Maintenance Manual
MODEL 510
COPYRIGHT © 2006
TEXTRON AVIATION INC.
WICHITA, KANSAS, USA
510MM14
30 AUGUST 2006
REVISION 14
1 APRIL 2019
Model 510 Maintenance Manual (Rev 14)
4-00-00-0 (Original Issue)
AIRWORTHINESS LIMITATIONS
1.
Scope
A.
B.
2.
This chapter gives the mandatory replacement times and inspection intervals for components and airplane structures. This
chapter also gives the required details to monitor them using scheduled inspections. This chapter applies to items such as
fatigue components and structures, which are a part of the certification procedures.
The Airworthiness Limitations section is FAA-approved. It gives inspections and maintenance procedures that Parts
43.16 and 91.409 of Title 14 of the Code of Federal Regulations require, unless the FAA approves an alternative program.
Definition
A.
This chapter has two sections:
(1) The Inspection Time Limits Section (4-10-00) records systems and components, that must be examined at specified
intervals. These intervals show the maximum time permitted between inspections.
(2) The Replacement Time Limits Section (4-11-00) records life-limited components, that are to be replaced at a
specified time.
Copyright © Textron Aviation Inc.
Retain printed data for historical reference only. For future maintenance, use only current data.
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Model 510 Maintenance Manual (Rev 14)
4-10-00-0 (Rev 4)
INSPECTION TIME LIMITS
1.
General
A.
2.
The inspection time intervals that apply to the systems and components that follow represent the maximum inspection
intervals. Detailed inspection and maintenance check procedures are described in the associated tasks elsewhere in this
manual.
Inspection Schedule
A.
Landing Gear (Chapter 32)
(1) Landing Gear System Uplock and Downlock Switches - Complete an operational check every 950 hours. Task 3200-00-710
NOTE:
This Certification Maintenance Requirement (CMR) inspection was derived from the Model 510
System Safety Assessment. This item is a one star CMR as defined in Advisory Circular (AC)
25-19. The tasks and intervals specified are mandatory and cannot be changed, escalated, or
deleted without the concurrence of the responsible Aircraft Certification Office (ACO).
(2) Landing Gear Control Solenoids, Relays, and Left and Right Main Landing Gear Regenerative Shuttle Valves Complete a functional test every 950 hours. Task 32-00-00-720
NOTE:
NOTE:
This functional test is to make sure that the solenoids, relays, and valves do not stay open or
closed all of the time.
This Certification Maintenance Requirement (CMR) inspection was derived from the Model 510
System Safety Assessment. This item is a one star CMR as defined in Advisory Circular (AC)
25-19. The tasks and intervals specified are mandatory and cannot be changed, escalated, or
deleted without the concurrence of the responsible Aircraft Certification Office (ACO).
(3) Emergency Brakes - Complete a functional check every 500 hours. Task 32-40-00-720
NOTE:
B.
This Certification Maintenance Requirement (CMR) inspection was derived from the Model 510
System Safety Assessment. This item is a one star CMR as defined in Advisory Circular (AC)
25-19. The tasks and intervals specified are mandatory and cannot be changed, escalated, or
deleted without the concurrence of the responsible Aircraft Certification Office (ACO).
Oxygen (Chapter 35)
(1) Oxygen Bottle and Pressure Gage - Complete a functional check every 1400 hours or 3 years, whichever comes first.
Task 35-10-00-720
NOTE:
This Certification Maintenance Requirement (CMR) inspection was derived from the Model 510
System Safety Assessment. This item is a one star CMR as defined in Advisory Circular (AC)
25-19. The tasks and intervals specified are mandatory and cannot be changed, escalated, or
deleted without the concurrence of the responsible Aircraft Certification Office (ACO).
(2) Passenger Oxygen System - Complete a functional check every 1400 hours or 3 years, whichever comes first. Task
35-20-00-720
NOTE:
C.
This Certification Maintenance Requirement (CMR) inspection was derived from the Model 510
System Safety Assessment. This item is a one star CMR as defined in Advisory Circular (AC)
25-19. The tasks and intervals specified are mandatory and cannot be changed, escalated, or
deleted without the concurrence of the responsible Aircraft Certification Office (ACO).
Fuselage (Part Number 7010000-1) (Chapter 53)
NOTE:
An initial inspection and subsequent recurring structural inspections of these items are necessary
to find fatigue cracks. The recurring inspection intervals do not begin until after the completion of
the initial inspection. Detailed inspection procedures and illustrations of specific inspection
locations will be found in the Model 510 Nondestructive Testing Manual as they become available.
Table 1 shows the required fuselage inspections and intervals.
Table 1. Fuselage Inspections
Location
Inspection Type
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Retain printed data for historical reference only. For future maintenance, use only current data.
Initial Inspection Interval
Recurring Inspection
Interval
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Model 510 Maintenance Manual (Rev 14)
4-10-00-0 (Rev 4)
D.
All Pressure Vessel Skins
Visual
and Splices
Task 51-10-10-211
Forward Pressure Bulkhead Surface Eddy Current
Task 53-00-00-250
5000 hours
2500 hours
12,000 hours
4000 hours
Windshield Lower Sill
Task 53-10-20-250
Windshield
Surface Eddy Current
8250 hours
3400 hours
Visual
12,000 hours
4000 hours
Cockpit Side Windows
Cabin Door Lintel
Task 53-20-10-252
Cabin Door Threshold
Task 53-20-10-251
Visual
Surface Eddy Current
12,000 hours
12,000 hours
4000 hours
3900 hours
Surface Eddy Current
12,000 hours
4000 hours
Cabin Door Frame
Task 53-20-10-250
Escape Hatch Opening
Task 53-20-20-250
Cabin Escape Hatch Skin
Task 52-20-00-250
Surface Eddy Current
10,600 hours
500 hours
Surface Eddy Current
10,400 hours
2500 hours
Surface Eddy Current
12,000 hours
4000 hours
Wing Attach Fittings and
Frames
(FS 260.80, FS 261.30, FS
309.85, and FS 310.35)
Task 57-00-00-250
Surface Eddy Current
12,000 hours
4000 hours
Cabin Windows
Aft Pressure Bulkhead
Task 53-00-00-251
Aft Tailcone Skin And
Splices
Visual
Surface Eddy Current
12,000 hours
12,000 hours
4000 hours
4000 hours
Visual
12,000 hours
4000 hours
Stabilizers (Vertical Stabilizer Part Number 7031000-1 and Horizontal Stabilizer Part Number 7032001-1) (Chapter 55)
NOTE:
An initial inspection and subsequent recurring structural inspections of these items are necessary
to find fatigue cracks. The recurring inspection intervals do not begin until after the completion of
the initial inspection. Detailed inspection procedures and illustrations of specific inspection
locations will be found in the Model 510 Nondestructive Testing Manual as they become available.
Table 2 shows the required stabilizer inspections and intervals.
Table 2. Stabilizer Inspections
Location
Inspection Type
Initial Inspection Interval
Recurring Inspection
Interval
Horizontal Stabilizer - Front
Spar Upper Flange and
Splice Straps
(BL 0.00 - BL 6.00)
Task 51-00-00-250
Surface Eddy Current
12,000 hours
4000 hours
Horizontal Stabilizer - Front Surface Eddy Current
Spar Upper Flange (BL 6.00
- HSS 120.67)
Task 51-00-00-250
12,000 hours
4000 hours
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Model 510 Maintenance Manual (Rev 14)
4-10-00-0 (Rev 4)
E.
Horizontal Stabilizer - Center Surface Eddy Current
Spar Upper Flange and
Splice Straps (BL 0.00 - BL
6.00)
Task 51-00-00-250
12,000 hours
4000 hours
Horizontal Stabilizer - Center Surface Eddy Current
Spar Upper Flange
(BL 6.00 - HSS 120.67)
Task 51-00-00-250
12,000 hours
4000 hours
Horizontal Stabilizer - Rear
Spar Upper Flange and
Splice Straps
(BL 0.00 - BL 6.00)
Task 51-00-00-250
Surface Eddy Current
12,000 hours
4000 hours
Horizontal Stabilizer - Rear Surface Eddy Current
Spar Upper Flange (BL 6.00
- HSS 120.67)
Task 51-00-00-250
12,000 hours
4000 hours
Horizontal Stabilizer - Front Bolt-Hole Eddy Current
Horizontal Tail Attach Fittings
Task 55-10-10-250
12,000 hours
4000 hours
Horizontal Stabilizer - Rear Bolt-Hole Eddy Current
Horizontal Tail Attach Fittings
Task 55-10-10-250
12,000 hours
4000 hours
Elevator Hinges
Task 27-00-00-210
12 months
Every 12 months
Vertical Stabilizer - Front
Surface Eddy Current
Spar Outer Flanges (Lower
Closeout Rib - VFS 135.02)
Task 51-00-00-250
12,000 hours
4000 hours
Vertical Stabilizer - Forward, Bolt-Hole Eddy Current
Center, and Rear Spar
Attachment Holes
Task 55-30-00-250
12,000 hours
4000 hours
Vertical Stabilizer - Rear
Spar Outer Flanges and
Sideplates
(VFS 140.69 - WL 179.30)
Task 51-00-00-250
12,000 hours
4000 hours
Vertical Stabilizer - Front
Bolt-Hole Eddy Current
Horizontal Tail Attach Fitting
Task 51-00-00-250
12,000 hours
4000 hours
Rear Spar Integral Horizontal Bolt-Hole Eddy Current
Tail Attach Lugs
Task 51-00-00-250
12,000 hours
4000 hours
Rudder Hinges
Task 27-00-00-210
12 months
Every 12 months
Visual
Surface Eddy Current
Visual
Wings (Part Number 7020005-1) (Chapter 57)
NOTE:
An initial inspection and subsequent recurring structural inspections of these items are necessary
to find fatigue cracks. The recurring inspection intervals do not begin until after the completion of
Copyright © Textron Aviation Inc.
Retain printed data for historical reference only. For future maintenance, use only current data.
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Model 510 Maintenance Manual (Rev 14)
4-10-00-0 (Rev 4)
the initial inspection. Detailed inspection procedures and illustrations of specific inspection
locations will be found in the Model 510 Nondestructive Testing Manual as they become available.
Table 3 shows the required wing inspections and intervals.
Table 3. Wing Inspections
F.
Location
Inspection Type
Initial Inspection Interval
Recurring Inspection
Interval
Wing Forward Spar
Fasteners
(LBL 14.00 to RBL 14.00)
Task 57-20-20-256
Surface Eddy Current
12,000 hours
4000 hours
Wing Forward Spar
Fasteners
Task 57-20-20-253
Surface Eddy Current
12,000 hours
4000 hours
Wing Main Spar Fasteners
(LBL 14.00 to RBL 14.00)
Task 57-20-20-255
Surface Eddy Current
12,000 hours
4000 hours
Wing Main Spar Fasteners
Task 57-20-20-251
Surface Eddy Current
12,000 hours
4000 hours
Wing Rear Spar Fasteners
(LBL 14.00 to RBL 14.00)
Task 57-20-20-254
Wing Rear Spar Fasteners
Task 57-20-20-250
Surface Eddy Current
12,000 hours
4000 hours
Surface Eddy Current
12,000 hours
4000 hours
Flap Hinge Fastener Holes
Task 57-20-20-252
Bolt-Hole Eddy Current
12,000 hours
4000 hours
Aileron Hinges
Task 27-00-00-210
Visual
12 Months
Every 12 months
Engine Support Structure (The items shown below are part of the Fuselage Structure Assembly, Part Number 7010000-1)
(Chapter 71)
NOTE:
An initial inspection and subsequent recurring structural inspections of these items are necessary
to find fatigue cracks. The recurring inspection intervals do not begin until after the completion of
the initial inspection. Detailed inspection procedures and illustrations of specific inspection
locations will be found in the Model 510 Nondestructive Testing Manual as they become available.
Table 4 shows the required engine support inspections and intervals.
Table 4. Engine Support Structure Inspections
Location
Inspection Type
Initial Inspection Interval
Recurring Inspection
Interval
Forward Engine Mount
Upper Arm Radius
Task 54-50-00-253
Surface Eddy Current
12,000 hours
4000 hours
Forward Engine Mount Lugs Bolt-Hole Eddy Current
Task 54-50-00-250
12,000 hours
4000 hours
Forward Engine Mount
Outboard Fire Shield
Task 54-50-00-254
Upper and Lower Fire
Shields
Task 54-50-00-252
Surface Eddy Current
12,000 hours
4000 hours
Surface Eddy Current
12,000 hours
4000 hours
Copyright © Textron Aviation Inc.
Retain printed data for historical reference only. For future maintenance, use only current data.
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Model 510 Maintenance Manual (Rev 14)
4-10-00-0 (Rev 4)
Forward Engine Mount-toEngine Beam Interface
Task 54-50-00-251
Surface Eddy Current
12,000 hours
4000 hours
Forward Engine Beam
Upper Cap
(BL 24.86 - Outboard End)
Task 51-00-00-250
Surface Eddy Current
12,000 hours
4000 hours
Forward Engine Beam to
Tailcone Frame Interfaces
(TCS 132.25 and TCS
135.25)
Task 51-00-00-250
Surface Eddy Current
12,000 hours
4000 hours
Aft Engine Mount Tees
Task 51-00-00-250
Surface Eddy Current
12,000 hours
4000 hours
Aft Engine Mount to Aft
Engine Beam Interfaces
Task 51-00-00-250
Surface Eddy Current
12,000 hours
4000 hours
Aft Engine Beam to Pylon
Upper Interfaces
Task 51-00-00-250
Surface Eddy Current
12,000 hours
4000 hours
Aft Engine Beam Upper Cap Surface Eddy Current
(BL 23.72 - Outboard End)
Task 51-00-00-250
12,000 hours
4000 hours
Aft Engine Beam and
Tailcone Frame Interfaces
(TCS 150.35 and TCS
152.35)
Task 51-00-00-250
12,000 hours
4000 hours
4000 hours
4000 hours
Surface Eddy Current
Aft Engine Isolator Inspection Detailed Dimensional
Task 71-20-00-220
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Model 510 Maintenance Manual (Rev 14)
4-11-00-0 (Rev 4)
REPLACEMENT TIME LIMITS
1.
General
A.
2.
You must replace the life-limited components that follow at the specified time. It is recommended that you schedule the
components for replacement during the airplane's inspection interval that aligns with or occurs just before the specified
time limit expires. Procedures to replace the components are given in the applicable chapters in this maintenance manual.
Replacement Schedule
A.
Landing Gear (Chapter 32)
(1) Main Landing Gear (Refer to Table 1.)
NOTE:
Replace the related hardware (bolts, bearings, bushings, and axle components) that is used to
install the specified component when it is replaced. Refer to Chapter 32 for more information.
Table 1. Main Landing Gear Replacement Intervals
Part Name
Part Number
Replacement Interval
Left Main Landing Gear Trunnion
Assembly
Right Main Landing Gear Trunnion
Assembly
Left Trailing Link Assembly
Right Trailing Link Assembly
Main Landing Gear Oleo Assembly
Left Main Landing Gear Hydraulic
Actuator
Right Main Landing Gear Hydraulic
Actuator
7041020-3, -5, -7
Replace every 20,000 landings
7041020-4, -6, -8
Replace every 20,000 landings
7041030-1, -3, -5
7041030-2, -4, -6
7041050-2, -3, -4, -5
Replace every 20,000 landings
Replace every 20,000 landings
Replace every 12,000 landings
9912653-5
Replace every 12,000 landings
9912653-6
Replace every 12,000 landings
(2) Nose Landing Gear (Refer to Table 2.)
NOTE:
Replace the related hardware (bolts, bearings, bushings, and axle components) that is used to
install the specified component when it is replaced. Refer to Chapter 32 for more information.
Table 2. Nose Landing Gear Replacement Intervals
B.
Part Name
Part Number
Replacement Interval
Nose Landing Gear Strut Assembly
Nose Landing Gear Drag Brace
Assembly (Except Nose Landing
Gear Downlock Release Actuator)
7042010-4, -6, -8, DDA-04965-1
7042120-1, -5, DDA-05645-1
Replace every 20,000 landings
Replace every 20,000 landings
Nose Landing Gear Downlock
Release Actuator
Nose Landing Gear Actuator
9912655-1
Replace every 12,000 landings
9912654-2
Replace every 12,000 landings
Fuselage (Chapter 53)
(1) Nose Landing Gear Attach Fitting Assemblies (Refer to Table 3.)
NOTE:
Replace the related hardware (bolts, bearings, bushings, and axle components) that is used to
install the specified component when it is replaced. Refer to Chapter 32 for more information.
Table 3. Nose Landing Gear Attach Fitting Assembly Intervals
Part Name
Part Number
Replacement Interval
Left Nose Landing Gear Attach
Fitting Assembly
Right Nose Landing Gear Attach
Fitting Assembly
7013022-3, -15, DDA-05646-3
Replace every 20,000 landings
7013022-4, -16, DDA-05646-4
Replace every 20,000 landings
Copyright © Textron Aviation Inc.
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Model 510 Maintenance Manual (Rev 14)
4-11-00-0 (Rev 4)
Left Drag Brace Fitting Assembly
Right Drag Brace Fitting Assembly
C.
7013022-11, -17, DDA-05646-1
7013022-10, -18, DDA-05646-2
Replace every 20,000 landings
Replace every 20,000 landings
Wings (Chapter 57)
(1) Main Landing Gear Attach Fitting Assemblies (Refer to Table 4.)
NOTE:
Replace the related hardware (bolts, bearings, bushings, and axle components) that is used to
install the specified component when it is replaced. Refer to Chapter 32 for more information.
Table 4. Main Landing Gear Attach Fitting Assembly Intervals
Part Name
Part Number
Replacement Interval
Left Aft Trunnion Fitting Assembly
Right Aft Trunnion Fitting Assembly
Left Forward Trunnion Fitting
Assembly
Right Forward Trunnion Fitting
Assembly
7041165-1, -5
7041165-2, -6
7041155-5, -9
Replace every 20,000 landings
Replace every 20,000 landings
Replace every 20,000 landings
7041155-6, -10
Replace every 20,000 landings
Left Main Landing Gear Side Brace 7041175-5
Fitting Assembly
Right Main Landing Gear Side Brace 7041175-6
Fitting Assembly
D.
Replace every 20,000 landings
Replace every 20,000 landings
Powerplant (Chapter 71)
(1) Engine Isolator Assemblies (Refer to Table 5.)
NOTE:
NOTE:
This interval is to be completed when the engine is removed for overhaul. Refer to Task 71-2000-960.
The LM-471-SA11 isolator is included in the LM-471-SA12 isolator kit.
Table 5. Engine Isolator Assembly Intervals
Part Name
Part Number
Replacement Interval
Forward Engine Isolator Assembly
LM-471-SA12 (9912647-1)
Replace every 4000 hours
Aft Engine Isolator Assembly
LM-471-SA4 (9912647-3)
The equivalent Cessna part number is shown in brackets.
Copyright © Textron Aviation Inc.
Retain printed data for historical reference only. For future maintenance, use only current data.
Replace every 8000 hours
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