1?

eechcraft:
KING AIR F90
MAINTENANCE MANUAL
CHAPTER 57 - WINGS

LIST OF PAGE EFFECTIVITY

CHAPTER-SECTiON-SUBJECT PAGE DATE

57-Effectivity Dec 21/95

57-Contents
Dec 21/95
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 'l)eechcraft
KING AIR F90
MAINTENANCE MANUAL
CHAPTER 57 - WINGS

TABLE OF CONTENTS

SUBJECT PAGE

57-00-00
Wings· Description and Operation (Effectivity: All) 1
Wing Center Section (Effectivity: All) 1
Attach Fittings (Effectivity: All) 1
Wings· Maintenance Practices (Effectivity: All) 1
Wing Removal (Effectivity: LA-2 thru LA-225 without BEECHCRAFT Wing Spar Bridge Kit No.
90-4090-1 or 90-4090-3 installed; LA-226 and after) 1
Wing Installation (Effectivity: LA-2 thru LA-225 without BEECHCRAFT Wing Spar Bridge Kit No.
90-4090-1 or 90-4090-3 installed; LA-226 and after) 3
Wing Removal (Effectivity: LA-2 thru LA-225 with BEECHCRAFT Spar Bridge Kit No. 90-4090-1 or
90-4090-3 installed) 6
Wing Installation (Effectivity: LA-2 thru LA-225 with BEECHCRAFT Wing Spar Bridge Kit No. 90-4090-1
or 90-4090-3 installed) 9
Wing Disassembly (Effectivity: All) 17
Wing Assembly (Effectivity: All) 19
Wing Adjustment (Effectivity: All) 21
Wing Bolt Maintenance (Effectivity: All) 25
Wing, Bolt, Nut And Spar Fitting Inspection (Effectivity: All) 26
Outboard Wing Spar Cap Inspection (Effectivity: All) 26

57-30-00
Plates/Skin • Maintenance Practices (Effectivity: All) 1

57-50-00
Aileron - Maintenance Practices (Effectivity: All) 1
Balancing The Aileron (Effectivity: All) 1
Checking Balance (Effectivity: All) 1
Balancing Procedure (Effectivity: All) 1
Equipment Required to Perform Check Balancing by Force Measurement Method (Effectivity: All) 1
Force Measurement Method (Effectivity: All) 1
Equipment Required to Perform Check Balancing by Counterbalancing Method (Effectivity: All) .. 2
Counterbalancing Method (Effectivity: All) 2

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 Cj£echcraft
KING AIR F90
MAINTENANCE MANUAL
WINGS - DESCRIPTION AND OPERATION points of the main landing gear. The nacelle fairing
(Effectivity: All) and the cavity for the bladder fuel tank, located above
and forward of the wheel well, are constructed of
The King Air F90 wing assembly consists of the cen- formed sheet metal sections and stringers.
ter section and two outboard wing panels. Each wing
panel on airplane serials LA-1 thru LA-225 is attached ATTACH FITTINGS (Effectivity: Allj
to the center section with four tension bolts. The cen-
The major fittings in each wing and the center section
ter section installed on airplane serials LA-226 and
are the supporting structures adjacent to the attach-
after incorporates a three-element main spar. Each
ment points for the flap actuator, flap tracks and flap,
wing panel is attached to these later model center
the aileron hinge brackets and hinges, and the main
sections with a shear bolt at the lower forward attach
landing gear, drag legs, and landing gear doors. Minor
point and tension bolts at the other three attach points.
fittings include brackets to support cable pulleys,
The center section and outboard wing assemblies are bellcranks, and similar components. The main gear is
of semimonocoque box construction of conventional bolted to heavy aluminum alloy fittings attached to the
design. Both aluminum center section spars are main rib assembly at the aft end of the wheel well. The
I-beam sections built up from extruded tee caps, web- main gear drag leg is bolted to an aluminum alloy
bing and stiffeners. Similar construction is used in the forging attached to the main spar of the center sec-
outboard wing spars, except that a combination of alu- tion. If the landing gear support channels are warped
minum extrusion and formed U-channel members or buckled or if the landing gear hinge bolt extrusions
comprise the main spar caps while those of the rear are cracked, replacement is necessary.
are composed of formed aluminum angles and cap
strips. WINGS - MAINTENANCE PRACTICES
The leading edge assembly and the main outboard (Effectivity: All)
wing assembly are joined together at the main spar by
continuous hinges. A subspar is installed at the for- WING REMOVAL (Effectivity: LA-2 thru
ward end of the leading edge. The space forward of LA-225 without BEECHCRAFT Wing Spar
this subspar is utilized to route wiring and plumbing. Bridge Kit No. 90-4090-1 or 90-4090-3
Bladder fuel tanks are installed the full span of the installed; LA-226 and after)
outboard leading edge between the subspar and the
main spar.
A faying-surface-sealed integral (wet wing) fuel tank is
installed in the outboard end of each outboard wing
If the wing is to be disassembled after
assembly. The tank interior is coated for corrosion
removal, liberally apply a lubricant, (5,
protection and is accessible through gasket-sealed
Chart 1, 91-00-00) to the entire acces-
doors in the lower wing skin. Bladder fuel tanks are
sible length of each spar hinge as soon
installed inboard of the integral tanks. as possible after the airplane is turned
over for maintenance. Allow the lubricant
WING CENTER SECTION (Effectivity: All) to soak in as long as possible (at least
The center section main and rear spars are parallel 12 hours) before attempting to remove
the hinge pins.
and are continuous from one outboard wing attach
joint to the other outboard wing attach joint. A remov-
able leading edge is attached to the subspar, installed
forward of the main spar between the fuselage and NOTE
each nacelle. The area between the subspar and the When plumbing lines are disconnected,
leading edge is used to route engine controls, plumb- they must be capped immediately to pre-
ing and wiring, etc. A subspar located forward of the vent contamination of the respective
rear spar provides a tunnel for control cables and system.
shafts and serves as a fuel wall for the bladder fuel
tanks from the root rib to the nacelle. Machined alloy a. Disconnect the electrical leads from the battery.
plates in the nacelles provide support for the hinge b. Drain and purge the wing fuel cells.

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KING AIR F90
MAINTENANCE MANUAL

The fuel must be drained and purged With the exception of the lower forward
from both wings. bolt installation, the wing bolts must not
be forced from the fittings. If bolt binding
c. Install a tail stand. is encountered at any attach point
(except the lower forward position in the
d. Remove the leading edge skin outboard of the three-element spar), the wing must be
nacelle and the upper and lower access doors imme- repositioned until the binding bolt can be
diately aft of the main spar. Remove the wing bolt readily removed. The lower forward bolt
access covers. in the three-element main spar must be
carefully driven out with a rawhide mallet
e. Disconnect the wing wiring and the gravity feed and an aligning pin (available from
and crossvent fuel lines at the outboard wing root rib. BEECHCRAFT Parts And Service
Disconnect the fuel vent line from the leading edge Operations under PIN 10996). Care
and inboard wing fuel cell. must be exercised during the driving
operation to prevent damage to the bolt
f. Disconnect the aileron and aileron tab cables at threads and interior surfaces of the bolt
the turnbuckles inside of the wheel wells. bore. Refer to Figure 7.
g. Remove the inboard access covers on the lower
surface of the outboard wing just forward of the rear
spar. Disconnect the outboard flap actuator drive shaft
and remove the grommet in the wing rib.
h. Disconnect the pneumatic deicer lines.
I WARNING I
Anytime the upper wing fittings are
i. Disconnect the bonding straps. separated or shifted, the aluminum
washers between these fittings must
j. Disconnect the strobe light plug if installed.
be replaced with new washers. When
k. Support the wing being removed with a suitable the lower forward bolt is loosened on
cradle. Support the opposite wing in order to assure airplanes manufactured prior to the
airplane stability during and after removal of the wing. introduction of the three-element
main spar, the preload indicating
NOTE washer must be replaced with a new
washer assembly.
Prior to removing the wing bolts, draw a
line across each pair of fi~ings with a
grease pencil. The lines will aid realign- I. Remove the wing mounting bolts. Pull the wing
ment when the wing is installed. Do not straight away from the airplane until clear of all atten-
scratch or scribe the fittings. dant plumbing.

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 ~echcraft
KING AIR F90
MAINTENANCE MANUAL
WING INSTALLATION (Effectivity: LA-2 thru b. Align the wing and center section fittings and
LA-225 without BEECHCRAFT Wing Spar insert the bolts into the fittings. Install the bolts wash-
Bridge Kit No. 90-4090-1 or 90-4090-3 ers and nuts. Position the barrel nuts so that the lubri-
cation fittings are readily accessible for service. Refer
installed; LA-226 and after) to Figures 6 through 11.

I WARNING I NOTE
Steps b through f apply to airplanes
manufactured prior to the introduction of
Wing bolts and nuts that have the three-element main spar. Steps g
reached their life limit must be through I apply to airplanes incorporating
replaced with new Inconel compo- the three-element main spar.
nents. Refer to the BEECHCRAFT
Structural Inspection And Repair
Manual.
a. Using corrosion preventive compound (106, Chart To prevent damage to the wing fittings
1, 91-00-00), coat the bores and bearing surfaces of and/or false torque readings, ensure that
each fitting, bolt, washer, nut, and (on airplanes manu- the wing bolt wrenches do not bottom
factured prior to the introduction of the three-element out on the fittings while torquing the
main spar) the preload indicating washer assembly. bolts.

I WARNING I
The soft aluminum washers between
the upper wing attach fittings must be
replaced with new components any-
time the fittings are separated or
shifted. On airplanes produced prior
LUBRICATION FITTING
to the introduction of the three-
element main spar, the preload indi-
cating washer assembly must be
replaced with new parts whenever the ROLL PIN
bolt at this point is loosened or
removed. Ensure that each washer NUT
and (if applicable) the preload indicat- CAUTION
BEVELED AREA
ing washer assembly Is Installed ON NUT MUST
exactly as shown In each of the MATCH CONTOUR
attach point Illustrations. OF NUT CRADLE
CRADLE

Each bolt, except the lower forward bolt

installed in the three-element main spar,
must be inserted by hand without bind-
ing. If a bolt cannot be easily inserted
through the fittings, reposition the wing
until the bolt moves freely into the fit- Barrel Nut Assembly (Effectivity: All)
tings. Figure 1

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KING AIR F90
MAINTENANCE MANUAL
c. Tighten the lower forward bolt sufficiently to pro- NOTE
vide support while still permitting rotation of the wing. If correct alignment between the castel-
Adjust the wing until the alignment marks on the fit- lated nut and the safety wire hole in the
tings match. bolt cannot be obtained, install one
d. After the fittings are properly aligned, tighten the AN960PD1416L washer under the nut
lower forward bolt to a torque of 1200 inch-pounds, and retorque the nut to the correct value.
but do not load the preload indicating washer until the I. Torque the upper aft. upper forward, and lower aft
other bolts have been properly torqued. bolts to the applicable wet torque value. Refer to Fig-
e. Tighten each of the other wing bolts to the appli- ures 8 through 11. When a torque wrench adapter is
cable specified torque. Refer to Figure 8, 9, 10 or 11. used, the correct torque wrench readings must be
Torque the upper forward bolt at the bolt head and the computed. Refer to Chapter 20-01-00.
upper and lower aft bolts at the nut. When a torque m. When torquing procedures have been completed,
wrench adapter is used, the length of the adapter inject additional corrosion preventive compound (106,
must be added to the length of the torque wrench for Chart t, 91-00-00) into the lubrication fitting of the bar-
adjustment of the torque requirement. Refer to Chap- rel nut with a high quality grease gun fitted with an
ter 20-01-00. Alem ite 314150 nozzle. Sufficient corrosion preventive
1. Tighten the lower forward wing bolt at the bolt compound has been added when one of the following
head until the indicator ring of the preload indicating criteria has been met:
washer assembly remains immovable under a tangen- 1. The corrosion preventive compound emerges
tial force of 30 ±5 inch-pounds. Refer to Figure 2. from between the two portions of the barrel nut
g. Install the upper forward and upper and lower aft assembly.
wing bolts, washers, and nuts. Do not tighten the bolts 2. The compound emerges from around the
at this time. threaded portion of the bolt.
h. Align the outboard wing and center section. The 3. The lubrication fitting fails to accept additional
lower forward fitting holes must be perfectly aligned. compound after several actions of the grease gun.
i. Coat the 10996 aligning pin with corrosion preven- n. Coat the exposed threads of the wing bolts with
tive compound (106, Chart 1, 91-00-00) and carefully corrosion preventive compound (106, Chart 1, 91-00-
drive the pin through the lower forward fittings. Use a 00).
rawhide mallet to drive the pin.
o. Connect the wing fuel cell interconnect tube, and

~J
attach the electrical bonding cables.
p. Connect the fuel vent lines.
Do not allow any metallic washers to q. Mate the electrical connectors.
come into contact with the fitting face r. Connect the aileron and trim tab control cables at
during installation of the lower forward the turnbuckles in the wheel well.
bolt in the three-element main spar.
s. Connect the flap flex shaft to the outboard flap
actuator.
j. Install one AN960PD1416L metal washer and one
NAS1515H14 nylon washer on the attach bolt and t. Connect the pneumatic line to the deicer boot
carefully drive the bolt into the fittings from the forward hose.
side of the spar. u. Rig the aileron and trim tab control cables. Refer
k. Install one NAS1515H14 nylon washer and the to AILERON CONTROL SYSTEM RIGGING and
nut on the bolt. Torque the nut to the wet torque value. AILERON TRIM TAB RIGGING, Chapter 27-10-00.
Refer to Figure 7. The slots in the castellated nut must v. Rig the flaps. Refer to FLAP CONTROL SYSTEM
align with the safety wire hole in the bolt. Install the RIGGING, Chapter 27-50-00.
bolt retainers with NAS603-8 or MS27039-1-07 w. Secure the wing-to-nacelle fairing to the center
screws and AN960-10 washers. Safety wire the bolt section with the attaching screws.
head and nut to their respective clips.
x. Remove the tail stand and wing supports.

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KING AIR F90
MAINTENANCE MANUAL

y. Refuel the airplane. Refer to FILLING THE abo Check for proper operation of the fuel quantity
TANKS, Chapter 12-10-00. transmitters, strobe lights, and navigation light.
z. Check all connections for leakage and correct as ac. Install all access covers and doors.
necessary.
aa. When it has been ascertained that there is no ad. Test fly the airplane to ensure proper wing and
fuel leakage. connect the electrical power. stall warning vane adjustment.

OUTER RING OF THE

PRELOAD INDICATING
WASHER ASSEMBLY

To tighten the lower forward wing attach bolts. insert the tool into one of the holes in the outer ring of the preload Indicating washer
assembly Rotate the ring back and forth while tightening the nut The bolt is tight when the outer ring can no longer be rotated using
30 :!: 5 pounds tangential force applied as shown by the symbol above the tool Do not tighten the bolt beyond this point

Lower Forward Wing Bolt Tightening Procedure 60-31·15

Preload Indicating Washer Installation (Effectivity: LA-2 thru LA-225)

Figure 2

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KING AIR F90
MAINTENANCE MANUAL

WING REMOVAL (Effectivity: LA-2 thru k. Remove the center section fairings covering the
LA-225 with BEECHCRAFT Spar Bridge Kit spar bridge.
No. 90-4090-1 or 90-4090-3 installed) I. Attach weight hangers to the spar bridge. Refer to
Figure 3, Detail A. Apply 125 pounds of weight to each
hanger. Refer to Figure 3, Detail B.
m. Remove the screws and brackets from the spar
blocks. Refer to Figure 3, Detail D.
If the wing is to be disassembled after
removal, liberally apply a lubricant (5, n. Apply dry ice to the bottom side of the spar strap
Chart 1, 91-00-00), to the entire acces- immediately below the spacer blocks. Refer to Figure
sible length of each spar hinge as soon 3, Detail A. Allow the spar strap to chill for approxi-
as possible after the airplane is turned mately 10 minutes. Tap the spar at the block assem-
over for maintenance. Allow the lubricant blies until the adhesive breaks. Remove the spacer
to soak in as long as possible (at least blocks.
12 hours) before attempting to remove
o. Remove the two weight hangers and weights from
the hinge pins.
the spar bridge.

NOTE p. Remove the expandable bolts from the outboard

wing and center section bridge fitting interface. Refer
When plumbing lines are disconnected, to Figure 3, Detail C, and Figure 4.
they must be capped immediately to pre-
vent contamination of the respective q. Support the wing being removed with a suitable
system. cradle. Support the opposite wing in order to assure
airplane stability during and after removal of the wing.
a. Disconnect the electrical leads from the battery.

I
b. Drain and purge the wing fuel cells.

I WARNING

Anytime the upper wing fittings are

The fuel must be drained and purged separated or shifted, the aluminum
from both Wings. washers between these fittings must
be replaced with new washers. When
c. Install a tail stand. the lower forward bolt is loosened,
d. Remove the leading edge skin outboard of the the preload indicating washer must
nacelle and the upper and lower access doors imme- be replaced with a new washer
diately aft of the main spar. Remove the wing bolt assembly.
access covers.
e. Disconnect the wing wiring and the gravity feed
and crossvent fuel lines at the outboard wing root rib.
Disconnect the fuel vent line from the leading edge
and inboard wing fuel cell. The wing bolts must not be forced from
the fittings. If bolt binding is encountered
f. Disconnect the aileron and aileron tab cables at at any attach point, the wing must be
the turnbuckles inside of the wheel wells. repositioned until the binding bolt can be
g. Remove the inboard access covers on the lower readily removed.
surface of the outboard wing just forward of the rear
spar. Disconnect the outboard flap actuator drive shaft NOTE
and remove the grommet in the wing rib. Prior to removing the wing bolts, draw a
h. Disconnect the pneumatic deicer lines. line across each pair of fittings with a
grease pencil. The lines will aid realign-
i. Disconnect the bonding straps.
ment when the wing is installed. Do not
j. Disconnect the strobe light plug if installed. scratch or scribe the fittings.

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 'Deechcraft
KING AIR F90
MAINTENANCE MANUAL

BLOC K ---=-----=-- ~=c--BLOCK

ASSY ASSY

FITIINGS FITIINGS
SPLICE SPLICE
SCREW PLATE PLATE rSPAR STRAP
BLOCK BONDED
TO FUSELAGE

~--BRACKET
WEIGHT HANGER
ASSEMBLY
r-'=~~~i=::::J~~
~ '-
,-"~:---SHIM I C
~I

BRACKET WEIGHTS--~
BLOCK BONDED
TO STRAP
DETAILB
DETAIL 0
o
~~~~~.~B~~
~~l~O;"~~p lLOWER SPLICE
PLATE
~WEIGHTHANG~
AND WEIGHTS CENTER SPAR
STRAP
DETAIL A
INSTALL CLAMP-UP END OF
THE EXPANDABLE BOLT UP
~7_ ~
> -

CENTER SECTION OUTBOARD ._

SPAR STRAP . ""- .w

INSTALLCLAMP-UP END OF
THE EXPANDABLE BOLT UP

OUTBOARD WING
FITIINGS
DETAIL C F9031 104

Spar Bridge Installation (Effectivity: LA-2 thru LA-225

with BEECHCRAFT Kit NO. 90-4090-1 or 904090-3 Installed)
Figure 3

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 '1?eechcraft
KING AIR F90
MAINTENANCE MANUAL

TWIST OFF WRENCHING DEVICE

CLAMP-UP END
(SPACER, WASHER AND NUT)

SHOULDER

BUSHING

EXPANSION END
(WASHER AND NUT)
{
HEX RECESS (BOTH ENDS)

FASTENER INSTALLATION: METHOD

1, REMOVE CLAMP-UP NUT, WASHER AND SPACER. BUSHINGS WILL BE HELD IN PLACE BY
THE SHOULDER.

2 SNUG THE EXPANSION NUT UP TO THE BUSHINGS

3. CHECK TO ENSURE THAT SHOULDER PROTRUDES ABOVE PART.

4 INSTALL SPACER ON CLAMP-UP END OF FASTENER AND KEEP IN POSITION WHILE

EXPANSION NUT IS BEING TIGHTENED

5 WITH AN ALLEN WRENCH INSERTED IN HEX RECESS, AND KEEPING THE EXPANSION END
WASHER PUSHED UP AGAINST THE PLATE, TIGHTEN THE EXPANSION NUT TO APPROXI-
MATEL Y 50% OF THE RECOMMENDED TORQUE VALUE THIS SQUEEZES THE TAPERED
BUSHINGS BETWEEN THE EXPANSION WASHER AND THE SHOULDER, EXPANDING THE
BUSHINGS TO FILL THE HOLE.

6. INSTALL CLAMP UP WASHER AND NUT WITH AN ALLEN WRENCH IN THE HEX RECESS,
TIGHTEN CLAMP UP NUT TO APPROXIMATELY 55 INCH-POUNDS

7. TORQUE THE EXPANSION NUT TO 250 + 50 - 0 INCH-POUNDS THE BUSHING FRICTION

AGAINST THE HOLE SHOULD PREVENT BOLT ROTATION

8. TIGHTEN THE CLAMP-UP NUT UNTIL THE WRENCHING DEVICE TWISTS OFF IF BOLTS DO
NOT HAVE THE TWIST OFF DEVICE SHOWN IN THIS ILLUSTRATION, TORQUE THE CLAMP-UP
NUT TO 200 + 40 - 0 INCH-POUNDS THE BUSHING FRICTION AGAINST THE HOLE SHOULD
PREVENT BOLT ROTATION

200-31-29
001

Expandable Bolt Installation (Effectivity: LA-2 thru LA-225

with BEECHCRAFT Kit NO. 90-4090-1 or 90-4090-3 installed)
Figure 4

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 'Deechcraft
KING AIR F90
MAINTENANCE MANUAL
r. Remove the wing mounting bolts. Pull the wing a. Using corrosion preventive compound (106, Chart
straight away from the airplane until clear of all atten- 1, 91-00-00), coat the bores and bearing surfaces of
dant plumbing. each fitting, bolt, washer, nut, and the preload indicat-
ing washer assembly.
WING INSTALLATION (Effectivity: LA-2 thru
LA-225 with BEECHCRAFT Wing Spar
Bridge Kit No. 90-4090-1 or 90-4090-3
installed)

I WARNING ~
Wing bolts and nuts that have
reached their life limit must be
replaced with new Inconel compo-
nents. Refer to the BEECHCRAFT
King Air F90 Structural Inspection
And Repair Manual.

~"~~~~u
"~~-LEVER
" u
co ~

'-' u

" u

HINGE PIN

~ LOCKING PLIERS
20035-9

Wing Hinge Pin Removal (Method #1) (Effectivity: All)

Figure 5

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 'Deechcmft
KING AIR F90
MAINTENANCE MANUAL

BARREL NUT WING FITTING-

ASSEMBLY 90-380019-1 CENTER SECTION
WASHER ASSY

TO TIGHTEN
~~~THIS BOLT USE
~===jl A TK1817922-5
OR A 15/16 BOX
~~-+-~ ~END WRENCH
~~I ADAPTED TO
ACCEPT AN
~===~I EXTENSION OF

[~----1FJI~~~~~~~~~~~~~L 40 INCHES

/ APPROXIMATELY
BOLT

WING FITTING
OUTBOARD
LUBE FITTING

CAUTION
ASSEMBLE
TOWARDSWITH
SPAR RADIUS
CAP
PRELOAD INDICATING
WASHER ASSEMBLY
~,
eo@-
"'8 __ _ a ~

BOLT TIGHTENING PROCEDURE: COAT THE COMPLETE BOLT. NUT. WASHER ASSEMBLY. AND
WING FITTING BOLT BORES WITH MIL-C-16173. GRADE 2 CORROSION PREVENTIVE COMPOUND.
TIGHTEN THE BOLT WHILE APPLYING A TANAGENTIAL FORCE OF 30 ± 5 POUNDS TO THE
INDICATOR RING OF THE PREOAD INDICATING WASHER. AS SHOWN IN FIGURE 2. NO FURTHER
WRENCHING SHOULD BE APPLIED TO THE BOLT WHEN 30 ± 5 POUNDS OF TANGENTIAL FORCE
WILL NO LONGER MOVE THE INDICATOR RING. THE 90-380019-1 PRELOAD INDICATING WASHER
ASSEMBLY IS NOT TO BE REUSED AFTER ONCE BEING LOADED. AFTER TIGHTENING THE BOLT,
USE A HIGH QUALITY GREASE GUN AND AN ALEMITE PIN 314150 GREASE NOZZLE TO INJECT
MIL-C-16173. GRADE 2 INTO THE LUBRICATION FITTING ON THE BARREL NUT AND COAT THE
EXPOSED THREADS WITH CORROSION PREVENTIVE COMPOUND.

C9!lLA~7B2130 C

Lower Forward Wing Bolt Installation (Effectivity: LA·2 thru LA-225)

Figure 6

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 CDeechcraft
KING AIR F90
MAINTENANCE MANUAL

070 INCH DIA HOLE

NAS1515H14 WASHER
CENTER SECTION SPAR

AN960PD1416L
WASHER

NAS 603-8
OR
MS27039-1-07
MS20995C41
SCREW
(2 REQD EACH CLIP) SAFETY WIRE
\" -\,

NAS1515H14 . ;.
WASHER ~<"
AN960PD141~L<~
WASHEy /~~

~
~ 1 30909B 1 75 070 INCH

~
C BOLT DIA HOLE
CENTER SECTION
NAS1515H14
SPAR
WASHER
RETAINER CLIP

AN960-10 DETA.IL A DETA.IL B

WASHER

COAT THE SPAR BUSHING BORES, BOLT, NUT, METAL WASHERS, AND THE 10996 ALIGN-
ING PIN WITH MIL-C-16173 GRADE 2 CORROSION PREVENTIVE COMPOUND USING A
RAWHIDE MALLET, DRIVE THE 10996 ALIGNING PIN INTO THE FITTINGS INSTALL AN
AN960PD1416L METAL WASHER AND AN NAS1515H14 (NYLON) WASHER ON THE BOLT
THE METAL WASHER MUST BE DIRECTLY UNDER THE BOLT HEAD AND THE NYLON
WASHER MUST BE POSITIONED UNDER THE METAL WASHER POSITION THE BOLT ON
THE FORWARD SIDE OF THE FITTINGS DRIVE THE BOLT INTO THE FITTINGS UNTIL THE
WASHERS AND BOLT HEAD REST FIRMLY AGAINST THE FITTINGS THE ALIGNING PIN
WILL BE DRIVEN OUT OF THE FITTINGS AS THE BOLT IS DRIVEN IN INSTALL AN NAS
1515H14NYLON WASHER AND THE NUT ONTO THE THREADED PORTION OF THE BOLT
HOLD THE BOLT HEAD IMMOBILE WITH A BOX END WRENCH AND TORQUE THE NUT TO
30 TO 50 INCH-POUNDS WITH A 11001 ADAPTER AND TORQUE WRENCH THE SLOTS IN
THE CASTELLATED NUT MUST ALIGN WITH THE SAFETY WIRE HOLE IN THE BOLT IF
ALIGNMENT CANNOT BE ATTAINED WITHIN THE TORQUE LIMITATIONS, REMOVE THE
NUT AND INSTALL AN AN960PD1416L (METAL) WASHER INSTALL THE NUT AND RE-
TORQUE TO 30 TO 50 INCH-POUNDS INSTALL THE RETAINER CLIPS AND SAFETY THE
BOLT HEAD AND NUT TO THEIR RESPECTIVE CLIPS WITH MS20995C41 SAFETY WIRE
F90-31-100

Lower Forward Wing Bolt Installation Three-Element Main Spar (Effectivity: LA-226 and after)
Figure 7

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 'l}eechcraft
KING AIR F90
MAINTENANCE MANUAL

WASHER
WASHER (PIN MS20002-12)
POSITION WASHER WITH
MAYBE ADDED UNDER THE NUT TO WASHER
INNER CHAMFER AGAINST THE
PROVIDE A PROPER BOLT GRIP
BOLT HEAD RADIUS AND THE
ADJUSTMENT
OUTER RADIUS AGAINST THE
RADIUS IN THE WING FITTING

NUT
USE TS1176-10 WRENCH

BOLT
USE TS1222-5
OR
TS1222-4
WRENCH

WING FITTING WING FITTING -

OUTBOARD CENTER SECTION

COAT THE COMPLETE BOLT, NUT AND WASHERS

WITH Mll-C-16173 CORROSION PREVENTIVE COM-
POUND. GRADE 2
BOLT TORQUE 2380 TO 2500 INCH-POUNDS
F90·31·71

Upper Forward Wing Bolt Installation (Effectivity: LA-2 thru LA-225)

Figure 8

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 'i?eechcraft
KING AIR F90
MAINTENANCE MANUAL

• 1a I - 1000 I I - I
WASHER
80691CF-1216 VCC0025
OR OR
SL4092- 12 81784-12-32
BARREL NUT BOLT
ASSEMBLY

NAS578-12B
RETAINER

DRAIN
HOLE DRAIN
HOLE
OUTBOARD WING
PANEL FITTING VIEWB CENTER SECTION
WING FITTING

THE UPPER FORWARD SPAR BOLTS ARE TO BE INSTALLED AS FOLLOWS:COAT THE

SPAR FITTING BOLT BORE,WASHER BEARING SURFACES,THE COMPLETE BOLT,NUT
AND WASHERS WITH MIL-C-16173 GRADE 2 CORROSION PREVENTIVE COMPOUND.
TOROUE THE BOLT TO 2500 TO 2650 INCH-POUNDS,IN~ECT MIL-C-16173 GRADE
2 CORROSION PREVENTIVE COMPOUND INTO BARREL NUT LUBRICATION FITTING
WITH A GREASE GUN (CAPABLE OF 2000 TO 4000 PSI) EOUIPPED WITH A NO.
314150(P/N OF ALEMITE TOOL,A DIVISION OF STEWART WARNER) GREASE
NOZZLE.COAT THE EXPOSED THREADS OF BOLT WITH MIL-C-16173 GRADE 2
CORROSION PREVENTIVE COMPOUND. ASSURE THAT THE DRAIN HOLES IN THE
FITTINGS ARE NOT OBSTRUCTED.
-INSTALL THE WASHER WITH THE RADIUS TOWARD THE FITTING SURFACE
C95LA!l7BJI42 C

Upper Forward Wing Bolt Installation (Effectivity: LA-226 and after)

Figure 9

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 CQeechcraft
KING AIR F90
MAINTENANCE MANUAL

WASHER
ONE ADDITIONAL WASHER (PIN MS20002-10) WASHER POSITION WASHER WITH
MAY BE ADDED UNDER THE NUT TO INNER CHAMFER AGAINST THE
PROVIDE A PROPER BOLT GRIP BOLT HEAD RADIUS AND THE
ADJUSTMENT OUTER RADIUS AGAINST THE
RADIUS IN THE WING rrrnnc

USE TS 1176-11 WRENCH

BOLT
NUT~ (USE TS1222-5 WRENCH
9/16 INCH HEX) OR
(USE TS1222-7 WRENCH
1/2 INCH HEX)

WING FInING WASHER

- OUTBOARD WING FiniNG -
CENTER SECTION

COAT THE COMPLETE BOLT, NUT AND WASHERS

WITH MIL-C-16173 CORROSION PREVENTIVE COMPOUND,
GRADE 2
BOLT TORQUE 1180 TO 1300 INCH-POUNDS F90-31 73

Upper Aft Wing Bolt Installation (Effectivity: All)

Figure 10

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KING AIR F90
MAINTENANCE MANUAL

WASHER
POSITION WASHER WITH
ONE ADDITIONAL WASHER (PIN MS20002-10) WASHER
INNER CHAMFER AGAINST THE
MAY BE ADDED UNDER THE NUT TO
BOLT HEAD RADIUS AND THE
PROVIDE A PROPER BOLT GRIP
ADJUSTMENT OUTER RADIUS AGAINST THE
RADIUS IN THE WING FITTING

WING FITTING ~ WING FITTING

CENTER SECTION
OUTBOARD \

/
I
I
/
/
BOLT
USE TS1176-11 WRENCH (USE TS1222-5 WRENCH,
NUT 9/16 INCH HEX) OR
(USE TS1222-7 WRENCH,
I
112 INCH HEX)
COAT THE COMPLETE BOLT, NUT AND WASHERS
WITH MIL-C-16173 CORROSION PREVENTIVE COM-
POUND, GRADE 2
BOLT TORQUE 1180 TO 1300 INCH-POUNDS
F90-31-70

Lower Aft Wing Bolt Installation (Effectivity: All)

Figure 11

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 C1?eechcraft
KING AIR F90
MAINTENANCE MANUAL

I WARNING I wrench adapter is used, the length of the adapter

must be added to the length of the torque wrench for
adjustment of the torque requirements. Refer to Chap-
ter 20-01-00.
The soft aluminum washers between
the upper wing attach fittings must be f. Tighten the lower forward wing bolt at the bolt
replaced with new components any- head until the indicator ring of the preload indicating
time the fittings are separated or washer assembly remains immovable under a tangen-
shifted. The preload indicating tial force of 30 ± 5 inch-pounds. Refer to Figure 2.
washer assembly must be replaced g. When torquing procedures have been completed,
with new parts whenever the bolt at
inject additional corrosion preventive compound (106,
this point is loosened or removed.
Chart 1, 91-00-00) into the lubrication fitting of the bar-
Ensure that each washer and (if appli-
cable) the preload indicating washer rel nut with a high quality grease gun fitted with an
assembly is installed exactly as Alemite 314150 nozzle. Sufficient corrosion preventive
shown in each of the attach point compound has been added when one of the following
illustrations. criteria has been met:
1. The corrosion preventive compound emerges
from between the two portions of the barrel nut
assembly.

Each bolt must be inserted by hand with- 2. The compound emerges from around the
out binding. If a bolt cannot be easily threaded portion of the bolt.
inserted through the fittings, reposition 3. The lubrication fitting fails to accept additional
the wing until the bolt moves freely into compound after several actions of the grease gun.
the fittings.
h. Coat the exposed threads of the wing bolts with
b. Align the wing and center section fittings and corrosion preventive compound (106, Chart 1, 91-00-
insert the bolts into the fittings. Install the bolts wash- 00).
ers and nuts. Refer to Figures 6, 8, 10 and 11. Posi-
tion the barrel nuts so that the lubrication fittings are i. Connect the wing fuel cell interconnect tube and
readily accessible for service. attach the electrical bonding cables.
j. Lubricate the expandable bolts and fill the expand-
able bolt holes in the spar bridge with corrosion pre-
ventive compound (106, Chart 1,91-00-00).

To prevent damage to the wing fittings k. Install the expandable bolts. Refer to Figures 3
and/or false torque readings, ensure that and 4.
the wing bolt wrenches do not bottom I. Attach two weight hangers inboard of the spacer
out on the fittings while torquing the blocks, with 125-pound weights installed, to the spar
bolts. strap. Refer to Figure 3.
c. Tighten the lower forward bolt sufficiently to pro- m. Bond the two spacer blocks to the spar bridge
vide support while still permitting rotation of the Wing. with adhesive (111, Chart 1, 91-00-00) per adhesive
Adjust the wing until the alignment marks on the fit- manufacturer's recommendations.
tings match.
n. Install the spacer block brackets. Refer to Figure
d. After the fittings are properly aligned, tighten the 3.
lower forward bolt to a torque of 1200 inch-pounds,
but do not load the preload indicating washer until the NOTE
other bolts have been properly torqued.
If any rough areas are noted on the
e. Tighten each of the other wing bolts to the appli- mounting surfaces of either the spar
cable specified torque. Refer to Figures 8, 10 and 11. bridge or spacer blocks, smooth the
Torque the upper forward bolt at the bolt head and the area with fine-grit sandpaper before
upper and lower aft bolts at the nut. When a torque installing the blocks.

57-00-00
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 'lJeechcrnft
KING AIR F90
MAINTENANCE MANUAL
o. Remove the weights and weight hangers from the
spar bridge.
p. Install the wing spar bridge fairings.
q. Connect the fuel vent lines. Never use a drill motor to spin a hinge
pin out of the hinge. The resulting friction
r. Mate the electrical connectors. heat will cause the pin to expand and
s. Connect the aileron and trim tab control cables at seize in the hinge.
the turnbuckles in the wheel well.
t. Connect the flap flex shaft to the outboard flap act- Support the leading edge/spar assembly
uator. while the second main wing hinge pin is
being removed to prevent the assembly
u. Connect the pneumatic line to the deicer boot
from falling away from the wing.
hose.
v. Rig the aileron and trim tab control cables. Refer 1. Refer to Figure 5 to perform Method No. 1 as
to AILERON CONTROL SYSTEM RIGGING and follows:
AILERON TRIM TAB RIGGING, Chapter 27-10-00. a) Clamp locking pliers or equivalent) tightly on
w. Rig the flaps. Refer to FLAP CONTROL SYSTEM the pin.
RIGGING, Chapter 27-50-00.
b) Place a board in a suitable position on the
x. Secure the wing-to-nacelle fairing to the center wing spar to use as a fulcrum for a lever.
section with the attaching screws.
y. Remove the tail stand and wing supports.
z. Refuel the airplane. Refer to FILLING THE
TANKS, Chapter 12-10-00.
Use slow, steady pressure on the lever
aa. Check all connections for leakage and correct as
to avoid breaking the hinge pin.
necessary.
abo When it has been ascertained that there is no c) Bring the lever to bear against the locking
fuel leakage, connect the electrical power. pliers and pry the hinge pin out of the hinge.
ac. Check for proper operation of the fuel quantity d) Use thicker boards and shift the position of
transmitters, strobe lights, and navigation light. the locking pliers as the hinge pin is pulled out of the
ad. Install all access covers and doors. spar.
ae. Test fly the airplane to ensure proper wing and
2. Refer to Figures 12 and 13 to perform Method
stall warning vane adjustment.
No. 2 as follows:
WING DISASSEMBL Y (Effectivity: Allj a) Fabricate a support bracket and crank.
(Figures 5, 12, and 13 )
b) Attach the bracket to the end stiffener of the
a. Support the wing on a suitable cradle. spar with two screws.
b. Remove the wing tip, aileron, fuel cells; and other
c) Insert the crank through the bracket. Align
equipment as required by the work being done.
the hole in the crank so that tension will be applied to
c. Remove the screws around the spar caps at the the hinge pin in as straight a line as possible.
root and root tip ribs.
d. At the outboard end of the wing, free the ends of d) Insert the free end of the hinge pin through
the hinge pins. Remove each hinge pin by one of the the hole in the crank.
following methods:
NOTE
Before removing any single hinge pin,
pull all hinge pins out 1 inch (2 hinge
I WARNING I
lugs) to break any adhesion or binding Keep clear of the hinge pin end when
caused by corrosion or buildup of dust. the hinge pin is nearly removed. The
Remove the hinge pins from the wing sudden release of tension may cause
section first, then from the leading edge. the pin to spring free at high velocity.

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 'lJeechcraft
KING AIR F90
MAINTENANCE MANUAL

!--------~-WIDTHSUFFICIENT
TO FIT OVER TOP AND
BOTTOM OF SPAR
DRILL TO DIAMETER OF SCREW
141NCH---.....
------- HOLES IN SPAR (2 PLACES)

MILD STEEL JWmmiiiii:iiiiiiiii:iiiiiiiiiiiiii_iiiiiii~k--- WELD AROUND ENTIRE

PERIMETER OF JOINT
38 TO 1 2 INCH--~
DRILL TO ALLOW CRANK
MILD STEEL
TO TURN EASILY (2 PLACES)

* DEPTH WIDTH NOT CRITICAL.

BUT ALLOW SUFFICIENT ROOM
1------*-----1
FOR HINGE PIN TO FORM A
COIL ON THE CRANK

DRILL TO EASILY INSERT

AND REMOVE HINGE PIN
~--MILD STEEL
END (1'4 INCH)
ROUND STOCK

2003513

Hinge Pin Removal Tool (Method No.2) (Effectivity: All)

Figure 12

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 Ci?eechcraft
KING AIR F90
MAINTENANCE MANUAL
over any exposed rivets, fasteners, sheet metal edges
or protrusions which might scuff the fuel cell. Refer to
Figure 14.
Use slow, steady rotation of the crank to i. Pressure-check each fuel cell for leaks. Refer to
avoid breaking the pin. Chapter 28.
j. Inspect the entire interior and structure of the wing
e) Turn the crank to pull the hinge pin out of the
and leading edge for corrosion or damage.
hinge.
f) Remove the support bracket when all hinge
WING ASSEMBLY (Effectivity: All)
pins have been removed. (Figures 14 through 17 )
a. Place the leading edge in locally fabricated
e. After the spar is separated from the leading edge,
cradles. Refer to Figure 15
install a temporary hinge pin into each open hinge to
prevent damage, distortion or blockage of the hinge b. Install the outboard leading edge fuel cell into ils
lugs during handling. bay in the leading edge and secure all retaining but-
tons to the inner top surface of the leading edge.
f. If the spar is to be replaced, remove the fuel vent
NOTE
line from the spar. Retain the line for installation on
the new spar. Ensure that the fuel cell is pressure-
checked for leaks before installation.
g. Remove the outboard leading edge fuel cell from
c. Install the fuel cell. Refer to Chapter 28.
the leading edge.
d. Apply antichafing tape around the lip of the out-
h. Inspect the interior of each fuel cell bay for loose, board leading edge fuel cell bay so the tape will seal
torn, cracked or missing antichafing tape. Apply tape to the spar when it is installed. Refer to Figure 14.

WING SPAR--~-

200-35 10

Hinge Pin Removal (Method No.2) (Effectivity: All)

Figure 13

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 CReechcraft
KING AIR F90
MAINTENANCE MANUAL

e. Grind a conical point on one end of each new NOTE

hinge pin to ease installation. If necessary, gently tap the spar into
alignment with a rawhide mallet.
NOTE
i. Insert the pointed end of the pin into the spar and
Use only new hinge pins. Provide sev-
slide it into the hinge as far as possible by hand. Slide
eral extra pins in case any are damaged
the telescoping tubes of Repair Kit 35-5885 over the
or bent during installation. Never attempt
to install a bent or distorted hinge pin. pin.

1. Remove the temporary pins from the hinges of the

NOTE
leading edge and the forward hinges of the spar. If necessary, apply Door-Ease (33,
Leave the temporary pins in place in the aft hinges of Chart 1, 91-00-00) or an equivalent
the spar. beeswax preparation to the hinge pins to
ease installation.
g. Lubricate each open hinge lug and new pin with
lubricant (5, Chart 1, 91-00-00). j. Place supports at a suitable height to align the
telescoping tubes to the hinge. Clamp a stout bungee
h. Position the spar on the leading edge and align cord or spring to the larger tube and attach it to the
the hinge sections. Ensure that the anti-chafing tape spar so the tube is held firmly against the hinge
around the edge of the outboard leading edge fuel cell throughout the pin installation. Use the longest tubes
bay seals properly on the spar. at the beginning of the installation and change the

SPAR
ANTI-CHAFING TAPE

ANTI-CHAFING TAPE
(ADHESIVE SIDE OUT)

FUEL
CELL

OUTBOARD LEADING EDGE

FUEL CELL BAY

200-35 11

Anti-Chafing Tape Application (Effectivity: ALL)

Figure 14

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 CQeechcraft
KING AIR F90
MAINTENANCE MANUAL

tubes as necessary as the pin is driven into the hinge. p. Lubricate each open hinge lug and new pin with
Refer to Figure 16. lubricant (5, Chart 1, 91-00-00).

NOTE NOTE
Always keep the end of the inner If necessary, apply Door-Ease (33,
(smaller) tube tight against the spar to Chart 1, 91-00-00) or equivalent bees-
avoid bending or kinking the pin in the wax preparation to the hinge pins to
intervening gap. If a bungee cord or ease installation.
spring is not available, station a person q. Position the assembled spar and leading edge on
at the end of the tube to hold it firmly
the main wing section and align the hinge sections.
against the spar with locking pliers.
NOTE
If necessary, a strap or belt of webbing
may be used to cinch the spar into place
Do not allow the hinge pin to strike the and a rawhide mallet may be used to
wing attach fitting. Measure the hinge gently tap the spar into alignment. If a
and the hinge pin before installation to strap is used, locate it over a stiffener or
determine the proper installation dis- other structure to avoid damage to
tance. Mark the hinge pin to indicate a sheetmetal. Refer to Figure 17.
safe stopping point. r. Repeat steps i through I for the remaining hinges.
s. Trim the excess length of the pins to 4.88 ±O.12
k. Drive the pin in the hinge using an E-4 rivet gun or inches. Loop both ends clockwise around the nearest
equivalent and a rivet set with a 3/32-inch hole. screw on the spar end stiffener and tighten. Allow the
Replace the telescoping tubes as necessary to prop- washer to retain the loops.
erly support the hinge pin until the hinge pin is com- t. Install the screws around the spar caps at the root
pletely driven, then remove the tubes. Continue driv- and root tip rib.
ing the hinge pin until it is completely through the last
hinge loop, but not in contact with the wing attach fit- u. Paint the wing and spar as required.
ting. Refer to Figure 16.

WING ADJUSTMENT (Effectivity: All)

NOTE
If necessary, vibrate the spar with a raw-
NOTE
hide mallet or another rivet gun to aid Wing adjustment procedures for all King
installation. If a rivet gun is used, place a Air F90 airplanes are simi1ar. There are
phenolic block between the spar and the minor difference between LA-2 through
gun to protect the spar. LA-225 and LA-226 and after. Where
these differences do exist, the effectivity
I. Insert the free end of the hinge pin into a conve-
is clearly stated.
nient hole in the end of the spar, or tape it to the end
of the spar, to keep it from interfering during installa- Adjustment of the outer wing panel incidence angle is
tion of the remaining pins. not ordinarily necessary. Most prevailing wing-heavy
m. Repeat steps i through I for the remaining hinge. conditions can be traced to improperly rigged ailerons
or flaps. If, however, the ailerons and flaps are prop-
n. If a new spar is installed, install the fuel vent line erly rigged, change the angle of incidence of one of
on the new spar in the same manner and location as the wings slightly. It is desirable to have the trailing
on the old spar. Ensure that the vertical stiffeners edges of both wings as high as possible to minimize
have flat, smooth edges near the line and that they fuselage drag; consequently, when one- wing is heavy,
provide adequate clearance for the line. the trailing edge of the opposite wing should be
o. Remove the temporary pins from the hinges of the raised, decreasing its lift relative to the heavy Wing.
main wing and the aft hinges of the spar/leading edge Only if this is not possible should the trailing edge of
assembly. the heavy wing be lowered. If this Combination does

57-00-00
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 erkechcraft
KING AIR F90
MAINTENANCE MANUAL

LEADING EDGE

CANVAS OR
NYLON WEBBING

WOOD OR METAL
STRUCTURE

NOTE
PROVIDE TWO OR THREE CRADLES
TO SUPPORT THE LENGTH OF THE
LEADING EDGE AS REQUIRED

f - - - - - - - - - 4 - - WIDTH SUFFICIENT TO SUSPEND

LEADING EDGE AWAY FROM
CONTACT WITH SIDES OR 200-35-12
BOTTOM OF CRADLE

Leading Edge Cradle (Effectivity: All)

Figure 15

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 'Deechcraft
KING AIR F90
MAINTENANCE MANUAL

PIANO HINGE

HINGE PIN

~~.--~-CLAMP
ATTACHING HOOK <,------,--TELESCOPING TUBING
PIANO HINGES

?OG-323

Hinge Pin Installation (Effectivity: All)

Figure 16

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 'i)eechcraft
KING AIR F90
MAINTENANCE MANUAL

WEBBING STRAP
LOCATE STRAP OVER
TIGHTENER
STRUCTURE TO AVOID
DAMAGE TO SHEETMETAL

SPAR
MAIN WING SECTION
200358

Wing Assembly Strap (Effectivity: All)

Figure 17
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 C1?eechcraft
KING AIR F90
MAINTENANCE MANUAL
not correct the wing-heavy condition, rig the flaps of 1. The corrosion preventive compound emerges
the heavy wing slightly down. Do this only as a last from between the two portions of the barrel nut
resort since it will result in additional drag on the air- assembly.
plane.
2. The compound emerges from the threaded
Before loosening the wing attaching bolts to adjust the portion of the bolt.
wing incidence angle, mark (but do not scribe or
3. The lubrication fitting fails to accept additional
scratch) the position of the wing fittings on the center
after several actions of the grease gun.
section fittings for a reference point. Replace both soft
aluminum washers between the upper forward and c. Coat the exposed threads of the wing bolts with
the upper rear fittings and on LA-2 through LA-225 corrosion preventive compound (106, Chart 1, 91-00-
replace the washer assembly under the head of the 00).
lower forward bolt.
After the adjustment is completed, test fly the airplane
On LA-2 through LA-225 loosen all wing attach bolts. and check the new wing position. When it is deter-
On LA-226 and after, wing adjustment can be accom- mined that the wing incidence angle is correct, check
plished without loosening the lower forward wing the stall warning for operation. Refer to Chapter
attach bolt. Loosen only the upper forward and the 27-31-00.
upper and lower aft wing attach bolts.

I WARNING I
Ensure that the wing bolt wrenches do When adjusting the Wing, always
not bottom out on the wing fittings during replace soft aluminum washers and
the following torquing procedure to pre- preload indicating washers. With the
vent damage to the fittings and/or false exception of the lower forward wing
torque readings. attach bolt on LA-226 and after, check
a. Tighten the wing bolts to the applicable specified all wing bolts for proper torque at the
torque. Refer to Figure 8, 9, 10, and 11. Torque all
first scheduled inspection of the air-
plane.
bolts without barrel nuts at the nut. On LA-226 and
after, torque the upper forward bolt at the bolt head
and the upper and lower aft bolts at the nut. On LA-2 WING SOL T MAINTENANCE (Effectivity:
through LA-225, tighten the lower forward bolt at the All)
bolt head until the indicator ring on the preload indiact-
ing washer assembly remains immovable with a tan- NOTE
gential force of 30 ±5 pounds applied. Refer to Figure The lower forward attach point on air-
2. planes with the three element spar is
exempted from these maintenance pro-
NOTE cedures.
When a torque wrench adapter is used,
the length of the adapter must be added a. Check the torque of the upper and lower aft and
to the length of the torque wrench for the upper forward wing bolts at the first scheduled
adjustment of the torque requirements, inspection after the bolts have been loosened and
Refer to Chapter 20-01-00. retorqued, or after initial installation. Refer to Figures
8, 10 and 11). Concurrent with the torque check of
b. When torquing procedures have been completed,
these bolts, check the preload indicating washer at the
inject additional corrosion preventive compound (106,
lower forward wing bolt. Refer to Figure 2 for proper
Chart 1, 91-00-00) into the lubrication fitting of the bar-
checking procedures.
rel nut in the upper forward wing bolt position with a
high quality grease gun fitted with an Alemite 314150 b. Corrosion preventive compound on the upper and
nozzle. Sufficient corrosion preventive compound has lower forward wing bolts must be replenished annu-
been added when one of the following criteria has ally. Inject the corrosion preventive compound with a
been met: high quality grease gun equipped with an Alemite

57-00-00
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 'Reechcraft
KING AIR F90
MAINTENANCE MANUAL

314150 nozzle. A sufficient amount of corrosion pre- WING, BOLT, NUT AND SPAR FITTING
ventive has been added when one of the following cri- INSPECTION (Effectivity: All)
teria has been met:
1. The corrosion preventive compound emerges Refer to the BEECHCRAFT King Air F90 Structural
from between the two portions of the barrel nut Inspection and Repair Manual for inspection proce-
assembly. dures.
2. The corrosion preventive compound emerges
from around the threaded portion of the wing bolt. OUTBOARD WING SPAR CAP
3. The lubrication fitting on the barrel nut fails to INSPECTION (Effectivity: All)
accept additional compound after several actions of
Refer to the BEECHCRAFT King Air F90 Structural
the grease gun.
Inspection and Repair Manual for inspection proce-
c. Coat the exposed threads which protrude through dures.
the barrel nuts with corrosion preventive compound
(106, Chart 1, 91-00-00).

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 <aeechcraft
KING AIR F90
MAINTENANCE MANUAL
PLATES/SKIN - MAINTENANCE 9. Outboard wing fuel cell
PRACTICES (Effectivity: All) 10. Lower forward wing bolt (no cover)
1. Leading edge fuel cell outboard tank fuel 11. Fuel system plumbing
quantity transmitter unit 12. Aileron bellcrank and stops
2. Leading edge fuel cell inboard tank fuel quan- 13. Trim tab actuator
tity transmitter unit 14. Fuel filter
3. Upper forward wing bolt 15. Aileron pulley and fairlead
4. Remote compass (LH or RH) 16. Aileron pulley
5. Wing fuel cell fuel quantity transmitter unit 17. Outboard flap actuator
6. Wing plumbing 18. Fuel vent
7. Upper aft wing bolt 19. Lower aft wing bolt
8. Leading edge fuel cell and plumbing 20. Inboard wing fuel cell
14

LH UPPER RH UPPER

12 5 6 7 6 5 12
8 8 20 10 20 13 8 8 9 8

0
i --1
~~l
I i
~

RH LOWER LH LOWER

11 12 9 15 16 17 18 19 18 17 16 15 9 12 11 T90 12 1R

Wing Access Openings (Effectivity: All)

Figure 1

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 ~chcraft
KING AIR F90
MAINTENANCE MANUAL

2 12

4 18 17
4
3 15 15 11

~~9 ~~~
5

34 --34
9 10 B 6
6 8 7
20 16 16
20
21 21

32 3
3
22 15 15 22

23 23

24 24

26 T90-14-17
25 28

Wing Center Section Access Openings (Effectivity: All)

(Sheet 1 of 2)
Figure 2

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 '1?eechcraft
KING AIR F90
MAINTENANCE MANUAL

1. Nacelle fuel cell, plumbing and float gage 18. Electrical heat lockout relay, prop deice timer,
2. Fuel jet pump motive control valve LH bus tie relay, LH high current sensor, No. 1
Inverter feeder limiter, prop deice manual override
3. Wing rib access relay, prop deice fuse and panel relays
4. Wing ice light 19. Loadmeter, generator control, field sense cir-
5. Inverter, wing electrical connections and cir- cuit breakers, starter relays, tranzorbs, line contactor
cuit breakers relay, shunt and bus bars
6. Aileron and aileron tab cable 20. Fuel filter and drain valve
7. Fuel filter 21. Standby fuel boost pump, boost pump filter,
drains, nacelle fuel tank fuel quantity transmitter and
8. Inboard flap actuator
lower support
9. Fuel quantity transmltter unit
22. (Landing gear wheel wells) Fuel jet transfer
10. External flap switch pump, fuel check valves, engine fire extinguisher and
11. External power receptical, relay and fuel reverse current diodes
plumbing 23. Inverter vent
12. Start purge valve and fuel jet pump motive 24. Electrical wiring
control valve 25. Main landing gear suspension bolts
13. Fuel system firewall shutoff valve 26. Fuel line drain
14. Battery bus circuit breaker panel, vent blower, 27. Fuel line connectors
furnishings, avionics, windshield, inverter, subpanel,
28. Aileron cables
deice fuses and panel
29. Inboard flap actuators
15. Ble.ed air bypass valve, fuel crossfeed valve
(LH only) and external power terminal board 30. Center section fuel cell installation
31. Fuel strainer
16. Electrical wiring, hydraulic plumlbing, tran-
zorbs, engine control cables, pitot drain, boot deice 32. Landing gear retract universal bearing, bleed
relay, lip deice fuse and shunts air pressure valve and battery vent (RH only)
17. Battery, battery relay, external power relay, 33. Landing gear retact universal bearing and
current sensor, tranzorbs, fuel system start purge bleed air pressure valve
valve and firewall shutoff valve 34. Deicer plumbing line connectors

Wing Center Section Access Openings (Effectivity: All)

(Sheet 2 of 2)
Figure 2

57·30·00
Page 3
Dec 21/95
 'Reechcraft
KING AIR F90
MAINTENANCE MANUAL

3 4 6 5 4 2 5 4454544 5 2 4 5 6 4 3

10 9 12 1 5 2 2 4 8 2 8 4 2 2 5 12 6 9 10

UPPER

6 4 4 4 3 4 4 5 2 4 5 7 3 5 7 4 2 5 4 3 4 4 4 6

L ~
I
~ <,

10 9 11 12 11 11 3 2 2 2
-I
3 8 2 4 4 4 2 8 3 2 3 11
I
11 12 11 9 10

LOWER

F90-12- 17

Wing Skin Thickness (Effectivity: All)

(Sheet 1 of 2)
Figure 3

57-30-00
Page 4
Dec 21/95
 'Deechcrnft
KING AIR F90
MAINTENANCE MANUAL

NUMBER MATERIAL THICKNESS IN INCHES

1. 2024-T3 .016
2. 2024-T3 .020
3. 2024-T3 .025
4. 2024-T3 .032
5. 2024-T3 .040
6. 2024-T3 .090
7. 2024-T42 .064
8. 6061-T6 .020
9. 6061-T6 .025
10. 6061-T6 .032
11. 6061-T6 .250
12. AZ-31B-O .020
(Magnesium Alloy)

Wing Skin Thickness (Effectivity: All)

(Sheet 2 of 2)
Figure 3

57-30-00
Page 5
Dec 21/95
 '1?eechcraft
KING AIR F90
MAINTENANCE MANUAL

5 4 4 5

4 4---4
14 ~r----*---14

4 -+--4

~---I---I--------t-l+-----3
3

9 f[ l- _---i "]'---9

13 4 6 5 5 UPPER 5 5 3 6 4 13
3 3 12 4 6 1 1 6 4 12 3 3

~
I
IV -d-
L-------'v 1--------
.-------V
...------\-- r---..-
r-------. 1-
V
n
~
1--

~
3 6 3
6
I

r-~
4
I ( ) J
4
8
8
4 01
-
r 1 II I
IH
8
8
4

~
I~ w ~ ~ w 3
3
I'::::
3 3
11
4 ---r
1'--'

>- / ~ 1\ /
o . I
11

2 f--
~'--- ........ 'lr-

o cJiO 0 ,0 ),-6 0
. . . 11 4

2
f--

~If
1/
\11)]
10 9 4 2 7 7 7 7 7 3 7 LOWER 7 3 7 7 7 7 7 2 4 9 10
F90-14-18

Wing Center Section Skin Thickness (Effectivity: All)

(Sheet 1 of 2)
Figure 4

57-30-00
Page 6
Dec 21/95
 CQeechcraft
KING AIR F90
MAINTENANCE MANUAL

NUMBER MATERIAL THICKNESS IN INCHES

1. 2024-T3 .012
(Four layers of .012
material bonded together
with Epibond 104 adhesive)
2. 2024-T3 .020
3. 2024-T3 .025
4. 2024-T3 .032
5. 2024-T3 .040
6. 2024-T3 .050
7. 2024-T42 .063
(Bonded Honeycomb)
8. 2024-T42 .016
9. 2024-T42 .020
10. 2024-T42 .025
11. 2024-T42 .032
12. 2024-T42 .040
13. 6061-T62 .040
14. 6061-0 .032

Wing Center Section Skin Thickness (Effectivity: All)

(Sheet 2 of 2)
Figure 4

57-30-00
Page 7
Dec 21/95
 CQeechcraft
KING AIR F90
MAINTENANCE MANUAL
AILERON • MAINTENANCE PRACTICES BALANCING PROCEDURES (Effectivity:
(EFFECTIVITY:ALL) All)
BALANCING THE AILERON (Effectivity: All) EQUIPMENT REQUIRED TO PERFORM CHECK
(Figure 1 ) BALANCING BY FORCE MEASUREMENT
When the aileron control surface is being repainted, METHOD (Effectivity: All)
suspend it by the trailing edge so that excess paint will a. A stand with knife-edged supports. The knife
drain toward the leading edge. After any repainting or edges should be in the same horizontal plane. Refer
repair, the finished surface must be check balanced to to Figure 1.
ensure that its static moment about the hinge line is
b. A certified beam balance calibrated in units of .01
within the prescribed limits.
lb. or less. The balance should have a flat weighing
NOTE platform and its capacity should be equal tare plus 2.0
The finished aileron assembly, with lbs. minimum.
static discharge wicks (if required) c. A support spindle similar to the illustration and lev-
installed, must have a static overbalance eling blocks, as required (blocks + spindle =tare).
between 0.0 and 3.0 inch-pounds.
d. A straightedge, ruler and spirit level.
The static moment of the aileron is determined by mul-
tiplying the unbalanced weight of the aileron assembly FORCE MEASUREMENT METHOD (Effectivity:
times the perpendicular distance from the hinge cen- All)
ter line to the center of gravity when the chord line is
a. Locate the chord line at the inboard end of the
horizontally level. The weight is measured in pounds
surface by placing a straightedge at the inboard end
and the distance in inches. The static moment of a
so that one edge bisects the center of the hinge point
100 percent balanced control surface is 0.0 inch-
and the trailing edge.
pounds. A tail-heavy surface exhibits static underbal-
ance. A nose-heavy surface exhibits static overbal- b. Mark the chord line.
ance. c. Place a small platform scale under the trailing
edge if the aileron is nose-heavy.
CHECKING BALANCE (Effectivity: All)
d. Place the upper end of the spindle under the trail-
The aileron balance must be checked in a draft free ing edge of the tail-heavy surfaces or under the lead-
area with the aileron completely assembled in flying
ing edge of the nose-heavy surfaces. The spindle
condition. All painting, including stripes and touch-up, must be vertical throughout the balancing procedure.
must be completed. The tab, tab pushrod, static wicks
Hold a spirit level against the marked chord line and
and hinge bolts must be attached. The chord line must level it by extending or contracting the spindle, or by
be horizontally level and the hinge line must be prop- using blocks and shims under the spindle.
erly supported when the static moment is measured.
Although many different methods of check balancing e. Measure the perpendicular distance from the
exist, they can be categorized under the following two hinge center line to the point supported by the spindle.
headings: Ensure that the spirit level and rule are removed from
the surface and read the reaction on the beam bal-
a. Counterbalancing - The application of a known ance.
force or weight at a measured distance from the hinge
line to counter the unbalance moment of the aileron f. Calculate the static underbalance moment M from
assembly. the formula.
b. Actual Force Measurement - Measurement of the M = D (R-T) inch-pounds where,
force applied by the aileron surface on a single sup- D = Perpendicular distance from the hinge centerline
port at a known distance from the centerline of the to the spindle point (inches).
hinge.
NOTE R = Reaction (pounds) read from the beam balance.

Counterbalancing is the simplest method T = Tare, i.e. spindle plus leveling blocks or shims on
of check balancing. the scale platform (pounds).

57·50·00
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 ~echcraft
KING AIR F90
MAINTENANCE MANUAL
EXAMPLE e. Add small quantities of lead shot to the cup until
the aileron balances with the chord line level. Check
Dis 10.0 inches, R is 1.28 lb. and T = 1.13 lb. this by holding the spirit level aligned with the marked
M = 10.0 (1 .28 - 1.13); M = 1.50 inch-pounds. chord line.
M is within the prescribed range which is satisfactory.
If M is not within the prescribed range, refer to step i f. Carefully measure the perpendicular distance D
under BALANCING PROCEDURE COUNTERBAL- within 0.1 inch from the hinge line to the point of sus-
ANCING METHOD, this chapter. pension of the cup.

EQUIPMENT REQUIRED TO PERFORM CHECK g. Remove the cup, contents and string, then weigh
BALANCING BY COUNTERBALANCING METHOD them.
(Effectivity: All)
NOTE
a. A stand with knife-edge supports. The knife edges Since any weighing error is magnified by
must be in the same horizontal plane. Refer to Figure the distance D, weighing is most impor-
1. tant and must be done carefully on
b. A paper cup or similar lightweight container. scales that are certified for accuracy.
c. Approximately 3 pounds of lead shot. h. Calculate the static balance as follows:
d. A certified beam balance weighing device cali-
brated in units of .01 pound or less. 1. The weight of the cup and contents is desig-
nated by W.
e. A straightedge, rule and spirit level.
2. The over- or underbalance moment is desig-
COUNTERBALANCING METHOD (Effectivity: All)
nated by M.
a. Locate the chord line by placing a straightedge at
the inboard end of the aileron assembly so that one
3. M = Wx D.
end is on the trailing edge. Mark the chord line with a 4. The following is a typical example of a balanc-
suitable marker, such as a grease pencil, then remove ing calculation: Assume the aileron is overbalanced
the straightedge. (noseheavy) and the paper cup was suspended from
b. Secure the trim tab (LH only) in its neutral position the trailing edge. Assume that the aileron balances
with a small piece of masking tape. with the chord line level at W = .150 pound and D =
10.0 inches, then.
c. Fit the correct size bolts in the hinge brackets and
mount the aileron on the knife-edge supports. Ascer- M = .150 x 10.0.
tain that the aileron is free to rotate about the hinge M = 1.50 inch-pounds. The product of W x D.
line.
In this instance, M is within the required static balance
d. To determine if adjustment weights should be
range and is therefore acceptable.
added or removed, suspend a paper cup from a point
near the center of the aileron trailing edge. Use a k. If the static balance does not fall within the range
short length of small diameter string secured to the of 0.0 and 3.0 inch-pound overbalance, add or remove
surface with a small piece of masking tape The cup the lead washers as required to attain the desired bal-
must be free to hang vertically. Refer to Figure 1. ance.

57·50-00
Page 2
Dec 21/95
 Qeechcraft
KING AIR F90
MAINTENANCE MANUAL

r~-~
A
~CONTAINER
JIG MUST BE HORIZONTALLY LEVEL
COUNTERBALANCING METHOD

CONTAINER

POINTING HAND
DENOTES AREA
OF CHANGE.

c
S~
W

99-130000-151 LEAD WASHERS

AN366 Fl032 NUT PLATE
AN3 BOLT / JIG MUST BE HORIZONTALLY LEVEL
AN970-3 WASHER
ACTUAL FORCE MEASUREMENT METHOD

AJOO-4J-J
001

Aileron Balancing (Effectivity: All)

Figure 1

57-50-00
Page 3
Dec 21/95
LJ57B
144575AA.AI
LJ57B
144576AA.AI
LJ57B
144577AA.AI
 PIANO HINGE

HINGE PIN

CLAMP
TELESCOPING
TUBING

ATTACHING PIANO
HOOK HINGES
BUNGEE CORD
OR SPRING

RIVET GUN

LJ57B
144578AA.AI
LJ57B
144579AA.AI
LJ57B
144582AA.AI