— — "t" " m "'"' " ~0 """ w
i : ' ' ' '::. ::: : '. ' : :: ':..1: : :j i : 'i : ": :: ;i: : . :j i : u==-.-~ 0 — #_ . P. °==== "m t = =i· "lj °"
a ' ' ' i
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i L ,, "
"" r° ' """~4-?+t r · · · · q-p
· '"-' ·- ·-· ·' · :: ::' ···· :::: . ' ::::1:::: :,t· -E"====4:-,,_:+.; ';!Dk-u£m,!- -I , . ,= .J., I! }
-eU %':7iii,! ",1ii:i' i"iE:. "ii!ii:: ,iiii,i,) "=·==t,'1-'L'".:E¥::E,a': ,t £,l e .""
. V . . . · · . . . - . . - . . . . . . . . . . . .. .. .· . . I I -p P 0. · +
7!,e"a M r-M ^>" ;:iii ' :···: . :·::: :-:-:""' " ''"" ·'-·'-" """' """ X "'"""'=" ·-· -" '"·· "" "'· '7·' ' , P
°1,> j «~^' ^ ii!'i ';; i'|.i: :; ii, i "' ::"i-'ii ::: I' "' 'Qr:::i==
=:I=;,i 'I". =;a;";;% -.-1—'· i!!' '- I! '= " 'A " '
' ' ' ' ' ' - ' ' ' ' ' ' ' ' - ' ' ' · ' ' · ' · ' · · - · · X · · · · ' " ' " ' ' ' ' " ' ' ' M ' ' " ' - k·
· · · · ·- · · · · · - · · - · - · · · · · ' · · · · · · · - ' · · · · " P - · · · - -' t ' ' ' m" :" -- - · t ^.' - ·- '
· ··· · "t - '
'.,
_.,,
... , ~=¥= .. i i "i. i' i ! i. I' "I . .-:-!_L_ !E4X 2KEOFF GROSS "'"~-"" '
' ' i i i : '!' '! i i I , j" WEIGHT = 246 ,200 i i'"!: ii:,:
i ! i i i i ' ' ' ' ' ' ." . POUNDS-, ', '; _ 'iii
. ,
i I ' i : . . : i : ' · ' i i t "i. '"'-: , .'. "' :
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: I ' : · I , :"' ' " ' ,,SJQ ,? , ,'" -
) ) i '" ) " ) ""' ' ! :--- ·--·1---" ,-) "" ":'{9 """ 3z"'"<2:"": ""'"")4rigo '::
1 ! !
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:>)....)"'..' , JijiZ"It!t)I).))l,;;)'
>> ' ' }®g"jjyY 'i k '"!', " ' '!,!::i '!" 'x,'in:: ;j i "" i>i :Ej 'i::""::'S» jiS '
T"" 1 ' ) ' "":<> "i"" "t: >" t" "" ' :'jX:;:) :"' )Filit i::i i:::" ':,: "-'"I' -.m'"-
P · - - - · · · · - · · - -· .- - - · - - · - - · · · · » J~ ·· · · - · . .. . .. . , 0 —~ I!
' I "" a' ' ";W i' ' "' "' '-": msu i "i:ii'"; !:!, iii, :;; ,:;: '=- ' ="I.l I ' I ·1
' ' " " ' ' ' ' " "' ' ' ' 'I ' " " ' " " ' " "' ' ' ' "" '" ' ' "
, n,i)i"j:3|<, ,,,7>iti>|:;':i>Itii2))::ii",;E:;,,:,.::,:i,:;'
""" " '""" " iX^'¢j<i '- 'iK ' :iE::i :"' : :i:: '": :.:: ii:' i!!! i!i'ZZ ~:: ·zi £ Z:'"" = Z':
.:: : .= Ye::" := LL.1 '"" m"" ""' -'" ' . ' . ' ..' 7It |1. ,·1
.. · +· ·
~. µ.- . + '= . · , ,-- . t
"TK"Tmw , "aa sW . _ ~ — *
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: :. t , . .,. ii m , h ' ,+4 ·+·' ·· · t-
. J t . t · , . t" "
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. " "" :" ";:.' « "'i ' '" -Er t! .Lit" .ELI ..t!i .... . : 't:: === .:Tt :::1 "::t
: :' ..T" =· , . +4-j "
,
: ij= ' +t-··U ' ' ' a-· -·:- - ·-" ".'- :r -' """
' " " ' Tl I ""T "" i ¶i. !::' ::' ° """" """
""" :" .. "" , - ~m· , " ' -r ' t? 1,1' i!: !i'f ,,,, ...0 — ""' '::' ':tt ,o..; ..:: :::i "?-1 .=
' ' ' '" " "" .t: jrm .. ·" p a =¶ · ' " +H "t;, t"'" ""'° "" "'
· ~ ~ " 4+' . · · + H ii ? ' . " "':" T:"' """" ' i'
~~ i · ·.. ·& ' t Ir ' · -4 ·rr. ·-· - · —a - t
. : : · : :: : . ' ::: ·- ~ ' . St7 .= . , Ah :1" ., .,, 'it ii: '.if-'i"~ ju" ·?z-=:' jn' '."' '"" "" "" '"t ·
"" ' " "' " .I ' i "" "cp' I I I . ' , , ,, . . , ,, . _., ,.
-b -r· .H · ~ ·¶ ' " " " ' : t r' "" ' ' " ~ , "' ' " ""' m-"
""" " "- ;u :µ " "= ·¥· ?4 : ¥
, · . "ifj" ,..,. . , .. ,
e^< . j:'"'",":j'""'j" :'i"i'4 Z,fji 's 'i! ?' " ' """zEt .=' 'e. ijf ,!e ::;i;:!;; ;;;?!Ei :!i, € ""
K,wa"e'e a' ' i-' "" " ' " 'ZIt .. T '"" m "' a' ' ' ' " "" " '·· F'"^r· -' l'"i 'I-" E'"iiZ '"i ;',2 "2! ..;.r j?^
' ' '. . . ' " -·. :!; 1 ? 1¶ ¶t· ·
,. m. ,1j I != ,,., ,.,, ,... ,.. =- ..., 04-.
.?
. _: ' ' '" ' · t ; ' · ·- 't;;"tin "': 'P, ..,, ., . b.+ ..-. ..,. ..,. =. ::1.
. -b &., +, b · ' t ·:r.1 T q — k~
. ' ' , ' , b . .
, " ' '", _ 0 ;"1- l"li "' ,,'ii','"?, [-'j'i' ',S, e', .h iji. 12 ;.' .·l'= 7::lziEia lm·"ii'-"" .. .t : "".· ". ...r:. ,,
13 15
FLAPS
ive
/
,/'
,.
~"~
'Sq 160 170 IBO . 19O 200 210 220
GROSS WEIGHT AT START OF TAKEOFF - LOCK) POUNDS
230 240
1-9
Oct. 20/6i Code K

CCJNVAIR MODEL 3 e
FLIGHT MANUAL
Certificate
Liinitat ions
POWER PLANT LIMITATIONS
This airplane is equipped with four General Electric CJ 805-23 Aft Fan Turbojet
engines. A thrust reverser mechanism is installed on each engine.
The power setting charts included in Section 1, CERTIFICATE LIMITATIONS, of
this Flight Manual were used to determine airplane performance as noted in
Section 4, PERFORMANCE INFORMATION. Engine manufacturers warranty limits for
climb and cruise operations, which are not specific F. A. limitations, are
included in Section 9, POWER PLANT, of the Airplane Opera ion Manual.
" /
,
4"~. , /
Operating Limits ',,"--,, "-, /'
" ""~. " /
r'
7,,, ·-, ,/'
The engine and fan RPM limits, and EGT and =R,lmits,'&,re,,/shoW-A,2M charts
on the following pages.
I!ote.: The climb performance data presented in Section 4, PERFORMANCE
INFORMATION, is based on the EPR cyrves in this Sectiort. Thrust is set
by EPR, not a fixed RPM. Therefore,,""i-t. will 'be necessary to make
periodic adjustments during cI' b."The""EGT limit at maximum continuous
power is 59O°C. If necessaryjthe powCr lever should be retarded to
keep within this limit and njaintenance personnel should be notified so
that corrective action can b"e, initiated.
K
'r '... %,
%
Airplane takeoff is prohibited Mhen"'"the""EPR or FAN REM for takeoff is below
the minimum required. ,/
I
/
Engine Starters """'""'
b.
"%.
The use of engine startq;"; in Elight is prohibited.
Fuel Type s
The engine may be""op,erated on Commercial jet Fuel, JP-4 or JP-5 (per G.E.
Specification M51JT96S")>"The engiµe viii operate satisfactorily with any one of
the above fuels or a mixture thereof; no fuel control adjustment is required
for these different fuels.
Oil Types
The engine is to be operated with MIL-L-7808C oil. Intermixing of oils pro-
duced"by different vendors f6' not permitted.
,.
Engine Thrust Reverser Limitations
"The use of the thrust reversers in flight is prohibited.
..!Mrust reversers can be operated at not to exceed 95·% engine RFM until a
decrease in airplane speed to 60 knots IAS. Below 60 knots IAS, power setting
must".be reduced to IDLE reverse. Thrust reverser use on landing roll-out
should be ceased after 30 seconds of continuous operation.
l-lO
Oct. 20/6i Code K

CCJNVAJR MODEL. 3 W Certificate
Limitat ions
FLIGHT MANUAL.
Thrust Reverser Limitations (Cont. )
Do not exceed 99.4% REM fan operation or an EGT of 63O°C at 95·5% engine REM
during thrust reverser use.
!!OTE,: Operation as noted above will prevent severe compressor stalls.
Engine Anti-lee System Limitations
Engine anti-icing may be operated continuously at any powe"r setting when the
compressor inlet temperature is below 15°C. Do not qperate thq engine anti4ice
system when the compressor inlet temperature is abov'e"t5°c. ""'-.. "
,/'
'·, ,/ ' .. ,"
NOTE: For ground checking, or when a malfunctioning anti-i'Ce valve i-s,'
suspected, the engine may be operated with" a compressor inlet temper-
ature above 15°C for a period of five minutes at any power setting,
including takeoff, and for 20 minutes at IDLE power.
Engine Bleed Air Limits
To avoid exceeding maxijmuin allowable
systems are operating, the fo11owing
cases, engine anti-icing must be OFF
//. _. ~:;;
I
I
'Cngine b Etcd air limits when anti-icing
minimums shall be observed: (In all
,on inoperative engine s . )
t
I. During four engine operation, do not operate engiYes below 75 percent
REM between 10,000 and 22,500 feet· /"'
2. During three engine operation do not operat.e"engines:
a. At less than 66 percent rem below io,oo0 feet.
I). Below 77 percen' RJM between 10,000 anci 22J500 feet.
3. During two engine operation clo not operate engines:
a. At less than 73 percent REM below 10,000 feet.
b. Below 79 _pCrecnt REM between 10,000 and 22f500 feet.
c. Between go" and 95 percent REM (inclusive) from 20,000 to 22,5OO feet
except in transient conditions.
(
/' ") "--q,..........,.,,
,
..
<,%,
l-ll
Oct. aj/6t Code K

Certificate
Limitations
0
CCJNVAJR MODEL- 3 e
FLIGHT MANUAL.
EXHAUST GAS TEMPERATURE LIMITS
ENGINE STARTING
CJ 805-23
AN EGT IN THIS AREA INDICATES
ABNORMAL STARTING CONDITIONS AND
SHOULD BE INVESTIGATED. REFER TO
MAINTENANCE MANUAL FOR TROUBLE
SHOOTING INSTRUCTIONS.
IF CURVE LIMITS ARE EXCEEDED,
REFER TO MAINTENANCE MANUAL.
—820
79C'
—76o
" )//))))),),))=)I)
k
"" I I
.
"° - " " " I ' "TEI ,
" - ,. __ ENGINE SERVICEABIE AREA
610 · I , I i I ";1 I ! ' I I , ! , , i"' ' , ' , "
0 lo 20 30 40 50 60
TIME IN SECONDS
0
' : J-i $'- , '"" r"|""m' jl ' ' '.i " 'I-—
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1-12
Oct. 20/61 Code K

GCJNVAJA MODEL- 3 m
FLIGHT MANUAL-
Certificate
Limitations
EXHAUST GAS TAERATURE LIMITS
ALLOWABLE TRANSIENT EGT FOR TAKEOFF
CJ 805-23
IF CURVE LIMITS ARE EXCEEDED,
REFER TO MAINTENANCE MANUAL.
66o
650
640
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" """"' ) "! 59O°C MAX. CONT'INUCfjS LIMIT :il"!:!, !: :1 Z 7' {'i,/ '
· . · . . · p · .. . . k . . . ' · f · · · · - - - . . . . i -. . . . . . . . . ... - ..: . .
,. ,
630
620
610
S 60C
m
59Q
580
0 1 2 3 Lp 5 6
PERMISSIBLE DURATION OF EGT
MAXIMUMS - MINUTES
NOTE: 'Mis time scale does not
time sequence dim-ing the
For exampie, a 650 deeree
2 minutes t a period 30
initiating t keoff.
represent the chronological
takeoff run and flight path.
temperature might occur for
to 45 seconds after
1-13
Oct. 20/61 Code K

CI
Cl
d-
0
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otes:'KEER must
/ / s tire and
a€iigher
not be less than value indicated for appropriate ambient pres-
temperature prior to brake release. Increase power setting to
EFR level only if required to raise fan speed to minimum level.
2. If windshield rain clearing is in use , shut down one turbocompressor
and, c'itli umatic driven Freon packs, one Freon pack. If rain
clearing. ' s n required, both turbocompressors and Freon packs
can "de an .
t
2.00
1.,.'5
ZMGINE
PRESSURE
RATIO
(EPR)
L. X)
1.85
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NOTE: I. Fan speed must be equal to or above
'the minimum value shown for the
" 'a p opriate ambient conditions, (but
/ '/' "'~j,1/ "low e maximum fan speed limit ),
/' when the inimum EPR value is
,' obtained
94 A4LF4Lm4+~t,-.1444 Ui.i .1.1 ,J4 G>. -L-.i , S- . .L L_j:
,
2. If fan speed is below the minimum
when EPR minimum is obtained,
increase power setting until the
fan speed is at minimum.
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CCJNVAIR MODEL- 3 m
FLIGHT MANUAL.
Certificate
Limitations
ENGINE ROTOR SPEED LIMIT
CJ go5-23 Turbojet Engine
NOTE: Maximum allowable fan speed is 99.%
lob
103
ICE
IQ]
F LDC
F" 9S
L)
M
E 9E
K
B 97
a 9E
g
S 95
9'1
91
92
( 91 "i"" "' " " : ::: : :::: : :: ::;: ::::j;' ' :2:: :::: ::;; :::; :::: :::: :::: :::: ::::
,,' "" "60 -bo -20 0 20 40 60
,, OUTSIDE AIR TEMPERATURE IN DEGREES CENTIGRADE
1'/
/
< NOTE: Physical rotor speed is determined by power lever setting.
g - · · - - · - - · k··- - ·· --~ '
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,? TARGET EPR. INCREASE POWER SETTING TO HIGHER
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oct. 2cj6i- Code K

CXJNVAIR MODEL. 3 W
FLIGHT MANUAL.
CIT CONVERSION
Stat ic Air Temperature (SAT )
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Limitations
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1-19
Oct. 20/61 Code K

CCJNVAJR MODEL- 3 m
FLIGHT MANUAL.
CIT CONVERSION
Ram Air Temperature - RAT
Certificate
Limitations
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1-20
Oct. 20/6i Code K

CCJNVAJR MODEL. 3 m
FLIGHT MANUAL.
Certificate
Limitations
FUEL SYSTEM LIMITATIONS
Fuel in the Convair 990, Model 30, airplane is carried in four wing tank systems
(two inboard and two outboard) and a five bay center section auxiliary system.
The outboard wing systems consist of main, replenish and anti-shock body tanks.
The inboard wing system consists of a large tank located between the front spar
and the rear spar with a free flow of fuel through the center spar, and an anti-
shock body tank. When reference is made to inboard replenish tanks, reference
is intended to that portion of the inboard tank 1ocatedretween the front spar
and the center spar. """
Fuel Temperature Limits ,:""-·-
At the engine fuel control inlet.................0°C t:'"±7l;n3"2-.?^ 59-8°F)
" V """--..
fOTE,: If the engine fuel control inlet temperature . es ijciQw 0°C, the fuel
temperature should be monitored. An increase in""engine'RPM to maintain
minimum temperature may be required.r,---._.__.,, "" '·,
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At the fuel tank......................j("":'"",.."""">ZO°C to "S4°C"'"'("LO°F to 12$L2°F)
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fOTE: At ambient temperatures be1owiEL°C and a1t"±tjudes below 15,000 feet,
engine RPM must be 70%, or greater, or the fiie1 control inlet temperature
must be monitored and maintaMjd"'q,bove 0°C. "
/'1""'" """ '""%
" "
....
Fuel jettison Limitations /' ""...,..,,.:.,.,,,....
,,,,
Fuel jettison must be accomplished in such. a manlier as to stay within the
requirements of the Takeoff and Landing Fuel Distribution Limits and the
Inflight Asymmetric Fuel Distribution Limits ihcluded in Section I, CERTIFICATE
LIMITATIONS, of this Flight Manual.
Boost and Transfer Pump Limitations
Single Boost Pump Failure: Po.tcf reduction may be required for climb above
26,000 feet if a seCond pujup faits.
Failure of Ihboard Main or.Outboard"Tank Transfer Pumps:
1. With a fuel quantity of""3QOO pounds or more per tank (6000 pounds or
mgte total airplane) no action is required.
2. With less 'bhan".6000 pouudds (total airplane) or less than 1500 pounds in
'the tank having d"n. ino,p'erative transfer pump, crossfeed the affected
"engine to,.'f'ne-adjac"ent tank on the same side. Do not shut off the
affe,cte&'tank 1ihe.valve.
Failure of Anti-Shock Body Tank Transfer Pumps:
Maintain.,·extra fuC'l.in the inboard tanks to balance any fuel trapped in any
ASB tank. The difference between the inboard and outboard tanks (main and
replenish) should be double the quantity trapped in the anti-shock bodies.
0bserve·q.peed restrictions if applicable.
1-21
Oct. 20/61 Code K

CXJNVAIR MODEL- 3 m Cert ifi cate
Limitat ions
FLIGHT MANUAL.
Fuel Loading Liruitations
FOR AIRPLANE SERIAL NUMBERS: -I, -2, -3, -L -9, -10, -16, -18. -21, -22, -23,
-24, -26, -27, -31, -32, -43, -44, -45, -49, -So, -51, -52, -sh, -55
WING TANKS ONLY U.S. GALLONS POUNDS
Mdximum refuel quantity
Usable fuel quantity
10,890 76,230
10,791 . 75,537
Note that the limiting value, regardless of fuel de.psity, temperature or type,
is 10,890 U.S. Gallons or 76,230 pounds, whichever occurs first in loading.
CENTER SECTION TANK
U.S. GALLONS POUNDS
Maximum refuel quantity 3,125 ""--, '"21,875
Usable fuel quantity 3,113
_
"'""..,, m791
'
",, —^.
Note that the limiting value, regardless of fuel density, temperature or type,
is 3,125 U.S. Gallons or 21,875 poimCls, whichever occurs first in loading.
"
, "'·,
INBOARD ANTI-SHOCK BODIES U. S. GALLONS "., POUNDS
Maximum refuel- quantity / 708 ,"' 4,956
Usable fuel quantity . , 7Q5 . . , 4,935
,
I ".
.... ..
.
Note that the limiting value ,, regargiess otY,ue1 density, temperature or type ,
is 708 U.S. Gallons or 4, 956 i;bund·g , whichever occurs first in loading.
f'
OUTBOARD ANTI-SHOCK BODIES
'"·-. "U.S': GALLONS POUNDS
Maximum refuel.quantity
Usable fuel quantity r
- ,
436 3,052
432 3,024
Note that the limiting value, regardless of fuel density, temperature or type,
is 436 U.S. Gallons or 3,0fi2 P?unds, whichever occurs first in loading.
I
OBSERVE SPEED RESTRICTIXJ'NS WHEN CARRYING OUTBOARD ANTI-SHOCK BODY FUEL
The total maximum refuel quantity for these serial numbered airplanes is
15,159 u.s. 'Gallons or 106,113 pounds, whichever occurs first in loading.
1-22
Oct. 20/61 Code K

CCJNVAJR MODEL- 3 m
FLIGHT MANUAL.
Certificate
Liinitat ions
Fuel Loading Limitations (Cont· )
FOR AIRPLANE SERIAL NUMBERS: -5, -6, -7, -8, -11, -12, -i4, -i6, -17
WING TANKS ONLY U.S. GALLONS POUNDS
Maximum refuel quantity 10,890 76,230
Usable fuel quantity 10,791 75,537
Note that the limiting value, regardless of fuel densitj'",.,temperature or type,
is iO,890 U.S. Gallons or 76,230 pounds, whichever occurs'""first in loading,,
X
T-. "- /
·
b., X
CENTER SECTION TANK
I
'"""-.. " ", .I
U.S. GALLONS "". ·'""""--PQUN!BS . "
. ' -- ."
Maximum refuel quantity
Usable fuel quantity
3JL25 21,875
3,113 21,791
Note that the limiting value, regardless of fuel density, temperature or type,
is 3,125 U.S. Gallons or 21,875 pounds, whichever occurs first in loading,
INBOARD ANTI-SHOCK BODIES U.S. GALLONS POUNDS
Mdximum refuel quantity
Usable fuel quantity
708 4,956
705 ./ 4,935
/
Note that the limiting value, re{"ardless of fue't--density, temperature or type,
is 708 U.S. Gallons or 4,956 pounds , whichever"·occurs first in loading.
K
%
OUTBOARD ANTI-SHOCK EKJDIES U.S. GALLONS POUNDS
Mbtximum refuel quantity
Usable fuel quantity""""
938 6,%6
934 6,538
Note that the 1inlitine value, regardless of fuel density, temperature or type,
is 938 U.S. Gallons or 6,S66 pounds, whichever occurs first in loading.
OBSERVE SPEED RESTRICTIONS WHEN CARRYING OUTBOARD ANTI-SHOCK BODY FUEL
The total maximum refuel quantity for these serial numbered airplanes is
iS,66i TJ.S. Gallons or 109,627 pounds, whichever occurs first in loading.
, "xI
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1-23
Oct. 2O/6i Code K

CCJNVAIR MODEL- 3 m
FLIGHT MANUAL
Certificate
Limitations
Fuel Loading Limitat ions (Cont · )
FOR AIRPLANE SERIAL NUMBERS: -13, -19, -20
WING TANKS ONLY U.S. GALLONS POUNDS
b4aximtun refuel quantity i0,890 76,230
Usable fuel quantity 10,791 75,537
Note that the limiting value, regardless of fuel densitj, temperature or type,
is 10,890 U.S. Gallons or 76,23O pounds, whichever,occurs first in loading.
CENTER SECTION TANK
Mdximum refuel quantity
Usable fuel quantity
U.S. GALLONS POUNDS
,
3,170 '" 22,197
3,158 22,i06
Note that the limiting value, regardless of fuel ciensity, temperature or type,
is 3,170 U.S. Gallons or 22,197 pounds, whichever occurs first in loading.
INBOARD ANTI-SHOCK BODIES U.S. GALLONS POUNDS
Nxiinum refuel quantity
Usable fuel quantity
708 4,956
/ 705 4,935
Note that the limiting value, reeardless of Euel density, temperature or type,
is 708 U.S. Gallons or 4,956 pounds, whichever occurs first in loading.
OUTBOARD ANTI-SHOCK BODIES U.S. GALLONS POUNDS
Mbiximum refuel qumtity
Usable fuel quantity
938 6,566
934 6,538
Note that the limiting value, regardless of fuel density, temperature or type,
is 938 U.S. Gallons or 6,566 pounds, whichever occurs first in loading.
OBSERVE SPEED RESTRICTIONS WHEN CARRYING OUTBOARD ANTI-SHOCK BODY FUEL
The total maximum refuel quantity for these serial numbered airplanes is
15J06 u.s. Gallons or 109,949 pounds, "whichever occurs first in loading.
1-24
Oct. 20/61 Code K

GCJNVAIR MODEL- 3 m
FLIGHT MANUAL.
Certificate
Limitations
Fuel- System Operation Limitations
LOADING OF FUEL IN THE ANTI-SHOCK BODIES IS PROHIBITED. ALL INFORMA-
TION IN THIS FLIGHT MANUAL REGARDING ASB FUEL MANAGEMENT AND LOADING
I
IS TO BE DISREGARDED.
'I": rice: i':' must be made tank to engine 'without utilizing crossfeed systems. Ob-
. e- - .(- outboard ASB speed restrictions.
C. G. L i'"itations with Trapped Center Section Fuel
[.:' bot '-i center section tank boost/jettison pumps ar" "noperat e one of t
:'c.' Iowi ug two conditions must be met to insure that t e ' lane ' s with
;"ro;:e r CG limits.
I. With any amount of trapped center sec on fue the takeoff CG must
be aft of 24% M.A.C., or, if not aft or "21L%;
2. The total outboard fuel must bS ,at Least. 1000 pounds greater than
total inboard fuel plus the'" ceqtl:"eE.,section Fuel--at time of landing.
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'K
l~2f'
Nov. 3/6i Code K

CCJNVAIR MODEL- 3 m
FLIGHT MANUAL.
Certificate
Limitations
Fuel Balance Limitations
The fuel balance limitations for loading and all flight operations are
controlled by the loading and fuel usage procedures in the Weight and Balance
Report, the limitations and conditions of which must be observed at all times.
Inflight Asymmetric Fuel Distribution Limits
Inflight asymmetric fuel distribution limits must not exceed 150,000 foot
pounds, refer to Section 2, EMERGENCY PROCEDURES, for determination of values.
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1-26
Oct. 20/61 Code K