Structural Repair Manual

STRUCTURAL
INSPECTION AND
REPAIR MANUAL SUPER KING AIR® 350 (B300 SERIES)
SUPER KING AIR® 300
SUPER KING AIR® 200 SERIES
KING AIR® 100 SERIES
99 AIRLINER SERIES
KING AIR® 90 SERIES
KING AIR® F90 SERIES
QUEEN AIR® 88
QUEEN AIR® 65, 70, 80 SERIES
TWIN BONANZA® 50 SERIES

FAA APPROVAL HAS BEEN OBTAINED ON TECHNICAL DATA IN THIS PUBLICATION THAT AFFECTS AIRPLANE TYPE DESIGN.

COPYRIGHT © 2018
TEXTRON AVIATION INC.
WICHITA, KANSAS, USA 1 NOVEMBER 2018
98-39006D4 REVISION D4 1 APRIL 2023
 Structural Inspection and Repair Manual (Rev D4)
57-13-03 (Rev D1)

CRACK INSPECTION - WING STRUCTURE

(LJ-1085, LJ-1088 AND AFTER)
1. Crack Inspection
King Air 90 Serials LJ-1085, LJ-1088 and After are equipped with the three-element main spar, the three-element main spar may be
identified by the clevis fittings at the lower forward wing attach points. At the intervals designated in Table 201, the wing attach
fittings, center section and outboard wing spar caps, and the nacelle splice plates must be inspected for cracks, corrosion and
damage (Refer to Figure 208).
NOTE: This section is only applicable to airplanes that do not have winglets. For airplanes with winglets installed,
comply with all inspections in the applicable Instruction for Continued Airworthiness (ICA) documents. Then
comply with ANY index numbers in Table 201 that are not called out in the ICA documents.
Table 201. Standard Flight Profile
Recurring Component
Inspection Possible Initial
Index No. Figure No. Inspection Area Inspection Replacement
Method Findings Inspection
Interval Schedule
1. 201 Flat surfaces, Magnified Cracks, 5 yrs 5 yrs None
depressions and visual and Eddy corrosion and
counterbores of the current as mechanical
upper forward, specified damage
upper and lower aft
wing attach fittings
2. 202 Upper and lower Visual Cracks and 5 yrs 1 yr None
outboard wing corrosion
panel main spar
3. 204 Lower forward Visual Cracks, 5 yrs 5 yrs None
shear (clevis) fitting corrosion and
NOTE 1 bore damage
4. 205 Wing bolts and nuts Magnified Cracks and 5 yrs 5 yrs Refer to Chapter
206 - upper forward, visual and mechanical 4 of the 90
207 upper and lower aft fluorescent damage Series
liquid penetrant Airworthiness
Limitations
Manual (90-
590024-187)
5. 204 Lower forward wing Refer to Chapter
attach bolts and 4 of the 90
nuts Series
Airworthiness
Limitations
Manual (90-
590024-187)
6. Nacelle splice Visual Cracks 10,000 hrs 1000 hrs Refer to Chapter
plates Ref. 57-13- 4 of the 90
04 Series
Airworthiness
Limitations
Manual (90-
590024-187)
NOTE 1:
When inspecting the wing fitting pay close attention to the "POSSIBLE CRACK AREA" noted in Detail A of Figure 201.
2. Wing Attach Fitting
A. Inspection

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(1) Remove the wing bolt covers and any placards that are affixed to the wing attach fittings. With the wing bolts in place and
properly torqued, clean the inspection area. Eddy current inspect the exposed flat surface of all 16 fittings (Ref. Figure
201).
(a) Perform CALIBRATION (STANDARDIZATION) procedure (Ref. Chapter 20-00-00).
(b) Perform SURFACE INSPECTION WING SPAR FITTING procedure (Ref. Chapter 20-00-00).
(c) Perform INDICATION EVALUATION FOR SURFACE INSPECTION procedure (Ref. Chapter 20-00-00).
(2) In compliance with the inspection schedule (Table 201), remove and inspect the wing bolts one at a time as instructed
under the heading WING BOLT, NUT AND SPAR FITTING INSPECTION (LJ-1085, LJ-1088 and After).
(3) Eddy current inspect the bathtub area of the fittings, to include the counterbore face (washer face areas) and the
counterbore radius of all 16 wing attach fittings. Focus extra attention on the counterbore radius and the feathered edges
(Ref. Chapter 20-00-00, Figure 210, Figure 211 and Figure 212).
(a) Perform CALIBRATION (STANDARDIZATION) procedure (Ref. Chapter 20-00-00).
(b) Perform SURFACE INSPECTION WING SPAR FITTING procedure (Ref. Chapter 20-00-00).
(c) Perform INDICATION EVALUATION FOR SURFACE INSPECTION procedure (Ref. Chapter 20-00-00).
(4) It is possible that small cracks may be removed from the feathered edge of the counterbore and from the back of the tub of
the upper forward and upper and lower aft fittings and from the slot in the center section fittings. However, Textron Aviation
Support should be contacted prior to initiation of any crack removal procedure.
(5) Any fitting cracked beyond acceptable limits, as determined by Textron Aviation Technical Support, must be replaced.
(6) Replace all placards which were removed after the WING FITTING INSPECTION and WING BOLT, NUT AND SPAR
FITTING INSPECTION is completed.
(7) Ensure that the drain holes in the upper wing attach fittings are unobstructed.
3. Outboard Wing - Main Spar Crack and Corrosion
A. Inspection
The outboard wing main spar caps must be inspected for corrosion after the first five years of operation and annually thereafter.
WARNING: The entire upper and lower spar cap from the wing attach fitting to the wing tip must be inspected.
NOTE: Special emphasis should be placed on airplanes that have been operated and/or stored for extended
periods in areas where the geographical location and atmospheric conditions are conductive to
corrosion.
Inspection of the upper and lower spar caps must be performed as described in the following Steps:
(1) Visually inspect the exterior surfaces of the upper and lower spar caps for any buildup of the whitish, salt-like nonmetallic
substance indicative of corrosion. If any buildup of this substance is detected, the area should receive extra attention. Wax
or paint that may be trapped between the edge of the skin and the exposed portion of the spar cap should not be
interpreted as corrosion.
(2) Utilizing normal cleaning procedures, wash all exposed surfaces of the upper and lower spar caps.
(3) Visually inspect all exposed surfaces of the spar caps for paint blisters, raised areas and/or surface distortions and cracks
in the metal. The exposed surface of the spar cap is extruded flat. Any of the previously noted irregularities could indicate
corrosion and must be considered suspect (Ref. Figure 202).
NOTE: Spar cap surface irregularities may be detected by sliding the fingers over the surface, by moving a
straightedge over the surface or by sighting down the length of the spar cap.
If replacement of the wing panel main spar becomes necessary, refer to the King Air 90 Series Parts Catalog for component
part numbers.
If unusual conditions are noted which cannot be resolved locally, contact Textron Aviation support for consultation.
4. Wing Bolt, Nut and Spar Fitting Inspection (LJ-1085, LJ-1088 and After)
WARNING: All eight wing attach bolts and nuts must be removed and each of the wing attach fittings inspected. The
wing bolts and nuts are life limited parts and must be replaced with new components in compliance with the
time limits designated In Table 201. Render unserviceable all components removed in compliance with their
life limitation. ew wing attach components must be obtained only from Textron Aviation or a Textron Aviation
approved supplier.
CAUTION: As the lower forward wing attach bolt is being driven from the fittings, periodically check the bolt head side

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 Structural Inspection and Repair Manual (Rev D4)
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of the fittings to ensure that the bushings in the bolt bore are not being driven out with the bolt.
Before removing any wing attach bolt, support the wing with a wing stand and draw a line across each pair of wing fittings with a
grease pencil to aid wing alignment, if required.
CAUTION: Do not scribe or scratch the fittings.
If (while applying hand pressure only on the upper forward, upper and lower aft wing attach bolts) wing attach bolt binding occurs
upon disengagement or installation, support the outboard wing panel, loosen the upper forward, upper and lower aft wing attach bolts
and position the wing in a manner that releases binding of the bolt. Even though the lower forward wing bolts must be driven from the
fittings with a pin, excessive force should not be used to remove this bolt. When upper wing attach fittings are separated or shifted,
the aluminum washers between these fittings must be replaced with new washers. New aluminum washers should not be required if
wing attach bolts can be removed one at a time.
NOTE: Ensure that the 101-100011-1 washer shown in Figure 205, and the 90-110032-1 washers shown in Figures
206, and 207 have a full complete radius with no sharp edges which could mark the spar fittings. Replace
any washers which exhibit an incomplete radius or sharp edges.
Replace all placards which were removed after the WING FITTING INSPECTION and WING BOLT, NUT AND SPAR FITTING
INSPECTION is completed.
A. Lower Forward Wing Bolt, Nut and Fitting Inspection
NOTE: The lower forward wing bolts must be removed and the fittings inspected every five years. The bolts,
nuts and washers at this location are not reusable. These parts must be replaced with new components
any time the bolt is removed for any reason regardless of time in service.
(1) Cut the safety wire from the bolt head and nut.
(2) Remove the retaining bolts and clips at the head of the bolt and at the nut.
(3) Hold the bolt head immobile and remove the nut.
CAUTION: Exercise extreme care when driving the bolt and aligning pin out of the fittings. As the bolt is being
driven out of the fittings, ensure that the bushings in the bolt bore are not being driven out with the
bolt. Use only the Textron Aviation approved aligning pin for this procedure. The aligning pin (P/N
10996) may be ordered from Textron Aviation or a Textron Aviation approved outlet.
(4) Carefully drive the bolt out of the fitting with the aligning pin and a rawhide mallet. When the bolt has been removed, drive
the aligning pin out of the fittings with a flat-end smaller diameter pin.
(5) Discard the bolt, washers and nut.
(6) Clean the fittings and bolt bore with solvent (2 or 3, Table 208, 91-00-00).
NOTE: Use a 10-power or stronger magnifying instrument for the visual inspections of the fitting surfaces
and bolt bore.
(7) Inspect all visible surfaces of the fitting and the bolt bore for cracks, corrosion and mechanical damage. If corrosion, crack
indications, or mechanical damage are found in these areas, contact Textron Aviation Technical Support for consultation.
(8) Coat the exposed aluminum surfaces of the fitting with chemical conversion coating (2, 3, 4, 5, 6, Table 203, 91-00-00).
Allow the coating to dwell for approximately five minutes then rinse the coated surfaces with water and blow dry. Do not
wipe the treated surfaces. Paint the treated areas with primer (7, Table 206, 91-00-00) and allow sufficient time for drying.
(9) Coat the spar bushing bores, bolt, nut, metal washers, and the aligning pin with corrosion preventive compound (12, Table
203, 91-00-00).
(10) Install a new bolt, washers and nut. Torque the nut, install the safety wire and clips (Ref. Figure 204).
B. Upper Forward, Upper And Lower Aft Wing Bolt, Nut and Fitting Inspection
(1) Ensure that the wing is properly supported for maintenance. Remove only one wing bolt at a time. Perform the inspection
as detailed in this section, then replace and torque the bolt to the value specified in the appropriate illustration before
removing another bolt.
(2) Eddy current inspect the exposed spar fittings, focusing extra attention at the washer-seat and bolt-bore area. If scoring,
corrosion pitting, crack indications, or washer impressions are found in these areas, contact Textron Aviation Technical
Support for consultation.
(a) Perform CALIBRATION (STANDARDIZATION) procedure (Ref. Chapter 20-00-00).
(b) Perform SURFACE INSPECTION WING SPAR FITTINGS procedure (Ref. Chapter 20-00-00).
(c) Perform INDICATION EVALUATION FOR SURFACE INSPECTION procedure (Ref. Chapter 20-00-00).

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NOTE: The barrel nut must be disassembled for proper inspection. This may be accomplished by
moving one of the roll pins flush with the inside cradle surface and removing the nut (Ref.
Figure 203).
(3) If the bolts and nuts do not exceed their life limit, thoroughly clean the bolt, nut and washers with solvent (2 or 3, Table 208,
91-00-00) and inspect for cracks and mechanical damage with a 10-power or stronger magnifying glass. Scratches and
markings in the cadmium plating, and/or localized deterioration of the cadmium plating is not reason to reject a bolt. The
cadmium plating may be discolored and may have areas exhibiting a rubbed or polished appearance, usually resulting
from the installation procedure. If any mechanical damage or cracks are noted in any of the components, replace the
affected component. If the components are acceptable after the visual inspection, perform a fluorescent liquid penetrant
inspection on each of the bolts and nuts (Ref. Chapter 20-00-00). If the bolts and nuts are free of cracks and mechanical
damage, they may be reused after cleaning.
(4) Assemble the barrel nut (Ref. Figure 203).
(5) Coat the spar fittings, bolt bore and washer nut bearing face, the complete bolt, washers, and nut or barrel nut with
corrosion preventive compound (12, Table 203, 91-00-00).
CAUTION: Ensure that the wing bolt wrench does not bottom out against the wing fitting. Contact with the
fitting could result in erroneous torque readings and fitting damage.
NOTE: When installing the barrel nuts in the upper forward wing fittings, install them in a manner which
ensures that the lubrication fittings are accessible.
(6) Install the wing attach bolt, washers and nut and torque the nut (bolt at the upper forward attach point) to the torque value
specified in the applicable illustration (Ref. Figures 205, 206, or 207). After the nut (bolt at the upper forward attach point)
is properly torqued, coat the exposed threads of the wing bolt with corrosion preventive compound (12, Table 203, 91-00-
00). Inject corrosion preventive compound (12, Table 203, 91-00-00) into the barrel nut lubrication fittings with a good
quality grease gun and an Alemite nozzle (P/N 314150). Inject the compound until one of the following conditions are noted:
• The compound emerges from between the two portions of the nut assembly.
• The compound emerges beyond the locking portion of the nut.
• The fitting will accept no further compound after several pumps of the gun.
WARNING: Prior to installing the wing attach fitting covers, ensure that the drain holes in the upper
forward and aft fittings are free of obstructions and can drain freely.
5. Wing Bolt Maintenance
a. At the first scheduled airplane inspection as designated by the King Air 90 Series Maintenance Manual, after the bolts have
been loosened and retorqued or after initial installation, check the upper forward, upper and lower aft wing bolts for proper
torque as stated in the illustration for the specific location (Ref. Figure 205, Figure 206 and Figure 207).
b. Concurrent with Step a. and annually thereafter, coat the exposed bolt threads which protrude through the nuts with corrosion
preventive compound (12, Table 203, 91-00-00). At the upper forward attach nuts, inject corrosion preventive compound (12,
Table 203, 91-00-00) into the barrel nut assemblies until one of the following conditions are noted:
• The compound emerges from between the two portions of the nut assembly.
• The compound emerges past the locking portion of the nut.
• The fitting will accept no additional compound after several pumps of the gun.
WARNING: Prior to installing the wing attach fitting covers, ensure that the drain holes in the upper forward and
aft fittings are free of obstructions and can drain freely.
Table 202. Wing Bolt Tools
Position Bolt Part Number Wrench Part Number Nut Part Number Nut Torque Adapter
Lower Forward 130909B175 1 1/4-inch Box-End 130909N46 11001
Wrench
Upper Forward VCC0025 or 81784-12- T1176-6 80691CF-1216 or None
32 SL4092-12 (Barrel Nut)
Upper and Lower Aft 81786-10-18 or TS1222-5, 50-590012 or 81791-1018 TS1176-1 or TS1171-1
VCN0014 a 9/16-inch Hex Head
Wrench

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 Structural Inspection and Repair Manual (Rev D4)
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Figure 201 : Sheet 1 : Wing Attach Fitting Inspection

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 Structural Inspection and Repair Manual (Rev D4)
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Figure 201 : Sheet 2 : Wing Attach Fitting Inspection

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 Structural Inspection and Repair Manual (Rev D4)
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Figure 202 : Sheet 1 : Spar Cap Corrosion and Crack Inspection

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Figure 203 : Sheet 1 : Barrel Nut Assembly

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 Structural Inspection and Repair Manual (Rev D4)
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Figure 204 : Sheet 1 : Lower Forward Wing Bolt Installation (LJ-1085, LJ-1088 and After)

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Figure 205 : Sheet 1 : Upper Forward Wing Bolt Installation

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 Structural Inspection and Repair Manual (Rev D4)
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Figure 206 : Sheet 1 : Upper Aft Wing Bolt Installation

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Figure 207 : Sheet 1 : Lower Aft Wing Bolt Installation

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Figure 208 : Sheet 1 : Wing Attach Fittings

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57-13-03 (Rev D1)

Figure 208 : Sheet 2 : Wing Attach Fittings

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 Structural Inspection and Repair Manual (Rev D4)
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Figure 210 : Sheet 1 : Inspection Areas Bathtub Fittings

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 Structural Inspection and Repair Manual (Rev D4)
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Figure 211 : Sheet 1 : Inspection Areas Counterbore Radius

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Figure 212 : Sheet 1 : Lower Forward Fitting Inspection

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